CN110077592B

CN110077592B - Aircraft

Info

Publication number: CN110077592B
Application number: CN201910351809.1A
Authority: CN
Inventors: 王慧; 江飞鸿; 邢蓉
Original assignee: AVIC First Aircraft Institute
Current assignee: AVIC First Aircraft Institute
Priority date: 2019-04-28
Filing date: 2019-04-28
Publication date: 2022-04-01
Anticipated expiration: 2039-04-28
Also published as: CN110077592A

Abstract

The utility model belongs to special-shaped aircraft design field, in particular to aircraft, including fan-shaped lift ware, horizontal drive ware, vertical driver, the end protector, support body and power device, the support body is a polygon prism frame, and fan-shaped lift ware is installed in support body upper portion crossbeam, and vertical drive ware is installed in the vertical roof beam of support body, and horizontal drive ware is installed in support body lower part crossbeam, and fan-shaped lift ware, horizontal drive ware and vertical drive ware pass through the power device drive, and it is rotatory around the corresponding beam axis on the support body, and the end protector is installed in the bight of support body. The aircraft has the advantages of no runway taking off and landing, forward running by means of lateral wind power, self protection when falling, no serious injury to people or objects when colliding, simple, safe and reliable structure, and wide application prospect in transportation, aerial photography and athletic sports.

Description

Aircraft

Technical Field

The application belongs to the design field of special-shaped aircrafts, and particularly relates to an aircraft.

Background

The conventional aircraft generally comprises a fixed-wing aircraft and a rotor aircraft, wherein the fixed-wing aircraft generally comprises a thrust device, a lifting body and a control surface, the structural arrangement of the fixed-wing aircraft is conventional, the thrust device provides horizontal thrust, the lifting body consisting of an aircraft body and a wing surface provides lifting force, the control surface is controlled to adjust the flight attitude, and the take-off and landing need runway environment; rotor crafts often are in helicopter and many rotor unmanned aerial vehicle, and it has the ability of VTOL, through the control to the paddle direction or carry out the attitude adjustment of flying to the control of single screw, but when meetting the influence of natural wind, often can only fight wind-force flight, and its economic nature is relatively poor, simultaneously because the characteristics of self component shape, it can cause fatal injury to people or thing around after the flight is out of control, also can cause the injury of body when falling.

In recent years, consumption-level unmanned aerial vehicles are in the world, and the unmanned aerial vehicles do not need special airports, can take off and land vertically, are easy to operate and the like, and are widely used in short and medium-distance transportation, aerial photography and competitive sports, but the application range of the unmanned aerial vehicles is greatly limited due to the safety problem of runaway and crash. Meanwhile, the energy consumption problem is also obvious in the aspect of long-distance transportation in a windy environment.

Disclosure of Invention

In order to solve at least one of the above technical problems, the present application provides an aircraft.

The application discloses aircraft, including fan-shaped high lift ware, horizontal driver, vertical driver, end protector, support body and power device, the support body is a polygon prism frame, and fan-shaped high lift ware is installed in support body upper portion crossbeam, and vertical driver is installed in support body vertical beam, and horizontal driver installs in support body lower part crossbeam, and fan-shaped high lift ware, horizontal driver and vertical driver pass through the power device drive, and it is rotatory around the corresponding beam axis on the support body, and end protector installs in the bight of support body.

According to at least one embodiment of the present application, the fan-shaped lift-increasing device is a rotating body structure, and fan blades are laid on the outer surface of the fan-shaped lift-increasing device for one circle.

According to at least one embodiment of this application, fan-shaped high lift ware outer fringe is provided with the protecting crust of half circumference cross-section, the protecting crust can be rotatory around corresponding support body upper portion crossbeam.

According to at least one embodiment of the application, the protective shell is driven by an electric motor, the stator windings of which are fixed to the upper cross beam and the rotor windings are integrated with the inner surface of the protective shell.

According to at least one embodiment of the application, the horizontal drive and the vertical drive are of cylindrical tubular construction.

According to at least one embodiment of the present application, the end guard is a ball-shaped structure having elasticity.

According to at least one embodiment of the present application, the power unit is an electric motor, the stator windings of which are fixed to the beam of the frame body, and the rotor windings are combined with the inner surfaces of the horizontal driver, the vertical driver and the sector driver.

According to at least one embodiment of the present application, the aircraft further comprises a wireless transceiver, a controller and an independent power supply, the wireless transceiver receives the control signal, the controller is used for controlling the power plant according to the control signal, and the independent power supply is used for supplying power to the wireless transceiver, the controller and the power plant.

According to at least one embodiment of this application, the middle vacant region of support body is provided with the objective table, wireless transceiver, controller and independent power source set up on the objective table.

According to at least one embodiment of the present application, the frame body is a polygonal frustum frame.

