CN218198847U - Fixed wing unmanned aerial vehicle with VTOL function - Google Patents

Abstract

The utility model discloses a fixed wing unmanned aerial vehicle with vertical take-off and landing function, which comprises an unmanned aerial vehicle body, a main propeller and an auxiliary propeller, wherein the main propeller and the auxiliary propeller are turbofan propellers; the main propellers are provided with two groups, the two groups of main propellers are respectively and rotatably connected to the outer sides of the two groups of wings of the unmanned aerial vehicle body, rotating shafts of the main propellers are parallel to the connecting lines of the two groups of wings, and rotating shafts of fans of the main propellers are perpendicular to the rotating shafts of the main propellers; vice propeller is equipped with two sets ofly, and two sets of vice propellers rotate respectively to be connected in the front side of the two sets of fin of unmanned aerial vehicle body, and vice propeller's pivot is on a parallel with main propeller's pivot, and vice propeller's fan pivot perpendicular to vice propeller's pivot. This unmanned aerial vehicle can realize the conversion of many rotor modes and stationary vane mode through the every single move angle of adjustment main propeller and vice propeller, under the prerequisite that satisfies unmanned aerial vehicle's VTOL ability, can simplify unmanned aerial vehicle's structure as far as possible, reduces the energy consumption, extension duration.

Description

Fixed wing unmanned aerial vehicle with VTOL function

Technical Field

The utility model relates to an unmanned air vehicle technique field, concretely relates to fixed wing unmanned aerial vehicle with VTOL function.

Background

Currently, unmanned aerial vehicles are becoming increasingly important in industrial and agricultural application environments. Early unmanned aerial vehicle is mostly many rotor unmanned aerial vehicle and fixed wing unmanned aerial vehicle two kinds. Most of fixed wing unmanned aerial vehicles are bulky, drive the screw with the internal-combustion engine and provide power, are often used for fields such as survey and drawing or reconnaissance. The take-off and landing of fixed-wing drones require specific sites, and the basic flight can be guaranteed only by keeping a certain airspeed during the flight process, which limits the popularization of fixed-wing drones in industrial and civil environments. Compared with the prior art, the multi-rotor unmanned aerial vehicle provides lift force by means of rotation of the propellers, and has the advantages of being simple in operation, large in flying freedom degree and the like. However, since the propellers of a multi-rotor drone need to rotate at high speed to ensure lift, the endurance time of the multi-rotor drone is generally short, and the flight speed is slow, so that the operating radius of the multi-rotor drone is limited, and the popularization of the multi-rotor drone in industrial and civil environments is greatly influenced.

To having the occasion of patrolling and examining the demand on a large scale, it is inevitable trend to combine together fixed wing unmanned aerial vehicle and many rotor unmanned aerial vehicle's advantage. In take-off and landing and low-speed flight phase, use many rotor modes to give first place to, can guarantee the flight degree of freedom, in the stage of cruising, use the fixed wing mode to give first place to, can reduce energy consumption, extension time of endurance. The vertical take-off and landing fixed-wing unmanned aerial vehicle which does not need to depend on a specific field, is simple in take-off and landing operation and long in endurance time is successfully applied to many industries at present.

However, the existing vertical take-off and landing fixed-wing uavs mostly combine the fixed-wing uavs with multi-rotor uavs. For example, on the basis of a fixed-wing unmanned aerial vehicle, four groups of propellers are added to form a quad-rotor unmanned aerial vehicle so as to achieve the purpose of vertical take-off and landing. When the unmanned aerial vehicle flies in a fixed wing mode, the four extra propellers become extra loads, and drag force during flying is increased. And when flying with many rotors mode, fixed wing unmanned aerial vehicle self rearmounted power pack has just become extra load, and the increase of weight has brought high energy consumption, low flight degree of freedom scheduling problem, has shortened the time of endurance.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects of the prior art, the utility model aims to provide a fixed wing unmanned aerial vehicle with VTOL function, under the prerequisite that satisfies unmanned aerial vehicle's VTOL ability, can simplify unmanned aerial vehicle's structure as far as possible, reduce the energy consumption, prolong the time of endurance.

