CN211223836U

CN211223836U - Tailstock type supersonic speed unmanned aerial vehicle capable of taking off and landing vertically

Info

Publication number: CN211223836U
Application number: CN201921808934.2U
Authority: CN
Inventors: 赵超; 杨兆
Original assignee: Xian Flight Automatic Control Research Institute of AVIC
Current assignee: Xian Flight Automatic Control Research Institute of AVIC
Priority date: 2019-10-25
Filing date: 2019-10-25
Publication date: 2020-08-11
Anticipated expiration: 2029-10-25

Abstract

The utility model belongs to aircraft design technique, concretely relates to tailstock formula supersonic speed unmanned vehicles that can take off and land perpendicularly. The utility model discloses but tailstock formula supersonic speed unmanned vehicles of VTOL, this aircraft include fuselage, wing, engine and vertical fin, the wing includes inner wing and outer wing, and the engine is installed between inner wing and outer wing, and inner wing leading edge has the vortex flap, and the trailing edge has the flap, has the leading edge slat at the outer wing leading edge, and the trailing edge has the aileron, the vertical fin has the rudder; the engine adopts a thrust vector engine, and a retractable supporting rod for assisting vertical lifting is arranged at the lower end of the abdomen; and in different flight stages, the attitude of the aircraft is controlled by the thrust provided by the engine, the angle adjustment of each control surface and the matching of the vectoring nozzle. Relative tilting power's VTOL unmanned aerial vehicle is simpler, and security and reliability are higher, simultaneously, can realize the task demand of the big load transportation of this type of aircraft.

Description

Tailstock type supersonic speed unmanned aerial vehicle capable of taking off and landing vertically

Technical Field

The utility model belongs to aircraft design technique, concretely relates to tailstock formula supersonic speed unmanned vehicles that can take off and land perpendicularly.

Background

At present, aiming at a non-aircraft carrier platform, aircrafts equipped by navy comprise a manned/unmanned helicopter and a small reconnaissance unmanned aerial vehicle, and the purpose is to help the non-aircraft carrier platform to acquire sea surface information and acquire sea making right. With the development of science and technology, the premise that a non-aircraft carrier platform can acquire the sea making right is to acquire the air making right, and the existing equipment strength is obviously insufficient to capture the air making right in a strong confrontation environment. Certainly, in a combined operation mode under a multi-dimensional complex environment of land, sea, air, sky, electricity, magnetism and light in the future, an aircraft carrier still serves as a main carrying and delivering platform for marine striking force, is an important force for marine combined striking, capturing and controlling the air right and the sea right, and has irreplaceable effects in marine combined operation. Navy air force is the "fleet core" of aircraft carrier combat groups.

However, the carrier-based fighter plane of the current naval aircraft carrier platform equipment faces the following two important problems: 1, the cost of human is high, and casualties are avoided as much as possible in the fight. 2 for the carrier-based aircraft which runs and takes off and lands, taking off and landing on an aircraft carrier are also quite difficult. The supersonic unmanned aerial vehicle capable of taking off and landing vertically can be developed to serve as a novel carrier-based platform aircraft, and has the following advantages: the method comprises the following steps that 1, a plurality of driving protective ships, amphibious ships and the like are provided with novel carrier-based unmanned aerial vehicles, each naval vessel is built into a small aircraft carrier, and the sea control right and the air control right are obtained through self capacity. The unmanned aerial vehicle is used as loyalty guard for ship formation. 2 because of its high speed, high maneuvering ability, can match the performance of the aircraft carrier fighter plane, so can carry on the manned/unmanned cooperative strike to the area of battle, can already raise the efficiency of battle on the battle field and can guarantee the security of the man-machine to a certain extent, regard it as the "loyalty fighter" of the man-machine.

SUMMERY OF THE UTILITY MODEL

The utility model discloses the technical problem that will solve is: the tailstock type supersonic unmanned aerial vehicle capable of taking off and landing vertically is designed, can take off and land vertically, has certain maneuverability, has various flight control instructions and various key flight task modes, and can provide a scaling verification platform for related control technologies generated by research of the supersonic unmanned aerial vehicle with thrust vectors.

