CN218198818U - Fixed wing unmanned aerial vehicle structure capable of vertically taking off and landing - Google Patents

Abstract

The utility model discloses a fixed-wing unmanned aerial vehicle structure capable of taking off and landing vertically, the body of the unmanned aerial vehicle structure is designed into a forward swept wing fixed-wing aircraft structure, and the pneumatic layout of the whole unmanned aerial vehicle structure is reasonable through the structural design of wings and wing knives; and install the rotor mechanism of adjustable direction on wing front side intermediate position to two rotors provide power, make this unmanned aerial vehicle structure possess the structure basis of straight line flight and VTOL. The control system that the cooperation unmanned aerial vehicle was used always with detect components and parts, can realize the rotor mode in high efficiency flight and the VTOL fixed wing and the mutual switching of fixed wing mode, stability in the pneumatic overall arrangement design multiplicable switching of complete machine. Compare in prior art, fly and can change unmanned aerial vehicle flight mode and fly under the support of two rotors, have the adaptability of more scenes, reduce the operation degree of difficulty, and have small characteristics, improved the portability greatly.

Description

Fixed wing unmanned aerial vehicle structure capable of vertically taking off and landing

Technical Field

The utility model relates to an unmanned air vehicle technique field especially relates to a but fixed wing unmanned aerial vehicle structure of VTOL.

Background

Along with the wider unmanned aerial vehicle comes, more higher requirements are put forward to the performance of unmanned aerial vehicle by the industry, whether can be close to actual demand and make the trend out is also the challenge to unmanned aerial vehicle enterprises, so the current research focus lies in how to better use the VTOL technique to the fixed wing unmanned aerial vehicle. The vertical take-off and landing of the fixed wing is realized in a composite wing mode, which is really a method for opening a brain hole, but the method is not innovative enough, does not get rid of the constraint of multiple rotors actually, and the tire removal becomes a real vertical take-off and landing fixed wing. The composite wing type is simple superposition of four rotors and fixed wings, and the measures for realizing vertical take-off and landing are simple and rough. Simply means the mere superposition of the two structures. Multiple rotors can take off and land vertically, but a endurance of tens of minutes is difficult to realize. The fixed wing has long endurance time, but the taking-off and landing conditions are complicated. Therefore, the two are simply bound together to exert respective advantages; not much power reuse and aerodynamic drag reduction measures, such as tiltrotors, are done. The composite wing hangs up the hard life and ties together two aircrafts. The implementation mode has complicated mechanical structure redundancy, and in the horizontal flight stage, the four rotors are in a closed state, so that the structural weight is increased, additional flight resistance is brought, the flight attitude is influenced, and the flight efficiency is greatly reduced. Therefore, the composite wing has poor performances in the aspects of self weight, endurance and wind resistance of the airplane.

SUMMERY OF THE UTILITY MODEL

For solving prior art's not enough, this embodiment provides a but fixed wing unmanned aerial vehicle structure of VTOL. The airframe design of this unmanned aerial vehicle structure is fixed wing aircraft structure, through the structural design of wing and wingknife, and the rotor mechanism of the adjustable direction of reunion loading in the middle of the wing front side makes this unmanned aerial vehicle structure possess the structure basis of sharp flight and VTOL.

