CN108313281B

CN108313281B - Variable-configuration unmanned aerial vehicle

Info

Publication number: CN108313281B
Application number: CN201810222358.7A
Authority: CN
Inventors: 张炜; 李可; 马一元; 杜聪聪
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2018-03-19
Filing date: 2018-03-19
Publication date: 2021-07-16
Anticipated expiration: 2038-03-19
Also published as: CN108313281A

Abstract

The invention relates to a variable-configuration unmanned aerial vehicle which has two configuration modes of a fixed wing and a multi-duct mode. After reaching a target area, a designated task system is carried by utilizing a multi-duct configuration, and a task is executed by depending on hovering and accurate maneuvering capabilities.

Description

Variable-configuration unmanned aerial vehicle

Technical Field

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a variable-configuration unmanned aerial vehicle.

Background

The application of unmanned aerial vehicles in the world is more and more extensive nowadays, and especially in the military aspect, unmanned aerial vehicles play more and more important roles in modern war as means such as information collection, information investigation, territorial defense and the like.

Duct formula unmanned aerial vehicle is a special rotor unmanned vehicles, this unmanned aerial vehicle simple structure, easily control operation, through its structure and automatic control, can realize smooth flight in abominable pneumatic environment, can realize various functions through loading multiple different equipment, main study duct unmanned aerial vehicle have wherein the american sikorsky company developed the duct unmanned aerial vehicle of cyprer series, the ISTAR duct formula unmanned aerial vehicle that the company of aledaerospace developed etc., but because duct unmanned aerial vehicle's speed limit, it puts in the radius short, long-range service ability is little, it is weak to rush fast.

At present, small and medium-sized unmanned aerial vehicles capable of realizing remote and rapid rushing capabilities are mainly two types of unmanned aerial vehicles for patrolling missiles and shooting guns. The patrol missile is an aircraft which can be thrown by using the existing weapon and can perform patrol flight in a target area to execute related tasks. The main examples are the American military 'quick-look' detection cruise missile and the israel 'meteorite' individual patrol missile. Gun-shot drones are mainly used for reconnaissance functions, such as skylite drones in israel and KZO surveillance reconnaissance drones in germany. However, the two types of unmanned aerial vehicles are still not perfect, such as a small-sized shot unmanned aerial vehicle which has a low flying speed, a long time for entering a war zone and a short range; the large and medium-sized patrol missiles have long range and high flying speed, but are difficult to realize fixed-point hovering and low-speed accurate detection.

In order to solve the problem of complaints, the prior patent technology such as Chinese patent with application number CN103043214A discloses a folding unmanned aerial vehicle which has flexible launching and convenient use, can be quickly deployed in battlefields and can freely carry out mission flight at low altitude and ultra-low altitude. However, the unmanned aerial vehicle is small in size and light in weight, so that the range is short, the task load carrying capacity is poor, and the stable hovering and accurate maneuvering capacity in a low altitude state cannot be realized.

Disclosure of Invention

The technical problem solved by the invention is as follows: in order to solve the problems, the invention provides a variable-configuration unmanned aerial vehicle which has two configuration modes of a fixed wing and a multi-duct mode. After reaching a target area, a designated task system is carried by utilizing a multi-duct configuration, and a task is executed by depending on hovering and accurate maneuvering capabilities.

The technical scheme of the invention is as follows: a variable configuration unmanned aerial vehicle comprises two wings 1, two ailerons 3, two empennages 9, two tail rudders 4 and a multi-duct fuselage 5; the wings 1 are symmetrically positioned on two sides of the multi-duct fuselage 5, two tail wings 9 are V-shaped and positioned at the tail end of the multi-duct fuselage 5, the wings 1 are provided with ailerons 3, and the tail wings 9 are provided with tail rudders 4; the system is characterized by also comprising a rocket engine 2, a plurality of ducted fans 6, a load cabin 8, the rocket engine 2 and a plurality of speed reducers 7; the multi-duct body 5 is polygonal, a load cabin 8 is arranged at the center of the multi-duct body, a plurality of duct fans 6 and a plurality of speed reducers 7 are arranged on the periphery of the multi-duct body, and the duct fans 6 are uniformly distributed in the circumferential direction; a rocket engine 2 is arranged between the wing 1 and the multi-duct fuselage 5; the rocket engine 2 boosts and launches the unmanned aerial vehicle, the wings 1 provide stable lift force, and the ailerons 3 and the tail vane 4 provide operating force; after the multi-duct airframe 5 reaches the working area, the multi-duct airframe 5 is separated from other components, at the moment, the aircraft control platform controls the duct fan 6 to work, the multi-duct airframe 5 is stabilized and hovers in the working area, and the load cabin 8 starts to execute tasks.

