Development of a Mass Estimating Relationship Database for ...

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1.0 Wing Reference: 10b Derived from: Hypervelocity Aircraft Options: Continuous our discontinuous carry thru, landing gear location, strakes, trailing edge extension, and more. M = K K K K K K K K K K K K + K wing _ box wing lcf trc arc tac swc bwc gear dwr tm ps dc dw Space Shuttle Comparison -34% Elastic Axis Sweep =30deg ? bexp=baero ? 1.334 K wing = .7072S - for continuous wing/carry-thru structures 0 ref 1.334 = 0.7072S - for discontinuous wing/carry-thru structures (mid mount wings) exp S exp – Exposed wing planform area S ref – theoretical wing planform area K lfc – loading correction factor = 0.581 0.5585 0.00286N z Pexp + 0.1624N z N z – Ultimate load factor = 1.5*2.5 (factor of safety * limit load) P exp – Exposed wing planform loading (lb/ft 2 ) −1.385 ⎛ t ⎞ K trc – taper ratio correction factor = 0.0141⎜ ⎟ + 0. 758 ⎝ c ⎠ struct (t/c) struct – Thickness to chord ratio of the wing structure K arc – aspect ratio correction factor 1.148 = 0.0588AR exp + 0.28 AR exp – Aspect ratio of the exposed wing (b 2 exp/S exp ) K tac – taper ratio correction factor 0 .47R + 0. 833 = t Georgia Institute of Technology 1-12
1.0 Wing Rt – Wing taper ratio = tip chord over centerline root chord K swc – sweepback correction factor θ elastic_axis – unknown number?? −1.282 = 0.9031cos( θ elastic _ axis ) K bwc – body width correction factor b = 1.011− 0.07 b body b body – maximum width of vehicle body b exp – Exposed wing span = wing span less b body exp ⎛ b − 0.5⎜ ⎝ b body exp ⎞ ⎟ ⎠ 2 K gear – landing gear support penalty = 1.1 – for wing mounted gear, 1.0 – otherwise K dwr – dead weight relief factor = 1.0 – for wing without fuel or vertical tail ⎛ M f _ wing D f _ wing + M vert _ wing Dvert ⎞ = −1.2⎜ ⎟ − for wings with fuel and vertical tails attached. ⎝ 0.5M wing Dcp ⎠ D vert – distance from vehicle centerline to CG of wing mounted vertical tail D f_wing – distance from vehicle centerline to CG of wing stored fuel D cp – distance from vehicle centerline to wing center of pressure M f_wing – mass of fuel in the wing M vert_wing – mass of vertical control surfaces attached to the wing M wing – mass of the wing K tm – temperature and materials factor = 1.0 – for aluminum = 1.15 – for titanium = 2.8 – for nickel based superalloy Georgia Institute of Technology 1-13
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:
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Page 21 and 22: 1.0 Wing Reference: 4a Derived from
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Page 29 and 30: 2.0 Tail 2.0 Tail AR vert - Aspect
Page 31 and 32: 2.0 Tail Reference: 2 Derived for:
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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 and 50: 3.0 Body M ox _ tan ks 0. 0255 = M
Page 51 and 52: 3.0 Body Reference: 4b 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:
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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
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5.0 Landing Gear Reference: 3 Deriv
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5.0 Landing Gear Reference: 4b Deri
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5.0 Landing Gear Used M glow for co
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5.0 Landing Gear Reference: 10c Der
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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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