CN216186017U

CN216186017U - Shockproof aircraft landing gear component

Info

Publication number: CN216186017U
Application number: CN202122364412.1U
Authority: CN
Inventors: 牛霞
Original assignee: Harbin Zhuo Nengduo Aviation Equipment Co ltd
Current assignee: Harbin Zhuo Nengduo Aviation Equipment Co ltd
Priority date: 2021-09-28
Filing date: 2021-09-28
Publication date: 2022-04-05
Anticipated expiration: 2031-09-28

Abstract

The utility model discloses a shockproof aircraft landing gear component, which belongs to the technical field of aircraft auxiliary devices and comprises a mounting plate, wherein a fixing frame is welded below the mounting plate, fixing bolts are inserted into two sides of the fixing frame in a penetrating manner, a base is fixedly connected below the fixing frame, a plurality of fixing blocks are fixedly connected below the base, supporting frames are movably connected below the fixing blocks, cross rods are arranged between the supporting frames, a connecting piece is arranged in the middle of each cross rod, and a plurality of damping mechanisms are arranged between each cross rod and the base. When the device is used for installing the aircraft, the effect of quick installation can be achieved, the fixing effect is good, the normal use of the aircraft is facilitated, and when the device is used, the shock absorption effect and the protection effect are good when the device is landed, so that a worker can use the device conveniently.

Description

Shockproof aircraft landing gear component

Technical Field

The utility model relates to the technical field of aircraft auxiliary devices, in particular to a shockproof aircraft landing gear component.

Background

The aircraft is the most applied in the current aerial photography technology, but the aircraft often has certain inertial force when taking off and landing, has caused certain harm to flight, and the undercarriage shock-absorbing capacity of current aircraft is not good enough, and the power compartment sets up the top in the cabin, and the focus of aircraft all is in the upper end of aircraft like this, has a bit heavy and light, though its maneuverability is good, its structure is complicated, has just so improved its technical requirement and the material requirement of making, and the degree of difficulty and the cost of operation and maintenance also greatly increase.

Patent No. CN206187329U discloses an aircraft and a landing gear device thereof, comprising a landing gear and a driving mechanism, wherein the driving mechanism comprises a driving unit and a connecting unit; the driving unit comprises a motor and a connecting rod driven by the motor to rotate; one end of the connecting unit is fixedly connected with the undercarriage, the other end of the connecting unit is connected with the connecting rod, and the undercarriage is driven to rotate by the rotation of the connecting rod. The utility model is not only beneficial to improving the flight performance of the aircraft, but also can improve the shooting performance of the aircraft, and is convenient to carry.

The aircraft and its landing gear device of the above-mentioned technology have the following disadvantages: 1. when the device is used for installing the aircraft, the effect of quick installation cannot be achieved, and the fixing effect is poor, so that the aircraft is inconvenient to use; 2. when the device is used, the damping effect and the protection effect are poor when falling to the ground, so that the worker can use the device inconveniently.

SUMMERY OF THE UTILITY MODEL

The utility model provides a shockproof aircraft landing gear component, which can achieve the effect of quick installation when an aircraft is installed, has a good fixing effect and is convenient for the normal use of the aircraft, and has good shock absorption effect and protection effect when the aircraft is landed when the aircraft is used, so that a worker can use the aircraft conveniently.

The specific technical scheme provided by the utility model is as follows:

the utility model provides a shockproof aircraft landing gear component which comprises a mounting plate and is characterized in that a fixing frame is welded below the mounting plate, fixing bolts are inserted into two sides of the fixing frame in a penetrating mode, a base is fixedly connected below the fixing frame, a plurality of fixing blocks are fixedly connected below the base, supporting frames are movably connected below the fixing blocks, cross rods are installed among the supporting frames, connecting pieces are installed in the middle of the cross rods, and a plurality of damping mechanisms are installed between the cross rods and the base.

Optionally, the mounting plate is internally provided with mounting holes, guide bars are arranged at four corners of each mounting hole, and one end of each guide bar is provided with a positioning hole.

Optionally, the damping mechanism comprises a hydraulic rod and a damping spring surrounding the surface of the hydraulic rod.

Optionally, the fixed block is movably connected with the support frame through a bearing.

Optionally, the cross bar is telescopic inside the connector.

The utility model has the following beneficial effects:

the embodiment of the utility model provides a shockproof aircraft landing gear component which comprises the following components:

1. the fixing frame is arranged above the base, the base can effectively support the whole device, the mounting plate is arranged at the top of the fixing frame, the surface of the mounting plate is provided with a mounting hole which can be directly arranged in the mounting hole by matching with the lower part of the aircraft, the guide strips are arranged at the four corners of the mounting hole, so that the defect that the bottom of the aircraft can be conveniently arranged at one position when the aircraft is mounted can be overcome, and one end of the guide strip is provided with a positioning hole, so that the four corners of the bottom of the aircraft can be quickly positioned, the installation is convenient, and when the guide strip is placed above the installation plate, the fixing bolts are inserted at the two sides of the fixing frame, so that the bottom of the aircraft can be fixed, the aircraft is prevented from loosening and falling off, the device can reach the effect of quick installation when installing the aircraft, and fixed effectual makes things convenient for the normal use of aircraft.

