Single-action folding type multifunctional combined mechanism and application

Abstract

The invention belongs to the technical field of aviation structure design, and particularly relates to a single-actuation folding type multifunctional combined mechanism and application thereof. The single-actuation folding type multifunctional combined mechanism is composed of a supporting column, a cabin door, a buffer, an actuator cylinder outer cylinder, an actuator cylinder piston rod, a connecting rod, a connecting rod, a connecting rod and a connecting rod; the first connecting rod, the supporting column and the buffer form a supporting column four-connecting-rod mechanism, and the third connecting rod, the cabin door, the fifth connecting rod and the supporting column form a cabin door four-connecting-rod mechanism. According to the single-actuation folding type multifunctional combined mechanism designed by the invention, only one actuation cylinder is used in practical application, and folding, releasing and locking of an undercarriage (or an air oil receiving pipe) and a cabin door are realized in a folding manner.

Description

Technical Field

[0001] This invention belongs to the field of aerospace structural design technology, specifically relating to a single-actuation folding multi-functional combined mechanism and its application. Background Technology

[0002] Conventional landing gear mainly consists of landing gear struts, landing gear doors, strut retraction and extension mechanisms and actuators, and door retraction and extension mechanisms and actuators. In some special cases, such as the blunt-rounded nose of the space shuttle, the thick thermal insulation tiles result in a very large nose landing gear door hinge, occupying a large amount of space in the nose landing gear bay, causing severe structural damage to the fuselage, and making it difficult to arrange the landing gear retraction and extension mechanism. The aircraft's in-flight refueling system generally consists of a refueling probe (equivalent to a landing gear strut), a refueling probe retraction and extension device, and a refueling probe door and its retraction and extension device. Similar to the landing gear structure, traditional designs extend and retract the refueling probe through the retraction and extension device, requiring an additional door and its retraction and extension mechanism. The overall system is heavy, space-consuming, and costly. Summary of the Invention

[0003] The purpose of this invention is to address the problems of complex system structure, heavy weight, high cost, and large space occupation caused by the coexistence of two auxiliary mechanisms: landing gear and oil receiving device. This invention proposes a single-actuator folding multi-functional combined mechanism that can be used for the control of landing gear and oil receiving device. The technical solution of the present invention: In order to achieve the above-mentioned objective, the present invention proposes a single-acting folding multi-functional combined mechanism, which is composed of a support column, a hatch, a buffer, an actuator, an actuator piston rod, a connecting rod, a connecting rod, a connecting rod, a connecting rod, a connecting rod, a connecting rod, a connecting rod; One end of the first link is hinged to the fuselage, and the other end is hinged to the first end of the strut. The fixed end of the actuator cylinder is hinged to the fuselage, and the piston rod end of the actuator cylinder is hinged to the middle section of the first link. One end of the buffer is hinged to the fuselage, and the other end is hinged to the middle section of the strut. One end of the second link is hinged to the middle section of the first link, and the other end is hinged to the middle section of the strut. One end of the fourth link is hinged to the middle section of the third link, and the other end is hinged to the middle section of the strut. The connection point of the second and fourth links on the strut is coaxial, and this connection point can adaptively slide along the axial direction of the strut. One end of the third link is hinged to the hatch, and the other end is hinged to the first end of the strut. The connection point of the first and third links on the first end of the strut is coaxial. One end of the fifth link is hinged to the middle section of the strut, and the other end is hinged to the hatch. The second end of the strut is a free end.

[0004] Furthermore, the second and fourth links are provided with sleeves at their connection points on the support column, and the sleeves can slide along the axis of the support column.

[0005] Furthermore, the second and fourth links are provided with sliders at the connection points on the support column, and corresponding grooves are provided on the support column. The sliders slide along the axis of the support column within the grooves.

[0006] Furthermore, the buffer is a conventional compressible buffer.

[0007] Furthermore, the fixed end of the actuator cylinder has an elongated inner cylinder, and an outer cylinder is provided outside the inner cylinder. A piston rod, forming the cylinder structure, is located between the inner and outer cylinders and extends from the end of the outer cylinder. The space between the outer cylinder and the piston rod is the actuator cylinder contraction chamber, which is connected to an external oil circuit via a contraction chamber nozzle. The cavity formed by the outer cylinder, inner cylinder, and piston end face of the piston rod is the actuator cylinder extension chamber, which is connected to an external oil circuit via an extension chamber nozzle. The inner side of the inner cylinder is connected to the inner side of the piston rod, and the inner side of the inner cylinder is also connected to an external emergency air source through the fixed end of the actuator cylinder. Optionally, the fixed end of the actuator cylinder is equipped with a shuttle valve, which is connected to an emergency air source.

