CN113371182A

CN113371182A - Barrel-type transmitted reconnaissance attack rotor unmanned aerial vehicle

Info

Publication number: CN113371182A
Application number: CN202110453034.6A
Authority: CN
Inventors: 牛三库; 高学勤; 阎雪飞
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-04-26
Filing date: 2021-04-26
Publication date: 2021-09-10

Abstract

The invention discloses a drum-type launching reconnaissance attack rotor unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, wherein the unmanned aerial vehicle body is sequentially provided with a load cabin, a machine body cabin and a bottom cabin from top to bottom, an upper partition plate is arranged between the load cabin and the machine body cabin, and a lower partition plate is arranged between the machine body cabin and a base cabin; a sensing load or a guide head such as a camera is loaded in the load cabin; a rotor arm fixing seat is arranged in the machine body cabin and is movably connected with the rotor arm; and a power supply module and a time schedule controller are arranged in the base cabin, wherein the power supply module is electrically connected with the time schedule controller. The invention is convenient to be deployed in narrow roadways and semi-closed cavities; the system can be deployed in the field, in the environment of full building waste after disasters or wars; the unmanned aerial vehicle has the functions of vertical launching, cruising operation flying and high-speed attack, and can be expanded or simplified according to actual needs, so that the unmanned aerial vehicle can be more suitable for different task demand scenes.

Description

Barrel-type transmitted reconnaissance attack rotor unmanned aerial vehicle

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a barrel-type launching reconnaissance attack rotor unmanned aerial vehicle.

Background

The rotor craft has the advantages of hovering, closed space flight, dense obstacle area obstacle avoidance and the like. Common rotary-wing aircraft are coaxial helicopters, quad-rotor aircraft, and multi-rotor aircraft. Before the rotor aircraft is deployed in flight, generally, the rotor aircraft needs to be placed on a horizontal table board, a system is powered on, a propeller rotates to generate lift force, and the aircraft body gradually rises to a specific height to perform flight operation.

In the dense urban environment of building, rotor unmanned aerial vehicle has the technological advantage that is difficult to replace:

1) narrow tunnel and closed semi-closed environment release

In various narrow channels and closed semi-closed cavity environments in urban areas, the fixed wing unmanned aerial vehicle is difficult to apply in the environments due to the initial shooting angle and a certain climbing distance. And the unmanned gyroplane is easier to adapt to the environment due to the hovering characteristic of the unmanned gyroplane.

2) Small turning radius

The minimum turning radius of the fixed-wing flight is 100-500m due to the fixed cruising flight speed and the limited flight rolling angle, and the turning radius is difficult to deal with dense building obstacles in urban areas. And the specific fixed-point steering function of the rotor unmanned aerial vehicle can easily realize in-situ 360-degree turning.

Conventional rotorcraft are typically carried in a box or case, manually removed before use, placed horizontally on the ground, activated, and released.

Thus, in special cases, rotorcraft are difficult to release or convenient to use. These include:

1) high speed mobile platform deployment problem

Such as on high-speed moving vehicles and aircraft, strong lateral aerodynamic forces are generated due to the relatively high moving speed of the moving platform. Rotorcraft take-off at zero initial speed can be subject to attitude disturbances caused by the lateral aerodynamic forces of the moving vehicle and the aircraft. As the speed of movement of the vehicle and aircraft increases, this disturbance will gradually increase until the rotorcraft crashes.

2) Post-disaster and post-war complex terrain area deployment problem

In the complex terrain areas after disasters and wars, because the ground is full of building rubbles and the like, the complex terrain areas do not have basic flatness and levelness, and suitable areas for the deployment of the rotor craft are difficult to find.

3) Cluster deployment problem

When a large number of existing rotor crafts are deployed for cluster performance, a whole smooth place needs to be found. As the size and cluster size of rotorcraft continues to increase, the size of the field also increases, and flatness and levelness in different areas is difficult to ensure. Excessive differences in flatness and levelness can limit the number of clusters and the size of the rotorcraft.

4) Portable storage, transportation and issue questions

Traditional multi-rotor aircraft occupy a large transverse space, are generally stored in boxes for storage and transportation, and need to be taken out of the storage boxes in use. The problem is that the box type storage occupies a large transverse space and the using process is time-consuming. Especially when used on a large scale, the method is time-consuming, labor-consuming and inconvenient. In addition, standard ammunition in the world usually adopts a barrel launching platform, and the application mode is very mature no matter the ammunition is carried by an individual soldier, is placed on a vehicle or is placed on a machine.

