阅读说明：本技术 一种具有保护装置的单翼飞行器 (Single-wing aircraft with protection device ) 是由 陈佑明 刘哲 郭锐 于 2020-04-30 设计创作，主要内容包括：本发明属于飞行设备领域,具体涉及一种具有保护装置的单翼飞行器。包括翼片,载物台,动力模块,电源,控制装置和支撑杆；支撑杆上端和载物台下表面连接,电源和控制装置设置在载物台的上表面,支撑杆上设置有多个连杆,翼片通过一个连杆和支撑杆连接,动力模块设置在支撑杆的一个连杆上,翼片所在平面与载物台所在平面形成的二面角投影在垂直于连接两部分的连杆的平面上的平面角为0°到15°；动力模块带动翼片旋转,翼片旋转的中心轴为在一个圆柱形区域内运动的动轴。本申请的飞行器飞行过程中,传感器采集外界信息,控制装置对采集信息进行判断,控制飞行器的启停,且实现恶劣环境下的自我保护。(The invention belongs to the field of flight equipment, and particularly relates to a single-wing aircraft with a protection device. Comprises a wing panel, an object stage, a power module, a power supply, a control device and a support rod; the upper end of the supporting rod is connected with the lower surface of the objective table, the power supply and the control device are arranged on the upper surface of the objective table, the supporting rod is provided with a plurality of connecting rods, the fins are connected with the supporting rod through one connecting rod, the power module is arranged on one connecting rod of the supporting rod, and the plane angle of the dihedral angle projection formed by the plane where the fins are located and the plane where the objective table is located on the plane vertical to the connecting rods connecting the two parts is 0-15 degrees; the power module drives the fins to rotate, and a central shaft of the fin rotation is a moving shaft moving in a cylindrical area. The aircraft of this application flies the in-process, and external information is gathered to the sensor, and controlling means judges the information of gathering, controls opening of aircraft and stops, and realizes the self-protection under the adverse circumstances.)

1. The single-wing aircraft with the protection device is characterized by comprising a wing (1), an object stage (3), a power module, a power supply (7), a control device (8) and a support rod (18);

the upper end of the supporting rod (18) is connected with the lower surface of the objective table (3), the power supply (7) and the control device (8) are arranged on the upper surface of the objective table (3), the supporting rod is provided with a plurality of connecting rods, the fins (1) are connected with the supporting rod (18) through one connecting rod, the power module is arranged on one connecting rod of the supporting rod (18) and provides power for the whole device, and the plane angle of the projection of the dihedral angle formed by the plane where the fins (1) are located and the plane where the objective table (3) is located on the plane perpendicular to the connecting rods (2-2) connecting the two parts is 0-15 degrees; the control device (8) is connected with the power supply (7) and the power module;

the power module drives the wing pieces (1) to rotate, the whole aircraft is thrust in the rotating process, namely, the central shaft of the rotation of the wing pieces (1) is a moving shaft moving in a cylindrical area.

2. The aircraft according to claim 1, characterized in that the wing (1) comprises a main wing (1-1) and a lateral wing (1-2), the lateral wing (1-2) being connected to the lower end face of the main wing (1-1) at the rear;

the main wing (1-1) is fixed relative to the object stage (3), the side wing (1-2) can rotate relative to the main wing, the extending end of the side wing (1-2) is fixedly connected with a connecting shaft, a hole is formed in the extending end of the main wing (1-1), the hole in the main wing is matched with the connecting shaft, a driving device (10) is arranged on the connecting shaft, the driving device (10) is electrically connected with the control device (8), and the side wing (1-2) is driven to rotate by the driving device (10).

3. The aircraft according to claim 2, characterized in that said main wing (1-1) is shaped as an irregular figure consisting of a rectangle and a quarter circle with the short side of the rectangle as the radius, said side wing (1-2) is shaped as an irregular sector, and the profile of the whole wing (1) has a drop profile that is flat, convex upwards.

