A double-supported aircraft cushion landing gear

Abstract

The utility model provides a double-support aircraft cushion landing gear, comprising a fixed platform, a retractable leg, the retractable leg is hinged on the fixed platform: wheels mounted on the front and rear sides of the bottom end of the retractable leg; a cushion top cylinder, the number of the cushion top cylinders is two and they are respectively arranged above the first wheel body and the second wheel body, the fixed end of each cushion top cylinder is hinged on the retractable leg, and the movable ends of each cushion top cylinder are hinged to the first wheel body and the second wheel body in a one-to-one correspondence; a side support hinge rod, the two ends of the side support hinge rod are respectively hinged on the fixed platform and the retractable leg, and the middle part of the side support hinge rod is a hinge; a retractable cylinder, the fixed end of the retractable cylinder is hinged to the fixed platform, the free end of the retractable cylinder is hinged to the hinge position of the side support hinge rod, and the hinge position of the retractable cylinder and the fixed platform is higher than the hinge position of the retractable leg and the fixed platform; the structural design of the mechanism is exquisite, breaking through the constraints of the existing design.

Description

Technical Field

[0001] The utility model relates to the aircraft support mechanism industry, and therefore provides a double-support aircraft buffer landing gear. Background Art

[0002] During the landing process, the aircraft needs to use the landing gear for landing cushioning. The aircraft landing gear generally adopts the main support legs, struts, and retracting and extending power devices. The main support legs are linked with the retracting and extending power devices to achieve retraction and extension. Before landing, the landing gear is lowered in advance to wait for the wheels to contact the ground. The existing retracting and extending mechanism has several problems, such as

[0003] ① In the prior art, the retraction and extension direction of the support legs is consistent with the sliding buffer direction of the aircraft. This will cause the retractable power device to serve as one of the main force-bearing components during use, and generally requires an additional locking mechanism, wherein the locking mechanism also needs to be matched with an automated mechanism to achieve locking. This results in a very redundant structure and a heavy weight, which increases the energy consumption of the aircraft and also increases the workload during the maintenance process.

[0004] ② During the landing process, it is necessary to ensure that the aircraft attitude floats within a safe range. Generally, hard objects such as gravel or debris are not allowed to appear on airport runways. This situation is generally not considered in the existing technology. Generally, a double-wheel linkage design is adopted, and the front and rear wheels are rigidly connected by a rocker arm. However, in the design principles, when hard objects inevitably appear, the front and rear wheels of the existing technology will be affected. In order to ensure the reliability of the equipment structure, there should be a design record that can handle the above-mentioned emergency situations. The structure of the existing technology lacks consideration for the above defects. Utility Model Content

[0005] The utility model aims to at least solve the problem in the prior art that the retracting and extending unit of the existing landing gear structure is easily susceptible to impact. The utility model provides a double-support aircraft cushioning landing gear, which realizes that the contraction of the retracting cylinder is different from the force direction of the aircraft landing gear, and the two-level support structure of the side support and the main support realizes side-type retracting and the wheel part structure is improved.

[0006] The technical solutions provided are:

[0007] Provided is a double-supported aircraft cushion landing gear, comprising a fixed platform, a retractable leg, the retractable leg being hinged on the fixed platform, and further comprising:

[0008] A first wheel body and a second wheel body mounted on the bottom of the retractable leg, the first wheel body and the second wheel body are respectively located at the front and rear sides of the bottom end of the retractable leg;

[0009] Buffering top cylinders, the number of which is two and which are respectively arranged above the first wheel body and the second wheel body, the fixed end of each buffering top cylinder is hinged on the retractable leg, and the movable ends of each buffering top cylinder are hinged to the first wheel body and the second wheel body in a one-to-one correspondence;

[0010] A side support hinge rod, both ends of which are hinged to the fixed platform and the retractable legs respectively, and the middle part of the side support hinge rod is a hinge;

[0011] A retractable cylinder, the fixed end of which is hinged to the fixed platform, the free end of which is hinged to the hinge position of the side support hinge rod, and the hinge position of the retractable cylinder and the fixed platform is higher than the hinge position of the retractable leg and the fixed platform;

[0012] The retractable and extendable swinging direction allowed by the hinge between the retractable leg and the fixed platform is perpendicular to the allowed moving direction of the first wheel body and the second wheel body, and the side support hinge rod, the fixed platform and the retractable and extendable leg form a triangular support structure.

