Space Radiation & Charging Cube Satellite (SPARCCS) Project

Size: px

Start display at page:

Download "Space Radiation & Charging Cube Satellite (SPARCCS) Project"

Harvey Potter
6 years ago
Views:

1 Space Radiation & Charging Cube Satellite (SPARCCS) Project Preliminary Design Review Nicholas Vuono, Project Manager Zacharias Macias, Electronics and Control Michael Buescher, Mission, Systems, and Test Kenneth Vu, Manufacturing

Background - Electrostatic Discharge (ESD) is a potentially-harmful anomaly that occurs in space from accumulation of electrons on spacecraft, called spacecraft charging - Improper shielding for

2 Background - Electrostatic Discharge (ESD) is a potentially-harmful anomaly that occurs in space from accumulation of electrons on spacecraft, called spacecraft charging - Improper shielding for a spacecraft s environment can lead to mission-threatening ESD events - Important to update models of space environments to prepare spacecraft for their intended environment to avoid harmful ESD

3 Mission Objectives & Profile - The project shall be a cube satellite designed to measure radiation and electron energy and density levels in compliance with NASA Spacecraft Standards - The cost of the project shall not exceed $ The project shall be completed by December 16th, 2015

4 Work Breakdown Structure (WBS) Chart

5 Level 1 Program/Project Requirements

6 Level 1 Program/Project Requirements 1. The project shall be managed by and operated in collaboration with the CSULB CubeSat Club, as defined by the terms and agreements within the CSULB CubeSat Club SPARCCS Project Contract - This requirement will be verified with a formal contract establishing a working relationship between the CSULB CubeSat Club and the SPARCCS Project 2. The cost of the project shall not exceed $ This value has been set by the CSULB CubeSat Club - This requirement will be verified if the cost of the project, outlined in a final budget document, does not exceed $800.00

7 Level 1 Program/Project Requirements 3. The size of the project s cube satellite shall be 3U, or 30cm x 10cm x 10cm, as defined by the CubeSat Wikipedia resource. All attributes of the project shall be structured to fit within this size limitation - This requirement will be verified by measuring the chassis of the cube satellite at the time of presentation 4. The SPARCCS Team shall conduct preliminary research to determine design requirements for a spacecraft charging and radiation sensing cube satellite in geosynchronous Earth orbit - This requirement will be verified by the submission of a final report of all design requirements to the President of The Robot Company

8 Level 1 Program/Project Requirements 5. The SPARCCS Team shall design and construct a mockup cube satellite to present on the day of the final presentation - This requirement will be verified by the President of The Robot Company 6. The SPARCCS Team shall design and develop a custom printed circuit board to simulate data collection and transmission to the end user - This requirement will be verified by an inspection and demonstration of the custom PCB presented to the President of the Robot Company 7. All of the above requirements shall be met by December 16th 2015, the day of the EE400D Final Exam, in compliance with the CSULB Academic Calendar - This requirement will be verified by the President of The Robot Company

9 Level 2 System/Subsystem Requirements

10 Level 2 System/Subsystem Requirements 1. The chassis of the mockup cube satellite shall be constructed with a material on the order of 110 mils of aluminum-equivalent shielding, as described in Section of Guide to Mitigating Spacecraft Charging Effects by Henry B. Garrett - This requirement will be verified by documentation of the thickness of the materials used for the mockup cube satellite chassis 2. The chassis of the mockup cube satellite shall be constructed using a CNC manufacturing process - This requirement will be verified by final inspection of the mockup cube satellite chassis

11 Level 2 System/Subsystem Requirements 3. The chassis of the mockup cube satellite shall be designed using publicly available models developed by Innovative Solutions in Space - This requirement will be verified by documentation of the source file for the model used for mockup cube satellite chassis design 4. The model of the mockup cube satellite will successfully complete a random vibrations simulation of Hz, as described in the NASA General Environmental Verification Standard (GEVS, GSFC-STD-7000) - This requirement will be verified by the results of a SolidWorks vibrations test simulation of the mockup cube satellite chassis model

12 Level 2 System/Subsystem Requirements 5. All electronics within the mockup cube satellite shall be mounted in place and grounded to the chassis to prevent damage or floating metal charge accumulation, as described in Sections and of Guide to Mitigating Spacecraft Charging Effects by Henry B. Garrett and JPL Division 51 employee Wousik Kim s lecture on iesd - This requirement will be verified with a digital multimeter to detect any ungrounded metals 6. All cables of the mockup cube satellite should be wrapped in aluminum foil and conductive tape to prevent iesd effects in correspondence with JPL Division 51 employee Wousik Kim s lecture on iesd - This requirement will be verified with an inspection of all cables used inside the chassis of the mockup cube satellite