4. The aircraft according to claim 3, characterized in that a force sensor (12) and a speed sensor (13) are provided on the front side of the main wing (1-1);

the force sensor (12) and the speed sensor (13) are electrically connected with the control device (8).

5. The aircraft according to claim 4, characterized in that the object carrier (3) and the main wing (1-1) are provided with a protection module for protecting the aircraft when it comes to the ground.

6. The aircraft of claim 5, wherein the protection module comprises a cavity opened in the stage or the main wing, a spring disposed in the cavity, and an electric switch;

the electric switch is electrically connected with the control device, one end of the spring is fixedly connected with the cavity wall, and the control device controls the electric switch to be opened and closed, so that the spring is popped out, and the protection effect is achieved.

7. The aircraft according to claim 6, characterized in that the material of the vane (1) is EPP.

8. The aircraft of claim 7, characterized in that the power module comprises a motor (5), a motor mount (4) and a propeller (6);

the electrode is arranged in the motor base, and the motor (5) drives the propeller (6) to rotate so as to drive the fins to rotate.

9. The aircraft of claim 8 wherein the plurality of power modules are arranged in a plurality of groups, the number of power modules being determined based on the object carried by the carrier.

10. The aircraft of claim 9,

the support rod (8) is in threaded connection with the objective table;

the connecting rod is detachably connected with the supporting rod (8) through a connecting piece;

the wing pieces are detachably connected with the connecting rods;

the power module is detachably connected with the connecting rod.

Technical Field

The invention belongs to the field of flight equipment, and particularly relates to a single-wing aircraft with a protection device.

Background

The rotor unmanned aerial vehicle is an aerial robot, belongs to the category of special robots, has the advantages of vertical take-off and landing, hovering, high maneuverability, low cost and the like, and is widely applied to the fields of disaster search and rescue, military reconnaissance, map mapping and the like. Nowadays often can see and develop comparatively ripe for many rotor unmanned aerial vehicle, thereby many rotor unmanned aerial vehicle passes through the motor and drives the rotor and produce thrust. Through changing the relative speed between the different rotors, the size of unipolar propulsive force can be changed to the orbit of control aircraft.

With the development of the unmanned aerial vehicle technology, the concept of a single-rotor unmanned aerial vehicle appears, and CN 109305346a discloses a single-rotor aircraft, which is similar to a helicopter in that a propeller is driven by a motor to generate lift force, but the direction control is realized by a spoiler and other structures of a fuselage, and the single-rotor aircraft does not have stable flight capability and self-protection capability in a hostile environment.

Disclosure of Invention

The invention aims to provide a single-wing aircraft with a protection device, which effectively solves the problems of stable flight and self-protection of a single-wing unmanned aerial vehicle in a harsh environment.

The technical solution for realizing the purpose of the invention is as follows: a single wing aircraft with a protection device comprises a wing panel, an objective table, a power module, a power supply, a control device and a support rod;

the upper end of the supporting rod is connected with the lower surface of the object stage, the power supply and control device is arranged on the upper surface of the object stage, a plurality of connecting rods are arranged on the supporting rod, the fin is connected with the supporting rod through one connecting rod, the power module is arranged on one connecting rod of the supporting rod and provides power for the whole device, and a plane angle formed by a plane where the fin is located and a plane where the object stage is located and projected on a plane vertical to the connecting rods connecting the two parts is 0-15 degrees; the control device is connected with the power supply and the power module;

the power module drives the wing pieces to rotate, the whole aircraft is subjected to thrust in the rotating process, namely, a central shaft of the wing pieces is a moving shaft moving in a cylindrical area.

Further, the wing panel comprises a main wing and a side wing, and the side wing is connected with the rear part of the lower end face of the main wing;

the main wing is fixed relative to the objective table, the side wing can rotate relative to the main wing, the extending end of the side wing is fixedly connected with a connecting shaft, a hole is formed in the extending end of the main wing, the hole in the main wing is matched with the connecting shaft, a driving device is arranged on the connecting shaft, the driving device is electrically connected with the control device, and the side wing is driven to rotate by the driving device.

