Mars18-Inspiration Mars Contest - Published PDR
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This document provides an overview of a preliminary design review for a Mars flyby mission called Mars18. Key details include: - The mission would involve a 2018 flyby of Mars with two astronauts on board as cheaply, safely, and simply as possible. - A SpaceX-based launch concept in September 2017 was selected as the preferred option with a cost of $416.5 million. - The spacecraft design concepts addressed include the attitude control system, electrical power system, communications, thermal protection for re-entry, and life support systems. - Systems engineering areas needing further work were identified as risk management, the mission schedule, ground segment, science objectives, and public outreach.
![Open Loop <> Closed Loop
Equivalent System Mass (ESM) [kg]
10000
9000
Closed System (VPCAR)
8000
Closed System (MF+VCD)
7000
Open System
6000
- 5500kg
5000
4000
- 1300kg
3000
2000
1000
0
100
200
300
Mission Duration [d]
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400
500](https://image.slidesharecdn.com/20140128-pdrv6publish-140211050439-phpapp02/85/Mars18-Inspiration-Mars-Contest-Published-PDR-16-320.jpg)
![Attitude & Orbit Control System
Control system consisting of
Hydrazine thrusters [orbit]
Momentum wheels [attitude]
Resistojets [desaturation]
Sensor system consisting of
Sun sensors, star trackers
Inertial measurement units
GPS [Rendezvous]
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Mars18-Inspiration Mars Contest - Published PDR
- 1. Preliminary Design Review - Mars18 - The Mars Society International Student Design Competition
- 2. Content Attitude and Orbit Control System Electrical Power System Communications Re-entry and TPS Systems Engineering Introduction Launch Systems Trajectory Launch Concepts & Trajectory Spacecraft Design Structural Design Life Support Systems Radiation Shielding Thermal Control System Human Factors Economics To be done Supporters
- 3. Introduction The Mars Society International Student Design Competition: Design a two-person Mars flyby mission for 2018 as cheaply, safely and simply as possible Phase 0/A/B Study 3/ 37
- 4. Introduction Pushing the envelope towards human Mars exploration Gaining public attention and generating public interest for manned space missions Prepare students for future development projects with comparable goals Schedule Cost Selection criteria 20% 30% Simplicity 20% Technical Quality 30% 4/ 37
- 5. Team Over 40 students from aerospace engineering, economics, medicine and others in the 1st to 9th semester Faculty advisors from the Institute of Space Systems 5/ 37
- 6. Requirements Defined mission statement and top-level objectives Derived requirements on system and subsystem level ID TL.1 TL.2 TL.3 TL.4 6/ 37 Description The mission shall be executed by two astronauts. The mission objective is to complete a mars flyby and safely return to earth. The mission will commence in the year 2018. The mission shall result in scientific progress.
- 7. Schedule Critical Design Review: 14.02.2014 Mars18 Deadline (Design Freeze): 28.02.2014 Final Report: 14.03.2014 7/ 37
- 8. Launch Concepts Concept Cost Mio $ Date of first launch 1 (Atlas HLV based) 596,5 Sept. 2017 2 (SpaceX based) 416,5 Sept. 2017 690 Nov. 2017 586,5 Aug. 2017 Inspiration Mars Concept Cost in Mio$ Date of first launch Space Launch System & Commercial Crew Launcher 600-2100 Dec. 2017 3 (Atlas V551 based) 4 (Conservative) Comparison: 8/ 37
- 9. Concept 2 (SpaceX based) to Mars Trans-Mars-Injection (TMI) Sept. 2017 Dez. 2017 9/ 37 Dez. 2017 04. Jan. 2018
- 10. Trajectory Start orbit Start date 04.01.2018 Arrival date 19.05.2019 Duration Departure 350 x 350 km 1.37 years Capture 10/ 37 Flyby
- 11. Spacecraft Design Attitude and Orbit Control System Electrical Power System Communications Re-entry and TPS Systems Engineering Introduction Launch Systems Trajectory Launch Concepts & Trajectory Spacecraft Design Structural Design Life Support Systems Radiation Shielding Thermal Control System 11/ 37 Human Factors Economics To be done Supporters
- 12. Structural Design Baseline: sufficient space, simple and inexpensive deployment, support of all required structures Conservative Designs Advanced Designs 12/ 37
- 13. Structural Design Conservative Design + Costs and risks + Availability + Proven Design Less spacious (but above tolerable limit by NASA Standards) Modifications required 13/ 37
- 14. Structural Design Sizing structure for launch and re-entry loads Peak bending moment and compressive force Addition of supportive structure Secondary (e.g. International Standard Payload Racks) Docking adapters Utilizing proven materials (Aluminum, Titanium) 14/ 37
- 15. ECLSS Environment Control and Life Support System Recycling of most resources (almost closed system) Urine Water Management H2O Air Management O2 Waste Water CO2 Water Management Air Management Food Feces Storage Hygiene Products Storage Waste Clothes 15/ 37
- 16. Open Loop <> Closed Loop Equivalent System Mass (ESM) [kg] 10000 9000 Closed System (VPCAR) 8000 Closed System (MF+VCD) 7000 Open System 6000 - 5500kg 5000 4000 - 1300kg 3000 2000 1000 0 100 200 300 Mission Duration [d] 16/ 37 400 500
- 17. Dirty Laundry Waste ECLSS Eating and Waste Eating simple!?! Waste Compactor Waste W a t e r Shielding tile Water System 17/ 37
