有动力通用航空飞行器的概念研究

1、 第2 期 康炳南等: 有动力通用航空飞行器的概念研究 18 9 7 Graham W a r . www. F ightGloba l . w ick. Hype rsonic P roject s F ace Change a s Congre ss U rges Jo int Techno logy Off ice com 8 廖少英 . 液体 火箭 发动 机涡 轮泵 系统 多次 启动 的试 验研 究 . 上海航天, 2006, 23 (1 : 53 56 L iao Shaoying. Exper im ental R e sea rch of the T urbopump Syste

2、m S ta rt s for L iquid Ro cke t Engine. A e ro sp ace Shangha i, 2006, 23 (1 : 53 56 (in Chine se 9 Ph illip s T H. A Comm on A e ro V eh ic le (CAV M ode l, D escr ipt ion , and Em p loym ent Guide . 200311 10 F a lcon HTV ge ts DA RPA go 2 ahead. www. F ightGloba l. com 11 Rodi P E. The O scula t

3、ing F low fie ldM e thod of W ave rider Geom e try Genera tion. A I AA 22005 2 0511, 2005 12 Ca rte r P H , P ines D J , e t a l . A pp rox i 1644 m ate Pe rfo rm ance of Pe r iodic Hype r son ic. A I AA 298 2 13 Speye r J L . Nonop ti 1610 m ality of the Steady2State C ru ise for A ircraf t. A I AA

4、 Journa l, 14( 11 : 1604 14 Speye r J L. Pe r iodic Op tim a l F light. A I AA 21995 2 0001 15 Chuang J C H , M o r i m o to H. Op tim al Pe riod ic C ru ise for a Hype r sonic V ehicle w ith Constra in ts. A I AA 2 1996 2 3876 16 You ssef H , C how dhry R. H ype rsonic Skipp ing T ra je to ry. A I

5、5498 AA 22003 2 17 You ssef H , C how dhry R. H ype rsonic Globa l R each T rajec tory Op ti 20042 5167 m izat ion. A I AA 2 18 N go A D , A F ue l2 Op t i m a l T rajecto ry for a Constra ined Hype rsonic U sing a D irec t T ranscr ipt ion M e thod. A erospace Confe rence P roceedings, 2004 19 C he

6、n R H , W illiam son W R , Sp eye r J L , Husse in You ssef, R ajiv C how dh ry. O pt i m iza tion and I mp lem enta tion of Pe r iodic C ruise fo r a H yp er so nic V eh ic le . Jou rna l of Guidance , Cont ro l and Dynam ics 20 F a lcon R ankins, P ines D J , R e lative H ea tL oad Com pa r ison o

7、f V ehicle s F lying Hype rsonic T ran sa tm osphe re T ra jec tor y, Jo urnal of Spacec raft and Rockets, 37 (4 : 491 498 IEEE C oncep tua l Resear ch on P ower ed Comm on Aer o Veh icle K ang B ing nan , T ang Sh uo (College of A stronautics, No r thw estern Poly technical U n ive rsity, X i an 71

8、0072, Ch ina Abstrac t: W e review t he deve lopm ent of the F alcon p rogram of the U S . To avoid the diff icul ties in develop ing un2pow ered Comm on A ero V eh icle (CAV adop ted by the program , w e p ropose t he concep tua l pow ered CAV. W e analyze som e key enabling techno logies of pow e

9、red CAV , such a s selec tion of p ropuls ion system , de sign of ae rodynam ic configura t ion and t ra jecto ry de sign. Sec tion 1 of the fu ll pape r, af ter m uch discus sion including par ticularly that of F ig. 2 in the full paper, concludes that the pow ered CAV shou ld adop t rocket engine

10、a s it s p ropuls ion system. Sect ion 2, after analysis, conclude s that either the lift conf igurat ion w ith high lift2drag rat io or the w ave 2rider configura t ion w ith its capacity rat io im p roved is the idea l candida te fo r pow ered CAV. A fte r com pa ring the hyperson ic pe riodic cru

11、ise t ra jecto ry w ith the hyper sonic steady 2st ate cruise t ra jecto ry, sect ion 3 concludes that the pe riodic cruise t ra jecto ry is bet te r than the s teady s tate cru ise t rajectory and thus should be the first 2cho ice t rajecto ry of pow ered CAV. Section 4 ca lcu la tes and com pa re s tw o num er ica l exam ples. The calculat ion result s and their com pa rison, given in F igs. 9 t hrough 11 and T ab les 1 and 2, show p relim ina rily tha t the de sign of configura t ion and that of t rajecto ry should