RP HASA
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- ふじよし おえづか
- 5 years ago
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1
2 RP HASA RP RP 59 i
3 4.3.3 SSTO RP RP SSTO A 97 B 105 C Proof of Concept 19 ii
4
5 ( ISS:International Space Station) ISS km ISS ISS Fig1.1 ISS( NASA) Fig1. Space Shuttle( NASA) - -
6 X-Prize (TSTO Two Stage to Orbit) SSTO(Single Stage to Orbit) SSTO TSTO X-33(SSTO) (TSTO)Fig Fig1.3 X-33( NASA) Fig1.4 Saenger( Deutsche Aerospace ) 1.1. (RP:Rocket Plane) RP Rocket Plane RP RP RP RP - 3 -
7 RP (POC:Proof of Concept) Fig1.5 RP POC RP Vehicle Design Trajectory Optimization Top down verification Concept of RP System Bottom up verification POC Fig1.5 Methodology for RP system feasibility evaluation - 4 -
8 1. RP 1 RP 3 RP Hypersonic Aerospace Sizing Analysis(HASA) [1] DATCOM [] (SQP :Sequential Quadratic Programming) [3][4] SQP POC 1 3 RP HASA DATCOM RP SQP - 5 -
9
10 .1 RP (TSTO :Two Stage to Orbit) Rocket Plane RP...1 ISS ISS - 7 -
11 RP Fig.1 Fig.1 Vertical take-off and Horizontal take-off T L D m g TSTO SSTO TSTO TSTO TSTO SSTO SSTO SSTO SSTO - 8 -
12 NASA X-33 SSTO Stage type Propulsion type T/O type SSTO TSTO Pure Rocket RBCC ABE+Rocket HTHL VTHL VTVL Fig. Category of Space plane RBCC:Rocket Based Combined Cycle ABE:Air Breathing Engine HTHL VTHL VTVL VTVL DC-X RP HTHL HTHL TSTO[Saenger ] SSTO SSTO ( ) - 9 -
13 SSTO[X-33 ] ( ).. RP..1 RP RP RP RP RP RP RP RP TSTO SSTO RP ISS RP V ef V Mb + Ml V = Vef ln V Mb + Ml + Mp Mb + Ml = Vef ln V M 0 loss loss (.1) V ef =Ispg 0 Isp
14 g 0 V loss Mb Ml Mp M 0 M 0 = Mb + Ml + Mp (.) RP 3ton (.1) Fig.3 Fig.5 u1=14.4% Fig.3 Ideal V of SSTO u 1 M 0 Isp 445sec.1 ISS 8000m/s 000m/s H- Fig.4 [5]
15 Fig.4 Loss of Velocity of H- Rocket H- 1 H- 300ton RP ~3 RP H- 14.4% RP m/s RP ISS m/s Fig m/s 1/3 Fig.5-1 -
16 M0=70ton u1=14.4% Fig.5 Ideal V of RP system Fig % 70ton 9000m/s RP SSTO RP SSTO SSTO RP 3 4 RP RP 3 RP Fig
17 Fig.6 Oblique wing ( NASA) RP Isp 340sec Isp 450sec 71kg/m 3 RP Isp 340sec (.1) RP (IP:Interface Point) RP H- LE-7 GX RD-180 RP
18 Table.1 Engine performance Fig.7 LE-7,LE-7A( NASDA) Fig.8RD-180( Lockeed Martin) RP (1) () (1) 5% RP () () (1)
19 () (Ekranoplan) (3) Fig.9 Fig.9 Ekranoplan (1) HOTOL () m 0 5 [6] 375ton ton (3) RP 100km/s RP 00km/s 300km/s [7] RP
20 RP Fig.10 Return wing Stabilizer RD-180 Main wing LE-7 Fig.10 RP Image
21 RP RP RP RD-180 ( ) LE-7 ( ) M<0.5 Run M=0.5 take-off nd phase (LE-7) 1st phase (RD-180) Drop main wing Change engine Fig.11 Flight concept
