CALIFORNIA STATE UNIVERSITY, NORTHRIDGE
AN/DKT -47 (XMG-1)
!\
TELEMETRIC DATA
TRANSMITTING SET
A project submitted in partial satisfaction of the
requirements for the degree of Master of Science in
Engineering
by
David Ernest .,.,.-."'Bovey
-/
January, 1977
The project of David Ernest Bovey is approved:
California State University, Northridge
May, 1976
ii
NOTE
This thesis contains proprietary data of the United States Navy.
The data contained in this document is for informational use only
and is not intended for manufacturing.
All work done on this project
was done by this author or under his direct technical direction.
iii
ABSTRACT
AN/DKT-47
TELEMETRIC DATA
TRANSMITTING SET
by
David Ernest Bovey
Master of Science in Engineering
May 1976
This project describes the design and development of the AN/DKT-47
telemetry system for the SPARROW III AIM-7F missile.
The DKT-47 is an
S-band PAM/FM/FM telemetry designed to telemeter missile flight data
during Fleet training missions.
The system was intended to provide low cost reliable telemetry for
Fleet organizations.
This was accomplished by using in-house designed
microcircuits and a printed flexible wiring harness to minimize labor
costs.
iv
TABLE OF CONTENTS
CHAPTER
Page
1
INTRODUCTION
1
2
PROBLEM FORMULATION
4
3
DESIGN
8
4
EVALUATION
22
General Specification
39
Data Functions Available
42
Data Functions for AN/DKT-47
48
APPENDICES
I
II
III
IV
v
RF Carrier Deviations of Subcarrier Oscillators in
FM/FM Telemetry Systems
51
Development Specification for AN/OKT-47
54
v
Chapter 1
INTRODUCTION
The primary purpose of an organization such as the Pacific Missile
Test Center (PACMISTESTCEN) is the evaluation of Navy weapon systems.
This evaluation takes place in several steps.
A missile is subjected to
incoming inspections and tests to verify that it was received from the
contractor in good condition.
The missile is then subjected to a series
of environmental tests to insure that its performance will not degrade
over the anticipated operational environment.
The first true operation-
al testing takes place when the missile is carried by a potential launching aircraft for a series of captive flights.
These flights may extend
beyond 100 flight-hours and usually include many catapult takeoffs and
arrested landings to test the susceptibility of the missile to shock and
vibration.
The last and most spectacular phase of the evaluation is the launching of the missile at a simulated target.
As the target is launched,
land based radars begin tracking the target, the launch aircraft, the
missile, and the photo chase planes.
Controllers, watching radar plot-
ting boards, instruct each participant on the proper flight pattern to
achieve the correct parameters for the test. Surveillance radars and
range aircraft watch the launch area for unauthorized vessels in the
hazardous splash area.
As the missile is launched, engineers frantically try to assess inflight missile performance.
But even more important than a successful
missile flight is successful telemetry system operation.
1
2
Without reliable telemetry, there is no way to assess missile in-flight
performance.
With the cost of manpower and equipment operation ap-
proaching $500,000 for a typical operations, the telemetry system simply
must work even if the missile does not.
Thus, a fundamental requirement for any missile telemetry system is
reliability and not necessarily cost.
telemetry system (AN/DKT-37) is $8500.
The cost of the present AIM-7F
When comparing this to the
overall cost of a mission, very little can be gained or lost by decreasing or increasing the cost of the missile telemetry system. This makes
reliability the key to a good telemetry system.
The AN/DKT-47(XMG-1) Telemetric Data Transmitting Set is a telemetry system intended for use during Fleet training exercises with the
SPARROW III AIM-7F air-to-air missile.
The purpose of this graduate
project was to develop, test, evaluate, and document the DKT-47 and then
make recommendations to the Naval Air Systems Command (NAVAIR) for
future procurement of this system.
This project took place in four distinct steps:
1.
Problem Formulation
2.
Design
3.
Evaluation
4.
Conclusions and Recommendations
First, the Fleet data requirements were combined with other constraints such as cost, size, capabilities of available receiving stations
as well as others.
The complete problem formulation process also in-
volved addressing other possible alternatives to the system developed
during this project.
3
Second, the system concept was developed once the general Fleet
requirements were established.
A system specification was developed as
well as specifications for individual components.
All modules were
designed or purchased depending on the complexity and in-house capabilities.
Third, the evaluation process began as each module or component
was built.
A theoretical analysis of each
the limits of performance characteristics.
modul~was
done to determine
Those limits were extrap-
olated to the system level for use during environmental tests and final
system tests.
Fourth, the adequacy of the system to meet Fleet requirements was
based on the results of all tests and conclusions were forwarded to
NAVAIR.
Chapter 2
PROBLEM FORMULATION
Before any design work could be started, the requirements for the
DKT-47 had to be firmly established.
By AIRTASK-5105/054-D/6WAA51-000,
NAVAIR requested the PACMISTESTCEN to develop a Fleet training telemetry
system for the AIM-7F missile.
The exact requirements and system design
were to be determined by the Project Engineer.
The first step in the design of a telemetry system is to establish
the data requirements.
This in turn leads to the system design which
establishes how the data will be telemetered.
For the DKT-47, the data
requirements were established by a survey of Fleet representatives,
missile engineers at Pt. Mugu and the Naval Weapons Center, China Lake,
and other potential users in the Navy and Air Force.
A list of data
functions available for the AIM-7F missile given by Appendix I was sent
out and each representative was asked to pick those data functions
necessary for evaluating the success of a missile flight in a training
environment.
These representatives were to consider three basic
questions when making their choices:
1.
Was the missile launched properly?
2.
Did the missile guide properly?
3.
Did the missile fuze properly?
As a result of this survey, the data functions listed in Appendix
II were chosen for the DKT-47.
In general, the survey indicated that
potential users wanted as much data as possible.
But at the same time,
information from a particular data channel that could be inferred from
other channels would not be telemetered.
4
This was in keeping
5
with an original premise that a Fleet training telemetry system would be
used for a gross evaluation of the complete weapon system.
This evalua-
tion is unlike the Research, Development, Test, and Evaluation (RDT&E)
situation in which as much detail on missile performance as possible is
required not only to assess the exact nature of an unsuccessful missile
but also to suggest possible corrective actions for the problem areas.
The gross evaluation required by the Fleet is used to determine what
happened during a missile flight only in generalities and not necessarily why something happened.
The RDT&E organization is concerned not
only with what happened but also with why it happened.
Therein lie the
differences between the gross evaluation and the RDT&E evaluation.
Even though a Fleet training telemetry system was intended for a
gross evaluation of missile performance, missile analysts expressed
concern that the evaluation could become too broad and essentially
worthless.
The AIM-7F missile has exhibited certain failures which have
never been thoroughly understood or explained.
Should these same fail-
ures occur on a training mission, little can be done to explain the
cause of the failures unless the required data channels are telemetered.
The choice of data functions represents an attempt to anticipate
potential problem areas that will require solutions.
For example,
kinematic data is telemetered to trace the flight path of the missile. A
miss-distance of two feet at intercept does not necessarily imply that
the missile flight was proper.
The missile flight may have been wild
and rough with large oscillatory body accelerations and the missile just
accidentally intercepted the target.
Only with proper data selection
can problem areas be located and later corrected.
Historical data on
6
the AIM-7F is not as great as has been the case with other missile
systems.
The DKT-47 will provide this information during Fleet training
missions.
A detailed breakdown of the data functions for the DKT-47 and
the reasons why they were chosen is given in Appendix III.
After the data functions were chosen for the DKT-47, the various
constraints on the system had to be considered.
The fact that the DKT-47
was to be a Fleet training system was probably the biggest underlying
constraint.
A Fleet system is subjected to more abuse and mishandling
than a system that might be used a PACMISTESTCEN.
The telemetry system
is dropped, banged, and bounced around aboard an aircraft carrier as the
missile is loaded and unloaded from each aircraft.
The personnel in-
volved are not trained in the field of telemetry and usually do not have
any field test equipment for the telemetry system.
The first chance to
determine if the telemetry is functioning is when the aircraft is on a
live firing run against a target and the telemetry is turned on.
This
points out a very basic constraint that was implied earlier in this
paper. In spite of all the mishandling and lack of adequate testing
aboard the carrier, the telemetry system must be reliable.
It must be
capable of operation without attention or adjustment by qualified telemetry personnel.
The cost of the telemetry system commands undue attention.
But,
as was discussed in Chapter 1, the telemetry system contributes only a
small fraction of the cost of firing a missile.
The present DKT-37
costs about $6000 per unit and has been a reliable unit.
The antici-
pated reliability of the DKT-47 is higher than that of the DKT-37 due
primarily to a simpler construction.
The DKT-47 must be cheaper than
the DKT-37 since it provides less data.
The Navy would not pay for
7
for increased reliability at the expense of less data since the reliability of the DKT-37 is adequate.
Thus, reduced cost will be an
outcome of the design of the DKT-47.
Preliminary cost estimates devel-
oped a target production cost of under $3000 per unit for the DKT-47.
The cost will be held down by the extensive use of microcircuits and a
flexible wiring harness which reduces assembly and test time.
The problem of where to locate the telemetry system has been
researched in detail during the design of the DKT-37.
instrumental in that design.
This author was
It has been historically customary for
SPARROW telemetry systems to replace the warhead section primarily
because there is no other space available in the missile.
A second and
more economically based reason is that targets are just too expensive to
destroy needlessly. Data obtained from the telemetry system can be used
to extrapolate damage inflicted on the target without using a warhead.
Without a warhead, there is an empty 18 inch long 8 inch diameter tube
into which the telemetry system is installed.
Chapter 3
DESIGN
The actual design of tangible hardware for the DKT-47 depended
greatly on the development of the
total system concept.
Only after the
conceptual design was started could the design of physical components
take place.
From the previous chapter, the basic requirements for the DKT-47
were established.
In short, these requirements are:
1. Reliable
2. Replacement for warhead
3. PAM/FM/FM telemetry system
4. Compatible with existing receiving stations
5. Low cost
The DKT-47 will be similar to the DKT-37 for several reasons.
DKT-47 will be a PAM/FM/FM telemetry system.
The
The choice of PAM/FM/FM
was based on cost, available receiving stations, and the nature of the
signals to be telemetered.
A PAM/FM/FM telemetry system is shown in Figure 3-10.
The system
consists of a Pulse Amplitude Multiplexer (PAM) which time division multiplexes a number of data channels.
The amplitude of each individual
pulse is equal to the amplitude of the the corresponding input channel
at the time sampling occurred.
The PAM format that will be used is the
Non-Return-to-Zero (NRZ) format which follows the input waveform during
the entire duration of the pulse.
Other possible formats are the
Return-to-Zero (RZ) in which the amplitude returns to a level corresponding to 0% during half of the pulse width.
The RZ format has a
higher fundamental frequency than the NRZ for the same data frequency
8
9
response and will not be used for that reason.
First, examine the nature of the signals as listed in Appendix III.
There are 28 data channels to be telemetered.
Excluding the video dop-
pler, the other 27 channels could be telemetered by using a Voltage
Controlled Oscillator (VCO) for each channel.
However, there are only
21 !RIG (Inter-Range Instrumentation Group; sets telemetry standards for
use on national ranges) assigned proportional VCO channels, and at
approximately $200 each for VCOs for $5400 per system, the total price
of the DKT-47 would not be low.
The use of VCOs for each channel was
rejected for those two reasons.
The video doppler is a wideband video signal that extends from
about 5kHz to 120 kHz.
If this signal was telemetered on a subcarrier
oscillator of 600 kHz would be required.
Using a proportional VCO, the
center frequency of the VCO would be 4.0 MHz.
The RF carrier bandwidth
can be approximated by
B= 2 ( F + 2fm )
where F= peak frequency deviation
and
fm= highest baseband frequency.
This approximation yields a bandwidth of 24 MHz for a modulation index
of 1.0.
This is an unreasonable occuppied RF bandwidth because this
type of telemetry system is allowed a bandwidth of only 1.2 MHz.
All previous SPARROW telemetry systems telemetered the video
doppler by frequency modulating the RF carrier directly.
method will be used on the DKT-47 for a very good reason.
