Preset performance-based hypersonic aircraft longitudinal derogation control method

A vertical and hypersonic technology for aircraft, applied in the direction of instruments, computer-aided design, design optimization/simulation, etc., can solve the problems that the controller cannot reach

Active Publication Date: 2018-06-15
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, due to the lack of dynamic modeling of the damage on the wing, the purpose of adequate damage suppression cannot be achieved when designing the controller, so the damage crack model based on crack growth such as FASTRAN-2, the continuous-time damage model i

Method used

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  • Preset performance-based hypersonic aircraft longitudinal derogation control method
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  • Preset performance-based hypersonic aircraft longitudinal derogation control method

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Embodiment Construction

[0139] Embodiments of the invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the figures are exemplary only for explaining the present invention and should not be construed as limiting the present invention.

[0140] The force suffered on the hypersonic vehicle wing of the present invention is as follows figure 1 As shown, it is mainly affected by the lift force L w , resistance D w , Wing weight G w and engine thrust F T In order to calculate the bending moment, the lift force, drag force and wing weight should form a distributed force along the span direction, respectively q L ,q D and q w , then the lift force on a section can be calculated as q L And the product of the section width w here, similarly calculate the resistance and gravity at a certain section.

[0141] Such as figure 2 Shown, choose any section S d is the target section, then S d The bending mome...

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Abstract

The invention discloses a preset performance-based preset performance-based hypersonic aircraft longitudinal derogation control method. The method comprises the following steps of: 1) carrying out stress analysis on wings of a hypersonic aircraft; 2) carrying out damage dynamic modeling on the whole wings; and 3) designing a longitudinal layered preset performance derogation controller by utilizing real-time damage information obtained by a damage model through the established damage dynamic model. The method is capable of decreasing damage accumulation of aircrafts in flights and greatly maintaining flight performance of the aircrafts when derogation is not carried out, so that the method is good in application effect.

Description

technical field [0001] The invention relates to a method for controlling longitudinal damage of a hypersonic aircraft based on preset performance, and belongs to the technical field of aircraft damage control. Background technique [0002] The wing is the key structure for the lift of a hypersonic vehicle (HFV). Complex aerodynamic effects such as thin shock layer, viscous interference, entropy layer, high temperature effect and low density effect make the surface of the wing generate more complex aerodynamic load distribution, threatening Flight safety, so in order to prolong the life of the aircraft, it is necessary to adopt effective control strategies to reduce the damage of the wings during normal flight. [0003] In recent years, the research on aircraft damage reduction control has achieved important results. First, some scholars proposed a scheme based on limiting the maximum load factor of the aircraft, and designed a controller called "g-limiter". This controller ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20G06F2119/06
Inventor 王玉惠应竣棫牟金震张晓辉吴庆宪
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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