Robust Partial Integrated Guidance and Control of Interceptors in Terminal Phase

Das, Payel; Chawla, Charu; Padhi, Radhakant

doi:10.2514/6.2009-6275

Cited by 13 publications

(11 citation statements)

References 6 publications

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“…Full nonlinear equations of the air vehicle and target motions that is entitled as engagement kinematics is described in this section. As described earlier, the IGC system only improves the performance of the endgame phase while it does not noticeably affect the midcourse phase [9]. The IGC design for the endgame phase is considered in this paper.…”

Section: Nonlinear Kinematicsmentioning

confidence: 98%

“…A backstepping IGC design with impact angle constraint has been proposed in [8], where the authors utilize a sliding mode disturbance observer. In [9], a partial IGC was developed, which includes inner and outer loops and was designed based on model predictive spread control and dynamic inversion control. Sun and his colleagues have proposed an IGC design using a subspace stabilization method where the angle of attack tracking has been implemented in the IGC loop [10].…”

Section: Integrated Guidance and Control Of Elastic Vehicle 2609mentioning

confidence: 99%

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Integrated guidance and control of elastic flight vehicle based on robust MPC

Shamaghdari

Nikravesh

Haeri

2014

Int. J. Robust. Nonlinear Control

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SUMMARYIntegrated guidance and control of an elastic flight vehicle based on constrained robust model predictive control is proposed. The design is based on a partial state feedback control law that minimizes a cost function within the framework of linear matrix inequalities. It is shown that the solution of the defined optimization problem stabilizes the nonlinear plant. Nonlinear kinematics and dynamics are taken into account, and internal stability of the closed-loop nonlinear system is guaranteed. The performance and effectiveness of the proposed integrated guidance and control against non-maneuvering and weaving targets are evaluated using computer simulations.

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Section: Nonlinear Kinematicsmentioning

confidence: 98%

Section: Integrated Guidance and Control Of Elastic Vehicle 2609mentioning

confidence: 99%

Integrated guidance and control of elastic flight vehicle based on robust MPC

Shamaghdari

Nikravesh

Haeri

2014

Int. J. Robust. Nonlinear Control

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“…(13), Eq. (15) such that sin γ = cos α cos β sin θ − sin β sin φ cos θ − sin α cos β cos φ cos θ (32) Ensuring side slip angle to be zero through coordinated turn, Eq. (15) such that sin γ = cos α cos β sin θ − sin β sin φ cos θ − sin α cos β cos φ cos θ (32) Ensuring side slip angle to be zero through coordinated turn, Eq.…”

Section: Figure 3 3d View Of the Vectorial Representation Of The Uavmentioning

confidence: 99%

“…In the outer loop, guidance command tracking is executed through nonlinear dynamic inversion (NDI), 24 where the velocity vector aligns the aiming point by enforcing the angle correction in the flight path angles, while assuring the turn coordination. Neuro-adaptive controller [31][32][33] is designed to overcome the uncertainty in the aerodynamic coefficients which may get amplified during the inversion process. Control surface deflections generated through inner loop and are realized by the first order actuator dynamics.…”

Section: Introductionmentioning

confidence: 99%

Neuro-Adaptive Augmented Dynamic Inversion Based PIGC Design for Reactive Obstacle Avoidance of UAVs

Chawla

Padhi

2011

AIAA Guidance, Navigation, and Control Conference

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In this paper, the problem of reactive obstacle avoidance is addressed by an innovative partial integrated guidance and control (PIGC) approach using the Six-DOF model of real UAV unlike the kinematic models used in the existing literatures. The guidance strategy uses the collision cone approach to predict any possible collision with the obstacle and computes an alternate aiming direction for the vehicle to avoid the obstacle. The reactive nature of the avoidance problem within the available time window demands simultaneous reaction from the guidance and control loop structures of the system i.e, in the IGC framework (executes in single loop). However, such quick maneuvers causes the faster dynamics of the system to go unstable due to inherent separation between the faster and slower dynamics. On the contrary, in the conventional design (executes in three loops), the settling time of the response of different loops will not be able to match with the stringent time-to-go window for obstacle avoidance. Such tracking delays will affects the system performance adversely. However, in the PIGC framework, it overcomes the disadvantage of both the IGC design and the conventional design. PIGC approach executes the avoidance maneuver in two loops. In the outer loop, the vehicle guidance strategy attempts to reorient the velocity vector of the vehicle along the aiming point within a fraction of the available time-to-go. The outer loop generates the body angular rates which are tracked by the inner loop to generate the necessary control surface deflections. Control surface deflections are realized by the vehicle through the first order actuator dynamics. A controller for the first order actuator model is proposed in order to reduce the actuator delay. Every loop of the PIGC technique uses nonlinear dynamic inversion technique which has critical issues like sensitiveness to the modeling inaccuracies of the plant model. To make it robust against the parameter inaccuracies of the system, it is reinforced with the neuro-adaptive design. In NA design, weight update rule based on Lyapunov theory provides online training of the weights. To enhance fast and stable training of the weights, preflight maneuvers are proposed. Preflight maneuvers provides stabilized pre-trained weights which prevents any misapprehensions in the obstacle avoidance scenario. Simulation studies have been executed with different number and size of the obstacles. NA augmented PIGC design is validated with different levels of uncertainties in the plant model. Various comparative study shows that the NA augmented PIGC design is quite effective in avoiding collisions in different scenarios. Since the NDI technique involved in the PIGC design gives a closed loop solution and does not operate with iterative steps, therefore the reactive obstacle avoidance is achieved in a computationally efficient manner. Nomenclature CGCenter of gravity S Wing planform area, m 2 bWing span, m c Chord length, m dOffset of the thrust line from the CG of the vehicle., m mMass of the...

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“…Based on the feedback linearization, IGC was transformed into the trajectory optimization of finite-time linear quadratic form [11], [12], with the numerical solution of Riccati equation developed in [13]. In [1], [14], and [15], a robust partial IGC (PIGC) design was proposed. In the PIGC method, both the outer and inner loops were designed to preserve the philosophical benefits of both IGC and conventional separated design.…”

Section: Introductionmentioning

confidence: 99%

Fast Robust Integrated Guidance and Control Design of Interceptors

Song

Zhang

2016

IEEE Trans. Contr. Syst. Technol.

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In this brief, a fast robust integrated guidance and control design approach, considering the 3-D interception of interceptors for hypersonic vehicles, is proposed. The proposed method is designed using the modified fast terminal sliding mode control and dynamic surface control with signal compensation. The fractional integral fast terminal sliding functions are presented independently, and all the sliding phases run parallel to increase the system response speed. Utilizing the dynamic surface control method, the robust compensation signals are constructed to eliminate the influence of uncertainty equivalents thoroughly. Therefore, the proposed approach guarantees the fast convergence of line-of-sight angular rates and the system robustness for uncertainties. The simulation results demonstrate the robustness of the proposed controller, and a variety of comparison studies are also carried out to demonstrate the advantage of the new approach.Index Terms-Dynamic surface control, fast terminal sliding mode (FTSM) control, integrated guidance and control (IGC), interceptor.

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Robust Partial Integrated Guidance and Control of Interceptors in Terminal Phase

Cited by 13 publications

References 6 publications

Integrated guidance and control of elastic flight vehicle based on robust MPC

Integrated guidance and control of elastic flight vehicle based on robust MPC

Neuro-Adaptive Augmented Dynamic Inversion Based PIGC Design for Reactive Obstacle Avoidance of UAVs

Fast Robust Integrated Guidance and Control Design of Interceptors

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