This same
By tele-
metering the video doppler directly on the carrier, a detailed analysis
of the video may be made during post flight playback by feeding the
10
recorded video into a narrow-band digital spectrum analyzer. No other
special data processing equipment is required.
Additionally, there is
no bandlimiting of the video signal out of the missile as would be
required for inputting to a VCO.
Consider now the frequency spectrum of the modulation to the FM
transmitter as shown in Figure 3-5.
Having established that the video
will directly modulate the transmitter, a frequency band from 5 to 120
kHz must be allocated solely to the video.
No other subcarrier oscil-
lators may be placed in this band or their presence will interfere with
the analysis of the video during play-back.
There are still 27 data
channels to be telemetered in the remaining spectrum which consists of
400 Hz (the lower cutoff frequency for AC coupled transmitters) to about
5 kHz and from 120 kHz to about 350 kHz (the upper cutoff frequency of
most transmitters).
There are two possibilities for telemetering the remaining 27 data
channels:
1. PAM/ FM/ FM
2. PCM/FM/FM
Consider the second alternative first.
Pulse code modulation (PCM)
could be used to time-multiplex the data and that in turn could frequency
modulate a subcarrier oscillator placed in the upper end of the frequency
spectrum.
plexer
This scheme is shown in Figure 3-7.
waul~
A 32 channel PCM multi-
allow a 5 word frame synchronization (sync) pulse assuming
that each data channel is sampled only once during each frame.
This
implies that each data channel has the same frequency response and time
resolution requirements (this is not the case as will be shown later).
11
For both PAM and PCM, the ground station demultiplexer requires
' some means of determining which pulse is which.
This is accomplished
by providing a frame synchronization pulse (frame sync).
For PCM, this
· frame sync consists of a series of digital words on specific channels.
For PAM, this frame sync consists of a unique series of levels on specific channels.
The waveforms are shown in Figures 3-1 and 3-2.
The demultiplexer is set up to recognize the frame sync.
counters then can determine the number of each data channel.
to the commutator channel assignments in Appendix I.
are not as arbitrary as may seem at first glance.
Internal
Now refer
The assignments
In practice, it is
possible to assign functions to channels in such a manner that, during a
missile flight, the level of the functions creates a pattern similar to
the frame sync.
This pattern is called a false frame sync and will
actually cause the demultiplexer to lose its count and pick up a false
count.
So, some care must be taken in choosing the channel assignments
to minimize the possibility of creating a false frame sync.
The IA/CP/LG function is the most critical function for time resolution.
This is a summation of three steps whose maximum step indicates
missile fuzing.
During post-flight analysis, there is a requirement to
locate the position of the missile relative to the target.
If the
closing veloctiy of the missile relative to the target is 5000 feet per
second and the time resolution of the sampled data is one millisecond,
there is an uncertainty of five feet as to the location of the missile
when fuzing ocurred.
This uncertainty is usually considered the upper
limit for proper analysis.
For a time resolution of one millisecond per data channel, the
r· '
12
frame must repeat every one millisecond for a frame rate of 1 kHz.
Since there are 32 words (data channels), the word rate is 32kHz.
For
an 8 bit multiplexer, the bit rate is 256 kHz whcih is too high for any
VCO that could be used in the allocated spectrum.
A modulation index of
1.0 would require a peak deviation of 256 kHz on the VCO and even if a
~7.5%
proportional
deviation VCO was used, the center frequency of the
VCO would be 3.4 MHz.
This is definitely outside the capabilities of
the transmitter!
Now consider a PAM/FM/FM system.
10.
This system is shown in Figure 3-
The pulse amplitude modulation (PAM) process requires a 5 channel
frame sync pulse leaving 27 channels for data.
resolution requires a 32 kHz pulse rate.
As with PCM, 1 msec time
But there is only one pulse
per channel instead of the 8 required for PCM.
A 240 kHz +15% VCO has
become an industry standard by constant useage and could be used in this
case.
The peak deviation is 36 kHz yielding a modulation index of
slightly greater than 1.0.
This VCO would fit into the allocated spec-
trum without interfering with the video doppler signal.
A 32 channel PAM/FM/FM system with a 32 kHz rate has now been
established.
However, another problem has arisen.
Most ground station
demultiplexers do not have the built-in capability of accepting the 32
kHz rate.
One method of solving this problem is simply to reduce the
pulse rate and increase the number of times per frame the critical data
channels are sampled.
For the DKT-47, the pulse rate was set at 10 kHz which yields a
sampling rate of 312.5 samples per second (sps) per multiplexer channel
for 32 channels.
Four data channels required sampling rates higher than
13
this and were sampled twice in each frame to give a sampling rate of 625
sps.
This corresponds to a time resolution of 1.6 msec and a maximum
frequency response of 312.5 Hz.
The data channels requiring this higher
sampling rate are:
1.
IA/CP/LG
2.
Head Pitch Rate
3.
Head Yaw Rate
4.
Guard Channel The remaining channels do not require such a high
sampling rate.
In fact, most guidance information is at frequencies of
less than 10 HZ.
After assigning data channels to the available multiplexer channels, there are still four data channels for which no means of telemetering has been determined.
The Head Pitch Error and Head Yaw Error
will be telemetered on subcarrier oscillators because there is spectrum
available for the VCOs.
That leaves the Proximity Fuze Pulse and the
Contact Fuze Pulse.
During the post-flight analysis of the video doppler, a frequency
versus time plot of the spectrum is made of the intercept portion of the
missile flight.
This plot is shown in Fig. 3-15.
To facilitate analy-
sis and allow correlation of fuzing times with the video doppler curve,
the fuze pulses are used to trigger fixed frequency tone burst oscillators.
This is seen as a line of the frequency versus time plot of
Fig. 3-15 and the exact time correlations can be determined from this
plot.
The format of the DKT-47 is now fully determined and is as specified in Appendix I.
A block diagram of the system is shown in Fig. 3-
16. This completes the conceptual design of the DKT-47.
For review, the
14
system will be as follows:
1.
S-band frequency
2.
PAM/FM/FM
3.
Three vco•s
4.
Two TBOs
5.
10 KHZ 32 channel PAM multiplexer
The next step in the design process is to convert the conceptual
design into hardware.
This step requiries converting the output voltage
of the missile to levels and ranges acceptable to the encoding device,
in this case, a PAM commutator.
The basic philosophy for designing the hardware was to use off-theshelf hardware as much as possible.
For this reason, a commutator
previously designed by the Microelectronics Branch at PACMISTESTCEN was
chosen for the DKT-47.
This commutator is a 10 KHz pulse rate, PAM, 32
channel, Non-Return-to-Zero (NRZ) commutator in a 44 pin flat-pack
configuration.
This particular commutator had been used previously in
similar airborne applications and met the requirements for the DKT-47 as
shown below:
1.
Input voltage:
-2.5 to +2.5 Vdc
2.
Clock rate:
10 KHZ
3.
Format:
IRIG NRZ
4.
Channels:
32
5.
Output limiting:
+ 3 Vdc
The circuitry used for matching missile output voltages to the :
2.5 Vdc input range of the commutator consists of an operational amplifier used in the inverting configuration.
The three configurations
15
used are shown in Fig. 3-19.
For Fig. 3-19 (a), the gain is given by
_ Vo
Av - Vi
_
Rf
- - Ri
To be compatible with the commutator,
Vdc.
v0 must
be
between -2.5 and +2.5
For an input signal from the missile with a range of -10 to +10
Vdc, the required gain would be -0.25 yielding an output range of +2.5
to -2.5 Vdc.
Note that there is a change in polarity.
For this type of
input voltage range, a judicious choice of Ri and Rf will provide the
gain required.
The capacitor C causes the circuit to behave as a low-
pass filter (LPF) with a DC gain of Av and a -3 db point given by
f 3db
= 1/(21TRfC)
The LPF is used to bandlimit the signal to the commutator and thus
prevent aliasing error.
For the circuit of Fig. 3-19(b), the output voltage is given by
V0
= -Rf/
Ri Vi - 10 Rf/Rl
The - 3db point is the same as given above.
This circuit not only
provides a method of controlling the gain of the input signal but it can
also level shift the signal.
is proper for the commutator.
For a -5 to 0 Vdc input signal, the range
Therefore
Rf/ Ri = 1
If Fig. 3-19 (a) was used with Av = -1, the output voltage would be 0 to
+ 5 Vdc.
This illustrates the need for level shifting which is ac-
complished in both Fig. 3-19(b) and Fig. 3-19(c).
The polarity of the 0
Vdc power supply determines the direction of the shift.
19(c),
For Fig. 3-
16
V0 = -Rf/R.1 V.1 + 10 Rf/R.1
The following examples will serve to illustrate just how each of these
circuits is used:
Yaw Acceleration
V0
= ~ 3.75 Vdc
(~
25 G1 s)
F
.
Z0
= 20 KQ
.
V0 /V;
= -2.5/3.75 = -Rf/Ri
+ 20KQ
= -0.667
Note that the missile output impedance must be included as part
of Ri.
Set Rf
=
100 KQ(a convenient standard value)
= 150 KQ (also
V0 /V; = - 100/150
Ri
For V;
=
For C = .056
3.75 Vdc, V0
~f,
f 3db
~
a standard value)
+ -0.588
=- 2.209 (reasonable close for full scale).
28 Hz.
Front AGC
V0 = 0 to -5 Vdc
Z
0
= 5.11 KQ
-HOI/4c,
g.....IVY--t-~1,;\_
17
Ri = 35.7K for Av = -1.010 using standard resistor values.
If
the level shifting was not present, the range of V would be 0 to +5
0
Vdc.
The output must be level shifted down by 2.5 Vdc.
Since Rf = 41.2 KQ, R1 = 165 KQ.
Thus
The following table relates
Vi to V0 •
v.1
For C = 0.1
0 Vdc
-2.497 Vdc
-2.5 Vdc
0.027 Vdc
-5.0 Vdc
2.551 Vdc
~f,
f 3db =38Hz.
Rear AFC
Vi= 19 to 40 Vdc
c.
·~.
The input voltage range of 19 to 40 Vdc must be scaled to a 5 Vdc
range.
Since the input range is 21 Vdc and the output range must be
5 Vdc, it follows that
Rf/(Ri + 499K) = 5/21
Setting
Ri = 499K yields Rf = 143K
Rf/(Ri + 499K) = 0.143
(less than 5/21)
18
Picking R1 = 287 K will yield the following input-output table:
v.1
19 Vdc
2.260 Vdc
27.5
1.042
28.5
0.899
40
For C = .068
~f,
-0.749
f 3db
= 16 Hz.
These three examples illustrate how the signal circuitry not only
scales the range of the signals but also shifts the DC level to match
the commutator requirements.
For the DKT-47, the input voltages may
have been scaled to a range somewhat less than 5 Vdc.
However, each
of the data channels required a design process similar to the processes
just explained to develop the proper signal conditioning circuitry.
A signal conditioning circuit was developed for each of the commutated channels.
A worst-case analysis was performed on each of the
circuits using a Tym-share computer program.
This analysis resulted
in the tolerance specifications as shown in XAS-4461 in Appendix VII.
There are still two other types of signals that cannot be conditioned by the circuits shown in Fig. 3-19.
One type is the fuzing
pulses which are fast rise- and fall-time narrow width pulses.
A very
precise method of encoding the fuze data is required in order to provide adequate time resolution on the occurrence of the fuze pulse.
Analysts need to know precisely when fuzing occurred relative to
other missile flight events.
1~
One way to telemeter the fuze pulse is to turn on a gated oscillator when the pulse occurs.
If the oscillator puts out a given freq-
uency with a fixed duration, the analyst can easily determine if fuzing
occurred and when it occurred when performing the spectral analysis
shown in Figure 3-15.
This type of oscillator is called a Tone Burst
Oscillator (TBO).
The TBO shown in Figure 3-28 was designed to telmeter the Proximity
Fuze Pulse.
This pulse is a 50 Vdc pulse 50
detonate the warhead.
firing circuitry.
~s
wide and is used to
The detonators present a 10 ohm load to the
The TBO consists of a pulse stretcher, a gated
oscillator, and a low-pass filter.
50
~s
The pulse stretcher increases the
pulse and allows the gated oscillator to stay on approximately
25 msec.
