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1 17 ε -SAT Electric PropulSIon system Loading moon transfer Orbit Navigation SATellite 1 1.1, Copyright: ESA 1: SMART-I ESA SMART-I( 1 ) JAXA( 2 ) JAXA ESA BepiColombo( 3 ) 1 2: 3: BepiColombo Copyright: JAXA 1

2 1.3 SMART-I BepiColombo SMART-I 1.4 () 1.5 Electric P ropulsion system Loading moon transfer Orbit Navigation SATellite epsilon SAT,ε SAT() ε(epsilon) moon mars mercury ε SAT 2

3 [mN/kW] 50[W] 1.5[mN] mn (JPL) miniaturexenon Ion (MiXI) thruster 2000[s]3000[s] 70[]. 1 MiXI 1: [mm] 30 [s] [W] [mn] [kg] 0.2 4: MiXI MiXI () () 5 3

4 5:. 18[deg] 12[deg] (3.2.1 ) (3.2.2 ) e = () (3.2.3 ) (3.2.4 ) (3.2.5 ) (3.2.6 ) 36000[km]. 2.4, 1 4

5 x ()x z ()x z y () 180[deg] [km] [km] [km] 66000[km] J2 () 3.1 RARR(Range And Range Rate) RARR(Range And Range Rate) RARR RARR phase 1() 70% 2[deg] phase 2() 5

6 300000[km] 3.3 SELENE 2: phase 3() L1 300[h](12.5[day]) [-] [km] [deg] 30.0 [deg] [deg] 0.0 [deg] 0.0 UTC+9 [-] L phase phase 5 phase phase xyz 1[mN] 2000[s] () phase1 phase L1 (phase3) 7 L km phase phase5 9 6

7 6: 7: 7

8 8: 9: 8

9 3.4.5 () [day] 36000[km] 32900[km] [deg] [day] 2.9[kg] 7894[h] [h] 3.6 MiXI 1.5[mN] 1.0[mN] RARR RARR 0.3[deg] [deg],,, [km], ,,,, [deg] 4.2,, 4 PD Range And Range Rate 9

10 10: 3: phase total [g] [m/s] [deg],. n w = k p V (q ˆBB )+k d( ωˆ B ω B ) 4: [deg] n w : q ˆBB : V (q ˆBB ) : ωˆ B : ω B : k p : P (= 0.04) k d : D (= 0.4) 10

11 11: 5: [deg] () [], 11

12 ,, 3, ()[phase 1,2,3,6] ()[phase 1,2,3,6], () () [phase 3] 300 [phase 4,5], [ phase] [ phase], HK 4.4 a = [km]e = T o T r T t 3 0 T o = I y f 0 0 = 2Iyµe r sin f 3 0 T r = = 0 I yp f 0 T t = F th 0 2I ypµe r sin f 3 0 l x l z l y 12

13 I y : y (= 2[kgm 2 ]) μ : (= [km 3 /s 2 ]) r : f : I yp : y (= 0.1[kgm 2 ]) F th : (= 1[mN]) l i : i (l x =0.01[mm], l y = 1[mm], l z = 1[mm]) T o T r T t 12 1 I x : x (= 2[kgm 2 ]) I z : z (= 2[kgm 2 ]) F s : (= 5.58[mN]) M : (= [emu]) D : (= 20[polem]) ρ : 280[km] (= [kg/m 3 ]) S : (= 1.25[m 2 ]) C D : (= 2.2) x x T environmentalx T environmentaly Inner disturbance [Nm] T innerx T innery T innerz Outer disturbance [Nms] T environmentalz time [s] x 10 12: (a=123172[km]e=0.94) time [s] x 10 13: (a=123172[km]e=0.94) T g T s T m T a 4 (I z I y )θ x T g = 3f 2 (I z I x )θ y 0 F s l y sin ft T s = F s (l x sin ft + l z cos ft) F s l y cos ft T a = 1 ( 2μ 2 ρ r μ ) 0 SC D l a z 7 MD T m = 2 10 r I d dt ω B + 4 n wi ẑ wi + ωh T = n D i=1 I wi {( d dt ω B ) ẑ wi + d } dt ω wi = n wi l y 13

