CN219277780U - Catapulting folding multi-rotor unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses an ejection folding multi-rotor unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The automatic unfolding limiting mechanism comprises a machine body and a machine arm connected with the machine body, wherein the machine arm is connected with the machine body, and the machine arm is automatically unfolded and limited by the limiting mechanism. The automatic unfolding limiting mechanism of the horn between the horn and the machine body is used for folding the horn under the non-running state, so that the occupation of the unmanned aerial vehicle on the space is greatly reduced, and the unmanned aerial vehicle is convenient to normally store and carry; the automatic horn expansion limiting mechanism can enable the horn of the unmanned aerial vehicle rotor to be automatically expanded and folded, so that the unmanned aerial vehicle can be rapidly expanded in the air after being ejected, the response is rapid, and the ejection and emission requirements under specific environments are met.

Description

Catapulting folding multi-rotor unmanned aerial vehicle

Technical Field

The utility model relates to a multi-rotor unmanned aerial vehicle, in particular to an ejection folding multi-rotor unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles.

Background

With the increasing development of civil and military unmanned aerial vehicle industry, the application scene of the unmanned aerial vehicle is wider and wider. In recent years, the multi-rotor unmanned aerial vehicle has the advantages of environmental protection, low noise, small volume, light weight, low cost, portability, suitability for multi-platform and multi-space use, capability of vertical lifting and the like, and is widely developed and applied in various fields of society. However, the conventional multi-rotor unmanned aerial vehicle generally adopts fixed wings, which occupy a relatively large space, are inconvenient to store and carry, and cannot meet the ejection and emission requirements in specific environments.

Disclosure of Invention

The utility model aims to overcome the defects of the prior art and provide the ejection folding multi-rotor unmanned aerial vehicle with the wings convenient to store and carry and capable of ejecting and launching.

In order to solve the technical problems, the ejection folding multi-rotor unmanned aerial vehicle provided by the utility model comprises a machine body and a horn connected with the machine body, wherein a horn automatic unfolding limiting mechanism is connected between the horn and the machine body.

In the utility model, the automatic mechanical arm unfolding limiting mechanism comprises a spring, a mechanical arm fixing plate and a mechanical arm locking device;

the arm is hinged with the arm fixing plate, one end of the spring is connected with the machine body, the other end of the spring is connected with the arm, and the spring can drive the arm to be unfolded outwards relative to the arm fixing plate;

the horn locking device locks the horn after the horn is unfolded.

In the utility model, the horn locking device comprises two hooks which are arranged in opposite directions, and the hooks are respectively hinged with the horn fixing plate;

the clamping hook and the arm fixing plate are provided with a torsion device, and the torsion device controls the vertical rotation of the clamping hook relative to the arm fixing plate;

and a gap for accommodating the horn is formed between the two opposite hooks, and the horn is limited in the gap by the hooks after the horn is unfolded.

In the utility model, the landing gear is arranged below the machine body, and an automatic landing gear unfolding limiting mechanism is arranged between the machine body and the landing gear.

In the utility model, the landing gear automatic unfolding limiting mechanism comprises a mounting seat, a limiter and a torsion device;

the landing gear is hinged with the mounting seat, and a torsion device is connected between the landing gear and the mounting seat;

the landing gear is restrained from rotating outwards by the limiter after the landing gear is unfolded.

In the utility model, the limiter comprises a limiting pin and a limiting spring, wherein the limiting pin is connected with the limiting spring, and the limiting pin is positioned at one side of the landing gear;

when the landing gear is unfolded, the limiting pin automatically stretches out to limit the landing gear to rotate outwards.

In the utility model, the fuselage comprises an equipment cabin, a center cabin, a battery cabin and a load cabin;

the central cabin is connected with the horn, and a GPS positioning module and a flight control module are arranged in the central cabin;

the equipment cabin is positioned above the central cabin, and a communication module and an unmanned aerial vehicle electronic regulation module are installed in the equipment cabin;

the battery compartment is positioned below the central compartment;

the load cabin is positioned below the battery cabin and is used for arranging the visible light detection load.