The application has at least the following beneficial technical effects:

the aircraft realizes the vertical and oblique take-off functions by arranging the fan-shaped high lift device, does not need a runway, and does not need a special take-off environment; the additional lift force is obtained by utilizing the Magnus effect through arranging the horizontal driver, and the additional horizontal thrust force is obtained by utilizing the Magnus effect through arranging the vertical driver; the fan-shaped high lift device is internally provided with a protective cover to prevent the fan-shaped high lift device from being damaged and injuring others when falling; the end protector is arranged to prevent the falling protector from being damaged and injuring others; the body has no sharp and prominent high-speed rotating body, the frame body is firm and reliable, and the accident loss can be reduced to the maximum extent; the invention has simple structure, safety and reliability, and has very wide application prospect in transportation, aerial photography and athletic sports.

Drawings

FIG. 1 is a schematic mechanical diagram of the subject aircraft;

FIG. 2 is a schematic diagram of a fan lift-augmenter of the present application;

FIG. 3 is a schematic view of a right quadrangular prism frame of the present invention;

FIG. 4 is a structural diagram of the aircraft with a frame body of a triangular frustum;

wherein:

1-a fan-shaped high lift device; 2-a vertical drive; 3-a horizontal driver; 4-an end guard; 5-frame body; 11-a protective shell; 51-upper cross beam; 52-vertical beams; 53-lower cross beam; 54-corner.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

It should be noted that the magnus effect is a general phenomenon in fluid mechanics, and an object rotating in a fluid is subjected to a specific fluid force, and its scientific explanation is: when the rotational angular velocity vector of a rotating object does not coincide with the flying velocity vector of the object, a lateral force is generated in a direction perpendicular to the plane formed by the rotational angular velocity vector and the translational velocity vector. For example, the motion track of the rotating table tennis ball can drift, the banana ball effect on a football field can occur, and the like. Referring to the magnus effect principle, the application provides an aircraft which can take off and land without a runway, can move forward by means of lateral wind power, can protect itself when falling, and does not cause serious injury to people or objects when colliding with the aircraft.

The aircraft of the present application is described in further detail below with reference to fig. 1-4.

The first embodiment is as follows:

this embodiment is this application aircraft adopts the realization scheme that regular quadrangular prism support body is used for freight transportation, including fan-shaped lift promotion ware 1, horizontal drive ware 3, vertical drive ware 2, end protector 4, support body 5 and power device, support body 5 is a regular quadrangular prism frame, fan-shaped lift promotion ware 1 is installed in 5 upper portion crossbeams 51 of support body, vertical drive ware 2 is installed in support body vertical beam 52, horizontal drive ware 3 is installed in support body lower part crossbeam 53, fan-shaped lift promotion ware 1, horizontal drive ware 3 and vertical drive ware 2 pass through the power device drive, it is rotatory around the corresponding beam axis on the support body 5, end protector 4 is installed in the bight 54 of support body.

Furthermore, the fan-shaped lift-increasing device 1 is a rotator structure, fan blades are laid on the periphery of the outer surface of the fan-shaped lift-increasing device, and the fan-shaped lift-increasing device can provide lift force and lateral thrust in a static windless state of the aircraft.

Further, the outer edge of the fan-shaped high lift device 1 is provided with a protective shell 11 with a semi-circular cross section, and the protective shell can rotate around the corresponding upper cross beam 51 of the frame body 5 and is used for adjusting the windward direction of the aircraft and protecting fan blades of the fan-shaped high lift device 1 from being damaged by foreign matter impact.

Specifically, the protective shell 11 may be rotatably mounted on the upper cross member 51 through a bearing and driven by a motor; wherein the stator windings of the motor are fixed to the upper cross beam 51 and the rotor windings are coupled to the inner surface of the protective shell 11.

Further, the horizontal driver 3 and the vertical driver 2 are cylindrical tubular structures, in particular a hollow rigid foam rod.

Further, the end guard 4 is a spherical structure having elastic cushioning properties, in particular a rigid foam ball.

Further, the power devices of the fan-shaped high lift device 1, the horizontal driver 3 and the vertical driver 2 are electric motors, stator windings of the electric motors are fixed on corresponding beams of the frame body 5 (the fan-shaped high lift device 1 corresponds to the upper cross beam 51, the horizontal driver 3 corresponds to the lower cross beam 53, and the vertical driver 2 corresponds to the vertical beam 52), and the rotor windings are bonded with the inner surfaces of the horizontal driver 3, the vertical driver 2 and the fan-shaped driver 1 through gluing. It should be noted that the high-lift fan 1, the horizontal driver 3 and the vertical driver 2 may be rotatably mounted on corresponding beams of the frame body 5 through bearings.