[0013] Furthermore, the first wheel body and the second wheel body both include a pull rod, the pull rod of the first wheel body and the pull rod of the second wheel body are respectively located at the front and rear sides of the retractable legs, and the pull rod of the first wheel body and the pull rod of the second wheel body are hinged to the bottom end;

[0014] Furthermore, there are multiple wheels, and the multiple wheels are respectively and correspondingly pivotally connected to both sides of the pull rod of the first wheel body and the pull rod of the second wheel body.

[0015] Furthermore, the movable ends of the buffer top cylinders are hinged to the pull rods of the first wheel body and the pull rods of the second wheel body in a one-to-one correspondence.

[0016] Furthermore, a first hinge seat is provided on the fixed platform, an upper torsion block allowing free torsion is pivotally connected to the first hinge seat, the top end of the side support hinge rod is hinged to the torsion block, a second hinge seat is provided at the lower part of the retractable leg, a lower torsion block allowing free torsion is pivotally connected to the second hinge seat, and the bottom end of the side support hinge rod is hinged to the lower torsion block.

[0017] The beneficial effects compared with the prior art are:

[0018] 1. By adopting the side-type structural design, the retracting cylinder does not participate in the force during the landing impact process. Through the design of the side support hinge rod and the retracting leg bipolar support structure, a triangular support mechanism is formed in space. This structure has a strong impact resistance, and both the equipment reliability and the structural support performance are far superior to the existing technology.

[0019] 2. The double-hinged wheel design at the bottom has a certain buffering effect. When the front and rear wheels encounter a rigid impact, they will not be linked to each other and will work independently. Even if one set of wheels fails, the other set of wheels can still work normally. It has high reliability and a more scientific structure.

[0020] 3. The double-hinged structural design of the bottom gear train has a certain degree of shrinkage when encountering hard objects during use, which helps the aircraft absorb bumps and filter disturbances.

[0021] 4. The constructed torsion retraction lateral swing structure concentrates all the main force points at the hinge between the main support point and the fixed platform, where the hinge is structurally strengthened and a double hinge design is adopted. The two hinges can disperse the structural deformation caused by the impact force, making the overall structure more scientific and the structural design exquisite, breaking through the constraints of the existing design. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a double-supported cylinder-buffered landing gear retractable legs and a wheel body structure.

[0023] Figure 2 The utility model is a structure composed of a double-supported cylinder-buffered landing gear retracting and extending leg, a side support hinge rod and a retracting and extending cylinder.

[0024] Figure 3 It is a double-supported cylinder-buffered landing gear with two wheel body parts at the bottom.

[0025] Figure 4 The invention relates to the position distribution and connection mode of the two wheel body parts at the bottom of the double-support cylinder buffer landing gear, the fixed platform and the main supporting legs and the retracting and extending cylinder.

[0026] Figure 5 It is composed of the connecting part of the side support hinge rod and the upper torsion block.

[0027] Figure 6 It is composed of the connecting part of the side support hinge rod and the lower torsion block. DETAILED DESCRIPTION

[0028] In the following description, specific details such as specific system structures, technologies, etc. are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from obstructing the description of the present application.

[0029] The following is based on the attached Figure 1-6 The utility model is further described as follows:

[0030] like Figure 1 As shown, a double-supported aircraft cushion landing gear is provided, including a fixed platform 12, which is a fixed part at the bottom of the aircraft and is L-shaped, and also includes a retractable leg 1, which is hinged on the fixed platform 12, as shown in FIG. Figure 1 As shown, the top of the retractable leg 1 is a triangular configuration, which has two hinge points, such as Figure 1 The hinge point a shown in the figure, both hinge points are hinged on the fixed platform 12, and there is a hinge optical axis 6 located above the hinge point of the retractable leg 1. The hinge optical axis 6 is staggered from the central axis direction of the hinge point of the retractable leg 1 and the fixed platform 12. The hinge optical axis 6 extends obliquely, and it is best to be orthogonal to the side support hinge rod 8 in space.