The technical scheme of the utility model is that: a VTOL tailstock type supersonic unmanned aerial vehicle comprises a fuselage, a wing, an engine and a vertical tail, wherein the wing comprises an inner wing and an outer wing, the engine is installed between the inner wing and the outer wing, a vortex flap is arranged at the leading edge of the inner wing, a flap is arranged at the trailing edge, a leading edge slat is arranged at the leading edge of the outer wing, an aileron is arranged at the trailing edge, and the vertical tail is provided with a rudder; the engine adopts a thrust vector engine, and a retractable supporting rod for assisting vertical lifting is arranged at the lower end of the abdomen; and in different flight stages, the attitude of the aircraft is controlled by the thrust provided by the engine, the angle adjustment of each control surface and the matching of the vectoring nozzle.

Furthermore, the fusion design is adopted between the fuselage and the inner wing, between the inner wing and the engine, and between the engine and the outer wing.

Furthermore, the machine body is streamline, the head of the machine body is a photoelectric camera cabin, and a semitransparent design is adopted.

Furthermore, the wing is a double-sweepback sharp-cutting triangular wing, the sweepback angle of the inner wing is 70 degrees, the sweepback angle of the outer wing is 40 degrees, and the engine is installed in the middle of the single-side wing.

Further, the engine has a thrust vectoring nozzle.

Furthermore, the vertical tail is positioned at the upper part of the engine and adopts a V-shaped double tail.

Further, during the vertical take-off and landing stage, the attitude of the aircraft is controlled through the thrust provided by the engine and the thrust vectoring nozzle.

Further, during the transition phase, when the body reaches a certain speed and generates effective aerodynamic force, the attitude of the aircraft is controlled through each control surface, the thrust provided by the engine and the thrust vectoring nozzle.

Further, during the forward flight phase, the attitude of the aircraft is controlled by the control surfaces, the thrust provided by the engine and the thrust vectoring nozzle.

The utility model has the advantages that: the utility model relates to a tailstock formula supersonic speed unmanned vehicles that can take off and land perpendicularly. The design of this aircraft changes the mode design of traditional supersonic speed aircraft completely for engine thrust is at the vertical direction at the landing stage of taking off, and engine thrust flies the direction in the front at the stage of cruising, does not have thrust conversion structure, only relies on flight control system to carry out the change of flight gesture, so as to reach and get into the cruise mode that level flies from the VTOL mode, and the VTOL unmanned aerial vehicle of power that verts relatively of structure is simpler, and security and reliability are higher, simultaneously, can realize the task demand of this type of aircraft heavy load transportation.

Drawings

FIG. 1 is a schematic view of a vertical take-off and landing tailstock type unmanned aerial vehicle;

FIG. 2 is a schematic diagram of a vertical take-off and landing tailstock type unmanned aerial vehicle in a vertical take-off and landing stage;

fig. 3 is a schematic top view of the tailstock type unmanned aerial vehicle capable of vertical take-off and landing in the front flight stage.

Wherein, 1-fuselage, 2-inner wing, 3-engine, 4-vertical tail, 5-outer wing

Detailed Description

Referring to fig. 1, the tail-stock type unmanned aerial vehicle capable of taking off and landing vertically of the present invention includes four parts, namely, a body 1, wings, an engine 3 and a vertical tail 4, wherein the wings include an inner wing 2 and an outer wing 5.

The unmanned aerial vehicle adopts a pneumatic layout of double sweepback middle single wings, the power adopts an engine 3 with a thrust vector, and fusion designs are adopted between a fuselage 1 and an inner wing 2, between the inner wing 2 and the engine 3 and between the engine 3 and an outer wing 5.

The length-to-slenderness ratio of the machine body 1 is 13; the head edge strip wing is designed in 0.3d or shark head, so that large-attack-angle asymmetric nose vortex is improved, and the occurrence of lateral force is inhibited; the front machine body: the slenderness ratio: ln/d: parabolic-like shape, profile: R/R is (x/ln)0.75, R is the radius of the bottom of the nose is 220mm, and the length of the ln nose is 0.8 m; a rear body; conical contraction; the middle part is used for arranging an oil tank, a flight control system, a power supply, an electric system and the like.

The wing is a double-sweepback tip-cutting delta wing, a supersonic airfoil is adopted as the wing airfoil, the sweepback angle of the inner wing 2 is 70 degrees, the sweepback angle of the outer wing 5 is 40 degrees, the turning point of the double sweepback is 0.562b, the installation angle is 2 degrees, the dihedral angle is 0 degree, the torsion angle is 4 degrees, and the tip-root ratio is 0.375; the leading edge of the inner wing 2 is provided with a vortex flap, and the trailing edge is provided with a flap; the leading edge of the outer wing 5 is provided with a leading edge slat, and the trailing edge is provided with a flap; at 0.5b2 of the two side wings, the engine 3 is installed; the wing part structure is designed by adopting a double-beam type, reinforcing ribs are designed on the wing root and the wing tip, rib plates are uniformly distributed on the rest part, and the skin is made of carbon fiber glass rods and is integrally formed.