In addition, the flight speed of traditional rotor unmanned aerial vehicle self is than lower, is unfavorable for the promotion to the attack precision of wind disturbance and maneuvering target.

Disclosure of Invention

In order to solve the technical problem that the rotor unmanned aerial vehicle is inconvenient to use in the prior art, the invention provides a cylinder type launching reconnaissance attack rotor unmanned aerial vehicle.

In order to achieve the purpose, the invention provides the following technical scheme:

a drum-type launching reconnaissance attack rotor unmanned aerial vehicle comprises an unmanned aerial vehicle body and is characterized in that the unmanned aerial vehicle body is sequentially provided with a load cabin, a machine body cabin and a bottom cabin from top to bottom, wherein an upper partition plate is arranged between the load cabin and the machine body cabin, and a lower partition plate is arranged between the machine body cabin and a base cabin;

the wind cap is arranged above the load cabin, and an information perception processing module or a biological information perception module or a nuclear physics information perception module or a guidance tracking module is arranged in the load cabin and used for storing the obtained information or transmitting the obtained information to other equipment;

a plurality of windows are formed in the side wall of the machine body cabin, and a rotor wing arm fixing seat is arranged in the machine body cabin; the rotor arm fixing seat is arranged at the bottom of the engine body cabin, a fixing block is arranged on the rotor arm fixing seat, and the fixing block is fixedly connected with the side wall of the engine body cabin; the rotor wing arm fixing seat is provided with a connecting piece corresponding to the window, wherein the connecting piece is movably connected with the rotor wing arm through a pin shaft; the bottom end of the rotor wing arm is movably connected with the rotor wing arm fixing seat, and the top end of the rotor wing arm is provided with a motor mounting box; an upper rotor motor and a lower rotor motor are respectively arranged in the motor mounting box, wherein a rotating shaft of the upper rotor motor is fixedly connected with an upper rotor hub, and two ends of the upper rotor hub are provided with upper rotors; a rotating shaft of the lower rotor motor is fixedly connected with a lower rotor hub, and two ends of the lower rotor hub are provided with lower rotors;

the bottom cabin is made of materials with high structural strength and high magnetic conductance rate, and a power supply module and a time sequence controller are arranged in the bottom cabin; the power module is electrically connected with the time schedule controller and is connected with the upper rotor motor and the lower rotor motor.

Preferably, the rotor arm fixing seat is provided with a plurality of connecting pieces, wherein each connecting piece corresponds to a window on the side wall of the machine body cabin; the rotor arms are provided with a plurality of rotor arms, wherein each rotor arm is movably connected with a connecting piece; a circle of nylon belts are hooped outside the rotor arms, wherein the nylon belts are sleeved with electric heating wires; the heating wire is connected with the time schedule controller, and the time schedule controller supplies power to the heating wire through the control power module.

Preferably, a spring piece is arranged above the bottom end of the rotor arm and fixedly connected with the connecting piece; rotor arm bottom below has seted up the location locked groove, wherein lower baffle upper end is equipped with the fixed hasp that corresponds with the location locked groove, wherein fixed hasp and location locked groove block.

Preferably, the junction of the upper rotor and the upper rotor hub is provided with an upper rotor spring piece, and the junction of the lower rotor and the lower rotor hub is provided with a lower rotor spring piece.

Preferably, the timing controller receives external setting information including but not limited to time, relative and absolute position, speed, overload, attitude, angular rate and through alignment information, and the timing controller is used for receiving external wall synchronous and asynchronous instructions in batch, wherein the instructions are received in a UART/CAN/MAVLINK or 4G/5G form.

Preferably, the drone body comprises a projectile configuration and a rotor flight configuration, wherein the rotor flight configuration comprises a cruise flight attitude and an attack flight attitude; the last rotor on the rotor arm provides flight lift for the unmanned aerial vehicle body in the flight attitude of cruising, attacks the lower rotor on the rotor arm in the flight attitude and provides attack power, and the function of going up rotor and lower rotor is interchangeable.