2. When the aircraft lands after taking off, the bottom needs to keep stability, the fixed block is arranged below the base, the support frame is arranged below the fixed block, the support frame is movably connected with the fixed block through the bearing, so that when the aircraft drives the bottom support frame to land, the landing can be more stable through the bearing, and the shock can be generated when the aircraft lands, the shock absorption needs to be eliminated, the aircraft is prevented from being damaged, the transverse rod is arranged between the support frames, the shock absorption mechanism is arranged between the transverse rod and the base, the hydraulic rod and the damping shock absorption spring are arranged in the shock absorption mechanism, the double advantages of low frequency and large damping of the steel spring shock absorber can be achieved, the inherent resonance amplitude phenomenon of the steel spring is eliminated, the shock is eliminated through the matching of the hydraulic rod, the connecting piece is arranged in the middle of the transverse rod, and the transverse rod can stretch out and draw back in the connecting piece, through the cooperation with damper for absorbing effect is better, and the device is when using, and the shock attenuation effect when falling to the ground is good with the protective effect, makes the staff conveniently use.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a schematic diagram of the overall structure of a shock-resistant aircraft landing gear component according to an embodiment of the utility model;

FIG. 2 is a top plan view of a mounting plate for a shock resistant aircraft landing gear component in accordance with an embodiment of the present invention;

FIG. 3 is a schematic diagram of a shock absorbing mechanism for a shock absorbing aircraft landing gear component according to an embodiment of the present invention.

In the figure: 1. mounting a plate; 2. a fixing frame; 3. fixing the bolt; 4. a base; 5. a fixed block; 6. A support frame; 7. a damping mechanism; 8. a cross bar; 9. a connecting member; 10. mounting holes; 11. conducting bars; 12. Positioning holes; 13. a hydraulic lever; 14. damping shock-absorbing spring.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention will be described in further detail with reference to the accompanying drawings, and it is apparent that the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

A shock-resistant aircraft landing gear component according to an embodiment of the utility model will now be described in detail with reference to figures 1 to 3.

Referring to fig. 1 to 3, the shockproof aircraft landing gear component provided by the embodiment of the utility model comprises a mounting plate 1, and is characterized in that a fixing frame 2 is welded below the mounting plate 1, fixing bolts 3 are inserted into two sides of the fixing frame 2, a base 4 is fixedly connected below the fixing frame 2, a plurality of fixing blocks 5 are fixedly connected below the base 4, a support frame 6 is movably connected below the fixing blocks 5, a cross rod 8 is installed between the support frames 6, a connecting piece 9 is installed in the middle of the cross rod 8, a damping mechanism 7 is installed between the cross rod 8 and the base 4, and a plurality of damping mechanisms 7 are installed.

By way of example, by providing the fixed frame 2 above the base 4, the base 4 can provide an effective support for the overall device, by arranging the mounting plate 1 at the top of the fixed frame 2 and when the fixed frame is placed above the mounting plate 1, the fixing bolts 3 are inserted at the two sides of the fixing frame 2, so that the bottom of the aircraft can be fixed, the aircraft is prevented from loosening and falling off, when the aircraft lands after taking off, the bottom of the aircraft needs to keep stability, a fixed block 5 is arranged below a base 4, a support frame 6 is arranged below the fixed block 5, and can generate vibration when falling to the ground, needs to eliminate the vibration reduction and avoids damaging the aircraft, and the cross rods 8 are arranged between the support frames 6, a damping mechanism 7 is arranged between the cross rod 8 and the base 4, and a connecting piece 9 is arranged in the middle of the cross rod 8.

Referring to fig. 2, a mounting hole 10 is formed in the mounting plate 1, guide bars 11 are arranged at four corners of the mounting hole 10, and a positioning hole 12 is formed in one end of each guide bar 11.

The example, has seted up mounting hole 10 on the surface of mounting panel 1, and cooperation aircraft below can directly be placed inside mounting hole 10, all is equipped with conducting bar 11 through the four corners at mounting hole 10, can make things convenient for the aircraft when installing, and the bottom can carry out the shortcoming of a position, and has seted up locating hole 12 in the one end of conducting bar 11, can carry out quick location, conveniently installs to the four corners of aircraft bottom.

Referring to fig. 3, the shock-absorbing mechanism 7 includes a hydraulic rod 13 and a damping shock-absorbing spring 14, and the damping shock-absorbing spring 14 surrounds the surface of the hydraulic rod 13.

