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Variant stealth aircraft and variant method and application thereof

A kind of aircraft and variant technology, applied in aircraft parts, aircraft control, aircraft stability, etc., can solve the problems of lack of unity, poor maneuverability, and inability to strike air targets, etc., and achieve the effect of high lift coefficient and good course stability

Pending Publication Date: 2019-09-06
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There is currently no stealth fighter with a three-wing layout or a tailless layout
As for the sixth-generation fighter jets, all countries are exploring, and there is currently no unified standard
[0005] At present, there is no mature unmanned combat aircraft, and the existing unmanned combat aircraft basically adopt the flying wing layout, which has good stealth, but its maneuverability is poor, and it is mainly used to penetrate and attack ground and water targets. does not have the ability to engage air targets or engage in close-quarters air combat with manned fighter jets

Method used

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  • Variant stealth aircraft and variant method and application thereof
  • Variant stealth aircraft and variant method and application thereof
  • Variant stealth aircraft and variant method and application thereof

Examples

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Comparison scheme
Effect test

Embodiment 1

[0034] This variant stealth aircraft is integrally designed by the stealth requirement, by fuselage 1, landing gear 5, power unit 10, airborne equipment, main wing 8, retractable full-motion canard 2, deflectable full-motion empennage (11 and 12) and so on,

[0035] Wherein the fuselage 1 is a lifting body, the main wing 8 and the side strip wing 7 and the fuselage 1 adopt the wing-body fusion design, the leading edge of the main wing 8 is equipped with a motorized flap, the trailing edge is equipped with a flaperon 9, and the front edge of the main wing has a Side strip wing 7, canard 2 is positioned at side strip wing 7 front parts, and the left and right wing surfaces of all movable rudder surfaces of aircraft can be differentially moved. On both sides of the nose are DSI inlets 6 and S-shaped inlets. The belly and sides of the fuselage have built-in bomb bays. The power plant 10 has a vector nozzle, such as an adaptive variable cycle thrust vectoring engine or a combined...

Embodiment 2

[0044] For the above-mentioned variant stealth aircraft, the present invention also provides its variant mode to complete its flight mission.

[0045] During the takeoff and landing stages of the aircraft, the canard wings are released, the tail is a vertical tail or a V tail, and the aerodynamic layout is a canard layout ( image 3 ), with a higher lift coefficient and better directional stability.

[0046] During cruising or high-speed level flight, the canard retracts into the fuselage, the tail deflects to a horizontal position, and integrates with the main wing to form a tailless (flying wing) layout ( Figure 4 and Figure 7 ), thereby reducing the radar cross section and improving the stealth capability. The flaperon at this time also acts as an elevator. The engine vector nozzle serves as an auxiliary control surface and participates in trimming.

[0047] When performing high-maneuvering flight actions in close-range air combat, avoiding the threat of missiles or a...

Embodiment 3

[0049] On the basis of the present invention, such as adopting relevant measures such as increasing the area of ​​the wings and canards, and installing arresting hooks at the rear of the fuselage, the aircraft can also be used as an aircraft carrier-based aircraft.

[0050] The technical features and appearance layout features in the present invention can not only be applied to the next generation of advanced land-based / ship-based fighters, but also can be applied to bombers, land-based / ship-borne unmanned (combat) aircraft, unmanned target aircraft, hypersonic Aircraft or aircraft models, etc. For example, the aerodynamic layout of the variable configuration of the wing of the waverider formed by changing the lifting body to a waverider can be applied to hypersonic aircraft.

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Abstract

The invention provides a variant stealth aircraft and a variant method and application thereof. According to stealth requirements, the aircraft is designed by adopting a force-lifting body edge-wing variable-configuration pneumatic layout scheme, and comprises two retractable full-motion canards and two deflectable full-motion empennages. The retractable full-motion canards can be retracted into amachine body during cruising of an aircraft or flying at a high speed, so that the scattering cross section of a radar is reduced, thus improving the invisibility. The deflectable full-motion empennages can be deflected to different angles in different flight states so as to serve as V-shaped tails, flat tails or ventral fins. Thus, transformation of the pneumatic layout of the aircraft is achieved, and the layout comprises a canard-type layout, a tail-free layout and a three-wing-surface layout. Through the switching of the three pneumatic layouts, the advantages of the three pneumatic layouts can be combined, thus better satisfying the requirements for the maneuverability and invisibility of the aircraft under different flight profiles and flight states. As a new-generation manned and unmanned aerial combat platform with high lift-drag ratio, high maneuverability and good invisibility, the variant stealth aircraft can be used for executing air dominant combat tasks.

Description

technical field [0001] The invention is a variant stealth aircraft and its variant method and application, belonging to the direction of aircraft aerodynamics and overall design in the field of aviation technology. Background technique [0002] Variant aircraft can change its shape to adapt to different flight environments (not considering aircraft that only morph on the ground, such as aircraft with foldable wings on an aircraft carrier), and the existing variants are mainly variable wing sweep Angles (such as F-111, F-14, B-1, Tu-160, etc.), used to take into account both subsonic and supersonic flight performance. The Tu-114 supersonic airliner of the former Soviet Union has deflectable canards to improve take-off and landing performance. When flying at supersonic speeds, the canard deflections are integrated with the fuselage to reduce wave resistance. [0003] The aerodynamic layout of the aircraft includes a normal layout, a canard layout, a tailless layout (flying wi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C5/00B64C5/10B64C39/02B64D7/00
CPCB64C5/00B64C5/10B64C39/02B64D7/00
Inventor 申镇朱清华朱奕谛李宜恒招启军
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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