阅读说明：本技术 一种涡喷高速靶机 (Vortex-spraying high-speed target drone ) 是由 李涛 张广 刘睿 赵刚 张旭 陈李萍 李立 孙楠 刘鑫 石佳慧 于 2021-08-20 设计创作，主要内容包括：本发明公开了一种涡喷高速靶机,机身的尾部设有舵机,舵机设置在机身尾部上的舵机安装槽中,舵机的输出轴上连接有舵机摇臂,舵机摇臂上连接有尾翼控制摇臂；V型尾翼的底部镶嵌有的尾翼铝杆,V型尾翼的升降舵的底部设有尾翼控制摇臂插口；尾翼铝杆插进机身上的圆孔内并用紧固件固定,尾翼控制摇臂插进所述尾翼控制摇臂插口内,舵机驱动舵机摇臂并带动尾翼控制摇臂转动以驱动V型尾翼的升降舵上下摆动；机身的尾部安装有22公斤级涡喷发动机；机翼下方的机身上设有双侧增推型进气道。本发明采用增推型进气道设计和小于0.5推进比设计降低了发动机的成本,从而降低了整机成本,本发明的气动外型设计减小了飞机飞行时的阻力,提升了飞机的速度。(The invention discloses a turbojet high-speed target drone, wherein a steering engine is arranged at the tail part of a drone body and is arranged in a steering engine mounting groove on the tail part of the drone body, a steering engine rocker arm is connected to an output shaft of the steering engine, and a tail wing control rocker arm is connected to the steering engine rocker arm; an empennage aluminum rod is embedded at the bottom of the V-shaped empennage, and an empennage control rocker arm socket is arranged at the bottom of the elevator of the V-shaped empennage; the tail wing aluminum rod is inserted into a circular hole in the machine body and fixed by a fastener, the tail wing control rocker arm is inserted into the tail wing control rocker arm socket, and the steering engine drives the steering engine rocker arm and drives the tail wing control rocker arm to rotate so as to drive the elevator of the V-shaped tail wing to swing up and down; the tail part of the machine body is provided with a 22 kilogram-level turbojet engine; the fuselage below the wing is provided with a bilateral thrust-increasing air inlet channel. The invention adopts the design of the boost type air inlet passage and the design of the propulsion ratio less than 0.5 to reduce the cost of the engine, thereby reducing the cost of the whole machine.)

1. A turbojet high-speed target drone comprises a drone body (1), wings (2, 3) arranged on the left side and the right side of the drone body (1) and in a straight shape, and V-shaped empennages (4, 5) arranged on the two sides of the upper end of the drone body (1), and is characterized in that a steering engine (18) is arranged on the tail of the drone body (1), the steering engine (18) is arranged in a steering engine mounting groove on the tail of the drone body (1), an output shaft of the steering engine (18) is connected with a steering engine rocker arm (20), and the steering engine rocker arm (20) is connected with an empennage control rocker arm (21);

tail fin aluminum rods (17) are embedded at the bottoms of the V-shaped tail fins (4, 5), and tail fin control rocker arm sockets (19) matched with the tail fin control rocker arms (21) are arranged at the bottoms of elevators (16) of the V-shaped tail fins (4, 5);

the empennage aluminum rod (17) is inserted into a circular hole in the fuselage (1) and fixed by a fastener, the empennage control rocker arm (21) is inserted into the empennage control rocker arm socket (19), and the steering engine (18) drives the steering engine rocker arm (20) and drives the empennage control rocker arm (21) to rotate so as to drive the elevator (16) of the V-shaped empennages (4, 5) to swing up and down;

the tail part of the machine body (1) is provided with a 22 kg-level turbojet engine;

be equipped with two sides on the fuselage of wing (2, 3) below and increase and push away the type intake duct, this two sides increase and push away the type intake duct general shape and be the Y type, divide into air inlet plastic section (23), diffusion section (24), merge section (25), shrink fairing section (26), air inlet plastic section (23) are the cylindricality, and its air inlet is oval, and air inlet upper edge and wing leading edge coincide, and diffusion section (24) of both sides merge through merge section (25) after the complete diffusion, and diffusion section (24) are in the arc department of intake duct both sides, and the kneck of two sides increase and push away the type intake duct is merge section (25), contracts the rectification through shrink fairing section (26), and shrink fairing section (26) are cylindrical.

