Wave rider concept gliding aircraft profile design method satisfying filling demand

Abstract

The invention discloses a wave rider concept gliding aircraft profile design method satisfying filling demands; the method comprises the following steps: determining fuselage up and down contour control lines according to dimension constraints of the fuselage length and different cross sections, wherein the contour lines are spliced by linear segments; calculating an airflow deflection angle, calculating a two dimension tangent wedge flow field pressure, and calculating a FCT arc curve radius; determining an arc curve according to the FCT arc curve radius, and using the two dimension tangent wedge flow field to form a lower surface wave rider surface; using a secondary curve to form a leeside cross section shape; carrying out shrink ratio design for the lower surface wave rider surface according to the fuselage width and height dimension constraints and the upper surface shape, thus obtaining the whole fuselage shape; designing a passivation rounding with the radius of 15mm on the head and the wave rider tip leaning edge; match-designing a control surface. The aircraft has excellent pneumatic performance, and is high in practicality.

Description

technical field [0001] The invention relates to a shape design method of a waveriding concept glider aircraft meeting loading requirements. Background technique [0002] Different strategic goals, use modes and launch platforms have led to innovative and diversified development of hypersonic vehicle aerodynamic layout and flight methods. Hypersonic boost-glide vehicles have always been the focus of attention in the current hypersonic field. In order to achieve hypersonic boost-glide flight, the aircraft needs to have a large re-entry speed, a shallow re-entry angle, a small re-entry mass, a large hypersonic trim lift-to-drag ratio and trim lift, and meet the requirements of trim Static and dynamic stability in the three directions of pitch, yaw, and roll under the state, the control method is simple and efficient, the aerodynamic and thermal environment is relatively good, the heat protection burden is small, the internal filling volume and volume utilization rate are large,...

AI Technical Summary

Problems solved by technology

[0006] 3. The general design does not consider the difficulty of vertical and horizontal steering stability matching in the design of the rudder surface;

[0007] 4. If there are clear loading requirements and size requirements for the waverider aircraft, the waverider basically cannot be realized

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