CN220646620U

CN220646620U - Shock-absorbing device of flight controller

Info

Publication number: CN220646620U
Application number: CN202321547323.3U
Authority: CN
Inventors: 程运昌
Original assignee: Liaoning Dacheng Electronic Technology Co ltd
Current assignee: Liaoning Dacheng Electronic Technology Co ltd
Priority date: 2023-06-16
Filing date: 2023-06-16
Publication date: 2024-03-22
Anticipated expiration: 2033-06-16

Abstract

The utility model discloses a shock absorption device of a flight controller, which comprises a protective shell: the utility model discloses a protection shell, including protection shell, the inboard bottom fixedly connected with sponge board of protection shell, a plurality of bar grooves have been seted up to the upside of sponge board, the upside of sponge board is provided with flight controller main part, the outside of flight controller main part is provided with protection unit, protection unit includes the spout, the inner wall at protection shell is seted up to the spout, the outside of flight controller main part is provided with a plurality of fixture blocks, the equal fixedly connected with of both sides of fixture block changes piece two. Through being provided with protective housing, fixture block, spout, slider, commentaries on classics piece one, commentaries on classics piece two, control panel, connecting plate and attenuator two, be convenient for to control panel and the connecting plate on a plurality of fixture blocks, make the influence of external vibrations to flight controller main part reduce, avoid influencing flight controller's use because of vibrations are great.

Description

Shock-absorbing device of flight controller

Technical Field

The utility model relates to the technical field of flight controllers, in particular to a shock absorption device of a flight controller.

Background

Flight control, also known as flight control, is a component used to assist or fully autonomously control other systems and components of an aircraft during take-off, cruise, landing, etc. A flight controller is arranged on the unmanned aerial vehicle, so that the unmanned aerial vehicle can be conveniently controlled to fly.

By searching, the application number is 202221046907.8, a controller on an aircraft is provided, and a plurality of stripe grooves are formed in the inner wall of the shock absorption interlayer 3 and the bottom surface in the inner cavity. The contact area between the controller body 4 and the damping interlayer 3 can be reduced due to the action of the stripe grooves, so that friction force can be reduced, and the controller body 4 can be placed in the inner cavity more conveniently; in addition, since the streak grooves are formed, the ribs formed by the streak grooves have a more flexible deformability, and thus the vibration amplitude of the controller main body 4 can be suppressed more advantageously.

Above-mentioned be provided with a plurality of stripe grooves on the shock attenuation intermediate layer, conveniently reduce the influence of vibrations to flight controller main part, but unmanned aerial vehicle is when flying, because the accident falls down, and the vibrations impact force that receives is big, only relies on the friction between reduction flight controller and the shock attenuation intermediate layer, can not be fine weaken big vibrations and impact force, makes flight controller damage.

Disclosure of Invention

In order to overcome the defect that the flight controller is easy to damage due to large external vibration in the prior art, one of the purposes of the utility model is to provide a shock absorption device for the flight controller.

One of the purposes of the utility model is realized by adopting the following technical scheme: a flight controller damping device comprising a protective housing: the bottom of the inner side of the protective shell is fixedly connected with a sponge plate, a plurality of strip-shaped grooves are formed in the upper side of the sponge plate, a flight controller main body is arranged on the upper side of the sponge plate, and a protective unit is arranged on the outer side of the flight controller main body;

the protection unit comprises a sliding groove, the inner wall at the protective housing is seted up to the sliding groove, the outside of flight controller main part is provided with a plurality of fixture blocks, the equal fixedly connected with in both sides of fixture block changes the piece two the outside of changeing the piece two all rotates and is connected with the control panel, the inboard sliding connection of sliding groove has the slider, the outside fixedly connected with of slider changes the piece one, change the piece one and be connected with the control panel turn to, two the upside of control panel all rotates and is connected with the connecting plate, the upside of connecting plate rotates and is connected with the connecting block, the upside fixedly connected with fixed block of connecting block, fixedly connected with attenuator two between fixed block and the protective housing.