2. The turbojet high speed targeting machine of claim 1 wherein the airfoils (2, 3) are upper single-wing, double-lobed asymmetric laminar flow airfoils with a maximum relative thickness of 8.71%, the airfoils (2, 3) have an aspect ratio of 4.2 and a span of 1640 mm;

the length of the fuselage (1) is 2910mm, the distance from the front edge of the fuselage to the front edge of the head of the fuselage is 1300mm, the planar shapes of the wings (2 and 3) are trapezoidal, and the bottom of the flight control cabin in the middle of the two wings (2 and 3) is fixed on the fuselage (1) through four screws.

3. The turbojet high speed target drone of claim 1, characterised in that the V-shaped empennage (4, 5) is a trapezoidal empennage with a small aspect ratio, the maximum relative thickness is 7%, the angle between the V-shaped empennage (4, 5) and the horizontal plane of the drone body (1) is 40 degrees, the V-shaped empennage (4, 5) is fixed to the drone body tail through a pin and an empennage jack at the drone body tail, and the distance from the empennage trailing edge to the drone tail is 35 mm.

4. The turbojet high-speed target drone of claim 1, wherein the steering engine rocker arm (20) is connected with the output shaft of the steering engine (18) through cross screws M5 x 8, and the side surface of the steering engine rocker arm (20) is fixed by two cup-head hexagon socket head cap screws.

5. The turbojet high-speed target drone of claim 1, characterized in that a battery compartment (8) for placing batteries is arranged above the head of the drone body (1), a recovery umbrella compartment (9) for placing recovery umbrellas is arranged behind the battery compartment (8), and three-section oil tanks are arranged below and behind the battery compartment, and the oil tanks are made of carbon fiber composite materials; a flight control cabin (7) is arranged on the fuselage (1) between the wings (2, 3).

6. The turbojet high speed target drone of claim 1 wherein the tail control rocker arm (21) is secured to the steering engine rocker arm (20) by M2 x 5 socket head cap screws.

7. The turbojet high speed target drone of claim 1, characterized in that the fuselage (1) is made of a glass fiber reinforced plastic inner and outer skin intermediate honeycomb sandwich composite material, and the main structure is made of a carbon fiber balsa wood composite material.

8. The turbojet high speed drone of claim 1, characterised in that the outer trailing edges of the wings (2, 3) are provided with ailerons (13), the ailerons (13) being controlled by a steering engine control device (14) located on the lower surface of the wings (2, 3).

Technical Field

The invention belongs to the technical field of unmanned aerial vehicle equipment, and particularly relates to a turbojet high-speed target drone.

Background

The target drone is the earliest application field of unmanned aerial vehicles, and the target drone is developed in the western countries such as English, American and the like as early as 1922, and is the area with the highest technical level and the highest yield. With the rapid development of unmanned aerial vehicle technology, the target drone has become an important component of military aircraft, and the types of the target drone are complete from low-speed target drone, subsonic target drone to supersonic speed target drone, rotary-wing target drone and solid target drone. The unmanned aerial vehicle technology becomes one of the most influential technical means for future operations.

In particular, the medium-high speed target drone is widely applied to actual combat training in various countries, and is greatly helpful for improving the standard of actual combat training and the combat capability. The speed of the medium-speed target drone in the current market is mostly 150m/s, the engine adopts a 40 kg-level turbojet engine pushing 45 kg, the oil consumption is high, the existing pneumatic external resistance is high, and the cost is high.

Disclosure of Invention

Based on the defects of the prior art, the technical problem solved by the invention is to provide the vortex-spraying high-speed target drone, which reduces the resistance of the airplane during flying, and has higher speed and lower cost during flying.