22 .3 RP RP (1) () (3) (4) (5) (6) (7)SSTO (8) RP (1) () (3) (4) (5)
23
24 3 3.1 RP POC 3 f ( ) minimize x (3.1) Subject to; ( x) = 0 ( = 1,, ) p i n (3.) i ( x) 0 ( = 1,, ) q j m (3.3) j (3.) (3.3) f(x) x SQP SQP RP 3.3 HASA DATCOM HASA,, DATCOM,
25 RP Table3.1 Table 3.1 Vehicle design variables - -
26 RP Table3.1 Table RP RP RP HASA HASA 0HASA RP IP IP IP IP RP 3 HASA DATCOM RP RP IP ( ) ( )
27 HASA RP RP RP t/c 1 RP 3 x/c 0.5 RP x/c=0.5 [rad -1 ](0.1093[deg -1 ]) (Fig3.1 [8] ) t/c= [deg -1 ] Fig 3.1 Airfoil lift coefficient - 4 -
28 H- 4.0m R/t=1000 [9].0m 0.00m 0.5m 4.5m 1m 100km/h(7.8m/s) 400ton 300km/h(83.3m/s) [7] 400 /h(111m/s) 400ton 0.5(170m/s) ton 000ton [5] RP 83m/s170m/s C L =
29 S=300m S=550m Fig 3. V 0 vs S U=0.46 U=0.4 U1=0.18 U1= V 0 vs u 1 and u u1 u 400ton
30 Fig3. 83m/s m 170m/s m m/s RP RP m/s 7800m/s 8000m/s 300km/h, 10deg 3ton ISS 50kPa, m/s,1500m/s,000m/s 5deg,7deg,10deg,1deg,15deg,17deg,0deg,deg - 7 -
31 3.3 HASA DATCOM Mb M 0, u 1,, Mb= u1 M0 (3.4) M w b, u,, M w = u Mb (3.5) M final, M = Mb M (3.6) final w Mp M 0 =Mp+Mb+Ml,, Mp = M Mp Ml (3.7) 0 M LE7, Mach IP V f km,,, a 0 Mach IP, M 0 v= Vef ln + v0 (3.8) M,M,M 0,v 0, v V ef - 8 -
32 Vef = Isp g (3.9) 0 Isp, M LE7 V Isp g M + M a Mach V final LE7 f _ able = LE7 0ln + 0 IP loss _ after M final (3.10) (3.10) M LE7, M M V a Mach + V M f 0 IP loss_ after LE7 = final exp final IspLE7 g0 (3.11) V loss_after 000m/s RP m/s Vloss 5, Vloss Vloss _ after = ( 5 MachIP ) (3.1) 5 (3.11), M RD180, Mp, M RD180 RD-180 M = Mp M (3.13) RD180 LE7 M RP1 RD RP-1 LOX RP-1 1 MRP 1 = MRD 180 (3.14) 3.7 M LH - 9 -
33 LE-7 6, 1 MLH = MLE7 (3.15) 7 M LOX RD-180,LE-7,.7 6 MLOX = MRD MLE7 (3.16) V RP1,V LH,V LOX RP-1,,, 807kg/m 3, 71kg/m 3,1149kg/m 3, V / 807 RP1 = MRP 1 (3.17a) V /71 LH = MLH (3.17b) V = M /1149 (3.17c) LOX LOX 3.3. S need1 RP-1 Table.1 Fig.1 V k S 1.5 enable = (3.18),V enable,s (3.18) Table4.1 Fig
34 Table.1 Fuel coefficient Fig3.4 Wing area vs Fuel coefficient Venable 1.5 = S (3.19) (3.19) S
35 S need Venable = (3.0) 1 RP 5~8 RP RP RP-1 (3.0) % RP 3% RP RP RP-1 (3.0) S need 0.07 Venable = (3.1) RP-1 RD-180,LE-7,, L LH,L LOX D tnk 4.0m, t 0.00m 800kg/m3 Fig3.5, L π π 3 4 Dtnk Dtnk LH = VLH- / +Dtnk LLOX = π π 3 4 Dtnk Dtnk VLOX - / +Dtnk (3.a) (3.b), - 3 -
