GASP Preliminary Design Review

Transcription

1 GASP Preliminary Design Review Johns Hopkins and University of Maryland Brianna Brassard, Marie Hepfer, Nick Lybarger, Chris Mogni, Krysti Papadopoulos, Lauren Powers, Corrie Russell, Kristy Weber 11/12/2012 1

2 Purpose of Confirm that: Science objectives and required system performance have been translated into verifiable requirements Design-to specification can be met through proposed design (trade studies) Project risks have been identified, and mitigation plans exist Project management plan is adequate to meet schedule and budget Project is at a level to proceed to prototyping of high risk items 2

3 Presentation Content Section 1: Mission Overview Mission Overview Theory and Concepts Concept of Operations Expected Results Section 2: System Overview Functional Block Diagram Drawings/Pictures of Design Critical Interfaces (ICDs?) System/Project Level Requirement Verification Plan User Guide Compliance Sharing Logistics 3

4 Presentation Contents Section 3: Subsystem Design Organizational Chart Structures Power Science Command and Data Handling Software Other jessicaswanson.com 4

5 Presentation Contents Section 4: Initial Test/Prototyping Plan Section 5: Project Management Plan Schedule Budget Availability Matrix Team Contact info 5

6 Mission Overview Name of Presenter 6

7 Mission Overview: Mission Statement Primary Objective: Measure Electron Density in the E region (90-120km) Secondary Objective: Test water-tight container for future use with aerogels in upper atmosphere research 8

8 Mission Overview: Mission Requirements Project requirements The GPS receiver shall survive the flight The GPS receiver shall track GPS in flight Shall provide TEC to one satellite Should expose the aerogel sample to space Should not permit dissolution of aerogel Minimum Success criteria The GPS is able to collect data The aerogel is exposed to space and is retracted into the container crestock.com 9

9 Mission Overview: Mission Statement Who will this benefit/what will your data be used for? Increase understanding of electron density of E-region Test novel technique for measuring electron density of E-region Container provides preliminary test for future JHU team experiments with Aerogels 10

10 Mission Overview: Expected Results GPS: Expect to measure TECs The TECs will be used to derive an E- region profile Aerogel mission: Expect to return aerogel container with sensor readings 11

11 Mission Overview: Theory and Concepts GPS Ionosphere is dispersive Therefore, EM waves travelling along same path at different frequencies travel at different velocities Dual frequency GPS signals return from satellite at different times This is called a phase difference Phase difference ~ TEC TEC: Total Electron Content Electron density profile calculated by relation: N(x, y, z, t) ~ dtec/dt 13

12 Mission Overview: Theory and Concepts What other research has been performed in the past? Dual Frequency GPS flown on many previous space missions Electron density measured by interferometry, radio occultations, etc in past Measurement by phase differences with DF-GPS is a novel technique 14

13 Mission Overview: Theory and Concepts Aerogels Aerogels have been used on the Star Dust mission to collect interstellar particles Possibility of studying particle composition and other properties of upper atmosphere using aerogels Sounding rocket missions with aerogels have been unsuccessful due to water contamination Small quantities of water will dissolve aerogels Proper containment and collection system necessary for any successful scientific mission 15

14 Mission Requirements: Minimum success criteria The GPS is able to collect data The Aerogel container returns on-flight data crestock.com 17

15 Mission Overview: Expected Results Expect to measure TECs The TECs will be used to derive an E- region profile Aerogel mission: expect to return aerogel in container intact 19

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17 Mission Overview: Concept of Operations Receiver should power up ten minutes before flight Receiver should stop recording at chute deploy The Aerogel actuated gate valve should open at point B and close at point D Linear actuator pushes aerogel outside of vacuum chamber and return aerogel to chamber between points B and D See ConOps on next slide for definitions of point B, point D, and chute deploy 17

18 ConOps Altitude t 1.3 min Altitude: 75 km Event A Occurs t 1.7 min Altitude: 95 km Event B Occurs Apogee t 2.8 min Altitude: 115 km t 4.0 min Altitude: 95 km Event C Occurs t 4.5 min Altitude: 75 km Event D Occurs End of Orion Burn t 0.6 min Altitude: 52 km t 5.5 min Chute Deploys t = 0 min -G switch triggered -All systems on -Begin data collection t 15 min Splash Down

19 System Overview Name of Presenter 23

20 Design Overview: Aerogel Experiment Utilization of heritage elements: The University of Wyoming conducted an experiment in 2010 that was designed to collect particles using aerogel. Mission was unsuccessful due to aerogel contamination. Wyoming s design utilized an extendable arm. Similarly, our design uses a linear actuator to expose aerogel to outside conditions. Major Modifications: Structural design goal focuses on the preservation of the aerogel. Chamber and actuated gate are designed for vacuums. Prevent gasses or liquids from leaking in and contaminating the aerogel. 24