Illustratively, the hydraulic rod 13 and the damping spring 14 are arranged inside, so that the double advantages of low frequency and large damping of the steel spring shock absorber can be achieved, the inherent resonance amplitude phenomenon of the steel spring is eliminated, and the shock is eliminated through the cooperation of the hydraulic rod 13.

Referring to fig. 1, the fixing block 5 is movably connected with the support frame 6 through a bearing.

The support frame 6 and the fixed block 5 are movably connected through a bearing, so that the aircraft can fall to the ground more stably through the bearing when the aircraft drives the bottom support frame 6 to fall.

Referring to fig. 1, the cross bar 8 is telescopic inside the connecting member 9.

Illustratively, the cross rod 8 can be extended and contracted in the connecting piece 9, and the damping effect is better through the cooperation with the damping mechanism 7.

When in use, the fixing frame 2 is arranged above the base 4, the base 4 can effectively support the whole device, the mounting plate 1 is arranged at the top of the fixing frame 2, the surface of the mounting plate 1 is provided with the mounting hole 10, the lower part of the aircraft can be directly placed in the mounting hole 10 in a matching way, the guide strips 11 are arranged at the four corners of the mounting hole 10, the bottom of the aircraft can be conveniently positioned when the aircraft is mounted, one end of each guide strip 11 is provided with the positioning hole 12, the four corners of the bottom of the aircraft can be quickly positioned, the aircraft can be conveniently mounted, and when the aircraft is placed above the mounting plate 1, the bottom of the aircraft can be fixed by inserting the fixing bolts 3 at the two sides of the fixing frame 2, the aircraft can be prevented from loosening and falling off, and when the aircraft takes off and lands, the bottom needs to keep stability, a fixed block 5 is arranged below a base 4, a support frame 6 is arranged below the fixed block 5, the support frame 6 is movably connected with the fixed block 5 through a bearing, when an aircraft drives the bottom support frame 6 to land, the landing can be more stable through the bearing, and the aircraft can vibrate when landing, the shock absorption needs to be eliminated, so that the aircraft is prevented from being damaged, a cross rod 8 is arranged between the support frames 6, a shock absorption mechanism 7 is arranged between the cross rod 8 and the base 4, a hydraulic rod 13 and a damping shock absorption spring 14 are arranged inside, so that the double advantages of low frequency and large damping of a steel spring shock absorber are achieved, the inherent resonance amplitude phenomenon of the steel spring is eliminated, the shock is eliminated through the matching of the hydraulic rod 13, a connecting piece 9 is arranged in the middle of the cross rod 8, and the cross rod 8 can stretch out and draw back in the connecting piece 9, through the cooperation with damper 7 for the effect of shock attenuation is better.

The utility model relates to a shockproof aircraft landing gear component, which comprises a mounting plate and a bearing, wherein the mounting plate is provided with a mounting hole; 2. a fixing frame; 3. fixing the bolt; 4. a base; 5. a fixed block; 6. a support frame; 7. a damping mechanism; 8. a cross bar; 9. a connecting member; 10. mounting holes; 11. conducting bars; 12. positioning holes; 13. A hydraulic lever; 14. the damping spring is HV, and the specific model of the damping spring is general standard component or the component known by the technical personnel in the field, and the structure and the principle of the damping spring can be known by the technical manual or the conventional experimental method.

It will be apparent to those skilled in the art that various modifications and variations can be made in the embodiments of the present invention without departing from the spirit or scope of the embodiments of the utility model. Thus, if such modifications and variations of the embodiments of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to encompass such modifications and variations.

Claims

1. The utility model provides a type aircraft undercarriage part takes precautions against earthquakes, includes mounting panel (1), its characterized in that, the welding of mounting panel (1) below has fixed frame (2), fixed frame (2) both sides alternate has fixing bolt (3), fixed frame (2) below fixedly connected with base (4), base (4) below fixedly connected with fixed block (5), and fixed block (5) are a plurality of, fixed block (5) below swing joint has support frame (6), install horizontal pole (8) between support frame (6), establish connecting piece (9) in the middle of horizontal pole (8), establish between horizontal pole (8) and base (4) and be equipped with damper (7), and damper (7) are a plurality ofly.

2. The shock-proof aircraft landing gear component according to claim 1, wherein a mounting hole (10) is formed in the mounting plate (1), guide bars (11) are arranged at four corners of the mounting hole (10), and a positioning hole (12) is formed in one end of each guide bar (11).

3. Shock-resistant aircraft landing gear component according to claim 1, wherein said shock-absorbing mechanism (7) comprises a hydraulic rod (13) and a damping shock spring (14), said damping shock spring (14) surrounding the surface of the hydraulic rod (13).

4. Shock-resistant aircraft landing gear component according to claim 1, wherein the fixed block (5) is movably connected to the support frame (6) by means of bearings.

5. Shock-resistant aircraft landing gear component according to claim 1, wherein the cross bar (8) is telescopic inside the connecting piece (9).