In order to solve the above problem, the utility model discloses the technical scheme who adopts as follows: a wing unmanned aerial vehicle with vertical take-off and landing capacity comprises an unmanned aerial vehicle body, a main propeller and an auxiliary propeller, wherein the main propeller and the auxiliary propeller are turbofan propellers; the main propellers are provided with two groups, the two groups of main propellers are respectively and rotatably connected to the outer sides of the two groups of wings of the unmanned aerial vehicle body, rotating shafts of the main propellers are parallel to the connecting lines of the two groups of wings, and rotating shafts of fans of the main propellers are perpendicular to the rotating shafts of the main propellers; vice propeller is equipped with two sets ofly, two sets of vice propeller rotate respectively connect in the front side of two sets of fin of unmanned aerial vehicle body, vice propeller's pivot is on a parallel with main propeller's pivot, just vice propeller's fan pivot perpendicular to vice propeller's pivot.

Compared with the prior art, the beneficial effects of the utility model reside in that: when two sets of main thrustors and two sets of vice thrustors were all perpendicular up, two sets of main thrustors had constituteed many rotors with two sets of vice thrustors, and unmanned aerial vehicle can realize the VTOL. After unmanned aerial vehicle takes off perpendicularly, can adjust the every single move angle of two sets of main propulsors and two sets of depulsors, make main propulsor all be certain angle forward with depulsor, can make unmanned aerial vehicle remove forward. Along with the gradual increase of airspeed, then can adjust the every single move angle gradually, when the wing can provide sufficient lift, main propeller and vice propeller level forward, unmanned aerial vehicle is then with the flight of fixed wing mode. Compare with present VTOL fixed wing unmanned aerial vehicle of piecing together formula, this unmanned aerial vehicle has set up two sets of main propulsors and two sets of vice propellers, through the every single move angle of adjustment main propulsor and vice propeller, can realize the conversion of many rotor modes and fixed wing mode. No matter under which flight mode, there can not be extra load, under the prerequisite that satisfies unmanned aerial vehicle's VTOL ability, can simplify unmanned aerial vehicle's structure as far as possible, reduce the energy consumption, extension duration.

In the fixed-wing drone with the vertical take-off and landing function, the rotation angle range of the main propeller is [ -180 °, +180 ° ], wherein the 0 ° position is a position when the fan rotating shaft of the main propeller is parallel to the wing plane of the drone body.

In the fixed-wing drone with the vertical take-off and landing function, the range of the rotation angle of the auxiliary propeller is [ -90 °, +90 ° ], wherein the 0 ° position is a position where the rotating shaft of the fan of the auxiliary propeller is parallel to the empennage plane of the drone body.

Foretell fixed wing unmanned aerial vehicle with VTOL function, the main propeller with the outside of vice propeller all has the safety cover.

Foretell fixed wing unmanned aerial vehicle with VTOL function, the outside of safety cover covers there is foam.

In the fixed-wing unmanned aerial vehicle with the vertical take-off and landing function, the rotation angles of the main propellers can be independently adjusted, and the rotation speeds of the fans of the main propellers can be independently adjusted.

In the fixed-wing unmanned aerial vehicle with the vertical take-off and landing function, the rotating speeds of the fans of the two sets of auxiliary propellers can be independently adjusted.

Foretell fixed wing unmanned aerial vehicle with VTOL function, the inside skeleton of unmanned aerial vehicle body adopts carbon fiber material to make, the outside of unmanned aerial vehicle body covers there is foam.

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

Drawings

Fig. 1 is a schematic view of the overall structure of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic structural view of the main thruster of the embodiment of the present invention.

The reference numbers indicate: 100 drone body, 110 wings, 120 empennage, 200 primary propellers, 210 fans, 220 protective covers, 300 secondary propellers.