13 Level 2 System/Subsystem Requirements 7. The mockup cube satellite will be powered by a single battery in order to operate independently - This requirement will be verified by inspection of the final power supply 8. The mockup cube satellite will use a Geiger-Müller counter to demonstrate the capability to measure radiation - This requirement will be verified by inspection of the radiation sensor inside the mockup cube satellite chassis 9. The mockup cube satellite shall simulate RF communication by using a Bluetooth module to send sensor measurements and display them graphically to the end user - This requirement will be verified by a software demonstration

14 Level 2 System/Subsystem Requirements 10. The mockup cube satellite shall include a printed circuit board with 3-axis vibration sensors, a temperature sensor, and a 9-degree-of-freedom chip - This requirement will be verified by inspection of the PCB 11. The SPARCCS Team shall conduct research on the power, communication, attitude control, and payload subsystems of cube satellites in order to determine the best approach for each subsystem on the SPARCCS Project. - This requirement will be verified by the submission of reports regarding each area of research listed

15 Design Innovation

16 Design Innovation Geosynchronous Earth Orbit (GEO) Sending Data GEO Communications Satellites have docking stations Cube will land on the Satellite and transfer data, data will then be sent to Earth How to get to GEO US Air Force EELV-Ring Program will launch SPARCCS into GTO A trajectory will be made to send SPARCCS into GEO Attitude Control Will stabilize cube to receive max Solar power Exit strategy Attitude control will boost Cube outside GEO and into space or into Earth to burn up in atmosphere

17 System/Subsystem Design

18 System/Subsystem Design We are designing SPARCCS satellite to be capable of spaceflight Our mockup is a model of the satellite meant to demonstrate its capabilities Some systems are different between the two because they serve different purposes

19 System/Subsystem Design - SPARCCS Power: A solar array will be used as the main power source. A battery will store and provide the energy while sunlight is unavailable, and a charging circuit will control the current flow. This will be connected to the LDO on the main board of the CubeSat. RF Antenna: An RF antenna will be needed to relay information to the ground through a communications satellite. The antenna will communicate through USART. Payload: The CEASE payload and sensors will be housed inside the top unit of the chassis and communicate with RS422. Attitude Control: Three reaction wheels, cold gas thruster, gyroscope and Earth sensor used to stabilize, orient, and deorbit SPARCCS. Ground Support Equipment Interface: An interface that the ground support equipment can plug into to transfer data before launch

System/Subsystem Design - Mockup Power: A solar panel, battery, and charging circuit will be included to replicate the power system of the satellite Bluetooth Module: A bluetooth module will be used

20 System/Subsystem Design - Mockup Power: A solar panel, battery, and charging circuit will be included to replicate the power system of the satellite Bluetooth Module: A bluetooth module will be used in place of an RF antenna. It communicates via USART and transmits data taken from sensors Geiger Counter: A Geiger counter will be used to measure radiation in the mockup. It communicates with the microcontroller via USART Piezo Sensors and 9dof Board: "Dummy" sensors to simulate telemetry of sensor information to end user. Ground Support Equipment Interface: An interface that the ground support equipment can plug into to transfer data before launch

21 System/Subsystem Design - Interface Matrix

22 System Resource Reports

23 System Resource Reports Power resource reports were necessary for both the SPARCCS and the mockup The SPARCCS needs to maintain power during periods with no light The mockup should operate independently long enough to demonstrate its capabilities A mass resource report was only necessary for the SPARCCS CubeSat standards limit the mass to 3.99kg

24 System Resource Reports - Power Budget Estimation Assume solar panels cover five of the six sides (83%) of the CubeSat At 2.3W each, 5 solar panels can provide approximately 11.5W As the CubeSat is tumbling, three of the six faces (50%) will be exposed to sunlight at once 11.5W*(83%)*(50%) = 4.79W

25 System Resource Reports - Power

26 System Resource Reports - Mass Mass is an important factor for the SPARCCS project, but not for the mockup

27 Design & Unique Task Descriptions

28 Design & Unique Task Descriptions 1. Trade-off Studies 2. Needed Simulations 3. Rapid Prototyping

29 Trade-off Studies Communication Method Power Supply Manufacturing Method Chassis Material

Traditional low gain antennas are far too weak to reach Earth

30 Trade-off Studies: Communication Method Communication from geosynchronous orbit is very difficult from a small satellite Traditional low gain antennas are far too weak to reach Earth from GEO High gain antennas are too big and require too much power

Trade-off Studies: Communication Method Low Gain Antenna Pros Low power usage Cheap Cons Cannot communicate directly with Earth Laser Communication Pros Low power usage Fast data transfer Cons

31 Trade-off Studies: Communication Method Low Gain Antenna Pros Low power usage Cheap Cons Cannot communicate directly with Earth Laser Communication Pros Low power usage Fast data transfer Cons Requires very fine attitude control Inflatable Antenna Pros Lightweight Does not require attitude control Cons Takes up 1U of space Susceptible to damage from space debris Not yet developed Expensive