The utility model solves the technical scheme that a fixed wing unmanned aerial vehicle structure capable of taking off and landing vertically is designed, which is characterized in that the main body of the unmanned aerial vehicle structure adopts a fixed wing aircraft structure, CLARK Y wing type sweepforward wing wings (5) are symmetrically arranged on both sides of a fuselage (8), ailerons (10) are symmetrically arranged on the rear sides of the sweepforward wing wings (5), and the rear sides of the sweepforward wing wings (5) are connected with the front sides of the ailerons (10) in a hinged manner; moreover, an aileron steering engine (24) is fixedly arranged on the upper surface of the forward swept wing (5) through an accommodating hole, and an output shaft of the aileron steering engine (24) is vertical to the upper surface of the forward swept wing (5) at the mounting position; the upper part of the rocker arm (23) is of a plate-shaped structure, one end of the plate-shaped structure is provided with a first through hole, the other end of the plate-shaped structure is provided with a second through hole, the lower part of the first through hole extends downwards to form a sleeve structure, the central axis of the first through hole is superposed with the central axis of the sleeve structure, and the inner surface of the sleeve structure is provided with a circle of sawteeth; one end of the rocker arm (23) with a first through hole is fixed on an output shaft of the aileron steering engine (24) through a screw, and inner saw teeth of the sleeve structure are meshed and connected with outer saw teeth on the output shaft of the aileron steering engine (24); the movable end of the pull rod (22) is arranged in a second through hole of the rocker arm (23), the other end of the pull rod (22) is fixed on a quick regulator (21), the quick regulator (21) is fixed on the upper part of the rudder angle (20), and the lower part of the rudder angle (20) is fixed on the upper surface of the aileron (10); when the aileron steering engine (24) returns to the center, the aileron (10) is in a horizontal state, and a connecting line of the circle center of the first through hole of the rocker arm (23) and the circle center of the second through hole thereof is in a vertical intersection state with the pull rod (22);

the two sides of the top of the tail of the fuselage (8) are symmetrically provided with an upper vertical stabilizing winged knife (6), the middle of the bottom of the tail of the fuselage (8) is provided with a lower vertical stabilizing winged knife (11), the two sides of the bottom of the head of the fuselage (8) are symmetrically provided with a front vertical stabilizing winged knife, the wingtips of two forward swept wing wings (5) are symmetrically provided with a wingtip vortex winged knife (7), and the directions of the upper vertical stabilizing winged knife (6), the lower vertical stabilizing winged knife (11), the front vertical stabilizing winged knife and the wingtip vortex winged knife (7) are all arranged in parallel with the middle axial plane of the fuselage (8);

the middle positions of the front sides of the two forward-swept wing wings (5) are symmetrically and fixedly loaded with a direction-adjustable rotor wing mechanism respectively, and the angle change range of the rotor wing in the direction-adjustable rotor wing mechanism is at least from the horizontal direction to the vertical direction; the aileron steering engine (24) and the power system of the rotor wing mechanism with adjustable direction are connected with the control system arranged in the fuselage (8) through wires.

Compared with the prior art, the beneficial effects of the utility model are that: the airframe of the unmanned aerial vehicle structure is designed into a forward-swept wing fixed wing aircraft structure, and the overall aerodynamic layout is reasonable through the structural design of wings and wingknives; and install the rotor mechanism of adjustable direction on wing front side intermediate position to two rotors provide power, make this unmanned aerial vehicle structure possess the structure basis of straight line flight and VTOL. The control system that the cooperation unmanned aerial vehicle was used always with detect components and parts, can realize the rotor mode in high efficiency flight and the VTOL fixed wing and the mutual switching of fixed wing mode, stability in the pneumatic overall arrangement design multiplicable switching of complete machine. Compare in prior art, fly and can change unmanned aerial vehicle flight mode and fly under the support of two rotors, have the adaptability of more scenes, reduce the operation degree of difficulty, the fixed wing flight mode of cruising has reduced the drawback that unmanned aerial vehicle flight inefficiency brought among the prior art to a certain extent, and has small characteristics, has improved the portability greatly.

Drawings

Fig. 1 is the utility model relates to a but three-dimensional structure schematic diagram of an angle of fixed wing unmanned aerial vehicle structure embodiment of VTOL.

Fig. 2 is a schematic perspective view of another angle of an embodiment of the fixed-wing drone structure capable of vertical take-off and landing according to the present invention.

Fig. 3 is an assembly schematic diagram of a pull rod of an embodiment of the fixed-wing drone structure capable of vertical take-off and landing of the present invention.

Fig. 4 is the utility model relates to a but vertical take-off and landing's fixed wing unmanned aerial vehicle structure a rotor mechanism's of adjustable direction of embodiment structural sketch.

Fig. 5 is a schematic structural diagram of a rotor steering engine of an embodiment of the direction-adjustable rotor mechanism in fig. 4.

