CN210761289U - Aircraft shock attenuation undercarriage - Google Patents

Abstract

The utility model discloses an aircraft shock attenuation undercarriage, including bottom plate and fixed plate, the up end both sides of bottom plate all are fixed with the fixture block, the equal screw thread in fixture block outside both ends is installed first screw, the both ends in terminal surface both sides all are fixed with the fixed block under the bottom plate, and rotate through the pivot between the homonymy fixed block and install the arc, and two arcs are connected through the cowhide muscle, the lower extreme of arc is fixed with the rubber strip, the fixed plate is equipped with two altogether, and two fixed plates fix respectively in the lower terminal surface both sides of bottom plate, the lower terminal surface both ends of fixed plate all are fixed with branch, and the lower extreme of branch is fixed on the foot rest, logical groove has been seted up to the centre department of foot rest, and the cowhide muscle passes logical groove, the arc is equipped with two altogether, and two arcs are outer eight characters design. The utility model discloses possess dual shock attenuation, improve barrier propterty and improve balance performance, can carry out the advantage of parking on outdoor unevenness ground.

Description

Aircraft shock attenuation undercarriage

Technical Field

The utility model relates to an aircraft technical field specifically is an aircraft shock attenuation undercarriage.

Background

The four-axis aircraft is one of miniature aircraft, also is an intelligent robot. Originally made by the aviation model enthusiast, many automated manufacturers later found it to be useful for a variety of purposes and actively worked on. The unmanned aerial vehicle has the advantages that four rotors are used as flight engines to carry out aerial flight, the unmanned aerial vehicle is small in size and light in weight, can carry certain task load like an unmanned aerial vehicle suitable for carrying and using, and has autonomous navigation flight capability.

Four shaft air vehicle need carry out the buffering of descending through the undercarriage when the flight is descended, avoids causing the damage of machine because of the impact force is too big. In patent application No. CN201520311395.7, a simple shock absorbing landing gear is described, which provides a cushioning effect by the simple rubber ring shock absorption principle.

The existing aircraft landing gear has the disadvantages of too simple structure, poor damping performance, unobvious damping effect of a single structure, incapability of improving the damping performance and unsatisfactory protection effect; the existing undercarriage can only be matched with a smooth ground, the balance of the aircraft after landing can not be ensured in the outdoor environment with uneven ground, and the use is inconvenient.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aircraft shock attenuation undercarriage possesses dual shock attenuation, improves barrier propterty and improves balance performance, can carry out the advantage of parking on outdoor unevenness ground, solves the poor problem of poor and the equilibrium of existing equipment damping performance.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an aircraft shock attenuation undercarriage, includes bottom plate and fixed plate, the up end both sides of bottom plate all are fixed with the fixture block, first screw is installed to the equal screw thread in fixture block outside both ends, the both ends in terminal surface both sides all are fixed with the fixed block under the bottom plate, and rotate through the pivot between the homonymy fixed block and install the arc, and two arcs are connected through the cowhide muscle, the lower extreme of arc is fixed with the rubber strip, the fixed plate is equipped with two altogether, and two fixed plates fix respectively in the lower terminal surface both sides of bottom plate, the lower terminal surface both ends of fixed plate all are fixed with branch, and the lower extreme of branch fixes on the foot rest, logical groove has been seted up to the centre department of foot rest, and the cowhide muscle passes.

Preferably, the number of the arc-shaped plates is two, and the two arc-shaped plates are in a splayed design.

Preferably, the length of the supporting rod is smaller than the height of the arc-shaped plate, and the through groove is matched with the cowhide rubber band.

Preferably, both ends of the inner side of the arc-shaped plate are fixed with limiting blocks, and the limiting blocks are in contact with the lower end face of the bottom plate.

Preferably, the second screws are installed at two ends of the lower end face of the fixing plate in a threaded mode, and the second screws are connected with the inside of the bottom plate.

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

1. the utility model discloses a set up rubber strip and cowhide muscle, place the aircraft in the fixture block inboard of bottom plate, make the bottom of aircraft be connected with this device through first screw, when the aircraft descends, the rubber strip contacts ground earlier, carry out preliminary buffering through the elasticity of rubber strip material itself, the whereabouts inertia and the gravity of aircraft produce the power of pushing down, make the arc of bottom plate lower extreme both sides rotate to both sides, the arc displacement makes the cowhide muscle to the synchronous pulling-up in both ends, offset the power of pushing down through the pulling-up power of cowhide muscle, improve damping performance, when descending on uneven ground, the arc of one side contacts ground earlier, produce the skew earlier, both sides skew angle is different, the damping principle is the same, maintain overall balance through aircraft gravity itself, when the cowhide muscle uses for a long time and takes place to damage the fracture, the foot rest through the branch lower extreme carries out urgent support, avoid the aircraft to damage, this device simple structure, it is with low costs and damping performance good, possess safeguard procedures and avoid the special case to produce, and the overall balance is superior, and the practicality is higher.

Drawings

Fig. 1 is a schematic view of the structure of the present invention;

FIG. 2 is a schematic side view of the present invention;

fig. 3 is a schematic side view of the foot stool of the present invention.

In the figure: 1. a first screw; 2. a base plate; 3. a fixed block; 4. an arc-shaped plate; 5. a rubber strip; 6. cowhide tendons; 7. a strut; 8. a foot rest; 9. a limiting block; 10. a fixing plate; 11. a clamping block; 12. a through groove; 13. a second screw.