- 18. Radiation Protection against SPEs SPE (detected by sensors) diverse materials Alignment towards sun : 2 m water/feces water (decreasing) + tiles (increasing) Trunk Dragon Cygnus Trunk Water gets replaced by feces to maintain shielding against SPEs Amifostin is dispensed after SPE 18/ 37
- 19. Thermal Control System Dissipative and external heat sources Critical Points: Assembly in Earth orbit Passing Venus orbit Mars flyby 19/ 37
- 20. Thermal Control System 20/ 37
- 21. Attitude & Orbit Control System Control system consisting of Hydrazine thrusters [orbit] Momentum wheels [attitude] Resistojets [desaturation] Sensor system consisting of Sun sensors, star trackers Inertial measurement units GPS [Rendezvous] 21/ 37
- 22. Electrical Power System Goal: provide continuous average power and withstand daily power peaks Sizing Case: Arrival at Mars after ca. 230 days Largest distance to Sun, moderate degradation Including environmental, array and system losses 22/ 37
- 23. Electrical Power System Primary power source: UltraFlex arrays (4 x 5m) Secondary storage: Regenerative fuel cells Power management and distribution with 11.4 kW/kg 23/ 37
- 24. Electrical Power System 10.2m Off the shelf 24/ 37
- 25. Communications Goals Providing failure-safe communication between the spacecraft and ground stations on earth Limitations Antenna size/fairing space Suitable ground stations limit frequency bands selection Power consumption Environment Interference from solar radiation Communication blackout during flyby 25/ 37
- 26. Phases of communication Near Earth phase Live streaming Engineering data Cruise phase Pictures, videos Science data Engineering data Relay communication phase Science and engineering data, emergency link Cruise phase Pictures, videos Science & Engineering data 26/ 37
- 27. Re-entry 3 passes through atmosphere before re-entering Keep the load factors within a limit of 5 g Lower heat flux peaks 27/ 37
- 28. Thermal Protection System Use of PICA-X as in Dragon-C1 Increase in thickness due to higher integral heat load PICA-X is 10-times cheaper then PICA 28/ 37
- 29. Systems Engineering Mass, volume and power budgets Pressurized, unpressurized and packed volume Average, peak and waste power Element margins depending on technology readiness level and amount of required modifications 5%, 10% and 20% 29/ 37
- 30. Spacecraft Design Attitude and Orbit Control System Electrical Power System Communications Re-entry and TPS Systems Engineering Introduction Launch Systems Trajectory Launch Concepts & Trajectory Spacecraft Design Structural Design Life Support Systems Radiation Shielding Thermal Control System Human Factors Economics To be done Supporters 30/ 37
- 31. Human Factors 2 Ensure physical health To ensure physical health during the whole trip the team has to be prepared for all medical risks. Therefore the team supplies medical treatment and prevention . 3 e-Health Offering solutions for a 24/7 monitoring and documentation of all medical parameters through an health vest. The e-Health system offers self-treatment options. 1 Preselecting & Preparation The Team sets up the right criteria for the Preselection (age, experience, health situation, profession, ..). Moreover the astronauts have to be prepared mentally and physically. 4 Training & Food To prevent muscle degradation due to microgravity we provide training equipment and a suitable nutritional protocol. 5 Ensure mental health To establish and keep the astronauts mentally fit during the whole trip is a necessary key for a successful mission. This can be ensured by using audiovisual stimulation, a motivation and entertainment kit. 31/ 37
- 32. Economics - Cost estimating methods Parametric: mathematical equations relating cost to one or more physical or performance variables associated with the item being estimated Build-up: historical data (e.g. detailed work hours and bills of material) Analogy: the data is adjusted or extrapolated 32/ 37
- 33. To be done Finish design, cost estimations Risk management Mission schedule & development roadmap Ground segment Science Public outreach 33/ 37
- 34. Supporters Institut f端r Raumfahrtsysteme Uni Stuttgart ASTOS Solutions Bahnbestimmung und -optimierung Campus Konzept Stuttgart Studentische Unternehmensberatung Constellation Studentische Nachwuchsforschungsgruppe DGLR Stuttgart BrainLight GmbH Marktf端hrer f端r Entspannungstechnologie 34/ 37
- 35. Unterst端tzung Was f端r sie drin ist: Name und Logo im Abschlussbericht/Pr辰sentation Mediale Pr辰senz (z.B. Stuttgarter Nachrichten, Radio, etc.) Chance sich vor motivierten Studenten zu pr辰sentieren Image best辰rken als innovatives und zukunftsgestaltendes Raumfahrtunternehmen Was wir ben旦tigen: Professionelle Meinung und Korrekturleser Finanzielle Unterst端tzung f端rs Teambuilding (T-Shirts, etc.) Reisekostenzusch端sse (Abschlusspr辰sentation in den USA) 35/ 37
- 36. Danke f端r Ihre Aufmerksamkeit! www.mars18.de 36/ 37
- 37. Media Sources http://casolarco.com http://s400.photobucket.com/user/Donaldyax/ Emil Nathanson, Vorlesung Raumfahrttechnik 1 Johnson, J., and Marten, A., Testing of a High Efficiency High Output Plastic Melt Waste Compactor, AIAA-2013-3372, 2013. http://www.coconutsciencelaboratory.com www.nasa.gov www.spacex.com www.orbitalsciences.com Star Trek http://www.ulalaunch.com/site/pages/Products_AtlasV.shtml www.planetaryresources.com 37/ 37