In the utility model, the equipment compartment comprises a fairing.

In the utility model, the battery compartment comprises a vertical upright post, a baffle and a supporting plate;

the four vertical upright posts are circumferentially distributed, and two ends of each vertical upright post are respectively connected with the supporting plate;

and a baffle is arranged on any three surfaces formed by the four vertical upright posts.

In the utility model, the unmanned aerial vehicle adopts a symmetrical design, the gravity center position of the unmanned aerial vehicle is distributed at the central axis of the unmanned aerial vehicle, and the gravity center is positioned below the lifting surface.

The utility model has the beneficial effects that: (1) The automatic unfolding limiting mechanism of the horn between the horn and the machine body is used for folding the horn under the non-running state, so that the occupation of the unmanned aerial vehicle on the space is greatly reduced, and the unmanned aerial vehicle is convenient to normally store and carry; the automatic unfolding limiting mechanism of the horn can enable the horn of the unmanned aerial vehicle rotor to be unfolded and folded automatically, so that the unmanned aerial vehicle can be unfolded in the air quickly after ejection, the response is quick, and the ejection and emission requirements under specific environments are met; (2) The double-clip limiting horn is adopted, so that the automatic unfolding and limiting of the horn are realized, the stability of the horn in the flight process is further provided, and the flight safety coefficient of the unmanned aerial vehicle is improved; (3) The landing gear automatic unfolding limiting mechanism of the unmanned aerial vehicle can be folded, so that the unmanned aerial vehicle is convenient to store and carry; (4) The fairing can effectively reduce resistance during flying while realizing the function of the equipment cabin; (5) The three sides of the battery compartment are provided with the baffles to play a role in preventing rain and dust, and meanwhile, the modularized lithium battery is convenient to detach and replace; (6) The unmanned aerial vehicle adopts symmetrical design, and its focus position distributes in unmanned aerial vehicle central axis department and focus is located the below of lifting surface, and the moment that the relative lifting surface of focus produced is opposite with the moment that external interference produced, will produce the inhibitory action to interference vibration for unmanned aerial vehicle has better stability.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present utility model, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of an unmanned aerial vehicle in an unfolded state;

FIG. 2 is a schematic view of a landing gear assembly;

FIG. 3 is a schematic diagram of a limiting device;

FIG. 4 is a schematic view of a mechanical arm action assembly structure 1;

FIG. 5 is a schematic view of a mechanical arm motion assembly structure 2;

fig. 6 is a schematic view of the battery compartment structure.

In the figure: 1-radome, 2-GPS positioning module, 3-GPS mount, 4-flight control module, 5-flight control mount, 6-on-board development board, 7-rotor, 8-horn, 9-motor, 10-electronic governor, 11-communication module, 12-battery compartment, 13-landing gear, 14-photoelectric load, 15-top support plate, 121-vertical column, 120-battery compartment baffle, 122 support plate, 131-landing gear mount, 132-torsion spring, 130-stop, 1301-stop cap, 1302-stop spring, 1303-stop pin, 801-spring, 802-torsion spring, 803-hook, 804-horn fixing plate, 805-stop beam.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.

In the description of the present utility model, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, are merely for convenience of describing the present utility model and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal," "vertical," "overhang," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.

Some embodiments of the present utility model are described in detail below with reference to the accompanying drawings. The following embodiments and features of the embodiments may be combined with each other without conflict.

As shown in fig. 1, the catapulting folding multi-rotor unmanned aerial vehicle provided by the embodiment comprises a fairing 1, a GPS positioning module 2, a GPS mounting seat 3, a flight control module 4, a flight control mounting seat 5, an airborne development board 6, a rotor 7, a horn 8, a motor 9, an electronic speed regulator 10, a communication module 11, a battery compartment 12, a landing gear 13, a photoelectric load 14 and a top supporting plate 15. The catapulting folding multi-rotor unmanned aerial vehicle in the embodiment is divided into 4 functional cabins from top to bottom, namely an equipment cabin, a center cabin, a battery cabin and a load cabin, and isolation cabin division arrangement is carried out between adjacent cabins.

