Tailless flying wing layout plane with split type wing tip

Abstract

The invention provides a tailless flying wing layout plane with a split type wing tip, relating to the technical field of plane structure design, and being used for course regulation of the tailless flying wing layout plane. An upper wing tip and a wing are in shaft driving connection by means of an upper rotary shaft; a lower wing tip and the wing are in shaft driving connection by means of a lower rotary shaft; the upper rotary shaft drives the upper wing tip to deflect; the lower rotary shaft drives the lower wing tip to deflect; by matching with the upper rotary shaft and the lower rotary shaft, the wing is provided with a driving device for controlling the upper rotary shaft and a driving device for controlling the lower rotary shaft. According to the tailless flying wing layout plane with the split type wing tip, under the premises of not damaging the basic appearance of the plane and not adding additional parts, by means of local deflection of the split type wing tip, the course stability of the body of the tailless flying wing layout plane can be effectively increased, and the course operation stability is improved; in case of needing high stealth performance in defense penetration and the like, the plane is quickly converted into a high stealth structure by closing the wing tips.

Description

technical field [0001] The invention relates to the technical field of aircraft structure design, in particular to a tailless flying-wing layout aircraft with split wing tips. Background technique [0002] Tailless flying wing layout aircraft has good stealth performance because it has no vertical tail, but its heading is basically statically unstable. In the case of weapon delivery or failure of the flight control system, the effective control of the aircraft cannot be guaranteed. There is a risk of loss of control of the aircraft. At present, the measures that can effectively increase the directional stability of the flying wing layout body in the prior art are generally to increase the vertical tail or ventral fins. These devices are all fixed and cannot be retracted as needed during flight. The stealth performance is relatively large, and it is not suitable for combat aircraft that require relatively high stealth. [0003] Based on the defects in the above-mentioned pr...

AI Technical Summary

Problems solved by technology

At present, the measures that can effectively increase the directional stability of the flying wing layout body in the prior art are generally to increase the vertical tail or ventral fins. These devices are all fixed and cannot be retracted as needed during flight. The stealth performance has a relatively large impact, and is not suitable for combat aircraft that require relatively high stealth

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