In the attached drawing, 1-self-locking paddle, 2-motor, 3-tilting motor base, 4-rudder cabin, 5-CLARKY wing type forward swept wing, 6-upper vertical stable wing knife, 7-wingtip vortex wing knife, 8-fuselage, 9-camera, 10-aileron, 11-lower vertical stable wing knife, 12-carbon tube, 13-first carbon rod fixer, 14-second carbon rod fixer, 17-pin, 15-reed, 18-rotor steering engine, 19-rudder arm, 20-rudder angle, 21-quick adjuster, 22-pull rod, 23-rocker arm and 24-aileron.

Detailed Description

The invention is further described with reference to the following specific examples and accompanying drawings.

The utility model provides a fixed wing unmanned aerial vehicle structure capable of taking off and landing vertically, which is characterized in that the main body part of the unmanned aerial vehicle structure adopts a fixed wing aircraft structure, CLARK Y wing type sweepforward wings (5) are symmetrically arranged at both sides of a fuselage (8), the rear sides of the forward swept wing wings (5) are symmetrically provided with an aileron (10), and the rear sides of the forward swept wing wings (5) are connected with the front sides of the ailerons (10) in a hinged mode; moreover, an aileron steering engine (24) is fixedly arranged on the upper surface of the forward swept wing (5) through an accommodating hole, and an output shaft of the aileron steering engine (24) is vertical to the upper surface of the forward swept wing (5) at the mounting position; the upper part of the rocker arm (23) is of a plate-shaped structure, one end of the plate-shaped structure is provided with a first through hole, the other end of the plate-shaped structure is provided with a second through hole, the lower part of the first through hole extends downwards to form a sleeve structure, the central axis of the first through hole is superposed with the central axis of the sleeve structure, and the inner surface of the sleeve structure is provided with a circle of sawteeth; one end of the rocker arm (23) with a first through hole is fixed on an output shaft of the aileron steering engine (24) through a screw (a concave threaded hole is formed in the middle of the top surface of the output shaft of the aileron steering engine (24)), and inner sawteeth of the sleeve structure are meshed and connected with outer sawteeth on the output shaft of the aileron steering engine (24); the movable end of the pull rod (22) is arranged in a second through hole of the rocker arm (23), the other end of the pull rod (22) is fixed on a quick regulator (21), the quick regulator (21) is fixed on the upper part of the rudder angle (20), and the lower part of the rudder angle (20) is fixed on the upper surface of the aileron (10); when the aileron steering engine (24) returns to the center, the aileron (10) is in a horizontal state, and a connecting line of the circle center of the first through hole of the rocker arm (23) and the circle center of the second through hole of the rocker arm is vertically intersected with the pull rod (22);

specifically, as an embodiment, one end of a connecting rocker arm (23) of the pull rod (22) is bent vertically, the lower part of the end is a lower limiting rod arranged forwards, the middle part of the end is a connecting rod parallel to an output shaft of the aileron steering engine (24), the upper part of the end is a pull rod arranged backwards, and the lower limiting rod is parallel to the pull rod and is perpendicular to the connecting rod.

The quick regulator (21) is of a cylindrical structure, one end face of the quick regulator is provided with a convex mounting threaded rod which is fixed with the upper part of the rudder angle (20) through a nut, the other end face opposite to the end face is provided with a concave fastening threaded hole, a through hole penetrating through the cylindrical structure is arranged in the front-back direction which forms 90 degrees with the axis of the fastening threaded hole, and the horizontal plane of the circle center of the through hole is coplanar with the horizontal plane of the circle center of the fastening threaded hole; the rear end of the tension rod of the pull rod (22) is arranged in the through hole of the quick regulator (21), and the rear end of the tension rod is fixed on the quick regulator (21) by installing a screw in the fastening threaded hole.

