OUFTI-1
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OUFTI-1 Project
The objective of the OUFTI-1 project is to provide hands-on experience to students in the design, construction, and control of complete satellite systems that will ultimately serve as the basis for a variety of space experiments.
OUFTI-1 is a 1unit CubeSat and will be launched onboard the Vega maiden flight (scheduled for end-2010).
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Payload characteristics
OUFTI-1 will carry three payloads:
- D-STAR: digital amateur-radio communication protocol that allows the simultaneous transmission of voice and data. A complete understanding of the D-STAR protocol can be found on our website
- xEPS: experimental digitally-controlled electrical power supply, developed in collaboration with Thales Alenia Space ETCA
- High-performance (30%) solar cells, provided by AzurSpace
[edit] System overview
As any other satellite, OUFTI-1 will be made of different systems. The role and implementation of each one are listed below. For a more complete description, please feel free to refer to the documentation section on the OUFTI-1 website.
[edit] ADCS:
Because the telecommunication system does not require the satellite to point in one specific direction, the ADCS subsystem relies on passive magnetic stabilization.
It will use hysteretic materials alone or in conjunction with permanent magnets.
[edit] COM:
OUFTI-1 will use the amateurradio communication bands (435 MHz for uplink and 145 MHz for downlink). As mentioned above, D-STAR will be the payload. The AX-25 protocol will be used for TC/TM and a reliable telegraphy beacon should still be operational in case of D-STAR or AX-25 failure, so any ham-radio operator anywhere in the world will be able to listen to the beacon telemetry, and send it over to us.
[edit] EPS:
OUFTI-1 has two power controls and distribution (PCDU) units: one "classical" PCDU and one innovative PCDU proposed by, and developed in collaboration with, Thales Alenia Space ETCA.
[edit] MECH:
Antennas will be folded during launch and have to be deployed once in orbit. The role of the MECH subsystem is to design the retaining and deployment mechanisms. The retaining mechanism will hold the antennas in place during launch operation: the antennas will be wround around a support and maintained by a Dyneema wire. The deployment mechanism will allow a reliable deployment of the antennas: a resistor will melt the Dyneema-wire.
[edit] OBC:
The OBC system controls data flow aboard the spacecraft. Its main tasks involve supervision of OUFTI-1 operation, telemetry data formatting and storage, telecommand data decoding and management. It must also provide a time reference. The central microcontroller is the one provided in the Pumpkin's CubeSat kit (FM430 flight module with Texas Instruments single-chip 16-bit MSP430).
[edit] STRU:
OUFTI-1 will use the pumpkin structure. Finite element simulations of OUFTI-1 response to various launch loads are currently carried out to ensure its structural integrity. These simulations are performed using the commercial finite element software SAMCEF. Experimental verification using an electrodynamic shaker is also envisioned.
The spacecraft configuration is achieved using CATIA software. The objective is to position the different satellite components in an optimal manner (temperature and radiations issues) and within the available volume. Constraints on the location of the center of mass specified by thecubesat design specifications must also be fulfilled.
[edit] THER:
The thermal subsystem is mainly passive. Thermal control is achieved using carefully selected surface finishes and appropriate configuration. Thermal design verification is carried out using ESATAN-ESARAD softwares to ensure that all satellite components function within the prescribed temperature range. Experimental verification in a vacuum chambers of Centre Spatial de Liege is also will be performed.
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