Preferably, the missile body shape of the unmanned aerial vehicle body and the flight shape of the rotor wing can be quickly converted, wherein the included angle range of the unmanned aerial vehicle body between the central axis of the missile body shape and the vertical direction is-45 degrees to +45 degrees, and the course angle range is-45 degrees to +45 degrees; unmanned aerial vehicle body form flight and rotor flight form flight, the axis contained angle of this unmanned aerial vehicle body is 120 ~ 240, and wherein the barycenter that unmanned aerial vehicle body form conversion becomes rotor flight form is located the position before organism cabin to hood top, and unmanned aerial vehicle body pressure core is located the organism cabin position between the passenger cabin to the end.

Preferably, the unmanned aerial vehicle body is converted into an attacking flight attitude, and a lower rotor motor on a rotor arm drives a lower rotor to generate a plurality of thrust points in the same direction as the gravity direction of the unmanned aerial vehicle body; the unmanned aerial vehicle body axis and the vertical direction form a zeta angle, the zeta angle range is minus 45 degrees to plus 45 degrees, attack is carried out along the circumference at a psi angle, and the psi angle range is minus 180 degrees to plus 180 degrees; the acceleration range that rotor provided a plurality of impetus to produce down is 0 ~ 10g (g is 9.8 m/s) on the unmanned aerial vehicle body²) The attack speed range of the unmanned aerial vehicle body is 0-300 km/h.

Preferably, the unmanned aerial vehicle body uses the launching tube as the launch carrier, and wherein the unmanned aerial vehicle body is high-pressure gas transmission or electromagnetic emission.

Preferably, unmanned aerial vehicle body external diameter is 10 ~ 300mm, and wherein unmanned aerial vehicle body length is 40 ~ 2000 mm.

Compared with the prior art, the invention has the following beneficial effects:

1) the device is convenient for throwing in static and high-speed motion carrying platforms such as individual soldiers, vehicles, aircrafts and the like, and can be deployed in narrow tunnels and semi-closed cavities;

2) the system can be deployed in the field, in the environment of full building waste after disasters or wars;

3) the device has the functions of vertical launching, cruising operation flying and high-speed attack.

According to the invention, the functional modules of the unmanned aerial vehicle can be expanded or simplified according to actual needs, namely, the unmanned aerial vehicle can expand or simplify the functions more conveniently, so that the unmanned aerial vehicle can adapt to different task demand scenes; thereby unmanned aerial vehicle's user experience has been improved.

Drawings

Fig. 1 is a schematic perspective view of the retraction of a rotor arm of an unmanned aerial vehicle according to the present invention;

FIG. 2 is a schematic view of the configuration of the unmanned aerial vehicle according to the present invention with the rotor arms retracted;

FIG. 3 is a cross-sectional view of the structure A-A shown in FIG. 2;

FIG. 4 is a schematic structural view of a rotor arm fixing base of the unmanned aerial vehicle of the present invention;

FIG. 5 is a schematic structural view of a rotor arm and a rotor of the unmanned aerial vehicle according to the present invention;

FIG. 6 is a schematic structural view of a nylon band cinching rotor arm of the present invention;

fig. 7 is a schematic perspective view of the unmanned aerial vehicle rotor arm of the present invention;

FIG. 8 is a schematic view of the unmanned aerial vehicle rotor arm in front view configuration with the present invention deployed;

FIG. 9 is a cross-sectional view of the structure of B-B shown in FIG. 8;

FIG. 10 is a schematic view of the unmanned aerial vehicle rotor of the present invention deployed;

FIG. 11 is a schematic view of the flight condition of the present invention;

fig. 12 is a schematic view of the working state of the present invention.

The reference numbers illustrate: 1-a drone body, 2-a load cabin, 3-a body cabin, 4-a bottom cabin, 5-an upper partition, 6-a lower partition, 7-a wind cap, 8-an information perception processing module, 9-a window, 10-a rotor arm fixing base, 11-a fixing block, 12-a connecting piece, 13-a rotor arm, 14-a motor mounting box, 15-an upper rotor motor, 16-a lower rotor motor, 17-an upper rotor hub, 18-an upper rotor, 19-a lower rotor hub, 20-a lower rotor, 21-a power supply module, 22-a timing controller, 23-a leaf spring, 24-a positioning lock slot, 25-a fixing lock catch, 26-a nylon belt, 27-an electric heating wire, 28-an upper rotor leaf spring, 29-a lower rotor leaf spring.

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.

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

In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

The present invention will be described in further detail with reference to the accompanying drawings.

