CN215205335U

CN215205335U - Unmanned aerial vehicle fuselage structure

Info

Publication number: CN215205335U
Application number: CN202121407488.1U
Authority: CN
Inventors: 周鹏; 陈章国; 姜鹏瀚
Original assignee: Avic Zhuhai General Aviation Co ltd
Current assignee: Avic Zhuhai General Aviation Co ltd
Priority date: 2021-06-23
Filing date: 2021-06-23
Publication date: 2021-12-17
Anticipated expiration: 2031-06-23

Abstract

The utility model discloses an unmanned aerial vehicle fuselage structure, including the fuselage body, the fuselage body includes the bottom plate, the bottom plate is located the inside one side fixed mounting of fuselage body has levelling device and control box, levelling device includes displacement mechanism and balancing piece, the control box with the displacement mechanism electricity is connected, is used for control the displacement mechanism is right the position that the balancing piece was located is adjusted, through setting up levelling device inside the fuselage body, has avoided the influence of external air current to the levelling device, through the displacement mechanism makes the balancing piece can be to the opposite direction removal of the arbitrary inclination of fuselage to the regulation of balancing piece position, makes the fuselage can restore balance through adjusting the focus at once.

Description

Unmanned aerial vehicle fuselage structure

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is an unmanned aerial vehicle fuselage structure.

Background

The unmanned plane is an unmanned plane mainly controlled by radio remote control or self program, has no cockpit, but is provided with an automatic pilot, a program control device and other equipment, and personnel on the ground, a naval vessel or a mother machine remote control station can track, position, remotely control, telemeter and digitally transmit the unmanned plane through radar and other equipment.

At present, current unmanned aerial vehicle is because the size is little, the quality is light, receives wind-force, wind direction air current influence easily and takes place to rock even turn on one's side at the flight in-process, and is wayward when flying, and the equilibrium is poor, if not in flight in time adjustment, probably takes place equipment to turn on one's side and drops the equipment damage that causes.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an unmanned aerial vehicle fuselage structure, if meet wind-force weather and take place to rock the fuselage when slope in flight process, can adjust rapidly, guarantee unmanned aerial vehicle's steady flight.

In order to achieve the above object, the utility model provides a following technical scheme:

preferably, the unmanned aerial vehicle fuselage structure comprises a fuselage body, wherein the fuselage body comprises a pair of side plates, connectors are arranged on two sides of the side plates, the connectors are used for fixedly mounting a rotor of the unmanned aerial vehicle, the fuselage body further comprises a front end cover and a bottom plate, the front end cover is detachably connected with the fuselage body, a battery can be placed on the front end cover when the front end cover is opened, mounting ports are arranged on two sides of the bottom plate and used for fixedly mounting an undercarriage of the unmanned aerial vehicle, a leveling device and a control box are fixedly mounted on one side of the bottom plate, which is positioned in the fuselage body, the leveling device comprises a shifting mechanism and a balancing block, the control box is electrically connected with the shifting mechanism and is used for controlling the shifting mechanism to adjust the position of the balancing block, and when the fuselage is easily influenced by wind power and wind direction and swings to the front and back direction or the left and right direction in the flying process, the control box drives the position changing mechanism to adjust the balance block to the direction opposite to the offset of the machine body, so that the center of gravity can be immediately adjusted, and the machine body is restored to balance.

Preferably, the displacement mechanism includes that the circumference shifts the subassembly and radially shifts the subassembly, the circumference shifts the subassembly and includes driver part and rotary part, driver part is used for the drive rotary part carries out rotary motion, radially shift the subassembly and fix on the rotary part, rotary part drives radially shift the subassembly and carries out rotary motion, the balancing piece slidable mounting is in radially shift on the subassembly, circumference displacement mechanism is used for to installing balancing piece on the subassembly that radially shifts carries out position control, and radial direction's position control is made to the balancing piece to radially shift the subassembly, and circumferential direction's position control is made to the balancing piece to the subassembly that shifts simultaneously, makes the balancing piece can move to arbitrary position of the interval within range of the subassembly that circumferentially shifts, has great leveling scope.