[0008] Furthermore, a vent pipe is also provided in the inner cylinder, which is fixed inside the fixed end of the actuator cylinder. One end of the vent pipe is connected to an emergency air source, and the other end is connected to the interior of the inner cylinder. A gas-liquid isolation piston and a piston retaining ring are provided between the vent pipe and the inner cylinder. The gas-liquid isolation piston can move axially and isolate the chambers at both ends of the gas-liquid isolation piston. The piston retaining ring is located at the front end of the vent pipe to limit the front limit position of the gas-liquid isolation piston. The inner wall of the fixed end of the actuator cylinder limits the rear limit position of the gas-liquid isolation piston. The cavity formed between the front end of the gas-liquid isolation piston, the vent pipe, and the inner cylinder is connected to the interior of the inner cylinder to form a pressure accumulator chamber. The cavity formed between the rear end of the gas-liquid isolation piston, the vent pipe, and the inner cylinder is connected to the accumulator nozzle located on the side of the fixed end of the actuator cylinder and forms part of the accumulator oil chamber.

[0009] The above-designed single-actuation folding multi-functional combined mechanism can be applied to an aircraft landing gear system, wherein the landing gear wheels are mounted on the free end of the strut.

[0010] The above-designed single-actuation folding multi-functional combined mechanism can also be applied to the refueling device of an aircraft, wherein the refueling pipe of the refueling device is installed at the free end of the support.

[0011] Furthermore, an oil pipeline connected to the machine body is arranged on the support column.

[0012] The retraction principle of the single-acting folding multi-functional combination mechanism designed above in this invention is as follows: In the lowered position, the first link rotates around the fuselage hinge. The first link, strut, and buffer form a strut four-bar linkage. The third link, door, fifth link, and strut form a door four-bar linkage. When the landing gear is retracted, the actuator extends, pushing the first link to rotate around the fuselage hinge. The first link drives the fourth link through the second link, which in turn drives the third link. The third link drives the door. The fifth link and the third link together ensure that the door is in the correct position when retracted.

[0013] With the landing gear down, the mechanical lock inside the actuator cylinder locks the cylinder, changing it from a retractable state to a fixed length. The hinge mechanism formed by the actuator cylinder and the first link is also fixed. When the strut is compressed, the strut rotates around the lower hinge of the first link, compressing the buffer and realizing the landing gear's cushioning function.

[0014] The application principle of the single-actuation folding multi-functional combined mechanism in aerial refueling mechanisms is as follows: The refueling probe is equivalent to a wheel on the landing gear strut, and the rest of the linkage is completely similar to the landing gear mechanism. It opens the refueling access door and closes the refueling access door. When the refueling access mechanism is opened, the refueling probe extends and is locked by an actuator.

[0015] The beneficial effects of this invention: The single-acting folding multi-functional combined mechanism proposed in this invention has the following significant advantages compared with traditional landing gear mechanisms or hydraulic control mechanisms: 1. The door and landing gear retraction and buffering are achieved through a single mechanism, reducing the number of actuators and simplifying the landing gear retraction system and corresponding control system. The system is simple and low in cost.

[0016] 2. The hatch and struts are fully linked, with no additional hatch retraction mechanism. The fuselage connection and installation are user-friendly, and there will be no large hooks that could break the main fuselage frame.

[0017] 3. In the entire mechanism, the buffer and actuator have simple structures, while the remaining linkages are purely structural components, resulting in low manufacturing costs. The landing gear strut outer cylinder does not require traditional large-scale forgings, thus shortening the manufacturing cycle.

[0018] 4. This invention is applicable not only to the front starter, but also to the main starter and the oil receiving device. 5. When used for the forward takeoff of the space shuttle, the buffer can be designed with a large stroke to adapt to the forward takeoff of aircraft with large length-to-slender ratio and large descent speed, reduce the forward takeoff landing load, and protect the fuselage structure.