Referring to fig. 1 to 10, a drum-type launch reconnaissance attack rotor unmanned aerial vehicle includes an unmanned aerial vehicle body 1, the unmanned aerial vehicle body 1 has an outer diameter of 10 to 300mm, wherein the unmanned aerial vehicle body 1 has a length of 40 to 2000 mm; the unmanned aerial vehicle body 1 is sequentially provided with a load cabin 2, a machine body cabin 3 and a bottom cabin 4 from top to bottom, wherein an upper partition plate 5 is arranged between the load cabin 2 and the machine body cabin 3, and a lower partition plate 6 is arranged between the machine body cabin 3 and the base cabin 4;

an air cap 7 is arranged above the load cabin 2, and an information perception processing module 8 or a biological information perception module or a nuclear physics information perception module or a guidance tracking module is arranged in the load cabin 2 and used for storing the obtained information or transmitting the obtained information to other equipment;

a plurality of windows 9 are arranged on the side wall of the machine body cabin 3, and a rotor arm fixing seat 10 is arranged in the machine body cabin 3; the rotor arm fixing seat 10 is arranged at the bottom of the machine body cabin 3, a fixing block 11 is arranged on the rotor arm fixing seat 10, and the fixing block 11 is fixedly connected with the side wall of the machine body cabin 3; a connecting piece 12 is arranged at the position of the rotor arm fixing seat 10 corresponding to the window 9, wherein the connecting piece 12 is movably connected with a rotor arm 13 through a pin shaft; the bottom end of the rotor arm 13 is movably connected with the rotor arm fixing seat 10, and the top end of the rotor arm 13 is provided with a motor mounting box 14; an upper rotor motor 15 and a lower rotor motor 16 are respectively arranged in the motor mounting box 14, wherein a rotating shaft of the upper rotor motor 15 is fixedly connected with an upper rotor hub 17, and upper rotors 18 are arranged at two ends of the upper rotor hub 17; a lower rotor hub 19 is fixedly connected to a rotating shaft of the lower rotor motor 16, and lower rotors 20 are arranged at two ends of the lower rotor hub 19;

the base cabin 4 is made of materials with high structural strength and high magnetic flux conductivity, a power module 21 and a time schedule controller 22 are arranged in the base cabin 4, the power module 21 is electrically connected with the time schedule controller 22, and the power module 21 is connected with the upper rotary wing motor 15 and the lower rotary wing motor 16.

In the embodiment, the initial state of the unmanned aerial vehicle body 1 is in a projectile body shape, the rotor arms 13, the upper rotor wings 18 and the lower rotor wings 20 are all folded in the body cabin 3, and the unmanned aerial vehicle body 1 is adjusted to be in a minimum shape so as to be conveniently transported in a centralized manner or carried by an individual soldier and can be launched on a static and high-speed motion carrying platform such as an individual soldier, a vehicle-mounted platform and a vehicle-mounted platform; the time sequence controller 22 in the unmanned aerial vehicle body 1 can receive a state mode command input to the unmanned aerial vehicle by a user through a remote controller, and controls the rotor arms 13, the upper rotor 18 and the lower rotor 20 to switch the forms according to the state mode command, wherein the state mode command can be a flight mode; specifically, the flight mode can realize that rotor arm 13 and upper rotor 18, lower rotor 20 all expand, switch into many rotor forms with unmanned aerial vehicle body 1 by initial projectile body form, realize unmanned aerial vehicle air flight, carry out the flight task.

Go up rotor 18 and upper rotor motor 15 and lower rotor 20 and lower rotor motor 16 and set up respectively in rotor arm 13 upper and lower both sides, according to the task demand of difference, can adjust corresponding configuration, for example: only use upper rotor motor 15, upper rotor 18 and rotor arm 13, or only use lower rotor motor 16, lower rotor 20 and rotor arm 13, as long as do not influence unmanned aerial vehicle body 1 operation cruise and attack function, can adjust different configurations according to different task demands.

Power module 21 mainly used provides the power, and it can be understood that power module 21 can supply power for each part in unmanned aerial vehicle body 1 to each part can be switched on with normal work operation in the unmanned aerial vehicle body 1.

The timing controller 22 receives external setting information including, but not limited to, time, relative and absolute position, speed, overload, attitude, angular rate, so as to define environmental information such as time, relative and absolute position, speed, overload, attitude, angular rate, etc. in the process of converting the unmanned aerial vehicle body 1 from the projectile form to the multi-rotor state. Specifically, the timing controller 22 receives a state mode command input by a user through a UART/CAN/MAVLINK or other signal transmission method (e.g., a voice input method) in a 4G/5G format, analyzes a mode corresponding to the state mode command according to the state mode command, and controls the drone body 1 according to the mode corresponding to the state mode command.