The oscillator is an astable multivibrator with a transistor
switch in the ground lead to turn the oscillator on and off.
The last
stage of the TBO is a LPF designed to reduce the harmonics of the oscillator which has a square wave output.
The harmonics could obscure dop-
pler data when performing the spectral analysis shown in Figure 3-15.
The output of this tone burst oscillator is a burst with a frequency
of 5.4 KHz, and amplitude of 2.5 Vrms, and a duration of 25 msec.
The second TBO is similar to the one described above except for
the triggering circuit.
The Contact Fuze Pulse has a waveform as
shown in Figure 3-30 when terminated in a 15K ohm load.
The TBO consists
of an operational amplifier used as a voltage comparator to detect the
-2 Vdc pulse.
The rest of the TBO consist of a pulse stretcher, gated
oscillator, and LPF just as in the 5.4 KHz TBO.
The output of this
TBO is a burst with a frequency of 7.35 KHz, an amplitude of 2.5 Vrms,
and a duration of 160 msec.
The output of these two TBO allow the
20
differentiate between the TBOs in both frequency and time duration. The
complete Contact Fuze TBO is shown in Fig. 3-31.
These two schematics were submitted to the Microelectronics Branch
for implementation into microcircuits.
The actual circuits were changed
for ease of layout and implementation.
However, the basic operations
and requirements of the circuits remain identical with those submitted by
this author.
The last type of signal conditioning is quite different than any
described so far and is unique to the SPARROW missile.
The signal to be
telemetered is the boresight error (BSE) signal of the tracking antenna
of the missile.
The required information is contained in the amplitude
and relative phase of the BSE signal.
If the tracking antenna is pointed
directly at the target, the BSE signal will have zero amplitude.
As
the target deviates from boresight, the BSE developes both phase and
amplitude as shown in Figure 3-33.
For the SPARROW missile, an amplitude
of 1 Vrms corresponds to one degree off boresight.
If the phase of the
BSE signal is the same as that of Reference 02 of Figure 3-33, the error
is totally in the yaw axis.
ence
~1,
If the phase is the same as that of Refer-
the error is totally in the pitch axis.
In general, the phase
of the BSE signal can vary from 0° to 360° with respect to either of the
references.
A phase reference demodulator is required to convert the BSE error
signal to two DC signals (one for the pitch axis and one for the yaw
axis) proportional to the boresight error in the two axes.
The output
of this demodulator must be proportional to the amplitude and the relative phase of the signal with respect to the reference phase.
The demodulator designed for the DKT-47 is shown in Figure 3-34.
21
Basically the circuit consists of an FET switch and a LPF.
The switch
is alternately turned on and off in phase with the reference signal.
This yields a waveform whose peak amplitude is proportional to the
peak amplitude of the BSE signal.
The D.C. value of the waveform varies
with the phase difference between the BSE signal and the reference signal.
An example of the resultant waveform for difference relative phases
before filtering is shown in Figure 3-35.
To obtain the data for both
axes two identical demodulators are required, one switching in phase
with the reference corresponding to the pitch axis and the other switching in phase with the reference corresponding to the yaw axis.
The LPF is designed to 11 Smooth ouV 1 the waveform and provide a DC
level proportional to degrees off boresight for each of the axes.
The
cutoff frequency was picked to pass guidance information (typically
less than 10 Hz) while attenuating the chopping frequency of the switch
(approximately 300Hz).
The mechanical design and the flexible wiring harness were done by
the Instrumentation Department of PACMISTESTCEN under the technical
guidance of this author.
The basic guidelines provided to this group
for its part in the DKT-47 design were:
1.
Accessibility to all components for ease in testing
and repairing.
2.
Flexible wiring harness for reduced assembly time, less
errors in assembly, and increased reliability.
3.
Use existing parts (DKT-37 housing, etc) whenever possible.
The resultant system is shown in Figure 3-36.
Chapter 4
EVALUATION
The evaluation of any system must have as its objective the
determination of the adequacy of the system to meet its objectives.
The
definition of the objectives may be very general in nature and the value
judgments that establish the adequacy of the system may be subjective.
However, this generality does not negate the need to evaluate the system.
For the DKT-47, the evaluation started when the system specification
XAS-4461 was written (see Appendix V).
The evaluation of the DKT-47
was based on the requirements of XAS-4461 which were derived from the
specifications of the AIM-7F missile.
This specification sets specific
levels of environmental conditions under which the telemetry system must
perform satisfactorily.
The specification also defines satisfactory
operation of the system by setting tolerances on output signals for
fixed input signals.
Should the output fall outside the tolerances
given by XAS-4461 during environmental tests, the system will be considered to have failed.
The preliminary evaluation of the DKT-47 was based mainly on the
qualification of the individual components to stringent environmental
tests and an interface test of the complete system.
The environmental
tests on all microcircuits were performed by the Microelectronics
Branch prior to delivery to this author.
These tests consisted of the
following conditions:
1.
Shock: 1500 G's, 1 msec, half sine
2.
Acceleration: 5000 G's
3.
Temperature: -40 to +71
°c
22
23
4.
Leak: Gross leak and fine leak
5.
Pull Test: 2 grams tension on all wire bonds
6.
Temperature Storage: 24 hours at 150 °C prior to sealing
All microcircuits were built and qualified to MIL-STD-883 Class B
by the Microelectronics Branch.
The environmental conditions listed
above are equal to or exceed the environmental specifications of the
completed system.
Additionally, the microcircuit modules underwent
the functional tests as described in Appendix VII before being installed on the printed circuit board.
The purpose of the first prototype DKT-47 was to demostrate the
feasibility of such a system.
From this prototype was developed a
drawing package to build pre-production models.
In some respects, the
prototype was different than the preproduction models will be.
This
was due to the unavailability of parts in the time frame required for
this graduate project.
Bus wire instead of eyelet was used to connect
the flexible wiring harness to the multi-layer printed circuit board.
For this reason, vibration testing was eliminated on the prototype
system.
Eyelets will be used on the preproduction models and vibration
testing will start with those models.
The preliminary tests on the DKT-47 consisted of providing
simulated missile telemetry signals (including output impedances) to
the telemetry system and then, receiving the radiated signal at the
ground station.
data.
The signal was processed to retrieve the transmitted
The output of each data channel was then compared with the
required output for the given input.
with requirements of XAS-4461.
In all cases, these matched up
24
The result of this graduate project was to demostrate the feasibility of building a Fleet training telemetry system required by
NAVAIR.
The prototype developed will be modified as necessary for
production and the drawings for production will be completed in September. The complete drawing package will then be available from the
Navy as NAVAIR Drawing 588AS600.
~tion of the prototype DKT-47.
This project was finished upon com-
25
I l I0 l
0
I
I
I
l : I I ,o I 0
I
I I
I
NR=!.-\..
I
I
I I
I I
~:e
I
1
I I
I I
I
I
I
I
I
I
I
I J I I
I I I I I
I .I
I
u
i0 i ' I
I
I
I I I
I
I
I I
I
I
I ,,
\\ .
OV\c. '~
I
I
I I I
I
l
I
I I I
I
I
I I I I I
•
I I
I I '
l I
I
I0 I ' t
I
I
I
I 1
I
I I
I I
I I
I
I
I
I
I
b~ oV\t. \e.ue. \
"tt'("'O" \t. '('t.f'"('e,.e\'\~c:l
'o~ -th~ o+\-\e~ ·\e.ue.\
I I
l I
I
~d
'('t.~'('ftle"
410'1'\E.."
\)~
i"'b ~?~v-rtQd
0..
n6.\~. bi+ wl c\E..
'P ""\-t~e.
"u'<'O·· ·
\'$.
:\icl
Y"e.\)reg.~ t
b~ "'o ?I.A.\11e. c.o~i\1oV!
26
.........
-..------- ---------- -
0°/o C6.\\ \:n·o..""OV\ - '2.. 'S VdC..
'C.\o\o.V\l'\~\
2.8 )
\ OC0 /o
Co..,; \:>'('6.,-"t)V\
+'2..'5 V~c..
(C..~V\ne.~~ '2.,.q, ~OJ'!.\)
,. = e.'-'o.~Yt~ \ \ \1\.4-ev-"A.. \
'Fov
+\-\.~
bK..T .. 41
1
,..:.
l
.o ~'&eC.
27
N
I
~
0
C\J
N
I
~
If)
28
n
I
L"
u..
·-:!
I
~
l
T\
,J
~
~
tr
J
~
0
v
7
:r.
-~
-
z:
~
(l
~
Ill
Q._
-
.:.(:
!1
~
29
30
ltl
'
~- .
i
I
l
31
Df s-
~
~1
U-~
s,..
~
~a
~
l
nl::l
-:c-
)l! e
~~
'"
t'l,f4 /
trli
~ 2 ..,
-a.
jet)~
i'v':t
~Nll-::l
o.tll9~
~
-13
i "'1
d
~
~
(iiJ~
1
rU
ril
g
-;r:t'
"' cfJ
- I~
~ ~
0
.J)
\..
J1
-
:r:
)/.
1~
I
j)
)l
~
1]1 ,.:.
r-
ll
32
-i
p
c
lN
oOUT
(a)
-+10
Vclc
\N
OUT
(b)
-\0
Vdc
JN
OUT
(c.)
'
33
l
34
ovdc,
----------
- "2... 0 \) t!c..
35
~
?
D
-+
36
I
·--t--
0,
0.e:w.~w:e.
~,,'1\o..\
I
I
--1----1--- o\/ck
I
I
I
I
I
I
I
J
I
- -J- ovck.
I
I
I
I
I
I
I
I
I
I t
I
I
-I- -1--1--1--1- -t--t- 0 \/c:lc.
J
I
I
I
l
I
I
)
-
No\ e.~
¢, o.Y\d
¢ 4 4-'C"E.
~\~V\a\ ·,~ ~\\o~V\
~oo o.~Y't iV\ ~~-=e..
"T\1\e. ~sE..
tl4b ct. ~UAft.·Wo.,.~e, ~v- \\\u.~-h-o...f.iOY'!
~'"'-'C"\)~eco c't\l~. No-rwt~ll~ 1
~~i~!Q. ~
l .;.,.""'~
\t \":> a. -&\V\t:: -wa.ue.
~'f" .0~...-e.e. ot eT't"OV'.
vJ''""
37
~
..q-
co
~
-
'
tO
d"'
u:
'Y.
0
38
---I---- -1-----1- ----1--- 0 ~~<
BCSE
Hed
p,~
0\lck.
br\"'V'
(~"~,\fe.~)
~SE..
0 'J ~c.
1....--
r\e~
P\~
&ro't'
( ~.Ci Het"4ld)
L_ ~--1
'---1---1
o vclc.
39
Appendix I
General Specifications
Transmitter Frequency:
2200 to 2280 MHz
Transmitter Power Output:
2.0 Watts Minimum
Data Channels
Continuous:
5
Commutated:
23
Sampling Rate:
312.5 sps
Power Requirements:
+25 Vdc @ 0.5 A
Pre-launch Power Source:
Missile Power
Post-launch Power Source:
Missile Power
Instrumentation Format:
Video Doppler:
Direct on carrier
Proximity Fuze:
5.4 kHz TBO
Contact Fuze:
7.35 kHz TBO
Head Pitch Error:
144+ 4 kHz VCO
Head Yaw Error:
160+ 4 kHz VCO
PAM Commutator Data:
240 kHz + 15% VCO
40
Commutator Format:
Channel
Function
1
IA/CP/LG
2
Head Pitch Rate
3
Head Yaw Rate
4
Guard Channel
5
Pitch Acceleration
6
Front Feedthru AGC
7
Launch Initiate
8
Head Pitch Position
9
Recycle
10
Head Yaw Position
11
Speedgate AGC
12
Wing 1&3
13
S&A
14
Wing 2
15
Speedgate Sweep
16
Wing 4
17
IA/CP/LG
18
Head Pitch Rate
19
Head Yaw Rate
20
Guard Channel
21
Pitch Rate
22
Rear AGC
23
Yaw Rate
24
Rear AFC
41
25
Yaw Acceleration
26
FRont AGC
27
Roll Rate
28
0 % Reference
29
100 % Reference
30
100 % Reference
31
100 % Reference
32
50 % Reference
Enclosure (A) to
21P5 1-lissi1e - Hale
3.!£_?_ TELEME'f'ERING CONNECTOR ASSIGNMENT
Glu.ssr"al Prod.. Inc, liSH50··20PS-l038
----~--Raythe.on No, 293212
~IN-7F' 8LOCK_gQ
Pin
t;o.
