A Near Optimal Midcourse Guidance Law Based on Spherical Gravity

2002 ◽  
Author(s):  
Ali Deihoul ◽  
Mohammad Massoumnia
Keyword(s):  
Guidance Law ◽  
Midcourse Guidance

Suboptimal mid-course guidance algorithm for accelerating missiles

2016 ◽  
Vol 231 (11) ◽  
pp. 2032-2047 ◽  
Author(s):  
Min-Guk Seo ◽  
Min-Jea Tahk
Keyword(s):  
Performance Enhancement ◽  
Feedback Form ◽  
Velocity Change ◽  
Guidance Law ◽  
Burn Out ◽  
Homing Performance ◽  
Guidance Algorithm ◽  
Midcourse Guidance ◽  
Missile System ◽  
Loop Form

This paper deals with the closed-loop form of mid-course guidance law design for accelerating missile system, whose acceleration is approximately constant. A midcourse guidance algorithm of feedback form is proposed to satisfy the engagement geometry conditions at the burn-out time for terminal homing performance enhancement. The effect of velocity change due to missile acceleration is explicitly considered in the derivation of the guidance law. The terminal constraint update algorithm is proposed under the assumption that the target trajectory is predicted precisely. Simulation results are provided to show the performance and characteristics of the proposed algorithm.

Design and Simulation of Guidance Law for a Kind of Flight Test Missile

2012 ◽  
Vol 538-541 ◽  
pp. 2887-2891
Author(s):  
Yu Qian ◽  
Xiao Jun Xiang ◽  
Jun Li Yang
Keyword(s):  
Flight Test ◽  
Target Point ◽  
Impact Point ◽  
Integral Term ◽  
Guidance Law ◽  
Velocity Information ◽  
The Difference ◽  
Miss Distance ◽  
Midcourse Guidance ◽  
The Impact

To reduce the miss distance of flight test missile, the midcourse guidance law is studied in this paper. The nonlinear projectile dynamic model is developed at first, and then designed the midcourse guidance law with the impact point prediction information. The guidance law was designed using the difference between predicting impact point and target point. To improve the guidance law’s performance, this research inducted the predicted impact point’s velocity information and integral term into guidance law command. At the end, the simulation was developed. The results of simulation show that the guidance law designed in this study is successful and it can satisfy the test missile’s flight mission requirements.

Near-Optimal Spatial Midcourse Guidance Law with an Angular Constraint

2014 ◽  
Vol 37 (1) ◽  
pp. 214-223 ◽  
Author(s):  
Nahshon Indig ◽  
Joseph Z. Ben-Asher ◽  
Nathan Farber
Keyword(s):  
Guidance Law ◽  
Midcourse Guidance
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