It should be noted that the timing controller 22 can be used to control the power module 21 to start and stop supplying power, and the timing controller 22 can be used to control the upper rotor motor 15 and the lower rotor motor 16 to start supplying power and stop supplying power to the plurality of upper rotors 18 and the plurality of lower rotors 20.

Furthermore, a plurality of connecting pieces 12 are arranged on the rotor arm fixing seat 10, wherein each connecting piece 12 corresponds to the window 9 on the side wall of the machine body cabin 3; the number of the rotor arms 13 is multiple, wherein each rotor arm 13 is movably connected with a connecting piece 12; a circle of nylon belts 26 is hooped outside the rotor arms 13, wherein the nylon belts 26 are sleeved with heating wires 27; the heating wire 27 is connected with the timing controller 22, wherein the timing controller 22 supplies power to the heating wire 27 through the control power module 21.

In this embodiment, the symmetry sets up four windows 9 that are used for rotor arm 13 to expand around organism cabin 3, because of rotor arm 13 and rotor arm fixing base 10 are articulated through the round pin axle, in order to make things convenient for rotor arm 13 to use the round pin axle to expand outward through window 9 as the axle center to drive rotor motor 15, upper rotor 18 and lower rotor motor 16, lower rotor 20 and expand outward, make unmanned aerial vehicle body 1 switch into the four rotors form by the projectile form.

A plurality of rotor arms 13 draw in folding in organism cabin 3, establish the nylon tape 26 that has heating wire 27 through hooping outside a plurality of rotor arms 13, wherein nylon tape 26 can set up many, makes the adjustment of unmanned aerial vehicle body 1 be the projectile body form of minimum to in concentrated transportation or individual soldier carry. When the timing controller 22 receives the status mode command, the timing controller 22 may control the power module 21 to start supplying power to the heating wire 27, and when the heating wire 27 is heated to melt the nylon 26 band, the power module 21 stops supplying power.

Furthermore, a spring piece 23 is arranged above the bottom end of the rotor wing arm 13, and the spring piece 23 is fixedly connected with the connecting piece 12; a positioning lock groove 24 is formed below the bottom end of the rotor arm 13, a fixed lock catch 25 is arranged on the lower partition plate 6, the fixed lock catch 25 corresponds to the positioning lock groove 24, and the fixed lock catch 25 is clamped with the positioning lock groove 24.

In this embodiment, a spring piece 23 is disposed between the bottom end of the rotor arm 13 and the connecting member 12, and the spring piece 23 mainly plays a role in springing the rotor arm 13 outwards from the inside of the nacelle 3, wherein the spring piece 23 is in a vertically bent state when the rotor arm 13 is folded, and the spring piece 23 is in a horizontal state when the rotor arm 13 is unfolded; when the rotor arms 13 are spread outward by the spring pieces 23, the positioning lock grooves 24 below the bottom ends of the rotor arms 13 are engaged with the fixing locks 25 on the lower partition 6, thereby fixing the rotor arms 13.

Furthermore, an upper rotor leaf spring 28 is arranged at the joint of the upper rotor 18 and the upper rotor hub 17, and a lower rotor leaf spring 29 is arranged at the joint of the lower rotor 20 and the lower rotor hub 19.

In this embodiment, the upper rotor leaf spring 28 is mainly used to unfold the upper rotor 18 from the folded state to the horizontal state by the action of the elastic force, and the lower rotor leaf spring 29 is mainly used to unfold the lower rotor 20 from the folded state to the horizontal state by the action of the elastic force, so that the main body 1 of the unmanned aerial vehicle is switched from the missile state to the rotor flight state.

Further, the unmanned aerial vehicle body 1 comprises a projectile body form and a rotor wing flight form, wherein the rotor wing flight form comprises a cruise flight attitude and an attack flight attitude; the upper rotor 18 on the rotor arm 13 rotates in the cruising flight attitude to provide the flight lift force for the unmanned aerial vehicle body 1, the lower rotor 20 on the rotor arm 13 rotates in the attacking flight attitude to provide the attacking power for the unmanned aerial vehicle body 1, and the functions of the upper rotor 18 and the lower rotor 20 are interchangeable.