Furthermore, the main wing is in an irregular pattern consisting of a rectangle and a quarter circle with the short side of the rectangle as the radius, the side wing is in an irregular fan shape, and the side section of the integral wing is a water drop profile which is flat upwards and downwards.

Furthermore, a force sensor and a speed sensor are arranged on the front side surface of the main wing;

the force sensor and the speed sensor are electrically connected with the control device.

Furthermore, the object stage and the main wing are provided with protection modules, and the protection modules are used for protecting the aircraft when the aircraft falls to the ground.

Furthermore, the protection module comprises a cavity arranged on the objective table or the main wing, a spring arranged in the cavity and an electric switch;

the electric switch is electrically connected with the control device, one end of the spring is fixedly connected with the cavity wall, and the control device controls the electric switch to be opened and closed, so that the spring is popped out, and the protection effect is achieved.

Further, the material of the fin is EPP.

Further, the power module comprises a motor, a motor base and a propeller;

the electrodes are arranged in the motor base, and the motor drives the propeller to rotate so as to drive the fins to rotate.

Furthermore, the power modules are in multiple groups, and the number of the power modules is determined according to the object carried by the object carrying table.

Further, the support rod is in threaded connection with the objective table;

the connecting rod is detachably connected with the supporting rod through a connecting piece;

the wing pieces are detachably connected with the connecting rods;

the power module is detachably connected with the connecting rod

Compared with the prior art, the invention has the remarkable advantages that:

(1) according to the single-wing aircraft with the protection device, the propeller and the motor are connected with the objective table through the support device, the wing plates are connected with the objective table, the propeller generates thrust through the driving of the motor, and generates torque relative to the objective table, so that the wing plates are driven to rotate to generate lift force, vertical take-off and landing are realized, and in the flying process, the wing plates rotate around the shaft to enable a certain angle to be generated between the wing plates and the main wing plates so as to change the magnitude and direction of the force, and posture control of the aircraft is realized.

(2) By applying the single-wing aircraft with the protection device, the force sensor transmits external information to the control device in real time, when the external wind speed is too high and the pressure load of the aircraft reaches a bearing value, the control device controls the motor to stop rotating, the aircraft descends, and the uniform descending can be realized in a short time by means of a special structure of the control device; the speed sensor transmits the speed information of the aircraft to the control device, and when the aircraft is in a constant-speed falling state within a specific speed range for 3 seconds, the control device enables the electric switch to be turned on, and the spring is popped up, so that the landing protection function of the aircraft is realized.

Drawings

Fig. 1 is a schematic structural view of the aircraft of the present invention.

FIG. 2 is a schematic view of the airfoil assembly of the present invention.

Fig. 3 is a schematic view of the linkage and stage connection of the present invention.

Description of reference numerals:

1-wing panel, 2-connecting rod, 3-objective table, 4-motor base, 5-motor, 6-propeller, 7-power supply, 8-control device, 10-driving device, 12-force sensor, 13-speed sensor, 14-cavity, 15-electric switch, 1-1-main wing, 1-2-side wing, 2-1 connecting rod I, 2-2 connecting rod II, 17-connecting piece, 18-supporting rod and 19-limiting sleeve.

Detailed Description

The present invention is described in further detail below with reference to the attached drawing figures.

As shown in fig. 1 to 3, the present invention discloses an unmanned aerial vehicle to change the flight direction by the deflection of a spoiler.

Fig. 1 is a schematic structural view of a single-wing aircraft with a protection device according to an embodiment of the invention.

The invention provides a single wing aircraft with a protection device, which comprises a wing panel 1, a connecting rod 2, an object stage 3, a motor base 4, a motor 5, a propeller 6, a power supply 7 and a control device 8.

The propeller 6 provides power for the rotation of the fins 1, and specifically, the propeller 6 can be driven by a power element, and the power element can specifically adopt a motor and the like. A power module with a power element and a propeller 6 is preferably arranged on the connecting rod 2-2.

