Buffering, supporting and separating mechanism

Abstract

The utility model belongs to the technical field of launching equipment, and provides a buffering, supporting and separating mechanism. The buffering device comprises a mounting plate, a rolling assembly and a buffering assembly, the rolling assembly is connected to the mounting plate and comprises at least two clamping roller sets, and each clamping roller set comprises a fixed roller and a movable roller which are used for being clamped on the two side walls of a guide rail in the launching box in the width direction respectively. The fixed roller is fixedly connected to the mounting plate, and the movable roller is movably connected to the mounting plate; the buffering assembly is connected between the two clamping roller sets and at least comprises a first elastic piece and connecting rods connected to the two ends of the first elastic piece, the two ends of each connecting rod are rotationally connected with the movable roller and the mounting plate correspondingly, and when the movable roller gets close to or gets away from the fixed roller, the connecting rods are driven to rotate, so that the clamping roller sets are clamped to the mounting plate. And the first elastic piece is stretched or compressed. The buffering device plays a role in buffering and protecting the aircraft.

Description

Technical Field

[0001] This utility model relates to the field of launch equipment technology, and in particular to a buffer support release mechanism. Background Technology

[0002] Unlike wheeled takeoff and landing aircraft, booster aircraft lack sufficient initial velocity during takeoff. In current technology, common takeoff methods for aircraft include gas cylinder propulsion, rocket propulsion, etc. In order to reduce the friction between the aircraft and the launch box rail, a slider mechanism is specially designed to work with the aircraft.

[0003] During aircraft transportation, the aircraft inside the launch container experiences overloads in various directions. To protect the aircraft, cushioning and limiting measures are necessary. Typically, foam pads are added inside the launch container to cushion the aircraft during transport. However, this method is overly cumbersome; the foam pads must be placed inside the launch container before transport and removed before launch, significantly increasing workload.

[0004] Therefore, a new solution is needed to address the aforementioned technical problems. Utility Model Content

[0005] In view of the shortcomings of the prior art described above, the purpose of this utility model is to provide a buffer support release mechanism to solve the problem of how to conveniently perform buffering during the transportation process of aircraft in the prior art.

[0006] To achieve the above and other related objectives, this utility model provides a buffer support release mechanism, specifically configured as follows: It includes a mounting plate, a rolling assembly, and a buffer assembly. The rolling assembly is connected to the mounting plate and includes at least two sets of clamping rollers. Each set of clamping rollers includes a fixed roller and a movable roller for clamping the two side walls of the guide rail in the width direction inside the launch box, respectively. The fixed roller is fixed to the mounting plate, and the movable roller is movably connected to the mounting plate. The buffer assembly is connected between the two sets of clamping rollers and includes at least a first elastic element and a connecting rod connected to both ends of the first elastic element. The two ends of the connecting rod are rotatably connected to the movable roller and the mounting plate, respectively. When the movable roller approaches or moves away from the fixed roller, it drives the connecting rod to rotate, thereby extending or compressing the first elastic element.

[0007] Optionally, the mounting plate is provided with a first strip-shaped hole, the length direction of which is perpendicular to the line connecting the fixed roller and the movable roller of the clamping roller group; a first through hole is provided on the side of the connecting rod near the first elastic element; the buffer assembly further includes a first connecting pin, which passes through both the first strip-shaped hole and the first through hole to rotatably connect the connecting rod to the mounting plate.

[0008] Optionally, the buffer assembly further includes a clamping plate, which has a second strip hole that matches the first strip hole. The connecting rod is located between the mounting plate and the clamping plate, and the first connecting pin passes through the first strip hole, the first through hole, and the second strip hole simultaneously.

[0009] Optionally, a second connecting pin is provided at one end of the connecting rod near the first elastic member, and the first elastic member is sleeved on the second connecting pin.

[0010] Optionally, the mounting plate is provided with a third strip-shaped hole, the length direction of which is the same as the line connecting the fixed roller and the movable roller of the clamping roller group. The end of the connecting rod near the movable roller is provided with a second through hole. The connecting shaft of the movable roller passes through both the third strip-shaped hole and the second through hole, and the connecting rod can rotate relative to the connecting shaft. When the connecting shaft moves in the third strip-shaped hole, it drives the movable roller to move closer to or away from the fixed roller.