The further technical scheme of the invention is as follows: the load cabin 8 is connected with the multi-duct machine body 5 through an electric hydraulic rod, and the platform deflects in all directions through differential lifting of the electric hydraulic rod.

The further technical scheme of the invention is as follows: the wings 1 and the multi-duct fuselage 5, and the tail rudder 4 and the multi-duct fuselage 5 are connected through explosive bolts; after the airplane arrives at a working area, the airplane control platform controls the explosive bolts to explode, so that the multi-duct airplane body 5 is separated from the wings 1 and the tail rudder 4.

Effects of the invention

The invention has the technical effects that: the invention provides a variable-configuration unmanned aerial vehicle which has two modes of a fixed wing configuration and a multi-duct configuration, is launched by a rocket engine during the fixed wing configuration, and has the advantages of rapid launch, high cruising speed and long throw distance. When in a multi-duct configuration, the multi-duct navigation system has the capabilities of fixed-point hovering and accurate maneuvering.

Drawings

Fig. 1 is a schematic structural diagram of the variable configuration unmanned aerial vehicle.

Fig. 2 is a structural top view of the variable configuration unmanned aerial vehicle.

Fig. 3 is an isometric view of a multi-duct configuration of the variable configuration drone of the present invention.

Description of reference numerals: 1. wing 2, rocket engine 3, aileron 4, tail vane 5, multi-duct fuselage 6, duct fan 7, speed reducing umbrella 8, load cabin 9, tail wing 10 and explosive bolt

Detailed Description

Referring to fig. 1-3, the unmanned aerial vehicle multi-duct fuselage comprises an unmanned aerial vehicle multi-duct fuselage, wings, a V empennage, two rocket engines, eight lifting force fans and a multifunctional working platform. The multi-duct fuselage is in a polygonal configuration, in this embodiment, a heptagon; the wings are arranged on two sides of the polygon; the tail wing is arranged on one side of the polygon; the two rocket engines are arranged on wings of the unmanned aerial vehicle and arranged at the roots of the wings of the unmanned aerial vehicle; the eight lifting force fans are installed on the multi-duct unmanned aerial vehicle body and are uniformly distributed on the multi-duct unmanned aerial vehicle body; the load cabin is circular and is arranged in the center of the multi-duct fuselage.

The speed reducing umbrella is arranged on the airplane body, so that the airplane is ensured to be decelerated in the configuration change process.

The connection of the multi-duct fuselage, the wings and the empennage is explosive bolt connection. Ensures that the wings and the empennage can be separated from the multi-duct fuselage in the configuration change process.

The multifunctional working platform of the unmanned aerial vehicle is connected with the multi-duct body through four electric hydraulic rods, and the platform deflects in all directions through differential lifting of the electric hydraulic rods, so that the working range is changed.

The rocket engine installed on the wings of the unmanned aerial vehicle can directly launch the unmanned aerial vehicle in a boosting way, lift force is provided by the wings of the unmanned aerial vehicle, and the ailerons on the wings and the tail rudder on the empennage provide operating force, so that high-speed cruising and rapid deployment are realized. When the airplane arrives at a designated area, the airplane decelerates and flies, and the wings, the empennage and the multi-duct airplane body are separated under the action of explosive bolts at the joints of the wings and the airplane body and the empennage and the airplane body controlled by the flight control of the unmanned aerial vehicle, so that the configuration change process is completed; after breaking away from, the duct fan on the many ducts unmanned aerial vehicle starts, through flying the control of accuse to many duct fans, stabilizes many ducts fuselage and hovers in the specified area, and meanwhile, work platform begins the executive task on the many ducts fuselage.

Referring to fig. 1 and 3, the variable configuration unmanned aerial vehicle of the embodiment is shown, and comprises wings 1, a rocket engine 2, ailerons 3, a tail rudder 4, a multi-duct fuselage 5, a duct fan 6, a drogue 7, a load compartment 8, a tail wing 9 and explosive bolts 10. The two rocket engines 2 are symmetrically arranged at the root parts of the wings 1, the wings 1 are connected with a multi-duct fuselage 5 through explosion bolts, duct fans 6 are arranged on the multi-duct fuselage 5 and are uniformly distributed on the multi-duct fuselage, a speed reducing umbrella 7 is arranged on the fuselage, and a load cabin 8 is arranged in the center of the fuselage. The working process of the unmanned aerial vehicle can be divided into five stages of launching, high-speed cruising, decelerating and disengaging, fixed-point hovering, accurate maneuvering and task execution.

