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DMAT

Project Manager: Dhruv Patel Systems Engineer: Max Beasley. DMAT. the Decatur Mars Atmosphere Team. Team Introduction. Dhruv Patel 12th- Project manager Max Beasley 11th- Systems Engineer Trey Hargett 11th Jonathan Ford 11th Brent Higdon 11th Austin Lambert 11th Jay Chenault 11th

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DMAT

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  1. Project Manager: Dhruv Patel Systems Engineer: Max Beasley DMAT the Decatur Mars Atmosphere Team

  2. Team Introduction Dhruv Patel 12th- Project manager Max Beasley 11th- Systems Engineer Trey Hargett 11th Jonathan Ford 11th Brent Higdon 11th Austin Lambert 11th Jay Chenault 11th David Martin 11th Hayden Naumann 11th Trey Keown 10th

  3. Our Task Our task is to design and build a prototype experiment that could be performed on Mars during the Mars Sample Return Mission.

  4. Constraints of experiment • The experiment must fit into an 18 inch cube • The experiment must weigh less than 10 kilograms • The experiment is allocated 50 watts of energy from the Lander • The experiment must be completed during the duration of the mission

  5. Science objectives • Record and collect atmospheric data at various levels of the Martian atmosphere • Measure Atmospheric temperature, pressure, wind speed, radiation, magnetic force, and humidity • Secondary objective is to take a photo of the Mars Sample Return Lander from above

  6. Proposed Measurements And devices

  7. Pressure Beagle 2 Capacitance Manometer Weight – 15g Temperature Beagle 2 Instrument Weight – 6g Credit: Beagle 2 Credit: Beagle 2

  8. Radiation (UV Sensor) Density UVB, UVC Weight – 19g Density is going to be measured by using data from other measurements Credit: Beagle 2

  9. Altitude GP1L Acceleromter Visual Images RC Mini Cam

  10. Humidity Hygrometer More research is needed on hygrometers to determine an appropriate instrument for this mission.

  11. Wind Speed Magnetic Field Hot film anemometer Weight – 4g Honeywell HMC2003

  12. Figures of Merit

  13. Figures of Merit (Most important to least important) • Measurement Uncertainty • Complexity of Concept of Operations (ConOps) • Overall Measurement Space • Measurement Duration • Number of measurement data points inside specified measurement density • Mass reserve

  14. Figures of Merit Complete weighted factor analysis chart

  15. Martian Balloon The solution

  16. Martian Balloon • The Martian Balloon idea consists of balloon that floats up into the Martian atmosphere and carries a payload of various scientific instruments that measures atmospheric data. • Due to the low atmospheric density of mars, a very large balloon is required to displace enough air to create a buoyant force large enough to allow the balloon to rise. • The Density of the Martian atmosphere based upon previous experiments was found to be around .02 kg/m3 • According to Archimedes's principle, our balloon, the payload, and the helium inside of the balloon would have to weigh less than the Martian atmosphere in order to float.

  17. Martian Balloon

  18. Con-ops of Martian Balloon • Energy Storage • Balloon Deployment • Data Measurement, Storage, and Transmission

  19. Balloon Technical Details • Balloon Thickness- 5x10-5 m • Balloon deflated Volume- .0323 m3 • Balloon Material- Mylar, Kevlar, Polyethylene, and Adhesive • Balloon inflated Volume- 381.7 • Inflated Balloon Mass- 6.3 Kg

  20. Payload Technical Details • Payload Mass- 1Kg • Platform dimensions- 14”x14”x.0625” • Platform Material- Titanium • All scientific instruments are mounted on the platform

  21. Computer Technical Details • Two computers: the Lander System (LASY) and the Balloon System (BOSS) • Unsure of how much we’ll be able to use the Lander’s computer, so LASY was included. Controls lifting mechanism and possibly communications with BOSS. • BOSS must be as lightweight as possible. The weight of the entire computer system (motherboard, processor, flash memory) must be under .4kg. • Expecting technology to evolve exponentially before the mission launches

  22. Trade Studies

  23. Balloon Deployment trade Study • Two types of trade study • Spring load the balloon from the Lander to the ground and deploy from there. • Shoot the helium into the balloon and inflate it from the top of the Lander in a cone shape. This would create an upside down tear drop shape. • Lifting Mechanism Option • Inflate an air bag to raise the packaged balloon out of the 18 inch cube.

  24. Balloon Material Trade Study • Mylar- A plastic film that can take shape and form the skin of the balloon. • Polyethylene- A common balloon material that retains helium well. • Kevlar Scrim- Added to the polyethylene to make the skin of the balloon more resistant to tearing. • Adhesive- strong durable glue to hold previous materials together.

  25. Balloon Thickness Trade Study • The thicker the balloon the more volume it occupies, and the heavier the balloon, but it makes a more durable balloon. • The thinner the balloon the less volume it occupies, and the lighter the balloon, but it will be less durable.

  26. Power Trade Study • Solar Power: May provide a longer measurement sample during flight due to regenerative power. But, would cause extra hardware and weight. Also, there is limited solar exposure. • Battery Power: Lithium Ion batteries add to the payload weight, but can be charged by Lander’s power supply.

  27. Questions?

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