[0019] 6. The actuator of this invention has sufficient free stroke and integrates upper and lower position locks. The entire mechanism realizes the functions of raising, lowering, locking and buffering of the support column and the hatch through a single actuator. Attached Figure Description

[0020] Figure 1 This is the landing gear lowered position for the multi-functional combined mechanism; Figure 2 The landing gear of the multi-functional combination mechanism is in the retracted state. Figure 3 The aerial refueling mechanism of the multi-functional combined unit is in the deployed state; Figure 4 The aerial refueling mechanism of the multi-functional combined unit is in the retracted state; Figure 5 This is a schematic diagram of one type of actuator cylinder structure in a specific implementation of the present invention; The components include: support column 1, hatch 2, buffer 3, wheel 4, actuator cylinder 6, actuator cylinder piston rod 7, first connecting rod 8, second connecting rod 9, third connecting rod 10, fourth connecting rod 11, fifth connecting rod 12, oil receiving pipe 100, oil receiving pipe hatch in extended state 102, oil receiving pipe hatch in closed state 103; accumulator oil chamber 20, outer cylinder 21, piston rod 22, actuator cylinder extension chamber 23, actuator cylinder retraction chamber 24, accumulator air chamber 25, shuttle valve 26, gas-liquid isolation piston 27, vent pipe 28, piston retaining ring 29, accumulator nozzle 30, extension chamber nozzle 31, and retraction chamber nozzle 32. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0022] A single-actuated folding multi-functional combined mechanism consists of a support column 1, a hatch 2, a buffer 3, a wheel 4, an actuator cylinder 6, an actuator cylinder piston rod 7, a first connecting rod 8, a second connecting rod 9, a third connecting rod 10, a fourth connecting rod 11, and a fifth connecting rod 12.

[0023] One end of the first link 8 is hinged to the fuselage, and the other end is hinged to the support column 1. One end of the actuator cylinder 6 is hinged to the fuselage, and the other end is hinged to the first link 8. One end of the buffer 3 is hinged to the fuselage, and the other end is hinged to the support column 1. One end of the second link 9 is hinged to the first link 8, and the other end is hinged to the support column 1. One end of the fourth link 11 is hinged to the third link 10, and the other end is hinged to the support column 1. The connection points of the second link 9 and the fourth link 11 on the support column 1 are coaxial. One end of the third link 10 is hinged to the first link 8, and the other end is hinged to the hatch 2. One end of the fifth link 12 is hinged to the support column 1, and the other end is hinged to the hatch 2. The wheel 4 is hinged to the support column 1.

[0024] The buffer 3 is a conventional compressible buffer.

[0025] The actuator 6 is equipped with an internal lock when the fully extended landing gear is in the lowered state.

[0026] The retraction and extension principle of the single-actuation folding multi-functional combination mechanism is as follows: like Figure 1 As shown. In the lowered state, the first link 8 rotates around the fuselage hinge. The first link 8, strut 1, and buffer 8 form a strut four-bar linkage. The third link 10, door 2, fifth link 12, and strut 1 form a door four-bar linkage. When the landing gear is in operation, the actuator 6 extends, pushing the first link 8 to rotate around the fuselage hinge. The first link 8 drives the fourth link 11 through the second link 9, which in turn drives the third link 10. The third link 10 drives the door 2. The fifth link 12 and the third link 10 together ensure that the door is in the correct position when retracted. In the retracted state, as shown... Figure 2 As shown, The buffering principle of the single-acting folding multi-functional combined mechanism is as follows: like Figure 1 As shown. In the lowered state, the internal mechanical lock of the actuator 6 is locked, so that the actuator 6 changes from a retractable state to a fixed length. The hinge mechanism formed by the actuator 6 and the first link 8 is also fixed. When the support column 1 is compressed, the support column 1 rotates around the lower hinge of the first link 8, and at the same time compresses the buffer 3 to realize the landing gear buffer function.

[0027] The principle of the single-actuation folding multi-functional combined mechanism for controlling the refueling mechanism is as follows: like Figure 3 As shown. The oil receiver 100 is equivalent to... Figure 1 The landing gear strut 1, and the other linkages are completely the same as those in the landing gear strut 1. Figure 1The landing gear mechanism is similar. 102 is the refueling access door in the deployed state, and 103 is the refueling access door in the closed state. When the refueling access is deployed, the refueling pipe 100 extends and is locked by the actuator.