The equipment cabin comprises a fairing 1, a GPS positioning module 2, a GPS mounting seat 3, a flight control module 4, a flight control mounting seat 5 and an airborne development board 6. The outside of the equipment cabin is wrapped by the fairing 1, the bottom of the fairing 1 is connected with the top supporting plate 15, and the formed internal closed space is used as the equipment cabin. Two mounting seats, namely a GPS mounting seat 3 and a flight control mounting seat 5, are arranged in the space below the fairing 1 and are of an up-down stacking structure; in the equipment cabin, the GPS positioning module 2, the flight control module 4 and the onboard development board 6 are connected with the flight control module 4, and the flight control module 4 is connected with the GPS module.

In this embodiment, launch folding many rotor unmanned aerial vehicle's fuselage for streamlined design, be equipped with radome fairing 1 at the fuselage head, it can make unmanned aerial vehicle reduce the fuselage resistance in the flight in the time of parcel fuselage inside components and parts.

The four horn 8 symmetry are installed on top backup pad 15, and motor 9 is installed respectively to the outer end of horn 8, installs rotor 7 on the output shaft of motor 9.

An electronic speed regulator 10 and a communication module 11 are arranged in the central cabin, the electronic speed regulator 10 is respectively connected with the motor 9, and meanwhile, the electronic speed regulator 10 and the communication module 11 are both connected with the flight control module 4, and the embodiment adopts compact layout and fully utilizes space.

The battery compartment 12 is located below the central compartment, and is used for loading the lithium battery pack of the unmanned aerial vehicle to supply power for the whole unmanned aerial vehicle. The unmanned aerial vehicle lithium battery pack is installed in the battery compartment 12 to facilitate disassembly.

The load compartment is located below the battery compartment 12 and may be configured to mount a visible light load 14 or other functional device as desired. The visible light load 14 is arranged below the battery compartment 12, so that vision shielding of other devices is effectively avoided.

In this embodiment, the landing gear 13 is installed below the battery compartment 12, so that interference of the rotor 7 on the landing gear 13 can be effectively avoided.

As shown in fig. 2 and 3, the landing gear 13 at the bottom of the unmanned aerial vehicle is connected to the battery compartment 12 through a landing gear mount 131, and can vertically rotate around the landing gear mount 131. The landing gear 13 is provided with the limiting device 130 and the torsion spring 132 at the joint of the landing gear mounting seat 131, and the landing gear 13, the landing gear mounting seat 131, the limiting device 130 and the torsion spring 132 are matched to realize the up-down folding of the landing gear so as to be convenient to store and carry.

The torsion spring 132 is fixed on the pin, one end of the torsion spring abuts against the upper end face of the landing gear 13, and the other end abuts against the lower end face of the landing gear mounting seat 131. When the landing gear 13 is folded back up, the torsion spring 132 is in a torsion state, and the torsion force is large. During deployment of the landing gear 13, it is subjected to the torsion force of the torsion spring 132, rotating downwardly about the landing gear mount 131, the torsion force of the torsion spring 132 progressively decreasing.

As shown in fig. 3, the limiting device 130 includes a limiting cap 1301, a limiting spring 1302, and a limiting pin 1303, wherein the limiting spring 1302 is located in the limiting cap 1301, and the limiting pin 1303 is connected with the limiting spring 1302.

The limiting device 130 is fixed on the left side of the landing gear mounting seat 131, before the landing gear 13 is not fully unfolded, the limiting spring 1302 of the limiting device 130 is in a compressed state, the limiting pin 1303 is subjected to the elastic force of the limiting spring 1302, the right end face of the limiting pin 1303 props against the left end face of the landing gear 13 until the left end face of the landing gear 13 is separated from the limiting pin 1303, and the limiting pin 1303 moves rightwards and passes through a limiting device mounting hole on the landing gear mounting seat 131. The landing gear 13 continues to rotate downward, but when the upper end surface of the landing gear 13 comes into contact with the stopper pin 1303 again, the landing gear 13 cannot continue to rotate due to the obstruction of the stopper pin. At this time, the torsion spring 132 is not returned to the original state, and the torsion force is still present. The torsion force of the torsion spring 132 balances the thrust force of the stopper pin 1303, and the landing gear 13 is fixed.