Furthermore, the missile body shape of the unmanned aerial vehicle body 1 and the flight shape of the rotor wing can be quickly converted, wherein the included angle range of the central axis of the unmanned aerial vehicle body 1 in the missile body shape flight and the vertical direction is-45 degrees to +45 degrees, and the course angle range is-45 degrees to +45 degrees; after the transmission of unmanned aerial vehicle body 1, the axis that its body form was flown and the axis contained angle scope that the rotor flight form was flown are 120 ~ 240, wherein unmanned aerial vehicle body 1 is the twinkling of an eye of rotor flight form by the conversion of body form, and 1 barycenter of unmanned aerial vehicle body is located organism cabin 3 to the position before 7 tops of hood, and 1 heart of pressure of unmanned aerial vehicle body is located organism cabin 3 position between 4 cabins of passenger cabin on the bottom.

Further, the unmanned aerial vehicle body 1 is converted from a cruise flight attitude to an attack flight attitude, and the lower rotor motor 16 on the rotor arm 13 drives the lower rotor 20 to generate a plurality of pushing force points in the same direction as the gravity direction of the unmanned aerial vehicle body 1; the unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, a horizontal shaft, a vertical shaft, a horizontal; the acceleration scope that rotor 20 provided a plurality of impetus to produce on the unmanned aerial vehicle body down is 0 ~ 10g (g is 9.8 m/s)²) The attack speed range of the unmanned aerial vehicle body is 0-300 km/h.

Further, an information perception processing module 8 or a biological information perception module or a nuclear physics information perception module or a guidance tracking module is arranged in the load cabin 2 and used for storing the obtained information or transmitting the obtained information to other equipment, and monitoring, interfering or damaging the target according to a specific instruction.

In this embodiment, the load devices installed in the load compartment 2 are connected to the timing controller 22 in the base cabin 4, depending on the task requirements, for example: when the unmanned aerial vehicle body 1 needs to execute a reconnaissance task, the load cabin 2 can carry the information perception processing module 8 so as to be used for reconnaissance, and the information perception processing module 8 is connected with the time sequence controller 22 and used for collecting images; when the unmanned aerial vehicle body 1 needs to execute a flight battle task, the load chamber 2 can carry battle components (such as ammunition) and is connected with the time sequence controller 22 through the guidance tracking module so as to attack by using the battle components; when unmanned aerial vehicle body 1 need carry out the information antagonism, load cabin 2 can carry the electronic interference equipment, is connected with time schedule controller 22 through biological information perception module to be used for the information antagonism, carry out the extension of function module or retrench to unmanned aerial vehicle body 1 according to actual need, make unmanned aerial vehicle body 1 can adapt to different task demand scenes more.

Referring to fig. 11 and 12, when the rotor unmanned aerial vehicle of the present invention is in operation:

