Dissertation > Industrial Technology > Arms industry > Rockets, missiles > Missile > Guidance and Control > Flight control system > Missile attitude control system

Parametric Gain Scheduling Design Method of Attitude Control System for Supersonic Cruise Missiles

Author GuoWei
Tutor DuanGuangRen
School Harbin Institute of Technology
Course Control Science and Engineering
Keywords supersonic cruise missile attitude control gain scheduling parametric method
CLC TJ765.23
Type Master's thesis
Year 2008
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The missile control system is the nerve center of the missile, whose role is to overcome the disturbance during the flight, guarantee the stability of the missile and accurately control the flight attitude in real time according to the predetermined attitude program or the command given by the guidance system so as to reach the desired control objective. Thus, the missile control system is the critical part of the missile that concerns whether the missile can achieve successful fight and precise strike at the targets.In the aspect of missile control approaches, gain scheduling is always one of the popular engineering methods. It employs powerful linear design tools on difficult nonlinear problems, does not require complete, analytical plant models, responds rapidly to changing operating conditions and is broadly acknowledged for its successful applications in the engineering field.Since linear design strategies are used in the design of local controllers in gain scheduling, such rule provides much space for the flexibility of design. Just based on the idea, this dissertation adopts parametric eigenstructure assignment approach to device local controllers for traditional gain scheduling and applies this scheme to the attitude control system of a certain supersonic cruise missile. Firstly, the mathematical model of the pitch/yaw channel and roll channel of the bank-to-turn (BTT) missile is derived. Moreover, especially in the design of pitch/yaw channel, the whole parameterized design degrees of freedom (DOF) of the system can be obtained through the parametric expression of the controller; therefore the performance requirements and robust stability condition are converted to the restrictions on the design DOF of the system, consequently the criteria can be synthetically optimized via suitable selection of the parameters. Combining with the model-reference technique, the autopilot consists of the robust stabilizing controller and the feedforward tracking controller. The scheme not only attenuates the chattering when local controllers switch, but also realizes the following of the command. Finally, satisfactory six DOF simulation results of the missile are demonstrated.

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