Method and system for optimizing transverse course stability of quasi waverider configuration and lifting body
An optimization method and technology of waveriders, applied in design optimization/simulation, supersonic aircraft, instruments, etc., can solve problems such as reducing the success of flight missions, aerodynamic ablation of stabilizers, loss of lift-to-drag ratio, etc. Heading stability, ease of thermal protection problems, and little effect on lift-to-drag ratio
Pending Publication Date: 2021-06-11
INST OF MECHANICS - CHINESE ACAD OF SCI
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Problems solved by technology
However, due to the prominent aerodynamic and thermal problems during hypersonic flight, the aerodynamic ablation of the raised stabilizer on the fuselage is serious, which will face a greater risk of structural failure, and the shock waves generated will further increase the wave resistance, resulting in greater loss of lift-to-drag ratio, thereby greatly reducing the probability of mission success
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[0060] see figure 1 , which is a method for optimizing lateral and directional stability of a quasi-waverider configuration provided by an embodiment of the present invention, such as figure 1 As shown, the method may include:
[0061] S101: Obtain the target point on the original leading edge line of the original quasi-waverider configuration in the calculation coordinate system as a reference point; the calculation coordinate system is the body coordinate system of the original quasi-waverider configuration;
[0062] S102: Construct a datum plane through the reference point, the datum plane is parallel to the plane formed by the X-axis and the Y-axis in the calculation coordinate system;
[0063] S103: passing through the reference point to form a reference axis parallel to the Y axis;
[0064] S104: Construct an initial plane where the original leading edge line is located via the reference axis and obtain an initial angle between the initial plane and the reference plane...
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The invention discloses a transverse course stability optimization method and system for a quasi waverider configuration and a lifting body, and the method can achieve the shaping of an original quasi waverider, generates a projection plane through changing the included angle between an initial plane where a leading edge line is located and a horizontal plane. A leading edge line of an original quasi waverider configuration is projected on a projection plane to generate a new leading edge line, and the position of the leading edge line is adjusted by adjusting an included angle between an initial plane and a horizontal plane, so that the upward reflection characteristic of the lower surface of the quasi waverider is changed, and the transverse course stability of the quasi waverider is easily adjusted. And meanwhile, the transverse course stability of the aircraft can be adjusted without depending on a convex stabilizer on the aircraft body, so that the thermal protection problem during hypersonic flight is greatly relieved.
Description
technical field [0001] The present invention relates to the technical field of waverider configuration optimization, in particular to a method, system and lift body for optimizing the transverse and directional stability of a quasi-waverider configuration. Background technique [0002] Under hypersonic conditions, since the leading edge of a conventionally shaped aircraft in the supersonic flow is mostly an out-of-body shock wave, the pressure difference before and after the shock wave makes the wave resistance on the conventionally shaped aircraft very large, and the aircraft will suffer great damage. It is very difficult to increase the lift-to-drag ratio due to friction and wave resistance, and will face an insurmountable "lift-to-drag ratio barrier". In order to solve the above-mentioned problems, the aircraft of waverider configuration emerges as the times require. The waverider configuration, also known as the waverider, is an aircraft shape suitable for hypersonic fl...
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IPC IPC(8): G06F30/28G06F30/15B64F5/00B64C30/00G06F113/08G06F119/14
CPCG06F30/28G06F30/15B64F5/00B64C30/00G06F2119/14G06F2113/08Y02T90/00
Inventor 刘文张陈安杨磊李文皓
Owner INST OF MECHANICS - CHINESE ACAD OF SCI