µsada Solar Array Drive Mechanism (ESA Contract No /17/NL/PS)

Transcription

1 ISD Cubesat Panel µsada Solar Array Drive Mechanism (ESA Contract No /17/NL/PS) G. Cucinella - A. Negri - 11/09/2018

2 The Company IMT is a private SME, founded in 1991 and active in the space sector on two main types of activities: Systems Engineering: Design and Development of Nano/Microsatellites and relevant On-board units for space commercial, scientific and defence applications. Parts Engineering: Characterisation and Testing of EEE (Electrical, Electronic, Electro Mechanical) parts. IMT srl s Quality Management System has been formally certified by Det Norske Veritas (DNV) and declared compliant with the standard UNI EN ISO 9001:2008 (ISO 9001:2008). Certification number is CERT AQ ROM-SINCERT. The certification applies to the following application fields: Design and Development of equipment prototypes for Space and Defence. Engineering support in the field of systems and quality disciplines such as: Product Assurance, QA, Software QA, Reliability, Safety, Component characterization and tests, Materials and Processes. 11/09/2018 2

3 Company Organization Chairman Massimo Perelli Administration Ad Interim: Massimo Perelli 11/09/2018 3

4 IMT Plants Roma Valenzano (BA) 12 Employees Valenzano (BA) Main Office: Via C. B. Piazza, Roma - ITALY Tel.: Fax: imtsrl@imtsrl.it URL: Rome 8 Employees Technological Lab.: c/o Tecnopolis Via per Casamassima Valenzano (BA) Tel: /09/2018 4

5 IMT at glance IMT srl

6 IMT Main Customers 11/09/2018 6

7 Where we were - SADA for 3U Cubesat SADA aims to increase the on board available power energy It is composed of: Two independent Solar Arrays (SAW Solar Wings Assembly) Mechanisms / Logical Unit (SAC Solar Array Control) SADA project started in 2012 such as internal R&D program, later co-funded by Lazio Region (POR/FESR ). Nowadays the TRL is 3/4 11/09/2018 7

8 SADA for 3U Cubesat Advantages Increase of Orbit Average Power (OAP) for high performances missions Continuous sun tracking thanks to the 1 axis gimbal and slip rings; Autonomous or Slave Operation Modes; 2 independent Solar Array Wings; Modular and Scalable unit (3U CubeSat or upper) with no relevant re-design phase (only Solar Array Wings are affected) Tilt / compensation system for fast satellite integration Support for De-Orbiting (Life Time reduction at < 25 years) 11/09/2018 8

9 SADA for 3U Cubesat performances Power Transfer Output: Output Torque: max. 43W channel) 25 mnm Pointing accuracy: < 5 Step size: Configuration: 2 Solar Arrays (2 Channels) 6S3P / 3S6P (AzurSpace 3J30) Release Mechanism: Range of Motion: Sensors: 2 x 1.7A for each Solar Array Free rotation thanks to the Slip Rings 2 sun detectors (fine and coarse for each Solar Array) / Temperature Electrical Interfaces: Standard Cubesat Kit Bus 2 x 12 ways Molex Picoblade (to PDU) Power Supply: 5V / 3,3V Data links: Power Consumption: Mass: Idle: Holding: Tracking: SAC: WING: Total: CAN bus / I2C 160 mw 430 mw 450 mw 185 gr 275 gr (331 gr with wall panel and Thermal cutter) without solar cells 850 gr Compliant to: Cubesat Standard (over to 3U) Baseline: 3U structure 11/09/2018 9

10 SADA 3U - Design Architecture Solar Array Wing SAW Solar Array Control SAC Wall & Thermal Cutter Solar Array Wing (6S3P or 3S6P) with Sun Sensors (fine and coarse) Redundancy Thermal Cutter System on Wall Assembly Solar Array Control (Controller + Mechanisms) and Generated Power By-Pass 11/09/

11 SADA 3U - SAC - Solar Array Control SLIP RINGS ASSEMBLY SAC TOP VIEW Features: 2 x 9 ways Bi-Lobe Omnetics connectors (from/to Solar Array) 2 x 12 ways Molex PicoBlade (to PDU S/S) 2 x micro step motors (1:4096) 2 x16 ways custom slip rings Standard Cubesat Kit Bus (CKB) Cubesat Form Factor / Thickness: 12 mm Mass: 185 gr (including connectors) SLIP RING ASSEMBLY SAC BOTTOM VIEW 11/09/