the transmission of unmanned aerial vehicle body 1 is the cylinder transmission, and during the transmission, unmanned aerial vehicle body 1 receives gunpowder burning gas or the effect of electromagnetism impetus in the launch canisterThe launching canister generates high overload acting force to push the unmanned aerial vehicle body 1 to fly away quickly, wherein the overload numerical range of the unmanned aerial vehicle body 1 is 10-2000g (g is 9.8 m/s)²) The included angle range of the launching tube and the vertical plumb line is-45 degrees to +45 degrees, and the course angle range is-45 degrees to +45 degrees; after the unmanned aerial vehicle body 1 is separated from the launching canister, the unmanned aerial vehicle body 1 flies along an approximately inertial trajectory motion track in a projectile body shape within specific time, distance, speed, posture and other environmental variables; meanwhile, the time schedule controller 22 triggers the time schedule controller 22 according to the time, relative and absolute position, speed, overload, attitude, angular rate and other environmental information characteristics in the flying process of the unmanned aerial vehicle body 1, the time schedule controller 22 controls the power module 21 to heat the electric heating wire 27, the nylon belt 26 is fused, the spring leaf 23 arranged at the joint of the bottom end of the rotor arm 13 and the rotor arm fixing seat 10 pushes the rotor arm 13 to expand outwards by taking the pin shaft as the axis under the elastic action, the expanding process is enhanced along with the gravity action of the rotor arm 13 and the upper rotor motor 15, the lower rotor motor 16 and the air thrust action of the rotor arm 13, the upper rotor motor 15 and the lower rotor motor 16, when the rotor arm 13 is expanded to the position vertical to the axis of the unmanned aerial vehicle body 1, the positioning lock groove 24 at the bottom end of the rotor arm 13 is matched and locked with the fixing lock catch 25 at the upper end of the lower partition plate 6, the unmanned aerial vehicle body 1 is converted into a rotor flight form from a projectile form; after the unmanned aerial vehicle body 1 starts to launch the barrel, along with the expansion of the rotor arm 13, the upper rotor 18 and the lower rotor 20 are under the action of pneumatic resistance, so that the pressure center acting on the unmanned aerial vehicle body 1 moves towards the bottom cabin 4, the mass center moves towards the direction of the engine body cabin 3, the pressure center is close to the back by the transfer of the upper rotor 18 and the lower rotor 20, the mass center is close to the front, the unmanned aerial vehicle body 1 stably flies, and the head of the unmanned aerial vehicle body 1 gradually lowers downwards and tends to be vertical, so that the stability of the unmanned aerial vehicle body 1 in the form change process is ensured; when the rotor arms 13 are fully deployed, the upper rotor 18 is deployed on the upper rotor hub 17 via the upper rotor leaf spring 28, and the lower rotor 20 is deployed on the lower rotor hub 19 via the lower rotor leaf spring 29; meanwhile, the timing controller 22 controls the power module 21 to start supplying power to the upper rotor motor 15 and the lower rotor motor 16, so that the upper rotor motor 15 supplies power to the upper rotor 18 and the lower rotor motor 16 supplies power to the lower rotor motor 16The lower rotor 20 provides power; when the head of the unmanned aerial vehicle body 1 tends to be vertical, the upper rotor wings 18 stop rotating, the lower rotor wings 20 start to rotate to generate upward tension, so that the gravity of the unmanned aerial vehicle body 1 is balanced, besides, the multiple groups of lower rotor wings 20 can drive the unmanned aerial vehicle body 1 to adjust the operation height, the flight speed and the flight attitude, and the unmanned aerial vehicle body 1 can operate and fly in a rotor wing flight form; when attacking the target, the lower rotor 20 stall of unmanned aerial vehicle body 1, go up rotor 18 and begin to rotate and produce a plurality of thrust points the same with 1 gravity direction of unmanned aerial vehicle body, it is high-speed target that is close with specific gesture to promote unmanned aerial vehicle body 1, wherein, 1 axis of unmanned aerial vehicle body is zeta angle with vertical direction, this zeta angle scope is-45- +45, it attacks to be psi angle along the circumference, wherein psi angle scope is-180- +180, the acceleration scope that a plurality of thrust produced on unmanned aerial vehicle body 1 is 0 ~ 10g (g is 9.8 m/s)²) The attack speed range of the unmanned aerial vehicle body 1 is 0-300 km/h.

The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims

1. A drum-type launching reconnaissance attack rotor unmanned aerial vehicle comprises an unmanned aerial vehicle body and is characterized in that the unmanned aerial vehicle body is sequentially provided with a load cabin, a machine body cabin and a bottom cabin from top to bottom, wherein an upper partition plate is arranged between the load cabin and the machine body cabin, and a lower partition plate is arranged between the machine body cabin and a base cabin;

the blast cap is arranged above the load cabin, and an information perception processing module or a biological information perception module or a nuclear physics information perception module or a guidance tracking module is arranged in the load cabin and used for storing the obtained information or transmitting the obtained information to other equipment;

a plurality of windows are formed in the side wall of the machine body cabin, and a rotor wing arm fixing seat is arranged in the machine body cabin; the rotor arm fixing seat is arranged at the bottom of the engine body cabin, and is provided with a fixing block, wherein the fixing block is fixedly connected with the side wall of the engine body cabin; the rotor wing arm fixing seat is provided with a connecting piece corresponding to the position of the window, wherein the connecting piece is movably connected with the rotor wing arm through a pin shaft; the bottom end of the rotor wing arm is movably connected with the rotor wing arm fixing seat, and the top end of the rotor wing arm is provided with a motor mounting box; an upper rotor motor and a lower rotor motor are respectively arranged in the motor mounting box, wherein a rotating shaft of the upper rotor motor is fixedly connected with an upper rotor hub, and two ends of the upper rotor hub are provided with upper rotors; a rotating shaft of the lower rotor motor is fixedly connected with a lower rotor hub, and two ends of the lower rotor hub are provided with lower rotors;

the bottom cabin is made of materials with high structural strength and high magnetic conductance rate, and a power supply module and a time sequence controller are arranged in the bottom cabin; the power module is electrically connected with the time schedule controller and is connected with the upper rotary wing motor and the lower rotary wing motor.