As shown in fig. 1, 4 and 5, a horn fixing plate 804 is connected between the horn 8 and the top support plate 15, and the horn fixing plate 804 includes four square columns in a gantry structure. The arm 8 is hinged to two square posts of the arm fixing plate 804 through screw positioning pins, and the arm 8 has only one rotational degree of freedom, namely, can vertically rotate around the arm fixing plate 804. The tail part on the horn 8 is provided with a spring mounting seat, one end of a spring 801 is connected with the horn spring mounting seat, the other end of the spring 801 is connected with a spring mounting hole of the top supporting plate 15, and the central axis of the spring 801 and the plane of rotation of the horn are positioned on the same platform and are in a stretching state.

Two hooks 803 which are arranged in opposite directions are hinged with the gantry on the horn fixing plate 804 through hook positioning pins, and can vertically rotate around the gantry. A gap is formed between the two hooks 803 for accommodating the tail end of the arm 8. The torsion spring 802 is hinged with the gantry through a torsion spring positioning pin, one end of the torsion spring abuts against the back of the clamping hook 803, and the other end of the torsion spring abuts against the upper end of the gantry, so that rotation of the clamping hook 803 is restrained. The hook 803 is in an initial state in a vertical state due to the blocking of the limiting beam 805 of the gantry and the elastic force of the torsion spring 802. In the process of rotating the horn 8 from bottom to top, when the tail end of the horn 8 contacts with the hooks 803 positioned on the same plane, the hooks 803 are pushed to rotate anticlockwise (to be spread outwards) under the action of the tension force of the springs 801 until the tail end of the horn 8 is separated from the ends of the hooks 803. Since the hook 803 is subject to the elastic force of the torsion spring 802, after the end of the hook 803 is separated from the tail end of the arm 8, the hook 803 is rotated clockwise to return to the initial vertical state (locked inwards). When the upper end surface of the arm 8 is overlapped with the lower end surface of the hook 803, the arm 8 is fully unfolded, and the arm 8 is limited and fixed by the hook 803. Through the design of the structure, the movement of the horn 8 at an angle of 0-90 degrees is realized, so that the catapulting folding multi-rotor unmanned aerial vehicle can be automatically unfolded and can quickly enter a working state in the air; meanwhile, the arm of the catapulting folding multi-rotor unmanned aerial vehicle can be folded and contracted, and the catapulting folding multi-rotor unmanned aerial vehicle can be conveniently installed in the cylinder barrel.

As shown in fig. 6, the battery compartment 12 is formed by vertical columns 121, a battery compartment baffle 120 and a supporting plate 122, wherein the supporting plate 122 comprises an upper supporting plate and a lower supporting plate, the upper and lower parts of the battery compartment 12 are distributed, four vertical columns 121 are connected between the upper and lower supporting plates, and the four vertical columns 121 are circumferentially distributed and are used for bearing the gravity of the lithium battery pack of the unmanned aerial vehicle. The battery compartment baffle 120 is installed on three faces formed by four vertical upright posts 121, can play a role in dust prevention and rain prevention, ensures the use safety of the lithium battery of the unmanned aerial vehicle, and prolongs the service life of the lithium battery. The battery compartment 12 is positioned at the middle lower part of the unmanned aerial vehicle, so that the battery can be conveniently installed, detached and replaced.