:: l s:::: i le:
Co:-.r.c ctlon
A
2~Pl-17
Series 2K
ll
12P2-ll
20 .SK to Ground
c
4Pl-7
I
l
E
'1-
I
F'
4P 1-1
24Pl-9
9Pl-13
Impedance
e e
- (Emitter
Series S.llK
1
Fol10\~erl
'Series 100 K
Series 2K
+SO VDC
Feedthrougr. AC:C l 0 to
·
~lax
Loads
2 HA
·l·
5 VDC
l'ront AGC
0 to -
5 VDC
Rear AGC
0 to - 5 VDC
-50 VDC
- 50 VDC
Intercept Arm
Pre IA
Coincidence Pulse
No
500 K ohm
2 M.A
300K
IA
·p\1
Voltage Swing
unctlon
1+50 VDC
(ui;:Llf'\z)
,;J.f: 7043:72-1530
Page 1
....... ...... I .. . .
--- l
D
nayclleon Letter
~}(;fl:
100 to 200msec
.,s::
-25VDC,IA=-5VDC
i--r'
732 K
CP
PW = 20 to'4o msec
LG~
lOPl-10
l:i
_Series 100 K
And Level Gate
ilead Pitch Gyro
::::;
CP= -6VDC, CP =+lSVDC
(')
c-t
Pre I.G=-lBVDC, LG=+ 18V!1C
+ 6 VDC
-'•
.J
13AP1-4
Series 499 K
Fuze AGC
0 to + 5 VDC
K
24Pl-20
Series 2K
+25 VDC
1·
L
S1'Bl- 31
NL
226 K
--J\N~} _L
Battery- •'-/·.-v'
v/ing Lock and
:;r:.
-o
-o
CD
::::;
0
::::;
(75MV/"/sec and +80°/sec
HAXl
0
s:u
c-t
s:u
0...
-'•
Ul
-
><
:;r:.
.......
.......
<
s:u
-'·
'f
-----
Latch Command
97.6K
10P2-l3
M
Series 100 :K
Yaw Head gyro
1.-At.~NC..tt
11'1\"'I'P..\.:':"
25 VDC
\'IL= +25VDC, Unlock=-25VDC
SPl-2
1.
Series 20K
Guard Channel
--'
s:u
cr
--'
CD
battery = 0 1
Battery = + 25 VDC
No
+ 6 VDC
(75MV/ 0 /Sec and +80~/sec
t·lAX)
N
2M.A
-
.:!:. 3.1 VDC
'
-+»
N
--···--··--~-----·------·- ··---------------------------·-·--------~--------------..------·-····
-------------Enclosure (A) to
Rnytheon I.etter
W~M:slf:7043:7~-)S10
Pa<)e 2
Pin
No.
:-lissile
Connection
24Pl··l0
Tele
-
;
p
-
Missile Output
Impedance
l
!Series 2K
Max
Loads
Voltage Swing
Function
2 HA
1-25 VDC
-25 VDC
70VDC (0.213 VDC/Deg
and 55° !-!AX)
Normal +25 VDC, K.T. =
-25 VDC
s
lOPl-18
Series 100 K
I
·aead Pitch F.U.
T
8P2-20
I.S::lries 200 K
Killed Target
u
STBl-3
Series 4.99K
+lo
H
10P2-24
Series 100 K
l!ead
X
101'2-7
Series 100 K
'rime 'l'o Go
Pre TTGo = +25 VDC
Post TTGo= -25 VDC
y
STBl-10
!series 4.99K
-16 VDC
z
lOPl-15
lseries 20l<
Head Pitch Radar
5Pl-5
Series 499 K
aear AJ?C Sweep
-16 VDC
+121fDC MAX (+2. 4VDC/Deg
off !3oresiyht)
PD mode = 19 to 27, SVDC
C~l mode = 2 8
to 40VDC
cc
STBl-13
Direct
+26.5 VDC Power
+2 6 . 5 + 6 . 5 VDC
- 2. 0
FP
7P2-14
n.
Not Rf.lin=+25VDC,
RHi;, = -25 VDC
Pre HOJ = -25 VDC
HOJ = +16 V
+11.
+16 VDC
VDC
Ya~t
F.U.
+11.79 VDC (0. 214 VDC/Deg
and 55° HAX)
i
BB
.
200 K
R.Min
I
HOJ
llH
STBl-12
JJ
23Pl-21
·-'VV'-I'v:J-
..• ·- ·---'1./'v\,,
I Direct
FF
MIN and
!!OJ
100 K
'?"\~\!,;,~ Battery/Hydraulic Activate
Series 201<
2MA
Radar Error
1lMA
+25VDC at Battery &
Hydraulic Initiate
8
'
2 MA
VRMS' (Max)
( 7 VRt·!S/Deg @ 70 Khz
30 K chm
Post TTGo)
l
I
.
'
+::>
w
-------E:!IcYosue (Al to
....
I Connectio~j
II
Pin
No.
:·li%i le
__
Missile Output
----4------,-- I
LL
6P2-5
HN
·
Impedance
!
Raythenn Letter
WGM:slf:7043t72-l530
l?il<j(l
j
I
-
t-
Tel<:
,
Funct~on
Voltage
3
S~1ing
3 second Launch Delay
('l'est)
ST31-23
Direct
400 h:;: Return
Monitor
Pre=+25VDC,Post=-25VDC
ss
,.'
STBl-24
Direct
)l'2, llSVAC 400 Hz
RR
i
Pre-launch Tele pac
power
5P2-10
Seri.es 100 K
Coding
0 to +20VDC
w
1
6P2-17
5 l< to ground
Recycle
v-r.v
E25
Direct
System Ground
Unlock = 0 VDC
Lock = +4 , 8 VDC
RA = +2.6 VOC
XX
lJAPl.-7
lOK to Ground
Narrow Video
!
I
·I
I'
!
'{'[
!
£
I
3 to 145 KHz
12 VI1NS
4Pl-8
Series 100 K
l3AP1-l
lOK to Ground
8P2-24
Series 20 K
Ma~
Loam;
-see Encl
(HAX)
(D)
F=N'T
(Unit 4) Feedthru Ar,c
1!3road Video
!Head
Radar
0 to +5 VDC
See Encl
3 to 145 KHz
12 VRMS
(MAX)
2. SVm!S
(HAX)
(D)
(, SVRMS/
JOK ohm
Deg of Error
g
8Pl-2
Series 100 K
Speedgate AGC
+5 to +45 VDC
-~
5P2-5
10 K to Ground
_Range Reference
0 to 5.5 VRMS
!.
6P2-7
51. 1 K to Ground
Sweep (Test)
!1onitor
.
..r:::.
..r:::.
Enclosure tBl to
Raytheon
20J9 'l'Bl!lmetering Connector .!\ssi9nment
20J9 Hiss ile Hale
HS27477Yl2D22P
I ".Hss:~~e
'
p·
. 1n
..
No.
[
j
.
·t
161\l-26
I
.3
4
16A9-lB
l6A9-31
5
16111.-29
6
16A8-29
16.!\5-22
7
e.
16A4-22
I
9
1o
·t.
!
i
Conn<:ctlonj
-1---~.l
l6A8-2S
2
AIH-i':E' Block CQ
l6A3-3
16Al0~ 19
'
-:1."e 0 ut.put--t
! -••>•
-
!4'
. 1ss1
ln•peddnce
rect - - - - - - - -
IDiract
.
!
.~Direct
~,Series
fli.n~
.
2 F.U.
•-l-ing 4 F.U.
t
~itch
~
!
!
Series 20K
1ta~l
:!:_28
I±.
Gyro
Accelerometer
I
(iO~·io
l21K
-------.-JV\.,
A1t #2
----.1\,r._,.._:,,~::_s-
voc {l.275VDC/Deg
r!
Deg MAX)
.
6. 2VDC (31 mvDC/ 0 /sec
:!:_ 6
1!.
1 •10
z
11Min.~l.egz ohm
1
I
11 Heg ohm
Z
!!-lin
I
1
.
VDC (50 mvDC/ 0 /sec
lt. 1 and 2
6 voc (150 mvDC/G or
G Max)
:!:. 6 VDC (150 mvDC/G or
40 G Hal{)
.
A1t U
·;e-;:;:-1\<
Min
:!:.6 -VDC (50 mvDC/"/sec
or :!:. 120"/sec Max)
·1issil.e Velocity
Series 20K
l.oads
1 or 120 • /sec ~lax)
~,itch· Ace.elerometer
!
I
.
~·
ll
MAX)
:!:_28 voc {1.275VDC/Deg
and!_22 Deg w,x)
aw Gyro
I
Series 20K
VDC (l.2;5VDC;Deg
I '"
-1
or +2iJO"/sec Max
.
Series 20K
Vole"" S>iog
-
. and+22
-
jRoll G:rro
Series 2CK
I
I i"nd:!:_£2 Deg
II
20K
Page 1
·~li:;-;:--~~~:i:,-g-;-;:;.---t--;:28
I.
.
!
!.
Ij
1'Mccion
Lett~r
WGH:slfi7D4J:72-1~1n
1
.±_20 VDC (Integrated
long Accel. 0. S VDC/
100 ft-sec
A.LT
A
B
C
I D
*1 25 -25 +25 !+25 !VDC
#2 25 +25 +25 1-25
to
j
IT'eler25 I +G.3 +25J-8.
'-
~
-----·---.,..---,..
-------------------::---·
Enclosure. (B) to
Ra.ytileon Lc.:tt.er
t
WGM:ulf&70~3:72-l5JO
Pc~ge
Pin
No.
r
Missile Outp-~~----]
Impedance
1
z.tissile
' ConnectJ..on
Tele
Function
- ---1---------·
Series 20K
!
'ic\\1 S.D. Comp,
:
l
I
.!
11
, 16A6-16
I
i
1
i
16A6-15
jseries 21lK
Pitch S.D. Comp
1:
I
16A7-19
Direct
!ooost/Glide
12
13
14
__T___
:J.
Volt.J.ge Sv1ing
Max
Lo:=.ds
ICJ:·~6VDC)
3.94HVDC/G/Deg or
+1500 G/Deg Nax
(~6VDC) 3.94MVDC/G/Deg or
G/Deg Hax
l _::-1500
('l'est) Ground to
return. to Boost
!spare
15
lspat·e
16
jspare
17
jspare
:).B
!Spare
19
!Spare
1
20
I
21
spar::e
l
,Spare
!
22
II
"is pare
I'
I
I
I
'
~
0)
Enclosure (C}
21J.2 Video T~:).errtetcdng Connector Assignment
21J2 Missile - Female
JT02P-8-6S
Ravtheon No. 40357B-l
b.!H... 7.F Block CO
-~~-~T~~
Miss i 1·~ 0\ltput
~issile
Pin
No.
Impedance
Connection
1
21Al-E4.
I Direct
2
21Jl··J
Ill< to
i
Tele
Function
System Ground
Ground
.
~--c=-~-
---
'P ~t-y-.e
~oltage
3
21Jl-F
151.1!<
to Ground
4.
21Jl-K
j 3.16K
to Ground
5
21Jl-!?.
Direct (after Battery
Only)
IActivate
6
21J3-5
Is
and A
1
Swing
J-~axLoads
l
5 KHz to 160 KHz
Vidt..'O
1. 3 VRMS
•
to
R<1y th<~on Letter
HGH:Illf:704 ), 72-1530
24K ohm
(HAX)
0 to + 5 VDC
Speedgute Sweep
I
_Fu:~ Pulse
!nt.ent to Launch
0 to +50 VDC
10 ohm
+26.5
0.5 A
+6.5 VDC
-:2.0 VDC
jTriggerin~ Device
I
I
I
~
..j:::,
'-J
48
Appendix II I
Data Functions for the AN/DKT-47
Function
Description
IA/CP/LG
This is the summation of three separate fuzing
functions all of which must be satisfied for
final fuzing to occur.