36 Fig 3.5 Tank model Lb L nose Fig3.6 Lb = L + L + L (3.3) LH LOX nose L/W L / W = Lb/ Db (3.4) Fig3.6 Fuselage mode M tnk,, M 800 t 4 D L _ 3 Dt nk tnk = π π LH + tnk LH M 800 t 4 D L _ 3 Dt nk tnk = π π LOX + tnk LOX (3.5a) (3.5b) M = M + M (3.6) tnk tnk _ LH tnk _ LOX
37 3.3.3 b, TR 1/ Fig3.7 C 0 HOPE-X 85deg b tan λ + b/ tanφ C0 = (3.7) 1-TR Ct C 0 TR Ct = TR C 0 (3.8) S ( TR) bc 0 1+ S = (3.9) AR b AR = (3.30) S Fig3.7 Main wing model MAC C 0 C t MAC CC 0 t MAC = C0 + Ct 3 C 0 + C t (3.31)
38 C L, DATCOM π AR exposed C L = f α AR tan ( λ) (+(4+ 1 ) + η β S S (3.3) (3.3) β =1-Mach 0 (3.33) Clα β η= π (3.34) Db f=1.07 (1+ ) b (3.35) S exposed, S exposed Db Sexposed = S Db C0 4tanθ (3.36),, 1 b θ = tan 1 ( TR) C0 b /tanφ (3.37) S need 1 Mg 0 0 LRW = ρ0vs 0 need CL α α (3.38) (3.38) S need ( Mg 0 0 LRW ) Sneed = (3.39) ρv C 0,L RW L L 1 L= ρv0 CLS+ LRW (3.40)
39 D 1 D= ρv0 CDS (3.41) 3.3.4, V return 300m/s, return 10deg b RW, RW, TR RW t/c 0.03, Cl, C 0RW brw tan λrw C0 = (3.4) RW 1 TR RW C trw C 0RW TR C = TR C (3.43) trw RW 0RW S RW, 1 SRW = brw C0 ( 1+ TR RW RW ) (3.44) AR RW brw ARRW = (3.45) S RW
40 Fig 3.8 Return wing model MAC RW C MACRW = C0RW + CtRW 3 C 0RW 0RW C + C trw trw (3.46) CL RW,DATCOM π AR RW RWexposed C L = f α RW RW AR SRW RW tan ( λrw ) (+(4+ 1 ) + ηrw βrw S (3.47),S exposed, S exposed /S RW =0.5 β =1-Mach (3.48) RW Clα RW βrw ηrw = π (3.49) Db f RW =1.07 (1+ ) brw (3.50),Mach return return CL return return
41 C =C αreturn (3.51) Lreturn Lαreturn S RWneed S RW S RWneed 1 M final g0 = ρ0vreturnsrwneedcl return αreturn α (3.5) (3.5) S RWneed, S RWneed = M final g0 ρ0vreturncl α α (3.53) return return L return 1 Lreturn = ρvreturnclreturnsrw (3.54) D return 1 Dreturn = ρvreturncdreturnsrw (3.55) L RW, 1 LRW = ρ0v0srwcl RW 0 α α (3.56) C D0 (3.57) C = C + KC (3.57) D D0 L Buildup Component Method[] (Cf) (FF) (Q) (Swett)
42 C Dmisc C DL&P (3.58) c ( ) Cf ( CfcFFQ c cswetc ) C = + C + C 0 L& D D subsonic Dmisc D Sref 3.58 Cf C f = ( log R).58 ( M ) R R = ρ Vl / µ l FF (3.61)(3.63) 3.61 (x/c) m m t t FF = M ( cos Λm ) ( x/ c) c c m f FF = f 400 FF 1 ( 0.35/ f ) 3.6 =
43 f l l = = 3.64 d ( 4/ π ) Amax A max Q Q 1.5 Q 1.3 Q 1.0 Q Q=1.0 Q=1.03 Q=1.08 4~5 Buildup Component Method ρv0 Lb Rbody = (3.65) µ C fbody =.58 log R Mach ( 10 body ) ( 0 ) (3.66) 60 f FFbody = 1+ f Lb f = Db 3.68 Q = 1.0 (3.69) body π Swett _ body = Db Lb (3.70) ρv0 MAC Rwing = µ (3.71) C fwing =.58 log R Mach ( 10 wing ) ( 0 ) (3.7)
