CN218907645U - Rotor unmanned aerial vehicle with but automatic folding wing - Google Patents

Abstract

The utility model discloses a rotary wing type unmanned aerial vehicle with an automatically foldable wing, which consists of a wing folding mechanism, an adaptation mechanism and a safety recovery mechanism. The unmanned aerial vehicle is driven by only one group of second motors, two groups of plates are respectively in fit with the corresponding two groups of unmanned aerial vehicle wings through the transmission of the two groups of gears, the multiple groups of unmanned aerial vehicle wings can rotate downwards around the axial direction due to the rebound of the corresponding torsion springs, the folding work is completed quickly, otherwise, the unfolding work can be completed quickly, and the wing folding angle can be adjusted by changing the working mode of the motors; the adaptive mechanism is used for ensuring stable power supply of the first motors on the four groups of wings; the safety recovery mechanism realizes safety recovery mainly through parachuting. On one hand, the utility model solves the problems of space occupation and folding work of the corresponding wing driven by four groups of motors at present. On the other hand, the problem of safety protection and recovery that unmanned aerial vehicle directly falls aloft under the operation fault condition in the flight is solved.

Description

Rotor unmanned aerial vehicle with but automatic folding wing

Technical Field

The utility model relates to a rotary wing type unmanned aerial vehicle with an automatically foldable wing, and belongs to the technical field of unmanned aerial vehicles.

Background

Unmanned Aerial Vehicles (UAVs), which are unmanned aerial vehicles that are operated by radio remote control equipment and self-contained programming devices, or are operated autonomously, either entirely or intermittently, by an onboard computer.

In unmanned aerial vehicle use, in order to reduce occupation space, portable adopts the folding mode of wing to realize generally. Among the prior art, a rotor unmanned aerial vehicle wing folding device, the wing divide into first wing and second wing, connect through folding mechanism between first wing and the second wing, folding mechanism includes jacket, first arc cover, second arc cover and drive arrangement. Although the purpose of reducing space and being convenient to carry is achieved, the problem that four groups of wings are required to be correspondingly driven by four groups of motors to carry out folding work, the use of multiple motors not only can consume the electric quantity of the unmanned aerial vehicle, but also has the problem of high circuit design cost. Currently, in the use of unmanned aerial vehicles, unmanned aerial vehicle's safety protection technique is to be perfected. Because of factors such as mechanical failure, improper operation, external interference and the like, the falling event of the unmanned aerial vehicle frequently happens, and great economic loss and potential safety hazard are caused. In the prior art, the unmanned aerial vehicle parachute device has the problems of large volume, heavy weight, complex structure, high cost and the like.

Disclosure of Invention

The utility model aims at overcoming the defects of the prior art and provides a rotor unmanned aerial vehicle with an automatically foldable wing. The unmanned aerial vehicle mainly comprises a wing folding mechanism, an adaptation mechanism and a safety recovery mechanism. On the one hand, the problem of space occupation and the problem of folding work by driving the corresponding wings by using four groups of motors in the prior art are solved. On the other hand, the problem of safety protection and recovery of the unmanned aerial vehicle in the case of high altitude direct falling under the operation fault in the flight process is solved.

The technical scheme of the utility model is as follows:

the utility model provides a rotor unmanned aerial vehicle with but automatic folding wing, unmanned aerial vehicle 1 is last to have four groups first berth 2, four groups first berth 2 all rotates through connecting axle 22 and is connected with wing 3, four groups wing 3 with correspond all be provided with torsion spring 4 between the first berth 2.

Preferably, the bottom of the unmanned aerial vehicle 1 is connected with a first shell 5, the first shell 5 is rotationally connected with a group of circular shafts 62 through bearings, the circular shafts 62 and a motor shaft 61 horizontally placed side by side are respectively sleeved with gears 7, the gears 7 are meshed with each other, two groups of through grooves 8 are processed on the first shell 5, plate bodies 9 are fixedly connected on the motor shaft 61, the two groups of plate bodies 9 are respectively and correspondingly connected with the inner sides of the through grooves 8 in a sliding manner, the outer walls of the plate bodies 9 are respectively attached to the outer walls of the wings 3, and foot frames 21 are fixedly connected at the outer wall of the plate bodies 9.

Preferably, the unmanned aerial vehicle 1 is provided with four groups of second bunkers 10, and an adaptation mechanism is arranged in each second bunkers 10.