[0031] It also includes a first wheel body 3 and a second wheel body 4 mounted on the bottom of the retractable leg 1, wherein the first wheel body 3 and the second wheel body 4 are respectively located at the front and rear sides of the bottom end of the retractable leg 1;

[0032] The first wheel body 3 and the second wheel body 4 are as follows Figure 4 As shown, the first wheel body 3 and the second wheel body 4 both include a pull rod, and the pull rod of the first wheel body 3 and the pull rod of the second wheel body 4 are respectively arranged in a straight line opposite to the front and rear sides of the retractable leg 1, and the pull rod of the first wheel body 3 and the pull rod of the second wheel body 4 are hinged to the bottom end, and the first wheel body 3 and the second wheel body 4 can both swing within an allowable range with the bottom end of the pull rod as the center.

[0033] A buffer top cylinder 5 is also provided. There are two buffer top cylinders 5, which are respectively provided above the first wheel body 3 and the second wheel body 4. The fixed end of each buffer top cylinder 5 is hinged on the retractable leg 1, and the movable ends of each buffer top cylinder 5 are hinged to the first wheel body 3 and the second wheel body 4 one by one. The buffer top cylinder 5 adopts a pressure spring oil cylinder, and the allowable retraction of the design index value is small, and the impact resistance is extremely strong.

[0034] The structure of the swing part is as follows: Figure 2 , Figure 5 and Figure 6As shown, it has a side support hinge 8, the two ends of the side support hinge 8 are respectively hinged on the fixed platform 12 and the retractable leg 1, and the middle part of the side support hinge 8 is a hinge; and a retractable cylinder 9, the fixed end of the retractable cylinder 9 is hinged to the hinge optical axis 6 of the fixed platform 12, the retractable cylinder 9 is perpendicular to the side support hinge 8, the position of the hinge optical axis 6 is located above the hinge point of the retractable leg 1 and the fixed platform 12, and the free end of the retractable cylinder 9 is hinged to the hinge position in the middle of the side support hinge 8. Because the side support hinge 8 is composed of hinges at both ends, a seat body can be set near the hinge position on any hinge for hinge connection with the free end of the retractable cylinder 9, or an additional connecting member can be directly mounted on the hinge axis at this position for hinge connection with the free end of the retractable cylinder 9.

[0035] The hinge position of the retractable cylinder 9 and the fixed platform 12 is higher than the hinge position of the retractable leg 1 and the fixed platform 12;

[0036] In order to ensure the impact resistance of the whole mechanism and prevent interference with the equipment structure, the hinge between the retractable leg 1 and the fixed platform 12 allows the retractable swing direction to be perpendicular to the allowable movement direction of the first wheel body 3 and the second wheel body 4. The side support hinge rod 8, the fixed platform 12 and the retractable leg 1 form a triangular support structure in space. The side support hinge rod 8 extends obliquely, such as Figure 5 and Figure 6 As shown, in order to prevent the equipment structure from self-interference and complete the retraction and extension action, a first hinge seat is arranged on the fixed platform 12, and an upper torsion block 10 that allows free twisting is centrally connected to the first hinge seat, and the top end of the side support hinge rod 8 is hinged to the upper torsion block 10, and a second hinge seat is arranged at the lower part of the retractable leg 1, and a lower torsion block 11 that allows free twisting is centrally connected to the second hinge seat, and the bottom end of the side support hinge rod 8 is hinged to the lower torsion block 11.

[0037] To ensure the stability of the mechanism, the number of the wheels is preferably 4, in pairs of two, and the four wheels are respectively pivotally connected to the two sides of the pull rod of the first wheel body 3 and the pull rod of the second wheel body 4. The number of the buffer top cylinders 5 is two, and the movable ends of the two buffer top cylinders 5 are hinged to the pull rod of the first wheel body 3 and the pull rod of the second wheel body 4 one by one.

