A rotary aircraft based on a new type of flap rudder surface

Abstract

A rotary aircraft based on a new type of flap rudder is based on a sphere-conical configuration of a rotary aircraft. This aircraft has a new type of flap control rudder surface. By designing four x-shaped distributed flaps on the tail of the body of rotary aircraft, and using the flaps as the full-motion rudder surface of the aircraft, the maneuverability of the aircraft at hypersonic speed can be obtained by flap deflection. The new type of flap rudder surface, replacing a common tail layout scheme, is helpful to reduce or eliminate the aerodynamic interference and heating problems in the conventional tail-fin configuration scheme, and effectively increase the loading space inside the aircraft instead of conventional tail-fin configuration scheme. The novel flap type control rudder is arranged at the bottom of the body of revolution fuselage, the flow of the flap rudder surface under the hypersonic environment will not affect the flow of the upstream body of revolution fuselage, theaerodynamic interference between the flap rudder and the body of the aircraft fuselage is small, and the problem of mutual interference between the tail fins of the conventional body of revolution fuselage is effectively avoided.

Description

technical field [0001] The invention is a rotary aircraft based on a novel flap rudder surface, which belongs to the field of aerodynamic layout design of hypersonic aircraft. Background technique [0002] Ballistic missiles, as the basis for a country to maintain medium and long-range strike capabilities, are the focus of the research and development of weapons and equipment by major military powers in the world. With the rapid development of anti-missile technology in recent years, the inertial re-entry flight of traditional ballistic missiles has become difficult to break through the interception of current anti-missile systems. At present, countries around the world are seeking re-entry weapon systems that are more mobile and capable of penetrating defenses. Therefore, it is very urgent to develop a new type of reentry vehicle with high maneuverability. [0003] The layout of conventional reentry vehicles mostly adopts the ball-cone structure. At present, this type of ...

AI Technical Summary

Problems solved by technology

Although the thermal protection pressure of the trailing edge rudder surface is small, the rudder shaft will still have obvious thermal load problems at high angles of attack, which will adversely affect the safety and effectiveness of the rudder

In addition, under the premise of a given outer envelope, the four tail fins of the rotatable aircraft will greatly reduce the actual space of the fuselage, which will bring difficulties to the loading of the internal mechanism, and also reduce the amount of charge, which limits the weapon's capacity. Damage power

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