In order to solve the technical problems, the invention is realized by the following technical scheme: the invention provides a turbojet high-speed target drone, which comprises a drone body, wings arranged on the left side and the right side of the drone body and in a straight shape, and V-shaped empennages arranged on the two sides of the upper end of the tail part of the drone body, wherein a steering engine is arranged at the tail part of the drone body, the steering engine is arranged in a steering engine mounting groove on the tail part of the drone body, a steering engine rocker arm is connected to an output shaft of the steering engine, and an empennage control rocker arm is connected to the steering engine rocker arm; an empennage aluminum rod is embedded at the bottom of the V-shaped empennage, and an empennage control rocker arm socket matched with the empennage control rocker arm is arranged at the bottom of the elevator of the V-shaped empennage; the tail wing aluminum rod is inserted into a circular hole in the body and fixed by a fastener, the tail wing control rocker arm is inserted into the tail wing control rocker arm socket, and the steering engine drives the steering engine rocker arm and drives the tail wing control rocker arm to rotate so as to drive the elevator of the V-shaped tail wing to swing up and down; the tail part of the machine body is provided with a 22 kg-level turbojet engine; be equipped with two sides on the fuselage of wing below and increase and push type intake duct, this two sides increase and push type intake duct is the Y type for the shape on the whole, divides into air inlet plastic section, diffusion section, merging section, shrink rectification section, the air inlet plastic section is the cylindricality, and its air inlet is oval, and air inlet upper edge and wing leading edge coincidence, the diffusion section of both sides merge through the merging section after the complete diffusion, and the diffusion section is in the arc department of intake duct both sides, and the kneck of two sides increase and push type intake duct is the merging section, contracts the rectification through the shrink rectification section, and the shrink rectification section is cylindrical.

Further, the wing is an upper single-wing and double-protrusion asymmetric laminar flow wing type, the maximum relative thickness is 8.71%, the aspect ratio of the wing is 4.2, and the wingspan is 1640 mm; the length of the fuselage is 2910mm, the distance from the front edge of the fuselage to the front edge of the head of the fuselage is 1300mm, the planar shape of the wings is trapezoidal, and the bottom of the flight control cabin in the middle of the two wings is fixed on the fuselage through four screws.

Further, V type fin is the trapezoidal fin of little aspect ratio, and maximum relative thickness is 7%, and the contained angle of the horizontal plane of V type fin and fuselage is 40 degrees, V type fin passes through the bolt and fixes at the fuselage afterbody with the fin jack of fuselage afterbody, and the distance of fin trailing edge distance to the tail is 35 mm.

Optionally, the steering engine rocker arm is connected with an output shaft of the steering engine through a cross screw M5 × 8, and the side surface of the steering engine rocker arm is fixed by two cup head socket head cap screws.

Furthermore, a battery cabin for placing batteries is arranged above the head of the machine body, a recovery umbrella cabin for placing recovery umbrellas is arranged behind the battery cabin, and three-section oil tanks are arranged below and behind the battery cabin and are made of carbon fiber composite materials; and a flight control cabin is arranged on the fuselage between the wings.

Optionally, the tail wing control rocker arm is fixed on the steering engine rocker arm through M2 × 5 socket head cap screws.

Furthermore, the machine body is made of a glass fiber reinforced plastic inner skin and outer skin middle honeycomb sandwich composite material, and a main structure is made of a carbon fiber balsa wood composite material.

Furthermore, the outer side rear edge of the wing is provided with an aileron, and the aileron is controlled by a steering engine control device positioned on the lower surface of the wing.

By the aid of the bilateral boosting type air inlet channel, when the flight speed of the target drone is 0.5 Mach, the engine obtains more than twice of air flow, the turbojet engine generates large thrust under the condition of low oil consumption, high-speed flight of the target drone is met, low fuel consumption is achieved, and flight cost is reduced. The design of the thrust-increasing air inlet passage and the design of the thrust ratio less than 0.5 reduce the cost of the engine, thereby reducing the cost of the whole aircraft.

In addition, the vortex-spraying high-speed target drone is simple and stable in structure, strong in bearing capacity and convenient to install and maintain; the requirements on the structure and the space size of the fuselage and the wings are very small, and the fuselage and the wings are not influenced; compared with other existing installation structures, the installation structure of the empennage and the steering engine is free of a steering engine connecting rod, so that the structure is simpler and more compact, and the installation structure also has certain help on the space layout and the light-weight design of the machine body by reducing the installation size.