21 Design Overview: Aerogel Experiment Continued Major technology dependencies: Utilizes a position sensor in order to determine when the gate valve is open and closed. Linear actuator moves aerogel sample linearly, exposing it to outside conditions for particle collection. Actuated gate valve opens and closes the main chamber. Allows aerogel sample to pass through. Maintains vacuum inside chamber and protects sample from outside conditions (i.e. liquids and gases that are capable of contamination)

22 Design Overview: GPS Experiment Utilization of heritage elements: Dual frequency GPS have been flown Major Modifications: TEC measured in Radio/RF, but not in GPS frequencies. Major technology dependencies: Multiple satellites tracked with static and real time kinematic acuracy Dual Frequency, Omni Directional Antenna needed.

23 Aerogel Functional Block Diagram Key Parallel Bit Telemetry Power RS232 RS232 GPS Antenn a Battery Switch Power Block MCU Telemetry Actuated Gate Valve Aerogel w/ Linear Sensors Actuator Aerogel Vacuum Chamber

24 Design Overview: Aerogel System Drawings 3 Aerogel System consists of four main parts: 1. Actuated Gate Value 2. Back plate with Linear Actuator 3. Main Chamber 4. Aerogel Plate (inside) See Subsystems for detailed drawings and descriptions of each component

25 Design Overview: Aerogel System Drawings

26 Design Overview: GPS Casing

27 Design Overview: Antenna TW3400/TW3402 GPS/GLONASS Antenna

28 Subsystem Definitions AGV: Actuated Gate Valve ANT: Antenna AS: Aerogel Sample EPS: Electrical Power System GPS: GPS and its housing/casing LA: Linear Actuator VC: Vacuum Chamber VCF: Vacuum Chamber Flange STR: Structure

29 Critical Interfaces Interface Name GPS/STR GPS/ANT GPS/EPS ANT/STR Brief Description The GPS will be attached to the RockSat-X deck rigidly and withstand constant accelerations of 25 G s, impulses of up to 50 G and temperatures up to 500 F without being compromised. The GPS' male port interfaces with the Antenna's TNC female connector. Data transmited from the GPS to the Rocket's ports will be in standard form based on the pin assignments specification sheet. GPS will NOT draw power from the EPS. The Antenna will be attached to the RockSat-X deck rigidly and withstand constant accelerations of 25 G s, impulses of up to 50 G and temperatures up to 500 F without being compromised. Potential Solution Durable materials such as aluminum will be used to avoid failure from these stresses. Teflon coated high temperature wire will also be considered to avoid heat damage. Lines running between the GPS and Antenna will be insulated and kept clear of moving parts. Connectors must remain fixed throughout flight. Ports.and connectors will be tested to withstand mechanical stresses, high acceleration, impulses and temperatures. Data bits should not be compromised. The antenna will be bolted to the deck tested to withstand mechanical stresses, high acceleration, impulses and temperatures. Bolts will be of a low coefficiant of expansion so as to not fracture the deck.

30 Critical Interfaces Interface Name Brief Description Potential Solution EPS/STR AGV/EPS AGV/VCF LA/EPS LA/AGV VC/STR LA/AS The electrical power system will be attached to the RockSat-X deck rigidly and withstand constant accelerations of 25 G s, impulses of up to 50 G and temperatures up to 500 F without being compromised. The actuated gate valve motor will be interfaced with the electrical power system so that the gate will be opened and sealed shut at the appropriate time. The actuated gate valve motor must successfully provide a vacuum seal before and after deployment of the aerogel sample. The seal will prevent contaminants from entering the aerogel container and destroying the experiment. The linear actuator will be connected to the electrical power system through a port hole at the bottom of the vacuum chamber. The linear actuator will respond by pushing the aerogel in and out of the vacuum chamber when necessary. The linear actuator will be programmed so that it will be extended only when the gate is open, and immediately brought back into the pressure vessel at the appropriate time. The vacuum chamber will be fixed firmly to the RockSat-X deck. This will be done in a manner so that the pressure vessel will withstand withstand constant accelerations of 25 G s, impulses of up to 50 G and temperatures up to 500 F without being compromised. The aerogel sample will be contained in a manner so that it will be rigidly fixed to the linear actuator at all times. Durable materials such as aluminum will be used to avoid failure from these stresses. Teflon coated high temperature wire will also be considered to avoid heat damage. Lines running between the motor and power supply boards will be insulated and kept clear of moving parts. A custom ordered gate valve will be chosen that will interface well with the flanges of the VC and withstand thermal stresses in order to keep the vacuum sealed. The port that feeds the EPS to LA will be designed accordingly in a custom order chamber so the connections will remain fixed throughout the flight. Sensors TBD will allow for the AGV to close only when the LA is completely inside of the vacuum chamber, to avoid the arm of the LA from keeping the gate permanently open. The pressure vessel will be design in a manner TBD so that the stresses will not cause failure at its interface with the RockSat-X deck. A structure to contain the aerogel apprppriatly will be designed so that the mechanical stresses will not cause loss or contamination of the aerogel.

