CN211107954U

CN211107954U - Variant stealth aircraft

Info

Publication number: CN211107954U
Application number: CN201920994390.7U
Authority: CN
Inventors: 申镇; 朱清华; 朱奕谛; 李宜恒; 招启军
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2019-06-28
Filing date: 2019-06-28
Publication date: 2020-07-28
Anticipated expiration: 2029-06-28

Abstract

The utility model provides a stealthy aircraft of variant. The airplane is designed according to stealth requirements, adopts a lift body edge strip wing variable configuration pneumatic layout scheme, and comprises two retractable full-motion canard wings and two deflectable full-motion tail wings. The retractable duck wing can be retracted into the airplane body when the airplane cruises or flies at a high speed, so that the radar scattering cross section is reduced, and the stealth performance is improved. The deflectable full-motion tail wing can deflect to different angles under different flight states, thereby being used as a V-shaped tail, a horizontal tail or an abdominal fin. Therefore, the change of the aerodynamic layout of the airplane is realized, and the aerodynamic layout comprises a duck type layout, a tailless type layout and a three-wing-surface type layout. The switching of three kinds of pneumatic layouts can combine the advantages of the three kinds of pneumatic layouts, and the requirements of each flight section and each flight state on the maneuverability and the stealth of the airplane are better met. The variant airplane can be used as a new generation manned and unmanned aerial combat platform with high lift-drag ratio, high maneuverability and good stealth, and is used for executing aerial dominant combat tasks.

Description

Variant stealth aircraft

Technical Field

The utility model relates to a variant stealth aircraft belongs to the aerodynamic and general design direction of aviation technical field aircraft.

Background

The morphing aircraft can change the shape to adapt to different flight environments (regardless of the aircraft which only performs morphing on the ground, such as the aircraft with foldable wings on an aircraft carrier), and the currently existing morphing scheme mainly changes the wing sweepback angles (such as F-111, F-14, B-1, Tu-160 and the like) and is used for considering the flight performance of subsonic speed and supersonic speed. The supersonic passenger plane 114 in former Soviet Union has deflectable canard wings for improving take-off and landing performance, and the canard wing deflection is integrated with the plane body to reduce wave resistance during supersonic flight.

The aerodynamic layout of the aircraft includes a normal layout, a canard layout, a tailless layout (a flying wing layout), and a three-wing layout. The normal layout is common, the aircraft with the tailless layout has good stealth performance, and the aircraft with the canard layout and the three-wing-surface layout has good maneuvering performance.

Stealth fighters are represented by fifth generation fighters F-22 and F-35 in the united states. The device has the capabilities of stealth, supersonic cruise, supersonic maneuvering and the like, adopts normal layout or duck layout, and has no optimal stealth capability and maneuvering capability. At present, no stealth fighter with a three-wing surface layout or a tailless layout exists. For the sixth generation fighter, all countries are exploring, and at present, no unified standard exists.

At present, no mature unmanned fighter exists, and the existing unmanned fighter basically adopts flying wing layout, has better stealth performance, but has poor maneuverability, is mainly used for penetrating and striking ground and water surface targets and the like, and does not have the capacity of striking aerial targets or performing short-distance fighting in the air with manned fighters.

SUMMERY OF THE UTILITY MODEL

To above problem, the utility model provides an adopt variant stealth aircraft of lifting body strake wing morphism pneumatic layout of configuration can regard as a design of next generation fighter, compares in existing fifth generation fighter, and this variant stealth aircraft has better stealth ability and maneuvering ability, various flight environment of adaptation that can be better.

The variant stealth aircraft is designed according to stealth requirements and comprises an aircraft body, an undercarriage, a power device, an airborne device, wings, retractable full-motion canard wings, a deflectable full-motion empennage and the like.

The airplane body is a lifting body, the main wing, the strake wing and the airplane body are designed in a wing body fusion mode, the front edge of the main wing is provided with a motorized flap, the rear edge of the main wing is provided with a flaperon, the strake wing is arranged in front of the main wing, the canard wing is located in front of the strake wing, and the left wing surface and the right wing surface of all movable control surfaces can be in differential motion. The two sides of the machine head are provided with a DSI air inlet and an S-shaped air inlet. The belly and two sides of the fuselage are provided with built-in cartridge chambers. The power device is provided with a vector nozzle.