14 I : d dt ω B : ẑ wi : n wi : ω : h T : n D : I wi : (= [kgm 2 ]) ω wi : quaternion 1.5 q1 q2 q3 1 q time [s] x 10 14: n wi 4 n wi ẑ wi = n w i= h x h y h z n w n wi n wi () h x,h y,h z [Nms] time [s] x : () 180[deg] , 15, h T h T [Nms] h T (CSSFSS) time [s] x 10 16: 14

15 2 (CSS) AERO ASTRO Course Sun Sensor 1 (FSS) Optical Energy Technologies Model ,18 18: FSS AERO ASTRO Miniature Star Tracker : CSS 6: (CSS) [deg] 120 [deg] ±5(1 ) [kg] 0.01 [mm] φ [W] 0 [] -40 to 93 7: (FSS) [deg] 100 [deg] ±0.05(2 ) [kg] [mm] φ40 15 [W] 0.05 [] -30 to (ST) 3 19: Star Tracker (FOG) KVH DSP (RW) SURREY Microwheel 10SP-M

16 11: () () CSS FSS ST FOG RW PRM IE 8: (ST) [deg] 45 [arcsec] ±70(3 ) [-] 4 [Hz] 2 [deg/s] 10 [kg] 0.475() [mm] [V] 28 [W] 2 [] -30to60 21: 10: (RW) 20: 9: (FOG) [deg/s] ±375 [kg] 0.27 [mm] [V] 5 [W] 3 [] -40 to 75 [Nms] 0.42 [mnm] 10 [kgm 2 ] [rpm] ±5000 [Hz] 5 [kg] 0.96 [mm] φ [V] 32 [W] 3.5 []

17 PRM IE : CSS FSS FSS CSS ST FSS FOG(3 ) FOG(2 ) ST RW(4 ) RW(3 ) PRM(2 ) PRM(1 ) IE(2 ) IE(1 ) 14: Al A2024-T3 [mm] 0.25 Al 1/ [mm] 9.5 Al A7075-T6 CFRP [kg] 16: [K] [] 16.6 [MPa] [g/cc] [ppm] , [mm] [mm] 47.4 [kg] 24,25, ( 24 ) t, P, r σ β t t = Prβ 2σ M tank ρ tank r M tank = 4πr 2 tρ tank = 2πr2 Pβρ tank σ M pp M pp /M tank ρ pp M pp = 4πr3 3 ρ pp M pp M tank = 2σ ρ pp 3βρ tank P ρ tank /P 17

18 22: 23: 18

19 24: 25: 2 19

20 13: [mm] [kg] 4 Microwheel 10SP-M Miniature Star Tracker Course Sun Sensor Sun Sensor model DSP TXE430MFM-211A RXE430M-301A CPU SEMC5071B ( 0.75kg ) Sφ UR18650F XTJ Solar Cells A2 -(, ) B2 -(, ) DC-DC TPS A B

21 26: 2 15: Al A2024-T3 A7075-T6 [kg/m 3 ] [GPa] [GPa] [-] [MPa] [MPa] Al 1/ [kg/m 3 ] 72 [GPa] 0.44 [MPa] 2.4 CFRP [deg] 0 90 [kg/m 3 ] 1600 [GPa] [MPa] 67 [MPa]

22 50[] P 11.3[MPa] 1.4[g/cc] 17 M pp /M tank 17: [g/cc] 4.42 [GPa] 1 [] 10 15% β 2 11% M tank =0.75[kg] r=50.4[mm] β 2 t=0.058[mm] r=51[mm]t=2[mm] : [deg] A 180[deg] Pro Engineer / Mechanica H2A [g]