[0011] Optionally, the buffer support release mechanism further includes a release component, which includes a pusher, a second elastic member, and a limiting member connected to the mounting plate. The limiting member is hollow inside, with an open side near the mounting plate and a first clearance hole on the side away from the mounting plate. The pusher includes a connected boss and a protruding edge. The limiting member is fitted onto the boss through the first clearance hole. The protruding edge is located inside the limiting member. The two ends of the second elastic member abut against the protruding edge and the mounting plate, respectively. The boss is used to abut against the outer wall of the aircraft under the action of the second elastic member.

[0012] Optionally, the disengagement assembly further includes a base connected to the mounting plate, the limiting member being connected to the mounting plate via the base, the base being provided with a pin, the pushing member being provided with a second clearance hole, the pin extending out of the pushing member through the second clearance hole and for inserting into the pin hole of the aircraft that mates with the pin, the second elastic member being sleeved on the pin, and the two ends of the second elastic member respectively abutting between the flange and the base.

[0013] Optionally, the rolling assembly further includes at least one set of sliding rollers, the sliding roller set including roller mounting bases and sliding rollers for rolling connection with the top surface of the guide rail, both ends of the sliding rollers being connected to the roller mounting bases, and the sliding rollers being connected to the mounting plate through the roller mounting bases.

[0014] Optionally, the detachment component is disposed in the middle of the mounting plate, and at least two sets of sliding rollers are provided, with multiple sets of sliding rollers located on both sides of the detachment component and distributed along the length direction of the guide rail.

[0015] Optionally, the mounting plate is further connected to a support member, which is used to abut against the outer side wall of the aircraft, and the side of the support member facing the aircraft is adapted to the outer contour of the aircraft.

[0016] As described above, the buffer support release mechanism of this utility model has the following beneficial effects:

[0017] By installing at least two sets of clamping rollers on the mounting plate, each set of clamping rollers includes fixed rollers and movable rollers spaced apart on the mounting plate, wherein the fixed rollers are fixed to the mounting plate and the movable rollers are movably connected to the mounting plate; a buffer assembly is connected between the two sets of clamping rollers, the buffer assembly includes a first elastic element and connecting rods connected to both ends of the first elastic element, the two ends of the connecting rods being rotatably connected to the movable rollers and the mounting plate respectively, when the movable rollers approach or move away from the fixed rollers, they drive the connecting rods to rotate, thereby extending or compressing the first elastic element, which helps to reduce the shaking of the aircraft and plays a buffering and protective role for the aircraft. Attached Figure Description

[0018] Figure 1 The diagram shown is a structural schematic of the buffer support release mechanism according to an embodiment of the present utility model.

[0019] Figure 2 The diagram shown is a structural schematic of the mounting plate according to an embodiment of the present utility model.

[0020] Figure 3 The diagram shown is a structural schematic of the connecting rod according to an embodiment of the present utility model;

[0021] Figure 4 The diagram shown is a structural schematic of the detachment component according to an embodiment of the present invention.

[0022] Explanation of reference numerals in the attached figures

[0023] 1-Mounting plate; 11-First strip hole; 12-Third strip hole;

[0024] 2-Rolling assembly; 21-Fixed roller; 22-Movable roller; 221-Connecting shaft; 23-Sliding roller; 24-Roller mounting base;

[0025] 3-Buffer assembly; 31-Connecting rod; 311-First through hole; 312-Second connecting pin; 313-Second through hole; 32-First elastic element; 33-First connecting pin; 34-Clamping plate;

[0026] 4-Supporting components;

[0027] 5-Disengagement component; 51-Pushing component; 511-Boss; 512-Protruding edge; 52-Second elastic component; 53-Limiting component; 54-Base; 541-Pin. Detailed Implementation

[0028] The following specific examples illustrate the implementation of this utility model. Those skilled in the art can easily understand other advantages and effects of this utility model from the content disclosed in this specification. This utility model can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this utility model.