Preferably, the driver part includes first motor, rotary part includes the support column, and fixes the mount pad of first motor one side is kept away from to the support column, the coaxial fixed mounting of support column is in on the output of first motor, rotary part still includes an annular frame and a plurality of supporting beam, a plurality of supporting beam's one end is fixed on the support column, the other end is fixed annular frame is last, a supporting beam with form first contained angle between the support column, the subassembly setting that radially shifts is in the mount pad with between the annular frame, the home range that is the balancing piece is in annular frame's rotation range.

Preferably, the radial displacement assembly comprises a driving unit and a guiding unit, one end of the guiding unit is fixed on the mounting seat, the other end of the guiding unit is fixed on the annular frame, and the driving unit drives the balance block to slide on the guiding unit, so that the moving area of the balance block on the guiding unit is equivalent to the radius of the circumferential displacement assembly.

Preferably, the guide unit includes a pair of end plates, and is a pair of the end plates are fixed respectively the mount pad with on the ring frame, and is a pair of the mutual parallel arrangement of end plate, and the distance between a pair of end plates is equivalent to ring frame's radius promptly, the guide unit still includes rotary rod and symmetry setting and is in the guide bar of rotary rod both sides, the rotary rod with the guide bar all runs through the balancing piece, the rotary rod is equipped with the screw thread region, and the screw thread region slightly is less than the distance between a pair of end plates, the rotary rod with balancing piece threaded connection, drive unit includes the second motor, the rotary rod is close to the one end fixed mounting of mount pad is in on the output shaft of second motor, the rotary rod both ends respectively with a pair of the end plate is rotated and is connected, when the second motor rotates, drives and rotates with the coaxial fixed rotary rod of second motor, because the rotating rod is in threaded connection with the balance block, and the balance block penetrates through the guide rod, the balance block is driven to move back and forth in the rotating area of the rotating rod.

Preferably, the mounting seat and the annular frame are located on the same horizontal plane, so that the radial displacement assembly fixed on the mounting seat and the annular frame is located on the same horizontal plane, and the balance block is convenient to move.

Preferably, still fixed mounting has a level sensor on the mount pad, level sensor with the control box electricity is connected, and when level sensor sensed the fuselage and takes place the slope, can pass to the control box with the signal to make control box control deflection mechanism adjust the position of balancing piece, deflection mechanism consequently has faster response speed, can even correct the slope of fuselage.

Preferably, the rotary rod is provided with a bearing at the joint of the pair of end plates, so that the friction force generated by the rotary rod and the pair of end plates in a rotary connection is reduced, and the rotary resistance of the rotary rod is small and stable.

Preferably, the first included angle ranges from 40 degrees to 60 degrees, when the first included angle between the support beam and the support column is smaller than 40 degrees, the rotation range of the annular frame fixed on the support beam is small, the movement range of the balance block is too small, when the first included angle is larger than 60 degrees, the pressure of the balance block on the support beam cannot be well dispersed on the support column, and the support beam has the risk of breakage after the working time is long.

Preferably, support column, supporting beam and ring frame are hollow structure, can effectually alleviate levelling device's weight, do benefit to unmanned aerial vehicle's flight.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model discloses a fixed mounting levelling device and balancing piece on the inside bottom plate of fuselage body compare in the fuselage outside with traditional levelling device setting, have reduced the influence of wind-force to levelling device to set up level sensor and in time to fuselage slope signals, make levelling device response speed faster.

The utility model discloses a set up circumference subassembly and the radial subassembly that shifts, because the subassembly that radially shifts is fixed on the subassembly that shifts of circumference, the subassembly that shifts of circumference can drive the subassembly that radially shifts and carry out rotary motion, again because balancing piece slidable mounting is on the subassembly that radially shifts, make the balancing piece can be simultaneously along the subassembly that radially shifts and be linear motion, and be rotary motion in the within range of the subassembly that shifts of circumference, therefore the balancing piece can move to the arbitrary position of subassembly within range that shifts of circumference, make it rebalance through moving to the opposite direction with the arbitrary angle of fuselage slope, great accommodation has.