44 4 t t m 0.6 x/ c c c 0.18 FF = Mach ( cos λ ) ( ) wing 3.73 Q = 1.3 (3.74) body S =.003S (3.75) wett _ wing exposed ρv0 MACRW RRW = (3.76) µ C frw = log R Mach ( ).58 ( 10 RW 0 ) t t x/ c c c m 0.18 FF = Mach ( cosλ ) ( ) RW (3.77) 3.78 Q = 1.3 (3.79) RW S =.003S (3.80) wett _ RW RWexposed C D0 C FF Q S + C FF Q S + C FF Q S = S fbody body body wett _ body fwing wing wing wett _ wing frw RW RW wett _ RW (3.81) C = C + KC (3.8) D D0 L Swept-Wing K K 1 = (3.83) πar ( AR 0.68 )cos 0.15 λ-3.1)
45 R body ρv Lb µ return = (3.84) C fbody = ( log10 Rbody ) ( Machre ) (3.85) FF body 60 f = f Lb f = Db 3.87 Q = 1.0 (3.88) body S wett _ body π = Db Lb (3.89) R RW ρv MAC µ return RW = (3.90) C frw = ( log ).58 ( 10 RRW Mach0 ) (3.91) FF RW t t = Mach0 ( cosλ ) (3.9) ( x/ c) c c m Q = 1.3 (3.93) RW ( ) S _ = S _exp ( t/ c) (3.94) wett RW RW osed C C FF Q S + C FF Q S fbody body body wett _ body frw RW RW wett _ RW D0return= (3.95) S C = C + KC (3.96) Dreturn D0return L Swept-Wing K K 1 = (3.97) πar ( AR 0.68 )cos 0.15 λ-3.1) (3.81) (3.95) - 4 -
46 (3.81) (3.95) HASA,,HASA HASA 1 1 (1) () (3) (4) (5) (6) (7) (8) (9) (10) (11) (1) HASA 1988, HASA,,,RP,, M fuse Lb _ F ULF M fuse _ F = mf Qmax _ F Sb_ F Db _ F 0.15 ( ) ( ) (3.98) Sb, Sb = πdb C 0 (3.99) M whasa Mb _ F ULF TR 0.7 MwHASA _ F = mf S _ F AR t/ c cos λ (3.100)
47 M RW M final _ F ULF _ TRsub MRW F = mf SRW _ F ARRW t/ c cos λrw (3.101) M finv M _ F 5.0 S _ F finv 1.09 = finv (3.10) M tps M _ F = Wins_ F S _ F (3.103) tps wett,swett,, π Swett = SRW + Db Lb (3.104) 4 M thrur M thrur _ F = T _ F (3.105) T_F [lbf] M engine RPRD-180 LE-7 1 LE-7 1.7ton,RD ton, M engine = (3.106) = 7000 M tnk M = M + M (3.107) tnk tnk _ LOX tnk _ LH
48 M hydr ( S_ F + Sfinv _ F) M hydr _ F =.64 Lb_ F + b_ F 1000 ( ) 0.5 (3.108) M elect M _ F M _ F Lb_ F elect = 0 (3.109) Mb HASA,HASA Mb HASA = M body + M wing + M RW + M finv + M tps + M thrur + M engine + M tnk + M hydr + M elect (3.110) M 0HASA HASA bhasa Ml, M = M + Ml + Mp (3.111) 0HASA bhasa IP M IP_before M = M M (3.11) IP _ before 0HASA RD180 IP M IP_after M = M M M IP _ after 0HASA RD180 whasa = M M IP _ before whasa IP V IP_need IP IP V = a Mach (3.114) IP _ need 0 IP
49 V IP M 0HASA M IP_before M 0HASA VIP _ able = IspRD 180 g0ln + V0 Vloss _ before (3.115) M IP _ before V loss Vloss Vloss _ before = MachIP (3.116) 5 V f_able M V = Isp g ln + V V (3.117) IP _ after f _ able LE7 0 IP _ able loss _ after M final L/D L/D CL L/ D= (3.118) C D L/D return L/D CLreturn L/ Dreturn = (3.119) C Dreturn 1 HASA Mb HASA σ Mb Mb HASA 1 = (3.10) MbHASA HASA Mw HASA