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.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Referring to fig. 1 to fig. 3, the present invention provides an embodiment: the utility model provides an aircraft shock attenuation undercarriage, including bottom plate 2 and fixed plate 10, the up end both sides of bottom plate 2 all are fixed with fixture block 11, first screw 1 is installed to the equal screw thread in fixture block 11 outside both ends, the both ends of terminal surface both sides all are fixed with fixed block 3 under 2 bottom plates, and rotate through the pivot between the homonymy fixed block 3 and install arc 4, and two arcs 4 are connected through ox rubber band 6, the lower extreme of arc 4 is fixed with rubber strip 5, arc 4 is equipped with two altogether, and two arcs 4 are outer eight characters design, the inboard both ends of arc 4 all are fixed with stopper 9, and stopper 9 contacts with the lower terminal surface of bottom plate 2.

The two fixing plates 10 are arranged, the two fixing plates 10 are respectively fixed on two sides of the lower end face of the bottom plate 2, second screws 13 are arranged at two ends of the lower end face of each fixing plate 10 in a threaded mode, the second screws 13 are connected with the inside of the bottom plate 2, supporting rods 7 are fixed at two ends of the lower end face of each fixing plate 10, the lower ends of the supporting rods 7 are fixed on foot rests 8, through grooves 12 are formed in the middle of the foot rests 8, the cowhide tendons 6 penetrate through the through grooves 12, the length of each supporting rod 7 is smaller than the height of the corresponding arc-shaped plate 4, the corresponding through grooves 12 are matched with the cowhide tendons 6, the aircraft is placed on the inner sides of clamping blocks 11 of the bottom plate 2, the bottom of the aircraft is connected with the device through first screws 1, when the aircraft descends, the rubber strips 5 firstly contact the ground, preliminary buffering is carried out through elasticity of the materials of the rubber strips 5, downward-pressing force is generated, 4 displacements of arc make the sticky note 6 to the synchronous pulling-up in both ends, the power of pushing down is offset to the power of pulling-up through sticky note 6, improve damping performance, when descending on unevenness ground, the arc 4 of one side contacts ground earlier, produce the skew earlier, both sides skew angle is different, the shock attenuation principle is the same, maintain global balance through aircraft gravity itself, when sticky note 6 uses the emergence to damage when splitting for a long time, promptly support through foot rest 8 of branch 7 lower extreme, avoid the aircraft to damage, this device simple structure, with low costs and damping performance is good, it avoids the special case to produce to possess safeguard measure, and global balance is superior, and the practicality is higher.

The working principle is as follows: the utility model discloses in operation, place the aircraft in 11 inboards of fixture block of bottom plate 2, bottom and this device through 1 messenger's aircraft of first screw are connected, when the aircraft descends, rubber strip 5 contacts ground earlier, elasticity through rubber strip 5 material itself carries out preliminary buffering, the whereabouts inertia and the gravity of aircraft produce the power of pushing down, arc 4 to both sides rotation of 2 lower extreme both sides of messenger's bottom plate, 4 displacements of arc make the cowhide muscle 6 pull up to both ends are synchronous, the power of pushing down is offset to the power of pulling up through cowhide muscle 6, when descending on unevenness ground, arc 4 of one side contacts ground earlier, produce the skew earlier, both sides skew angle is different, the shock attenuation principle is the same, maintain overall balance through aircraft gravity itself, when the cowhide muscle 6 uses for a long time and takes place to damage the fracture, the foot rest 8 through branch 7 lower extreme carries out urgent support. The working principle of the present invention is the above.

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 (5)

1. An aircraft shock absorbing landing gear comprising a base plate (2) and a fixed plate (10), characterized in that: clamping blocks (11) are fixed on two sides of the upper end surface of the bottom plate (2), first screws (1) are installed at two ends of the outer side of each clamping block (11) in a threaded mode, the two ends of the two sides of the lower end surface of the bottom plate (2) are fixed with fixed blocks (3), an arc-shaped plate (4) is rotatably arranged between the fixing blocks (3) on the same side through a rotating shaft, the two arc plates (4) are connected through a rubber band (6), the lower ends of the arc plates (4) are fixed with rubber strips (5), the number of the fixed plates (10) is two, and the two fixing plates (10) are respectively fixed on the two sides of the lower end surface of the bottom plate (2), both ends of the lower end surface of the fixed plate (10) are fixed with supporting rods (7), and the lower end of the supporting rod (7) is fixed on the foot rest (8), a through groove (12) is formed in the middle of the foot rest (8), and the cowhide tendon (6) penetrates through the through groove (12).

2. An aircraft shock absorbing landing gear according to claim 1, wherein: the two arc-shaped plates (4) are arranged, and the two arc-shaped plates (4) are in a splayed design.

3. An aircraft shock absorbing landing gear according to claim 1, wherein: the length of branch (7) is less than the height of arc (4), lead to groove (12) and cowhide muscle (6) looks adaptation.

4. An aircraft shock absorbing landing gear according to claim 1, wherein: both ends of the inner side of the arc-shaped plate (4) are respectively fixed with a limiting block (9), and the limiting blocks (9) are contacted with the lower end face of the bottom plate (2).

5. An aircraft shock absorbing landing gear according to claim 1, wherein: and second screws (13) are installed at two ends of the lower end face of the fixing plate (10) in a threaded mode, and the second screws (13) are connected with the inside of the bottom plate (2).

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