The engine 3 is double-engine and symmetrical about the symmetry plane of the unmanned aerial vehicle, a streamline design is adopted, and a thrust vectoring nozzle is designed at the tail part of the engine; the lower end of the abdomen is provided with a retractable supporting rod for assisting in taking off and landing.

The vertical tail 4 is positioned on the engine, is provided with a V-shaped double tail, is symmetrical about the symmetry plane of the unmanned aerial vehicle, and has a swept-back angle of 1/4 chord lines of 48 degrees, l_vB is 0.6, the ratio of the cusps is 0.42; camber angle 20 deg., and trailing edge rudder.

And (3) a vertical take-off and landing stage: the two turbojet engines provide airplane lift force, and attitude control is carried out through engine thrust asymmetry and a thrust vectoring nozzle designed at the rear part of the engine.

A transition stage: when the engine body reaches a certain speed and generates effective aerodynamic force, the rudder, the flap and the aileron at the trailing edge of the outer wing are connected, and the system stability is maintained together with the direct force control and the thrust vector control of the engine.

A front flying stage: the course is controlled by a rudder, the direct force of an engine and a thrust vector, the rolling attitude is controlled by an aileron and the thrust vector, the body attitude is regulated by a self-balancing system, and the lifting motion is controlled by the aileron and the thrust vector.

Claims

1. The utility model provides a tailstock formula supersonic speed unmanned vehicles that can take off and land perpendicularly which characterized in that: the aircraft comprises a fuselage (1), a wing, an engine (3) and a vertical tail (4), wherein the wing comprises an inner wing (2) and an outer wing (5), the engine (3) is installed between the inner wing (2) and the outer wing (5), a vortex flap is arranged at the leading edge of the inner wing (2), a flap is arranged at the trailing edge of the inner wing, a slat is arranged at the leading edge of the outer wing (5), an aileron is arranged at the trailing edge of the outer wing, and the vertical tail (4) is provided with a rudder; the engine (3) adopts a thrust vector engine, and a retractable supporting rod for assisting vertical lifting is arranged at the lower end of the abdomen; and in different flight stages, the attitude of the aircraft is controlled by the thrust provided by the engine (3), the angle adjustment of each control surface and the matching of the vectoring nozzle.

2. The tailstock-type supersonic unmanned aerial vehicle according to claim 1, wherein: the fusion design is adopted between the fuselage (1) and the inner wing (2), between the inner wing (2) and the engine (3), and between the engine (3) and the outer wing (5).

3. The tailstock-type supersonic unmanned aerial vehicle according to claim 1, wherein: the machine body (1) is streamline, the head of the machine body is a photoelectric camera cabin, and a semitransparent design is adopted.

4. The tailstock-type supersonic unmanned aerial vehicle according to claim 1, wherein: the wing is a double-sweepback sharp-cutting triangular wing, the sweepback angle of the inner wing (2) is 70 degrees, the sweepback angle of the outer wing (5) is 40 degrees, and the engine (3) is installed in the middle of the single-side wing.

5. The tailstock-type supersonic unmanned aerial vehicle according to claim 1, wherein: the engine (3) has a thrust vectoring nozzle.

6. The tailstock-type supersonic unmanned aerial vehicle according to claim 1, wherein: the vertical tail (4) is positioned at the upper part of the engine and adopts V-shaped double tails.

7. The tailstock-type supersonic unmanned aerial vehicle according to claim 1, wherein: and during the vertical take-off and landing stage, the attitude of the aircraft is controlled by the thrust provided by the engine and the thrust vectoring nozzle.

8. The tailstock-type supersonic unmanned aerial vehicle according to claim 1, wherein: during the transition phase, when the body reaches a certain speed and generates effective aerodynamic force, the attitude of the aircraft is controlled through each control surface, the thrust provided by the engine and the thrust vectoring nozzle.

9. The tailstock-type supersonic unmanned aerial vehicle according to claim 1, wherein: during the forward flight phase, the attitude of the aircraft is controlled by the control surfaces, the thrust provided by the engine and the thrust vectoring nozzle.