Through the structure, the vertical drivers 2 can obtain the driving force in the horizontal direction through the Magnus effect under the driving of the motor, and meanwhile, the windward direction and the advancing direction of the aircraft are realized through the rotation speed ratio of the groups of vertical drivers 2; the horizontal drivers 3 can obtain lift force and driving force in the horizontal direction through the Magnus effect under the driving of the motor, the height control and the lateral inclination angle control of the aircraft are realized through rotating speed ratios of the groups of horizontal drivers 3, and the height control and the lateral inclination angle control of the aircraft can be realized with higher precision by combining the rotating speed ratios of the fan-shaped lift-increasing devices 1.

Further, the aircraft also comprises a wireless transceiver, a controller and an independent power supply; the controller can be provided with a gyroscope, an accelerometer, a geomagnetic induction part, an air pressure sensor, an ultrasonic sensor, an optical flow sensor, a GPS module, a control circuit and other parts, and the attitude of the aircraft is controlled by adjusting the output power of a power device of the aircraft through the controller. Specifically, the wireless transceiver receives a control signal, the controller is used for controlling the power device according to the control signal, and the independent power supply is used for supplying power to the wireless transceiver, the controller and the power device.

It should be noted that the wireless transceiver, the controller and the independent power supply can be arranged at suitable locations on the aircraft, for example inside the guards 4, inside the corresponding high lift or drive, etc.; in this embodiment, it is preferable that an object stage is disposed in the middle vacant region of the frame body 5, and the wireless transceiver, the controller and the independent power source may be disposed at corresponding positions on the object stage; in addition, the goods box can be fixed on the article intercepting platform to place other goods.

Example two:

the embodiment is an implementation scheme that the aircraft adopts a triangular platform body frame body for aerial photography, and the actual part of the implementation scheme is the same as that of the embodiment; the support body 5 is a triangular platform body frame, an objective table is arranged in a middle vacant area of the support body 5, and a three-degree-of-freedom aerial photography holder camera can be hung on the lower surface of the objective table.

In summary, the aircraft of the application realizes the vertical and oblique take-off functions by arranging the fan-shaped high lift device without using a runway or a special take-off environment; the additional lift force is obtained by utilizing the Magnus effect through arranging the horizontal driver, and the additional horizontal thrust force is obtained by utilizing the Magnus effect through arranging the vertical driver; the fan-shaped high lift device is internally provided with a protective cover to prevent the fan-shaped high lift device from being damaged and injuring others when falling; the end protector is arranged to prevent the falling protector from being damaged and injuring others; the body has no sharp and prominent high-speed rotating body, the frame body is firm and reliable, and the accident loss can be reduced to the maximum extent; the invention has simple structure, safety and reliability, and has very wide application prospect in transportation, aerial photography and athletic sports.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An aircraft, characterized in that: the fan-shaped lift-increasing device comprises a fan-shaped lift-increasing device (1), a horizontal driver (3), a vertical driver (2), an end protector (4), a frame body (5) and a power device, wherein the frame body (5) is a polygonal prism frame, the fan-shaped lift-increasing device (1) is installed on an upper cross beam (51) of the frame body (5), the vertical driver (2) is installed on a vertical beam (52) of the frame body, the horizontal driver (3) is installed on a lower cross beam (53) of the frame body, the fan-shaped lift-increasing device (1), the horizontal driver (3) and the vertical driver (2) are driven by the power device to rotate around corresponding beam shafts on the frame body (5), and the end protector (4) is installed on a corner (54) of the frame body;

the horizontal driver (3) and the vertical driver (2) are cylindrical tubular structures;

the fan-shaped lift-increasing device (1) is of a rotating body structure, and fan blades are laid on the periphery of the outer surface of the fan-shaped lift-increasing device;

the fan-shaped high lift device (1) is characterized in that the outer edge of the fan-shaped high lift device is provided with a protective shell (11) with a semi-circular cross section, and the protective shell (11) can rotate around a cross beam (51) at the upper part of the corresponding frame body (5).

2. The aircraft according to claim 1, characterized in that said protective shell (11) is driven by an electric motor, the stator windings of which are fixed to the upper cross-member (51), the rotor windings being integrated with the inner surface of said protective shell (11).

3. The aircraft according to claim 1, characterized in that said end guards (4) are spherical structures with elasticity.

4. The aircraft according to any of the claims from 1 to 3, characterised in that the power plant is an electric motor, the stator windings of which are fixed to the beams of the frame (5) and the rotor windings are coupled to the inner surfaces of the horizontal drive (3), the vertical drive (2) and the sectorial high lift (1).

5. The aircraft of claim 4, further comprising a wireless transceiver that receives the control signal, a controller for controlling the power plant in accordance with the control signal, and an independent power source for powering the wireless transceiver, controller, and power plant.

6. The aircraft of claim 5, characterized in that the intermediate vacant area of the rack (5) is provided with an object stage on which the wireless transceiver, the controller and the independent power supply are provided.

7. The aircraft according to claim 1, characterized in that said frame body (5) is a polygonal frustum frame.