[0029] It should be noted that the illustrations provided in this embodiment are only schematic representations of the basic concept of this utility model. Therefore, the illustrations only show components relevant to this utility model and are not drawn according to the actual number, shape, and size of the components in implementation. In actual implementation, the shape, quantity, and proportion of each component can be arbitrarily changed, and the component layout may be more complex. The structures, proportions, and sizes shown in the accompanying drawings are only for illustrative purposes to aid those skilled in the art and are not intended to limit the implementation conditions of this utility model. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to size, without affecting the effects and objectives of this utility model, should still fall within the scope of the technical content disclosed in this utility model. Furthermore, terms such as "upper," "lower," "left," "right," "middle," and "one" used in this specification are only for clarity of description and are not intended to limit the scope of implementation of this utility model. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of implementation of this utility model.

[0030] Before describing the embodiments of this utility model in detail, the application environment of this utility model is first described. The technology of this utility model is mainly applied to aircraft installed in a launch canister. The buffer support release mechanism of this utility model clamps the aircraft inside the launch canister and can move synchronously with the aircraft inside the launch canister. When the aircraft is installed inside the launch canister, the buffer support release mechanism of this utility model is slidably mounted on the guide rail inside the launch canister and located on opposite sides of the outer wall of the aircraft to clamp the aircraft inside the launch canister. During the launch of the aircraft, the buffer support release mechanism of this utility model moves synchronously with the aircraft along the guide rail inside the launch canister; when the buffer support release mechanism slides out of the launch canister, the buffer support release mechanism separates from the aircraft.

[0031] like Figure 1 As shown, some embodiments of this utility model provide a buffer support release mechanism, including a mounting plate 1, a rolling assembly 2, and a buffer assembly 3. The rolling assembly 2 is mounted on the mounting plate 1 and is used for rolling connection with a guide rail inside the launch box.

[0032] The rolling assembly 2 includes at least two sets of clamping rollers. The number of clamping roller sets can be set to two, four, or other multiples of 2, adaptable to actual needs. Each set of clamping rollers includes a fixed roller 21 and a movable roller 22, which are spaced apart on the mounting plate 1. The fixed roller 21 is fixedly mounted on the mounting plate 1, while the movable roller 22 is movably mounted on the mounting plate 1, allowing the movable roller 22 to move relative to the fixed roller 21, thereby changing the distance between the fixed roller 21 and the movable roller 22. It should be noted that the fixed roller 21 and the movable roller 22 are clamped on two side walls in the width direction of the guide rail, and both can roll on the side walls of the guide rail to achieve movement. Therefore, the minimum distance between them is adaptively set according to the width of the guide rail they are paired with.

[0033] The buffer assembly 3 is connected between two sets of clamping rollers and includes at least a connecting rod 31 and a first elastic element 32. There are two connecting rods 31, with the first elastic element 32 connecting between them. Each connecting rod 31 is rotatably connected at both ends to the movable roller 22 and the mounting plate 1, respectively. It should be noted that the first elastic element 32 is initially in a compressed state, meaning the first spring has preload.

[0034] When the launch container carrying the aircraft moves smoothly during transport, the movable roller 22, under the restoring force of the first elastic element 32, abuts against the side wall in the width direction of the guide rail, so that the fixed roller 21 and the movable roller 22 are stably clamped on both sides in the width direction of the guide rail, and the aircraft remains stable inside the launch container. At this time, the movable roller 22 is close to the fixed roller 21, and the first elastic element 32 is relatively extended.

[0035] When the launch container containing the aircraft experiences bumps during transport, causing the aircraft to be subjected to an upward overload, the buffer support release mechanism of this invention moves upward as a whole under the action of the aircraft. The fixed roller 21 moves away from the side wall in the width direction of the guide rail, causing the movable roller 22 to move away from the fixed roller 21, and driving the connecting rod 31 to rotate. This further compresses the first elastic element 32, increasing its restoring force. Subsequently, the current restoring force of the first elastic element 32 acts on the connecting rod 31, causing it to rotate and drive the movable roller 22 back into position, while the fixed roller 21 moves closer to the side wall in the width direction of the guide rail. During this process, the first elastic element 32 reduces the vibration of the aircraft within the launch container, providing buffer protection for the aircraft.