The foregoing description is only an overview of the technical solutions of the present invention, and in order to make the technical means of the present invention more clearly understood, the present invention may be implemented in accordance with the content of the description, and in order to make the above and other objects, features, and advantages of the present invention more clearly understood, the following detailed description is given in conjunction with the preferred embodiments, together with the accompanying drawings.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings of the embodiments will be briefly described below.

FIG. 1 is a schematic structural view of a turbojet high-speed target drone of the present invention;

FIG. 2 is a schematic view of another angle of the vortex high-speed target drone of the present invention;

FIG. 3 is a schematic view of the V-shaped empennage of the present invention mounted on the fuselage;

FIG. 4 is a schematic structural diagram of a bilateral boost-type air inlet according to the present invention;

FIG. 5 is a cross-sectional view of a dual-sided boost air inlet of the present invention.

In the figure, 1-fuselage, 2-left wing, 3-right wing, 4, 5-V type empennage, 6-engine cabin, 7-flight control cabin, 8-battery cabin, 9-recovery umbrella cabin, 10-airspeed tube, 11, 12-air inlet at two sides, 13-aileron, 14-aileron steering engine control device, 16-elevator, 17-empennage aluminum rod, 18-steering engine, 19-empennage control rocker arm socket, 20-steering engine rocker arm, 21-empennage control rocker arm, 22-screw, 23-air inlet shaping section, 24-diffuser section, 25-merging section and 26-contraction rectifying section.

Detailed Description

Other aspects, features and advantages of the present invention will become apparent from the following detailed description, taken in conjunction with the accompanying drawings, which form a part of this specification, and which illustrate, by way of example, the principles of the invention. In the referenced drawings, the same or similar components in different drawings are denoted by the same reference numerals.

It should be noted that all the directional indicators (such as upper, lower, outer, inner, front and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly.

As shown in fig. 1 to 5, the turbojet high-speed target drone of the present invention includes a fuselage 1, wings 2 and 3 arranged on the left and right sides of the fuselage 1 and in a straight line shape, V-shaped empennages 4 and 5 arranged on the two sides of the upper end of the fuselage 1, a 22 kg-level turbojet engine is arranged at the tail of the fuselage 1, the wings 2 and 3 are upper single-wing and double-protrusion asymmetric laminar flow wing profiles, the maximum relative thickness is 8.71%, the span-chord ratio of the wings is 4.2, the span is 1640mm, the length of the fuselage 1 is 2910mm, the distance from the front edge of the fuselage to the front edge of the fuselage head is 1300mm, the planar shapes of the wings 2 and 3 are trapezoidal, the wings 2 and 3 are integrated wings, and the bottom of a flight control cabin in the middle of the two wings 2 and 3 is fixed on the fuselage through four screws.

The V-shaped tail wings 4 and 5 are trapezoidal tail wings with small aspect ratio, the maximum relative thickness is 7%, the included angle between the tail wings and the plane of the machine body is 40 degrees, the tail wings are fixed at the tail part of the machine body through bolts and tail wing insertion holes at the tail part of the machine body, and the distance from the rear edge of each tail wing to the tail part is 35 mm.

The outer rear edges of the wings on the two sides of the fuselage 1 are provided with ailerons 13, and the ailerons 13 are controlled by steering engine control devices 14 positioned on the lower surfaces of the wings 2 and 3. The afterbody of fuselage 1 is equipped with steering wheel 18, sets up in the wing root department of V type fin 4, 5, respectively opens four round holes in the 1 afterbody left and right sides of fuselage, respectively digs out a steering wheel mounting groove in the fuselage afterbody left and right sides, and two steering wheel mounting grooves are bilateral symmetry, fix steering wheel 18 in the steering wheel mounting groove. Threaded holes are formed in the steering engine mounting groove, mounting holes are formed in the steering engine 18, the mounting holes in the steering engine 18 correspond to the threaded holes in position, and the steering engine 18 is fixed in the steering engine mounting groove by penetrating through the mounting holes by using M4 x 10 socket head hexagon socket head screws and then being in threaded connection with the threaded holes. The two steering engines 18 are fixed by 8M 4X 10 cup head socket head cap screws, the output shaft of each steering engine 18 is connected with a steering engine rocker arm 20, the steering engine rocker arms 20 are connected with the output shaft of the steering engine 18 through M5X 8 cross screws, 2M 5X 8 cross screws are required for two V-shaped tail wings 4 and 5, and the side surface of each steering engine rocker arm 20 is fixed by two cup head socket head cap screws which are 4 in total.