32 Trade-off Studies: Communication Method Summary Laser communication requires extra parts (would require bigger than 1U CubeSat) Low gain antenna would require an extra satellite nearby dedicated to transferring data Inflatable antenna requires larger CubeSat, but will meet our communication requirements Conclusion Each option will require project revision. We will need to adjust our project mission and requirements and likely upgrade to 3U CubeSat to accommodate suitable communication method

Trade-off Studies: Power Supply Solar Arrays Pros Produces Constant power Lasts 40+ years Relatively Cheap Cons Can only be active when sun is pointed at Array Does not generate enough constant power

33 Trade-off Studies: Power Supply Solar Arrays Pros Produces Constant power Lasts 40+ years Relatively Cheap Cons Can only be active when sun is pointed at Array Does not generate enough constant power Battery Pros No need for external source Cons (540 Wh / 5 V )= 108 Ah High Capacity Lithium Battery: 75 Ah (68 Ah Can be utilized) 2 Lithium Batteries Necessary Dimensions : 12.4 cm x 7.3 cm x 2.9cm (Too big for 1U Cube)

34 Trade-off Studies: Power Supply Cont. Battery alone The High Capacity lithium Battery will not fit in a 1U sized cube Solar arrays alone Solar array does not supply enough power to run the SPARCCS Solar arrays and Battery together With the solar array charging the lithium battery for 14 hours a day, the battery will be able to supply the cube for two hours a day

Trade-off Studies: Manufacturing Method (CNC) CNC Pros Well-established method of production Proven to be more efficient than conventional machining

35 Trade-off Studies: Manufacturing Method (CNC) CNC Pros Well-established method of production Proven to be more efficient than conventional machining Capable of metal production Cost-effective for mass production Cons Takes Time Not ideal for rapid prototyping Harder to produce smaller, intricate parts

36 Trade-off Studies: Manufacturing Method (3D Printing) 3D Printing Pros Ideal for rapid prototyping Increased level of precision for smaller parts Cons Limited material selection Materials are expensive Lower Quality

37 Trade-off Studies: Chassis Material Relative Cost 5005 $24.27 per ½ thick, 1 x 1 sheet 5052 $24.27 per ½ thick, 1 x 1 sheet 6061 $24.23 per ½ thick, 1 x 1 sheet 7075 $50.00 per ½ thick, 1 x 1 sheet

38 Trade-off Studies: Manufacturing and Chassis Summary CNC will be used as the method of manufacturing the chassis Limited material selection for 3D printing 3D Printing production varies in quality CNC is a proven, well-established process CNC is compatible with metal Aluminum 6061 alloy will be used to produce the chassis Proven in its applications in aerospace (according to Amari Aerospace spec sheet) Second highest strength to weight ratio compared to 5005, 5052, and 7075 High corrosion and extrudability Cost-efficient

39 Needed Simulations Chassis Vibroacoustics Test Simulation The chassis will undergo a random vibrations test in each of the perpendicular axes (x, y, and z) to check for component and structural integrity in accordance with the NASA General Environmental Verification Standard (GEVS, GSFC-STD-7000) To be verified via Solidworks Chassis Shock Test Simulation The chassis will undergo an external shock test in which an externally induced shock will be applied once to each of the perpendicular axes (x, y, and z) to check for component and structural integrity in accordance with the NASA General Environmental Verification Standard (GEVS, GSFC-STD-7000) To be verified via Solidworks

40 Rapid Prototyping Faraday Cage The SPARCCS chassis will need to be constructed as a Faraday Cage to shield internal components against electrostatic and electromagnetic fields (Garrett 2012) Graphic from

41 Rapid Prototyping Exploded View 3U-sized CubeSat Model (30 cm x 10 cm x 10 cm)

42 Project Cost

43 Project Cost

44 Project Schedule

45 Project Schedule - Project scheduling will be conducted using ProjectLibre software tool - Development of formal schedule TBD. Brief outlines are provided Top Level Schedule:

46 Project Schedule System/Subsystem Level Tasks:

47 Project Schedule After ProjectLibre is configured for EE400D Tasks: - All tasks will be updated to model SPARCCS tasks - Gantt Chart will be designed corresponding to tasks - Project Completion Reports will be generated to monitor progress

48 Closing Remarks

49 Acknowledgements - California State University, Long Beach College of Engineering - NASA Jet Propulsion Laboratory - CSULB CubeSat Club - Arxterra - Dr. Henry B. Garrett - Professor Gary Hill

50 References Garrett, H. (2012). Guide to Mitigating Spacecraft Charging Effects. Hoboken, NJ.:Wiley. Walt, M. (1994). Introduction to Geomagnetically Trapped Radiation. Cambridge: Cambridge University Press.

51 Thank You

In the summer of 2002, Sub-Orbital Technologies developed a low-altitude

1.0 Introduction In the summer of 2002, Sub-Orbital Technologies developed a low-altitude CanSat satellite at The University of Texas at Austin. At the end of the project, team members came to the conclusion