Predictive Tunnel Display for Hypersonic Flight Path Control

Sachs, Gottfried; Moravszki, Csaba

doi:10.2514/6.2006-6562

Cited by 3 publications

(5 citation statements)

References 6 publications

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“…(1), the presence of a nonminimum phase zero in the transfer function Δγ∕Δδ e is caused by the lift corresponding to the elevator deflection [12]. In particular, Z δ e −1∕m∂L∕∂δ e is very small for the Mars airplane because of the very low atmospheric density, such that this nonminimum phase zero is located to the far right.…”

Section: A Longitudinal Model and State Transformationmentioning

confidence: 99%

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Flight Control Law Using Composite Nonlinear Feedback Technique for a Mars Airplane

Liu

Peng

et al. 2016

Journal of Guidance, Control, and Dynamics

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Section: A Longitudinal Model and State Transformationmentioning

confidence: 99%

“…Considering the model uncertainties ω V and ω h and substituting Eqs. (12)(13)(14)(15)(16)(17)(18) into Eq. (7), we have…”

Section: Flight Control Law Design Using Composite Nonlinear Feementioning

confidence: 99%

Flight Control Law Using Composite Nonlinear Feedback Technique for a Mars Airplane

Liu

Peng

et al. 2016

Journal of Guidance, Control, and Dynamics

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“…The method was developed by the Technische Universität München (e.g. Sachs, 2008;Moravszki and Sachs, 2008;Sachs and Moravszki, 2002;2006). Since that, the principles haven been applied widely in other solutions (for example: .…”

Section: Introductionmentioning

confidence: 99%

Tunnel/Predictor Display for Trajectory Control in Hypersonic Flight

Moravszki

Rohács

Sachs

2018

Period. Polytech. Transp. Eng.

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A tunnel/predictor display which presents guidance information in a 3-dimensional format is considered for improving trajectory control in hypersonic flight. The displayed 3-dimensional information comprises a tunnel image and a predictor for indicating the aircraft position at a specified time ahead. The 3-dimensional guidance information is introduced to support the pilot in controlling the flight path. It is considered that piloting problems can be avoided which exist with conventional trajectory control techniques due to path-attitude decoupling. A predictor control law is constructed which yields controlled element properties (predictor-aircraft system) requiring minimum pilot compensation. This predictor control law forms the basis of the trajectory control improvement goal. Results from hypersonic flight simulation tests at the NASA Dryden Flight Research Center are presented for experimental verification. This paper is an outcome of a joint research effort of the NASA Dryden Flight Research Center, and the Institute of Flight Mechanics and Flight Control of the Technische Universität München and the Department of Aeronautics, Naval Architecture and Railway Vehicles (former Department of Aircraft and Ships at the Budapest University of Technology and Economics.

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“…Thus, the transfer function between the flight path angle and elevator deflection angle is emphatically discussed, which was explored in Ref. [27]:…”

Section: Performance Indices and Compromise Optimization For Hypersonmentioning

confidence: 99%

“…Specially, the trim angle of attack should be constrained within the certain rang e in which the scramjet can function well. In turn, the trim elevator deflection angle and pro pulsive coefficient should escape the input saturation to guarantee larger control authority [27].…”

Section: Performance Indices and Compromise Optimization For Hypersonmentioning

confidence: 99%

Compromise Optimal Design using Control-based Analysis of Hypersonic Vehicles

Liu¹,

Hua²

2015

International Journal of Aeronautical and Space Sciences

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Hypersonic vehicles exhibit distinct dynamic and static characteristics, such as unstable dynamics, strict altitude angle limitation, large control bandwidth, and unconventional system sensitivity. In this study, compromise relations between the dynamic features and static performances for hypersonic vehicles are investigated. A compromise optimal design for hypersonic vehicles is discussed. A parametric model for analyzing the dynamic and static characteristics is established, and then the optimal performance indices are provided according to the different design goals. A compromise optimization method to balance the dynamic and static characteristics is also discussed. The feasibility of this method for hypersonic vehicles is demonstrated.

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Predictive Tunnel Display for Hypersonic Flight Path Control

Cited by 3 publications

References 6 publications

Flight Control Law Using Composite Nonlinear Feedback Technique for a Mars Airplane

Flight Control Law Using Composite Nonlinear Feedback Technique for a Mars Airplane

Tunnel/Predictor Display for Trajectory Control in Hypersonic Flight

Compromise Optimal Design using Control-based Analysis of Hypersonic Vehicles

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