50 σ M M whasa w = (3.11) M whasa HASADATCOM Optimization Variables M0 u1 u MachIP b TR brw TRRW RW Mb C0 S AR C0RW SRW ARRW Mp Mw Mfinal MLE7 MRD180 VLH VLOX VRP1 Mtnk Lb Sneed1 L/W HASA DATCOM Mfuse MwHASA MRW Mfinv Mtps CD CL CLRW CLreturn CDreturn Mthrur Mengine Mhydr Melect L/D Sneed SRWneed L/Dreturn MbHASA M0HASA MIP_before MIP_after Constraint Variable VIP_able Vf_able Constraint Relation Objective Function Fig Determination of Variables
51 3.4 f = M 0HASA : ( ) (3.1) M 0 Mach b TR IP λ brw (3.13) TRRW λrw 1/ u1 u S S S S SRW S L/ D 6 need1 need L/ Dreturn 6 (3.14) VIP _ able VIP _ need Vf _ able Vf σ1 ε σ ε RWneed ( ) ( ) M 0HASA HASA
52
53 SQP 4. HASA RP 010 RP SSTO SSTO 3 ( ) Fig4.1 Composite utilization
54 [10] [11] % RP HASA RP RP CFRP 58 CFRP 0.75 HASA kg/m 3 CFRP 1600kg/m 3 CFRP TPS TPS TPS [11] TPS TPS 0.60 SSTO
55 4.3 SQP, Vloss Vloss=1000,1500,000 [m/s] =(5,7),10,1,15,17,0,,(5) [deg] 0.3Lb RP L/D, Vloss 1000m/s Fig4. Take off Angle of attack vs M 0 and Mw - 5 -
56 Fig4.3 Take off angle of attack vs Required wing area Fig 4.4 Take off angle of attack vs Take off L/D
57 Fig4.5 Take off angle of attack vs Aspect ratio
58 Vloss 1500m/s Fig4.6 Take off angle of attack vs M 0 and Mw Fig 4.7 Take off angle of attack vs Required wing area
59 Fig4.8 Take off angle of attack vs Take off L/D Fig4.9 Take off angle of attack vs Aspect ratio
60 000m/s Fig4.10 Take off angle of attack vs M 0 and Mw Fig 4.11 Take off angle of attack vs Required wing area
61 Fig4.1 Take off angle of attack vs Take off L/D Fig4.13 Take off angle of attack vs Aspect ratio
62 Fig4.,4.6,4.10 (Fig4.3,4.7,4.11) Fig4.,4.6,4.10 L/D L/D 6 L/D (3.97) (3.100) 17deg 1000m/s,1500m/s,000m/s 380ton,500ton,640ton
63 1000m/s Fig4.14 Take off angle of attack vs M 0 and Mw Fig4.15 Take off angle of attack vs Required wing area
64 1500m/s Fig4.16 Take off angle of attack vs M 0 and Mw Fig4.17 Take off angle of attack vs Required wing area
65 000m/s Fig4.18 Take off angle of attack vs M 0 and Mw Fig4.19 Take off angle of attack vs Required wing area - 6 -
66 ,17deg, 1000m/s,1500m/s,000m/s 3ton,84ton,353ton SSTO SSTO 1000m/s Fig4.0 Take off angle of attack vs M 0 and Mw
67 Fig4.1 Take off angle of attack vs Required wing area 1500m/s Fig4. Take off angle of attack vs M 0 and Mw
68 Fig4.3 Take off angle of attack vs Required wing area 000m/s Fig4.4 Take off angle of attack vs M 0 and Mw
