Games in Aerospace: Homing Missile Guidance
The development of a homing missile guidance law against an intelligent adversary requires the solution to a differential game. First, we formulate the deterministic homing guidance problem as a linear dynamic system with an indefinite quadratic performance criterion (LQ). This formulation allows the navigation ratio to be greater than three, which is obtained by the one-sided linear-quadratic regulator and appears to be more realistic. However, this formulation does not allow for saturation in the actuators. A deterministic game allowing saturation is formulated and shown to be superior to the LQ guidance law, even though there is no control penalty. To improve the performance of the quadratic differential game solution in the presence of saturation, trajectory-shaping feature is added. Finally, if there are uncertainties in the measurements and process noise, a disturbance attenuation function is formulated that is converted into a differential game. Since only the terminal state enters the cost criterion, the resulting estimator is a Kalman filter, but the guidance gains are a function of the assumed system variances.
KeywordsPursuit-evasion games Homing missile guidance Disturbance attenuation
We thank Dr. Maya Dobrovinsky from Elbit Systems for converting part of this document from Word to LATE X.
- Basar T, Bernhard P (1995) H∞ optimal control and related minimax design problems: a dynamic game approach, 1st edn. Birkhäuser, BostonGoogle Scholar
- Ben-Asher JZ, Yaesh I (1998) Advances in missile guidance theory, vol 180. Progress in astronautics and aeronautics. AIAA, Washington, DCGoogle Scholar
- Bryson AE, Ho YC (1975) Applied optimal control. Hemisphere, New YorkGoogle Scholar
- Nesline WN, Zarchan P (1981) A new look at classical vs. modern homing missile guidance. AIAA J. Guidance, Control and Dynamics 4(1):878–880Google Scholar
- Shinar J (1981) In: Leondes CT (ed) Automatic control systems, vol 17, 8th edn. Academic Press, New YorkGoogle Scholar
- Shinar J (1989) On new concepts effecting guidance law synthesis of future interceptor missiles. In: AIAA CP 89-3589, guidance, navigation and control conference, Boston. AIAAGoogle Scholar
- Zarchan P (1997) Tactical and strategic missile guidance, progress in astronautics and aeronautics. AIAA, Washington, DCGoogle Scholar