2. The drum-type launch reconnaissance attack rotor unmanned aerial vehicle of claim 1, wherein the rotor arm mounts are provided with a plurality of connectors, each of which corresponds to a window in a sidewall of the nacelle; the rotor arms are provided with a plurality of rotor arms, wherein each rotor arm is movably connected with a connecting piece; a circle of nylon belts is hooped outside the rotor arms, wherein the nylon belts are sleeved with electric heating wires; the heating wire is connected with the time schedule controller, and the time schedule controller supplies power to the heating wire through the control power module.

3. The drum-type launch reconnaissance attack rotor unmanned aerial vehicle of claim 2, wherein a spring plate is arranged above the bottom end of the rotor arm, and the spring plate is fixedly connected with the connecting piece; rotor arm bottom below has seted up the location locked groove, wherein lower baffle upper end is equipped with the fixed hasp that corresponds with the location locked groove, wherein fixed hasp and location locked groove block.

4. The drum-launch reconnaissance attack rotor-wing drone of claim 1, wherein an upper rotor leaf spring is provided at a junction of the upper rotor and the upper rotor hub, and a lower rotor leaf spring is provided at a junction of the lower rotor and the lower rotor hub.

5. A drum launch, reconnaissance attack rotorcraft as claimed in claim 1 wherein the timing controller receives external, fixed information including but not limited to time, relative and absolute position, speed, overload, attitude, angular rate and through-pilot alignment information, and receives external wall synchronous and asynchronous commands in bulk in the form of UART/CAN/MAVLINK or 4G/5G.

6. The drum launch, reconnaissance attack rotor drone of claim 1, wherein the drone body comprises a projectile configuration and a rotor flight configuration, wherein the rotor flight configuration comprises a cruise flight attitude and an attack flight attitude; the upper rotor on the rotor arm provides flight lift for the unmanned aerial vehicle body in the flight attitude that cruises, and the lower rotor on the rotor arm provides attack power in the attack flight attitude, and the function of upper rotor and lower rotor is interchangeable.

7. The drum-type launch reconnaissance attack rotor unmanned aerial vehicle of claim 6, wherein the missile body configuration of the unmanned aerial vehicle body and the rotor flight configuration can be rapidly switched, wherein the angle between the central axis of the missile body configuration flight and the vertical direction ranges from-45 ° to +45 °, and the course angle ranges from-45 ° to +45 °; unmanned aerial vehicle body form flight and rotor flight form flight, the axis contained angle of its unmanned aerial vehicle body is 120 ~ 240, and wherein the barycenter that unmanned aerial vehicle body form conversion was rotor flight form is located the position before organism cabin to the hood top, and unmanned aerial vehicle body pressure heart is located the organism cabin position between the passenger cabin to the end.

8. The drum-launch reconnaissance attack rotor drone of claim 6, wherein the rotor flight configuration of the drone body is converted to an attack flight attitude, wherein the lower rotor motor at the top end of the rotor arm drives the lower rotor to generate a plurality of thrust points in the same direction as the direction of gravity of the drone body; the unmanned aerial vehicle body axis forms a zeta angle with the vertical direction, the zeta angle range is minus 45 degrees to plus 45 degrees, attack is carried out along the circumference at a psi angle, and the psi angle range is minus 180 degrees to plus 180 degrees; the acceleration scope that the rotor provided a plurality of propulsion to produce on the unmanned aerial vehicle body down is 0 ~ 10g, and the attack speed scope of this unmanned aerial vehicle body is 0 ~ 300 km/h.

9. The drum-type launching reconnaissance attack rotor unmanned aerial vehicle of claim 1, wherein the unmanned aerial vehicle body uses a launch drum as a launch carrier, wherein the unmanned aerial vehicle body is high-pressure gas launch or electromagnetic launch.

10. The drum-type launching reconnaissance attack rotor unmanned aerial vehicle as claimed in claim 1, wherein the unmanned aerial vehicle body is a cylinder, a rectangular cuboid, a hexagonal cuboid or other polygonal cuboids, the outer diameter of the unmanned aerial vehicle body is 10-300 mm, the length of the unmanned aerial vehicle body is 40-2000 mm, and the length of the unmanned aerial vehicle body is not more than 52 times of the diameter of the unmanned aerial vehicle body.