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MPSAT-2
MISSION DESCRIPTION
MULTI-PAYLOAD SATELLITE PROGRAM
MPSAT-2
MULTI-PAYLOAD SATELLITE PROGRAM
Version: 1.02
Page: 2 of 8
CONTENTS
1.
Introduction .............................................................................................................. 4
1.1.
Multi-payload Satellite Program ............................................................................................ 4
2.
MPSAT-2 ................................................................................................................... 4
2.1.
2.2.
2.3.
2.4.
General description .............................................................................................................. 5
Optional characteristics ........................................................................................................ 6
Launch ................................................................................................................................. 6
3U cubesat images............................................................................................................... 6
3.
Hosted payloads ...................................................................................................... 7
3.1.
3.2.
MPSAT-2 payloads specifications ........................................................................................ 7
General requirements ........................................................................................................... 8
4.
Contact...................................................................................................................... 8
Figure 1: MPSAT-2 schematic view
TEST IN SPACE – Multi-Payload Satellite Program
Solar MEMS Technologies S.L. CIF. B-91794131. Parque Científico y Tecnológico Cartuja’93
c/ Leonardo da Vinci 18, Tecnoincubadora Marie Curie, Planta 1, Modulo 2-41092 Sevilla, SPAIN
Phone: +34-95-446 01 13
E-Mail: [email protected]
MPSAT-2
MULTI-PAYLOAD SATELLITE PROGRAM
Version: 1.02
Page: 3 of 8
IMAGES
Figure 1: MPSAT-2 schematic view .................................................................................................................. 2
Figure 2: Nano-satellite type 3U cubesat (30x10x10 cm) ................................................................................. 4
Figure 3: 3U cubesat platform ready for integration .......................................................................................... 6
Figure 4: 3U cubesat mechanical design .......................................................................................................... 6
Figure 5: into a 3U cubesat ready for test campaign ......................................................................................... 6
Figure 6: 3U cubesat mechanical design .......................................................................................................... 6
TABLES
Table 1: MPSAT-2 main characteristics ............................................................................................................ 5
Table 2: main specifications for hosted payloads .............................................................................................. 7
TEST IN SPACE – Multi-Payload Satellite Program
Solar MEMS Technologies S.L. CIF. B-91794131. Parque Científico y Tecnológico Cartuja’93
c/ Leonardo da Vinci 18, Tecnoincubadora Marie Curie, Planta 1, Modulo 2-41092 Sevilla, SPAIN
Phone: +34-95-446 01 13
E-Mail: [email protected]
MPSAT-2
MULTI-PAYLOAD SATELLITE PROGRAM
Version: 1.02
Page: 4 of 8
1. Introduction
This document introduces a brief description of a MPSAT-X mission, included in the Multi-Payload Satellite
Program, from TEST IN SPACE.
1.1. Multi-payload Satellite Program
Multi-Payload Satellite program is a fast service to evaluate and test new devices and technologies in orbit.
This service offers hosted payload slots in a nanosatellite and includes a full satellite mission, containing
launch and in-orbit operations, to place your payload in space and to carry out experiments. The program is
composed by nano-satellites, called MPSAT-X, that are launched every year.
2. MPSAT-2
The Multi-Payload Satellite MPSAT-2 is the first of the MPS program, and it is a 3U cubesat. It is planned to
start during 2015 and launch before 2017, with a lifetime up to 2018 at least.
Figure 2: Nano-satellite type 3U cubesat (30x10x10 cm)
TEST IN SPACE – Multi-Payload Satellite Program
Solar MEMS Technologies S.L. CIF. B-91794131. Parque Científico y Tecnológico Cartuja’93
c/ Leonardo da Vinci 18, Tecnoincubadora Marie Curie, Planta 1, Modulo 2-41092 Sevilla, SPAIN
Phone: +34-95-446 01 13
E-Mail: [email protected]
MPSAT-2
MULTI-PAYLOAD SATELLITE PROGRAM
Version: 1.02
Page: 5 of 8
2.1. General description
The main characteristics of the MPSAT-2 are the following:
PARAMETER
VALUE
SATELLITE
MPSAT-2
Platform
Cubesat
Size
Expected lifetime
3U
> 12 months
Orbit
Sun-Synchronous LEO
Mass
4 kg
ATTITUDE CONTROL
Pointing accuracy
5°
Attitude determination
5°
Actuators
Sensors
3-axis magnetorquer
4x Fine sun sensors
6x Coarse sun sensors
3-axis magnetometer
3-axis gyroscope
ELECTRICAL INTERFACE
Connector
PC-104
Energy capacity
20 Wh
Max current consumption
2000 mA
THERMAL INTERFACE
Exposure temperature
Operational temperature
from -10° to 60°C
from 0° to 45°C
LINK BUDGET
Antenna
Dipoles
Band
UHF/VHF
Downlink budget
4Mb/pass
INTERNAL COMMUNICATION
Platform node
Master
Payload node
Slave
Communicacion buses
I2C, UART, CAN, SPI
Table 1: MPSAT-2 main characteristics
TEST IN SPACE – Multi-Payload Satellite Program
Solar MEMS Technologies S.L. CIF. B-91794131. Parque Científico y Tecnológico Cartuja’93
c/ Leonardo da Vinci 18, Tecnoincubadora Marie Curie, Planta 1, Modulo 2-41092 Sevilla, SPAIN
Phone: +34-95-446 01 13
E-Mail: [email protected]
MPSAT-2
MULTI-PAYLOAD SATELLITE PROGRAM
Version: 1.02
Page: 6 of 8
2.2. Optional characteristics
The following characteristics are optional depending on the needs of every hosted payload.






