PicoSat Mission Examples and Design Suggestions. Department of Electrical Engineering National Cheng Kung University

Transcription

1 PICOSAT SYSTEM ENGINEERIN PicoSat Mission Examples and Design Suggestions Department of Electrical Engineering National Cheng Kung University

2 2 Contents Introduction Motivations Overview of international activities Launch vehicles Launcher Standard Review of previous missions Various University programs NSPO Projects of previous semesters (2002, 2003) Guidelines and suggestions Summary of mission Next steps

3 Classification of Satellites Large satellites: over 1000 kg Medium-size satellites: kg Mini satellites: kg Micro satellites: kg Nano satellites: 1 10 kg Pico satellites: kg Femto satellites: less than 100 g 3

4 Drivers of Nano/PicoSat Programs Education Provide students with hands-on experience System engineering approach with emphasis on multi-disciplinary collaboration Access to space Rapid development time Relatively low cost Launch vehicle: availability, affordability, and flexibility International cooperation New technology demonstration Miniature Nanotechnology Biotechnology Unique mission or scientific goal Public relationship 4

5 United States International Activities Many universities and research institutes Government organizations Europe Germany Denmark Norway Italy Asia Japan Korea Taiwan Others 5

6 Stanford University OPAL (Orbiting Picosat Automatic Launcher) Aerospace/DARPA ARTEMIS MTSat StenSat Sapphire Prof. Bob Twiggs CANSat CubeSat 6

7 CubeSat A standard on the mechanical design A standard set of launch interfaces is specified limiting the spacecraft to approximately 100x100x100mm cube in volume, and 1000g in mass. Students and other participants are encouraged to develop their own designs, but some companies provide suitable building blocks and sub-systems. 7

8 Can Sat Another standard Size is the same as a coke can GPS in Coca Cola 8

9 P-POD A standard on the mechanical interface Creation of a standard to facilitate the design process of small satellites. Deployment system to support the standard. Safe and reliable. Efficient and cost effective. Versatile. The P-POD has been fully qualified in both vibration and thermal-vacuum environments according to NASA worst case test levels. 9

10 First CubeSat Launch Successful launch on June Multiple orbit mission Picosats: Stanford University: QuakeSat Tokyo University, XI Tokyo Institute of Technology, CUTE-1 University of Toronto, Can-X Aalborg University Technical University of Denmark 10

11 MCS Components 11 Stanford University, QuakeSat Mission: Collect ELF earthquake precursor signals AX.25 Protocol Mission Data Files Health Files Research Tasks NORAD Tracking 2 line element sets Uplink Tasking Files, New Software Stanford Ground Station (unmanned) FTP Files Internet Control Results Requests QuakeFinder Mission Control Center (MCC) Additional Ground Stations (Fairbanks)

12 Mission University of Tokyo, XI Gathering the satellite health information via beacon signal Command uplink & data downlink Telemetry data broadcasting service On-orbit verification of the commercial-off-theshell (COTS) components. Main functions OBC PIC16F877 4MHz, 256kbytes EEPROM data recorder CMOS image sensor Telemetry Transmitter 430MHz, FM FSK AX bps Command Receiver 140MHz, FM FSK AX bps Beacon Transmitter, 430MHz band CW 50WPM Li-ion secondary battery, charged from solar cell Permanent magnet,libration damper Sensors: Solar cell current,voltage, Battery voltage, Charge current, Consuming current, Temperature, RSSI 12

13 Tokyo Institute of Technology, CUTE CUTE: CUbical Titech Engineering satellite The objectives are design/development of pico satellite equipped with bus components under the leadership of students, and reduce the total costs by using commercial off-the-shelf components. Mission Communication mission: CW transmitter, FM transmitter, protocol Sensing mission: acceleration, rate, and temperature Depolyment mechanism mission: solar battery 13

14 14 Aalborg University AAU CubeSat: for the involved students to achieve a great deal of knowledge about designing and constructing Space worthy technology, but the "scientific" mission of the AAU CubeSat is to take pictures of the surface of the Earth and particularly of Denmark by using the on-board camera. The images recorded by the satellite will later be transmitted to the ground station from where they will be distributed over the Internet and made accessible for the general public.