Head Pitch Rate
Output of the pitch gyro on the tracking
antenna.
Head Yaw Rate
Output of the yaw gyro on the tracking
antenna
Guard Channel
Output of the Guard Channel discriminator.
Pitch Acceleration
Output of the pitch accelerometer on the
missile body
Yaw Acceleration
Output of the yaw accelerometer on the
missile body.
Front Feedthru AGC
AGC voltage developed as a result of spillover
energy in the front receiver.
Launch Initiate
Summation of step functions that indicate
missile battery activation and missile
hydraulics activation.
Head Pitch Position
Output voltage from pitch follow-up
potentiometer on tracking antenna.
Head Yaw Position
Output voltage from yaw follow-up
potentiometer on tracking antenna.
Recycle
Indicates the quality of the front signal.
49
Speedgate AGC
AGC voltage developed in the missile•s
velocity tracker.
Speedgate Sweep
AFC control voltage from the missile•s
velocity tracker.
Wings 1&3
Output voltage from the follow-up
potentiometer on Wings 1&3 which are
mechanically coupled together.
Wing 2
Output voltage from follow-up
potentiometer on Wing 2.
Wing 4
Output voltage from follow-up
potentiometer on Wing 4.
Pitch Rate
Output voltage of Pitch gyro located
on missile body.
Yaw Rate
Output voltage of yaw gyro located
on missile body.
Roll Rate
Output voltage of roll gyro located
on missile body.
Rear AGC
AGC voltage developed by the rear receiver.
Rear AFC
AFC control voltage of rear receiver.
Front AGC
AGC voltage developed by the video signal
in the front receiver.
S&A
Step functions that indicate arming of the
S&A device.
Video Doppler
Wideband video signal from 5 to 120 kHz whose
frequency is proportional to the closing
velocity of the missile with respect to the
target.
50
Proximity Fuze
Fuze system that provides a fuze pulse to
the warhead detonators when there is no
contact.
Contact Fuze
Fuze system that provides a fuze pulse to
the warhead detonators when the missile hits
the target.
Head Pitch Error
Pitch boresight error of the tracking antenna.
Head Yaw Error
Yaw boresight error of the tracking antenna.
APPENDIX IV
RF Carrier Deviations of Subcarrier
Oscillators in FM/FM Telemetry Systems
Engineers are often required to choose the RF carrier deviations
for each subcarrier oscillator in an FM/FM telemetry system.
This
appendix discusses the basic theory used in making such a choice and
presents a simple method for calculating the RF carrier deviations for
any FM/FM telemetry system.
All FM/FM telemetry systems are described by the same basic formula
as given below:
(1)
where
(S/N)D= Signal-to-noise ratio of data
(S/N)c= Signal-to-noise ratio of carrier
Be
= Receiver IF bandwidth
fD
= Highest data frequency
fdc
= Peak carrier deviation
fs
= Subcarrier center frequency
fds = Peak subcarrier deviation
The unknown quantity in (1) is the peak carrier deviation fdc for each
subcarrier oscillator of frequency fs.
Two modulation index terms are
now defined:
mD= fd/fD
(2)
ms= fd/fs
(3)
Knowing ms for a particular subcarrier frequency fs determines fdc"
The
data modulation index mD is normally assumed to be 5.0 when using standard
!RIG subcarrier oscillators.
However, mD may take on any value.
51
52
For an FMIFM telemetry system with many subcarrier oscillators, the
peak RF carrier deviation fdc of each subcarrier may be determined by
substituting all known quantities into (1).
The following are known:
fs
fds
fo
Be
It is desirable to produce the same (SIN) 0 for all fs as the (SIN)e
decreases. As a side note, at the threshold of the receiver ( or when
(SIN)e=10 dB.), the (SIN) 0 should be about 40 dB for acceptable data.
However, this may require a total peak deviation that produces an
occupied bandwidth greater than allowed.
Some compromise in (SIN) 0 at
threshold may be required to stay within the allocated bandwidth.
Now define a new term.
(4)
k= fd/fs
Using (2) and (4), rearrange (1).
(SIN) 0= {SIN)e (3 Befdc m 0 )~ I (fs
2
3
3
2
k )~
(5)
All quantities that do not change as the subcarrier oscillator freqency
fs is changed are combined into one term K.
3
3
(6)
de = K ( 2 f s k I mD )~
Since K will be a constant for a given (SIN)e and Be with equal (SIN) 0
for each subcarrier oscillator, a term called the peak relative carrier
f
deviation can now be defined.
(7)
f Rdc = ( 2f s 3klm D3 )~
This term fRdc is proportional to the actual peak carrier deviation
fdc by K.
The sum of the fRdc of all the subcarriers is likewise
proportional to the sum of the actual peak carrier deviations.
The
53
total peak carrier deviation is usually determined by some physical
constraint on the system such as the transmitter capability or occupied
bandwidth of the RF carrier.
A general method for calculating fdc for each subcarrier may now
be described.
Step 1:
Determine fRdc for each subcarrier from (7).
Step 2:
Add all fRdc to yield FRdc·
Step 3:
From system constraints, determine the total peak
carrier deviation Fdc that may be used.
Step 4:
The fdc for each subcarrier may now be calculated.
fdc= ( fRdc Fdc ) I ( FRdc )
where fRdc is the peak relative carrier deviation
for the subcarrier in question.
54
Appendix V
Development Specification for the AN/DKT-47
The development specification presented in this appendix was written by this author.
Basically, the specification defines the environ-
mental conditions under which the DKT-47 must operate.
Additionally, it
defines satisfactory operation.
After the DKT-47 has been developed, evaluated, and approved for
service use, NAVAIR will contract with private industry for further
production of the DKT-47.
This specification will serve as a legal and
binding document listing the requirements of the system.
The environmental specifications set forth in XAS-4461 were given
in various missile specifications and were compiled by this author
during the initial conceptual design phase of the project. The performance characteristics were calculated by this author as the system was
designed.
55
XAS-4461
Code !dent
30003"
NAVAL A1R SYSTENS COt1MAND
DEPARTr-IENT OF
:I
'
THE NAVY
I
DEVELOPHENT
l
SPECIFICATION
FOR
f
TRANSNITTING SET,
I
TELEMETRIC DATA
'
IL
I
I
I
'
I
I
I
1.
1.1
SCOPE AND CLASSIFICATION.
i~2ilil.·
The eq•Jipment covered by this specification shall M for
airborne u,_;.e an-d shan be used on the AIM-7F
SPAP.RO~l
I II Guided i'lissi1 e
for Navy Technical Evaluati.on {i!TE). Production Monitoring Tests {PMT),
and fleet training missions.
1.2
C1ass!..fJ...s"1io.!!_.
See 6.1 for intended use of the. ty·ansmitting set.
The equipment cDver·ed by this ·specification
shall consist of the following (see 6.2.2):
Te1e1netric Data
AN/DKT-47 (XMG-1}
Transmitting Set
2.
2.1
APPU CABLE OOCUr1ENTS.
General.
The following documents of the. issue in effect on date
of invitation for bids or request for proposal form a part of this
specification to the extent specified herein:
I
I
'l
I
II'
AN/DKT-47 (XNG-1)
.
'
56
...
SPECIFICATiONS
Federal
PPP-S-601
r~i 1 i
Box, Wood, Cleated-Plywood.
t.ar·y
AR-34
Failure Classification for
Re1iabi1ity Testing, Gener·al.
MIL-?-116
Methods of Preservation.
MIL-C-45662
Calibration System Requirements.
~Hl- T-18303
Test Procedures, Preproduction,
Acceptance, and Life for Aircraft
Electronic Eq1.1ipment; Format for.
STANDARDS
Military
MIL-ST0-129
Marking for Shipment and Storagz.
MIL-STD-414
Samp1ing Procedures and Tables.
MIL-STD-454
Standard General Requirements
for E1ectt·onic Equipment ..
MIL-ST0-461
Electromagnetic Interference
Characteristics, Requirements
for Equipment.
MIL-STD-462
Electromagnetic Interference
Characteristics, Measurement of.
MIL-STD-781
Reliabiiity Tests; Exponential
Distribution.
MIL-STD-810
Nilitary Standa;-·d Environmental
Test
t~ethods 'for·
Aerospace and
Ground Equipment.
MIL-STD-831
Test Reports, Preparation of.
57
I
l
I
DRAWINGS
Naval Air Systems Command
{Code Ident 30003)
Dl588AS600
Transmitting Set, Telemetric
Data, AN/DKT-47 (XMG-1).
PUBLICJHHJNS
RCC-106-73
2.1.1
.Telemetry Standards.
~~ilab_ility
of documents.
When requesting specifications,
stundards, drawings, and publications, refer to both title and number.
Copies of this specification and applicable specifications required by
contractors in connection •11ith spec1 fi c procurement functions may be
obta·ined upon application to the Cmnmanding Officer, Publications and
Forms Center, Code 105, 5$01 Tabor Avenue, Philadelphia, Pennsylvania
19120.
Copies of RCC-·106-73 are available from:
Center (ODC), Attn:
Defense Documentation
DOC-IRA, Cameron Station, Alexandria, Virginia
22314.
2.1.2
Precede!~~of dc~nts.
~lhen
the requirements of the contract,
this specification, or appncable subsidiary specifications. are in
conflict, the following precedence shall apply:
(a)
Contract.
The contract shall have precedence over any
sped fication.
(b}
This
St@.£:-ifjc~_ij.£!!_.
This specification shall have precedence
over all appl !cable subsidiary specifications.
Any
deviation from this specification, or from s·ubsidiary
(c)
specifications
wher~
writing by the
procur~i ng
~nc?d
applicable, shall be approved in
specification.
activity.
Any referenced specification
58
shall have precedence over.all applicable subsidiary
specifications referenced therein.
All referenced
specifications shall apply to the extent specified.
3.
REQUIREMENTS.
3.1
Pr~groduction
requirements.
Unless other..dse specified in the
contract or order, preproduction samples of this equipment shall be
manufactur·ed using the same processes and testing methods proposed for
the production.
The
sample~
will be tested as specified in Section 4
herein for the purpose of determining that, before starting production,
. the contractor's. production methods wi 11 produce equipment that will
I
I
II
i
I
I
t
I
I
I
I·
I
meet the requirements of this specification.
sh~ll
No production equipment
be ds1ivered before apprGval of the_preproduction models.
Fabrication
of pr·oduction equipment prior to such approval is at the contractor's
The preproduction models sha1l not be considered as part of the
own risk.
equi p:r.,~nt t:nder the contract un 1ess otherwise specified in the contract
or brder (see 6.2 (c)}.
3 .1.1
Nanufacturi ng_..Q..i:ocesses and testing
met_~ods.
Fo 11 owing the
acceptance of the preproduction sample, the manufacturer shall not change
his manufactur1 ng proc=sses or testing methods without prior written
approval of the procur·ing activity.
th~:reof,
The preproduction tests, or any portion
shall be repeated at no additional cost to the procuY'ing agency
under any of the fo 11 o1i ng conditions:
(a)
The manufacturer has modified his product by a change of
sources of supply, production procedure, or testing methods.
(b)
When there is evidence that the minimum quality requirement
of the product has not been maintained.
This evidence may
59
be in the form of accumulated failure reports (see 6.2(f}l).
(c)
When production mode 1 s fail to meet the requirements of this
specification.
3. 2
Oocumenta ti on requirements.
Oocumentati on sha l1 be submitted
by the supplier in accordance with the Contract Data Requirement List,
00 Form 1423, and the purchase order to meet the following requirements:
{a}
Samplin_g_p_l~.
The supplier shall prepare sampling plans
describing application in accordance with MIL-STD-414
(as prescribed by the procuring agency) wherever required
(see 6.2(f)2).
(b)
Test, inspection, and report procedures.
The supplier
shall prepare written detailed test and inspection procedures.
These procedures shan be in· accordance with MIL-T -18303 and
shall be submitted w'ithin 60 days after the award contract.
The procedures shall consist of five documents to correspond
I
I
I
I
to the ir.spections and tests of Sections 4.6, 4.8, 4.9,
4.10, and 4.11.
(see 6.2(f}3).