[0036] For example, the first elastic element 32 may include, but is not limited to, a spring.

[0037] In some embodiments, the rolling assembly 2 further includes at least one set of sliding rollers, each set comprising a sliding roller 23 and a roller mounting base 24. The sliding roller 23 is used for rolling connection with the guide rail of the launch container. Both ends of the sliding roller 23 are connected to the roller mounting base 24, and the sliding roller 23 is connected to the mounting plate 1 via the roller mounting base 24. The sliding roller 23 engages with the top surface of the guide rail inside the launch container. During launch, the sliding roller 23 rolls on the top surface of the guide rail, thereby reducing friction between them and helping to reduce drag during launch.

[0038] like Figure 1 , Figure 2 and Figure 3 As shown, in some embodiments, the mounting plate 1 is provided with a first strip-shaped hole 11. The length direction of the first strip-shaped hole 11 is perpendicular to the line connecting the fixed roller 21 and the movable roller 22 of the set of clamping rollers, that is, it is consistent with the length direction of the guide rail inside the launch box. A first through hole 311 is provided on the side of the connecting rod 31 near the first elastic member 32. The buffer assembly 3 also includes a first connecting pin 33, which passes through both the first strip-shaped hole 11 and the first through hole 311 to rotatably connect the connecting rod 31 to the mounting plate 1. Moreover, due to the presence of the first strip-shaped hole 11, the connecting rod 31 can also move along the length direction of the first strip-shaped hole 11, which increases the range of motion and flexibility of the connecting rod 31, and also helps to optimize the power transmission of the connecting rod 31, making the movement of the movable roller 22 more stable.

[0039] In one example, the buffer assembly 3 further includes a clamping plate 34, which has a second slotted hole that matches the first slotted hole 11. The connecting rod 31 is located between the mounting plate 1 and the clamping plate 34, with the first slotted hole 11 and the second slotted hole positioned opposite each other. The first connecting pin 33 passes through the first slotted hole 11, the first through hole 311, and the second slotted hole simultaneously, thus making the linear movement of the connecting rod 31 smoother. It should be noted that both ends of the first connecting pin 33 are provided with limiting structures to prevent the first connecting pin 33 from falling out of the first slotted hole 11, the first through hole 311, and the second slotted hole.

[0040] In some embodiments, a second connecting pin 312 is provided at the end of the connecting rod 31 near the first elastic member 32, and the first elastic member 32 is sleeved on the second connecting pin 312 so that the first elastic member 32 and the connecting rod 31 are always connected. It should be noted that the second connecting pins 312 of the two connecting rods 31 will not interfere with each other within the first elastic member 32.

[0041] In some embodiments, the mounting plate 1 is provided with a third strip-shaped hole 12, the length direction of which is the same as the line connecting the fixed roller 21 and the movable roller 22 of the clamping roller assembly. A second through hole 313 is provided at the end of the connecting rod 31 near the movable roller 22. The connecting shaft 221 of the movable roller 22 passes through both the third strip-shaped hole 12 and the second through hole 313 to connect the mounting plate 1, the connecting rod 31, and the movable roller 22 together, and the connecting rod 31 can rotate relative to the connecting shaft 221. When the connecting shaft 221 moves within the third strip-shaped hole 12, it drives the movable roller 22 to move closer to or away from the fixed roller 21. It should be noted that a limit structure is also provided at the end of the connecting shaft 221 near the third strip-shaped hole 12 to prevent the connecting shaft 221 from falling out of the third strip-shaped hole 12 and the second through hole 313.