The transformation of the aerodynamic layout of the airplane is realized through the retractable full-motion canard and the deflectable full-motion tail wing, and comprises canard layout, tailless layout and three-wing-surface layout.

In the takeoff and landing stages of the airplane, canard wings are released, the tail wings are vertical tails or V-shaped tails, the aerodynamic layout form is canard layout, and the canard layout has a high lift coefficient and good course stability.

In the cruising or high-speed flat flight stage, the canard wing is retracted into the aircraft body, the empennage deflects to the horizontal position and is integrated with the main wing to form a tailless (flying wing type) layout, so that the scattering cross section of the radar is reduced, and the stealth capability is improved. The flaperon at this moment also plays the role of rudder lifting.

When a short-distance air combat, missile or aerogun threat avoidance or high maneuvering flight action is carried out, the canard wing is released, the two tail wings deflect to different angles according to maneuvering flight states and pilot operation requirements, and the four forms of vertical tail, V-shaped tail, horizontal tail and ventral fin are switched to form a canard layout or three-wing-surface layout. When switching to a three-wing configuration, direct force may be used for actuation.

The planform of the canard, wing and empennage includes many different forms, as shown in fig. 9, the main geometrical features of the planform are: the front edge sweepback angle of the wing and the rear edge sweepback angle of the wing root part are the same as those of the duck wing and the empennage, and the rear edge sweepback angles of the wing tip part and the empennage tip part are the same as those of the duck wing.

The cross section of the handpiece is approximately diamond and consists of a quadratic curve and a straight line segment, as shown in figure 8. In the figure, curve AB and curve CD are quadratic curves, and BC is a straight-line segment. The curve AB is tangent to the horizontal auxiliary line a at the point A and tangent to the auxiliary line B at the point B, wherein the included acute angle between the auxiliary line B and the horizontal line is equal to the included acute angle between the straight line segment BC and the horizontal line. The curve CD is tangent to the straight line segment BC at point C and to the horizontal auxiliary line D at point D.

The retractable full-motion canard (fig. 10) can control the magnitude of lift and pitching moment by deflecting around the shaft f. The left canard wing and the right canard wing can be differentiated to generate airplane rolling torque. When the duck wing deflects to be in the same plane with the strake wing around the shaft f, the duck wing can rotate backwards around the rotating shaft e, and therefore the duck wing is retracted into the strake wing and the airplane body.

The deflectable full-motion tail (figure 10) can deflect around two mutually perpendicular axes h and g, and when the two tail deflects to different angles around respective rotating shafts h, the two tail can be used as a vertical tail, a V-shaped tail (figure 3), a horizontal tail (figure 6), a ventral fin (figure 5) or integrated with a wing (figure 4), or a combination of the two tail and the wing. The tail wing can be used as an elevator or a rudder when deflecting around the shaft g. The left and right tail wings can be differentiated on two deflection axes.

The deflectable full-dynamic tail wing comprises a tail wing full-dynamic control surface and a tail wing stabilizing surface. Wherein, the stabilizer of the tail wing with smaller area near the root of the tail wing only deflects around the shaft h, and the actuator is positioned on the body. And an actuator is arranged in the tail fin stabilizer and is used for realizing the deflection of the full-motion control surface of the tail fin around the shaft g. A part of the front and rear edges of the root part of the full-dynamic control surface of the empennage is obliquely cut off so as to avoid the interference with the fuselage, the main wing or the power device when the empennage deflects.

The variant stealth aircraft comprises two configurations of manned and unmanned. The pilotless type (figure 7) removes a cockpit and a pilot life support system on the basis of a piloted type, replaces the cockpit and the pilot life support system with an aerogun or a directional energy weapon, is used for short-distance air combat, and simultaneously adds an artificial intelligence system to realize autonomous flight and operation of the pilotless aircraft. Remote control manipulation can also be performed by a person. The aircraft is provided with a distributed aperture system for improving the battlefield situation perception capability of pilots and artificial intelligence systems.