69 Fig4.5 Take off angle of attack vs Required wing area SSTO 0deg 1000m/s,1500m/s,000m/s 50ton,334ton,476ton
70 4.4 Fig4.6 A-1 B-1 C-1 A- B- C- A-3 B-3 C-3 Fig 4.6 Result for Body optimization 1000m/s 380ton 000m/s 600ton 3ton 600ton 000m/s 350ton SSTO 480ton [13] m/s 1500m/s RP 500ton 80ton SSTO 330ton
71 Fig4. Table4.1 RP 1000m/s,1500m/s,000m/s A-1,A-,A-3 RP SSTO B-1,B-,B-3 C-1,C-,C-3 Table4.1 Definition of Optimized Vehicle Model
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73 n 5. h h ρ = 1.5e (5.1) T h 0 h < T = h h < 0000 T = h < 3000 T = ( h- 0000) 3000 h < T = ( h- 3000) h < T = (5.) h < T = ( h ) h < T = ( h ) h < T = h h h T = 760(1- exp(( h) / 54800)) / T µ = (5.3) T
74 g h g g R 0 = 0 R0 + h (5.4) R 0,g km,9.807m/s RP dv F cosα D = g sin γ (5.5) dt m dγ Fsinα + L v v = g cosγ dt m r (5.6) ds R = v cos γ dt r (5.7) dr dh = = vsinγ dt dt (5.8) dm = mt () dt (5.9) F L D s h r m Isp (5.9) F m = (5.10) Isp g L, D 1 L= ρv CLS (5.11) 1 D= ρv CDS (5.1) 0 71
75 H- 300m/s t f Vloss = g sinγ dt (5.13) gravity 0 t f D Vlossdrag = dt (5.14) m DATCOM 5.3.1, DATCOM π AR exposed C L = f α AR tan ( λ) (+(4+ 1 ) + η β S S (5.15) (5.15) β =1-Mach (5.16) Clα β η= π (5.17) Db f=1.07 (1+ ) b (5.18) C L CL α = α (5.19) 7
76 ρv Lb V Lb Rbody = = (5.0) µ υ C fbody =.58 log R Mach ( 10 body ) ( ) (5.1) 60 f FFbody = 1+ f Lb f = Db 5.3 Q = 1.0 (5.4) body π Swett _ body = Db Lb (5.5) ρv MAC V MAC Rwing = = µ υ (5.6) C fwing =.58 log R Mach ( 10 wing ) ( ) t t 0.8 x/ c c c m 0.18 FF = Mach ( cos λ ) ( ) wing (5.7) 5.8 Q = 1.3 (5.9) body S =.003S (5.30) wett _ wing exposed 1.3 CfbodyFFbodyQbodySwett _ body + Cfwing FFwingQwing Swett _ wing CD0 = 1.3 (5.31) S C = C + KC (5.3) D D0 L Swept-Wing K 1 K = (5.33) πar ( AR 0.68 )cos 0.15 λ-3.1) 73
77 5.3. (RW:Return Wing) RD180 M RD180 4 C L α = (5.34) Mach 1 C = α (5.35) L CL α CfbodySwett _ body + CfwingSwett _ wing IP CD0 = CDwave S (5.36) CfbodySwett _ body + CfRW Swett _ RW CD0 = CDwave S (5.37) RW l Recutoff = 44.6 k Mach 1.16 (5.38) (5.38) k Table5.1 Skin roughness value(k) Lb Rbody = 44.6 k Mach C fbody =.58 log R Mach 1.16 ( 10 body ) ( ) (5.39) (5.40) 74
