Abstract
In this article, a low-order partial integrated guidance and control (PIGC) design method is proposed for diving hypersonic vehicles to impact ground maneuver target. A three-channel analytical model of body rates is deduced based on acceleration components of the hypersonic vehicle. By combining the analytical model of body rates and relative dynamic model between the hypersonic vehicle and target, three-channel commands of body rates are directly generated based on the extended state observer (ESO) technique, sliding mode control approach, and dynamic surface control theory in the guidance subsystem. In the attitude control subsystem, a sliding mode controller is designed to track the commands of body rates and generate commands of control surface fin deflections. By making full use of acceleration information of the hypersonic vehicle measured by the mounted accelerometer, the proposed PIGC design method provides a novel solution to compensate the unknown acceleration of the ground maneuver target. Besides, the order of design model is also reduced, and the design process is simplified. The effectiveness and robustness of the PIGC design method are verified and discussed by 6DOF simulation studies.
Highlights
(1) Single-channel/plane integrated guidance and control (IGC) scheme: the three-dimensional (3D) motion of the air vehicle is decomposed into different channels or planes, and the coupling between each channel/plane is regarded as a small amount, which is generally neglected
(2) Full-state IGC scheme: a full-state high-order IGC design model is established, which takes rotational motion model of the air vehicle and relative motion model between the air vehicle and target into account. e order of the design model is usually 8–10, and the design model is generally transformed into a strict feedback form. en, the backstepping control, dynamic surface control, or other control methods are used to solve the high-order IGC system
(3) partial integrated guidance and control (PIGC) scheme: the PIGC scheme is executed in the guidance and control loops. e two-loop controller structure is similar to the full-state single-loop controller structure under some conditions. e PIGC method takes body rates instead of acceleration components of the air vehicle as the virtual inputs. e control loop is designed to track the commands of body rates. e order of design model and the number of design parameters can be reduced by using this method [15,16,17]
Summary
The design scheme of a novel PIGC system is presented, which contains a guidance loop and a control loop. A sliding mode attitude controller is designed to track the commands of body rates, and commands of control surface fin deflections are directly obtained in the control loop. Combining equations (15) and (22), the desired three-channel body rates of the hypersonic vehicle can be directly generated as ωx,c ωy,c ωz,c (AB)−1⎛⎜⎜⎜⎜⎜⎜⎜⎜⎜⎜⎜⎜⎜⎜⎝TGHC−1⎡⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎢⎣. By designing the attitude controller to track the three-channel commands of body rates, λ_ D and λ_ T can gradually converge to zero. E elements of matrix AB are the functions of components of velocity vector of the hypersonic vehicle in the body coordinate system and rotational Euler angles. To track the commands of body rates generated in the guidance subsystem, the commanded control surface fin deflections of the hypersonic vehicle should be calculated by designing the attitude control subsystem. Where ωn 20 Hz is the natural frequency of the secondorder model and ξ 0.7 is the damping ratio of the model
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