Detailed Description

The following detailed description refers to fig. 1, the embodiment of the present invention provides a fixed wing drone with vertical take-off and landing function, including drone body 100, main propeller 200 and vice propeller 300, the front left and right sides of drone body 100 all has wing 110, and the afterbody left and right sides all has fin 120, and main propeller 200 is the turbofan propeller with vice propeller 300. Two groups of main propellers 200 are arranged, the two groups of main propellers 200 are respectively and rotatably connected to the outer sides of the two groups of wings 110 of the unmanned aerial vehicle body 100, the rotating shaft of the main propeller 200 is parallel to the connecting line of the two groups of wings 110, and the rotating shaft of a fan 210 of the main propeller 200 is perpendicular to the rotating shaft of the main propeller 200; the auxiliary propeller 300 is provided with two sets, two sets of auxiliary propellers 300 are respectively rotatably connected to the front sides of the two sets of fins 120 of the unmanned aerial vehicle body 100, the rotating shaft of the auxiliary propeller 300 is parallel to the rotating shaft of the main propeller 200, and the rotating shaft of the fan of the auxiliary propeller 300 is perpendicular to the rotating shaft of the auxiliary propeller 300. It should be noted that the rotation axis of the main propeller 200 refers to the rotation axis of the main propeller 200 relative to the wing 110, the rotation axis of the fan 210 of the main propeller 200 refers to the rotation axis of the fan 210 in the main propeller 200, and the rotation axis of the auxiliary propeller 300 is similar to the rotation axis of the fan, which is not described herein again.

When two sets of main propulsors 200 and two sets of auxiliary propulsors 300 are all perpendicular up, that is to say, when the thrust direction of two sets of main propulsors 200 and two sets of auxiliary propulsors 300 is all vertical down, two sets of main propulsors 200 and two sets of auxiliary propulsors 300 have constituteed many rotors, and unmanned aerial vehicle can realize the VTOL. After unmanned aerial vehicle takes off perpendicularly, can adjust the every single move angle of two sets of main propulsors 200 and two sets of vice propellers 300, make main propulsors 200 all be certain angle forward with vice propeller 300, can make unmanned aerial vehicle move forward. With the gradually increasing airspeed, the pitch angle may be gradually adjusted until the main propeller 200 and the auxiliary propeller 300 are horizontally forward when the wing 110 can provide sufficient lift, that is, when the thrust directions of the main propeller 200 and the auxiliary propeller 300 are both horizontally backward, the unmanned aerial vehicle flies in the fixed-wing mode. Compare with the VTOL fixed wing unmanned aerial vehicle of present piecing together formula, this unmanned aerial vehicle has set up two sets of main propulsors 200 and two sets of vice propulsors 300, through the every single move angle of adjusting main propulsors 200 and vice propulsors 300, can realize the conversion of many rotor modes and fixed wing mode. No matter under which flight mode, there can not be extra load, under the prerequisite that satisfies unmanned aerial vehicle's VTOL ability, can simplify unmanned aerial vehicle's structure as far as possible, reduce the energy consumption, extension duration.

Specifically, the rotation angle range of the main propeller 200 is [ -180 °, +180 ° ], wherein the 0 ° position is the position when the fan 210 rotation axis of the main propeller 200 is parallel to the wing 110 plane of the drone body 100. The range of the rotation angle of the auxiliary propeller 300 is [ -90 °, +90 ° ], wherein the 0 ° position is a position when the fan rotation shaft of the auxiliary propeller 300 is parallel to the plane of the tail 120 of the drone body 100. It should be noted that, the utility model provides an unmanned aerial vehicle body 100's wing 110 plane and fin 120 plane defined to the position in fig. 1 is the example, when unmanned aerial vehicle's aircraft nose level flight, the wing 110 plane and the fin 120 plane of unmanned aerial vehicle body 100 all are on a parallel with the horizontal plane, and when unmanned aerial vehicle's aircraft nose was flown with certain angle, the wing 110 plane and the fin 120 plane of unmanned aerial vehicle body 100 also rotated certain angle for the horizontal plane correspondingly.

This unmanned aerial vehicle's two sets of main propulsors 200's turned angle can be adjusted alone, and two sets of main propulsors 200's fan 210 rotational speed can be adjusted alone, and two sets of vice propulsors 300's fan rotational speed can be adjusted alone. When the pitch angles of the main thruster 200 and the sub-thruster 300 are adjusted during flight, the fore-and-aft translation in the multi-rotor mode can be realized. By adjusting the rotation speed of the left and right main propellers 200, the motion at the roll angle can be realized, so that the left and right translation in the multi-rotor mode can be realized. Adjusting the pitch angles of two sets of main propellers 200, for example, with one set of main propellers 200 facing forward and the other set of main propellers 200 facing backward, allows for in-situ rotation in a multi-rotor mode.