78 ( ) π Swett _ body = Db Lb (5.41) MAC Rwing = 44.6 k Mach C fwing =.58 log R Mach 1.16 ( 10 wing ) ( ) (5.4) (5.43) S =.003S (5.44) wett _ wing exposed ( ) MACRW RRW = 44.6 k Mach C frw = log R Mach 1.16 ( ).58 ( 10 RW ) (5.45) (5.46) S =.003S (5.47) wett _ RW RWexposed Sears-Haack-body Sears-Haack-body ( D/ q) ( D/ q) Sears-Haack Sears-HaackRW 9π Amax = Lb 9π Amax RW = Lb (5.48a) (5.48b) Sears-Haack-body Sears-Haack-body Sears-Haack-body ( ) ( ) ( *180 / π) π λ D/ q = Ewd Mach 1. 1 D/ q wave 100 ( ) Sears-Haack (5.49a) 75
79 ( ) ( ) ( *180 / π) π λ RW D/ q = Ewd Mach 1. 1 D/ q waverw 100 ( ) Sears-HaackRW (5.49b) A max Ewd Sears-Haack A max + ( ) IP C = C + KC (5.50) D D0 L K = ( 1) AR Mach 4AR Mach 1 cos λ (5.51)
80 5.4 4 RP IP u v mg = + (5.5) 10km ISS 8000m/s, 10km 0 50kPa u maximize (5.53) n α i ( i = 1,,, n) (5.54) i ( ) ( ) h 0 i=1,,,n Q i=1,,,n (5.55) v n i V IP v maximize (5.56) n α i ( i = 1,,, n) (5.57) i ( ) ( ) h 0 i=1,,,n Qi i=1,,,n h = 1000 n γ = 0 n (5.58) i n 0 77
81 5.4. RP RP Fig5.1 Result of velocity Fig5. Result of height 78
82 Dynamic Pressure=50kPa Fig5.3 Velocity vs Height Fig5.4 Distance vs Height 79
83 Fig5.5 Result of Angle of attack 1500m/s,000m/s (A-,A-3) 8000m/s Fig5.6 Loss of velocity (A-1Model) 80
84 Fig5.7 Loss of velocity (A-Model) Fig 5.8 Loss of velocity (A-3Model) 10km 8000m/s 81
85 700800m/s 00~400m/s H- 1700m/s RP Table 5. Result of Present RP model Table m/s (A-1) H m/s 1000m/s RP RP Fig 5.9 Result of velocity 8
86 Fig 5.10 Result of height Dynamic Pressure=50kPa Fig 5.11 Velocity vs Height 83
87 Fig 5.1 Distance vs Height Fig 5.13 Result of Angle of attack ISS 84
88 Fig 5.14 Loss of Velocity (B-1 Model) Fig 5.15 Loss of Velocity (B- Model) 85
89 Fig 5.16 Loss of velocity (B-3 Model) Table 5.3 Result of Next RP model 1000m/s 300m/s 1500m/s RP RP RP RP SSTO SSTO 86
90 Fig 5.17 Result of velocity Fig 5.18 Result of height 87
91 Dynamic Pressure=50kPa Fig5.19 Velocity vs Height Fig5.0 Distance vs Height 88
92 Fig 5.1 Result of Angle of attack Fig 5. Loss of Velocity (C-1 Mode) 89
93 Fig 5.3 Loss of Velocity (C- Model) Fig 5.4 Loss of velocity (C-3 Model) SSTO SSTO 90
94 Table 5.4 Result of Next SSTO model Fig5.5 Velocity vs Height(velocity loss =1000m/s model) 91
95 Fig5.6 Velocity vs Height(velocity loss =1500m/s model) Fig5.7 Velocity vs Height(velocity loss =000m/s model) 9
96 km ISS 8300m/s 8300m/s 300m/s ISS 8000m/s B-1 C-1 B- C- B-3 A-1 A- C-3 final velocity=8300m/s A-3 Fig5.8 Result of trajectory optimization Fig5.8 0 A-,B-,C-3 0 RP 40ton, RP 75ton, SSTO 480ton 93
