Embry Riddle Final
- 1. Professor: Dr. Bogdan Udrea Team Lead: Robert Latta Team Members: David Paiz Brandon Walsh-Reed Svilen Kozhuharov Mathieu Naslin Johann Schrell
- 2. Overview Financial Excellence History Immediate Funding USD Budget Sustainable Funding Technical Excellence Subsystems Screenshots Relevant Legal and Ethical Issues Coherence of the Mission Concept Summary
- 3. Financial Excellence History Historical precedents During the heydays of Earth exploration prospectors were funded by wealthy sponsors to prospect for the commodities of the time: Spices, Gold, Other resources, Fame Besides discovering commodities the prospectors opened trade routes and avenues of colonization Nowadays: Solar system exploration is on the current NASA, ESA, and various national space agencies (Russia, India, China) agenda. Readily available resources found only on Earth. Propellant and Facilities Solar system exploration could be accelerated by making resources available beyond Earth Earth-Moon system fuelling stations and star shipyards. Near future avenues of expansion: Moon settlements Human exploration of Mars and possible settlements Asteroid mining Outer solar system exploration and exploitation.
- 4. Financial Excellence Immediate Funding Estimated mission cost: US$30million Possible avenues of funding of the Aquila Aurealis prospector mission: Energy companies: Shell, Exxon, British Petroleum, General Electric Independent wealth funds (possibly from the Middle East and Asia) Private wealthy persons seeking fame or profit. Fund raising (Embry-Riddle development office.)
- 5. Financial Excellence USD Budget $26.14 Million Total Project Cost $10 Mil Launch $1 Mil OBC $0.14 Mil Engineers $1 Mil Telecom $1 Mil Structures $1 Mil Power $5 Mil Software development $2 Mil Cameras and lidar (procurement) $5 Mil Throttable rocket engines COST COMPONENT
- 6. Financial Excellence Sustainable Funding Maintains the company presence in the space exploration industry: If the presence of water ice is confirmed commence the water exploitation (get rich fast plan.) If not, the Moon regolith will be exploited for oxygen, hydrogen, silicon* (get rich slow plan.) * Paul Eckert, International and commercial strategist, Boeing Company http://news.nationalgeographic.com/news/2006/07/060725-moon-money.html
- 7. Technical Excellence Trajectory Trade-Offs Δv vs. time A higher ∆v results in less time, however the high ∆v will require more propellant. More propellant means more mass and more mass equals more money A low ∆v results in a very large time of flight. Although mass is saved, the length of the mission may cost more in the long run. Time vs. Cost Payroll If the time of the mission is extensive, then people are needed to observe/oversee the mission in its entirety. Time vs. Risk If the spacecraft is in space for an extended period of time, it would be exposed to numerous dangers. Radiation Temperature extremes Collisions with debris
- 8. Technical Excellence Lunar Transfer Trajectories Figure 7‑42: LEO to Moon at 180 o Figure 7‑64: LEO Arrival to Moon at 180 o
- 9. Technical Excellence Lunar Transfer Trajectories Figure 7-15: Arrival at Moon and Landing Figure 7-13: Bi-Elliptic Transfer Figure 7-14: Arrival to the Moon’s Sphere of Influence
- 10. Technical Excellence Lunar Transfer Trajectories Figure 7‑182: Successful WSB Trajectory from LEO
- 11. Technical Excellence MATLAB Code 3.103 5.66 3.155 5.571 5.613 TOTAL Δv (km/s) 90 55 4.65 120 4.63 Time of Flight (days) 2.374 First Maneuver 3.15 Second Maneuver 0.1355 GTO Bi-elliptic (Moon fly-by) 2.39 2.48 2.39 2.502 Landing Δv (km/s) .713 GTO WSB (Moon fly-by) 0.6745 GTO Direct 3.181 LEO WSB 3.111 LEO Direct TLI Δv (km/s) Trans-lunar Trajectory
- 12. Technical Excellence From the Earth to the Moon Earth Moon STAR 13B Stage 1 STAR 13B Stage 2 Craft Launcher Payload Fairing
- 13. Technical Excellence Stage 1 Purpose Boost craft from GTO to LTI Engine Thiokol STAR 13B solid rocket Impulse = 1.16 E 5 N-s Attains 100% required 0.675 km/s Δ v