Drawings

Fig. 1 is a schematic structural view of a fuselage body of the unmanned aerial vehicle fuselage structure of the present invention;

fig. 2 is a front view of the unmanned aerial vehicle body structure after the front end cover is opened;

fig. 3 is a schematic structural view of a leveling device of the unmanned aerial vehicle body structure of the present invention;

fig. 4 is a front view of the circumferential deflection component of the unmanned aerial vehicle body structure of the present invention;

fig. 5 is the utility model relates to a radial top view that shifts subassembly of unmanned aerial vehicle fuselage structure.

In the figure: 1. a body; 11. a side plate; 12. a connecting port; 13. a front end cover; 14. a base plate; 15. An installation port; 2. a leveling device; 3. a control box; 4. a counterbalance; 5. a circumferential deflection assembly; 51. a first motor; 52. a support pillar; 53. an annular frame; 54. a support beam; 55. a mounting seat; 6. a radial deflection assembly; 61. an end plate; 62. rotating the rod; 63. a guide bar; 64. a second motor; 7. a level sensor; 8. and a bearing.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

An embodiment of the present invention is described in further detail below:

as shown in fig. 1, an unmanned aerial vehicle fuselage structure, including fuselage body 1, fuselage body 1 includes a pair of curb plate 11, and is a pair of the both sides of curb plate 11 all are equipped with connector 12, connector 12 is used for fixed mounting unmanned aerial vehicle's rotor, and the rotor is also called the lift screw, is unmanned aerial vehicle's main lift part, fuselage body 1 still includes front end housing 13 and bottom plate 14, front end housing 13 with fuselage body 1 can dismantle the connection, opens front end housing 13 can place the battery, the both sides of bottom plate 14 are equipped with installing port 15 for fixed mounting unmanned aerial vehicle's undercarriage.

As shown in fig. 2, one side fixed mounting that bottom plate 14 is located fuselage body 1 inside has levelling device 2 and control box 3, levelling device 2 includes displacement mechanism and balancing piece 4, control box 3 with displacement mechanism electricity is connected, control box 3 is used for controlling displacement mechanism is right the position that balancing piece 4 was located is adjusted, when the fuselage is influenced by wind-force, wind direction air current and is rocked the skew to the front and back or left and right directions easily in flight, control box 3 drives displacement mechanism and adjusts balancing piece 4 to the opposite direction with the fuselage skew, can adjust the focus immediately, makes the fuselage restore balance.

As shown in fig. 3, the indexing mechanism comprises a circumferential indexing assembly 5 and a radial indexing assembly 6, the circumferential indexing assembly 5 comprises a driving part and a rotating part, the driving component is used for driving the rotating component to rotate, the radial deflection component 6 is fixed on the rotating component, the rotating component drives the radial deflection component 6 component to rotate, the balance block 4 is slidably mounted on the radial deflection component 6, the circumferential deflection mechanism is used for adjusting the position of the balance weight 4 arranged on the radial deflection component 6, the radial deflection component 6 adjusts the position of the balance weight 4 in the radial direction, meanwhile, the circumferential deflection component 5 adjusts the position of the balance block 4 in the circumferential direction, and the balance block 4 can move to any position in the range of the circumferential deflection component 5, so that the leveling range is large.

Specifically, as shown in fig. 3 and 4, the driving component includes a first motor 51, the rotating component includes a supporting column 52, and a mounting seat 55 fixed on a side of the supporting column 52 away from the first motor 51, the mounting seat 55 and the annular frame 53 are located on the same horizontal plane, so that the radial displacement assemblies 6 fixed on the mounting seat 55 and the annular frame 53 are located on the same horizontal plane, which facilitates the movement of the balance weight 4. The coaxial fixed mounting of support column 52 is in on the output of first motor 51, rotary part still includes annular frame 53 and a plurality of supporting beam 54, and a plurality of supporting beam 54's one end is fixed on the support column 52, and the other end is fixed on the annular frame 53, supporting beam 54 with form first contained angle between the supporting beam 52, radial deflection subassembly 6 sets up mount pad 55 with between the annular frame 53, the rotation range of annular frame 53 is balance weight 4's home range promptly.

