Robust lateral control of hypersonic vehicles

Heller, Matthias; Holzapfel, Florian; Sachs, Gottfried

doi:10.2514/6.2000-4248

Cited by 16 publications

(11 citation statements)

References 3 publications

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“…The thrust model of hypersonic aircraft is very complex, scholars are attracted extensive research interest by the engine model [1][2][3][4] . The complex of force model mainly depends on a huge impact of attack angle and elastic form.…”

Section: Introductionmentioning

confidence: 99%

Speed control of high speed aircraft with fixed attack angle and constant elastic shape states

Jin¹,

Wang²

2015

Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications

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Abstract. For high speed vehicles, the engine model is difficult to built. Also it is very important and difficult to design a proper oil supplying law to make the speed of control object to tracking the desired value as accurate as possible. So a kind of speed controller is designed based on the pitch channel model built according to Lagrange equation and released by USA force. Since the speed of this flying object is too high, to make the question simple, a kind of virtual flying condition is proposed such that the design of speed controller can be simple and easy to verify. So the attack angle is assumed to be constant and the elastic shape states are also assumed to be a constant. And this virtual flying design method can not only make the speed controller design simple, it can also make it is possible to testify the rightness of the engine model with the help of numerical simulation technology.

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Section: Introductionmentioning

confidence: 99%

Speed control of high speed aircraft with fixed attack angle and constant elastic shape states

Jin¹,

Wang²

2015

Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications

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“…The thrust changing sharply causes the pitching rotation moment of hypersonic flight vehicle difficult to balance from open-loop characteristics of canard test simulation graph [1][2][3][4]. Thus it leads to the divergence of attack angle.…”

Section: Introductionmentioning

confidence: 99%

The open loop response analysis of duck wing with trust resistance balance and constant elasticity

Wang¹,

Chu²,

Li³

et al. 2015

Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications

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Abstract.A kind of virtual flying condition is assumed that the trust and resistance is the same that can keep the force balance during the flying process of high speed aircraft. The main function of this virtual assumption is that it can the unstable open loop aircraft fly a longer time so more date can be gotten and the duck wing response or effect can be analyzed more clearly. So it is a new method and it is effective and meaningful for the open loop dynamic analysis especially for high speed unstable control objects.

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“…Starting point is based on the above in this paper. The divergence speed of attack angle is researched in canard steady cases based on hypersonic longitudinal motion model published by the U.S. air force research laboratory by selecting typical cases of the constant speed and constant elasticity, thereby standard the instability degree of from the canard to angle attack [6][7][8][9][10] .…”

Section: Introductionmentioning

confidence: 99%

The research on open loop actuator response of high speed vehicle based on constant speed and constant elasticity

Liu¹,

Chen²,

Li³

et al. 2015

Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications

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Abstract. Based on a kind of pitch channel model of supersonic aircraft which is released by America air force research center, a kind of open loop testing method is proposed to testify the actuator effect of a kind of high speed aircraft. The difference between this type of aircraft and other traditional aircraft is that open loop response is unstable so it is not easy to do this kind of actuator test. So a kind of virtual flying condition is assumed to make the simulation can last for a longer time, also it can make the analysis of actuator effect to be more clear and simple. Also the physical meanings of this kind of unstable open loop response is analyzed.

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Robust lateral control of hypersonic vehicles

Cited by 16 publications

References 3 publications

Speed control of high speed aircraft with fixed attack angle and constant elastic shape states

Speed control of high speed aircraft with fixed attack angle and constant elastic shape states

The open loop response analysis of duck wing with trust resistance balance and constant elasticity

The research on open loop actuator response of high speed vehicle based on constant speed and constant elasticity

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