15 Technical University of Denmark The main payload of DTUsat is an electrodynamic tether for dumping the satellite. The tether is deployed using a novel yo-yo system, greatly simplifying construction and deployment. A calibrated test transmitter is flown as secondary payload. The satellite is 3-axis stabilized using magnetorquers, while attitude determination is done by a combination of a 3-axis magnetometer and 5 chip scale dual-axis sun angle sensors designed and built for this satellite. 15

16 University of Toronto, CanX-1 The Canadian Advanced Nanospace experiments (CanX) promote the development and testing of low-cost space technologies and push the envelope of performance that can be achieved with small low-power devices. CanX-1 technologies A Powerful CubeSat Computer based on an Atmel ARM microprocessor. Triple-Junction GaAs Solar Cells with Peak Power Tracking CMOS imagers for observation and Star Tracking Active Magnetic Control including B-dot Detumbling and 3-axis stabilization The satellite is a 10 cm cube, with a mass less than one kilogram. The satellite will generate about two Watts of peak power using direct energy conversion. More power will be available when peak power tracking is enabled. 16

17 NASA ISGEN Objective: Develop, design, assemble, and test a flight-ready autonomous spacecraft as a technology demonstration platform which will accommodate genomic research. Sample management Imaging Detection and analysis QuickTime?and a Video decompressor are needed to see this picture. 17

18 NSPO: YAMSAT YAM (Young, Amateur radio, Micro-spectrometer) developed by NSPO, Taiwan Battery Magnetic Coil Micro-Spectrometer CW Antenna x 1 TT&C Antenna x 1 X FOV θ δt θ δt DRU Antenna x 1 Magnetometer Magnetic Coil CW Antenna x 1 OBMU 18

19 Kansas University, KUTE Objective of the pathfinder: develop and operate a simple pico-satellite in low Earth orbit (LEO) Highlights: HAM transmitter and receiver Four dosimeters Digital imager Primary Payloads: EECS Camera Secondary Science Payloads: Measuring Space Environment Spacecraft Bus Temporary Data Storage Communications Subsystem Ground Station 19

20 CalPoly, CP1 & CP2 CP1: Provides a reliable bus system to allow for flight qualification of a wide variety of small sensors and attitude control devices. Carries a sun sensor developed and an experimental magnetorquer. Has undergone vibration and thermalvacuum qualification testing at NASA worstcase qualification levels. CP2: To provide a highly capable bus system that can support numerous small payloads. The ambitious mission concept includes duplex 1200bps digital communications, three-axis attitude determination and control, and substantial data processing and storage capability while still providing at least 33% of the spacecraft mass, volume, and power for payloads. 20

21 University of Hawaii Standard single Cubesat: Mea Huaka i Payloads Active antenna: grid oscillator Thermal sensor Attitude stabilization: hysteresis rods Self-steering 21

22 Cornell University, ICE Cube Mission: Ionospheric Scintillation Experiment Using GPS receivers as sensors to probe the variation of the ionosphere 22

23 Montana University, MEROPE Mission: measure radiation in the Van Allen belts. Which cause satellite components, particularly semiconductor and optical devices to degrade. The radiation also induces background noise in detectors, causes error in digital circuits, induces electrostatic charge-up in insulators, and is even a threat to astronauts. Payload: Geiger tube 23

24 Hankuk Aviation University, HAUSAT Mission Statement: The mission of HAUSAT-1 satellite is to offer graduate students great opportunities and help them understand the whole development process of satellite design, analysis, manufacturing, assembly, integration, test, launch and operation, and consequently make them specialists in the field of satellite development. Mission Collecting information on satellite position using spaceborne GPS receiver Experimenting with solar panel deployment mechanism Verifying home-made sun sensor Getting data related to health of satellite from various sensors 24

25 Cheng Kung University, PACE PACE: Platform for Attitude Control Experiment A double cube design Three-axis stabilization for pico-satellites Momentum biased wheel + magnetic coil Sensor suite integration for attitude determination: magnetometer, gyro, coarse sun sensor Dual CPU design 8051-based CPU MEMS sensor technology Temperature sensor Coarse sun sensor Coarse sun sensor Temperature sensor 25

26 26 PicoSat Projects in Previous Terms Examples of student picosat projects that have been proposed in the previous semesters are Taro: CCD Eclipse: Spaceway: Random: CCD CAFA Sat: Messenger: Thomas Sat: Formo Sat: UBI Sat: : Hot Sat: UV-B Lego Sat: Seed Sat:

27 Summary of Missions Technology demonstration: Miniature Payload Sensor, actuator, processor, communication Control, propulsion, health monitoring Constellation Formation flight Scientific discoveries: Space environment Data collection Material and signal properties Bio engineering 27

28 28 Actions Needed 1. Problem definition. What is the problem 2. Value system design. How to judge success? 3. System synthesis. What are the alternatives? 4. System analysis. How are alternatives related to objectives? 5. Optimization. Make the best of the alternative. 6. Decision making. Which alternatives? 7. Planning for action. Plan for the next phase.

29 Issues System tree: system subsystem component Organization: groups Resources Risk Schedule Constraints Cost Configuration management 29

30 Summary PicoSat program (system engineering) Challenge innovative students to get hands-on experience in the life-cycle of a space project. Experience the design/development/operation processes of small satellite system. Acquire the fundamental development technology and operation methodology of small satellite system. Promote interdisciplinary collaboration from a system engineering perspective. Encourage international cooperation among universities and research institutes. Preparation for the semester Identify the mission and resources Perform sensible analyses 30

31 Thank you 31