Test reports sha 11 conform to MI L-STD-831
All test and inspection procedures and reports
shall be subject to approva1 by the procuring activity.
parts sha 11 conform to the drawings and documents lis ted
on
Orav1i ngs
DL588AS500 and sha 11 meet the requi rer~ents of these drawings and doc\.lments.
3.4
Product i_on
eq:J i pmen_!.
Equi prnent supplied under the contract
sha.ll in an respects be equivalent to tne approved preproduction sample.
Each equipment shall be capable of successfully passing the same tests as
imposed on the preproduction sample.
Evidence of noncompliance with the
above sha11 constitute cause for rejection; and for equipment already
'
:!
s
60
c ;; c.:;;
accepted by the Government, it shall be the obligation of the contractor
to make any necessary corrections as requested by the procuring activity.
l
3.5
!
3.5.1
General requirements.
Satisfactory operat:i._2.!!_.
Satisfactory operation shall be defined
as conforming to the requirements of this specification.
I
I
r
I
3.5.2 DELETED.
3.5.3
Service cond·i ~ions.
I
II
I
I
I
II
I
oper<~te
satisfactori1y
under any of the following service conditions or natural combinations thereof
which are normally encountered during its service life.
3.5.3.1
I
The equipment shall
Temperatur-e.
The equipment shall be capable of satisfactory
operation wheri operating at an ambient temperature range from - 40 pegree
celciu:s (°C) to .+ 71°C. except that the ri1dio frequency (rf} pcv1er output
may drop to not less Uwn LO watt at transrnitter baseplate temperatures
betW<'en 72°C and 80°C.
3,5.3.2
A1tituc!:l·
Test-; shal1 be as :;pec1fied in 4.7.1.
The <:;quipment shall be capab:!e of satisfactory
operation from sea level to 90,000 feet of altitude {29.92 to 0.52 inches
of mer'cury),
3.5.3.3
Tests shall be as specified in 4.7.4.
Humidit:f.•. The equipment shall be capable of satisfactory
opel·ation under reldtive humidity conditions up to 100. percent of temperatura~ up to + 71°t:.
Tests shall ·be as specified in 4 . 7 .2.
3. 5. 3. 4 }'i b.~~l"!E!!.·
The equipment sha 11 operate satisfactorily undel'
vibration app1ied along the longitudinal, vertical, and hor-izontal axes
separate 1y in accordance
\~i th
MIL-ST0-810, Method 514.1, Procedure n,
Part 1, Curve D (Captive), Part 2, Test Curve Q (Flight). and Part 3, Tes.t
Curve t-,G of Figure 514.1-4.
Refer to: 4.7 of this specification for pretest,
during test, and after test data required.
Tests shall be as specified in
61
r.
i
I.
i
I
!I
!,
I
I
i
4.7.3.
3.5.3.5
Shock.
Ttie equipment shall be capable of satisfactory operation
without damage or maladjustment resulting from impact shock of 65 gravity
II
!
units (g) peak for a time duration of not less than 5 milliseconds (rns)
I
I
applied along the longitudinal, vet'tical, and horizontal axes separately.
Tests shall be as specified in 4.7.5.
Accel~tiOJ!.
3.5.3.6
The equipment shall be capable of satisfactory
operation during and after peak longitudinal acceleration of 40 g applied
for a minimum of one minute; peak longitudinal deceleration of 15 g applied
\
I
for a minimum of one minute; and a peak transverse acceleration (any
direction normal to that line corresponding to longitudinal axis) of 25 g
I
!
I
!1
I
applied for a minimU!i1 of one minute.
3.5.4 }nterch-a_ngeability.
Tests shall be as specified in 4.7 .6.
All parts, subassembli<:>s, and assemblies
havin9 the same part number shall be physically and functionally inter-
changeable.
3.5.5
Interference_.
The s·et shall meet the requirements of MIL-ST0-461
Nethods C£03, CE04, RE03, and paragraph 2-6c of RCC-106-73.
Tests shall
be as specified in 4.10.
3. 5.6
Rf carrier frequency.
The frequency sha 11 be be tween 2200 and 2290
megahertz (r.!Hz) as specified by the contract or purchase order.
frequencies are:
2212.5, 2228.5, 2236.5, 2244.5. 2252, 2264.5 MHz (see
I
6.2{d)).
I
I
454, Requirement 9.
I
I
3. 5. 7 \oiorkmanshiQ...
3.6.1
Applicable
\>lorkmanshi p sha 11 be in accor·dance with 11I L-STD-
Exam·)nation shall be as specified in 4.8 .. 1.
System accuracy.
JDJ
commutated data channe1s shall be accurate
7
I
Il
I
I
62
within the limits specified in Table II.
Tests shall be as specified in
4.6.2.1.
3.6.2
Input power require_nients.
The equipment shall operate satis-
factori 1y from the fallowing pmver source:
(a)
115 VAC nns 400 Hertz (Hz) single phase.
(b)
50 watts maximum.
Tests shall be as specified in 4.6.2.2.
3.6.2.1
Ovel'load _p_rgtec!:ion.
Overload protection for the equipment
need not be provided.
3.6.2.2
Under voltage protection.
The equipment sha11 not be damaged
by voltages be10¥1 the minimum specified and shall automatically resume
normal operation >1hen the voltage returns within the limits specified in
3.6.2.
1
!
1
3.6.3 l.!2!22!:~i t_t§.I. modulation.
follo~li119 cen-·it;r deviations.
4.9.
Transm·itter· modu1,; 'on shall have the
Test shdl1 be as specified in 4.6.2:3 and
A11 peak c<.rder deviations shall be
mt~asured
with the Voltage
Controlled Oscillators (VCO's) unmodulated,
Peak Ca.,.rier Oevi a ti on Kilohertz (kHz)
NOil~flAL
!HUH
5.40 kHz Tone Burst
75
60
90
7.35 kHz Tone Burst
75
60
90
120
105
135
225
200
250
Signal. 0.7. + 0.01
Vrms at 21P2-2)
i
!
~lAX
--.....,-,·~
Video {40 kHz Test
II
I
MINIMUN
-·---
240 kHz
3.6.3.1
vco
Interr.;odulation and harmonic distortion.
Intermodulation and
63
I
l·
I,
i
I'
;:
I
'
!
harmonic distortion products shall be at least 40 decibels (dB) down
from the level of a 40 +5kHz video test signal of 0.7
~
O.OlVrms when
I
!
I'
operated under the service conditions specified in 3.5.2.
Tests shall be
as speCified in 4.6.2.10.
I'
l
f.
conditioning circuitry shall mateo data input voltages and impedances to·
I·
the
I
I.
co~mutator.
Throughout the service conditions and for a time duration
of 30 minutes, the gain and offset stability of the signal condHioning
circuitry sha11 remain within!. 2.0 percent of initia-l values, referenced
to the output signal measured at the input of the commutator.
Under
standatd conditions (see 4.6.1) and for a time duration of 90 minutes,
I
the gain and offset stability shall remain
within~
1.0 percent of initial
values referenced to the output signal measured at the input to the commutator.
Prior to fina"l assemo·ly, three point calibration, representing
zero, half, and fun scale voitage (vtithin one percent) shall be provided
!
for every data charnel.
\
I
j
The data sheets of this calibration shall be
delivered as specified in the contract or purchase order (see 6.2(f)9).
I"
Test sha11 be as sp2cified in 4.6.2.4.
l
I
ditions, thf! signal conditioner cards shell provide the outputs·specified
in Table II with inputs and loads as specified therein. Test shall
be as specified in 4.6.2.4.
II
3.£.4.2
Ton,_? burs_:L_9scil1a!2I:2.·
The tone burst osdl1ator circuitry
shan convert data input voltages into tone bursts.
The tests sha11 be
as specified in 4.6.2.11.
I
II
I!
3.6.5
Warm-up time.
The system shall achieve stablized operation
·64
within speification limits under all conditions in no more than 30
seconds after the application of operating voltages.
Tests shall be as
·specified in 4.6.2.5.
3.6.6
Noise.
The residual noise shall not exceed 12.5 millivolts
peak on any data channel (see 4.6.2.6).
3.6.7
Li~arity.
The signal conditioning input to output linearity
of each data channel shall be within 0.025 volts of a straight line through
Tests shall be as specified in 4.6.2.7 and 4.6.3.2.1.
the end points.
The
linear-ity of the 240 kHz VCO, shall be as specified in Drawing 106AS905.
3.5.8 Crosst9.11.
i,.
norm.::l or over
I
I
i
volt<~ge
millivolts peak.
3.6.9
The effect on any one channel by any combination of
signals to any other channels shall not exceed 2.5
Test shall be specified in 4.6.2.8.
RF POi'!'?.r
o~_2i.t__l:,.
The rf power output of the system, referenced
to the transmitter rf connector shall be two watts minimum under all combinatio~s
of line voltage and temperatures, except as noted in 3.5.3.1,· into
a 50 ohm ioad with mismatches up to 1.2:1 for all phase angles.
sha 11 be as spec iii ed in 4.6 .2. 9.
The transmi t.ter sha 11 not be damaged by
operation viith the output short circuited or open
3.6.10
Tests
Bf_carrier.~53ue~_to1er~ce.
circuited~
The rf carrier frequency
to1eranct; shall be tested as specifi-ed in 4.6.2.16.
3. 7 -B.f?_l.t~biJ.:i!X:
The equipment sha 11 have a spec;i fi ed mean-time-
betHeen-failure (1·1TBF (9
0
))
of 30 hours when tested and accepted as out-
lined under the requirements of 4.11.
3.8
I
I
t
'
)
I
~_tor~.
The transmitting set sha 11 not be damaged by. storage
of three years when stored in shipping and storage container Drawing 588AS350.
j!)
65
4.
QUALWTY ASSURANCE PROVISIONS.
4.1
Resoonsib·ility for insp_ection.
The supplier is responsible for
the perfonnance of a11 inspections and tests as specified herein.
The
supp1irer· may utilize his own or any other inspection facilities and services acceptable to the Government.
Inspection records of the examinations
and tests shall be kept complete and furnished to the Government as specified in the contract or order (see 6.2{f)4).
The Government reserves the
riJht to perform any tests or inspections herein v1here such inspections· are
deemed necessary to assure that suppliers and services conform to the
· pt•escribed requirements.
4.2
f.I:~subrrj_~si~!!___!esting.
No item, part, or complete equipment shall
be submitted by the contractor until it has been previously tested and
inspected by the contractor and found to comply, to the best of his knowl-
edge and belief, with all applicable requirements.
4.3
4.4
Clas3.ifi~tio!!_2.f_te·;ts.
Tests sha11 be classified as follov1s:
(a)
Prepr·oduction Tests (see Table I and 4.6}.
(b)
Quality Conformance Inspection {see 4.8).
(c)
Sampling Tests (see 4.9).
(<1)
R"1iability Assurance Tests {see 4.11).
Test
eguip~n~l·
The following test equipment, or equivalent
test equ·ipment approved by the procuring activity, shall be used:
(a)
115 VAC
rms 400 Hz po'·ler supply, one amp maY.imum.
(b) AC ard CC Voltage Standards, low output impedance.
· (c)
(d)
Digital Voltmeter, HP-3440A with 3445 AC/DC range unit.
Mu1t·imeter, Simps?n 260.
(e) Oscillator,
HP~404D.
I/
·66
I
....
j·.
I.
!t•
i
i
l'
l
(f)
Discriminator, Frequency Modulation (FM} Telemetr·y, HlR 4140.
(g)
Receiver, Microdyne llOOR, 2200 to 2300 ~1Hz tuning
range, 1.5 MHz Intermediate Frequency (IF) bandw-idth.
(h)
RF Wattmeter, Bird 43.
(i)
Coaxial Resistor, Bird 8080.
(j)
Oscilloscope, HP-140A.
(k}
Spectrum Analyzer; Nelson-Ross TA-1013, 0-400 kHz.
{1)
Signal Generator, FM, HP-3205A.
(m)
Frequency Counter, Beckman 6164 with 609
plug:-in unit.
(n)
Directional Coupler. Narda 30438-30.
(o)
Oecornmutator ANiUKQ-3 (XN-1).
(p)
01 scrim ina tor, FM Te 1 emetry, EMR 229 •.