According to the flight controller damping device, a damper I is fixedly connected between the outer side of the sliding block and the inner wall of the sliding groove. Facilitating a reduction in the amplitude of slider movement.

According to the flight controller damping device, the control panel and the connecting plate are both arranged in an inclined structure. The clamping block is convenient to share the acting force.

According to the flight controller damping device, the clamping block is arranged in an L-shaped structure.

According to the flight controller damping device, the front side of the protective shell is provided with a wiring port. The flight controller main body is convenient to be connected with external equipment.

According to the flight controller damping device, a rubber plate is arranged on the upper side of the protective shell, and a cover plate is fixedly connected to the upper side of the rubber plate. Facilitating protection of the upper side of the aircraft body.

The beneficial effects are that:

through being provided with protective housing, fixture block, spout, slider, commentaries on classics piece one, commentaries on classics piece two, control panel, connecting plate and attenuator two, be convenient for to control panel and the connecting plate on a plurality of fixture blocks, make the influence of external vibrations to flight controller main part reduce, avoid influencing flight controller's use because of vibrations are great.

Additional aspects and advantages of the utility model will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the utility model.

Drawings

The utility model is further described below with reference to the drawings and examples;

FIG. 1 is a perspective view of the overall structure of a shock absorbing device for a flight controller according to the present utility model;

FIG. 2 is a perspective view of the inside of a protective housing of a shock absorbing device for a flight controller in accordance with the present utility model;

FIG. 3 is a perspective view of the flight controller damping device of the present utility model with the protective housing of the flight controller body removed;

fig. 4 is an enlarged view at a in fig. 3.

Legend description:

1. a protective housing; 2. a wiring port; 3. a rubber plate; 4. a cover plate; 5. a flight controller body; 6. a protection unit; 601. a chute; 602. a damper I; 603. a slide block; 604. a first rotating block; 605. a second rotating block; 606. a control board; 607. a clamping block; 608. a connecting plate; 609. a connecting block; 610. a fixed block; 611. a damper II; 7. a sponge plate; 8. a bar-shaped groove.

Detailed Description

Reference will now be made in detail to the present embodiments of the present utility model, examples of which are illustrated in the accompanying drawings, wherein the accompanying drawings are used to supplement the description of the written description so that one can intuitively and intuitively understand each technical feature and overall technical scheme of the present utility model, but not to limit the scope of the present utility model.

Referring to fig. 1 to 4, a shock absorbing device for a flight controller according to an embodiment of the present utility model includes a protective housing 1: the bottom of the inner side of the protective shell 1 is fixedly connected with a sponge plate 7, the upper side of the sponge plate 7 is provided with a plurality of strip-shaped grooves 8, the strip-shaped grooves 8 are convenient for reducing the release area of the sponge plate 7 and reducing the friction during vibration, the upper side of the sponge plate 7 is provided with a flight controller main body 5, the outer side of the flight controller main body 5 is provided with a protective unit 6, the front side of the protective shell 1 is provided with a wiring port 2, the wiring port 2 is used for connecting the flight controller main body 5 with external equipment, the upper side of the protective shell 1 is provided with a rubber plate 3, the upper side of the rubber plate 3 is fixedly connected with a cover plate 4, bolts are arranged between the cover plate 4 and the protective shell 1 to facilitate the disassembly of the cover plate 4,

