CN113443145A

CN113443145A - Military unmanned aerial vehicle

Info

Publication number: CN113443145A
Application number: CN202110600404.4A
Authority: CN
Inventors: 王月星; 李军; 欧帅
Original assignee: Avic Chengdu Uav System Co ltd
Current assignee: Avic Chengdu Uav System Co ltd
Priority date: 2021-05-31
Filing date: 2021-05-31
Publication date: 2021-09-28
Anticipated expiration: 2041-05-31
Also published as: CN113443145B

Abstract

The invention discloses a military unmanned aerial vehicle, which comprises a vehicle body and two wings, wherein the two wings are fixedly connected to two sides of the vehicle body respectively, the vehicle body comprises a receiving unit and a control unit, any one wing comprises at least two sections of fins, a sub-missile is arranged between any two adjacent sections of fins, and the sub-missile is connected with the fins through auxiliary explosion bolts; when the receiving unit receives the cruise instruction, the control unit controls the machine body to carry the guided missile to synchronously fly at the preset cruise speed so as to realize cruise reconnaissance; when the receiving unit receives the attack instruction, the control unit controls the auxiliary explosion bolt to explode and break and controls the sub-missile to separate from the machine body at the preset attack speed, and target attack is achieved. The military unmanned aerial vehicle provided by the invention integrates reconnaissance and attack, and has the advantages of strong attack capability, simple connection mode and low manufacturing cost.

Description

Military unmanned aerial vehicle

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to a military unmanned aerial vehicle.

Background

Military unmanned aerial vehicles revolutionarily start a new modern war mode as emerging air combat power, have zero casualties, have the advantages of flexible performance, remote combat and the like, and are favored by various countries. At present, a military unmanned aerial vehicle is developed into an intelligent weapon similar to a missile from a single reconnaissance or attack role, the function is continuously improved, and the existing military unmanned aerial vehicle has some defects.

For example, for military use, a reconnaissance and combat integrated unmanned aerial vehicle represented by a "predator" and "rainbow" series is generally equipped with a guided weapon, and although the guided weapon can meet the combat requirement, the unmanned aerial vehicle has a complex structure, involves more high-precision electronic equipment, and has a high manufacturing cost. However, when an attack type missile with low cost is used, it is very likely to be intercepted by an enemy defense system, and the attack capability is weak.

Therefore, how to develop a military unmanned aerial vehicle with both low manufacturing cost and strong attack capability is a technical problem to be solved by technical personnel in the field.

Disclosure of Invention

In view of the above, the invention aims to provide a military unmanned aerial vehicle, wherein when the military unmanned aerial vehicle is cruising, a body carries a sub-missile to synchronously fly at a preset cruising speed through a wing; during attack, the auxiliary explosion bolts among all the parts are exploded and broken, the sub-missile is separated from the machine body at a preset attack speed to carry out target attack, the attack capacity is strong, the connection mode is simple, and the manufacturing cost is low.

The invention provides a military unmanned aerial vehicle, which comprises:

the machine body comprises a receiving unit and a control unit;

two wings respectively fixedly connected to two sides of the aircraft body, wherein any one wing comprises at least two sections of wing panels, a sub-missile is arranged between any two adjacent sections of wing panels, and the sub-missile is connected with the wing panels through auxiliary explosion bolts;

when the receiving unit receives the cruise instruction, the control unit controls the machine body to carry the guided missile to synchronously fly at the preset cruise speed so as to realize cruise reconnaissance;

when the receiving unit receives the attack instruction, the control unit controls the auxiliary explosion bolt to explode and break and controls the sub-missile to separate from the machine body at the preset attack speed, and target attack is achieved.

Preferably, the two wings are connected with the aircraft body through main explosion bolts, and when the receiving unit receives a defense penetration instruction, the control unit controls the main explosion bolts to explode and break and controls the aircraft body to match with the sub-missile to attack the target together at a preset defense penetration speed.

Preferably, the main body further comprises a processing unit, when the receiving unit receives the defense command, the processing unit plans a preset attack track of the main body and the sub-missile, and the control unit controls the main body and the sub-missile to attack the target together along the preset attack track.

Preferably, the sub missile comprises a secondary driving member, and when the secondary explosive bolt is exploded and broken, the control unit starts the secondary driving member to drive the sub missile to fly out.

Preferably, the aircraft body further comprises a reconnaissance unit, and when the reconnaissance unit reconnaissance the attack targets smaller than or equal to the preset number, the reconnaissance unit feeds back the attack instruction to the receiving unit; when the reconnaissance unit reconnaissance the attack targets larger than the preset number, the reconnaissance unit feeds back the penetration instruction to the receiving unit.

