Terminal-Phase Guidance and Control Analysis of Asteroid Interceptors

2010 ◽  
Author(s):  
Matt Hawkins ◽  
Alan Pitz ◽  
Bong Wie ◽  
Jesus Gil-Fernandez
Keyword(s):  
Terminal Phase ◽  
Control Analysis ◽  
Guidance And Control ◽  
And Control

Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker

2011 ◽  
Vol 110-116 ◽  
pp. 2513-2520
Author(s):  
Netra Singh ◽  
Manoranjan Sinha
Keyword(s):  
Coupling Effect ◽  
Three Dimensional ◽  
Impact Angle ◽  
Terminal Phase ◽  
Dynamic Inversion ◽  
Control Laws ◽  
Guidance And Control ◽  
Guidance Law ◽  
Hamilton Jacobi Bellman ◽  
And Control

Dynamic inversion control in conjunction with nonlinear suboptimal three dimensional (3-D) guidance law, in terminal phase, is implemented in both the pitch and yaw plane for a short range surface to surface missile with onboard active strapdown seeker. The implemented guidance and control laws intercept the target with a minimum miss distance in addition to meeting the various constraints such as line of sight, seeker field-of-view (FOV), and impact angle. This is achieved using approximate solution to Hamilton-Jacobi-Bellman (HJB) equation [1]. Dynamic inversion control is implemented in two time scales for the inner loop body rate and outer loop angles. Various nonlinearities including that due to the coupling effect between pitch and yaw channels are accounted for in the six-degree-of-freedom (6-DOF) formulation.

scholarly journals Orion Crew Exploration Vehicle Launch Abort System Guidance and Control Analysis Overview

2008 ◽  
Author(s):  
John Davidson ◽  
Sungwan Kim ◽  
David Raney ◽  
Vanessa Aubuchon ◽  
Dean Sparks ◽  
...  
Keyword(s):  
Control Analysis ◽  
Guidance And Control ◽  
And Control
Sign in / Sign up

Export Citation Format

Share Document