Trajectory control for a low-lift re-entry vehicle

Roenneke, Axel J.; Cornwell, Phillip

doi:10.2514/3.21103

Cited by 37 publications

(6 citation statements)

References 5 publications

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“…Through the limited on-board computer performance, the early Fast algorithm for predictive guaranteeing control with application to low-lift re-entry operational guidance schemes, such as that used at the Gemini and the Apollo final phase of re-entry, relied on a pre-stored trajectory (lift-to-drag reference, in fact). Although this study is still in progess [4,5], the development of more powerful on-board computers, as well as the growing interest to the future economic aerospace transportation systems and intelligent guidance schemes, resulted in that the focus is gradually shifting to the predictive guidance strategy as more flexible and self-reliant [6][7][8]. Since a predictive guidance system is based on a detailed mathematical model of the controlled dynamic object, it allows guiding a re-entry vehicle to the destination point under considerable unforeseen disturbances and limited control capabilities, including emergency cases.…”

Section: Introductionmentioning

confidence: 91%

Fast Algorithm for Predictive Guaranteeing Control with Application to Low-Lift Re-Entry

Kozynchenko

2009

Journal of Algorithms & Computational Technology

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The paper touches the general problem of predictive bounded final state control of dynamic systems, which is typical in many applications, especially in aerospace area. Two closely interrelated aspects of this problem are under consideration, namely, maximizing the manoeuvring capabilities of a space vehicle and reducing the computational load when finding the final state control function in repetitive corrections over a trajectory. The suggested control strategy addresses the both aspects. The main idea consists in replacing the hard differential eigenvalue problem to be solved within a limited time in a correction session by the algorithm that solves initial-value problems with average control over the flight time and makes decisions based on a predicted miss. The equality of manoeuvrability margins is provided in the maximal remaining part of trajectory. The computer simulation of the reduced targeting problem of a low-lift re-entry vehicle shows feasibility and effectiveness of the proposed strategy.

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Section: Introductionmentioning

confidence: 91%

Fast Algorithm for Predictive Guaranteeing Control with Application to Low-Lift Re-Entry

Kozynchenko

2009

Journal of Algorithms & Computational Technology

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“…Other possible solutions foresaw the use of a receding-horizon scheme based on the linearized time-varying dynamics to be controlled [15], and a unied predictor-corrector algorithm [16], which covers all the possible entry mission proles. The problem was also approached by using dierent gain-scheduling controllers [17,18], or by tracking altitude and velocity via Model Reference Adaptive Control (MRAC) [19,20]. A possible alternative to the state-tracking schemes is a generalized constrainttracking guidance, with a particular emphasis on the tracking of the heat-ux [21,22].…”

Section: Introductionmentioning

confidence: 99%

Adaptive Disturbance-Based High-Order Sliding-Mode Control for Hypersonic-Entry Vehicles

Sagliano

Mooij

Theil

2017

Journal of Guidance, Control, and Dynamics

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In this paper an adaptive, disturbance-based sliding-mode controller for hypersonic entry vehicles is proposed. The scheme is based on high-order sliding-mode theory, and is coupled to an extended sliding-mode observer, able to reconstruct online the disturbances. The result is a numerically-stable control scheme, able to adapt online to reduce the error in presence of multiple uncertainties. The transformation of a highorder sliding-mode technique into an adaptive law by using the extended sliding-mode observer is, together with the multi-input, multi-output formulation for hypersonic entry vehicles, the main contribution of this paper. The robustness is veried with respect to perturbations in terms of initial conditions, atmospheric density variations, as well as mass and aerodynamic uncertainties. Results show that the approach is valid, leading to accurate disturbance reconstruction, to a better transient, and to good tracking performance, improved of about 50% in terms of altitude and range errors with respect to the corresponding standard sliding-mode control approach.

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“…Most of the existing works about trajectory tracking on guided rockets were based on time invariant models, [4][5][6][7][8] and therefore the adaptability of controller cannot be guaranteed since the parameters of guided rockets vary fast over a large operation range. 9 To improve the performances of different categories of flight vehicles, lots of high-performance control methods have been employed for trajectory tracking, [10][11][12] with which, the trajectory error system was constructed on the basis of the reference trajectory while the linear quadratic regulation (LQR) theory was used for trajectory tracking. However, this kind of method is still based on the time invariant model, thus the scheduling gain obtained by solving the Riccati differential equations cannot ensure the global stability of the trajectory error system.…”

Section: Introductionmentioning

confidence: 99%

Trajectory tracking using robust gain-scheduling control with a new independent variable

Jiang

Chen

Wang

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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To reduce the expenditure, a low-performance guidance and control system is usually employed in the design of guided artillery rockets, which however will induce great difficulties in trajectory tracking because the rocket's parameters vary fast over a large operation range. The traditional time invariant control approaches for trajectory tracking cannot guarantee the adaptability of controller. On the other hand, since time is routinely considered as the independent variable, the dynamic error system varies sharply, resulting in a weak anti-jamming capability. To address these issues, a new trajectory tracking approach for guided rockets is developed by using the robust gain-scheduling control technique based on the linear parameter varying system, in conjunction with a new coordinate transformation that considers the arc length of reference trajectory as the independent variable. Through comparative studies, it is observed that the proposed method outperforms the existing ones in trajectory tracking during the whole flight trajectory, which demonstrates its effectiveness and advantages.

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Trajectory control for a low-lift re-entry vehicle

Cited by 37 publications

References 5 publications

Fast Algorithm for Predictive Guaranteeing Control with Application to Low-Lift Re-Entry

Fast Algorithm for Predictive Guaranteeing Control with Application to Low-Lift Re-Entry

Adaptive Disturbance-Based High-Order Sliding-Mode Control for Hypersonic-Entry Vehicles

Trajectory tracking using robust gain-scheduling control with a new independent variable

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