12 SADA 3U Wall & Thermal Cutter Features: 2 Redundant Thermal Cutter System Deployment Yaw tilting to facilitate the mounting of SAC inside the Satellite (max. tilting around the center 10 mm) Wall frame to protect the satellite Conical clutch for increase the stiffness in the Stowed configuration 11/09/

13 SADA 3U - SAW Solar Array Wings Features: 2 Omnetic BiLobe connectors for power and data link (between SAW and SAC units) 2 photodiode (fine and coarse) for autonomous operation mode Temperature sensor 6S3P or 3S6P configurations (AzurSpace 3J30 Solar Cells); Solar Panels in FR4 RIGID-FLEX PCB (thickness 1.6 mm) Max power: 25W WINGS (3U Cubesat) 11/09/

14 SADA 3U Functional Tests These functional tests have been performed: Electrical Tamb Deployment cycles Tamb Functional tests on tracking algorithms (in Lab.) Coarse Photodiode Four operating areas Slope switching levels Two rotary mechanisms Fine Photodiode Two independent controls Azimuth independent Maximum Power Point Tracking Standard P&O algorithm 11/09/

15 SADA 3U Functional Tests 11/09/

16 SADA 3U Follow-on activities Due to the tests results, the following actions have been established to be implemented: Re-Design of SAW hinges and clutches (implemented but not tested yet); Compatibility with both solar cells: CESI (CTJ30 / CTJ-LC) and AZUR SPACE (3G30A) Future activities: Upgrade to 6U Cubesat Solar Array Manufacturing and Testing Electro-mechanical life time test Deployment Tamb Tmin Tmax Functional tests during Thermal Cycles Vibration test and Thermal Vacuum Cycles 11/09/

17 Where we are - µsada for 6U/12U Cubesats Currently, Under a contract with ESA (as part of GSTP), IMT is developing the miniaturized for Cubesat 6U and 12U. The objectives of the activity encompass the development and testing of a miniaturised (SADA) suitable for future utilisation on 6U/12U CUBESAT platforms in order to enable deployable and steerable solar arrays generating significantly increased power for RF payloads, high-speed downlink and electric propulsion. Contract N /17/NL/PS ON-GOING 11/09/

18 Where we are - µsada for 6U/12U Activities included: 1. Design and Development 2. Preliminary duration tests of critical parts 3. Qualification Test to reach TRL 6 4. Deliver a proto-flight model for a future IOD CubeSat mission to reach TRL 7 Currently, we are concluding the Preliminary Design Review (PDR) Completion forecast 3 rd Quarter /09/

19 µsada for 6U/12U Preliminary Design of SADA (Note that only one wing is in the block diagram) 11/09/

20 µsada for 6U/12U - Satellite Configurations Body mounted: With SADA: Enhanced Configuration: up to 49 Solar Cells for 6U (ca. 117W total) up to 56 Solar Cells for 12U (ca. 134W total) Standard Configuration: up to 42 Solar Cells for each Wing (ca. 100W total) 11/09/

21 µsada 6U/12U - Power Budget 6U The target of 90W is assured by the SADA with 42 each wing AzurSpace 3J Solar Cells. If power transfer in the range of W shall be considered, the SADA Enhanced Configuration shall be used. > 49 Solar Cells each wing for 105W generated power > 56 Solar Cells each wing for 120W generated power 12U Standard Enhanced Standard Enhanced SADA Delivered Power (W) Improvement Comparison 6U/12U Standard 6U Enhanced 12U Enhanced 6U / 12U Standard SADA 0% 16% 33% 6U Enhanced SADA 0% 14% 12U Enhanced SADA 0% Values Shall be EOL with 92% of efficency due to the electrical loss 11/09/

22 µsada for 6U/12U - Layout General architecture with data and power supply links 11/09/

23 µsada for 6U/12U - Layout External interfaces 11/09/

24 µsada for 6U/12U - Stepper Motor 11/09/

25 µsada for 6U/12U - Stepper Motor Preliminary Test Setup: 11/09/

26 µsada for 6U/12U Slip Ring 11/09/

27 µsada for 6U/12U SADM design SADM Preliminary family tree 11/09/

28 µsada for 6U/12U SADM design SADM in 3U SADA Design The new design for µsada (current design company reserved) 11/09/

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