project bellerophon0 backup slides. project bellerophon1 trajectory - steering law function of time...
DESCRIPTION
Project Bellerophon2 Model Analysis 5,616 possible combinations for each payload …… Launch Vehicle Stage 1Stage 2Stage 3Launch Method MaterialPropellant Ground Aircraft Balloon Cryogenic Storable Hybrid Solid Aluminum Steel TitaniumTRANSCRIPT
Project Bellerophon 1
Backup Slides
Project Bellerophon 2
Trajectory - Steering Law• Function of time • Defines the orientation of the launch
vehicle
b
br
2e
3e
1e
Project Bellerophon 3
Model Analysis
5,616 possible combinations for each payload
… …
Launch Vehicle
Stage 1 Stage 2 Stage 3 Launch Method
Material PropellantGround
Aircraft
BalloonCryogenic
Storable
Hybrid
Solid
Aluminum
Steel
Titanium
Project Bellerophon 4
Historical Catastrophic Risk
Number ofLaunches
Success of Previous10 Launches
10 60.00 %20 80.00 %30 100.00 % s
Number of Launches Success RateLess than 12 60.00 %Less than 24 80.00 %24 or greater 93.84 %
Pegasus
Our Vehicles
Project Bellerophon 5
Aircraft Steering Law – Parameter Optimization
tb2
25% tb2
25% tb2
Ψmid1=5 deg
Ψmid2=0 deg
Ψe2
To be optimized
tclimb
1st Stage: tangent law
2nd Stage: 3 linear sections
Project Bellerophon 6
Definition of Eccentricity• e = c/a
a: Semi-Major Axisb:
Sem
i-Min
or A
xis
c: center to focus
Project Bellerophon 7
Risk Assessment - Non-Catastrophic FailureMonte Carlo Histograms - 200g Payload
200g Periapsis Altitude Histogram; std = 21.803 km, mean = 437.44 km
200g Eccentricity Histogram; std = 0.0467, mean = 0.438
Project Bellerophon 8
Risk Assessment - Non-Catastrophic FailureMonte Carlo Histograms - 1kg Payload
1kg Periapsis Altitude Histogram; std = 15.774 km, mean = 367.727 km
1kg Eccentricity Histogram; std = 0.041094, mean = 0.173289
Project Bellerophon 9
Risk Assessment - Non-Catastrophic FailureMonte Carlo Histograms - 5kg Payload
5kg Periapsis Altitude Histogram; std = 20.215 km, mean = 516.546 km
5kg Eccentricity Histogram; std = 0.050, mean = 0.445
Project Bellerophon 10
Performance Characteristics - 200 g PayloadBALLOON STRUCTURE GONDOLA STRUCTUREFeatures FeaturesMinimum volume: 3237.7 m3 Dimensions: 0.876[3] x 0.876[3] x 3.346[4] m3
Maximum volume: 279,950 m3 Material: Aluminum Minimum diameter: 18.3547 m Thickness: 0.04 mMaximum diameter: 81.1635 m Weight: 177.188 kgMaterial: Polyethylene plastic film PROPULSIONGas used: Helium FeaturesShape: Spherical Propellant type:STRUCTURES Stage 1 H2O2 & HTPBFeatures Stage 2 HTPB/AP/Al & H2O2
[5]
Length: Stage 3 HTPB/AP/AL Stage 1 4.9929 m Propellant amount: Stage 2 1.7678 m Stage 1 1462.00 kg Stage 3 0.9874 m Stage 2 566.64 kgDiameter: Stage 3 37.26 kg Stage 1 1.3015 m Engine type: Stage 2 0.6741 m Stage 1 Hybrid Stage 3 0.2721 m Stage 2 SolidInert mass: [1] Stage 3 Solid Stage 1 349.477 kg Thrust: Stage 2 153.4559 kg Stage 1 34045.3 N Stage 3 14.8011 kg Stage 2 8782.6 NMaterial: Stage 3 625 N Stage 1 Al ISP: Stage 2 Al Stage 1 352.3 seconds Stage 3 Al Stage 2 309.3 secondsThickness: [2] Stage 3 309.3 seconds Stage 1 0.0037 m Expansion ratio: Stage 2 0.0055 m Stage 1 60 Stage 3 0.0022 m Stage 2 60AVIONICS Stage 3 60Features NOTESMass: 1. Inert masses include tank, skirt, and nose cone masses. Stage 1 6.024 kg 2. Thickness values pertain to the fuel tanks. Stage 2 30.2664 kg 3. Gondola square base width and length. Stage 3 1.2 kg 4. Gondola height.Total system power: 200 Watts 5. Used for LITVC.
