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Guidance and control of standoff air-to-surface carrier vehicle

Published online by Cambridge University Press:  05 April 2019

I. Mir ,
S. Akhtar ,
S.A. Eisa  and
A. Maqsood
I. Mir*
Affiliation:
National University of Sciences and Technology Research Center for Modeling and Simulation, Islmabad, Pakistan
S. Akhtar
Affiliation:
National University of Sciences and Technology, College of Aeronautical Engineering, Risalpur, Pakistan
S.A. Eisa
Affiliation:
University of California, Mechanical and Aerospace Engineering Department, Irvine, CA, USA
A. Maqsood
Affiliation:
National University of Sciences and Technology Research Center for Modeling and Simulation, Islmabad, Pakistan
*
*[email protected]
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Abstract

This paper presents an open framework, through which, conventional general purpose aerial munitions can be converted into smart munitions. The retrofit consists of a smart adaptation kit (SAK) having a dedicated Guidance and Control Module (GCM). The adaptation kit along with the GCM ensures that the SAK glide optimally towards the designated target. To reduce cost, the number of control surfaces of the SAK has been kept to a bare minimum, which resulted in an under actuated system. The methodology proposed utilises the theory of gain-scheduled control and leads to an efficient procedure for the design of the controllers, which accurately track reference trajectories defined in an inertial reference frame. The paper illustrates the application of this procedure to the design of stabilisation and tracking controller for the SAK. The design phase is summarised, and the performance of the resulting controllers is assessed in simulation using dynamic model of the vehicle. Simulation results show that apart from improved circular error probable (CEP) of hitting the target, munition ballistic range has also significantly increased with the proposed modification.

Keywords

Range enhancement kitTrajectory optimizationControl law synthesisNumeric simulations
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1261 , March 2019 , pp. 283 - 309
Copyright
© Royal Aeronautical Society 2019 

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