CAHIER DES CLAUSES TECHNIQUES PARTICULIÈRES PUMA N Objet du marché : SUPPLY OF CUBESAT COMPONENTS FOURNITURE DE COMPOSANTS CUBESAT
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1 CAHIER DES CLAUSES TECHNIQUES PARTICULIÈRES PUMA N Objet du marché : SUPPLY OF CUBESAT COMPONENTS FOURNITURE DE COMPOSANTS CUBESAT Renseignements techniques : Sylvestre Lacour, Responsable scientifique : Téléphone : E- mail: sylvestre.lacour@obspm.fr Vincent Lapeyrere, Chef de projet : Téléphone : E- mail : vincent.lapeyrere@obspm.fr Lester David, Ingénieur système Téléphone : E- mail : lester.david@obspm.fr Renseignements administratifs : Ourdya Achelhi ; phone : ; E- mail : Ourdya.Achelhi@obspm.fr François Kine ; phone : ; E- mail : marches@dr5.cnrs.fr RESUME This document presents the requirements for CubeSat bus Type de document : Technical specification
2 SOMMAIRE 1 INTRODUCTION OBJECT ACRONYMS REFERENCES DOCUMENTS TECHNICAL SPECIFICATIONS GENERAL CHARACTERISTICS OF THE CUBESAT Scientific target Orbit Payload Attitude Standards DETAILED SPECIFICATIONS Payload ADCS Bus GENERAL REQUIREMENTS Documentation Acceptance condition Packaging Schedule for delivery Page : 2 / 10
3 CCTP CubeSat bus 1 INTRODUCTION 1.1 OBJECT The main goal of the project is the photometric study of the Beta Pictoris star system. The satellite will carry the payload: an opto- mechanical system and a specific electronic card for power and control. The ADCS will be placed in the center unit, the payload is located in one of the extremity of the 3U CubeSat, and the other one is dedicated for electronics components, including power, communication systems and OBC. LESIA laboratory based in Meudon, France is in charge for the development of the payload and the integration and validation of the CubeSat. For this, all devices and components mentioned in this call for tender will be integrated in clean rooms and tested under vacuum / vibration. A prototype of the payload was built in our laboratory to demonstrate feasibility: Figure 1: Opto- mechanical assembly of the prototype The object of this document is the description of the technical specifications of a bus supporting our payload in a 3U CubeSat. Page : 3 / 10
4 1.2 ACRONYMS ADCS CDHS CCTP CNRS EPS FOV HK ICD ICR LEO LESIA LOS OBC PCB POD RW SMF SSO TM/TC TERME DEFINITION Attitude Determination and Control System Command and Data Handling System Cahier des Clauses Techniques Particulières Centre National de la Recherche Scientifique Electrical Power System Field of View House Keeping Interface Control Document International Celestial Reference Low Earth Orbit Laboratoire d Etudes Spatiales et d Instrumentation en Astrophysique Loi sur les Operations Spatiales On Board Computer Printed Circuit Board Picosatellite Orbital Deployer Reaction Wheel Single Mode Fiber Sun Synchronous Orbit Telemetry/Telecommand 1.3 REFERENCES DOCUMENTS ## RÉFÉRENCE TITRE DATE [R 1] CDS- REV13- FINAL CubeSat Design Specification Rev /20/2014 [R 2] GSFC- STD- 7000A General Environmental Verification Standard for GSFC Flight Programs and Projects 04/22/2013 [R 3] PC104_Spec_v2_6 PC/104 Specification Version /13/2008 [R 4] LSP- REQ LSP Program Level P- POD and CubeSat Requirements Document 01/30/2014 Page : 4 / 10
5 2 TECHNICAL SPECIFICATIONS 2.1 GENERAL CHARACTERISTICS OF THE CUBESAT Scientific target The Beta Pictoris star is located in the southern hemisphere s sky declination: and right ascension: 05h 47m s. Science mode consists on a continuous observation of this star when it is visible from the spacecraft. Depending on the orbit, observational window will be around one hour Orbit To ensure a good observability of the star, the orbit (not defined yet) will be close from a 650km SSO. This kind of polar orbit is frequent for earth observation satellite and guaranties both observability (65% visibility of Beta Pic during the min orbit) and a reentry in the atmosphere compatible with the laws about space debris. French LOS (law on space operation) requires that a satellite in LEO shall not remain in orbit more than 25 years after the end of operations Payload The payload is the scientific instrumentation of the satellite. It is composed of 3 mirrors and their support: a 50mm parabola (M1), a 25.4x35.9mm elliptical mirror (M2), and a small flat mirror. The piezo stage is a parallelepiped of 60x60x25mm and the total mass for piezo/mirrors/support/fiber is around 700g. Mechanical integration for the fixation of piezo and mirrors supports is not define yet. The payload also includes the electronic power and control PCB holding the detector. Figure 2: Visualization of payload elements in a 10 cm cube Page : 5 / 10