Project Bellerophon 11
Performance Characteristics - 1 kg PayloadBALLOON STRUCTURE GONDOLA STRUCTUREFeatures FeaturesMinimum volume: 2,197.9 m3 Dimensions: 1[3]x1[3]x3.849[4] m3
Maximum volume: 190,040 m3 Material: AluminumMinimum diameter: 16.1312 m Thickness: 0.04 mMaximum diameter: 71.3312 m Weight: 227.114 kgMaterial: Polyethylene plastic film PROPULSIONGas used: Helium FeaturesShape: Spherical Propellant type:STRUCTURES Stage 1 H2O2 & HTPBFeatures Stage 2 HTPB/AP/Al & H2O2
[5]
Length: Stage 3 HTPB/AP/Al Stage 1 4.1555 m Propellant amount: Stage 2 1.4816 m Stage 1 947.9 kg Stage 3 1.0554 m Stage 2 336.92 kgDiameter: Stage 3 45.09 kg Stage 1 1.1264 m Engine type: Stage 2 0.5669 m Stage 1 Hybrid Stage 3 0.2900 m Stage 2 SolidInert Mass: [1] Stage 3 Solid Stage 1 97.0893 kg Thrust: Stage 2 30.6403 kg Stage 1 21435.5 N Stage 3 5.8567 kg Stage 2 6052.4 NMaterial: Stage 3 743.4 N Stage 1 Al ISP: Stage 2 Al Stage 1 352.3 seconds Stage 3 Al Stage 2 309.3 secondsThickness: [2] Stage 3 309.3 seconds Stage 1 0.0032 m Expansion ratio: Stage 2 0.0046 m Stage 1 60 Stage 3 0.0024 m Stage 2 60AVIONICS Stage 3 60Features NOTESMass: 1. Inert masses include tank, skirt, and nose cone masses. Stage 1 6.024 kg 2. Thickness values pertain to the fuel tanks. Stage 2 30.2664 kg 3. Gondola square base width and length. Stage 3 1.2 kg 4. Gondola height.Total system power: 200 Watts 5. Used for LITVC.
Project Bellerophon 12
Performance Characteristics - 5 kg Payload
Project Bellerophon 13
200 g Failure
Project Bellerophon 14
1 kg Failure
Project Bellerophon 15
John Tsohas’ Table200 g Payload
Stage mprop/(mi+mprop) V/stage mstage/GLOM Isp1 80.7% 3,808 m/s (32%) 70.11% 352.2s
2 78.69% 4,358 m/s (37%) 27.87% 309.3s
3 71.57% 3,740 m/s (31%) 2.02% 309.3s
1 kg Payload
1 77.11% 3,818 m/s (39%) 70.48% 352.2s
2 74.3% 3,211 m/s (32%) 25.97% 309.3s
3 72.7% 2,864 m/s (29%) 3.55% 309.3s
5 kg Payload
1 83% 3,211 m/s (32%) 78.95% 352.2s
2 79.44% 3,963 m/s (39%) 20.2% 309.3s
3 71.76% 2,978 m/s (29%) 0.85% 309.3s
Saturn VStage mprop/(mi+mprop) V/stage mstage/GLOM Isp
1 94.09% 75.83% 265-310s
2 92.04% 16.28% 421s
3 44.81% 7.89% 421s
Ariane 5 ECA
1 86.28% 71.81% 250-275s
2 93.17% 24.00% 434s
3 44.31% 4.19% 446s
Project Bellerophon 16
John Tsohas’ Table IIPayload Prop mass fraction – 3rd stage Payload mass fraction Payload mass fraction (3rd
Stage)200 g 0.0038 0.0077% 0.38%
1 kg 0.016 0.05733% 1.64%
5 kg 0.0935 0.07949% 9.35%
Vehicle Prop mass fraction – 3rd stage Payload mass fraction Payload mass fraction (3rd Stage)
Saturn V 0.0354 3.91% 49.6%
Ariane 4 0.0186 2.06% 1.64%