Each steering engine rocker arm 20 is connected with an empennage control rocker arm 21, and two M2X 5 cup head socket head cap screws are needed for fixing one empennage control rocker arm 21, and 4 are needed. Two tail wing aluminum rods 17 are embedded at the bottom of each tail wing, a tail wing control rocker socket 19 is arranged at the bottom of an elevator 16 which is rotationally connected with the V-shaped tail wing, and the shape of the tail wing control rocker socket 19 is matched with that of a tail wing control rocker 21. The tail wing control rocker arm socket 19 is aligned with the tail wing control rocker arm 21, two tail wing aluminum rods 17 are aligned with two round holes on the outer side of the machine body and are inserted into the round holes, and then 2 screws 22 (fasteners) are used for fixing the V-shaped tail wings on the machine body 1, wherein 4 screws are needed. After the installation is finished, the receiver sends a signal to the steering engine 18, the steering engine 18 drives the steering engine rocker arm 20, the steering engine rocker arm 20 drives the tail wing control rocker arm 21 to rotate, so that the elevator 16 of the tail wing is driven to swing up and down, and the functions of the elevator 16 and the rudder are realized through the V-shaped tail wings 4 and 5.

Fuselage head front end is equipped with airspeed head 10 for calculate unmanned aerial vehicle airspeed, fuselage head top is equipped with the battery compartment 8 of placing the battery, and 8 backs in battery compartment are provided with the recovery parachute bay 9 of placing the recovery umbrella, and below and rear are provided with the syllogic oil tank, and the oil tank adopts carbon-fibre composite, and the centre of rear integral type wing is provided with flies accuse cabin 7. The shell (fuselage 1) of the unmanned aerial vehicle is made of a glass fiber reinforced plastic inner skin and outer skin middle honeycomb sandwich composite material, and a main structure is made of a carbon fiber balsa wood composite material. The fuselage part below the wing is provided with a bilateral thrust-increasing air inlet channel.

The fuselage below the wings 2 and 3 is provided with a bilateral thrust augmentation type air inlet which is generally Y-shaped and is divided into an air inlet shaping section 23, a diffusion section 24, a merging section 25 and a contraction rectification section 26. The two air inlets 11 and 12 are arranged below the wing, the air inlet shaping section 23 is cylindrical, the air inlets are oval, the upper edge of each air inlet is overlapped with the front edge of the wing, the diffusion sections 24 on the two sides are combined through the combining section 25 after complete diffusion, the diffusion sections 24 are arranged at the arc-shaped positions on the two sides of the air inlet, the joint of the air inlet is the combining section 25, contraction rectification is carried out through the contraction rectification section 26, and the contraction rectification section 26 is the last cylindrical section.

The invention is used for optimally designing the bilateral thrust-increasing type air inlet when the flying speed is 0.5 Mach. The designed cavity is used for increasing the pressure difference between the inside and the outside of the air inlet at the speed, so that the high-speed large-flow compressed air is used for pushing the turbojet engine to output full horsepower under the condition of 0.7-0.8 of throttle opening. In other words, through the design of the boost type air inlet channel, when the flight speed of the target drone is Mach 0.5, the engine obtains more than twice of air flow, so that the turbojet engine generates large thrust under the condition of low oil consumption, high-speed flight of the target drone is met, lower fuel consumption is consumed, and flight cost is reduced.

In addition, the vortex-spraying high-speed target drone is simple and stable in structure, strong in bearing capacity and convenient to install and maintain; the requirements on the structure and the space size of the fuselage and the wings are very small, and the fuselage and the wings are not influenced; compared with other existing installation structures, the installation structure of the empennage and the steering engine provided by the invention has the advantages that a steering engine connecting rod is omitted, the structure is simpler and more compact, and certain help is provided for the space layout and the light weight design of the engine body by reducing the installation size.

While the foregoing is directed to the preferred embodiment of the present invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof, and the scope thereof is determined by the claims that follow.