Download presentation
Presentation is loading. Please wait.
1
AAE450 Spring 2009 Launch Vehicle Selection Zarinah Blockton Mission Ops~Group Earth to LEO~Phase March 5, 2009
2
AAE450 Spring 2009 [Blockton] [OPS] Arbitrary Payload Case Goal: Minimize $/kg to LLO (low lunar orbit) Additional Launch Vehicles –Delta IV (All configurations) –Atlas V –Long March 2C, 2E –PSLV –Falcon 9 Heavy Iterate between propulsion and mission ops code Notables –Biggest assumption ~ structural mass scale-up –Parking orbit = 400 km –Time of Flight = 351 days
![AAE450 Spring 2009 [Blockton] [OPS] Arbitrary Payload Case Goal: Minimize $/kg to LLO (low lunar orbit) Additional Launch Vehicles –Delta IV (All configurations) –Atlas V –Long March 2C, 2E –PSLV –Falcon 9 Heavy Iterate between propulsion and mission ops code Notables –Biggest assumption ~ structural mass scale-up –Parking orbit = 400 km –Time of Flight = 351 days](http://images.slideplayer.com/32/9917346/slides/slide_2.jpg "AAE450 Spring 2009 [Blockton] [OPS] Arbitrary Payload Case Goal: Minimize $/kg to LLO (low lunar orbit) Additional Launch Vehicles –Delta IV (All configurations) –Atlas V –Long March 2C, 2E –PSLV –Falcon 9 Heavy Iterate between propulsion and mission ops code Notables –Biggest assumption ~ structural mass scale-up –Parking orbit = 400 km –Time of Flight = 351 days")
3
AAE450 Spring 2009 [Blockton] [OPS] LV Mass (kg) to LEO Thrust (mN) Number of Thrusters Mass (kg) to LLO($/kg) LL0 Dnepr340063422,129.4045,046.00 Falcon 99953185046,521.8010,486.00 Falcon 9 H2798052001118,601.009,821.80
![AAE450 Spring 2009 [Blockton] [OPS] LV Mass (kg) to LEO Thrust (mN) Number of Thrusters Mass (kg) to LLO($/kg) LL0 Dnepr , , Falcon , , Falcon 9 H , ,821.80](http://images.slideplayer.com/32/9917346/slides/slide_3.jpg "AAE450 Spring 2009 [Blockton] [OPS] LV Mass (kg) to LEO Thrust (mN) Number of Thrusters Mass (kg) to LLO($/kg) LL0 Dnepr , , Falcon , , Falcon 9 H , ,821.80")
4
AAE450 Spring 2009 Back-up Slide [Blockton] [OPS] LVAltitude (km)Mass (kg)Thrust (mN) Number of Thrustersmdot_optMpay (kg) Power Required (W)Mprop (kg) Dnepr400340063231.00E-052,108.104,045.90909.79 Falcon 94009953188589.90E-066,779.504,897.802,401.90 Delta IV H400237574760196.50E-0618,545.007,135.203,745.30 Atlas V40011300215599.60E-067,835.805,272.502,620.20 LM 2C400280051031.00E-051,517.002,773.90909.79 LM 2E4006900128661.00E-054,465.704,162.201,819.60 PSLV400350070131.00E-052,206.404,290.70909.79 Delta IV M4009400177889.40E-066,359.904,599.802,280.50 Delta IV M(4,2)400125002500108.90E-068,897.705,419.502,699.00 Delta IV M (5,2)40011050222299.20E-067,705.305,089.902,511.00 Delta IV M (5,4)400137502690118.70E-069,874.305,678.302,902.20 Falcon 9 H400279805718235.80E-0622,234.007,491.204,045.50 Ares V40012000022200441.10E-038.06E+048.10E+033.23E+04