The lower part of the rudder angle (20) is a horizontal plate and is fixed on the aileron (10) in an adhesion mode, the upper part of the rudder angle is a connecting plate vertical to the horizontal plate, the upper part of the connecting plate is provided with a through hole, and the end surface of the quick regulator (21) provided with a mounting threaded rod is fixed on the upper part of the connecting plate through a nut;

the pull rod (22) is a steel wire pull rod of a Z-shaped steering engine, and the size of the through hole of the rocker arm (23) is provided with allowance, so that the movable end of the pull rod (22) can turn into the through hole of the rocker arm (23).

The airplane wing tip vortex wing cutter comprises a fuselage (8), wherein two upper vertical stabilizing wing cutters (6) are symmetrically arranged on two sides of the top of the tail of the fuselage (8), a lower vertical stabilizing wing cutter (11) is arranged in the middle of the bottom of the tail of the fuselage (8), two front vertical stabilizing wing cutters are symmetrically arranged on two sides of the bottom of the head of the fuselage (8), two wing tip vortex wing cutters (7) are symmetrically arranged at wing tips of two forward-swept wing wings (5), and the orientations of the upper vertical stabilizing wing cutters (6), the lower vertical stabilizing wing cutters (11), the front vertical stabilizing wing cutters and the wing tip vortex wing cutters (7) are all parallel to a central axis plane of the fuselage (8) (namely, a symmetrical plane in the head-tail direction of the fuselage (8)).

The middle positions of the front sides of the two forward swept wing wings (5) are symmetrically and respectively fixedly loaded with a direction-adjustable rotor wing mechanism, and the loading mode can be realized by directly fixing and bonding or respectively connecting and fixing the two through structural parts, so that the two are connected together. The angle of the rotor wing in the direction-adjustable rotor wing mechanism is at least in the range from the horizontal direction to the vertical direction;

a groove is arranged in the middle of the head of the machine body (8), and a camera (9) is arranged in the groove.

The power system of the rotor wing mechanism with adjustable direction, the camera (9) and the aileron steering engine (24) are connected with a control system arranged in the machine body (8) through wires. The control system controls the action of a power system of the direction-adjustable rotor wing mechanism, so that the rotor wing on the direction-adjustable rotor wing mechanism rotates, and the angle is changed when the direction needs to be adjusted. The control system controls the aileron steering engine (24) to control the angle of the aileron (10).

The specific structure of the direction-adjustable rotor mechanism can refer to the existing design, but the rotor mechanism which is provided with a tilting structure and can change the angle at least from the horizontal direction to the vertical direction (namely not less than 90 degrees) meets the requirement of the scheme. In addition, as an embodiment, the arrangement among the fuselage, the wings and the winglets is realized by means of hot melt adhesive bonding.

As an embodiment, the control system comprises an electric controller, a flight controller and a battery, a power system of the rotor wing mechanism with an adjustable direction comprises a motor and a rotor wing steering engine, three lines of the motor are connected to the electric controller, a signal line of the electric controller is connected to the flight controller, a power supply line of the electric controller is connected with the battery, signal lines and power supply lines of the rotor wing steering engine and an aileron steering engine (24) are connected with the flight controller, a control signal and power supply are provided by the flight controller, and a camera is connected with the flight controller through a power supply line. The electric controller, the flight controller, the battery, the motor, the steering engine and the camera are all conventional public components, the using methods of the electric controller, the flight controller, the battery, the motor, the steering engine and the camera are all conventional public mechanical technical means in the field and are necessary electronic devices of a conventional unmanned aerial vehicle, the details are not needed to be described herein, the specific structure of part of the devices is not needed to be shown in the attached drawings, and the technical personnel in the field can clearly understand the specific structure, how to install, control logic, specific control circuits and the like, so that a complete technical scheme can be realized.