Preferably, the top of the unmanned aerial vehicle 1 is connected with a second shell 20, and a safety recovery mechanism is arranged in the second shell 20.

Preferably, the adaptation mechanism includes second berth 10 and wire 11, four groups second berth 10 are located first berth 2 top, four groups all are processed on the second berth 10 and are had wing through-hole 12, four groups wire 11 all connect from on the unmanned aerial vehicle 1, four groups wing through-hole 12 inboard respectively with correspond wire 11 outer wall leaves the clearance, four groups second berth 10 is inside all to be equipped with roller bearing 17, roller bearing 17 both ends with second berth 10 casing passes through the bearing and rotates and link to each other. The outer walls of the four groups of rollers 17 are respectively contacted with the outer walls of the corresponding leads 11, the inner sides of the four groups of second cabin positions 10 are fixedly connected with two groups of sliding rods 13, a plurality of groups of sliding rods 13 are respectively provided with a first spring 15, the outer walls of the sliding rods 13 are respectively connected with a sliding sleeve 14 in a sliding manner, every two groups of sliding sleeves 14 are respectively connected with a groove pulley 16, two ends of the first springs 15 are fixedly connected to the corresponding sliding sleeves 14 and the sliding rods 13, and the outer walls of the groove pulleys 16 are attached to the outer walls of the leads 11.

Preferably, the safety recovery mechanism mainly comprises a second shell 20, a through hole 39 is formed in the top of the second shell 20, a spring support 38 is installed in the second shell 20, a second spring 34 is installed on the outer wall of the spring support 38, and the second spring 34 is fixedly connected to the spring support 38 at the lower part and fixedly connected to the plate body 36 with the hook at the upper part; the second housing 20 is internally provided with a sensor 31 and a third motor 37. The output end of the third motor 37 is connected with a round rod 32, the round rod 32 is fixedly connected with a pressing plate 33 and a hatch cover 35 in sequence, and the hatch cover 35 is required to be attached to the top end inside the second shell 20.

Preferably, the second motor 23 is installed in the first housing 5, the output end of the motor is connected to the motor shaft 61, and the end of the motor shaft 61 supports the supporting seat 24.

Preferably, the four groups of wings 3 are provided with first motors 18, and the output ends of the four groups of first motors 18 are fixedly connected with fan blades 19.

The beneficial effects are that:

1. according to the utility model, wing folding is realized through cooperation among the wings, the plate body, the gears and the torsion springs, so that the occupied space of the unmanned aerial vehicle is reduced.

2. The utility model can complete the electric folding work of four groups of wings by only one group of second motors, and can realize the unfolding work on the contrary. The consumption of unmanned aerial vehicle self electric quantity has been reduced, and circuit design cost is lower relatively.

3. According to the utility model, the working mode of the motor can be adjusted, so that the wing can be folded at multiple angles, and smooth passing can be ensured when the wing passes through any complex and narrow space.

4. According to the utility model, through the cooperation among the sliding block and the sliding rod, the lead and the spring, the adaptation function is realized, and the stability of connecting the lead on the first motor with the power supply of the unmanned aerial vehicle body can be ensured when the wing rotates and folds or rotates and expands.

5. According to the utility model, through the cooperation of the sensor, the motor and the spring, the parachute landing mode is adopted, so that the safe recovery of the unmanned aerial vehicle in a fault state can be realized.

6. The safety recovery device has the advantages of small volume, light weight, simple structure and the like; can be used separately.

Drawings

Fig. 1 is a schematic diagram of the present utility model.

Fig. 2 is a schematic overall cross-sectional view of the present utility model.

Fig. 3 is a schematic top view of the first housing according to the present utility model.

Fig. 4 is an enlarged schematic view of the wing fold mechanism and adaptation mechanism of the present utility model.

Fig. 5 is a schematic top view of the adaptation mechanism of the present utility model.

FIG. 6 is a schematic cross-sectional view of the safety retrieval mechanism of the present utility model.

Identification description: 1. unmanned plane; 2. a first bunk; 3. a wing; 4. a torsion spring; 5. a first housing; 61. a motor shaft; 62. a circular shaft; 7. a gear; 8. a through groove; 9. a plate body; 10. the second cabin level; 11. a wire; 12. a wing through hole; 13. a slide bar; 14. a sliding sleeve; 15. a first spring; 16. groove pulleys; 17. a roller; 18. a first motor; 19. a fan blade; 20. a second housing; 21. a foot rest; 22. a connecting shaft; 23. a second motor; 24. a support base; 31. a sensor; 32. a round bar; 33 pressing plates; 34. a second spring; 35. a hatch cover; 36. a hook plate body; 37. a third motor; 38. a spring support; 39. and a through hole.