As shown in fig. 4, the radial displacement assembly 6 includes a driving unit and a guiding unit, one end of the guiding unit is fixed on the mounting seat 55, the other end of the guiding unit is fixed on the annular frame 53, the driving unit drives the balance weight 4 to slide on the guiding unit, and the moving area of the balance weight 4 on the guiding unit corresponds to the radius of the circumferential displacement assembly 5.

As shown in fig. 2 and 3, the mounting seat 55 is further fixedly provided with a level sensor 7, the level sensor 7 is electrically connected with the control box 3, and when the level sensor 7 senses that the body is inclined, a signal is transmitted to the control box 3, so that the control box 3 controls the displacement mechanism to adjust the position of the balance weight 4, and the displacement mechanism has a faster response speed, even if the inclination of the body is corrected.

As shown in fig. 3 and 5, the guiding unit includes a pair of end plates 61, a pair of end plates 61 are respectively fixed on the mounting base 55 and the annular frame 53, and a pair of end plates 61 are arranged in parallel with each other, the guiding unit further includes a rotating rod 62 and guiding rods 63 symmetrically arranged on two sides of the rotating rod 62, the rotating rod 62 and the guiding rods 63 both penetrate through the balance weight 4, the rotating rod 62 is provided with a threaded area, the threaded area is slightly smaller than the distance between the pair of end plates 61, the rotating rod 62 is in threaded connection with the balance weight 4, the driving unit includes a second motor 64, one end of the rotating rod 62 close to the mounting base 55 is fixedly mounted on an output shaft of the second motor 64, two ends of the rotating rod 62 are respectively in rotational connection with the pair of end plates 61, and when the second motor 64 rotates, the rotating rod 62 coaxially fixed with the second motor 64 is driven to rotate, since the rotating rod 62 is screwed to the weight 4 and the weight 4 penetrates the guide rod 63, the weight 4 is driven to move back and forth in the rotating area of the rotating rod 62.

Preferably, as shown in fig. 3 and 4, a bearing 8 is arranged at the connection position of the rotating rod 62 and the pair of end plates 61, so that the friction force generated by the rotating connection of the rotating rod and the pair of end plates 61 is reduced, and the rotating resistance of the rotating rod is small and stable; the first included angle ranges from 40 degrees to 60 degrees, when the first included angle between the supporting beam 54 and the supporting column 52 is smaller than 40 degrees, the rotation range of the annular frame 53 fixed on the supporting beam 54 is small, so that the movement range of the balance weight 4 is too small, when the first included angle is larger than 60 degrees, the pressure of the balance weight 4 on the supporting beam 54 cannot be well dispersed on the supporting column 52, and the supporting beam 54 has a risk of breaking after the working time is long; the support column 52, the support beam 54 and the annular frame 53 are all hollow structures, so that the weight of the leveling device 2 can be effectively reduced, and the unmanned aerial vehicle can fly in an advantageous manner.

The working principle is as follows:

when the fuselage is affected by wind force and wind direction airflow and is shaken and deviated in the flying process, the level sensor 7 immediately transmits signals to the control box 3, the control box 3 controls the circumferential displacement component 5 and the radial displacement component 6 to start working, at the moment, the second motor 64 starts to rotate to drive the rotating rod 62 coaxially fixed with the second motor 64 to rotate, as the rotating rod 62 is in threaded connection with the balance weight 4 and the balance weight 4 penetrates through the guide rod 63, the balance weight 4 can be driven to linearly move in the threaded area of the rotating rod 62, meanwhile, the first motor 51 drives the annular frame 53 fixed on the support beam 54 to rotate when rotating, as the radial displacement component 6 is fixedly arranged on the circumferential displacement component 5, the second motor 64 is fixed on the mounting seat 55, the pair of end plates 61 are respectively arranged on the mounting seat 55 and the annular frame 53, the balance weight 4 can simultaneously linearly move along the radial displacement component 6, and rotating in the range of the circumferential deflection component 5, so that the balance weight 4 can move to any position in the range of the annular frame 53, and the balance weight 4 moves towards the direction inclined at any angle with the machine body to adjust the gravity center of the machine body so as to restore the balance.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Claims

