Development of a Mass Estimating Relationship Database for ...

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3.0 Body Chart showing inlet weight per square foot of inlet area as a function of inlet pressure for three different vehicle configurations. Source [ref. 4]. Georgia Institute of Technology 3-13
3.0 Body Reference: 4b Derived from: Lifting body rocket. Options: None. M = 3 .0724A + 0. 0008T body body vac N eng Body mass including fuselage, thrust structure, and miscellaneous, for a lifting body upper stage. Space Shuttle Comparison N/A Lifting body design M crew _ cabin = 1801 + 1.15V crew + 180 Mass of crew cabin and windscreen/canopy. This reference recommends that the volume for the crew be calculated as: V crew = 60N crew +255 M 0. 224S M M aft _ skirt = body Mass of aft skirt, aerodynamic fairing over engines. S body – Planform area of vehicle body ox _ tan k = 0. 0181 M tot _ ox Mass of liquid oxygen tank for lifting body second stage M tot_ox – Mass of all oxidizer on stage f _ tan k = 0. 1188 M tot _ fuel Mass of liquid hydrogen tank for lifting body second stage, including mounting. M tot_fuel – Mass of all fuel on stage M _ = 555 f ins 0.666 1. V f Mass of insulation for liquid hydrogen tank on lifting body second stage. V f – Total fuel volume Georgia Institute of Technology 3-14
Page 1 and 2: Development of a Mass Estimating Re
Page 3 and 4: 20.0 Residual Propellants .........
Page 5 and 6: Acronyms & Notation AMLS AVID EMA E
Page 7 and 8: for air-breathing launch vehicles.
Page 9 and 10: Equations that predict this vehicle
Page 11 and 12: . The second stage is a rocket powe
Page 13 and 14: 11. Hawkins [x] This source is focu
Page 15 and 16: 1.0 Wing 1.0 Wing AR - Aspect ratio
Page 17 and 18: 1.0 Wing Reference: 1 Derived from:
Page 19 and 20: 1.0 Wing Reference: 2 Derived for:
Page 21 and 22: 1.0 Wing Reference: 4a Derived from
Page 27 and 28: 1.0 Wing Rt - Wing taper ratio = ti
Page 29 and 30: 2.0 Tail 2.0 Tail AR vert - Aspect
Page 31 and 32: 2.0 Tail Reference: 2 Derived for:
Page 33 and 34: 2.0 Tail Reference: 4a Derived from
Page 35 and 36: 2.0 Tail Reference: 5 Derived from:
Page 37 and 38: 2.0 Tail Reference: 10 Derived from
Page 39 and 40: 3.0 Body N crew - Number of crew N
Page 41 and 42: 3.0 Body Reference: 1 Derived from:
Page 43 and 44: 3.0 Body K t = 0.0030 - aluminum th
Page 45 and 46: 3.0 Body K ns_cowl =2.21 - Ti3Al Be
Page 47 and 48: 3.0 Body S base - Surface area of b
Page 49: 3.0 Body M ox _ tan ks 0. 0255 = M
Page 57 and 58: 3.0 Body K thrust = 1.949e-3 - inli
Page 61 and 62: 3.0 Body M = 0. 5623 Payload bay do
Page 63 and 64: 4.0 TPS 4.0 TPS A acc - Area of adv
Page 65 and 66: 4.0 TPS Reference: 1 Derived from:
Page 67 and 68: 4.0 TPS Reference: 3 Derived from:
Page 69 and 70: 4.0 TPS Reference: 4b Derived from:
Page 71 and 72: 4.0 TPS M = mono _ tan k _ ins 0. 2
Page 73 and 74: 4.0 TPS A body_tps - Wetted area of
Page 75 and 76: 5.0 Landing Gear Reference: 1 Deriv
Page 79 and 80: 5.0 Landing Gear Reference: 4b Deri
Page 83 and 84: 5.0 Landing Gear Used M glow for co
Page 87 and 88: 5.0 Landing Gear Reference: 10c Der
Page 89 and 90: 6.0 Main Propulsion Reference: 1 De
Page 91 and 92: 6.0 Main Propulsion Reference: 2 De
Page 93 and 94: 6.0 Main Propulsion Reference: 4a D
Page 95 and 96: 6.0 Main Propulsion Reference: 4b D
Page 97 and 98: 6.0 Main Propulsion purge V body =
Page 99 and 100: 7.0 RCS 7.0 RCS L - Length of vehic
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7.0 RCS Reference: 2 Derived for: A
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7.0 RCS Reference: 3 Derived from:
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7.0 RCS Reference: 6 Derived from:
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7.0 RCS Reference: 10a Derived from
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8.0 OMS Reference: 1 Derived from:
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8.0 OMS Reference: 3 Derived from:
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8.0 OMS Reference: 10a Derived from
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9.0 Primary Power Reference: 1 Deri
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9.0 Primary Power Reference: 3 Deri
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9.0 Primary Power Reference: 4b Der
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9.0 Primary Power Reference: 10 Der
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10.0 Electrical Conversion & Distri
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11.0 Hydraulic Systems Reference: 1
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12.0 Surface Control & Actuators 12
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12.0 Surface Control & Actuators Re
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13.0 Avionics 13.0 Avionics A body
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13.0 Avionics Reference: 2 Derived
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13.0 Avionics Reference: 4a Derived
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13.0 Avionics Reference: 6 Derived
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13.0 Avionics Reference: 10a Derive
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14.0 Environmental Control & Life S
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15.0 Personnel Equipment Reference:
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16.0 Dry Weight Margin 16.0 Dry Wei
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16.0 Dry Weight Margin Reference: 2
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17.0 Crew & Gear Reference: 1 Deriv
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17.0 Crew & Gear Reference: 4a Deri
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17.0 Crew & Gear Reference: 6 Deriv
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18.0 Payload Provisions 18.0 Payloa
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18.0 Payload Provisions Reference:
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20.0 Residual Propellants 20.0 Resi
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20.0 Residual Propellants Reference
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20.0 Residual Propellants Reference
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21.0 OMS/RCS Reserve Propellants 21
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21.0 OMS/RCS Reserve Propellants Re
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22.0 RCS Entry Propellants 22.0 RCS
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22.0 RCS Entry Propellants Referenc
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23.0 OMS/RCS On-Orbit Propellants R
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23.0 OMS/RCS On-Orbit Propellants R
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25.0 Ascent Reserve Propellants 25.
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25.0 Ascent Reserve Propellants Ref
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26.0 Inflight Losses & Vents 26.0 I
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26.0 Inflight Losses & Vents Refere
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27.0 Ascent Propellants Reference:
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27.0 Ascent Propellants Reference:
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28.0 Startup Losses Reference: 1 De
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28.0 Startup Losses Reference: 3 De
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28.0 Startup Losses Reference: 10 D
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Reference: 6 Derived from data prov
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