![AAE450 Spring 2009 Back-up Slide [Blockton] [OPS] LVAltitude (km)Mass (kg)Thrust (mN) Number of Thrustersmdot_optMpay (kg) Power Required (W)Mprop (kg) Dnepr E-052, , Falcon E-066, , , Delta IV H E-0618, , , Atlas V E-067, , , LM 2C E-051, , LM 2E E-054, , , PSLV E-052, , Delta IV M E-066, , , Delta IV M(4,2) E-068, , , Delta IV M (5,2) E-067, , , Delta IV M (5,4) E-069, , , Falcon 9 H E-0622, , , Ares V E E E E+04](http://images.slideplayer.com/32/9917346/slides/slide_4.jpg "AAE450 Spring 2009 Back-up Slide [Blockton] [OPS] LVAltitude (km)Mass (kg)Thrust (mN) Number of Thrustersmdot_optMpay (kg) Power Required (W)Mprop (kg) Dnepr E-052, , Falcon E-066, , , Delta IV H E-0618, , , Atlas V E-067, , , LM 2C E-051, , LM 2E E-054, , , PSLV E-052, , Delta IV M E-066, , , Delta IV M(4,2) E-068, , , Delta IV M (5,2) E-067, , , Delta IV M (5,4) E-069, , , Falcon 9 H E-0622, , , Ares V E E E E+04")
5
AAE450 Spring 2009 Back-up Slide LV2009 Launch CostTotal $ LLO($/kg) LL0($/kg) LEO Dnepr21,257,667.552.64E+0712,520.906,252.26 Falcon 938,201,663.204.60E+076,782.473,838.21 Delta IV H308,289,232.413.20E+0817,250.9512,976.77 Atlas V122,699,257.071.31E+0816,732.9410,858.34 LM 2C31,886,501.323.58E+0723,567.6711,388.04 LM 2E70,858,891.827.72E+0717,288.3610,269.40 PSLV44,194,735.024.96E+0722,469.7212,627.07 Delta IV M161,427,039.021.69E+0826,535.5517,173.09 Delta IV M(4,2)167,495,724.701.76E+0819,797.7013,399.66 Delta IV M (5,2)182,060,570.321.90E+0824,679.5916,476.07 Delta IV M (5,4)194,197,941.682.03E+0820,594.7614,123.49 Falcon 9 H98,232,848.231.11E+084,973.403,510.82 Ares V500,000,000.005.47E+086,787.804,166.67 [Blockton] [OPS]
![AAE450 Spring 2009 Back-up Slide LV2009 Launch CostTotal $ LLO($/kg) LL0($/kg) LEO Dnepr21,257, E+0712, , Falcon 938,201, E+076, , Delta IV H308,289, E+0817, , Atlas V122,699, E+0816, , LM 2C31,886, E+0723, , LM 2E70,858, E+0717, , PSLV44,194, E+0722, , Delta IV M161,427, E+0826, , Delta IV M(4,2)167,495, E+0819, , Delta IV M (5,2)182,060, E+0824, , Delta IV M (5,4)194,197, E+0820, , Falcon 9 H98,232, E+084, , Ares V500,000, E+086, , [Blockton] [OPS]](http://images.slideplayer.com/32/9917346/slides/slide_5.jpg "AAE450 Spring 2009 Back-up Slide LV2009 Launch CostTotal $ LLO($/kg) LL0($/kg) LEO Dnepr21,257, E+0712, , Falcon 938,201, E+076, , Delta IV H308,289, E+0817, , Atlas V122,699, E+0816, , LM 2C31,886, E+0723, , LM 2E70,858, E+0717, , PSLV44,194, E+0722, , Delta IV M161,427, E+0826, , Delta IV M(4,2)167,495, E+0819, , Delta IV M (5,2)182,060, E+0824, , Delta IV M (5,4)194,197, E+0820, , Falcon 9 H98,232, E+084, , Ares V500,000, E+086, , [Blockton] [OPS]")
6
AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Spring Calculation PE = ½*k*x 2 KE = PE KE = ½*m*v 2 V yf = V y0 – g moon *t ∆x = V X0 *t
![AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Spring Calculation PE = ½*k*x 2 KE = PE KE = ½*m*v 2 V yf = V y0 – g moon *t ∆x = V X0 *t](http://images.slideplayer.com/32/9917346/slides/slide_6.jpg "AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Spring Calculation PE = ½*k*x 2 KE = PE KE = ½*m*v 2 V yf = V y0 – g moon *t ∆x = V X0 *t")
7
