Abstract
This paper presents a comprehensive study on the performance analysis of 8 conceptual guidance laws for exoatmospheric interception of ballistic missiles. The problem is to find the effective thrust direction of interceptor for interception of short-to-super range ballistic missiles. The zero-effort miss and the generalized required velocity concept are utilized for interception of moving targets. By comparison of the 8 conceptual guidance laws, the thrust direction is suggested to be in the direction of generalized velocity-to-begained, or constant velocity-to-be-gained direction, rather than to be in the direction along zero-effort miss, or that of linear optimal solution for long-to-super range interception. Even for short coasting ranges, the generalized velocity-to-be-gained may be utilized because of reasonable computational burden for required velocity rather than the numerical computation for zero-effort miss or linear optimal solution with the same miss distance error. In addition, the fuel consumption of the suggested direction has less sensitivity due to estimation error in intercept time. The guidance law based on constant velocity-to-be-gained direction and the optimal solution are suitable for satellites launch vehicles and space missions.
Highlights
Exoatmospheric intercept guidance improvements are of high interest in anti-ballistic air defense systems
The fuel consumption, ∆V = | ath | tco, of the mentioned conceptual guidance laws are shown in Figs. 2 – 4, where tco is the thrust cut-off time, applied when |zero-effort miss (ZEM)| ≤ ε
This study suggests the effective thrust direction of an exoatmospheric interceptor for interception of short-tosuper range moving targets with final position constraint
Summary
Exoatmospheric intercept guidance improvements are of high interest in anti-ballistic air defense systems. The mean value of |θVZ| is plotted in Fig. 11 versus range angle for a deviation of ±20% with respect to the final time of minimum energy orbit. The interceptor initial position, velocity, and acceleration due to thrust is taken similar to the studied case of spherical-Earth model with stationary targets.
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