Abstract
Two types of autopilot-guidance schemes for linear quadratic multi-input missile systems are compared: singleand two-loop configurations. In both cases, all the states are fed back into the guidance loop. In the two-loop case, the inner autopilot loop is designed separately from the outer guidance loop, whereas in the single-loop scheme, the guidance command is injected directly to the actuator, without a definite autopilot. It is proven that the two schemes achieve the same performanceif and only if the number of guidance commands is identicalto the numberof available controllers. Thus, using the full-state two-loop scheme may be preferred, because it ensures a stabilized airframe whether the guidance loop is active or not. The theorem and guidance laws are illustrated using a dual-control missile model.
Original language | English |
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Pages (from-to) | 843-853 |
Number of pages | 11 |
Journal | Journal of Guidance, Control, and Dynamics |
Volume | 38 |
Issue number | 5 |
DOIs | |
State | Published - 2015 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Applied Mathematics
- Electrical and Electronic Engineering
- Control and Systems Engineering
- Space and Planetary Science