The theory of operation and the work flow of this unmanned aerial vehicle structure: the unmanned aerial vehicle structure is characterized in that a CLARK Y wing type forward swept wing (namely a Clark Y wing which is the most typical design in the cross section of the wing, the cross section of the wing is bent upwards and flat downwards, the most protruding part of the wing is the position with 30 percent of chord length) (5), a vertical stabilizing wing knife (6) and a wing tip vortex wing knife (7) form an integral pneumatic structure, and a basic frame of a vertical take-off and landing fixed wing structure is formed; as an embodiment, the wing area of the forward swept wing CLARKY airfoil type forward swept wing (5) is 38dm ² The wing tip vortex wing knife (7) can reduce the wing tip induced resistance of the wing. The ailerons (10) of the CLARKY airfoil forward swept wing (5) have higher efficiency and good large-attack-angle control characteristic. And because the wings are swept forward, the boundary layer tends to be accumulated towards the wing roots, airflow is separated at the wing roots at first, the wing resistance is small, and the problem of wing tip stall is solved. After the wings begin to stall, the ailerons (10) of the forward swept wings can still maintain the equivalent steering efficiency, and do not lose the lateral steering capacity at first like the conventional backward swept wings, which is important for ensuring the large incidence maneuverability of the unmanned aerial vehicle. Have better stall characteristic, also be favorable to preventing unmanned aerial vehicle to get into the tail spin, the conversion of two kinds of modes of aircraft is more stable when making the low speed.

The wing tip vortex winged knife (7) can effectively delay the separation of the wing tip and reduce the induced resistance of the wing tip of the wing. The stability of the airplane during horizontal flight and transition of the two modes is improved. The vertical stabilizing wing knife (6) provides the transverse static stability of the airplane, and simultaneously provides transverse damping moment, namely transverse dynamic stability of the airplane. When the airplane flies along a straight line in an approximately uniform linear motion, the vertical stabilizing surface does not generate extra moment on the airplane, and the stability of the airplane in the horizontal direction is ensured.

When the unmanned aerial vehicle structure is applied, firstly, a fuselage (8) is horizontally arranged on the ground, a control system arranged in the fuselage (8) controls the action of a power system of a direction-adjustable rotor wing mechanism, and controls an aileron steering engine (24) to control the angle of an aileron (10), so that blades of two rotor wings rotate in the direction parallel to the horizontal plane (as the state of the direction-adjustable rotor wing mechanism on the right side of the fuselage in figure 1), and simultaneously controls the aileron steering engine (24) to tilt the aileron (10) upwards for an angle, the power system of the rotor wing mechanism drives the head of the fuselage (8) to move upwards, when the direction-adjustable rotor wing mechanism breaks away from the ground (nodes can be preset by the running time of a relevant size control motor), the actions of the power system of the direction-adjustable rotor wing mechanism and the aileron steering engine (24) are changed,

the rotor wing steering engine enables the rotor wing to change the angle, the aileron steering engine (24) enables the deflection angle of the aileron (10) to be reduced until the blades of the rotor wing rotate in the direction vertical to the horizontal plane (as the state of the left direction-adjustable rotor wing mechanism of the fuselage in figure 1), and at the moment, the fuselage (8) is adjusted to be in the state vertical to the ground under the driving of the rotor wing; thereafter, fuselage (8) is with the steady rising of vertically state under the effect of rotor, after rising to target height (accessible loading height measuring device realizes high monitoring), the rotor steering wheel drives the blade of rotor and deflects toward the bottom surface direction that is close to fuselage (8), aileron steering wheel (24) make the aileron deflect an angle to the bottom surface direction that is close to fuselage (8) simultaneously, the rotor of predetermineeing the angle and the aileron cooperation of predetermineeing the angle, the air current that produces makes the wing of fuselage (8) adjust toward the horizontal direction, when fuselage (8) are located approximate horizontal direction (through setting for the accurate control of certain angle), the blade of rotor steering wheel control rotor rotates with the state of perpendicular to horizontal direction, the control of whole process can be through setting up in fuselage (8) inside accelerometer, gyroscope (angle monitoring) realizes data acquisition and feedback, fuselage (8) take-off completion this moment, later fuselage can realize approximate straight line flight. When needs descend, the rotor steering wheel drives the blade of rotor and toward the top direction deflection that is close to fuselage (8), aileron steering wheel (24) make the aileron to the top direction deflection an angle that is close to fuselage (8) simultaneously, the rotor of predetermineeing the angle and the aileron cooperation of predetermineeing the angle, the air current that produces makes the wing of fuselage (8) toward vertical direction adjustment, when fuselage (8) are located approximate vertical direction (through setting for the accurate control of certain angle), the blade of steering wheel control rotor rotates with the state along the horizontal direction, and the operating speed of adjustment motor, make fuselage (8) with the stable decline to ground of vertically state.