Advantageous effects

The mutual switching of the three pneumatic layouts of the variant stealth aircraft can combine the advantages of the three layouts, and can better meet the requirements on the maneuverability and stealth of the aircraft under each flight section and flight state. The variant airplane can be used as a new generation manned and unmanned aerial combat platform with high lift-drag ratio, high maneuverability and good stealth, and is used for executing aerial dominant combat tasks.

Drawings

Fig. 1 is a perspective view of all control surfaces of a variant stealth aircraft in a deflection state.

Fig. 2 is a perspective view of the variant stealth aircraft with all control surfaces folded.

Fig. 3 is a configuration diagram of the takeoff and landing states of the variant stealth aircraft.

Fig. 4 is a structural diagram of a variant stealth aircraft in cruising and high-speed level flight states.

Fig. 5 is a schematic view of a canard layout during maneuvering flight of the variant stealth aircraft.

Fig. 6 is a schematic diagram of a three-wing layout of a variant stealth aircraft during maneuvering flight.

Fig. 7 is a schematic view of the cruising state of the unmanned variant stealth aircraft.

Fig. 8 is a sectional shape of an aircraft nose.

Fig. 9 is a schematic view of three typical wing and tail planforms of a morphing stealth aircraft.

FIG. 10 is a schematic view of the working principle of the retractable full-motion canard and the deflectable full-motion empennage

In the figure, a lifting body fuselage 1, a retractable full-motion canard wing 2, a cockpit 3, a nose radar 4, an undercarriage 5, a DSI air inlet 6, a strake wing 7, a main wing 8, a flaperon (elevator) 9, a power device 10, a deflectable full-motion empennage stabilizer 11 and a deflectable full-motion empennage rudder 12.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and the following detailed description.

Example 1

The variant stealth aircraft is designed according to stealth requirements and comprises a lifting body fuselage 1, an undercarriage 5, a power device 10, airborne equipment, a main wing 8, a retractable full-motion canard wing 2, a deflectable full-motion empennage and the like,

the airplane comprises a lifting body fuselage 1, a main wing 8, an edge strip wing 7 and the lifting body fuselage 1, wherein the lifting body fuselage 1 is designed by adopting a wing body fusion, a maneuvering flap is installed at the front edge of the main wing 8, a flaperon 9 is installed at the rear edge of the main wing, the edge strip wing 7 is arranged in front of the main wing, a retractable full-motion canard wing 2 is positioned in front of the edge strip wing 7, and the left wing surface and the right wing surface of all movable control surfaces of the airplane can be in differential motion. The two sides of the machine head are provided with a DSI air inlet 6 and an S-shaped air inlet channel. The belly and two sides of the fuselage are provided with built-in cartridge chambers. The power plant 10 has vectoring jets, such as with an adaptive variable cycle thrust vectoring engine or a combined thrust vectoring engine, to accommodate various flight speeds and conditions while enhancing maneuverability at subsonic and supersonic speeds.

The change of the aerodynamic layout of the airplane is realized by the retractable full-motion canard 2 and the deflectable full-motion empennage, including canard layout (figures 3 and 5), tailless layout (figures 4 and 7) and three-wing layout (figure 6).

The planform of the wings and empennage can be in many different forms, as shown in fig. 9, and the main geometrical characteristics of the planform are: the front edge sweepback angle of the wing and the rear edge sweepback angle of the wing root part are the same as those of the duck wing and the empennage, and the rear edge sweepback angles of the wing tip part and the empennage tip part are the same as those of the duck wing.

The section of the aircraft nose is approximately rhombic and consists of a quadratic curve and a straight line segment, as shown in figure 8. In the figure, curve AB and curve CD are quadratic curves, and BC is a straight-line segment. The curve AB is tangent to the horizontal auxiliary line a at the point A and tangent to the auxiliary line B at the point B; wherein the acute angle between the auxiliary line b and the horizontal line is equal to the acute angle between the straight line segment BC and the horizontal line, preferably, the angle is 63 degrees. The curve CD is tangent to the straight line segment BC at point C and to the horizontal auxiliary line D at point D.