[0042] In some embodiments, a support member 4 is also installed on the mounting plate 1. The support member 4 is used to abut against the outer wall of the aircraft to improve the stability of the aircraft when installed in the launch box. Furthermore, the side of the support member 4 facing the aircraft is adapted to the outer contour of the aircraft, thereby increasing the contact area between the support member 4 and the aircraft, which helps to reduce the damage to the aircraft caused by the support member 4 during the clamping process.

[0043] For example, there may be two support members 4, located on both sides of the mounting plate 1 along the length of the inner guide rail of the launch box.

[0044] like Figure 4As shown, in some embodiments, the buffer support release mechanism of this utility model further includes a release component 5. The release component 5 includes a pusher 51, a second elastic member 52, and a limiting member 53, which is mounted on the mounting plate 1. The limiting member 53 is hollow inside, with an open side near the mounting plate 1 and a first clearance hole on the side away from the mounting plate 1. The pusher 51 includes a boss 511 and a flange 512 connected together. The limiting member 53 is sleeved on the boss 511 through the first clearance hole. The flange 512 is located inside the limiting member 53. The two ends of the second elastic member 52 abut against the flange 512 and the mounting plate 1, respectively. The boss 511 abuts against the outer wall of the aircraft under the compression preload of the second elastic member 52.

[0045] After the aircraft is installed in the launch box, it is clamped between two buffer support release mechanisms, and a certain preload is applied to the aircraft to ensure its stability within the launch box. During launch, when the buffer support release mechanism slides out of the launch box, it moves away from the aircraft under the restoring force of the second elastic element 52.

[0046] For example, the second elastic element 52 may include, but is not limited to, a spring.

[0047] In some embodiments, the disengagement assembly 5 further includes a base 54 mounted on the mounting plate 1, and a limiting member 53 mounted on the base 54 for connection with the mounting plate 1. A pin 541 is provided on the base 54, and a second clearance hole is provided on the pusher 51, through which the pin 541 extends out of the pusher 51. A second elastic member 52 is sleeved on the pin 541, with its two ends abutting against the flange 512 and the base 54, respectively. The aircraft has a pin hole that mates with the pin 541; when the pin 541 is inserted into the pin hole, the relative position between the buffer support disengagement mechanism and the aircraft is fixed.

[0048] In one application scenario, when the aircraft is installed into the launch box, the pin 541 is first inserted into the pin hole of the aircraft. After the pins 541 on both sides of the aircraft are inserted into the pin holes, the second elastic element 52 is compressed so that the rolling assembly 2 engages with the guide rail inside the launch box, thus completing the installation between the aircraft and the launch box.

[0049] In one example, the disengagement component 5 is located in the center of the mounting plate, and at least two sets of sliding rollers are provided, with multiple sets of sliding rollers located on both sides of the disengagement component 5. Specifically, the multiple sets of sliding rollers are distributed along the length of the guide rails inside the launch box, thereby improving the stability of the aircraft's movement within the launch box.

[0050] In summary, the buffer support release mechanism provided by this utility model involves installing at least two sets of clamping rollers on a mounting plate. Each set of clamping rollers includes fixed rollers and movable rollers spaced apart on the mounting plate. The fixed rollers are fixed to the mounting plate, and the movable rollers are movably connected to the mounting plate. A buffer assembly is connected between the two sets of clamping rollers. The buffer assembly includes a first elastic element and connecting rods connected to both ends of the first elastic element. The two ends of the connecting rods are rotatably connected to the movable rollers and the mounting plate, respectively. When the movable rollers approach or move away from the fixed rollers, they drive the connecting rods to rotate, thereby extending or compressing the first elastic element. This helps to reduce the shaking of the aircraft and provides buffer protection for the aircraft.

[0051] The above embodiments are merely illustrative of the principles and effects of this utility model and are not intended to limit the scope of this utility model. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this utility model. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this utility model should still be covered by the claims of this utility model.