- 14. Technical Excellence Stage 2 Purpose Slow craft from LTI speed to close to 0 m/s Engine Thiokol STAR 13B solid rocket Impulse = 1.16 E 5 N-s Attains 95.58% of required 2.485 km/s Δ v Remaining Δ v = 0.110 km/s
- 15. Technical Excellence Stage 3 Purpose Provide soft landing for the craft. Provide ability for wheeled locomotion. Engine Four Bi-Propellant Liquid Hypergolic Engines UDMH Hydrazine + Nitrogen Tetroxide Isp = 340 sec o/f = 3 Thrust = 24 N each Burn Time = 12 sec Total Impulse = 1114 N-s for all four. Δ v = 0.110 km/s
- 16. Technical Excellence To the Lunar Surface Lunar Surface – South Pole Ignite SRM 35 km, 2.48 km/s SRM Burnout 2 km, 0.11 km/s + Craft Separation Horizon acquisition and lateral motion cancellation Hazard avoidance Liquid engine cutoff, 1 m
- 17. Technical Excellence Subsystems Instruments Altimeter Camera Spectrometer Inertia Measurement Device Power Electrical – Batteries Chemical – Rocket Fuel Locomotive Communication Funding Etch-a-sketch Payload
- 18. Instruments Spectrometer Part of the payload on the Craft will be a miniature neutron spectrometer that uses light diffractions caused by negatively charged hydrogen ions to detect the presence of water. The same technology is being used in the LCROSS-LRO joint mission, headed by NASA Ames. The spectrometer is custom built and counts as part of the science payload. Mass estimated to be 750g and is not expected to occupy a large volume. 100mm 50mm 25mm
- 19. Instruments Altimeter The altitude measuring device is a laser altimeter that determines the Craft’s altitude by bouncing the laser light off the surface of the Moon and read back. It is a proven technology with space heritage like the Mars Orbiter. JPL provides these custom devices. Courtesy: JPL
- 20. Instruments Camera Specifications: 30 fps 84 g 22 x 22 x 75 mm 2.5 watts FOV (Full angle: H=107, V=80) Courtesy: Rocketcam DVS
- 21. Instruments Inertia Measurement Device Low accuracy Needed for: De-tumbling after craft separation from launcher Fault detection isolation and recovery in case of star tracker failure Event triggering during decent
- 22. Power Electrical - Batteries
- 25. Instruments Mass Budget 15 Dry weight 0.5 Science package 0.4 Payload 0.5 Thermal control system 0.5 Attitude control thrusters 1 GNC package 0.65 Onboard computer 1.5 Tanks (pressurant + hydrazine) 1 Telecom 3 Structures 1.75 Power unit (batteries, wiring, solar panels) 0.2 Cameras + baffles 4 Throttable rocket engines + mounting TOTAL COMPONENT MASS (Kg) COMPONENT
- 27. Technical Excellence Mooncasts NASA Lunar Reconnaissance Orbiter (LRO) Communication Relay S-Band TX: 2.65 GHz, RX: 2.56 Communication Rate (Max.): ~ 120 Mbps Visibility time of LRO from Landing Site: 127s Min. Data Rate per LRO-cycle: 117 MB/LRO-cycle Est. Data Rate per LRO-Cycle: 1910 MB/LRO-cycle HD data to transfer: 34837 MB Days to transfer HD: ~ 36 hours
- 28. Technical Excellence Mooncasts Encryption algorithm analysis Requirements Small CPU Footprint Small Memory Footprint Work in a multitasking environment Fast! The Vector Stream Cipher (VSC) * Algorithm Encryption speed: 25.62 Gbps (AES: 4.8 Gbps) Stream cipher (AES: Block Cipher) * Communications Research Laboratory and ChaosWare, Inc. - Japan
- 29. Technical Excellence Mooncasts HD Images Generated by software stitching of low-resolution captured by twin cameras Time-stamped Advantages Low-cost Disadvantages Software complexity on ground-station level
- 30. Technical Excellence XPF Payload Stationary Mass: 250 g Mobile Mass: 1% of mass = 150g
- 31. Technical Excellence Ethical and Legal Issues Ethical Custom laser logo projection seen from telescopes will not be distinguishable from earth with naked eye. Legal Extract hydrogen from the moon. The Moon Treaty is not signed by the USA. LRO Communication has an allocation license. FCC Frequency allocation of the S-Band during cruising.
- 32. Summary Financial Excellence History Immediate Funding USD Budget Sustainable Funding Technical Excellence Subsystems Screenshots Relevant Legal and Ethical Issues Coherence of the Mission Concept
- 33. Questions Questions and Feedback