Preferably, any one wing comprises a rectangular fin disposed on the outermost side.

Preferably, any one wing further comprises a trapezoidal wing panel arranged between the rectangular wing panel and the machine body.

Preferably, the machine body further includes:

a main housing;

a task load cabin fixedly arranged at the front end of the main shell;

an oil supply tank provided in the main casing;

a main driving member fixedly arranged at the tail part of the main shell;

and the air inlet channel is fixedly arranged at the bottom of the main shell.

Compared with the background technology, the military unmanned aerial vehicle provided by the invention comprises a vehicle body and two wings, wherein the vehicle body comprises a receiving unit and a control unit, the two wings are respectively connected to two sides of the vehicle body, a sub-missile is arranged between any two adjacent sections of wings, and the sub-missile is connected with the wings through auxiliary explosion bolts.

When the receiving unit receives the cruise instruction, the control unit controls the missile body to synchronously fly at a preset cruise speed by the wing carrier missile, so that cruise reconnaissance is realized; when the receiving unit receives the attack instruction, the control unit controls the auxiliary explosion bolt to explode and break, and simultaneously controls the sub-missile to separate from the machine body at a preset attack speed, so that target attack is realized.

Therefore, the military unmanned aerial vehicle provided by the invention integrates reconnaissance and attack, has strong attack capability, is connected with the wing pieces by virtue of the explosive bolts, has a simple connection mode, is convenient to disassemble and assemble, and is beneficial to reducing the manufacturing cost. Therefore, the military unmanned aerial vehicle provided by the invention is low in manufacturing cost and strong in attack capability.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.

Fig. 1 is a block diagram of a military drone provided in an embodiment of the present invention;

FIG. 2 is a front view of FIG. 1;

fig. 3 is a structural view of the main body of fig. 1.

The reference numbers are as follows:

the aircraft comprises an aircraft body 1, wings 2 and sub-missiles 3;

a main housing 11, a mission load compartment 12, an oil supply tank 13, a main drive member 14, and an air intake duct 15;

a rectangular tab 21 and a trapezoidal tab 22.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific examples.

Referring to fig. 1 to 3, fig. 1 is a structural diagram of a military drone according to an embodiment of the present invention; FIG. 2 is a front view of FIG. 1; fig. 3 is a structural view of the main body of fig. 1.

The embodiment of the invention discloses a military unmanned aerial vehicle which comprises a machine body 1 and two wings 2, wherein the two wings 2 are fixedly arranged on two sides of the machine body 1 respectively, and the two wings 2 are symmetrically distributed.

The machine body 1 comprises a receiving unit and a control unit, wherein the receiving unit is used for receiving instructions, the control unit is electrically connected with the receiving unit, and the control unit controls corresponding executing parts to execute corresponding actions according to signals sent by the receiving unit.

Two wings 2 are split type structure, conveniently transport parts such as quick-witted body 1 and each fin to the battlefield, directly assemble out a large amount of for military use unmanned aerial vehicle behind the battlefield, provide the advantage to the battlefield for a large amount of equipment of rapid set, provide probably for forming the battlefield fast.

The two wings 2 have the same structure, any one wing 2 comprises at least two sections of wing panels, the sub-missiles 3 are arranged between any two adjacent sections of wing panels, the number of the sub-missiles 3 carried by each wing 2 is the same, and the uniform stress of the wings 2 is ensured. Specifically, each wing 2 only carries one sub-missile 3, the carrying of the sub-missiles 3 can be adjusted adaptively according to the specification of the aircraft body 1 and the length of the wing 2, and the specific carrying number is not specifically limited herein. The sub-missile 3 is connected with the wing through the auxiliary explosion bolt, so that the connection mode is simple, the disassembly and the assembly are convenient, and the manufacturing cost is favorably reduced. In addition, the connection mode between the sub-missile 3 and the wing pieces ensures that the sub-missile 3 is not recycled after being used for a single time, and the whole machine can break through the front edge of an enemy position to carry out reconnaissance and attack at a higher risk.

The electric control unit of the auxiliary explosion bolt is electrically connected with the control unit, so that the control unit controls the electric control unit to be started or closed, and the auxiliary explosion bolt can be conveniently and automatically detonated. The structure and the working principle of the auxiliary explosion bolt can be referred to the prior art.

When the receiving unit receives the cruise instruction, the receiving unit sends a signal to the control unit, the control unit controls the aircraft body 1 to fly at a preset cruise speed, and the aircraft body 1 carries the sub-missile 3 to synchronously fly through the wings 2, so that cruise reconnaissance is realized. The preset cruising speed can be 0.3Ma, and can be specifically adjusted according to the specification of the machine body 1. In this embodiment, the military drone can cruise at 0.3Ma cruise speed for 6 hours before being disassembled, and can continue cruising at the front of the battlefield, waiting for the most appropriate time.