4.4.1
Test
e:Ej_Rr~ent
calib-ration.
be cal-ibrated at least every
si:~
All equipment used in testing shall
months in accordance with f.lTL-C-45662 and
to the :'ICCuracy originally specified by the equipment manufacturer (see
6.2(f)9).
4.5
Pr~roduction
sample..
A preproduction sample of the equipment
shall be subjected to the preproduction tests of Table I at a laboratory
approved by the procuring activity,
shaH be based on no defects ·in the
Acceptan<:e of the preproduction samp 1 e
sample~
Furthet' production of the
equ·ipment by the supplier prior to approval of the preproduction sample
I
shell be at the supplier's risk.
I
!
I
I
i
4.6.1
Standill~-~
conciitions.
The following conditions shall be used
for performing bench tc,st on the equipment:
67
...
I
l
(a}
Temperature:
(h)
Altitude:
Sea level ·to 10,000 feet.
(c)
Vibration:
None.
(d)
Humidity:
Ambient (up to 90 percent).
(e)
Input
115 VAC rms, 400 Hz.
4.6.2
po~1er:
Functi_.9nal test.
Unless otherwise specified, the fo1lo'tling
operating characteristics shall be measured under standard conditions
(see 4.6.1).
Test methods will be supplied by the contractor in accord-
ance with 3.2(b) using the test equipment of 4.4.
4.6.2.1 _?_ystem accu!acy.
Requirement 3.6.1 s:'lall be demonstrated
using the inputs and loads specified in Table II using the set
Figure 1.
up of
This test shall be accomplished prior to final assembly of the
system even though equivalent measurements or individual circuit cards
have demonstrated the required outputs for given inputs.
3.6.2 and 3.6.2.2 sr.aii be demonstrated.
4.6. 2.3
Transmitter·· carrier de vi a ti on.
Verify that the transrni tter
car-rier devi.ation schedule conforms to 3.6.3 with no input signals to system.
4.6.2.4
~j_gnal .~r.liti£!.."!1._11_9
check.
The gain and offset stability
1-1ith r(lspect to the signa·! conditioner inputs shall be measured a.t the
input of the commutator (output of signa1 conditioner cards} {requirement
3.6A).
4.6.2.5
War~up
tims.
Stabilized operation, 30 seconds after turn-
on, sha11 be demonstrated dudng the functional check at lm1 tempera-
ture {see 4.7.1.1) (l·equirement 3.6.5).
4.6.2.6
Nois~.
Requirement 3.6.6 shall be demonstrated.
68
...
4.6.2.7.
Lineari.,:tr.
4.6.2.8 Crosstalk.
Requirement 3.6.7 shall be demonstrated.
While performing the functional check of 4.6.2.1
(Corrmutated Channels), verify that the channel irrmediately preceding and
following the active c:Jannel does not vary more than: 2.5 millivolts
(requ·irement 3.6.8).
The over voltage requirements
of.
3.6.8 sbal1 also
be demonstrated.
4.5.2.9 RF
po~~Jtput.
Output power shall be measured under
standard conditions (4.6.1) and environmental tonditions (tests 4.7 through
4.7.6). (requirement 3.6.9).
4.6.2.10 Transmitter modulation distortion.
I
Using the same set up
for check 4.6.2.3, observe the video spectrum at the output of an FM
telemetry receiver.
Verify that all spurious modulation components are
!
more than 40 dS below the amplitude of the 40 kHz video test signal
I
(requirement 3.6.3.1}.
l
I!
II
Ii
I
4.6,2 .. 11 Tone
During the functional checks,
bur·~L2.~fllat9rs.
app1y a 50 : 5 Vdc 200 + 50 microsecond pulse to 21P2-4.
Observe a 20 to
40 ms burst of 5.4 kHz+ l.S percent at the receiver output.
Repeat
the test with a - 2.0:;: 0.1 Vdc pulse applied to 21P2-6 and obse-rve a
burst of 7,35 kHz+ 7.5 percent (requirement 3.6.4.2}.
4.6.2.12 CELETED.
4.6.2.13 DELETED.
4.6.2.14
DELETED.
4.6.2.15
240kHz VCO.
from .the receiver output.
Filter and discriminate the 240 kHz VCO signal
Verify that the deviation of the center. frequency
of the 240 kHz VCO falls linearly 1vithin 204 to 276 kHz when + 2.5 and - 2.5
Vdc inputs·are applied to Jl90 pin 1-1.
I
l
I
I
Verify that the deviation of the
1'-/
69
I
I
I
J
l·
!
transmitter carrier center frequency meets requirement 3.6.3 when modui
lated by the unmodulated 240 kHz IJCO.
Decorrmutate the modulated 240 kHz
VCO di scrimi na tor output and verify the presence of a correct corr.mutated
fi
wavetrain as observed on an oscilloscope.
Typical input and output test
!
setups are indicated in Figures 2 and 3 (see 3.6.7).
I
frequency sha 11 be measured and recorded.
4.6.2.16
RF carrier frequency tolt;rance.
The transmitter carrier
The tolerance sha 11 be : 0. 003
percent of the assigned frequency under a l1 combinations of 1i ne voltage
II
and environmental conditions specified herein.
I
befor·e, during. and after each of the following environmental .tests (re-
l
4.7
Enyiri2nrnenta1 tests.
quirement 3.5.3).
The equipment shall operate satisfactorily
The results of the tests shan be forwarded, in writing,
to the procuriiVJ acdvi ty (see 6.2(f)5) only if required by contract.
t
I
4.7.1.1
.h~-~~~r!.:~..!::2!~i!.·
The transmitting set s.hall be temperature
condit:lo11ed and tested in accordance with MIL-STD-810, Method 502, Procedure I, except as follows:
Pr·eproduction_
Quality Acceptance
Irtsec:£.1JE_n~.__ _
Exposure
3~0 hDurs @ - 40°C.
3.0 hours @ - 40°C
Operati,;g
30 minutes @ - 40°C
30 minute$
Input Voltage
115 VAC 400 Hz
115 VAC 400 Hz
.@ -
40°C
The warm-up time measurement shall be made during this test (see 4.6.-2.5).
4.7.1.2
High
·~erature...
The transmitting set sha11 be temperature
conditioned and tested in accordance with MIL-STD-810,
Procedure I, except as
fo1lo~1s:
t
l
I
Il
/£
M~thod
501,
70
Temperature
Preproduction_ .
Quality Acceptance
Ins p ec t'-'i-"'o"-'.n__.
Exposure
3.0 hours @ + 71°C
3.0 hours @ + 71°c
Operating
30 minutes @ + 71°C
30 minutes @ + 71°C
Input Voltage
115 VAC 400 Hz
US VAC 400 Hz
4.7.2
Humidity.
The transmitting set shall be subjected to the
humidity te:;t of NIL-STD-810, Nethod 507, Procedure I, except that only
one complete cycle shall be conducted.
4.7 .3
Vibratj.Q!!_.
The transmitting set shall be subjected to the
vibration test of MIL-STD-810, Method 514.1.
Part 1, Test CurveD (Captive):
Part 2, Test Curve
Q (Flight):
2.0 hours.
30 minutes.
Part 3, Test Curve AG of Figure 514.1-4;
The equ·ipment shall be securely mounted to the vibration table such that
the vibration acceleration on the telemetry shan be the level specified
in HIL-SiD-810 when a tracking filter with 100 Hz bandwidth maximum is
used in the vib1·ation control loop.
4~7.4
Altitude.
The transmitter set shall be subjected to the low
pr-essure test of MIL-STD-810, 14ethod 500, Procedure II.
The specified
altitude sha11 be go,ooo feet (0.52 inches of Mercury}.
The low temperature
shall be - 40°C.
4. 7. 5
Shor~.
The trunsmi tti ng set sha 11 be subjected to the shock
test of NIL-STD-810, Method 516.1, Proceclure IV, except that the shock
pulses shall be 65 g peak,·half sine in shape, and a minimum of five ms
in duration.
4.7.6
Acceleration.
The transmitting set shall be subjected to the
acceleration test of MIL-STD,.810, Method 513.1, Procedure II.
\C:,
The peak
71
I
I
i
\
i
i
acceleration shall be 40 g in the fore direction, 15 g in the aft direction,
I
and 25 g in each of the four lateral directions.
i
I,
The duration of each
exposure shall be one minute minimum.
I
I
I
4.8
~lity confon~ance
inspection.
Quality conformance inspection
shall consist of the following:
(a)
Examination (4.8.1).
{b)
Manufacturing Run-in Test (4.8.2) where applicab1e.
(c)
Reliability Assurance Test {4.11).
(d)
Operational Test (4.3.3}.
I
i
I
I
I
I
I
I
Fai"l ure to meet any requirement specified herein sha 11 be considered
cause for rejection.
4.8.1
I
I
I
i
Examination.
Each equipment shall be examined to verify
compliance with the requirements for material, workmanship, form factor,
content, and presence of connections set forth in the latest revision of
Drawing 588AS605.
4.8.2
Manufacturin~un-i~.
The manufacturing run-in test
shall be utilized by the manufacturer to eliminate infant mortality prior
to the reliability assurance tests of 4.11.
The run-in test plan shall be
prepared by the manufacturer and submitted to the procuring activity for
approval prior to performing the test (see 6.2(f)6).
4.8.3 Q2erational
te~!·
The operational test shall consist of
the functional test (4.6.2) and rf power output under standard conditions
only (4.6.4.9).
4.8.3.1
Equip:nent failure.
The criteria for equipment failure
shall be as defined in MIL-STD-781.
4.8.3.2
Restorati~~-
Restoration of failed equipment shall be as
defined in MIL-STD-781.
1/
72
I
I
J
f '-
!
4.8.3.3
pispositio~
of equipment.
The disposition of equipment
used in reliability ass.urance testing and in preproduction testing shan
be as specified by the procuring activity in the contract.
I
II
I
i
I
4.9
Periodic production samples shall be s.elected
at random and shall be subjected to the Temperature Tests (4.7.1)
and Vibration Tests (4.7.3).
Samples shall be selected by the Government
Inspe·ctor in <}ccordance with the following:
Quantity of Equipment
Offend For Acceot:ance
~-
Ii
I
II
Quantity to be Selecte·d
For S~lin2L1 ~T~e~s~t_____
Ftrst 10
1
Next 50
1
Next 75
1
Next 100
1
1 for each additional 200 or fraction thereof.
4.9.1
I
Sa111piii!_9 tests.
Failur~L~~·
In the event of a f'.li lure, the Government
representative and procuring activity shall be notified immediately.
When .specified ·;n the contract or order (see 6.2{f)7), a report sh.,;ll be
submitted to the procuring activity upon completion of the test.
In this
report, the crmtr:>.ctor shall propose suitable and adequate design or
material cof'rections for all failures that occurred.
The procuring activity
shan reyi ew such proposa 1s and deterrni ne whether they are accep tab 1e.
4.10 Badio__1nt~rfere~~~·$t~.
Compliance with requirements of
3.5.5 shaJ l be demonstr•1ted with the radio inter·ference tests of t-IIL-STD-462,
Methods CE03, CE04, RE03, and paragraph 2-6c of RCC-106-73.
4.11
Re1iabilit.z
ass~e
sha11 be conducted using
tests_.
MIL-STD~781.
Reliability Assurance Tests
Tests as required by both the Quali-
fication Phase and the Production Acceptance (Sampling) Phase shall be
11
f·
'
73
I
conducted.
The test level to be utilized sha11 be as described under Test
Details, paragraph 4.11.3.
Classification and reporting of failures shaH
be in accordance with MIL-STD-781 and AR-34 (see 6.2(f)8).
Equipment
selected for the reliability assurance tests sha 11 have first passed the
examination test (4.8.1), manufacturing run-in test (4.8.2),and operational
te:5t {4.8.3).
4.11.1
Qualification phase.
Prior to the acceptance of equipments
under the contract or order, a minimum of three equi pments sha 11 be
tested as outlined in NIL-STD-781, under the section entHled "Qualification Phase of Production Reliability Tests."
The maximum number of
equipments to be used shall be those listed in Table V of MIL-STD-781.
The Accept/Reject Criteria shall be in accordance with Test Plan III.
Test levels shall be in accordance with 4.11.3.
4.11. 2
Produc~ i 0_0
:1cceptar.ce phase.