The retractable full-motion canard (fig. 10) can control the magnitude of lift and pitching moment by deflecting around the shaft f. The left canard wing and the right canard wing can be differentiated to generate airplane rolling torque. When the duck wing deflects to be in the same plane with the strake wing around the shaft f, the duck wing can rotate backwards around the rotating shaft e, and therefore the duck wing is retracted into the strake wing and the airplane body. Wherein the axis e is vertical to the plane of the canard, and the plane of the axis f is vertical to the axis e.

The deflectable full-motion tail (fig. 10) is capable of deflecting about two mutually perpendicular axes h and g, where the h-axis is parallel to the plane of bilateral symmetry of the aircraft and the g-axis lies in a plane perpendicular to the h-axis. The two tail wings can be used as vertical tails, V-shaped tails, horizontal tails, ventral fins or a combination thereof when deflected to different angles around the respective rotating shafts h. The tail wing can be used as an elevator or a rudder when deflecting around the shaft g. The left and right tail wings can be differentiated on two deflection axes.

The deflectable full-dynamic tail wing comprises a deflectable full-dynamic tail wing full-dynamic control surface 12 and a deflectable full-dynamic tail wing stabilizer surface 11. Wherein the deflectable full-dynamic empennage stabilizer 11 with smaller area close to the empennage root deflects only around the shaft h, and the actuator thereof is positioned on the machine body. An actuator is arranged in the deflectable full-motion tail fin stabilizer 11 and used for realizing the deflection of the deflectable full-motion tail fin full-motion control surface 12 around the shaft g. The front and rear edge positions of the root part of the deflectable full-dynamic tail wing full-dynamic control surface 12 are obliquely cut off (two angles on the lower bottom edge of the trapezoid are cut off by the trapezoid deflectable full-dynamic tail wing full-dynamic control surface 12 of the tail wing in fig. 10), so that the deflectable full-dynamic tail wing full-dynamic control surface can be prevented from interfering with the lifting body 1, the main wing 8 or the power device 10.

Example 2

To above-mentioned stealthy aircraft of variant, the utility model discloses still provide its variant mode in order to accomplish its flight task.

In the takeoff and landing stages of the airplane, canard wings are released, the tail wings are vertical tails or V-shaped tails, the aerodynamic layout form is canard layout (figure 3), and the canard wing aerodynamic layout has a high lift coefficient and good course stability.

In the cruising or high-speed flat flight stage, the canard wing is retracted into the airplane body, the empennage deflects to the horizontal position and is integrated with the main wing to form a tailless (flying wing type) layout (figures 4 and 7), so that the scattering cross section of the radar is reduced, and the stealth capability is improved. The flaperon at this moment also plays the role of rudder lifting. The engine vector nozzle is used as an auxiliary control surface and participates in balancing.

When the high maneuvering flight action is carried out by close-distance air combat, missile or cannon threat avoidance, the canard wing is released, the two tail wings deflect to different angles according to maneuvering flight states and pilot operation requirements, and the four forms of vertical tail, V-shaped tail (figure 3), horizontal tail (figure 6) and ventral fin (figure 5) are switched to form a canard layout (figures 3 and 5) or a three-wing layout (figure 6). When the three-wing-surface layout is switched, direct force can be used for operation. When the empennage is a movable ventral fin, the flight performance of the airplane with a large attack angle can be improved, and the control efficiency of the control surface of the empennage is improved (figure 5).

Example 3

On the basis of the utility model, if adopt increase wing and canard area, fuselage afterbody to install arresting hook additional relevant measure, this aircraft also can be used as aircraft carrier.

The utility model provides a technical feature and appearance layout feature except can being applied to next generation advanced land-based/carrier-borne fighter, still can be applied to bomber, land-based/carrier-borne unmanned (fighter) plane, unmanned target plane, hypersonic aircraft or aeromodelling etc.. The pneumatic layout of the edge wing configuration of the wave rider formed by changing the lifting body into the wave rider can be applied to hypersonic aircrafts.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications can be made without departing from the principles of the present invention, and these modifications should also be regarded as the protection scope of the present invention.

