Closed-Form Control Algorithm for Continuous-Time Disturbance-Utilizing Control Including Autopilot Lag,
Abstract
Missile dynamic time lag is a major factor contributing to excessive terminal miss distances resulting from short range intercept trajectories. The objective of this paper is to describe a linear closed loop guidance law which compensates for this lag. Disturbance-Utilizing Control (DUC) theory 1 is applied to the terminal homing missile intercept problem as described in 2 except that the plant model is extended to include the missile dynamics, represented as a single time lag. The final form of the guidance law is identical with the result of Cottrell 3, and extends the results of 5 which discusses the relations between DUC and some well known guidance laws. The results described in this paper are applicable to problems in which the external disturbances have waveform structure (e.g. target maneuvers or wind gusts). Further work is under way to derive controllers which can drive the missile to the target in the face of both waveform and noise-type disturbances. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1982
- Accession Number
- ADP001091
Entities
People
- Jerry Bosley
- Wayne Kendrick
Organizations
- Computer Sciences Corporation