In the embodiment, the unmanned aerial vehicle provides lift force by means of the wings in the high-speed cruising stage when the unmanned aerial vehicle is in the fixed wing configuration, the control surfaces on the wings provide the transverse control capability, and the control surfaces on the V-shaped empennage provide the longitudinal and heading control capabilities. In the hovering and maneuvering stages in the multi-duct configuration, the multi-duct fan is used for providing stable torque and maneuvering speed.

In the first embodiment, when the rocket engine is started, the unmanned aerial vehicle obtains the maximum thrust, takes off from the launcher directly, provides lift force by means of the wings, provides flight control capability for each control surface of the wing empennage, and achieves high-speed cruising and long-distance delivery.

In the second embodiment, when each ducted fan is started, eight fans are used for providing lift force, and the thrust of different fans is changed through flight control, so that low-speed short-distance maneuvering can be realized.

The working process of the invention is as follows:

the invention relates to a variable-configuration unmanned aerial vehicle, wherein the take-off state is a fixed wing configuration, after a take-off instruction is received, a rocket engine is started, the unmanned aerial vehicle takes off from an ejection rack and flies to a designated area, at the moment, wings provide lift force, airplane ailerons provide transverse operation capability, and V-shaped empennage control surfaces on empennages provide longitudinal operation capability and course operation capability. And after the aircraft decelerates to a specified speed, controlling explosion bolts at the joints of the wings and the empennage to explode, so that the wings and the empennage are separated from the multi-duct fuselage respectively. Simultaneously, eight duct fans of many duct unmanned aerial vehicle begin work, the thrust of duct fan provides the lift of flying, and enable the aircraft further to slow down, and stably hover, later the multi-functional work platform on the many duct unmanned aerial vehicle starts, carry out the work task to this region, and change many duct unmanned aerial vehicle's each fan thrust in real time according to the task demand, change unmanned aerial vehicle's position, the direction of deflection according to connecting device's lift change platform simultaneously, with change working range and region.

Claims

1. A variable configuration unmanned aerial vehicle comprises two wings (1), two ailerons (3), two tail wings (9), two tail rudders (4) and a multi-duct fuselage (5); the wings (1) are symmetrically positioned on two sides of the multi-duct fuselage (5), two tail wings (9) are V-shaped and positioned at the tail end of the multi-duct fuselage (5), the wings (1) are provided with ailerons (3), and the tail wings (9) are provided with tail rudders (4); the rocket engine is characterized by further comprising a rocket engine (2), a plurality of ducted fans (6), a load cabin (8) and a plurality of speed reducers (7); the multi-duct body (5) is polygonal, a load cabin (8) is arranged at the center of the multi-duct body, a plurality of duct fans (6) and a plurality of speed reducers (7) are arranged at the periphery of the multi-duct body, and the duct fans (6) are uniformly distributed in the circumferential direction; a rocket engine (2) is arranged between the wing (1) and the multi-duct fuselage (5); the rocket engine (2) launches the unmanned aerial vehicle in a boosting mode, the wings (1) provide stable lift force, and the ailerons (3) and the tail rudder (4) provide operating force; after the multi-duct airframe reaches a working area, the multi-duct airframe (5) is separated from the wings and the empennage, at the moment, the aircraft control platform controls the duct fan (6) to work, the multi-duct airframe (5) is stabilized and hovers in the working area, and the load cabin (8) starts to execute tasks.

2. The unmanned aerial vehicle with the variable configuration in claim 1, wherein the load cabin (8) is connected with the multi-duct fuselage (5) through an electro-hydraulic rod, and the load cabin (8) can deflect in all directions through differential lifting of the electro-hydraulic rod.

3. The unmanned aerial vehicle with variable configuration as claimed in claim 1, wherein the wings (1) and the multi-duct fuselage (5), the empennage (9) and the multi-duct fuselage (5) are connected by explosive bolts; after the airplane arrives at a working area, the airplane control platform controls the explosive bolts to explode, so that the multi-duct airplane body (5) is separated from the wings (1) and the empennage (9).