23 27: 28: 23

24 18: 30[Hz] 10[Hz] 3.2[G] 1.8[G] 0.1[G] 1.8[G] MECO 4.0[G] 0.5[G] 1.0[G] 1.0[G] : x[mm] y[mm] z[mm] : I x [kgm 2 ] I y [kgm 2 ] I z [kgm 2 ] [Hz], [G] 1.8[G] 1.5 6[G] 2.7[G] 31 Al Al 13.4[MPa] [MPa] MS MS = 1= [kg] Power Control Unit(PCU) [V] DC-DC () 6.2 SANYO UR18650F 24

25 30: 31: 25

26 21: [V] [W] 5V PCU CPU () () V [V] 22 22: [V] 3.7 [Ah] 2.5 [g] 47 [mm] C r = P et e C d NV d n C r P e T e C d N V d n [A h] [W] [h] DOD[ ] [] ()[V] [ ] 21 5V 28V 28[V] [V] 5[V] 2 7.2[V] Texas Instruments DC DC TPS [V] 21 10% 50 DOD 92% 83% N(5V ) = = N(28V ) = P e T e C d C r V d n /60 =18.58 < 19[] /60 =2.21 < 3[] V 19 28V 5V 38 2, 28V 6 8, = 5828[g] [deg] 26

27 SPEC- TROLAB GaInP2/GaAs/Ge next Triple Junction(XTJ) Solar Cells 23 2[cm] 2[cm] 500[ m] 23: (at 28 ) [-] [ma/cm 2 ] [V] [-] 0.90 [mm] 0.14 [mg/cm 2 ] 84 [-] 0.88 [-] 0.95 [% / ] [cm 2 ] 4.0 5V P sa (EOL)=30.79[W] 28V P sa (EOL)=96.29[W] Psa(EOL) Psa (BOL) P sa (BOL) =P (EOL)/(ηγɛ cos θ) η : γ : ɛ : θ :. 74.5[] γ ( ) ( 0.286/100) = η =0.836 θ 9[deg] ɛ 0.92 Psa(BOL) 5V P sa (BOL) =46.77[W] 28V P sa (BOL) = [W] P sa = P et e /X e + P d T d /X d T d [W/m 2 ] 5V P sa (BOL) =0.116[m2 ] 28V P sa (BOL) =0.363[m2 ] 1 2[cm] 2[cm] P e [W] = P d [W] T e [min] = 290[](5V ) T d [min] = 908[](28V ) X e [ ] X d [ ] 308(5V )992 (28V ) Xe=0.90Xd= (5V )0.397(28V )[m 2 ] 90% = 0.138[m2 ](5V ) = 0.442[m 2 ](28V ) 27

28 840[g/m 2 ] 0.58[m 2 ] = 487.2[g] [V]29.6[V] =8.64[V ] = 35.52[V ] 2.333[V] (5V )8.64/2.333 = 3.70 < 4 (28V )35.52/2.333 = < (5V )992 (28V ) 308/4=775V 992/16=62 28V 6.5 (MDS-1) 32 GTO 26.5[%] 0.2 [%] GTO (= ) = [kW] : InGaP/GaAs GTO 32 InGaP/GaAs (Isc) (Voc) 2 28

29 phase 285[km], 7.2 i m i c pi dt i dt = Q i ΣC ij (T i T j ) ΣR ij σ(t 4 i T 4 j ) m i : i [kg] c pi : i [W s/(k kg)] T i,t j : i, j [K] Q i : i [W] C ij : i, j [W/K] R ij : i, j [m 2 ] σ : (= [W/(T 4 m 2 )]) (1) Q E 1399[W/m 2 ] 1309[W/m 2 ] A Q Q s = E s Aμ μ θ μ = / sin θ (2) Q e E e [W/m 2 ] A Q e Q e = E e AF e F e R e, H e, 33, + /2 F e =cosλr 2 e/h 2 e (3) Q m 107[] 153[] Q m Q m = E m AF m F m : E m [W/m 2 ] 5 (4) Q a 29

