COMPARISON OF HIGH-GAIN-LINEAR AND SELF-ADAPTIVE FLIGHT CONTROL SYSTEMS FOR A TYPICAL WINGED RE ENTRY VEHICLE
Abstract
To establish the differences between self-adap tive and normal linear designs, both systems are applied to the problem of controlling the short period dynamics of the X-15. The self-adaptive system studied is an early design of the MH-96 Autopilot. The high-gain-linear system is de signed on the basis of selecting the forward branch compensation so that the system is in sensitive to vehicle-parameter variations over the bandwidth of the desired response and a pre filter or feedback-branch compensation is used to obtain the desired command response. The root-locus method is used in the initial design of the system; but, the system could not be simu lated on the analog computer. The frequency response method was used for the design of a second system. From this linear analysis of design procedures and response data, it is con cluded that the high- gain-linear system is pre ferred to a self-adaptive system; however, an analysis of the effects of system non-linearities and component noise must be made before a fixed gain system can be applied to the physical problem of widely varying vehicle parameters.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1963
- Accession Number
- AD0411806
Entities
People
- Frazier J. Hellings
- Robert E. Beale
Organizations
- Air Force Institute of Technology