The present embodiment provides only a basic frame structure of a fixed-wing drone capable of achieving both straight-line flight and vertical take-off and landing, and the control components involved in the description of the application scenario are only used for illustrating a usage method of the drone structure, and in order to make the drone structure better applicable, more control components may be adopted, but the scope of the claims of the present patent is not within the scope of the present patent.

As a self-designed embodiment, the direction-adjustable rotor wing mechanism comprises a self-locking blade (1), a motor (2), a tilting motor base (3), a rudder cabin (4), a rotor wing steering engine (18) and a square carbon rod (12), wherein the self-locking blade (1) is double-blade, and the self-locking blade (1) is fixedly arranged on an output shaft of the motor (2) through internal threads of the self-locking blade; the lower part of the motor (2) is fixed on the top surface of the tilting motor base (3) through a screw;

the tilting motor base (3) is of an approximate n-shaped structure, the top of the tilting motor base is a platform, two supporting edges of the lower portion of the platform are parallel, the supporting edge on one side of the platform is short in the other side, a through hole is formed in the lower portion of the long supporting edge, a rudder arm (19) is installed in the middle of the inner side of the short supporting edge through a screw and a nut, and the rudder arm (19) is parallel to the two supporting edges. The lower part of the rudder arm (19) is provided with a through hole, and one side of the through hole is horizontally and outwards fixedly provided with a sleeve structure in the direction vertical to the rudder arm (19).

The upper part of the rudder cabin (4) is provided with a hollow cavity, one side wall of the hollow cavity is provided with a steering engine mounting hole, the side wall of the other side opposite to the side wall is provided with a circular hole, the inner side of the circular hole is provided with a circular step groove, and in addition, the hollow cavity is provided with a hole for allowing a signal line and a power supply line of a rotor steering engine (18) to pass through; a square channel is arranged in the middle of the bottom surface of the hollow cavity; the rotor wing steering engine (18) is fixedly arranged inside the hollow cavity of the rudder cabin (4) in an adhesion mode, and the output shaft of the rotor wing steering engine (18) faces to one side of the hollow cavity, which is provided with the rectangular hole; an output shaft of the rotor wing steering engine (18) is sleeved in a sleeve structure of the rudder arm (19) and is fixedly connected with the rudder arm (19) through a screw (a concave threaded hole is formed in the middle of the top surface of the output shaft of the rotor wing steering engine (18)).

The flange bearing is installed on the inner side of a circular hole of a hollow cavity of the rudder cabin (4), the pin (17) penetrates through the flange bearing, the circular hole of the hollow cavity and a through hole in the lower portion of the longer supporting edge of the tilting motor base (3), one side, provided with the circular hole, of the rudder cabin (4) is connected with the lower portion of the longer supporting edge of the tilting motor base (3), and the reed (15) is installed at the tail end of the pin (17). The axis of the output shaft of the rotor wing steering engine (18) and the axis of the pin (17) are positioned on the same straight line and are vertical to the square channel of the rudder cabin (4) in space. One end of a square carbon rod (12) is fixedly arranged in a square channel on the bottom surface of the rudder cabin (4) in an adhesion mode, and the other end of the square carbon rod (12) is fixed in the middle of the front side of the sweepforward wing (5) through a first carbon rod fixer (13) and a second carbon rod fixer (14).

The middle of a carbon rod fixer (13) and a second carbon rod fixer (14) is provided with a rectangular groove, the size of the rectangular groove is matched with that of a square carbon rod (12), the other end of the square carbon rod (12) is fixed in the rectangular groove of the first carbon rod fixer (13) and the second carbon rod fixer (14) in an adhesion mode, and the first carbon rod fixer (13) and the second carbon rod fixer (14) are fixed on a carrier wing in an adhesion mode. The two carbon rod fixers increase the bonding area of the square carbon rod and the wing, and increase the stability of the connection of the rotor wing mechanism and the wing.

