Development of a Mass Estimating Relationship Database for ...

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3.0 Body V f – Total fuel volume V i – Fuel volume in integral tanks V ox – Total oxidizer volume ρ f – Density of fuel ρ ox – Density of oxidizer θ nose – Nose cone angle Georgia Institute of Technology 3-3
3.0 Body Reference: 1 Derived from: Aircraft and Space Shuttle. Options: Materials, windshield, and tanks.. body c 0.5 crew b body 1/ 3 z f f ox 1.1 ox t 1. 15 ( N T ) K S M = K N + K A N + K V + K V + K + Crew cabin constants K c = 2043 – full windshield aluminum construction = 1293 – aluminum construction with no windshield = 1740 – full windshield composite construction = 1140 – composite construction with no windshield eng vac bf bf Space Shuttle Comparison -7% Assumes no ascent propellant in orbiter. Body construction constants K b = 2.72 – composite structure, no TPS = 3.20 – aluminum structure, no composites, no TPS = 3.40 – hot metallic Ti/Rene HC, no TPS required = 4.43 – moldline tankage; tank, body structure, cryogenic insulation integrated Tank geometry/propellant constants K f , and K ox – see table below. Georgia Institute of Technology 3-4
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: 3.0 Body N crew - Number of crew N
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 and 50: 3.0 Body M ox _ tan ks 0. 0255 = M
Page 51 and 52: 3.0 Body Reference: 4b Derived from
Page 53 and 54: 3.0 Body Reference: 5 Derived from:
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
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6.0 Main Propulsion Reference: 2 De
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6.0 Main Propulsion Reference: 4a D
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6.0 Main Propulsion Reference: 4b D
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6.0 Main Propulsion purge V body =
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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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