阅读说明：本技术 一种超音速隐身靶机 (Supersonic stealth target drone ) 是由 王超 黄国江 张桂彬 王斌 于 2020-12-10 设计创作，主要内容包括：本发明提供一种超音速隐身靶机,包括机身、尾翼、机翼、进气道和数据链天线,所述机身的两侧对称安装有机翼,所述机身的底部的一端设置有进气道,所述进气道的底部的一端固定安装有数据链天线,该发明超音速隐身靶机专门针对超音速(Ma1.4)、隐身(RCS≤0.01m～2)的飞行特点进行优化设计,依据国产加力型涡喷发动机几何尺寸,性能特点,根据气动布局的升阻特性、稳定特性、操纵特性和发动机的推力特性、进气道特性以及布局的隐身特性进行计算,满足超音速隐身要求,同时具有结构简洁容易制造的优点。(The invention provides a supersonic stealth target drone, which comprises a drone body, an empennage, wings, air inlet channels and a data chain antenna, wherein the wings are symmetrically arranged on two sides of the drone body, the air inlet channels are arranged at one end of the bottom of the drone body, and the data chain antenna is fixedly arranged at one end of the bottom of the air inlet channels 2 ) The flight characteristics of the jet engine are optimally designed, calculation is carried out according to the geometric dimension and the performance characteristics of the domestic stress-applying turbojet engine, the lift-drag characteristic, the stability characteristic and the manipulation characteristic of the pneumatic layout, the thrust characteristic and the air inlet characteristic of the engine and the stealth characteristic of the layout, the supersonic stealth requirement is met, and meanwhile, the jet engine has the advantages of simple structure and easiness in manufacturing.)

1. The utility model provides a stealthy target drone of supersonic speed, includes fuselage (1), fin (2), wing (3), intake duct (4) and data link antenna (5), its characterized in that, fuselage (1) divide into the three-section along length direction, wing (3) are installed to the bilateral symmetry of fuselage (1), wing (3) are sweepback fusion wing, fin (2) evenly set up the one end in fuselage (1), fin (2) become 90 contained angles, 4 with the axis of fuselage (1) fin (2) combination forms "X" type fin, the one end of the bottom of fuselage (1) is provided with intake duct (4), the one end fixed mounting of the bottom of intake duct (4) has data link antenna (5).

2. The supersonic stealth target drone of claim 1, wherein: the forepart of fuselage (1) is the conical body, the middle section of fuselage (1) is the biarc cross-section, the outside that the fuselage breaks is provided with the edge that rises, the rear end of fuselage (1) is the conical surface of class circular cross-section.

3. The supersonic stealth target drone of claim 1, wherein: 4 the specifications of the empennage (2) are the same, and the shape of the empennage (2) is a thin airfoil profile and a symmetrical airfoil profile with a small aspect ratio.

4. The supersonic stealth target drone of claim 1, wherein: the air inlet channel (4) is an S-shaped air inlet channel.

5. The supersonic stealth target drone of claim 1, wherein: the data chain antenna (5) is a fin-shaped omnidirectional antenna.

6. The supersonic stealth target drone of claim 1, wherein: the airfoil profile of the wing (3) is a supercritical airfoil profile.

7. The supersonic stealth target drone of claim 1, wherein: the machine body (1) is additionally provided with a recovery umbrella and an air bag.

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a supersonic stealth target drone.

Background

The supersonic target drone is a simulated target for testing and identifying an air defense weapon system and training troops. In order to deal with the threat of increasingly large high-speed targets and improve the combat efficiency of air defense weapons, all countries pay great attention to the development of supersonic target drone. The project is based on the future battlefield operation environment and tactical requirements, and the development of the supersonic speed target drone is developed according to the practical requirements of the current army training and weapon shaping. The supersonic target drone is mainly used for simulating the target characteristics of enemy high-speed operational airplanes and cruise missiles and providing a vivid high-speed moving aerial shooting target for the aerial weapon ball shooting training, thereby training and examining the information processing, supporting and cooperative hitting capability of an aerial weapon system.

Therefore, the invention provides the supersonic stealth target drone.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide the supersonic stealth target drone to solve the problems in the background technology.

In order to achieve the purpose, the invention is realized by the following technical scheme: the utility model provides a stealthy target drone of supersonic speed, includes fuselage, fin, wing, intake duct and data link antenna, the fuselage divide into the three-section along length direction, the wing is installed to the bilateral symmetry of fuselage, the one end of the bottom of fuselage is provided with the intake duct, the one end fixed mounting of the bottom of intake duct has the data link antenna.

As a preferred embodiment of the present invention, the front section of the fuselage is a conical body, the middle section of the fuselage is a double-arc cross section, the outer side of the interruption of the fuselage is provided with a high lift edge, and the rear end of the fuselage is a conical surface with a similar circular cross section.

As a preferred embodiment of the invention, the tail wings and the axis of the fuselage form an included angle of 90 degrees, the tail wings are uniformly arranged at one end of the fuselage, the specifications of 4 tail wings are the same, the shape of the tail wings is thin wing type and symmetrical wing type with small aspect ratio, and the 4 tail wings are combined to form an X-shaped tail wing.

As a preferable embodiment of the present invention, the air intake duct is an S-shaped air intake duct.

As a preferred embodiment of the present invention, the data chain antenna is a fin-shaped omnidirectional antenna.

In a preferred embodiment of the present invention, the wing is a swept-back fusion wing, and the airfoil profile of the wing is a supercritical airfoil profile.