1. The utility model provides an unmanned aerial vehicle fuselage structure, includes fuselage body (1), its characterized in that: the machine body (1) comprises a pair of side plates (11), connecting ports (12) are arranged on two sides of the side plates (11), the connecting port (12) is used for fixedly mounting a rotor wing of the unmanned aerial vehicle, the fuselage body (1) further comprises a front end cover (13) and a bottom plate (14), the front end cover (13) is detachably connected with the machine body (1), mounting ports (15) are arranged on two sides of the bottom plate (14), the landing gear is used for fixedly mounting the unmanned aerial vehicle, one side of the bottom plate (14) positioned in the fuselage body (1) is fixedly provided with a leveling device (2) and a control box (3), the leveling device (2) comprises a position changing mechanism and a balance block (4), the control box (3) is electrically connected with the position changing mechanism, the control box (3) is used for controlling the displacement mechanism to adjust the position of the balance block (4).

2. The airframe structure of claim 1, wherein: the deflection mechanism comprises a circumferential deflection component (5) and a radial deflection component (6), the circumferential deflection component (5) comprises a driving part and a rotating part, the driving part is used for driving the rotating part to perform rotary motion, the radial deflection component (6) is fixed on the rotating part, the rotating part drives the radial deflection component (6) to perform rotary motion, the balance weight (4) is slidably installed on the radial deflection component (6), and the circumferential deflection mechanism is used for adjusting the position of the balance weight (4) installed on the radial deflection component (6).

3. The airframe structure of claim 2, wherein: the driving part comprises a first motor (51), the rotating part comprises a supporting column (52) and is fixed on a mounting seat (55) at one side of the supporting column (52) far away from the first motor (51), the supporting column (52) is coaxially and fixedly installed on the output end of the first motor (51), the rotating part further comprises an annular frame (53) and a plurality of supporting beams (54), one end of each supporting beam (54) is fixed on the supporting column (52), the other end of each supporting beam is fixed on the annular frame (53), a first included angle is formed between each supporting beam (54) and the supporting column (52), and the radial deflection assembly (6) is arranged between the mounting seat (55) and the annular frame (53).

4. The airframe structure of claim 3, wherein: the radial displacement assembly (6) comprises a driving unit and a guide unit, one end of the guide unit is fixed on the mounting seat (55), the other end of the guide unit is fixed on the annular frame (53), and the driving unit drives the balance block (4) to slide on the guide unit.

5. The airframe structure of claim 4, wherein: the guide unit comprises a pair of end plates (61), the pair of end plates (61) are respectively fixed on the mounting seat (55) and the annular frame (53), and a pair of the end plates (61) are arranged in parallel with each other, the guide unit further comprises a rotating rod (62) and guide rods (63) symmetrically arranged at both sides of the rotating rod (62), the rotating rod (62) and the guide rod (63) both penetrate through the balance block (4), the rotating rod (62) is provided with a threaded area, the rotating rod (62) is in threaded connection with the balance block (4), the driving unit comprises a second motor (64), one end of the rotating rod (62) close to the mounting seat (55) is fixedly mounted on an output shaft of the second motor (64), and two ends of the rotating rod (62) are respectively and rotationally connected with the pair of end plates (61).

6. The airframe structure of claim 3, wherein: the mounting seat (55) and the annular frame (53) are on the same horizontal plane.

7. The airframe structure of claim 3, wherein: and a horizontal sensor (7) is fixedly mounted on the mounting seat (55), and the horizontal sensor (7) is electrically connected with the control box (3).

8. The airframe structure of claim 5, wherein: and a bearing (8) is arranged at the joint of the rotating rod (62) and the pair of end plates (61).

9. An unmanned aerial vehicle fuselage structure as defined in any of claims 3-8, wherein: the first included angle ranges from 40 degrees to 60 degrees.

10. The airframe structure of claim 9, wherein: the supporting columns (52), the supporting beams (54) and the annular frame (53) are all hollow structures.