For a traditional double-engine fixed wing unmanned aerial vehicle of the same type, the main power components of the double-engine fixed wing unmanned aerial vehicle comprise 6 groups, namely a left engine, a right engine, a left aileron steering engine, a right aileron steering engine, an elevator steering engine and a rudder steering engine. For the current mainstream vertical take-off and landing fixed wing unmanned aerial vehicle, 9 main power components are provided, namely 4 groups of vertical direction propellers, 1 group of advancing direction propellers, a left aileron steering engine, a right aileron steering engine, an elevator steering engine and a rudder steering engine. Therefore, 3 groups of main power components are additionally added to the existing mainstream vertical take-off and landing fixed wing unmanned aerial vehicle in order to realize the function of vertical take-off and landing. For unmanned aerial vehicle, its main trouble source is power component for the majority, for example, many rotor power unit goes wrong, or the direction of advance propeller goes wrong, all can cause serious crash accident, leads to huge loss. Therefore, the additional 3 main power parts that increase will increase the probability that unmanned aerial vehicle broke down, and the crash risk will follow and increase.

In this unmanned aerial vehicle, adopt left propeller angle modulation steering wheel and right propeller angle modulation steering wheel to control the deflection of two sets of main propulsors 200 respectively, adopt 1 group of afterbody propeller angle modulation steering wheel to control the deflection of two sets of vice propellers 300, in addition two sets of main propulsors 200 and two sets of vice propellers 300, this unmanned aerial vehicle has adopted 7 main power unit of group in other words. Therefore, compared with the traditional unmanned aerial vehicle, the unmanned aerial vehicle only has 1 more main power component, and the vertical take-off and landing function of the unmanned aerial vehicle can be realized. The unmanned aerial vehicle weight can be greatly reduced, the possibility of unmanned aerial vehicle failure is reduced, and the risk of crash is reduced.

The unmanned aerial vehicle cancels the ailerons, elevators and rudders of the traditional fixed wing unmanned aerial vehicle, deflects upwards or downwards by a certain angle through the main propeller 200 during flying, and obtains acting forces in the horizontal direction and the vertical direction through vector decomposition of thrust to replace the acting forces in the horizontal direction and the vertical direction of the wings 110 provided by the traditional ailerons. Similarly, the vertical and horizontal deflection angles of the auxiliary propeller 300 are adjusted, and the horizontal and vertical forces are obtained by the vector decomposition of the thrust, instead of the horizontal and vertical forces of the tail wing 120 provided by the elevator. The left and right steering capability provided by the rudder is replaced by adjusting the rotation speed of the auxiliary propeller 300.

For example, in the fixed wing mode of the present drone, the main thruster 200 on the left deflects forward and downward, which can be equivalent to the ailerons of a conventional fixed wing drone deflecting upward, reducing lift. The main propeller 200 on the right deflects forward and upward, which can be equivalent to the aileron of a conventional fixed wing drone to deflect downward, providing lift. The two groups of auxiliary propellers 300 deflect forwards and downwards, so that the two groups of auxiliary propellers can be equivalent to the elevator of the traditional fixed wing unmanned aerial vehicle to deflect upwards, and the two groups of auxiliary propellers 300 deflect forwards and upwards, so that the two groups of auxiliary propellers can be equivalent to the elevator to deflect downwards. The deflection of the rudder can be equivalent by adjusting the fan rotating speed of the two groups of auxiliary propellers 300 and adjusting the thrust.

Traditional fixed wing unmanned aerial vehicle, it is higher to lift center and the centrobaric configuration requirement of complete machine, to the goods of different weight and volume, traditional fixed wing unmanned aerial vehicle need carry out the trim operation earlier to guarantee the stability of flight. And the utility model provides an unmanned aerial vehicle when flying with the fixed wing mode, can realize the focus position adjustment on a large scale through the every single move angle to vice propeller 300 and the adjustment of thrust, when carrying on different loads, need not the centrobaric step of complicated adjustment complete machine, can improve the operating efficiency effectively. This feature can be used very well in a delivery drone system.

This unmanned aerial vehicle has got rid of the definite demarcation between the stationary vane mode that mainstream VTOL stationary vane unmanned aerial vehicle exists and the many rotor modes, can be according to information dynamic adjustment such as airspeed, gesture and position main propeller 200 and vice propeller 300's position and fan speed. For example, when the airspeed is insufficient, the main propeller 200 may be deflected forward and upward to provide a certain lift to compensate for the insufficient lift of the wing 110. This unmanned aerial vehicle does not have clear and definite mode switch problem to can further improve maneuverability and security, avoid mainstream VTOL fixed wing unmanned aerial vehicle to carry out the operation and control risk that mode switch exists.

