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Project Goals

Project Goals. Improve students’ design skills by working co-operatively as members of a large team , on the design of a complex product . Organization similar to industry Multi-disciplinary nature. Current 4 th Year Projects. General Project Structure. Subsystems. Lead Engineers.

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Project Goals

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  1. Project Goals Improve students’ design skills by working co-operatively as members of a large team, on the design of a complex product. Organization similar to industry Multi-disciplinary nature

  2. Current 4th Year Projects

  3. General Project Structure • Subsystems • Lead Engineers

  4. Project Evaluation Participation Progress reports Technical memos Conceptual Design Review Preliminary Design Review Final reports

  5. Recent Spacecraft Projects • NORSAT Constellation • (2006-2007) AEGIS (2005-2006)

  6. 2008-2009 Project Selection

  7. Let’s Go!

  8. Mission Overview

  9. Mission Statement To design a micro-penetrator to survive lunar impact and report upon the characteristics of the sub-surface regolith

  10. Mission Objectives Primary: To survive as a tech demo and report on impact characteristics Secondary: To detect water proxies

  11. Top Level Requirements 1. Scientific measurements: 2.0 ± 0.5 m deep 2. Micro-class penetrator: ≤ 10 kg, ≤ 30 W 3. Functional for at least 5 days 4. Two measurements with at least one sample, relating to the second objective 5. Measure vertical penetration depth

  12. Top Level Requirements 6. Measure temperature changes at the mid and aft point of the penetrator body 7. Shall transmit all collected data to Earth 8. Conform to Consultative Committee of Space Data Systems (CCSDS) 9. Compatible with JAXA SELENE-1 as a carrier satellite 10. Contain a black & white camera operating in visual spectrum

  13. Mission Profile (1) [1] Launch from Earth [2] SELENE-1 Manoeuvres [3] Polar Orbit Reached

  14. Mission Profile (2) [4] [5] [6] [4] Detachment from SELENE-1 [5] Propulsion Module Engaged [6] Propulsion Module Detachment [7] Penetrator Free-fall [8] Impact [7] [8]

  15. Mission Profile (3) [9] Payload Instrument Measurements [10] Survive for 5 days [9] [10]

  16. SELENE-1 • 100 km polar orbit • Carries two satellites • Okina: Relay satellite • Ouna: Gravity analysis

  17. Target South Pole Aitken Basin Cold traps (eternal darkness)

  18. Integrator J. Pelletier Communications K. Barakat Mission Analysis S. Lee, J. Pelletier, T. Yuen C&DH T. Tracey Payload M. Gallant, J. Polansky Documentation M. Gallant, K. Barakat Thermal S. Charbonneau, O. Carriere Structures C. Arends, A. Lantz Budget C. Arends Power S. Shanmuganathan Propulsion S. Golby ADCS J. Tunis

  19. Video Simulation

  20. SUBSYSTEM Presentations

  21. Mission analysis Descent Phase Stephen Lee

  22. Outline • Derived requirements • Early descent manoeuvre cases • Nominal case selection • Nominal trajectory • Determination of impact accuracy • Conclusions • Recommendations Stephen Lee

  23. Derived Requirements Lunar-Penetrator 1 shall: • Begin manoeuvre at circular orbit of 100 km above lunar surface • Impact the surface with velocity of 234-376 m/s • Impact the surface within 9.5 km of target impact zone • Impact the surface at an angle of less than 20° from vertical Stephen Lee

  24. Descent Manoeuvre Case 1 7.3° Burn 1 Selene-1 Orbit Descent 1 Δ t= 4 s • t = 8 min 30 s • Δv = 1.75 km/s • mfuel= 9 kg Burn 2 vimpact=300 m/s Δ t= 2 s 100 km 28 km Descent 2 Engine Data: ISP = 285 s T = 4500 N Simulated with STK Stephen Lee

  25. Descent Manoeuvre Case 2 1.1° Selene-1 Orbit Manoeuvre • t = 13 min 46 s • Δv = 1.88 km/s • mfuel= 10.5 kg Δ t= 11 min vimpact=300 m/s 100 km 28 km Descent Engine Data: ISP = 285 s T = 45 N Simulated with STK Stephen Lee 27

  26. Nominal Case Trade-Off Study Stephen Lee

  27. Nominal Descent Manoeuvre 14.8° Selene-1 Orbit Manoeuvre • t = 13 min 8 s • Δv = 1.73 km/s • mfuel= 18.7 kg • Dry mass = 15 kg Δ t= 666 s (11 min) vimpact=300 m/s 100 km 22 km Descent Engine Data: ISP = 220 s T = 60 N Simulated with STK Stephen Lee