31 Requirement Verification At the level you should highlight the most critical (Top 3?) system and project level requirements and how they will be verified prior to flight (an example below). Requirement Verification Method Description The GPS receiver shall receive data from launch until chute deployment. The aerogel vacuum chamber shall keep a complete seal before and after the experiment is performed. The full system shall fit on a single RockSat-X deck The sytem shall survive the vibration characteristics prescribed by the RockSat- X program. Demonstration Analysis Inspection Test We will demonstrate that the reciever works at various altitudes and through simulation software. The system s dynamical characteristics will be derived from SolidWorks, thermal and force simulations will be run to demonstrate these functions. Visual inspection will verify this requirement The system will be subjected to these vibration loads in June during testing week. 30

32 RockSat-X User s Guide Compliance (Corrie) Rough Order of Magnitude (ROM) mass estimate Estimate on payload dimensions Payload space given: diameter = 12 in. (minus keep out area) height = 5.5 in. Deployables/booms? How many ADC lines? Do you understand the format? We are given ten lines Asynchronous use? Do you understand the format? Parallel use? Do you understand the format? Power lines and timer use? What do you know so far? CG requirement Do you understand the requirement Are you utilizing high voltage? 31

33 Sharing Logistics We are sharing with West Virginia University (WVU). We are unsure what their mission objectives are. We are going to try to reach out to them after the is completed. grandpmr.com 32

34 Subsystem Design Name of Presenter 33

35 Subsystem Design: GPS Power Subsystem independently powered by Li-ion 7.2V 1.37 Ah battery Up to 10 hrs runtime Data 67 Bytes for NMEA 0183 (i.e $GPXXX, *xx <0D><0A> ) 67B *100 Hz *330s in flight=2.1 MB of recorded data 256 MB of internal storage Mechanical and Electrical Interfaces Reciever interfaces with Antenna and Rocket Weight 435g (reciever) + 150g (antenna) = 585g total for Subsystem Critical Technology Used GPS reciever: JAVAD GNSS Alpha Dual feed omnidirectiona Antenna: Tallysman TW3402 Current Issues Must develop waterproof and insulated housing for reciever grandpmr.com 34

36 Subsystem Design: Aerogels Aerogel Subsystems Mechanical Subsystems Aerogel Experiment Electrical Subsystem Actuated Gate Valve Linear Actuator

37 Subsystem Design: Actuated Gate Valve Power Activated by MCU to open and close valves at appropriate times 24 VDC Mechanical and Electrical Interfaces AGV interfaces with EPS, and directly to VCF Weight ~1300 g Critical Technology Used Allows for aerogel sample to be kept as vacuum before and after experiment to avoid contamination and destruction of aerogel Current Issues Must develop plan to make sure AGV will work properly Must decide on which gate valve/motor, potential is one of the rectangular gate valves from MDC Vacuum graphics/img2121.jpg 37 grandpmr.com

38 Subsystem Design: Actuated Gate Valve Drawings Approximate Dimensions: Height: 2.25 with 2.5 motor attachment (top) Length: 2.5 long with 0.2 flange extending on backside for attachments Width: 0.75 Gate Dimensions: 2.0 x 1.0 (length x height) **Final Dimensions will be determined by custom order and product constraints.

39 Subsystem Design: Aerogel Chamber Drawings

40 Subsystem Design: Side and Top View Drawings

41 Subsystem Design: Linear Actuator Power Activated by MCU to extend and bring aerogel back into chamber 12 VDC Mechanical and Electrical Interfaces LA interfaces directly to the VC, EPS, and aerogel Weight ~1500 g Critical Technology Used Responsible for exposing aerogel directly to space environment Current Issues Must develop a plan to motorize LA with space constraint Must decide on which linear actuator/motor, potential is the Bug DC92x-low power DC servo motor from Ultramotion 41 grandpmr.com

42 Subsystem Design: Linear Actuator Drawings

43 Subsystem Design: Aerogel Plate Drawings Attached to linear actuator

44 Subsystem Design: Aerogel Experiment Data Aerogel acts a storage mechanism for particles being studied Further analysis after retrieval will verify results of experiment Mechanical and Electrical Interfaces Aerogel sample is directly interfaced with the LA Weight ~ g Critical Technology Used LA Current Issues Must develop a way to properly interface aerogel with LA without compromising the aerogel grandpmr.com 44

