Stage Separation Analysis of the X-43A Research Vehicle

Liever, Peter A.; Habchi, Sami D.; Engelund, Walter C.; Martín, José Manuel Sánchez

doi:10.2514/6.2004-4725

Cited by 7 publications

(3 citation statements)

References 3 publications

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“…It is suggested in Ref. [1] that the above conditions achieve pole placement and the system is stable when…”

Section: Design Of Switching Controller For Hypersonic-vehicle Fairin...mentioning

confidence: 99%

“…Several studies [1][2][3][4][5] have analyzed the feasibility of X-43A interstage separation and the aerodynamic characteristics of separation. Yang et al [6] elaborated on the interstageseparation strategy and flight-test verification of the X-43A hypersonic vehicle.…”

Section: Introductionmentioning

confidence: 99%

“…Compared with interstage separation, fairing separation is complex in its aerodynamic and interference characteristics, mainly reflected in the following: (1) the general parameters and shape of the hypersonic vehicle will not change in the process of interstage separation, but they often greatly change during the fairing-separation process. (2) when interstage separation occurs, the hypersonic vehicle is in front of the booster so the separation disturbance has less impact on the vehicle, whereas in fairing separation, the vehicle is behind the fairing, and the shockwave interference caused by the fairing movement will act on the body of the vehicle.…”

Section: Introductionmentioning

confidence: 99%

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A Switching-Based Control Method for the Fairing Separation Control of Axisymmetric Hypersonic Vehicles

Zhong

Fan

Wu³

2022

Aerospace

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For hypersonic-vehicle fairing separation, the reliable separation of the fairing and rapid suppression of the separation disturbance are required in scenarios where there is high dynamic pressure and there are abrupt changes in the aerodynamic shape of the aircraft as well as overall parameters. A switching-based control method is proposed in this paper for the interference suppression of hypersonic-vehicle fairing separation, aiming to ensure the stability of the control system in cases of abrupt changes in the controlled object. First, an unsteady-flow calculation method is adopted to clarify the aerodynamic interference characteristics of the aircraft in fairing separation, and the aerodynamic calculation model of the hypersonic-vehicle fairing-separation process is established; then, two states of the aircraft, with and without fairing, are transformed into a subsystem with switching characteristics. The attitude-stability problem in the fairing-separation process is transformed into a problem of solving the arbitrary switching of the switched system by using the linear matrix inequality (LMI) approach. Meanwhile, the control system for interference suppression of the fairing separation is designed by considering the aerodynamic interaction of the fairing movement with the aircraft during the separation. The simulation results showed that the designed control system can realize the reliable separation of the fairing under high dynamic pressure and effectively suppress interference in the separation process.

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“…It is suggested in Ref. [1] that the above conditions achieve pole placement and the system is stable when…”

Section: Design Of Switching Controller For Hypersonic-vehicle Fairin...mentioning

confidence: 99%