1、 pw 7PM M+063/“-030$, on-board propulsion; engine; pulse plasma thruster 1 l10j100kga? Z T y 21 R ? VFVIf LCvE ?bYata4a bW SaZ U ?Z -9Caa %4 m b l ia?Z yb 7Ew“d p 1Ky b T eVIfE LCb5 B lw“dj q ?9by7lEw“d4 n1 pb “ -w/ Va7 O1 _ / ww b w/ “? T nV 1b lEw/ 412 w“d w“d “d b K Bw“db+ “de # f V 3Y yz1 KO P5b
2、 “dR p9 1 pl (l500 NS) b S (Surrey)v / K (SSTL)Microsatellite, 50kglMinisatellite, 400kg “d SEY _MYV9 w TE e“db “dFrw r Viab ? #1 “d 1 K aKaKBEw“dby 1 ?Z F“d (N2O4/MMHNTO/N2H4)“dY (1 av ) EaE4 61w a9 b V “ -WFF“dw4 ( r ) aa“ 1L$ ) ! P sa a ?rw4 HAN/ HAN/b Y?# H2O2/ Y? Viw4bw“d I ? l5 (F? i ?l5w44z s
3、 ?/ )# w ? lvw b ; ? T9 V bV 1 Ew“d ? Tab.1 The performances of typical on-orbit propulsion systems w“d “d w4 1/s w /N N2, NH3, 40j75 0.05j250 He 158 H2260 N2O2150j225 0.05j0.5 F N2H4200j230 0.05j103F N2O4/MMH (NTO/N2H4) 270-340 5j104 H2O H2+ O2340j380 50j500 Tridyne N2 + H2+ O2138 0.1j w“d EF N2, N
4、H3, N2H4,H2150j700 510-6 j0.5 T F NH3, N2H4,H2450j1500 0.002j5 0 Xe 1500j5000 110-5 j0.2 0 Xe 1500j5000 110-5 j0.2 o 0 Xe 1500j5000 110-5 j0.2 8 Glycerine 1200 510-6 j0.5 F ? Cs 6000j10000 110-6 j0.1 SPT Xe 800j3000 0015j0.26 TAL Xe 800j3000 0015j0.26 H F TPPT Y 300j1500 110-6 j0.005 p w 2006 M 32 4
5、23 w“d w B1 alw rEw“dbw“d* W 60 M 7 S bW 90 MF ?a SPT 0?va p R 2 e #EF Tw FV 1997 M? 67 RF R 600 e1b 1v q1j2kW qKlE4bN a,a a xSE?Z q 100j500WArcjetw a 20j200W SPTa 0w b|w 1-25W l e1 pbV eCw lja qb “ qh w ? AM yN1 all qArcjetaSPT 0w Sv Tb“ -K aRl+Y a ,i$ Az H 08w (TPPT)? w A (F ) Tw b 3.1 08w X 08w E
6、 K HTeflonii%8 Y Tw4 Ew m 1 UbVm VnBE% ? Mb Hw4T/YV W bWZ b| B?b bT H n5 P% ? T 1j3kV9Fw b b P b b30 P% ? Ww4V ?bbb KV B Hc sa 08b 1H 3H T/ 08 EF 3B wbm 1 08w Uim Fig.1 Schematic of pulse plasma thruster m 2 ? w m Fig.2 Schematic of field emission thrusterw 1+ (1) l q/1? q20W H1 r 800j1200sb w “- 4S
7、 (2) ew4 %8 ? b/ ibiLQa5aD + y) Bqb“d8a VSl O V L (3) T HW E ) b H1 HW e ( 31 e )ZL 2b qvh ( q (4) w Vl d ) b ?4w 9 V4r w O ? lEw/ 431 r q/w V LC e (5) bW q 100 bTPPT B bW ( - 1964 M )w b S5 LES-6 1968 M 9Y Z + TIP2/3 70 M NOVA1/2/3 80 M t E h M NASA o4 1| EO-11999 M? f k L ( e ? S b + MightySat II.
8、12000M? L PPTEM 4 6 ?1,2b + P ; a19 a ( eE E E e , qKl X e“dbN S 90 M 7 S B ? PPT 99|YVv $4 r q Waq kBhl 8 ?Z?“3 bWf kb T b 3| (DS-3)( e Dawgstar , ( S b + ,9Bz ) ( ea If e T S b+TechSat21 100kg“ w l 25kg Micro-PPT4bISAS5 20J PPT w4 kb“ES x?Z9,T 10j150J 100j1000J PPTa k vb “ - lE e1 pX?Z TPPT“d ,e 0
9、.5j5J(1j100Ns)“d5j50J(100j1000Ns)“d#l e 50j150J “db 3.2 ? w x 1 ES ! M70 M 7 S? 0w FEEPl e bm 2 w T Uimb ? aF zFb? A aw4YV %5V f Tr50U gF? U H10j12kV ? w4 w4F F T/F 0 3QTw 0 $ ? 0bw 1(6000j10000s)aw 1uNj1mN+7 O VYV“ Fw w b1 %15w4 P 8/ # bWfb9 ESlo Microscopep o b 9b 3.3 A Tw ,a S NASAaMITat S b + 7Z
10、“w/ “ FF/ MEMSA !K Y0 ; ; “daE Microresistjetw a# 0?bBA 0 400V 400H ?/ ASiC 0 4FbyNA Tw ? Lb “ -tT)$ b 4 YV1 4 Aw“d + ?91 KbvaEw“dV T“d B CX?Z T T“d FF“dF#w“d Ea # b1 w“dXv va p 2 e#l bW wb l7 T 14blEw“d4 51 alw a1 awr q O8l b7Cw“d1 8a 4hl vw“d s ?Ky7 sK 08w Z K 8 b /: p w 2006 M 32 62“?Z g |/* H|4
11、7A 4 6 1 p1 p g -M A 94 h“d E#8 E g Yb “ - 2 | 9 ? X 1 p k9F A8aA8a 9D 9 8 (3) T V k 1 pb 6 X EQA / ? a“da k -= EQ TZ T V 10000a9AQ k 7 S i TZT ( | XrTbYV s1 V/ (1) w4“d ! Vrhl H“d E8 E A/ ? k1 p (2) T HT ZE V k1 p7 HT1 TZEeaVea V L (3) HTZE Y 9 A Yv7 9 A Yv Y -9b I y :?Z A Tw a, e 1ilbSM1w“d w“d v
12、jg byp SCHq?Z 0wY$? FA Tw TwSl Y?Zb ID1 qvfw/ ?Zt Jw/ 2003(5) 2 q 08p eZ J ?/ 1986(3) 3 R M Myers, S R Oleson, Melissa Mcguire, et al. Pulsed plasma thruster technology for small satellite missionsC. In: Proc. of the 9th annual AIAA/USU Conf. of small satellite, 1995. 4 Gregory G, Spanjers, Daron R, Bromaghim, et al. AFRL MicroPPT development for small spacecraft propulsionR. AIAA 2002-3974. 5 Hgw“d NaC J e 2001(5) I *