  28. Selene-1 Separation t = 1200s (20 min) 273 m At separation: Δv = 0.282 m/s 282 m Simulated with STK t = 0s Stephen Lee

  29. Propulsion Module Separation LP-1 separation • Burn Properties: • Δ t = 1.5 s • Δv = 0.13 km/s t1 = 0 s 22 km t2 = 10 s Propulsion Module descent burn 5.6 km Simulated with STK Stephen Lee

  30. Determining Impact Accuracy • Monte Carlo Analysis used • Script written in Matlab to numerically solve equations of motion for penetrator descent: • Differential equations solved using Matlab’s built-in ODE45 solver • Includes J2 term Stephen Lee

  31. Trajectory Simulation Comparison Stephen Lee

  32. Monte Carlo Results Monte Carlo Results X Burn Initiation Time Burn Length Z Engine Isp Overall Results Engine Thrust Thrust Drift Distance From Target [km] Resulting Data: Variable Offset Angle • σ of initiation time: 1.13 s • σ of burn length: 4.13 s • σ of thrust (const): 0.2 N • σ of thrust (drift): 0.41 N • σ of offset angle • - (constant): 0.30 ° • (varied): 0.70 ° • Mean distance: 3.38 km • σ of impact distance: 1.96 km Drifting Offset Angle Constant Offset Angle Resulting Data: σ of max offset angle: 0.7° Mean distance: 3.04 km σ of impact distance: 2.23 km σ of max offset angle: 0.69° Mean distance: 1.88 km σ of impact distance: 1.33 km Average σ of offset angle: 2° Mean distance: 0.48 km σ of impact distance: 0.43 km Max change: 2.64 s σ of Isp: 0.62 s Mean distance: -1.95 km σ of impact distance: 1.42 km Max change: 3.5 s σ of initiation time: 1.01 s σ of distance: 1.57 km Covariance: 1.59 km Max change: 0.96 N σ of thrust: 0.30 N Mean distance: -1.96 km σ of impact distance: 3.31 km Max change: 22.4 s σ of burn length: 7.00 s Mean distance: 0.09 km σ of impact distance: 0.78 km Max change: 1.60 N σ of thrust drift: 0.30 N Mean distance: 1.95 km σ of impact distance: 1.43 km Approach direction Distance From Target [km] Stephen Lee

  33. Conclusions • Single, liquidfuelled descent manoeuvre has been selected as nominal case • Propulsion Module not in danger of contaminating impact site • Shackleton Crater is a feasible impact site • ADCS must maintain orientation to within 1.5° and maintain a drift rate less than 2.0° per hour • Propulsion must maintain thrust to within 1 N of nominal 60 N case Stephen Lee

  34. Recommendations • Detailed propulsion module separation analysis • Refine SELENE-1 separation manoeuvre • Determine more accurate prediction of propulsion module impact location using Monte-Carlo approach • Further analysis on effect of propulsion subsystem blow-down operation on descent trajectory Stephen Lee

  35. Questions? Stephen Lee

  36. Mission analysis Penetration Studies Jared Pelletier

  37. Outline Jared Pelletier Applicable requirements Penetration studies & current design S values & regolith hardness gradients Nose performance coefficient Conclusions Recommendations

  38. Requirements Jared Pelletier • Top-Level • Scientific measurements: 1.5 m to 2.5 m deep • Derived • Nose penetration: 1.7 m to 2.7 m deep

  39. Penetration Equation Jared Pelletier

  40. Assumptions LP-1 Pre-Impact LP-1 Post-Impact Jared Pelletier • LP-1 remains intact during penetration • Stable trajectory

  41. Current Design Values Payload 5.2 cm 21.2 cm 58.8 cm Jared Pelletier

  42. S Value Jared Pelletier Considered S values from two to six

  43. S Gradient LP-1 Lunar Surface Direction of increasing hardness Direction of decreasing S value Jared Pelletier Three cases analyzed • Constant (design value) • Linear • Exponential

  44. Linear S Gradient Jared Pelletier ΔS/ΔD = -1 m-1V = 300 m/s

  45. Impact Depth Jared Pelletier

  46. Exponential S Gradient Jared Pelletier ΔS/ΔD ≠ Constant V = 300 m/s Many possible curves

  47. Impact Depth Jared Pelletier

  48. Nose Performance Jared Pelletier N Nose performance coefficient Ln Penetrator nose length [m] d Penetrator diameter [m]

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