1993
DOI: 10.2514/3.21103
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Trajectory control for a low-lift re-entry vehicle

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Cited by 37 publications
(6 citation statements)
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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%
“…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%
“…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%
“…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%