30 h ij i, j [W/(m 2 K) A ij i, j [m 2 ] [W/(m 2 K)] R ij (1) A i A j R ij R ij = ɛ i ɛ j F ij A i ɛ i,ɛ j : i, j 33: A Q a Q a = ae s AF a a F a Bannister F - θ s cos θ s 0 F a = F cos θ s cos θ s 0 F a =0 F ij F ij =ln{(1 + x 2 )(1 + y 2 )/(1 + x 2 + y 2 )} 1 2 +y 1+x 2 arctan(y/ 1+x 2 ) +x 1+y 2 arctan(x/ 1+y 2 ) y arctan(y) x arctan(x) x = y = F ij =ln { (1 + x 2 )(1 + y 2 )/(1 + x 2 + y 2 ) } +y 2 ln { x 2 (1 + x 2 + y 2 )/(1 + y 2 )/(x 2 + y 2 ) } +x 2 ln { y 2 (1 + x 2 + y 2 )/(1 + x 2 )/(x 2 + y 2 ) } +4y arctan(1/y)+4x arctan(1/x) 4 x 2 + y 2 arctan(1/ x 2 + y 2 ) x = y = F ik = F i(j+k) F ij C ij ij C ij (2) A i ɛ i C ij = h ij A ij R ij = ɛ i A i 30

31 24: [] [W] -20/ ( 4) -40/ /+80 -( 2) -30/ / ( 3) -30/ / / /+100-0/+45(charge) - -20/+60(discharge) - -20/+40(storage) - CPU -20/ [] 10[] 10 35[] [] 10[] [] [] 10[] [] Du Pont Kapton-HN(146448G405120) [] OSR phase1 phase3 phase4 phase [km] 285[km] phase

32 25: () () 0.2mm OSR (0.02) (0.02) : 1 -Z [] Y ( [] X [] X [] Y [] Z [] Z [] Y [] [] () [] Y [] Z [] [] [] [] [] [] [] []

33 8.2 34: [] [] 0.05[m 2 ] 0.10[m 2 ] HK TXE430MFM-211A RXE430M-301A 430[MHz] 120[deg] V 120[deg] V 50[] 27 27: [MHz] 435 [mm] 340 [g] 100 [dbi] [deg] [km] 33

34 28: TXE430MFMCW-211A [W] 3 [W] 9.1 [V] 7 [] [] 50 [mm] [g] 44 RXE400MFM-101A [dbm] -121 [ma] 26 [V] 5 [] [mm] [g] : [m] 5 [dbi] [kbyte] 30 27[kbyte] 1080[s] 200[bps] 30: HK (3 ) (1 ) (3 ) (3 ) (3 ) RH (4 ) (4 ) IE C/N 0 C/N : HK [bit] 112[bit] 10[s] 1[s] [pixel] JPEG [kbyte] HK 9 CPU 34

35 31: C/N 0 [MHz] [km] EIRP [dbw] [dbw] [db] 0 0 [dbi] [db] 1 0 [db] [km] [db] 3 3 [db] [db] [db] 0 0 G/T [db/k] [db] 0 1 [dbi] [db] 0 0 [dbk] [K] [K] [K] [db] 3 2 C/N 0 [dbhz] [dbhz] : C/N 0 FM GMSK E b /N 0 [db] [db] [db] [dbhz] [db] 3 3 C/N 0 [dbhz]

36 CPU CPU SEMC5701B CPU 33 33: SEMC5701B CPU VR [MHz] [MByte] 16 DRAM,I/F [MByte] byter SDRAM 64 [V] +5 [mm] [1] 2002 [2] 1993 [3] Wiley J.LarsonJames R.WertzSPACE MIS- SION ANALYSIS AND DESIGN1999 [4] 2007 [5] ERSDAC (Earth Remote Sensing Data Analysis Center): [6] Tokyo Institute of Technology Lab for Space System [7] OS OS OS OS OS OS OS OS TRON ITRON(TOPPERS). [8] 1969 [9] 1992 [10] 1990 [11] 2001 [12] Paul.D.spudig :The Once and Future Moon,2000 [13] γ [14] JAXA- (MDS-1) [15] [16],,,, :,2003 [17] 2005 [18] 2001 [19] 2006 [20] : 2008 [21] FRANK KREITHRadiation Heat Transfer for Spacecraft and Solar Power Plant Design

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