In order to increase the effectiveness of the kinetic kill vehicle (KKV), control of impact angle is required in the terminal engagement. The purpose of this research is to achieve an optimal guidance law (OGL) with a specified impact angle as well as zero terminal miss distance. An energy OGL based on a simplified mathematical model to achieve the performance of the KKV is presented. Numerical simulation is used to analyse the performance of the guidance law. The results show that the proposed law has higher accuracy, larger capture zone, and lesser energy consumption than the conventional proportional navigation guidance laws. Moreover, the influence of the initial heading angle is discussed, and the capture zone of both the initial heading angle and the terminal impact angle are given.
Schindler, R. C. SDI thinks small – miniaturized propulsion is needed for ground- and space-based kill vehicles. In Proceedings of the 27th AIAA/SAE/ASME Joint Propulsion Conference, Sacramento, California, 24–26 June 1991, AIAA-1991–1932, 8 p.
2.
Pavlinsky, J. Advanced thrust chambers for miniaturized engines. In Proceedings of the 28th AIAA/SAE/ASME/ASEE Joint Propulsion Conference and Exhibit, Nashville, Tennessee, 6–8 July 1992, AIAA-1992–3258.
3.
Martinez-ValR.PerezE.Aeronautics and astronautics: recent progress and future trends. Proc. IMechE, Part C: J. Mechanical Engineering Science, 2009, 223(C12), 2767–2820. DOI: 10.1243/09544062JMES1546.
4.
KimB. S.LeeJ. G.HanH. S.Biased PNG law for impact with angular constraint. IEEE Trans. Aerosp. Electron. Syst., 1998, 34, 277–288.
5.
Felio, D. A. and Duggan, D. S. Lecture note on autonomous vehicle guidance, control, and simulation. In 2000 Aerospace Short Course of the University of Kansas Continuing Education, San Diego, California, September 2000.
6.
Baba, Y., Takehira, T., and Takano, H. Guidance law for a free-flying projectile. In Proceedings of the Asian Control Conference, Tokyo, 27–30 July 1994, pp. 437–440.
Sang, D., Ryoo, C. K., Song, K. R., and Tahk, M. J. A guidance law with a switching logic for maintaining seeker's lock-on for stationary targets. In AIAA Guidance, Navigation and Control Conference and Exhibit, Honolulu, Hawaii, 18–21 August 2008, AIAA-2008–6497.
11.
Sang, D., Min, B. M., and Tahk, M. J. Impact angle control guidance law using Lyapunov function and PSO method. In SICE Annual Conference, Kagawa University, Japan, 17–20 September, 2007.
12.
LeeJ. I.JeonI. S.TahkM. J.Guidance law to control impact time and angle. IEEE Trans. Aerosp. Electron. Syst., 2007, 43, 301–310.
13.
ChoH.RyooC. K.Implementation of optimal guidance laws using predicted missile velocity profiles. J. Guid. Control Dyn., 1999, 22, 579–588.
14.
Belapolsky, O. and Ben-Asher, J. On two formulations of linear quadratic optimal guidance. In AIAA Guidance, Navigation and Control Conference and Exhibit, Hilton Head, South Carolina, 20–23 August 2007, AIAA-2007–6533.
15.
ShafieenejadI.NovinzadehA. B.Analytical solutions for two-point boundary value problems: optimal low-thrust orbit transfers. Proc. IMechE, Part G: J. Aerospace Engineering, 2010, 224(G7), 843–853. DOI: 10.1243/09544100JAERO653.
16.
SongG. B.AgrawalB. N.Vibration suppression of flexible spacecraft during attitude control. Acta Astronaut., 2001, 49, 73–83.
17.
ArantesG.Martins-FilhoL. S.SantanaA. C.Optimal on-off attitude control for the Brazilian multimission platform satellite. Math. Prob. Eng., 2009, 2009, Article ID 750945, 17 pages. DOI: 10.1155/2009/750945.
18.
XiaoB.HuQ. L.MaG.Adaptive sliding mode backstepping control for attitude tracking of flexible spacecraft under input saturation and singularity. Proc. IMechE, Part G: J. Aerospace Engineering, 2010, 224(G2), 199–214. DOI: 10.1243/09544100JAERO668.
19.
OmranA.LandmanD.NewmanB.Design of experiments-based stability and control derivative modeling. Proc. IMechE, Part G: J. Aerospace Engineering, 2010, 222(G8), 1123–1137. DOI: 10.1243/09544100JAERO417.
20.
SchütteA.ReinM.HöhlerG.Experimental and numerical aspects of simulating unsteady flows around the X-31 configuration. Proc. IMechE, Part G: J. Aerospace Engineering, 2009, 223(G4), 309–321. DOI: 10.1243/09544100JAERO387.
21.
KaragiannisD.AstolfiA.Non-linear and adaptive flight control of autonomous aircraft using invariant manifolds. Proc. IMechE, Part G: J. Aerospace Engineering, 2010, 224(G4), 403–415. DOI: 10.1243/09544100JAERO571.
22.
SteinbergM.Historical overview of research in reconfigurable flight control. Proc. IMechE, Part G: J. Aerospace Engineering, 2005, 219(G4), 263–275. DOI: 10.1243/095441005X30379.