the protection unit 6 comprises a chute 601, the chute 601 is arranged on the inner wall of the protection shell 1, a plurality of clamping blocks 607 are arranged on the outer side of the flight controller main body 5, the clamping blocks 607 are arranged in an L-shaped structure, two sides of each clamping block 607 are fixedly connected with a second rotating block 605, the outer sides of the two second rotating blocks 605 are rotatably connected with a control plate 606, the control plates 606 and the connecting plates 608 are arranged in an inclined structure, the inner sides of the chute 601 are slidably connected with a sliding block 603, the outer sides of the sliding blocks 603 are fixedly connected with a first rotating block 604, the first rotating block 604 and the control plates 606 are rotatably connected, the upper sides of the two control plates 606 are rotatably connected with a connecting plate 608, the upper sides of the connecting plates 608 are rotatably connected with a connecting block 609, the upper sides of the connecting blocks 609 are fixedly connected with a fixed block 610, a damper two 611 is fixedly connected between the fixed block 610 and the protection shell 1, a damper one 602 is fixedly connected between the outer sides of the sliding block 603 and the inner wall of the chute 601, when in use, when the outside impacts the protective shell 1, external vibration can act on the flight controller main body 5 to slightly move the flight controller main body 5, when in movement, the flight controller main body 5 drives the clamping blocks 607 to move, the clamping blocks 607 drive the control plates 606 on two sides to rotate, the control plates 606 drive the sliding blocks 603 to move, the first damper 602 weakens the movement amplitude of the sliding blocks 603, when the control plates 606 rotate, the two connection plates 608 are driven to rotate, the connection plates 608 drive the connection blocks 609 to move, the second damper 611 on the fixed block 610 is driven by the connection blocks 609 to move, the second damper 611 blocks the movement of the fixed block 610, the movement amplitude of the clamping blocks 607 on the control plates 606 is reduced, thereby reducing the vibration amplitude on the flight controller main body 5, reducing the influence of the external vibration on the flight controller main body 5, avoiding damage to the flight controller body 5.

Working principle: when the flight controller main body 5 is impacted by the outside, the outside impact causes the flight controller main body 5 to slightly move, and when the flight controller main body moves, the flight controller main body 5 drives the sliding block 603 to move through the clamping block 607 and the control board 606, the moving amplitude is reduced through the damper I602, and meanwhile, the moving amplitude is weakened again through the connecting board 608, the connecting block 609, the fixing block 610 and the damper II 611, so that the influence of vibration on the flight controller main body 5 is reduced, and the damage of the flight controller main body 5 is avoided.

The embodiments of the present utility model have been described in detail with reference to the accompanying drawings, but the present utility model is not limited to the above embodiments, and various changes can be made within the knowledge of one of ordinary skill in the art without departing from the spirit of the present utility model.

Claims

1. A damping device for a flight controller, characterized by comprising a protective casing (1): the bottom of the inner side of the protective shell (1) is fixedly connected with a sponge plate (7), a plurality of strip-shaped grooves (8) are formed in the upper side of the sponge plate (7), a flight controller main body (5) is arranged on the upper side of the sponge plate (7), and a protective unit (6) is arranged on the outer side of the flight controller main body (5);

protection unit (6) are including spout (601), the inner wall at protective housing (1) is seted up to spout (601), the outside of flight controller main part (5) is provided with a plurality of fixture blocks (607), the equal fixedly connected with of both sides of fixture block (607) changes piece two (605), two the outside of changeing piece two (605) all rotates and is connected with control panel (606), the inboard sliding connection of spout (601) has slider (603), the outside fixedly connected with of slider (603) changes piece one (604), change piece one (604) and control panel (606) to be connected with, two the upside of control panel (606) is all rotated and is connected with connecting plate (608), the upside of connecting plate (608) is rotated and is connected with connecting block (609), the upside fixedly connected with fixed block (610) of connecting block (609), fixedly connected with attenuator two (611) between fixed block (610) and protective housing (1).

2. The shock absorbing device for the flight controller according to claim 1, wherein a damper I (602) is fixedly connected between the outer side of the sliding block (603) and the inner wall of the sliding groove (601).

3. The flight controller vibration damper of claim 1, wherein the control board (606) and the connecting board (608) are both provided in an inclined configuration.

4. The flight controller damping device according to claim 1, wherein the latch (607) is provided in an L-shaped configuration.

5. The flight controller damping device according to claim 1, wherein the front side of the protective housing (1) is provided with a wiring port (2).

6. The flight controller damping device according to claim 1, wherein a rubber plate (3) is arranged on the upper side of the protective shell (1), and a cover plate (4) is fixedly connected to the upper side of the rubber plate (3).