In this embodiment, the folding many rotor unmanned aerial vehicle of whole ejection adopts symmetrical design, battery compartment 12 and load cabin all are located the below in centre cabin, centre cabin is located top backup pad 15 and horn 8 hookup location, horn 8 is for top backup pad 15 symmetric distribution, this focus position that makes the folding many rotor unmanned aerial vehicle of whole ejection distributes in unmanned aerial vehicle central axis department and focus is located the below of lifting surface, the moment that the relative lifting surface of focus produced is opposite with the moment that external interference produced, will produce the inhibitory action to interference vibration, thereby guarantee unmanned aerial vehicle has better stability in the flight.

The utility model provides a thinking of an ejection folding multi-rotor unmanned aerial vehicle, and a plurality of methods and approaches for realizing the technical scheme are provided, the above is only a preferred embodiment of the utility model, and it should be pointed out that a plurality of improvements and modifications can be made by those skilled in the art without departing from the principle of the utility model, and the improvements and modifications are also considered as the protection scope of the utility model. The components not explicitly described in this embodiment can be implemented by using the prior art.

Claims (9)

1. The utility model provides a launch folding many rotor unmanned aerial vehicle, includes fuselage and the horn that is connected with the fuselage, its characterized in that: the automatic unfolding limiting mechanism of the horn is connected between the horn and the machine body;

the automatic horn unfolding limiting mechanism comprises a spring, a horn fixing plate and a horn locking device;

the arm is hinged with the arm fixing plate, one end of the spring is connected with the machine body, the other end of the spring is connected with the arm, and the spring can drive the arm to be unfolded outwards relative to the arm fixing plate;

the horn locking device locks the horn after the horn is unfolded.

2. The catapulting folding multi-rotor drone of claim 1, wherein: the horn locking device comprises two opposite hooks which are respectively hinged with the horn fixing plate;

the clamping hook and the arm fixing plate are provided with a torsion device, and the torsion device controls the vertical rotation of the clamping hook relative to the arm fixing plate;

and a gap for accommodating the horn is formed between the two opposite hooks, and the horn is limited in the gap by the hooks after the horn is unfolded.

3. The launch fold multi-rotor drone of any one of claims 1 to 2, wherein: the landing gear is arranged below the machine body, and an automatic landing gear unfolding limiting mechanism is arranged between the machine body and the landing gear.

4. The catapulting folding multi-rotor drone of claim 3, wherein: the landing gear automatic unfolding limiting mechanism comprises a mounting seat, a limiter and a torsion device;

the landing gear is hinged with the mounting seat, and a torsion device is connected between the landing gear and the mounting seat;

the landing gear is restrained from rotating outwards by the limiter after the landing gear is unfolded.

5. The catapulting folding multi-rotor drone of claim 4, wherein: the limiting device comprises a limiting pin and a limiting spring, wherein the limiting pin is connected with the limiting spring, and the limiting pin is positioned on one side of the landing gear;

when the landing gear is unfolded, the limiting pin automatically stretches out to limit the landing gear to rotate outwards.

6. The launch fold multi-rotor drone of any one of claims 1 to 2, wherein: the machine body comprises an equipment cabin, a center cabin, a battery cabin and a load cabin;

the central cabin is connected with the horn, and a GPS positioning module and a flight control module are arranged in the central cabin;

the equipment cabin is positioned above the central cabin, and a communication module and an unmanned aerial vehicle electronic regulation module are installed in the equipment cabin;

the battery compartment is positioned below the central compartment;

the load cabin is positioned below the battery cabin and is used for arranging the visible light detection load.

7. The catapulting folding multi-rotor drone of claim 6, wherein: the equipment pod includes a fairing.

8. The catapulting folding multi-rotor drone of claim 6, wherein: the battery compartment comprises vertical upright posts, a baffle plate and a supporting plate;

the four vertical upright posts are circumferentially distributed, and two ends of each vertical upright post are respectively connected with the supporting plate;

and a baffle is arranged on any three surfaces formed by the four vertical upright posts.

9. The launch fold multi-rotor drone of any one of claims 1 to 2, wherein: the unmanned aerial vehicle adopts symmetrical design, and its focus position distributes in unmanned aerial vehicle central axis department and focus is located the below of lifting surface.

Images