[0028] As one implementable actuator cylinder structure of the present invention, the specific design structure is as follows: Figure 5 As shown, it includes an accumulator oil chamber 20, an outer cylinder 21, a piston rod 22, an actuator extension chamber 23, an actuator contraction chamber 24, an accumulator air chamber 25, a shuttle valve 26, a gas-liquid isolation piston 27, a vent pipe 28, a piston retaining ring 29, an accumulator nozzle 30, an extension chamber nozzle 31, and a contraction chamber nozzle 32. The fixed end of the actuator cylinder 6 has an elongated cylindrical section as an inner cylinder, and an outer cylinder 21 is provided outside the inner cylinder. The piston rod 22, which is a cylindrical structure, is located between the inner cylinder and the outer cylinder 21 and extends from the end of the outer cylinder 21. The space between the outer cylinder 21 and the piston rod 22 is the actuator cylinder contraction chamber 24, which is connected to the external oil circuit through the contraction chamber nozzle 32. The cavity formed by the outer cylinder 21, the inner cylinder, and the piston end face of the piston rod 22 is the actuator cylinder extension chamber 23, which is connected to the external oil circuit through the extension chamber nozzle 31. The inner side of the inner cylinder is connected to the inner side of the piston rod 22, and the inner side of the inner cylinder is also connected to an external emergency air source through the fixed end of the actuator cylinder 6.

[0029] The inner cylinder is also equipped with a vent cylinder, which is fixed inside the fixed end of the actuator cylinder 6. One end of the vent cylinder is connected to an external emergency air source, and the other end is connected to the interior of the inner cylinder. A gas-liquid isolation piston 27 and a piston retaining ring 29 are provided between the vent cylinder and the inner cylinder. The gas-liquid isolation piston 27 can move axially and isolate the chambers at both ends of the gas-liquid isolation piston 27. The piston retaining ring 29 is located at the front end of the vent cylinder to limit the front limit position of the gas-liquid isolation piston 27. The inner wall of the fixed end of the actuator cylinder 6 limits the rear limit position of the gas-liquid isolation piston 27. The cavity formed between the front end of the gas-liquid isolation piston 27, the vent cylinder, and the inner cylinder is connected to the interior of the inner cylinder to form a pressure accumulator chamber 25. The cavity formed between the rear end of the gas-liquid isolation piston 27, the vent cylinder, and the inner cylinder is connected to the accumulator nozzle 30 located on the side of the fixed end of the actuator cylinder 6 to form part of the accumulator oil chamber 20. A shuttle valve 26 is provided at the fixed end of the actuator cylinder 6, and the shuttle valve 26 is connected to an external emergency air source.

[0030] When the actuator cylinder 6 is in the retracted state, the actuator cylinder extension chamber 23 and retraction chamber 24 of the actuator cylinder 6 are connected to the accumulator oil chamber 20 through the hydraulic control valve. At this time, the high pressure of the gas inside the accumulator gas chamber 25 inside the actuator cylinder 6 acts on the gas-liquid isolation piston 27. The gas-liquid isolation piston 27 pushes the accumulator oil chamber 20 to hydraulically enter the actuator cylinder extension chamber 23 and retraction chamber 24 through the hydraulic control isolation valve, thereby driving the actuator cylinder 6 to extend. When the actuator cylinder 6 is in the retracted state, and the high-pressure gas inside the accumulator chamber 25 inside the actuator cylinder 6 leaks and cannot drive the actuator cylinder 6 to extend, the gas generated by connecting an external emergency gas source or pyrotechnic device through the shuttle valve 26 directly enters the accumulator chamber 25 through the vent pipe 28. The accumulator chamber 25 is also the piston rod 22 chamber of the actuator cylinder 6, directly pushing the piston rod to extend.

[0031] This invention integrates a pressurized oil tank into the actuator cylinder by incorporating a high-pressure accumulator inside, reducing the number of structural components and enabling passive automatic lowering. It also automatically creates a secondary redundancy for the actuator cylinder. When both the primary and secondary redundancies fail, the actuator cylinder can be lowered via an external air source or pyrotechnic device. Furthermore, the hydraulic oil inside the actuator cylinder provides damping during fluid movement, mitigating the impact of excessively high pneumatic speeds.