When the receiving unit receives the attack instruction, the receiving unit feeds back a signal to the control unit, the control unit controls the auxiliary explosion bolt to explode and break, and meanwhile the sub-missile 3 is controlled to be separated from the machine body 1 at a preset attack speed, so that target attack is achieved. Wherein, the preset attack speed can exceed 0.7Ma and can reach 3Ma at most.

Each sub-missile 3 comprises an auxiliary driving part, the auxiliary driving part can be a solid rocket engine specifically, when an auxiliary explosion bolt is exploded and broken, the sub-missile 3 is separated from the machine body 1, the control unit starts the auxiliary driving part, and the auxiliary driving part drives the sub-missile 3 to shoot to an attack target at a high speed, so that a greater damage effect is achieved.

The simple connection mode between the aircraft body 1 and the wing 2 is favorable to reducing the volume, makes whole realization lightweight, discovers and is hit the probability and also reduces thereupon, and the security obtains promoting.

In conclusion, the military unmanned aerial vehicle provided by the invention integrates reconnaissance and attack, and has the advantages of stronger attack capability, simpler assembly and lower manufacturing cost.

Further, the two wings 2 are connected with the machine body 1 through the main explosion bolts, so that the connection mode is further simplified, and the manufacturing cost is further reduced. Similarly, the electric control unit of the main explosion bolt is also electrically connected with the control unit, the control unit is used for controlling the main explosion bolt to automatically explode, and the structure and the working principle of the main explosion bolt can also refer to the prior art.

When the receiving unit receives the penetration instruction, the receiving unit sends a signal to the control unit, the control unit controls the main explosion bolt to explode and break, and meanwhile, the machine body 1 is controlled to fly out at a preset penetration speed, so that the machine body 1 and the sub-missile 3 are matched to attack a target together, the penetration success rate is improved, and a larger damage effect is achieved. Obviously, once an attack target is found, the whole machine can be automatically split into an elevated unmanned aerial vehicle and two sub-missiles 3, and the tasks are cooperatively executed in a cluster mode, so that high-efficiency defense burst is realized, and the attack capability is stronger. In addition, during the penetration, the aircraft body 1 can quickly achieve high subsonic flight by shortening the length of the wings 2, so that the large-maneuvering flight attack is realized, the battlefield survival capacity is higher, and the combat efficiency is higher.

The machine body 1 further comprises a processing unit which is used for planning the attack tracks of the machine body 1 and the sub-missiles 3 at the same time. When the receiving unit receives a defense penetration instruction, the processing unit plans the preset attack tracks of the machine body 1 and the sub-missile 3 at the same time according to the instruction, the processing unit is electrically connected with the control unit, and the control unit controls the machine body 1 and the sub-missile 3 to attack the target along the preset attack tracks according to the signal fed back by the processing unit, so that the target is attacked accurately. And planning the preset attack track in real time according to the position of the attack target.

In addition, the aircraft body 1 further comprises a reconnaissance unit, and the reconnaissance unit is used for reconnaissance of the position of the attack target in real time. The scout unit may particularly be an image recognition device. The reconnaissance unit is fixedly arranged on the machine body 1. The scout unit is electrically connected with the receiving unit. When the reconnaissance unit reconnaissance is smaller than or equal to the preset number of attack targets, the number of the attack targets is small, and at the moment, the reconnaissance unit feeds back an attack instruction to the receiving unit, so that the control unit only controls the sub-missile 3 to attack. When the reconnaissance unit reconnaissance attack targets larger than the preset number, the number of the attack targets is larger, and at the moment, the reconnaissance unit feeds back a defense command to the receiving unit, so that the control unit controls the machine body 1 and the sub-missiles 3 to cooperatively realize cluster combined attack. The reconnaissance unit can enable the aircraft body 1 to automatically switch task modes, and is favorable for efficient combat. The preset number may be two, but is not limited to this, and is the same as the set number of the sub-missiles 3.

In addition, after the sub-missile 3 attacks the target, the reconnaissance unit can also feed back the attack effect of the sub-missile 3 before the machine body 1 attacks the target, so that the control unit can adjust the attack track of the machine body 1 in time, and efficient attack is realized. The whole aircraft flies in an initial state as a whole, networking is not needed, and the cooperative control difficulty is small.