Specifically, the inside skeleton of unmanned aerial vehicle body 100 adopts carbon fiber material to make, and the outside of unmanned aerial vehicle body 100 covers there is foam. As shown in fig. 2, the main thruster 200 and the sub-thruster 300 each have a protective cover 220 on the outside thereof, and the outside of the protective cover 220 is covered with a foam material. Both can keep reasonable streamlined structure, when whole quick-witted out of control, can alleviate the secondary damage that unmanned aerial vehicle part led to the fact personnel and vehicle etc. on ground again, improve the security that unmanned aerial vehicle used.

It should be noted that, in the description of the present invention, if the orientation or the positional relationship indicated by the orientation description, such as up, down, front, back, left, right, etc., is referred to the orientation or the positional relationship shown in the drawings, it is only for the convenience of description of the present invention and simplification of description, but not for the purpose of indicating or implying that the indicated device or element must have a specific orientation, be constructed or operated in a specific orientation, and should not be interpreted as limiting the present invention.

In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the present number, and the terms greater than, less than, within, etc. are understood as including the present number. The description to first or second etc. is for the purpose of distinguishing between technical features and is not to be construed as indicating or implying a relative importance or implying a number of indicated technical features or implying a precedence relationship between indicated technical features.

In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.

The above embodiments are only preferred embodiments of the present invention, and the protection scope of the present invention cannot be limited thereby, and any insubstantial changes and substitutions made by those skilled in the art based on the present invention are all within the protection scope of the present invention.

Claims (8)

1. A fixed wing unmanned aerial vehicle with vertical take-off and landing functions comprises an unmanned aerial vehicle body (100), a main propeller (200) and an auxiliary propeller (300), wherein the main propeller (200) and the auxiliary propeller (300) are both turbofan propellers;

the two groups of main propellers (200) are arranged, the two groups of main propellers (200) are respectively connected to the outer sides of two groups of wings (110) of the unmanned aerial vehicle body (100) in a rotating mode, the rotating shaft of each main propeller (200) is parallel to the connecting line of the two groups of wings (110), and the rotating shaft of a fan (210) of each main propeller (200) is perpendicular to the rotating shaft of the corresponding main propeller (200);

vice propeller (300) are equipped with two sets ofly, two sets ofly vice propeller (300) rotate respectively connect in the front side of two sets of fin (120) of unmanned aerial vehicle body (100), the pivot of vice propeller (300) is on a parallel with the pivot of main propeller (200), just the fan pivot perpendicular to of vice propeller (300) the pivot of vice propeller (300).

2. Fixed wing drone with vtol functionality according to claim 1, characterized by the fact that the angular range of rotation of the main propeller (200) is [ -180 °, +180 ° ], with the 0 ° position being the position when the fan (210) rotation axis of the main propeller (200) is parallel to the wing (110) plane of the drone body (100).

3. The fixed-wing drone with VTOL function according to claim 1, characterized by the fact that the secondary propeller (300) has a rotation angle range of [ -90 °, +90 ° ], wherein the 0 ° position is the position when the secondary propeller (300) has its fan rotation axis parallel to the plane of the empennage (120) of the drone body (100).

4. The fixed-wing drone with VTOL function according to claim 1, characterized in that the primary propeller (200) and the secondary propeller (300) have a protective cover (220) on the outside.

5. The fixed-wing drone with VTOL functionality according to claim 4, characterized in that the external part of the protection cover (220) is covered with foam.

6. The fixed-wing drone with VTOL function of claim 1, characterized in that the rotation angle of the two sets of the main propellers (200) is adjustable individually and the fan (210) rotation speed of the two sets of the main propellers (200) is adjustable individually.

7. The fixed-wing drone with VTOL function of claim 1, wherein the fan speed of the two sets of secondary propellers (300) is adjustable individually.

8. The fixed-wing drone with VTOL function of claim 1, characterized in that, the internal skeleton of the drone body (100) is made of carbon fiber material, and the exterior of the drone body (100) is covered with foam material.

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