[0038] The retractable cylinder 9 can also be directly connected to the omnidirectional ball joint seat, which is then hinged to the hinged optical axis 6. The omnidirectional ball joint seat includes a ball joint joint, which can move in all directions. When matched with the omnidirectional ball joint seat, during the folding process of the side support hinge rod 8, the retractable cylinder 9 will tilt with the twisting amount of the folding point, and the movement amount is provided by the omnidirectional ball joint seat.

[0039] During use, the retracting cylinder 9 moves. For example, when the retracting cylinder 9 retracts, the middle part of the extended side support hinge rod 8 will be pulled. Since the side support hinge rod 8 is inclined and extended, there will be some very small rotation in the process of the side support hinge rod 8 being pulled. The rotation is ensured by the upper torsion block 10 and the lower torsion block 11. At this time, the side support hinge rod 8 will tend to fold. Since the retracting cylinder 9 is also hinged, the retracting cylinder 9 will swing upward under the structural restriction, and the side support hinge rod 8 will also gradually fold. Figure 2 It can be seen that the free end of the retracting cylinder 9 is hinged to the seat body provided with the hinged part in the middle of the side support hinge rod 8. Therefore, when the retracting cylinder 9 is fully retracted to the limit, the hinge point between the retracting cylinder 9 and the side support hinge rod 8 will be located above the folded side support hinge rod 8. At this time, the main support leg will also be driven to retract to the predetermined position along the lateral swing. During the whole process, the force direction of the main support leg is staggered with the swing direction of the retracting cylinder 9.

[0040] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some of the technical features therein by equivalents. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be included in the protection scope of the present application.

Claims

1. A double-supported aircraft cushion landing gear, comprising a fixed platform and a retractable leg, wherein the retractable leg is hinged to the fixed platform. Features: Also includes, A first wheel body and a second wheel body mounted on the bottom of the retractable leg, the first wheel body and the second wheel body are respectively located at the front and rear sides of the bottom end of the retractable leg; Buffering top cylinders, the number of which is two and which are respectively arranged above the first wheel body and the second wheel body, the fixed end of each buffering top cylinder is hinged on the retractable leg, and the movable ends of each buffering top cylinder are hinged to the first wheel body and the second wheel body in a one-to-one correspondence; A side support hinge rod, both ends of which are hinged to the fixed platform and the retractable legs respectively, and the middle part of the side support hinge rod is a hinge; A retractable cylinder, the fixed end of which is hinged to the fixed platform, the free end of which is hinged to the hinge position of the side support hinge rod, and the hinge position of the retractable cylinder and the fixed platform is higher than the hinge position of the retractable leg and the fixed platform; The retractable and extendable swinging direction allowed by the hinge between the retractable leg and the fixed platform is perpendicular to the allowed moving direction of the first wheel body and the second wheel body, and the side support hinge rod, the fixed platform and the retractable and extendable leg form a triangular support structure.

2. A double-supported aircraft cushion landing gear according to claim 1, characterized in that: The first wheel body and the second wheel body both include pull rods, which are respectively located at the front and rear sides of the retractable legs and are hinged to the bottom ends.

3. A double-supported aircraft cushion landing gear according to claim 1, characterized in that: There are multiple wheels, and the multiple wheels are respectively and correspondingly pivoted to both sides of the pull rod of the first wheel body and the pull rod of the second wheel body.

4. A double-support aircraft cushion landing gear according to claim 2, characterized in that: The movable ends of the buffer top cylinders are hinged to the pull rods of the first wheel body and the second wheel body in a one-to-one correspondence.

5. The double-support aircraft cushion landing gear according to claim 1, characterized in that: A first hinge seat is provided on the fixed platform, an upper torsion block that allows free torsion is centrally connected to the first hinge seat, the top end of the side support hinge rod is hinged to the upper torsion block, a second hinge seat is provided at the lower part of the retractable leg, a lower torsion block that allows free torsion is centrally connected to the second hinge seat, and the bottom end of the side support hinge rod is hinged to the lower torsion block.

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