The equipment, throughout
production, shall be te:>ted as outlined in f.liL-STD-781 (as modified herein)
under the section entitled "Production Acceptance (Samplin·g) Phase of
Production Re l i abi 'ii ty Tests."
The Accept/Reject Criteria sha 11 be in
accordance with Test Plan XXIX of MIL-ST0-781.
ment produced shall be tested for six hours.
Specifically, each equipA run-in test shal1 be
performed prior to the six hour test on each equipment.
whether the riTBF is being
mf~t
To determine
at any time during the contract, the operating
test hours and the failures thereon (not count-ing run-in failures or run-in
operating time) shall be totaled and the results compared v<ith the reject
line of Test Plan XXIX of MIL-STD-781.
accoiT'.modate the data).
{Extend the line as necessary to
These totals shall accumulate so that at any one
time the experience from the beginning of the contract. is included.
At
the conclusion of each month the test results sha 11 be sent to the procuring
;a
. I
74
I
I
I
J
I
I
I
I
I
I
I
!
I
i
I
activity (see 6.2(f)8).
hours and test failures plotted on Test p·tan XXIX curves show a reject·
situation, the procuring activity shall be notified.
The procuring
activity reserves the right to stop the acceptance of equipment at any time
that a reject situation exists pending a review of the contractor's efforts
to imp1·ove the equipment, the equipment parts, the equipment workmanship,
etc., so that the entire compilation will show other than a reject decision.
4.11.2.1
Reduced testing.
When the test history indicates signifi-
cantly better results (in terms .of MTBF) than 30 hours testing shall be
reduced.
I
I
At any time, should the current total of test
Reduced testing shall be implemented as detailed below only upon
written authorization of the procuring activity, and the reduced testing plan
shall be used only when production is continuous,
(a)
I
When eight successive lots or tests have been completed
without the occurrence of a rejection decision, and the
I
observed MTBF (G
0
)
is equal to or greater than 45 hours,
the test time may be reduced to three hours per unit.
(b)
At anytime a reject decision occurs during testing at a
reduced level, corrective action shall be taken, and the test
shall be repeated using a test time of six hom·s (two cycles)
per unit.
Testing shall continue using the specified six
hours per unit until eligibility for reduced testing is
again established.
If the pr·oduction line is shut down
for 60 calendar days or longer, the test plan using six
hours per unit sha 11 be resumed.
4.11.3 Test details.
The test level, duty cycle, and operational
tests to be utilized during the r·eliability assur·ance. testing will be as
i
I
i
I
I
II
I
75
i
:i
follows;
(a)
Test level.
Temperature:
- 40°C to + 71°C.
A programmed
temperature chamber con tro 11 ed from the
base of the traTismi her shall be used to
control the transmitter base temperature
withi:n ~ 4°C of the steady state
temperature described by Figure 3.
Vibration:
Per MIL-ST0-810, Test Procedure II.,
Curve AG, Figure 514.1-4 (see Figure 4).
The vibration shall be applied to the
perpendicu1ar to the long1tudina1 axis
of the transmitting set for IO· minutes
at the + 71°C temp-erature level.
I
I
Heating Cycle:
Three hours (see Figure 3).
l
Cooling Cycle:
Time to stabilize at- 40°C.
Input Voltage:
115 VAC rms, 400 Hz, 1 0.
(b). Q!:!_cy cycle.
The transmitting set shall be turned off during
the cooling period and
ener:.:~ized
continuously during the
heating portion of the cycle.
(c)
Opera__!_i.!?..@Lte~~·
The performance characteristics to be
measured shal'l be part of th<" test procedures to be- submitted
and appr-oved by the procuring activity prior to the beginning
of the Qualification Test Phase of the Reliability Assurance
Tests.
76
I
II,
i
I!
i
5.
PREPARATION FOR DELIVERY,
5.1
Preservation and packa.sJ1!.9.·
The preservation and packaging
I
shall be in accordance with Drawing 588AS350, unless specified in the
l
contract order to be level A, B, or C (see 6.2.5).
!
f
l
I
I
!
5.1.1
PreservaJ:ion,.
Preservation for levels A, B, and C shall be in
accordance with MIL-P-116, Method III.
5.1.2
I
Packagin_g_.
(a)
I
I
Packaging shall be as follows:
Level A. Each Transmitting
----·conforming to
I
PPP-8~601,
Set shall be packed in a box
overseas type, Style B, Type 1.
The telemetry system shall be blocked, braced, cushioned, and
anchored
I
\oJi
thin the box in a manner to prevent movement
within the box and damage to .the contents.
I
(b)
Level
- -8. Each Transmitting Set shall be packaged as
specified in 5.1.2(a) except the box shall be domestic,
Sty.le B, Type 1.
(c)
Level C.
Each Transmitting Set shall be packaged to ensure
carrier acceptance and safe delivery to the destination at
the lowest rates in compliance with the Uniform Rate Classification
Rules or other carrier rules applicable to the mode of
transportation.
5.1.3
~re
parts.
When required, spare parts shall be preserved
and packaged to the same specifications as a complete Transmitting Set
except that the weight of the spare parts will determine selection of
i
I
I
!
j.
l
I
I
the style of the box.
5.2 MarkinJL.
MIL-STD-129.
Marking for shipment
sh~11
be in accordance with
II:
...
I
I
!
I
I
I
I
·:..·
6.
6.1
NOTES.
Intended use.
Telemetric Data Transmitting Set AN/DKT-47 is
intended for use in the AIM-7F missiles designated for NTE and PNT.
The transmission of missile data associated with the tests and exercises.
will be accomplished by use of the Telemetry Syste.m installed in place of
the Missile Warhead Section.
No special wiring harness is required.
Missile
safe, arm, and fuzing signals are provided by an MK 33 Mod 0 Safe and
Arm Device (S&A).
Space and mounting provisions are provided within the
telemetric data set for field installation of the S&A, which is gover·nment
furnished.
6.2
Ordering_j_ata.
Procurement documents should specify the
following:
(a)
Title, number, and date of this specification.
{b)
Quantity of Transmitting Sets AN/DKT-47(XMG-l) required.
(c)
Preproduction requi rernent (see 3.1) and date preproduction
rr~del(s)
(d)
is (are) required.
Specific transmitting frequencies for each set ordered
(see 3.5.6).
(e)
Level of preservation and packaging if shipping and storage
container (Drawing 588AS350) is not used.
PPP-8-601 is an
alternate requirement {see 5.1).
(f)
Technical data, if any, specified in the contract or
purchase order.
1.
Failure Reports {see 3.1.1(d)).
MIL-STD-781 for format.
2.
Sampling Plans (see 3.2(a)).
Use Figure 7 of
78
i
....
l'
I
l
I
I
I
!
I
3.
Test Inspection and Report Procedures (see 3.2(b)).
4.
Inspection Records (see 4.1).
I
5.
Environmental Test Results (see 4.7}.
6.
Manufacturing Run-In Test Plan (see 4.8.2).
7.
Sampling Test Failure Report {see 4.9.1).
8.
Reliability Test Failure Record (see 4.11).
9.
Calibration Sheets (see 3.6.4 and 4.4.1).
'
10.
I
I
I
Disposition of equipment (see 4.8.3.3).
(g)
Universal document number for test reports (if required}.
(h)
Quantity of preproduction models.
(i)
Disposition of equipment (see 4.8.3.3).
6.3 Satisfacto.!:,L_o_£eration.
Satisfactory operation shall be defined
as conforming to the requirements of this specification.
I
!
I
Ii
!
I
I
I
I
l
79
II.
Tabl~
Signal Conditioner Functional Test
NOTL Unless other>'li se indica ted, DC and AC
voltages accurate within 0.5 percent of the
specified value shall be applied. Voltage
measurements are taken with respect to ground
(21P5 pin WW). All source resistances shall
be + 1.0 percent. Operational amplifier
power supplies shall be set to+ 10 + 0.01 Vdc
and - 10 + 0.01 Vdc.
-
Source
Resistance
Pin
21P5-C
5.1K
D lOOK
F 150K
Input
(Vdc)
Commutator
Channels
0.0
- 2.5
- 5.0
26
0.0
- 2.5
- 5.0
22
-
19.625
- 7.646
- 5.409
- 3.360
2.282
6.569
l; 17
Min
Output (Vdc)
Nom
M3.X
- 2.502
0.100
2.375
- 2.497
0.028
2.553
- 2.492
0.156
- 2.540
- 0.052
2.386
- 2.487
0.013
2.513
- 2.436
. 0.078
2.641
2.480
0.043
0.515
0.91!6
2. 13')
3. fj3;3
2.586
0.001
0.475
0.909
2.089
2.500
-
2.376
0.087
0.556
0.985
2.182
3.108
-
2.730
-
H
lOOK
6.0
0.0
- 6.0
2, 18
- 2.558
- 0.025
2.432
- 2.494
0.000
2.494
- 2.432
0.025
2.558
L
68.2K
7.54
25.0
9.92
- 7.54
7
0.980
2.600
1.262
- 1.032
1.006
3.335
1.323
- 1.006
1.032
3.410
1.386
- 0.980
M lOOK
6.0
0.0
- 6.0
3, 19
- 2.558
- 0.0£:5
2.432
- 2.494
0.000
2.494
- 2.432
0.025
2.558
s lOOK
11.66
0.0
- 11.66
8
- 2.558
- 0.025
2.440
- 2.508
0.000
2.508
- 2.440
0.025
2. 558
80
Table II.
Continued
Source
Resistance
Pin
Input
(Vdc)
Commutator
Channels
Output (Vdc)
Nin
Nom
Max
+ 11.66
0.0
- 11.66
10
·- 2.558
- 0.025
2.440
- 2.508
0.000
2.508
- 2.440
0.025
2.558
19.0
27.5
28.5
40.0
24
2.031
0.885
0.708
- 0.981
2.260
1.042
0.899
- 0.749
2.364
1.208
1.067
- 0.556
VV 5K
0.0
2.6
4.8
9·
2.439
- 0.087
- 2.338
2.488
0.008
- 2.312
2.538
- 0.097
- 2.286
YY lOOK
0.0
2.5
5.0
6
2.434
- 0.073
- 2.628
2.486
- 0.007
- 2.500
2.539
0.057
- 2.374
lOOK
0.0
25.0
50.0
11
2.314
- 0.127
- 2.512
2.488
- 0.012
- 2.512
2.665
0.102
.. 2. 336
0
26.0
0.0
- 26.0
12
- 2.466
- 0.025
2.370
- 2.418
0.000
2.418
- 2.370
0.025
2.466
2 0
26.0
0.0
- 26.0
14
- 2.466
- 0.025
2.370
- 2.418
0.000
2.418
- 2.370
0.025
2.466
3 0
26.0
0.0
- 26.0
16
2.466
·- 0.025
2.370
- 2.418
0.000
2.413
- 2.370
0.025
2.466
6.2
0.0
- 6.2
27
- 2.363
- 0.025
2.248
- 2.305
0.000
2.305
- 2.248
0.025
2.363
6.0
21
- 2.287
- 0.025
2.175
- 2.230
0.000
2.230
- 2.175
0.025
2.287
23
- 2.287
- 0.025
2.175
- 2.230
0.000
2.230
- 2.175
0.025
2.287
21P5-W
lOOK
BB 499K
d
20J9-l
4
20K
5 20K
0.0
- 6.0
6
20K
6.0
0.0
- 6.0
d7
\
I
II
'I
81.
Table II.
Continued
Source
Resistance
Pin
Input
(Vdc)
Cowmutator
Channels
Output (Vdc)
Min
Nom
Max
20~19-7
20K
3.75
0,0
- 3.75
25
- 2.233
- 0.025
2.146
- 2.206
0.000
2.206
- 2.146
0.025
2.233
8
20K
3.75
0.0
- 3.75
5
- 2.233
- 0.025
2.146
- 2.206
0.000
2.206
- 2.146
0.025
2.233
0.0
2.5
5.0
15
2.438
0.155
- 2.172
2.491
0.219
2.056
2.543
0.282
- 1. 940
2.50
2.00
0.9
- 1. 75
13
2.450
1.960
0.882
- 1. 785
2.500
2.000
0.900
- 1. 750
2.550
2.04D
0.918
21J2-3 0
6
0
- 1.715