[0032] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A single-actuation folding multi-functional combined mechanism, characterized in that, The combined mechanism consists of a support column (1), a hatch (2), a buffer (3), an actuator (6), an actuator piston rod (7), a first connecting rod (8), a second connecting rod (9), a third connecting rod (10), a fourth connecting rod (11), and a fifth connecting rod (12); One end of the first connecting rod (8) is hinged to the machine body, and the other end is hinged to the first end of the support column (1). The fixed end of the actuator cylinder (6) is hinged to the machine body. The piston rod (7) of the actuator cylinder is hinged to the middle section of the first connecting rod (8). One end of the buffer (3) is hinged to the machine body, and the other end is hinged to the middle section of the support column (1). One end of the second connecting rod (9) is hinged to the middle section of the first connecting rod (8), and the other end is hinged to the middle section of the support column (1). One end of the fourth connecting rod (11) is hinged to the middle section of the third connecting rod (10). The first link (8) and the second link (11) are connected at the same point on the support (1), and the connection point can slide adaptively along the axis of the support (1). The third link (10) is connected at one end on the hatch (2) and at the other end on the first end of the support (1). The first link (8) and the third link (10) are connected at the same point on the first end of the support (1). The fifth link (12) is connected at one end on the middle section of the support (1) and at the other end on the hatch (2). The second end of the support (1) is a free end.

2. The single-acting folding multi-functional combined mechanism as described in claim 1, characterized in that, The second link (9) and the fourth link (11) are provided with sleeves at the connection point on the support (1), and the sleeves can slide along the axis of the support (1).

3. The single-acting folding multi-functional combined mechanism as described in claim 1, characterized in that, The second link (9) and the fourth link (11) are provided with sliders at the connection point on the support (1), and corresponding grooves are provided on the support (1). The sliders slide along the axis of the support (1) in the grooves of the support (1).

4. The single-acting folding multi-functional combined mechanism as described in claim 1, characterized in that, The buffer (3) is a compressible buffer.

5. The single-acting folding multi-functional combined mechanism as described in claim 1, characterized in that, The actuator (6) has an elongated cylinder at its fixed end as an inner cylinder, and an outer cylinder (21) outside the inner cylinder. The piston rod (22), which is a cylinder structure, is located between the inner cylinder and the outer cylinder (21) and extends from the end of the outer cylinder (21). The space between the outer cylinder (21) and the piston rod (22) is the actuator cylinder contraction chamber (24), which is connected to the external oil circuit through the contraction chamber nozzle (32). The cavity formed by the outer cylinder (21), the inner cylinder, and the piston end face of the piston rod (22) is the actuator cylinder extension chamber (23), which is connected to the external oil circuit through the extension chamber nozzle (31). The inner side of the inner cylinder is connected to the inner side of the piston rod (22), and the inner side of the inner cylinder is also connected to the external emergency air source through the fixed end of the actuator (6).

6. The single-acting folding multi-functional combined mechanism as described in claim 5, characterized in that, The inner cylinder is also equipped with a vent pipe, which is fixed inside the fixed end of the actuating cylinder (6). One end of the vent pipe is connected to an external emergency air source, and the other end is connected to the inside of the inner cylinder. A gas-liquid isolation piston (27) and a piston retainer (29) are provided between the vent pipe and the inner cylinder. The gas-liquid isolation piston (27) can move axially and isolate the chambers at both ends of the gas-liquid isolation piston (27). The piston retainer (29) is located at the front end of the vent pipe to limit the front limit of the gas-liquid isolation piston (27). The position is limited, and the inner wall of the fixed end of the actuator (6) limits the rear limit position of the gas-liquid isolation piston (27). The cavity formed between the front end of the gas-liquid isolation piston (27), the vent cylinder and the inner cylinder is connected to the inside of the inner cylinder to form a pressure accumulator cavity (25). The cavity formed between the rear end of the gas-liquid isolation piston (27), the vent cylinder and the inner cylinder is connected to the accumulator nozzle (30) located on the side of the fixed end of the actuator (6) and forms part of the accumulator oil cavity (20).

7. The single-acting folding multi-functional combined mechanism as described in claim 6, characterized in that, The fixed end of the actuator (6) is equipped with a shuttle valve (26), which is connected to an external emergency gas source.

8. The single-actuated folding multi-functional combination mechanism as described in any one of claims 1 to 7, wherein the combination mechanism can be applied to an aircraft landing gear system, and the landing gear wheels are mounted on the free end of the strut (1).

9. The single-acting folding multi-functional combined mechanism as described in any one of claims 1 to 7, wherein the combined mechanism can also be applied to an aircraft refueling device, wherein the refueling pipe of the refueling device is installed at the free end of the support (1).

10. A single-acting folding multi-functional combined mechanism as described in claim 9, wherein an oil passage communicating with the machine body is arranged on the support column.

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