In a preferred embodiment of the present invention, the body is provided with a recovery umbrella and an airbag.

The invention has the beneficial effects that: the invention discloses a supersonic stealth target drone which comprises a drone body, an empennage, wings, an air inlet channel and a data link antenna.

The supersonic stealth target drone is specially used for supersonic speed (Ma1.4) and stealth (RCS is less than or equal to 0.01 m)²) The flight characteristics of the unmanned aerial vehicle are optimally designed, calculation is carried out according to the geometric dimension and performance characteristics of a domestic boost turbojet engine, the lift resistance characteristic, the stability characteristic and the manipulation characteristic of the pneumatic layout, the thrust characteristic and the air inlet channel characteristic of the engine and the stealth characteristic of the layout, the design of a streamline fuselage, sweepback wings and a full-motion tail wing is adopted, the unmanned aerial vehicle can have small resistance under the supersonic speed condition, the boost turbojet engine is equipped to meet the requirement of supersonic speed stealth, and meanwhile, the boost turbojet engine has the advantages of being simple in structure and easy to manufacture.

Drawings

FIG. 1 is a schematic diagram of a supersonic stealth target of the present invention;

FIG. 2 is a side view of a supersonic stealth target of the present invention;

FIG. 3 is a bottom view of a supersonic stealth target of the present invention;

FIG. 4 is a top view of a supersonic stealth target of the present invention;

in the figure: 1. a body; 2. a tail wing; 3. an airfoil; 4. an air inlet channel; 5. a data chain antenna.

Detailed Description

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.

Referring to fig. 1 to 4, the present invention provides a technical solution: the utility model provides a stealthy target drone of supersonic speed, includes fuselage 1, fin 2, wing 3, intake duct 4 and data chain antenna 5, fuselage 1 divide into the three-section along length direction, wing 3 is installed to the bilateral symmetry of fuselage 1, the one end of the bottom of fuselage 1 is provided with intake duct 4, the one end fixed mounting of the bottom of intake duct 4 has data chain antenna 5, can alleviate this target drone aircraft resistance, realizes stealthy flight of supersonic speed.

As a preferred embodiment of the present invention, the front section of the fuselage 1 is a conical body, the middle section of the fuselage 1 is a double-arc cross section, the outer side of the interruption of the fuselage is provided with a high lift edge, and the rear end of the fuselage 1 is a conical surface with a similar-circular cross section, so that the air resistance on the fuselage is reduced, and the supersonic flight adaptability is improved.

As a preferred embodiment of the invention, the tail wings 2 form an included angle of 90 degrees with the axis of the machine body 1, the tail wings 2 are uniformly arranged at one end of the machine body 1, the specifications of 4 tail wings 2 are the same, the tail wings 2 are in the shape of thin wing type and symmetrical wing type with small aspect ratio, the 4 tail wings 2 are combined to form an 'X' -shaped tail wing, and the reflection of the target drone to radar waves is reduced by improving the tail wings 2. By optimizing the mounting position of the tail wing, the control characteristic of the whole drone is improved, and the characteristics of flexible control and lowest rudder efficiency of the drone are realized.

As a preferred embodiment of the present invention, the air inlet 4 is an S-shaped air inlet, the air inlet 4 isolates a boundary layer of an incoming flow from a free incoming flow, and the free incoming flow enters the air inlet 4 and enters the inside of the engine. The improved air passage is specially designed for high subsonic speed and supersonic speed, and meets the requirements of the inlet distortion index and total pressure recovery characteristic of the engine.

As a preferred embodiment of the present invention, the data link antenna 5 is a fin-shaped omnidirectional antenna, and the antenna is installed right below the target drone, so that pneumatic interference is small, and data transmission is facilitated.

As a preferred embodiment of the present invention, the wing 3 is a swept-back fusion wing, the wing profile of the wing 3 is a supercritical wing profile, the thickness and the bending torque of the wing 3 are optimized, the lift characteristic of the target drone aircraft is increased, the resistance of the target drone aircraft is reduced, the stability and the optimization of the whole aircraft are realized, and the supersonic flight is realized.

As a preferred embodiment of the invention, the machine body 1 is additionally provided with a recovery umbrella and an air bag, and a stable recovery speed and landing buffer are realized by optimizing the area of the umbrella, the installation position of an umbrella hanging point, the size of the air bag and the installation position, so that the target drone is recovered.

When the supersonic stealth target drone is used, the launching of radar waves by the target drone and the air inlet 4 can be reduced through the sweepback type wing 3, the full-motion tail wing 2 and the air inlet 4 when the target drone flies, the stealth purpose of the target drone is realized, the resistance of the target drone under the supersonic speed condition can be reduced through the streamline fuselage 1, the sweepback type wing 3 and the tail wing 2, and the supersonic flying is realized through the boost type turbojet engine, and the supersonic stealth target drone is specially used for supersonic speeds (Ma1.4) and stealths (RCS is less than or equal to 0.01 m)²) The flight characteristics of the jet engine are optimally designed, calculation is carried out according to the geometric dimension and the performance characteristics of the domestic stress-applying turbojet engine, the lift-drag characteristic, the stability characteristic and the manipulation characteristic of the pneumatic layout, the thrust characteristic and the air inlet characteristic of the engine and the stealth characteristic of the layout, the supersonic stealth requirement is met, and meanwhile, the jet engine has the advantages of simple structure and easiness in manufacturing.

While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.