Design of guidance and control system for high speed reentry aerocraft

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica

Volumn 23, Issue 2, 2002, Pages 115-119

  Lian, Bao Hua ^a   Cui, Ping Yuan ^a   Cui, Hu Tao ^a  

^a HARBIN INSTITUTE OF TECHNOLOGY   (China)

Author keywords

Control; Feedback linearization; Guidance; Optimal; Reentry aerocraft

Indexed keywords

COMPUTER SIMULATION; FEEDBACK CONTROL; NONLINEAR SYSTEMS; REENTRY;

AUTOPILOT; REENTRY AEROCRAFT; TERMINAL GUIDANCE; TIME SCALE SEPARATION;

AIRCRAFT;

EID: 0036519847     PISSN: 10006893     EISSN: None     Source Type: Journal    
DOI: None     Document Type: Article

References (6)

1. Adaptive control of feedback linearizable nonlinear systems with application to flight control
2. Adaptive control for feed-back-linearized missiles with uncertainties
3. Guidance algorithm design: A nonlinear inverse approach
4. Fuzzy missile guidance laws
5. Angle of attack guidance via robust approximate inversion