Rocket engine integration wave rider aircraft

Abstract

The invention provides a rocket engine integration wave rider aircraft. The aircraft comprises wave-riding wings (1), a load bin (2), an engine bin (3), a tail bin (5), V tails (4) and an engine tailspraying pipe (6). The load bin (2), the engine bin (3) and the tail bin (5) are sequentially connected in a transition manner to form an aircraft body. The wave-riding wings (1) are located below theaircraft body. The V tails (4) are symmetrically installed above the tail portion of the engine bin (3) and the tail bin (5). The engine tail spraying pipe (6) extends out from the end face of the rear portion of the tail bin (5). The wave-rider aircraft can solve and avoid the technical problems that the shape of a combination body of an existing boosting gliding hypersonic flight vehicle and aroll booster is poor in stability characteristic, high dynamic pressure stage separation risk of the non-axis symmetry shape is high, and the aerodynamic resistance of a driving section is large, andthe overall performance indexes such as the higher lift-drag ratio and the higher filling volume utilization rate are achieved.

Description

technical field [0001] The invention relates to a waverider hypersonic aircraft powered by a solid rocket, which is applicable to boost-glide hypersonic flight. Background technique [0002] Near-space boost-glide vehicles generally use solid rocket boosters to obtain initial velocity, such as figure 1 As shown in Fig. 1, after the active flight of the rocket, the aircraft is separated from the booster, and then the aircraft flies in an unpowered gliding mode. In order to achieve long-distance and long-term gliding flight, the near-space gliding vehicle needs to adopt a symmetrical aerodynamic layout with a high lift-to-drag ratio. When launching, it is generally connected in series with the axisymmetric booster rocket, resulting in a combination of the vehicle and the booster. There are technical problems such as poor body shape stability, non-axisymmetric shape with high dynamic pressure, high risk of separation between stages, and large aerodynamic resistance in the acti...

AI Technical Summary

Problems solved by technology

In order to achieve long-distance and long-term gliding flight, the near-space gliding vehicle needs to adopt a symmetrical aerodynamic layout with a high lift-to-drag ratio. When launching, it is generally connected in series with the axisymmetric booster rocket, resulting in a combination of the vehicle and the booster. Poor body shape stability characteristics, non-axisymmetric shape, high dynamic pressure stage separation risk, high aerodynamic resistance of the active section and other technical problems

Images