AAE450 Spring 2009 Spring Cannon Conclusions 100g case (7.6kg ball) For 1s impact time we can get to 720m and be under 30g's at impact For.5s impact we can get to 180m and be under 30g's at impact 10kg case (18.5kg ball) For 1s impact time we can get to 667m and be under 30g's at impact For.5s impact we can get to 148m and be under 30g's at impact However if we launch to our maximum distance the length of the springs grows. Therefore here are my recommendations 100g case (7.6kg ball) D = 180m 30g's at launch 15g's at landing for 1s impact time 30g's at landing for 0.5s impact time 6m distance spring is extended 10kg case (18.5kg ball) D = 148.13m 30g's at launch 13g's at landing for 1s impact time 27g's at landing for 0.5s impact time 5m distance spring is extended I haven't found a spring that meets these requirements yet, however I think one could be custom made to meet our needs either in-house or through a contract company. If we can determine that using a spring that extends to a length over 6m is possible/feasible, then we could launch to a greater distance. As of right now the spring length and launch g's are the limiting factors in this design. [Blockton] [OPS]
8
AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Part #x(m)# Springsm (kg)t (s)D (m)Max Height (m)Takeoff G's Landi ng G’s (1s impact) Landing G's (0.5s impact) Spring L @ 30 g's LHC 250U 08M0.1524118.52.151542127.40661363.70330679948.599826753.042740056.0854800950.24688712 10kg case0.1524106.8037735874.06613637.03306799485.99826759.6219888819.243977762.4688712 0.1524209.62198888148.13227274.06613597971.996535113.607547227.215094344.9377424 0.15243011.7844815222.198408111.0992041457.99480316.665773633.331547217.4066136 0.15244013.6075472296.264544148.13227191943.9930719.243977838.487955519.8754848 0.15245015.2137002370.33068185.16533992429.99133821.515421243.0308424212.344356 0.15246016.6657736444.396816222.19840792915.98960523.568963147.1379261214.8132272 0.15247018.0010929518.462952259.23147593401.98787325.457389750.9147793817.2820984 0.15248019.2439778592.529088296.26454393887.9861427.215094354.4301886719.7509696 0.15249020.4113208666.595224333.29761194373.98440828.865966657.7319332722.2198408 0.152410021.5154212740.66136370.33067994859.98267530.427400560.8548009524.688712
![AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Part #x(m)# Springsm (kg)t (s)D (m)Max Height (m)Takeoff G s Landi ng G’s (1s impact) Landing G s (0.5s impact) Spring 30 g s LHC 250U 08M kg case](http://images.slideplayer.com/32/9917346/slides/slide_8.jpg "AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Part #x(m)# Springsm (kg)t (s)D (m)Max Height (m)Takeoff G s Landi ng G’s (1s impact) Landing G s (0.5s impact) Spring 30 g s LHC 250U 08M kg case")
9
AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Part #x(m)# Springsm (kg)t (s)D (m)Max Height (m)Takeoff G's Landi ng G’s (1s impact) Landing G's (0.5s impact) Spring L @ 30 g's LHC 250U 08M 0.1524 1 7.63.3618.039.01118.304.759.490.60 100g case 0.1524 10 10.62180.2990.151183.0215.0130.026.01 0.1524 20 15.01360.59180.292366.0421.2342.4612.02 0.1524 30 18.39540.88270.443549.0726.0052.0018.03 0.1524 40 21.23721.17360.594732.0930.0260.0524.04 0.1524 50 23.74901.46450.735915.1133.5767.1430.05 0.1524 60 26.001081.76540.887098.1336.7773.5436.06 0.1524 70 28.091262.05631.028281.1539.7279.4442.07 0.1524 80 30.021442.34721.179464.1842.4684.9248.08 0.1524 90 31.851622.63811.3210647.2045.0490.0754.09 0.1524 100 33.571802.93901.4611830.2247.4794.9560.10
![AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Part #x(m)# Springsm (kg)t (s)D (m)Max Height (m)Takeoff G s Landi ng G’s (1s impact) Landing G s (0.5s impact) Spring 30 g s LHC 250U 08M g case](http://images.slideplayer.com/32/9917346/slides/slide_9.jpg "AAE450 Spring 2009 [Blockton] [OPS] Back-up Slide Part #x(m)# Springsm (kg)t (s)D (m)Max Height (m)Takeoff G s Landi ng G’s (1s impact) Landing G s (0.5s impact) Spring 30 g s LHC 250U 08M g case")
Similar presentations
![AAE450 Spring 2009 Hopper Trajectory February 26, 2009 [Alex Whiteman] [Mission Ops] [Lunar Descent] Page 1.](/15/4837170/big_thumb.jpg "AAE450 Spring 2009 Hopper Trajectory February 26, 2009 [Alex Whiteman] [Mission Ops] [Lunar Descent] Page 1.>")
![AAE450 Spring 2009 Brian Erson Attitude Control Systems Trans Lunar Phase Alternative Design Analysis Cold Xe Gas Thrusters [Brian Erson] [Attitude] 1.](/15/4842566/big_thumb.jpg "AAE450 Spring 2009 Brian Erson Attitude Control Systems Trans Lunar Phase Alternative Design Analysis Cold Xe Gas Thrusters [Brian Erson] [Attitude] 1.>")
![AAE450 Spring 2009 Analysis of Trans-Lunar Spiral Trajectory [Levi Brown] [Mission Ops] February 12, 2009 1.](/15/4845348/big_thumb.jpg "AAE450 Spring 2009 Analysis of Trans-Lunar Spiral Trajectory [Levi Brown] [Mission Ops] February 12, 2009 1.>")
![AAE450 Spring 2009 Final Sizing and Trajectory Design for 100 g/10kg Payloads [Levi Brown] [Mission Ops] March 12, 2009 1.](/15/4846745/big_thumb.jpg "AAE450 Spring 2009 Final Sizing and Trajectory Design for 100 g/10kg Payloads [Levi Brown] [Mission Ops] March 12, 2009 1.>")
![AAE450 Spring 2009 Tony Cofer Power Group TLI Phase 03/05/09 Power Limitations for Arbitrary Payload Tony Cofer] [Power] page 1.](/15/4848045/big_thumb.jpg "AAE450 Spring 2009 Tony Cofer Power Group TLI Phase 03/05/09 Power Limitations for Arbitrary Payload Tony Cofer] [Power] page 1.>")
![AAE450 Spring 2009 LEO Atmospheric Drag Analysis and Lunar Orbit Circularization [Andrew Damon] [Mission Ops] February 19, 2009 1.](/15/4849233/big_thumb.jpg "AAE450 Spring 2009 LEO Atmospheric Drag Analysis and Lunar Orbit Circularization [Andrew Damon] [Mission Ops] February 19, 2009 1.>")
![AAE450 Spring 2009 Lunar Descent Final Numbers Josh Lukasak Attitude Group Lead Lunar Decent Phase Lead 03/12/09 [Josh Lukasak] [Attitude] (1)](/15/4850949/big_thumb.jpg "AAE450 Spring 2009 Lunar Descent Final Numbers Josh Lukasak Attitude Group Lead Lunar Decent Phase Lead 03/12/09 [Josh Lukasak] [Attitude] (1)>")
![AAE450 Spring 2009 Descent Trajectory Hover Trajectory LD Code Integration John Aitchison March 5 th, 2009 [John Aitchison] [Mission Ops]](/15/4852501/big_thumb.jpg "AAE450 Spring 2009 Descent Trajectory Hover Trajectory LD Code Integration John Aitchison March 5 th, 2009 [John Aitchison] [Mission Ops]>")
