Design of a Normal Acceleration and Angle of Attack Control System for a Missile Having Front and Rear Control Surfaces

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  • 双翼操舵飛しょう体の垂直加速度及び迎角制御系の設計
  • 双翼操舵飛翔体の垂直加速度及び迎角制御系の設計
  • ソウヨク ソウダヒショウタイ ノ スイチョク カソクド オヨビゲイカク セイギョケイ ノ セッケイ

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Abstract

Precise normal acceleration control is essential for missile guidance. Missiles with both front and rear control surfaces have a higher ability to control normal acceleration than missiles with front or rear control surfaces only. From the viewpoint of control, however, the control problem becomes a two-input-one-output problem, where generally control input cannot be determined uniquely. This paper proposes controlling angle of attack as well as normal acceleration, which makes the problem a two-input-two-output one and determines the controls uniquely. Normal acceleration command is given by a guidance system, but angle of attack command must be generated in accordance to the acceleration command without affecting the normal acceleration control. This paper also proposes such a command generator for angle of attack. Computer simulation is conducted using a nonlinear missile model to investigate the effectiveness of the control system along with control systems designed using three other methods.

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