45 Subsystem Design: Electrical Subsystem Power Subsystem powers motors which are actuated during the duration of the aerogel experiment Data An MCU will be programmed to send the proper signal to turn on each motor for the valve and linear actuator individually Mechanical and Electrical Interfaces Interfaces with AGV, LA and Rocket Critical Technology Used Rocket interface, LA, and AGV Current Issues Must develop proper electrical and software components grandpmr.com 45

46 Organizational Chart Name Marie Hepfer Chris Mogni Nick Lybarger Lauren Powers Krysti Papadopoulos Corrie Russell Brianna Brassard Kristy Weber Darryn Waugh Ethan Miller Jonathan Fentzke Role Project Manager Lead Aerogel Scientist Aerogel Build Lead GPS Team Lead Lead Electrical Engineer Lead GPS MechE Aerogel Team Lead Faculty Advisor GPS APL Mentor Aerogel APL Mentor 36

47 Test/Prototyping Plan Name of Presenter 37

48 Test/Prototyping Plan GPS Date Test Risks Mitigated/Functionality Tested Nov Sea Level Test Electrical functionality. Power-up in timely fashion, satellites tracked, and location cross verified with other GPS, ie Iphone. Data stores in memory. Nov-Dec Antenna Test Antenna truly omni-directional. Diagrams of maximum field of view created. Verify that Antenna will work inside housing material. Dec-Feb Flight Simulation Data collected at various altitudes and locations (with weather baloon). Simulation software used. Jan-Feb TEC inferring test Dual frequency capability verified. TEC algorithm developed and referenced with heritage data. Jan-Feb Waterproof test Develop and test casing tested for waterproofing. Feb-Mar Thermo-Vac test Rocket and space environment simulated. Casing Internal temperature within -30 C and +55 C Mar-Apr Integrated Shock Test Flight's Gees, linear velocity, and rotation simulated. GPS works at real time kinematic accuracy. Apr Project Integration Fits into payload board. Test with other systems. 38

49 Test/Prototyping Plan Aerogels Order MCU (Late November) Design and custom order vacuum chamber (Late November) Order linear actuator and actuated gate valve according to vacuum chamber specs (Late November) Test functionality of motors (January-February) Develop algorithm for gate valve actuation and use of linear actuator (December-February) Test algorithm with motors without the use of the vacuum chamber (for functionality) (February-March) Assemble vacuum chamber with various motorized components integrated (March April) Further test payload for mechanical and electrical functionality (April-June) If possible, test in thermo-vac to prove capabilities of payload (As time permits) 39

50 Project Management Plan Name of Presenter 40

51 Schedule What are the major milestones for your project? See Previous Slides for Testing and Prototyping Timetable 12/10/2012: CDR Due 01/28/: Action Item Review 02/18/: Individual Subsystem Testing Reports Due 03/18/: Payload Subsystem Integration and Testing Report Due 04/15/: First DITL Test Report Due 05/06/: Beginning of Weekly Teleconferences December 2012-January : Ordering Parts January : Initial Build/Prototyping 01/28/ /18/ /18/ /19/ /25/ /18/ /19/ /08/ /15/ /16/ /06/2 013 Post Firs Indi Ind Tele Exp Cus Payl Rep Payl Rep Fina Firs DIT Wee 41

52 Budget Margin: 0.25 Budget: $7,500 Last Update: 11/12/12 Subsystem Item Supplier Cost Number Total Notes Testing Materials $ $ Estimated cost to test system Aerogel Linear Actuator Ultramotion $ $ Vacuum Chamber MDC Vacuum $5, $5, Gate Valve Actuator MDC Vacuum 1 MCU Sparkfun Electronics $ $30.00 GPS GPS Antenna Tallysman Wireless $ $89.55 Unlocked GPS Module JAVAD GNSS $ $0.00 Provided by 42 APL at no charge

53 Team Availability Matrix Fall 2012 RS- X Team Availability Matrix Time Monday Tuesday Wednesday Thursday Friday 7:00 AM No No No No No 8:00 AM No no no No No 9:00 AM No no No 10:00 AM No No No 11:00 AM No No no No No 12:00 PM No No No No No Note: Times are in the Mountain Time Zone 1:00 PM No No No No No 2:00 PM No No No No No 3:00 PM No Yes Yes Yes Yes 4:00 PM No No Yes Yes Yes 43

54 Contact Matrix Role Name Phone PM Marie Hepfer (616) Chris Mogni (617) Aerogel Lead Scientist Nick Lybarger (615) Aerogel Build Lead Lauren Powers (216) GPS Team Lead Krysti Papadopoulos (978) Aerogel Lead Electrical Engineer Corrie Russell (410) GPS Lead Mechanical Engineer Brianna Brassard Aerogel Team Lead Kristy Weber (240)

55 Conclusion Please include a list of your biggest issues and concerns 45