Abstract
In the application of adaptive flight control, significant issues arise due to limitations in the plant inputs, such as actuator displacement limits, actuator rate limits, linear input dynamics, and time delay. A method is introduced that allows an adaptive law to be designed for the system without these input characteristics and then to be applied to the system with these characteristics, without affecting adaptation. This includes allowing correct adaptation while the plant input is saturated and allows the adaptation law to function when not actually in control of the plant. To apply the method, estimates of actuator positions must be found. However, the adaptation law can correct for errors in these estimates. Proof of boundedness of system signals is provided for a single hidden-layer perceptron neural network adaptive law. Simulation results utilizing the methods introduced for neural network adaptive control of a reusable launch vehicle are presented for nominal flight and under failure cases that require considerable adaptation.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 906-913 |
| Number of pages | 8 |
| Journal | Journal of Guidance, Control, and Dynamics |
| Volume | 26 |
| Issue number | 6 |
| DOIs | |
| State | Published - Jan 1 2003 |
Fingerprint
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering
- Aerospace Engineering
- Space and Planetary Science
- Electrical and Electronic Engineering
- Applied Mathematics
Cite this
}
Limited Authority Adaptive Flight Control for Reusable Launch Vehicles. / Johnson, Eric N.; Calise, Anthony J.
In: Journal of Guidance, Control, and Dynamics, Vol. 26, No. 6, 01.01.2003, p. 906-913.Research output: Contribution to journal › Article
TY - JOUR
T1 - Limited Authority Adaptive Flight Control for Reusable Launch Vehicles
AU - Johnson, Eric N.
AU - Calise, Anthony J.
PY - 2003/1/1
Y1 - 2003/1/1
N2 - In the application of adaptive flight control, significant issues arise due to limitations in the plant inputs, such as actuator displacement limits, actuator rate limits, linear input dynamics, and time delay. A method is introduced that allows an adaptive law to be designed for the system without these input characteristics and then to be applied to the system with these characteristics, without affecting adaptation. This includes allowing correct adaptation while the plant input is saturated and allows the adaptation law to function when not actually in control of the plant. To apply the method, estimates of actuator positions must be found. However, the adaptation law can correct for errors in these estimates. Proof of boundedness of system signals is provided for a single hidden-layer perceptron neural network adaptive law. Simulation results utilizing the methods introduced for neural network adaptive control of a reusable launch vehicle are presented for nominal flight and under failure cases that require considerable adaptation.
AB - In the application of adaptive flight control, significant issues arise due to limitations in the plant inputs, such as actuator displacement limits, actuator rate limits, linear input dynamics, and time delay. A method is introduced that allows an adaptive law to be designed for the system without these input characteristics and then to be applied to the system with these characteristics, without affecting adaptation. This includes allowing correct adaptation while the plant input is saturated and allows the adaptation law to function when not actually in control of the plant. To apply the method, estimates of actuator positions must be found. However, the adaptation law can correct for errors in these estimates. Proof of boundedness of system signals is provided for a single hidden-layer perceptron neural network adaptive law. Simulation results utilizing the methods introduced for neural network adaptive control of a reusable launch vehicle are presented for nominal flight and under failure cases that require considerable adaptation.
UR - http://www.scopus.com/inward/record.url?scp=0344898942&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=0344898942&partnerID=8YFLogxK
U2 - 10.2514/2.6934
DO - 10.2514/2.6934
M3 - Article
AN - SCOPUS:0344898942
VL - 26
SP - 906
EP - 913
JO - Journal of Guidance, Control, and Dynamics
JF - Journal of Guidance, Control, and Dynamics
SN - 0731-5090
IS - 6
ER -