Auxiliary power supply.
Auxiliary electronical systems.
Customized communication protocol, according to the main buses: I2C, CAN, UART and SPI.
Additional sensors.
Additional harnessing.
Others: under request.
2.3. Launch
The MPSAT-2 launch is planned to first quarter of 2017, and the orbit will be LEO, Sun-Synchronous, using a
Falcon-9 launcher.
2.4. 3U cubesat images
Figure 3: 3U cubesat platform ready for integration
Figure 4: 3U cubesat mechanical design
Figure 5: into a 3U cubesat ready for test campaign
Figure 6: 3U cubesat mechanical design
TEST IN SPACE – Multi-Payload Satellite Program
Solar MEMS Technologies S.L. CIF. B-91794131. Parque Científico y Tecnológico Cartuja’93
c/ Leonardo da Vinci 18, Tecnoincubadora Marie Curie, Planta 1, Modulo 2-41092 Sevilla, SPAIN
Phone: +34-95-446 01 13
E-Mail: [email protected]
MPSAT-2
Version: 1.02
MULTI-PAYLOAD SATELLITE PROGRAM
Page: 7 of 8
3. Hosted payloads
Every customer shall develop and adapt its own payload according to the technical specifications and
requirements of the mission and the satellite platform. TEST IN SPACE engineering team will support
customers during this payload design and development phase, including:
 Training course.
 Design manuals and guidelines.
 Space engineering consultancy.
 Project management protocols.
 Technical support.
3.1. MPSAT-2 payloads specifications
The MPSAT-2 satellite has 2U empty units for hosted payloads, with the following main specifications:
SPECIFICATIONS
VALUE
MECHANICAL INTERFACE
HOSTED PAYLOAD
Size
90 x 95 mm
Max height
85 mm
Max mass
1 kg
Connector
PC-104
Max energy
15 Wh per experiment
ELECTRICAL INTERFACE
Max current consumption
2000 mA per experiment
THERMAL INTERFACE
Exposure temperature
Operational temperature
from -10° to 60°C
from 0° to 45°C
COMMUNICATION INTERFACE
Platform node
Master
Payload node
Slave
Internal communicacion buses
Downlink to Earth
I2C, UART, CAN, SPI
4 Mb per communication
ATTITUDE DATA SOURCES
Actuators
Sensors
3-axis magnetorquer
4x Fine sun sensors
6x Coarse sun sensors
3-axis magnetometer
3-axis gyroscope
Table 2: main specifications for hosted payloads
TEST IN SPACE – Multi-Payload Satellite Program
Solar MEMS Technologies S.L. CIF. B-91794131. Parque Científico y Tecnológico Cartuja’93
c/ Leonardo da Vinci 18, Tecnoincubadora Marie Curie, Planta 1, Modulo 2-41092 Sevilla, SPAIN
Phone: +34-95-446 01 13
E-Mail: [email protected]
MPSAT-2
MULTI-PAYLOAD SATELLITE PROGRAM
Version: 1.02
Page: 8 of 8
3.2. General requirements
The payload requirements are summarized as follows:
 Requirements: requirements for each payload according to its own characteristics and features:
o Technical conditions:
 Power supply.
 Data volume.
 Recovery option.
 Pointing of the satellite.
 Auxiliary electronics.
o Warning: toxicity, gasses or liquids, thermal generation, blast warnings, others.
 Satellite interface: mechanical, thermal, electrical, communication.
The requirements are described in the document “General Requirements”, also called GDIR.
4. Contact
Contact us if you need more information about this flight opportunity. We will provide you any support or
information you may need:

Technical Sales Manager:
Manuel Rodríguez Halcón
[email protected]

Program manager:
José Miguel Moreno López
[email protected]

Mission coordinator:
Laura León Pérez
[email protected]
If you want to receive more information about our future flight opportunities and launches, fill the form in
the following link: keep informed about our flight opportunities.
TEST IN SPACE – Multi-Payload Satellite Program
Solar MEMS Technologies S.L. CIF. B-91794131. Parque Científico y Tecnológico Cartuja’93
c/ Leonardo da Vinci 18, Tecnoincubadora Marie Curie, Planta 1, Modulo 2-41092 Sevilla, SPAIN
Phone: +34-95-446 01 13
E-Mail: [email protected]