97 Fig5.9 A- model Fig5.30 B- model Table 5.5 Parameter of A- mode M0[Mg] 497. S[m ] 37.9 Lb[m] b[m] AR 1.06 Table 5.6 Parameter of B- mode M0[Mg] 84.8 S[m ] Lb[m] b[m] AR 1.45 Fig5.31 C-3 model Table 5.5 Parameter of C-3 mode M0[Mg] S[m ] 34.9 Lb[m] b[m] 4.16 AR
98
99 6 RP RP 1000m/s,1500m/s,000m/s RP 500ton, RP 80ton, SSTO 480ton 500ton 170m/s RP RP SSTO
100 [1] Gary J.HarloffBrian M.Berkowitz:HASA-Hypersonic Aerospace Sizing Analysis for the Preliminary Design of Aerospace Vehicles1988 [] Dnaniel P.Raymer:Aircraft Design:A Conceptual AttroachAIAA1999 [3] : 00 [4] :FORTRAN [5] : 001 [6] Nobuyuki Tomita Alexander V.Nebylov Victor V.Sokolov Yoshiaki Ohkami:Performance and Technological Feasibility of Rocket Powered HTHL-SSTO with Take-off Assist(Aerospace Plane/Ekranoplane)1999 [7] :TSL VOL.37, ,1998 [8] : 1968 [9] : 199 [10] : 001 [11] L.B.ILCEWICS: Composite Applications in Commercial Airframe Structures [1] : TPS 1999 [13] : 1997 [14] : 1989 [15] : 1993 [16] : 1998 [17] :
101 POC POC POC POC POC
64 3 g=9.85 m/s 2 g=9.791 m/s 2 36, km ( ) 1 () 2 () m/s : : a) b) kg/m kg/m k
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II Karel Švadlenka * [1] 1.1* 5 23 m d2 x dt 2 = cdx kx + mg dt. c, g, k, m 1.2* u = au + bv v = cu + dv v u a, b, c, d R
![II Karel Švadlenka * [1] 1.1* 5 23 m d2 x dt 2 = cdx kx + mg dt. c, g, k, m 1.2* u = au + bv v = cu + dv v u a, b, c, d R](/thumbs/95/125540821.jpg "II Karel Švadlenka * [1] 1.1* 5 23 m d2 x dt 2 = cdx kx + mg dt. c, g, k, m 1.2* u = au + bv v = cu + dv v u a, b, c, d R")
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Stacking sequence optimization of composite wing using fractal branch and bound method Orbiting Plane : HOPE-X (JAXA) Fractal Branch and Bound Method (FBBM) Fractal structure of design space 5 y V a 9º
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(Compton Scattering) Beaming 1 exp [i (k x ωt)] k λ k = 2π/λ ω = 2πν k = ω/c k x ωt ( ω ) k α c, k k x ωt η αβ k α x β diag( + ++) x β = (ct, x) O O x
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3 February 25, 2009 1 Armijo Wolfe Newton 2 Newton Lagrange Newton 2 SQP 2 1 2.1 ( ) S R n (n N) f (x) : R n x f R x S f (x ) = min x S R n f (x) (nonlinear programming) x 0 S k = 0, 1, 2, h k R n ɛ k
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医系の統計入門第 2 版 サンプルページ この本の定価 判型などは, 以下の URL からご覧いただけます. http://www.morikita.co.jp/books/mid/009192 このサンプルページの内容は, 第 2 版 1 刷発行時のものです. i 2 t 1. 2. 3 2 3. 6 4. 7 5. n 2 ν 6. 2 7. 2003 ii 2 2013 10 iii 1987
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