Claims

1. A cushioned support breakaway mechanism characterized by, The utility model relates to a kind of buffer support disengaging mechanism, including: Mounting plate; Rolling assembly, connected on the mounting plate, the rolling assembly includes at least two groups of clamping roller groups, each group of the clamping roller group includes fixed roller and movable roller for respectively clamping on the guide rail width direction two side walls in launch box, the fixed roller is fixedly connected on the mounting plate, the movable roller is movably connected on the mounting plate; Buffering assembly, connected between two groups of the clamping roller group, at least including first elastic member, and connecting rod connected at both ends of the first elastic member, both ends of the connecting rod are rotatably connected with the movable roller and the mounting plate respectively, when the movable roller is close to or away from the fixed roller, the rotation of the connecting rod is driven, to stretch or compress the first elastic member.

2. The cushioned support disconnect mechanism of claim 1, wherein: The mounting plate is provided with a first slot, the length direction of the first slot is perpendicular to the connecting direction of the fixed roller and the movable roller of a group of the clamping roller group;The side of the connecting rod close to the first elastic member is provided with a first through hole, the buffering assembly further includes a first connecting pin, the first connecting pin is simultaneously provided in the first slot and the first through hole, to rotatably connect the connecting rod with the mounting plate.

3. The cushioned support disconnect mechanism of claim 2, wherein: The buffering assembly further includes a clamping plate, the clamping plate is provided with a second slot matched with the first slot, the connecting rod is located between the mounting plate and the clamping plate, and the first connecting pin is simultaneously provided in the first slot, the first through hole and the second slot.

4. The cushioned support breakaway mechanism of claim 1, wherein: The end of the connecting rod close to the first elastic member is provided with a second connecting pin, and the first elastic member is sleeved on the second connecting pin.

5. The cushioned support disconnect mechanism of claim 2, wherein: The mounting plate is provided with a third slot, the length direction of the third slot is the same as the connecting direction of the fixed roller and the movable roller of a group of the clamping roller group, the end of the connecting rod close to the movable roller is provided with a second through hole, the connecting shaft of the movable roller is simultaneously provided in the third slot and the second through hole, and the connecting rod can rotate relative to the connecting shaft, when the connecting shaft moves in the third slot, the movable roller is driven to be close to or away from the fixed roller.

6. The cushioned support breakaway mechanism of any of claims 1-5, wherein: The buffering support disengaging mechanism further includes a disengaging assembly, the disengaging assembly includes a pushing member, a second elastic member, a limiting member connected to the mounting plate, the limiting member is hollow inside, and the side close to the mounting plate of the limiting member is open, and the side away from the mounting plate is provided with a first gap;The pushing member includes a boss and a convex edge connected to each other, the limiting member is sleeved on the boss through the first gap, the convex edge is located in the interior of the limiting member, the two ends of the second elastic member are respectively abutted between the convex edge and the mounting plate, and the boss is used to abut on the outer side wall of the aircraft under the action of the second elastic member.

7. The cushioned support disconnect mechanism of claim 6, wherein: The disengaging assembly further comprises a base connected to the mounting plate, the limiting member is connected to the mounting plate through the base, the base is provided with a latch, the pusher is provided with a second clearance hole, the latch extends out of the pusher through the second clearance hole, is used for being inserted into the pin hole matched with the latch of the aircraft, the second elastic member is sleeved on the latch, and two ends of the second elastic member are respectively abutted between the convex edge and the base.

8. The cushioned support disconnect mechanism of claim 6, wherein: The rolling assembly further comprises at least one set of sliding roller groups, each sliding roller group comprises a roller mounting seat and a sliding roller used for rolling connection with the top surface of the guide rail, both ends of the sliding roller are connected with the roller mounting seat, and the sliding roller is connected to the mounting plate through the roller mounting seat.

9. The cushioned support disconnect mechanism of claim 8, wherein: The disengaging assembly is arranged in the middle of the mounting plate, the sliding roller groups are provided with at least two groups, and a plurality of sliding roller groups are respectively arranged on both sides of the disengaging assembly and are distributed along the length direction of the guide rail.

10. The cushioned support disconnect mechanism of any of claims 7-9, wherein: The mounting plate is further connected with a support, the support is used for abutting against the outer side wall of the aircraft, and one side of the support towards the aircraft is matched with the outer contour of the aircraft.

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