The wing 1 provides lift for the flight of the aircraft, and particularly, a thrust and a torque are given through a power module on the connecting rod 2-2, the torque enables the wing 1 to rotate, the aircraft is subjected to the thrust in the whole rotating process, namely, the rotating shaft of the wing 1 is a moving shaft fixed in a region, and the force direction is perpendicular to the connecting rod 2-2 at any position of the rotating surface. The upper surface of the wing panel 1 is a convex curved surface, the lower surface is a plane, the plane angle formed by the plane of the wing panel 1 and the plane of the object stage 3 is 0-15 degrees when the projection of the dihedral angle is perpendicular to the plane of the connecting rod 2-2 connecting the two parts, and the flow velocity of the gas above the wing panel 1 is greater than that of the gas below the wing panel to generate lift force. In this embodiment, the wing panel 1 is detachably connected to the stage 3 through the connecting rod 2-2 and the rubber sleeve, and may be connected by other mechanical connection methods as needed.

Under the condition that the aircraft carries different objects, the weight changes, in order to adapt to different aircraft weights, the power module is detachably connected with the connecting rod 2-2 through the motor base 4, namely the power module 20 can move along the connecting rod 2-2, the distance between the power module 20 and the center of the objective table 3 is adjusted through moving the motor base 4 according to the requirements of the aircraft with different weights, and the distance and the thrust provide enough torque for the rotation of the wing pieces 1. The power module 20 and the connecting rods may be provided in a plurality of sets, and are preferably detachably connected to the stage 3.

Objective table 3 is unmanned aerial vehicle's main part bearing structure for connect power module 20, fin 1 and fixed controlling means 8 and the power 7 of placing. The structure, shape, and the like of the stage 3 can be set as needed.

The connecting rod 2 is detachably connected with the object stage 3, preferably the connecting rod 2 is connected with a supporting rod 18 through a connecting piece 17, and clamping and fixing are realized through a limiting sleeve 19. The support bar 18 with a fixing function is preferably arranged at the center of the lower surface of the object stage 3, and is fixedly connected with the object stage 3 by a thread.

The wing panel 1 consists of a main wing 1-1 and a side wing 1-2, the main wing 1-1 is fixed, and the side wing 1-2 can rotate relative to the main wing 1-1. The extending end of the side wing 1-2 is fixedly connected with a shaft, a hole of the extending end of the main wing 1-1 is in transition fit with a connecting shaft, a driving device 10 is arranged on the connecting shaft, and the driving device 10 is electrically connected with a control device 8.

The driving device 10 is used for driving the side wing 1-2 to rotate relative to the main wing 1-1, and in the flying process, the control of the flying path is realized by controlling the rotating angle and the rotating direction of the side wing 1-2 relative to the main wing 1-1. The specific control logic can be determined by means of simulation, experiment and the like.

The force sensor 12 and the speed sensor 13 are electrically connected to the control device 8, and the force sensor 12 and the speed sensor 13 are preferably provided at the front end of the main wing 1-1.

In order to realize stable flight and self-protection in severe environment, the force sensor 12 transmits external information to the control device 8 in real time, when the external wind speed is too high and the pressure load of the aircraft reaches a bearing value, the control device 8 controls the motor 5 to stop rotating, the aircraft falls freely, and the uniform speed descent can be realized in a short time by means of a special structure of the aircraft. The speed sensor 13 transmits the speed information of the aircraft to the control device 8, when the aircraft is in a constant-speed falling state within a specific speed range and lasts for 3 seconds, the control device 8 enables the electric switch 15 to be opened, the spring is popped up, and the landing protection function of the aircraft is realized. The protection modules 30 with the cavities 14 and the springs are preferably arranged at the bottom of the aircraft object table 3 and the main wing 1-1, and the specific number, arrangement and the like of the protection modules 30 can be set as required.

The utility model provides an aircraft, at unmanned aerial vehicle flight in-process, external information is gathered to the sensor, and controlling means judges the information of gathering, and opening of steerable aircraft stops, and in the short time before falling to the ground auto-eject spring, realizes the self-protection under the adverse circumstances condition.