As an example, the square carbon rod (12) has a size of 10mm by 10mm.

As an embodiment, the motor (2) adopts the X2216-III KV 880X-fixed wing series (third generation) of Langyu (SUNNYSKY).

As an example, aileron steering engines (24) and rotor steering engines (18) both use the KM1703MD model of KINGMAX HOBBY.

As an embodiment, a motor (2) of a rotor wing mechanism with adjustable direction is a brushless motor, three lines of the motor (2) are connected to an electric regulator (a good happy day 40A brushless electric regulator (model is XRotor 40A)), a signal line of the electric regulator is connected to a flight control (a Dome Zealott H743 is used for flying control), a power supply line of the electric regulator is connected with a battery, an aileron steering engine (24) is connected with a signal line and a power supply line of a rotor wing steering engine (18) and is connected with the flight control, the flight control provides signals and supplies power, and a camera (9) is connected with the flight control. According to the requirement, the flight control can be connected with the wireless image transmission system, the flight control transmits the camera picture and the flight data fusion image to the wireless image transmission system, and the wireless image transmission system transmits the picture to the ground receiving end. The electric regulation, the flight control, the battery and the wireless image system are all arranged in the machine body (8).

As another embodiment, the power system of the direction-adjustable rotor wing mechanism comprises two motors, wherein each motor comprises a self-locking blade, a driving motor, a tilting motor base, a tilting motor, a carrier mounting frame, a driving gear and a driven gear; the lower part of the tilting motor base is provided with two parallel mounting pieces, the front end of the carrier mounting rack is movably arranged between the two mounting pieces through a pin and a reed, the middle part of the carrier mounting rack is arranged into a hollow structure, the tilting motor is fixedly arranged in the hollow structure in a bonding mode, and the output shaft with threads is arranged towards the direction vertical to the arrangement direction of the tilting motor base; a driving gear is fixedly arranged on an output shaft of the tilting motor, a driven gear is fixedly arranged on a mounting plate close to one side of the driving gear, and the driving gear is meshed with the driven gear; the tail end of the carrier mounting frame is a mounting end, and the carrier mounting frame is fixedly connected with the wing in a bonding mode through mounting holes matched with the wing in the corresponding positions.

The utility model discloses the nothing is mentioned the part and is applicable to prior art.

Claims (7)

1. A fixed wing unmanned aerial vehicle structure capable of taking off and landing vertically is characterized in that a main body part of the unmanned aerial vehicle structure adopts a fixed wing aircraft structure, forward swept wing wings (5) of CLARKY wing type are symmetrically arranged on two sides of a fuselage (8), ailerons (10) are symmetrically arranged on the rear sides of the forward swept wing wings (5), and the rear sides of the forward swept wing wings (5) are connected with the front sides of the ailerons (10) in a hinged mode; moreover, an aileron steering engine (24) is fixedly arranged on the upper surface of the forward swept wing (5) through an accommodating hole, and an output shaft of the aileron steering engine (24) is vertical to the upper surface of the forward swept wing (5) at the mounting position; the upper part of the rocker arm (23) is of a plate-shaped structure, one end of the plate-shaped structure is provided with a first through hole, the other end of the plate-shaped structure is provided with a second through hole, the lower part of the first through hole extends downwards to form a sleeve structure, the central axis of the first through hole is superposed with the central axis of the sleeve structure, and the inner surface of the sleeve structure is provided with a circle of sawteeth; one end of the rocker arm (23) with a first through hole is fixed on an output shaft of the aileron steering engine (24) through a screw, and inner saw teeth of the sleeve structure are meshed and connected with outer saw teeth on the output shaft of the aileron steering engine (24); the movable end of the pull rod (22) is arranged in a second through hole of the rocker arm (23), the other end of the pull rod (22) is fixed on a quick regulator (21), the quick regulator (21) is fixed on the upper part of the rudder angle (20), and the lower part of the rudder angle (20) is fixed on the upper surface of the aileron (10); when the aileron steering engine (24) returns to the center, the aileron (10) is in a horizontal state, and a connecting line of the circle center of the first through hole of the rocker arm (23) and the circle center of the second through hole thereof is in a vertical intersection state with the pull rod (22);

