How Autopilot Requirements Constrain the Aerodynamic Design of Homing Missiles

Nesline, F.; Nesline, Mark L.

doi:10.23919/acc.1984.4788471

Cited by 42 publications

(28 citation statements)

References 3 publications

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“…Generally, the controller is in a form of proportional-integral-derivative (PID) parameters, and the control gains are determined by using classical control theory, such as the root locus method, Bode method or Nyquist stability criterion [14][15][16]. Modern control theory has been used extensively to design the flight control system, such as in the linear quadratic techniques [17,18], generalized singular linear quadratic technique [19], H ∞ design technique and μ synthesis technique [20].…”

Section: Conventional Design Methodsmentioning

confidence: 99%

Comparison of Flight Control System Design Methods in Landing

Sadati¹,

Parvar²,

Menhaj³

2011

Advances in Flight Control Systems

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Section: Conventional Design Methodsmentioning

confidence: 99%

Comparison of Flight Control System Design Methods in Landing

Sadati¹,

Parvar²,

Menhaj³

2011

Advances in Flight Control Systems

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“…The sign of determines the stability of the open loop airframe. When the is negative the airframe is stable, and when it is positive the airframe is unstable, which occurs when the aerodynamic center of pressure is forward of the center of gravity [5].…”

Section: Autopilot and Missile Dynamicmentioning

confidence: 99%

“…But when adding a synthetic stability loop, it is called three-loop autopilot [5], [6]. Lateral autopilot acts as an inner loop of the guidance loop which is used to control the pitch and yaw motions.…”

Section: Introductionmentioning

confidence: 99%

Design and Comparison of Two-Loop with PI and Three-Loop Autopilot for Static Unstable Missile

Mohamed¹,

Lin²

2016

IJCEE

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Abstract:The characteristics of nonminimum phase and static unstable of a tail controlled tactical missile are presented firstly. Then, in order to eliminate the static error, a cascade PI compensator was introduced to the classic two loop autopilot. Due to the slow tracking for command acceleration, the longitudinal three-loop autopilot design is driven based on LTI model of missile plant to stabilize the nonminimum phase static unstably missile airframe. The focus is to explain the performance and the control effect at different values of velocity and stability derivative ( ) of two algorithms on missile plant. The analysis is executed by establishing a standard algorithm in virtue of MATLAB/Simulink for autopilot design. The simulation results indicated that three-loop topology gives better tracking than two-loop with a cascade PI compensator at different value of stability derivative . On the other hand, two-loop has a better response and less control effort at different velocities. fin angle and fin angle rate are less than the three loop for static unstable and stable missile.

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“…보통의 유도무기의 경우 유도조종을 위하여 3 루프 오토파일럿을 구성하는 것이 일반적이다 [1]. 3루프 오토파일럿을 구성하기 위해서는 3축의 가 속도계와 3축의 각속도계의 관성센서 조합이 필 요하기 때문에 최소 6가지의 관성센서를 위한 공 간이 필요하다.…”

Section: ⅰ 서 론unclassified

Look-Angle-Control Homing Loop Design with a Strapdown Seeker and Single Gyroscope

Hong¹,

Park²,

Park³

et al. 2016

Journal of the Korean Society for Aeronautical & Space Scie

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In this paper, the terminal homing loop with a IIR-type strapdown seeker and a roll rate gyroscope is proposed. Basically, the proposed homing loop is based on the look-angle-control guidance. Since the range of the seeker is strictly limited, the missile is delivered to a point to lock the target on the seeker via non-guided flight during the midcourse guidance. The non-standard firing table is developed to compensate the wind and the target movement. To secure the delay margin is very important to prevent the instability of the homing loop when the time delay of the seeker is included. To validate the proposed homing loop, the 6-DOF nonlinear simulation is performed, and the Monte-Carlo simulation is also done for checking the robustness for the various kinds of uncertainty. 초 록본

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How Autopilot Requirements Constrain the Aerodynamic Design of Homing Missiles

Cited by 42 publications

References 3 publications

Comparison of Flight Control System Design Methods in Landing

Comparison of Flight Control System Design Methods in Landing

Design and Comparison of Two-Loop with PI and Three-Loop Autopilot for Static Unstable Missile

Look-Angle-Control Homing Loop Design with a Strapdown Seeker and Single Gyroscope

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