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Full-waverider aircraft and design method and system thereof

A design method and technology for aircraft, which can be used in computer-aided design, design optimization/simulation, instruments, etc., and can solve the problems of complex adjustment, reduction, and large amount of calculation.

Active Publication Date: 2020-04-14
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The present invention provides a full waverider aircraft and its design method and system, which are used to overcome the defects in the prior art that cannot directly adjust and optimize the shape of the aircraft according to the design requirements, resulting in a large amount of calculation and complicated adjustment, and realize the design of the lip shape. The three-dimensionalization of the domain, the lift distribution of the aircraft is obtained through the horizontal projection shape of the leading edge line. Through the design of the horizontal projection shape, aerodynamic designers can adjust and optimize the shape of the aircraft more directly according to the design requirements, simplifying the design process and reducing calculation. volume, improving design efficiency

Method used

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Embodiment 1

[0075] As attached figure 1 As shown, the embodiment of the present invention provides a fully-wave-riding aircraft design method. The fully-wave-riding design of a drop-shaped air inlet based on a horizontal projection profile includes the following steps:

[0076] Step S1: Solve and obtain the reference flow field of the airframe according to the design parameters of the reference flow field of the given airframe;

[0077] Step S2: Discrete and solve the discrete points of the above three curves according to the equations of the horizontal projection profile of the front edge line of the full wave multiplier aircraft, the inlet lip and the front edge line of the wing;

[0078] Step S3, according to the given precursor-inlet reference flow field parameters, cyclically solve the precursor-intake reference flow field in the meridian plane corresponding to the discrete points of the horizontal projection profile of each precursor front edge;

[0079] Step S4: Perform streamline tracing i...

specific Embodiment

[0168] A specific embodiment of the present invention is provided below, which is specifically as follows:

[0169] The design parameters of the airframe reference flow field are shown in Table 1, and the design parameters of the precursor-inlet reference flow field are shown in Table 2. The input parameters of geometric shape design are shown in Table 3.

[0170] Table 1

[0171]

[0172] Table 2

[0173]

[0174] table 3

[0175]

[0176] Fig. 20(a), Fig. 20(b), and Fig. 20(c) are three views of specific embodiments of the fully-riding aircraft. The test model has a three-dimensional lip profile, so that the shape of the air inlet has a drop-shaped feature. Therefore, in terms of appearance, the original design intention of this article is realized. Next, in order to verify whether the design plan meets the full wave characteristics, the flow field structure of the test model under the design conditions needs to be verified.

[0177] Such as Figure 21 As shown, the non-stick Mach ...

Embodiment 2

[0179] Based on the first embodiment above, the present invention provides a fully multiplied aircraft design system, including a memory and a processor, the memory stores a fully multiplied aircraft design program, and the processor is running the fully multiplied aircraft design program When performing the steps of any embodiment of the above method.

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Abstract

The invention discloses a full-waverider aircraft and a design method and system thereof. The method comprises the steps that an aircraft body reference flow field is obtained through solving according to given aircraft body reference flow field design parameters; discretizing and solving discrete points of the three curves according to an equation of horizontal projection molded lines of a leading edge line, an air inlet lip and a wing leading edge line of the given full waverider aircraft; according to given precursor-air inlet channel reference flow field parameters, circularly solving a precursor-air inlet channel reference flow field in a meridian plane corresponding to each precursor front edge line horizontal projection molded line discrete point; performing streamline tracking in the forebody-air inlet reference flow field and the body reference flow field, and generating and outputting streamlines forming the aerodynamic configuration of the full waverider aircraft; generatingdifferent water drop type air inlet full waverider components according to output streamline geometric lofting, and generating an upper surface through a free flow surface method. The problems of complex design steps, large calculation amount and the like in the prior art are solved, and the calculation steps and the calculation amount are simplified.

Description

Technical field [0001] The invention relates to the technical field of aerodynamic shape design of hypersonic aircraft, in particular to a drop-shaped full-wave-riding aircraft based on a horizontal projection profile and a design method and system thereof. Background technique [0002] Hypersonic aircraft is an aircraft with a speed exceeding Mach 5, including air-breathing hypersonic aircraft, rocket-powered hypersonic aircraft, and unpowered gliding aircraft. Specific application forms include hypersonic cruise missiles, hypersonic manned / unmanned aircraft, and air Sky plane and many other aircraft. [0003] It is worth noting that the air-breathing hypersonic vehicle is one of the important development directions. It is difficult to distinguish between the propulsion system unit of the air-breathing hypersonic vehicle and the airframe (airframe), and an integrated airframe / propulsion design is required. The development of airframe / propulsion integration technology relies on a...

Claims

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Application Information

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IPC IPC(8): B64F5/00G06F30/20G06F30/15G06F119/14G06F113/08
CPCB64F5/00Y02T90/00
Inventor 柳军陈韶华丁峰罗仕超蒋浩张文浩唐培杰
Owner NAT UNIV OF DEFENSE TECH
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