Claims

1. A morphing stealth aircraft, characterized by: the stealth aircraft adopts a lifting body strake wing deformation type pneumatic layout and comprises an aircraft body, an undercarriage, a power device, airborne equipment, a strake wing, a main wing, a retractable full-motion canard wing and a deflectable full-motion tail wing; the landing gear is positioned at the lower part of the fuselage, and the two sides of the fuselage are sequentially provided with a duck wing, an edge wing, a main wing and a tail wing which are symmetrically arranged from front to back; the aircraft body is in a lifting body configuration, the main wing, the strake wing and the aircraft body are designed in a wing body fusion mode, the front edge of the main wing is provided with a motorized flap, the rear edge of the main wing is provided with a flaperon, the strake wing is arranged in front of the main wing, and the canard wing is positioned in front of the strake wing; the left wing surface and the right wing surface of all the movable control surfaces can be in differential motion; DSI air inlets are formed in two sides of the head of the machine body, the air inlet channel is S-shaped, and the power device is provided with a vector nozzle; the belly and two sides of the machine body are provided with built-in cartridge chambers.

2. The variant stealth aircraft of claim 1, wherein: the change of the aerodynamic layout of the plane is realized through the retractable full-motion canard and the deflectable full-motion tail wing, and the aerodynamic layout of the stealth plane can be changed into canard layout, tailless layout and three-wing-surface layout.

3. The variant stealth aircraft of claim 2, wherein: the main wing is a swept-back wing with a small aspect ratio; the planar shapes of the canard wing, the main wing and the empennage comprise various different forms, and the geometric characteristics of the planar shapes are as follows: the front edge sweepback angle of the main wing and the rear edge sweepback angle of the wing root part of the main wing are the same as those of the duck wing and the empennage, and the rear edge sweepback angles of the wing tip part of the main wing and the tail tip part of the empennage are the same as those of the duck wing.

4. The variant stealth aircraft of claim 1, wherein: the cross section of the head of the machine body is an axisymmetric figure which is approximately rhombic and consists of a quadratic curve and a straight line segment; the first quadratic curve, the straight line segment and the second quadratic curve which are connected end to end are arranged on one side of the symmetry axis from top to bottom; one end of the first quadratic curve is tangent to the horizontal line on the symmetry axis, and the included acute angle between the tangent line of the other end and the horizontal line is equal to the included acute angle between the straight line segment and the horizontal line; one end of the second quadratic curve is tangent to the straight line segment, and the other end of the second quadratic curve is tangent to the horizontal line on the symmetry axis.

5. The variant stealth aircraft of claim 2, wherein: the retractable full-motion canard controls the magnitude of lift force and pitching moment by deflecting around a first axis f, and the left canard and the right canard generate airplane rolling moment by differential motion; when the wing deflects to be in the same plane with the strake wing around the first axis f, the wing rotates backwards around a second axis e vertical to the plane of the wing, and then the wing is retracted into the strake wing and the airplane body;

the left and right duck wings are arranged in a left-right symmetrical mode.

6. The variant stealth aircraft of claim 2, wherein: the deflectable full-motion empennage deflects around two mutually vertical axes h and g, and the two empennages are used as a vertical tail, a V-shaped tail, a horizontal tail and a ventral fin or are integrated with a wing when deflecting to different angles around an axis h parallel to the left and right symmetrical planes of the airplane, or the combination of the two empennages and the wing; when the tail wings deflect around an axis g vertical to the axis h, the tail wings are elevators or rudders, and the left tail wing and the right tail wing can be in differential motion on two deflection axes;

the left and right empennages are symmetrically arranged.

7. The variant stealth aircraft of claim 2, wherein: the deflectable full-motion tail comprises two parts: the tail wing full-moving control surface and the tail wing stabilizing surface; the stabilizer of the tail wing with smaller area close to the wing root of the tail wing only deflects around an axis h parallel to the left-right symmetrical plane of the airplane, and an actuator of the stabilizer is positioned on the fuselage; an actuator is arranged in the empennage stabilizer and used for realizing the deflection of the full-dynamic control surface of the empennage; and a part of the front and rear edge positions of the root part of the full-dynamic control surface of the empennage is obliquely cut off.