Detailed Description

In the description of the present utility model, unless otherwise indicated, the meaning of "a plurality" is two or more; furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. In the description of the present utility model, the terms "affixed," "mounted," "connected," and the like are to be construed broadly, unless explicitly stated and limited otherwise. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances. It should be noted that all directional indications (such as up, down, left, right, front, rear … …) are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indication is changed accordingly.

In the description of the present utility model, the wing fold section, the adaptation section, and the safety recovery section will be mainly described in detail.

In the specific implementation process of the wing folding part, the wing part has two action modes of folding action and unfolding action.

As shown in fig. 1-5. The following describes the embodiments taking the wing folding action as an example: the unmanned aerial vehicle 1 is provided with four groups of first bunkers 2, the four groups of first bunkers 2 are respectively connected with wings 3 through a connecting shaft 22 in a rotating way, the wings 3 can rotate around the connecting shaft 22, torsion springs 4 are respectively arranged between the four groups of wings 3 and the corresponding first bunkers 2, and under the action of the torsion springs 4, the wings 3 can rotate downwards around the connecting shaft 22. The bottom end of the unmanned aerial vehicle 1 is fixedly connected with a first shell 5, the first shell 5 is rotationally connected with a group of circular shafts 62 through bearings, the circular shafts 62 and a motor shaft 61 horizontally arranged side by side are respectively sleeved with gears 7, the two groups of gears 7 are meshed with each other, the first shell 5 is provided with two groups of through grooves 8, the circular shafts 62 and the motor shaft 61 are fixedly connected with plate bodies 9, the circular shafts 62 and the motor shaft 61 can drive the plate bodies 9 to rotate, the two groups of plate bodies 9 are respectively and slidably connected with the inner sides of the corresponding through grooves 8, the outer walls of the two groups of plate bodies 9 are respectively attached to the bottoms of the two groups of wings 3, and the plate bodies 9 can limit the rotation of the corresponding two groups of wings 3.

Through starting the second motor 23, drive the motor shaft 61 and rotate, and then can make through the transmission of two sets of gears 7 the circle axle 62 with motor shaft 61 drives simultaneously and corresponds plate body 9, respectively with circle axle 62 with motor shaft 61 and first casing 5 junction is the centre of a circle rotation downwards, cancel respectively two sets of plate body 9 and correspond the laminating of two sets of wings 3, and then four sets of wings 3 just accessible torsion spring 4's resilience moves downwards, accomplishes folding work. The whole occupation space of the unmanned aerial vehicle 1 can be reduced.

By controlling the inversion of the second motor 23, an automatic unfolding action of the wing 3 can be achieved.

It should be noted that, by changing the working mode of the second motor 23, the rotation angle of the plate body 9 can be adjusted, so as to realize multi-angle folding of the wing 3.

When the folding action is carried out, the corresponding implementation mode of the adapting mechanism is as follows: when the wing 3 drives the first motor 18 to fold downwards around the connecting shaft 22, the lead 11 is pulled, the groove pulley 16 and the sliding sleeve 14 are driven in the second cabin 10, and the lead 11 with the redundant length is further compensated outwards in the direction defined by the two groups of sliding rods 13 and is moved towards one end close to the unmanned aerial vehicle 1, so that the stability of connection between the first motor 18 and a power supply of the unmanned aerial vehicle 1 when the wing 3 drives the first motor 18 to fold in a rotating mode is ensured.

On the contrary, when the unfolding action is performed, under the action of the first spring 15, the wing 3 can be guaranteed to quickly retract the redundant part of the lead 11 into the second cabin 10 when the first motor 18 is driven to rotate and unfold.

As shown in fig. 6, the main embodiment of the safety recovery apparatus is: when the unmanned aerial vehicle 1 falls out of control due to failure, the sensor 31 detects abnormal data, sends a start instruction to the third motor 37, drives the round rod 32 to rotate, and then the hatch 35 is rotated and opened, and simultaneously the pressing plate 33 moves away from the top of the second spring 34, and the second spring 34 ejects the hook plate 36 out of the second shell 20 under the action of elasticity; the parachute is fully opened by utilizing the air resistance principle, so that the unmanned aerial vehicle 1 safely falls down in a parachute landing mode.