In this embodiment, any one of the wings 2 includes a rectangular wing 21, and the rectangular wing 21 is disposed at the outermost side to ensure a larger aspect ratio before the whole wing is not disassembled. When the attack mission is executed, the control unit firstly controls the secondary explosion bolt connected between the rectangular wing 21 and the sub-missile 3 to explode firstly, so that the rectangular wing 21 is abandoned firstly, and then the control unit controls the sub-missile 3 to launch at a high speed.

Any wing 2 further comprises a trapezoidal wing 22, the trapezoidal wing 22 is arranged between the rectangular wing 21 and the machine body 1, and the wide side of the trapezoidal wing 22 faces the machine body 1. The trapezoidal wing 22 can provide the lifting force for the machine body 1 after the sub-missile 3 and the rectangular wing 21 are separated. When the high-speed penetration is carried out, the control unit controls the main explosion bolt between the trapezoidal wing panel 22 and the machine body 1 to explode, so that the machine body 1 is matched with the sub-missile 3 to carry out the high-speed penetration. In addition, the trapezoidal shaped fins 22 may increase the radius of play to some extent.

Of course, the structure of each wing 2 is not limited thereto.

The machine body 1 includes a main housing 11, a mission load compartment 12, an oil supply tank 13, a main drive member 14, and an air intake duct 15, and the main housing 11 is cylindrical. The task load cabin 12 is fixedly arranged at the front end of the main shell 11, and task loads of different specifications can be replaced according to task requirements. The fuel supply tank 13 is arranged in the main shell 11 and used for containing fuel oil for the aircraft body 1 to fly. The main driving member 14 is fixedly disposed at the rear portion of the main housing 11, and may be a small turbojet engine. The air inlet 15 is fixedly arranged at the bottom of the main shell 11 and provides a passage for air inlet of the small turbojet engine.

The military unmanned aerial vehicle provided by the invention is described in detail above, and a specific example is applied in the description to explain the principle and the implementation mode of the invention, and the description of the above embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims

1. A military unmanned aerial vehicle, comprising:

the machine body (1), the machine body (1) comprises a receiving unit and a control unit;

the aircraft comprises two wings (2) which are fixedly connected to two sides of an aircraft body (1) respectively, wherein any one wing (2) comprises at least two sections of wing panels, a sub-missile (3) is arranged between any two adjacent sections of wing panels, and the sub-missile (3) is connected with the wing panels through auxiliary explosion bolts;

when the receiving unit receives a cruise instruction, the control unit controls the aircraft body (1) to carry the sub-missile (3) to synchronously fly at a preset cruise speed, so that cruise reconnaissance is realized;

when the receiving unit receives an attack instruction, the control unit controls the auxiliary explosion bolt to explode and break and controls the sub-missile (3) to separate from the machine body (1) at a preset attack speed, and target attack is achieved.

2. The military unmanned aerial vehicle of claim 1, wherein two wings (2) are connected with the main body (1) through main explosion bolts, and when the receiving unit receives a defense command, the control unit controls the main explosion bolts to explode and break and controls the main body (1) to cooperate with the sub-missile (3) to attack a target at a preset defense penetration speed.

3. The military unmanned aerial vehicle of claim 2, wherein the body (1) further comprises a processing unit, when the receiving unit receives the defense penetration instruction, the processing unit plans a preset attack track of the body (1) and the sub-missile (3), and the control unit controls the body (1) and the sub-missile (3) to jointly attack a target along the preset attack track.

4. Military drone according to claim 2, characterised in that the child missile (3) comprises a secondary drive which is activated by the control unit to drive the child missile (3) to fly out when the secondary explosive bolt is explosively broken.

5. The military unmanned aerial vehicle of claim 2, wherein the vehicle body (1) further comprises a reconnaissance unit, and when the reconnaissance unit reconnaissance the attack targets less than or equal to a preset number, the reconnaissance unit feeds back the attack instructions to the receiving unit; when the reconnaissance unit reconnaissance the attack targets larger than the preset number, the reconnaissance unit feeds back the penetration instruction to the receiving unit.

6. Military drone according to any of claims 1 to 5, characterised in that any of the wings (2) comprises rectangular fins (21) arranged on the outermost side.

7. Military drone according to claim 6, characterised in that any one of the wings (2) further comprises a trapezoidal tab (22) provided between the rectangular tab (21) and the body (1).

8. Military drone according to any one of claims 1 to 5, characterised in that the body (1) further comprises:

a main housing (11);

a task load compartment (12) fixedly arranged at the front end of the main shell (11);

an oil supply tank (13) provided in the main casing (11);

a main driving part (14) fixedly arranged at the tail part of the main shell (11);

and the air inlet channel (15) is fixedly arranged at the bottom of the main shell (11).