the two sides of the top of the tail of the fuselage (8) are symmetrically provided with an upper vertical stabilizing winged knife (6), the middle of the bottom of the tail of the fuselage (8) is provided with a lower vertical stabilizing winged knife (11), the two sides of the bottom of the head of the fuselage (8) are symmetrically provided with a front vertical stabilizing winged knife, the wingtips of two forward swept wing wings (5) are symmetrically provided with a wingtip vortex winged knife (7), and the directions of the upper vertical stabilizing winged knife (6), the lower vertical stabilizing winged knife (11), the front vertical stabilizing winged knife and the wingtip vortex winged knife (7) are all arranged in parallel with the middle axial plane of the fuselage (8);

the middle positions of the front sides of the two forward swept wing wings (5) are symmetrically and fixedly loaded with a direction-adjustable rotor wing mechanism respectively, and the angle change range of the rotor wing in the direction-adjustable rotor wing mechanism is at least from the horizontal direction to the vertical direction; the aileron steering engine (24) and the power system of the rotor wing mechanism with adjustable direction are connected with the control system arranged in the fuselage (8) through wires.

2. The fixed-wing unmanned aerial vehicle structure capable of vertically taking off and landing according to claim 1, wherein one end of a connecting rocker arm (23) of the pull rod (22) is vertically bent, the lower portion of the end is a lower limiting rod arranged forwards, the middle portion of the end is a connecting rod parallel to an output shaft of the aileron steering engine (24), the upper portion of the end is a tension rod arranged backwards, and the lower limiting rod is parallel to the tension rod and is perpendicular to the connecting rod.

3. The structure of the fixed-wing unmanned aerial vehicle capable of taking off and landing vertically as claimed in claim 1, wherein the fast regulator (21) is a cylindrical structure, one end face of the fast regulator is provided with a convex mounting threaded rod, the fast regulator is fixed with the upper part of the rudder angle (20) through a nut, the other end face opposite to the end face is provided with a concave fastening threaded hole, a through hole penetrating through the cylindrical structure is arranged in the front-back direction at 90 degrees to the axis of the fastening threaded hole, and the horizontal plane of the center of the through hole is coplanar with the horizontal plane of the center of the fastening threaded hole; the rear end of the tension rod of the pull rod (22) is arranged in the through hole of the quick regulator (21), and the rear end of the tension rod is fixed on the quick regulator (21) by installing a screw in the fastening threaded hole.

4. The structure of the fixed wing drone capable of vertical take-off and landing according to claim 1, characterized in that the lower part of the rudder angle (20) is a horizontal plate fixed on the aileron (10) by means of adhesion, the upper part thereof is a connecting plate perpendicular to the horizontal plate, the upper part of the connecting plate is provided with through holes, and the end surface of the quick regulator (21) provided with the mounting threaded rod is fixed on the upper part of the connecting plate by nuts.

5. The structure of the fixed-wing UAV capable of taking off and landing vertically as claimed in claim 2, wherein the pull rod (22) is a Z-shaped steering engine steel wire pull rod.

6. The structure of claim 1, wherein a groove is formed in the middle of the head of the main body (8), the inside of the groove is provided with the camera (9), and the camera (9) is connected with the control system through a wire.

7. The structure of claim 1, wherein the control system comprises an electric controller, a flight controller, and a battery, the power system of the direction-adjustable rotor mechanism comprises a motor and a rotor steering engine, three lines of the motor are connected to the electric controller, a signal line of the electric controller is connected to the flight controller, and a power supply line of the electric controller is connected to the battery; and signal lines and power supply lines of the rotor wing steering engine and the aileron steering engine are connected with the flight control, and the flight control provides control signals and supplies power.

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