It should be noted that, in fig. 6, the hatch 35 needs to be attached to the top end of the inner portion of the second housing 20, and the hatch 35 can be rotated in a plane. The second spring 34 is normally required to be in a compressed state. The parachute is required to be orderly stacked between the hook plate body 36 and the pressing plate 33, and the parachute rope is connected to the hook position of the hook plate body 36.

While the utility model has been described with reference to the preferred embodiments, it will be understood by those skilled in the art that the foregoing and various other changes, omissions and deviations in the form and detail thereof may be made without departing from the scope of this utility model.

Claims (5)

1. Rotor unmanned aerial vehicle with but automatic folding wing, its characterized in that: the unmanned aerial vehicle (1) consists of a wing folding mechanism, an adaptation mechanism and a safety recovery mechanism; four groups of first bunkers (2) are arranged on the unmanned aerial vehicle (1), the four groups of first bunkers (2) are connected with wings (3) through connecting shafts (22) in a rotating mode, and torsion springs (4) are arranged between the four groups of wings (3) and the corresponding first bunkers (2); the unmanned aerial vehicle (1) bottom rigid coupling has first casing (5), first casing (5) are connected with a set of circle axle (62) through the bearing rotation, all cup joint gear (7) on circle axle (62) and motor shaft (61) placed rather than the level side by side, two sets of gear (7) intermeshing, processing has two sets of logical groove (8) on first casing (5), circle axle (62) with on motor shaft (61) all rigid coupling have plate body (9), two sets of plate body (9) respectively with correspond logical inslot side slip links to each other, two sets of plate body (9) outer wall is laminated with two sets of wing (3) outer wall respectively, two sets of plate body (9) outer wall department rigid coupling has foot rest (21.) unmanned aerial vehicle (1) is last to have four sets of second cabin positions (10), are equipped with adaptation mechanism in the second cabin position (10); the top of the unmanned aerial vehicle (1) is connected with a second shell (20), and a safety recovery mechanism is arranged in the second shell (20).

2. A rotary-wing drone with automatically collapsible wings as recited in claim 1, wherein: the adaptation mechanism comprises a second cabin position (10) and a wire (11), wherein four groups of second cabin positions (10) are positioned at the top end of a first cabin position (2), four groups of second cabin positions (10) are respectively provided with wing through holes (12) in a processing mode, four groups of wire (11) are respectively connected with unmanned aerial vehicle (1), gaps are reserved between the inner sides of the wing through holes (12) and the outer walls of the wire (11), four groups of second cabin positions (10) are respectively provided with rolling shafts (17) through bearing rotation, the outer walls of the four groups of rolling shafts (17) are respectively in contact with the outer walls of the wire (11), two groups of sliding rods (13) are respectively fixedly connected with the inner sides of the second cabin positions (10), a plurality of groups of first springs (15) are respectively arranged on the sliding rods (13), the outer walls of the plurality of groups of sliding rods (13) are respectively connected with sliding sleeves (14), the inner sides of the wing through holes (12) are respectively connected with groove pulleys (16), and the plurality of groups of first springs (15) are respectively fixedly connected with the sliding sleeves (14) and correspond to the two ends of the sliding sleeves (16) and are respectively attached to the outer walls of the sliding sleeves (16).

3. A rotary-wing drone with automatically collapsible wings as recited in claim 1, wherein: the safety recovery mechanism mainly comprises a second shell (20), a through hole (39) is formed in the top of the second shell (20), a spring support (38) is arranged in the second shell (20), a second spring (34) is arranged on the outer wall of the spring support (38), the second spring (34) is fixedly connected onto the spring support (38) in a lower mode, and is fixedly connected onto a plate body (36) with a hook in an upper mode; install sensor (31), third motor (37) in second casing (20), with third motor (37) output is connected with round bar (32), round bar (32) rigid coupling has clamp plate (33), cabin cover (35) in proper order, cabin cover (35) need with the laminating of the inside top of second casing (20).

4. A rotary-wing drone with automatically collapsible wings as recited in claim 1, wherein: the motor is characterized in that a second motor (23) is arranged in the first shell (5), the output end of the motor is connected with the motor shaft (61), and the tail end of the motor shaft (61) is supported with a supporting seat (24).

5. A rotary-wing drone with automatically collapsible wings as recited in claim 1, wherein: the four groups of wings (3) are provided with first motors (18), and the output ends of the four groups of first motors (18) are fixedly connected with fan blades (19).

Images