6 2.1.4 Attitude The aperture of the payload always point in the direction of the star during science mode. From Earth, the angle between Beta Pictoris and the Sun is With this attitude, a 3U face will always be inclined 15.5 with respect to the Sun. Considering the declination of Beta Pic (- 51 ) and the latitude of Meudon ground station (45 ), science mode and communication mode shouldn t interfere. When the star is not in view, the payload can switch to a standby mode with low power consumption. Figure 3: Pointing direction of the Payload Standards All components and sub- systems have to fit within the CubeSat standards developed by California Polytechnic State University. See the reference document 1: CubeSat Design Specification revision 13. Electronic card like PCB shall fit the PC/104 specification. See reference document 3: PC/104 Specification Version 2.6. The System must resist to a typical acceleration of 14Grms during the launch (see reference document 2: General Environmental Verification Standard). If your sub- system doesn t comply with these standards, please indicate your own specifications. Page : 6 / 10
7 2.2 DETAILED SPECIFICATIONS Payload Parameter Value Unit Mass <800 G Power consumption <1.5 W Data to be stored 70 Mo/day Data to be transferred <0.5 Mo/day Volume 1 CubeSat Unit Power alimentation 3.3 / 5 Volt ADCS The system is an iadcs100 from Hyperion Technologies. You can find the main characteristics here: content/uploads/2015/07/ht- iadcs100- V0.95_Flyer.pdf Parameter Value Unit Mass <400 G Power consumption 1.5 W Volume 0.34 CubeSat Unit Power alimentation 5 V Bus This part describes the systems we need in two copies: one engineering and one flight model. Element Target Comment Structure Solar panels 3U No deployable 1U side free for payload Assuming 3W for ADCS and Payload Page : 7 / 10
8 aperture EPS & Battery 2.8W during solar eclipse UHF/VHF antenna UHF/VHF transceiver UHF dipole & VHF dipole 1 Mo/day OBC UART Storage up to 30Go Bus PICSAT- BUS- 01 Data handling PICSAT- CDHS- 01 PICSAT- CDHS- 02 PICSAT- CDHS- 03 Power system PICSAT- PWR- 01 PICSAT- PWR- 02 The satellite structural design shall be such that it will not distort the alignment of the payload The satellite shall be able to communicate with the Payload and ADCS through UART (RS- 422) OBC shall include Software Development Kit, RTOS, drivers and librairies for sub- systems Data production rate of the payload is about 70Mo/day. This data shall be stored for one year operation Payload and ADCS need 2.8 W in nominal mode. This power shall be provided even during solar eclipse at each orbit (maximum duration: 1/2h) Voltage provided by EPS shall be 3.3V and 5V with a tolerance of 0.1V. EPS shall have the capacity to switch off the voltage. PICSAT- PWR- 03 In standby mode, payload consumption is around 0.5W Solar panels PICSAT- PWR- 04 PICSAT- PWR- 05 PICSAT- PWR- 06 Ground Station Sun pointing deviation is 15.5 during science mode Solar panels shall be body mounted, with 7 cells per 3U side Solar panels shall cover all the CubeSat except for 1 unit side In the following we consider our ground station located in Meudon, France. Others station around the world with different parameters (antennas, transceiver ) may be considered. PICSAT- TRX- 01 PICSAT- TRX- 02 Our station will be equipped with a VHF up and a UHF down Yagi antennas. Both antennas can be upgradable for up&downlink Gain of VHF is 12.3dBd and UHF is 14dBd Page : 8 / 10
9 PICSAT- TRX- 03 PICSAT- TRX- 04 Engineering model The transceiver will be a ICOM IC A full communication mode is currently considered during station visibility, i.e. no science observation simultaneously The engineering model shall be functional, and have similar mechanical, electrical, and software interface as the flight model. No requirements on performance and standards (including vibrations tests) are asked on the engineering model. 2.3 GENERAL REQUIREMENTS Documentation Your answer to this call will be accompanied by documents where the following information is included: 1) A report of the measured characteristics (mass, volume, power consumption, performances) and parameters 2) An ICD describing the software interface and mechanical interface for each component 3) A CAD file compatible with CATIA will be provided for mechanical interface 4) Examples of mission (past and/or present) using each sub- system under operational conditions In case of selection, components shall be accompanied by the additional information: 5) The storage conditions 6) Cleaning procedures Acceptance condition The order and the final payment will only be accepted under the condition of successful tests and measurements which will be performed in our facilities Packaging For all lots, the components will be packaged as follows: Sealed protective envelope to air. Rigid box with internal identification number to the supplier. The box must be of a material compatible with use in ISO Room 8. Page : 9 / 10
10 2.3.4 Schedule for delivery Assuming signature of contract at date T0. T0+1month: Delivery of engineering mechanical structure for payload integration T0+2month: Delivery of the rest of the engineering model T0+4month: Delivery of flight model If you cannot adapt to this schedule, please propose your own in your reply to this call. Page : 10 / 10
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