Lateral limiting separation mechanism

Abstract

The utility model belongs to the technical field of aircrafts, and provides a lateral limiting separation mechanism, which is arranged in a box body of a box-type emitter, is used for installing an aircraft in the box body, and comprises at least two first support frames oppositely arranged in the box body; the driving assembly comprises rolling wheels and connecting shafts, the rolling wheels are connected to the first supporting frame through the connecting shafts, and the rolling wheels can roll on the rails in the box body so as to drive the first supporting frame to move in the box body in the length direction; the separation assembly comprises a positioning pin, a separation block and an elastic piece, the separation block and the elastic piece are arranged on the positioning pin in a sleeving mode, the separation block is connected with the elastic piece, when the aircraft is installed, at least part of the positioning pin can stretch into a fixing hole of the aircraft so that the aircraft can be clamped in the box body, and the separation block abuts against a fuselage of the aircraft; the elastic part is pressed by the machine body; the use of sliding blocks in the box-type launching process is reduced, the influence of friction force on aircraft launching is reduced, and the boosting launching efficiency is improved.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a lateral limit release mechanism. Background Technology

[0002] Traditional booster-type and wheeled takeoff and landing aircraft require frequent maintenance, cannot be stored for long periods, and have long preparation times for each takeoff, which cannot meet the needs in certain environments. Therefore, box-launch systems were developed. However, box-launch structures require the use of many sliders to assist in the launch. After the aircraft leaves the box, it detaches from the sliders and throws them out. The large number of sliders in traditional box-launch structures means that the weight of the sliders and the friction they generate can affect the launch effect. In severe cases, this can lead to insufficient initial velocity and crashes. Utility Model Content

[0003] In view of the shortcomings of the prior art, the purpose of this application is to provide a lateral limiting and release mechanism to solve the problem that the use of a large number of sliders in the box-type launch structure in the prior art affects the launch effect of the aircraft.

[0004] To achieve the above and other related objectives, this application provides a lateral limiting and release mechanism, disposed within the housing of a box-type launcher, for mounting an aircraft within the housing, comprising:

[0005] At least two primary support frames are arranged opposite to each other inside the box;

[0006] A drive assembly is disposed on the side of the first support frame away from the aircraft. The drive assembly includes a roller and a connecting shaft. The roller is connected to the first support frame through the connecting shaft. The roller can roll on a track inside the box to drive the first support frame to move along the length direction inside the box.

[0007] The release assembly is located on the side of the first support frame near the aircraft. The release assembly includes a positioning pin, a release block, and an elastic element. The release block and the elastic element are both sleeved on the positioning pin. The release block is connected to the elastic element. When the aircraft is installed into the housing, the positioning pin can at least partially extend into the fixing hole of the aircraft to clamp and position the aircraft in the housing. The release block abuts against the fuselage of the aircraft and is squeezed by the fuselage to press the elastic element.

[0008] Optionally, the disengagement assembly further includes a guide sleeve that surrounds the locating pin, the disengagement block, and the elastic element, with the locating pin and the disengagement block extending at least partially beyond the guide sleeve.

[0009] Optionally, any of the first support frames is further provided with a second support frame, the second support frame being fixed to the top of the first support frame, the second support frame having a first conforming block for constraining the side wing of the aircraft on the side near the aircraft, and the first conforming block having a bent portion matching the side wing of the aircraft on the side near the aircraft.

[0010] Optionally, the first conformal block is provided with a first ball bearing on the side away from the aircraft.

[0011] Optionally, the first support frame is further provided with a second conforming block for constraining the aircraft fuselage, and the second conforming block has an inclined portion that matches the aircraft fuselage.

[0012] Optionally, the first support frame is further provided with limiting members on both sides of the roller, and a second ball is provided at one end of each of the two limiting members that are close to each other. The side wall of the housing is provided with a protruding track, and the roller is locked on the track by the limiting members, and the second ball is in close contact with both sides of the track.

[0013] Optionally, the top of the first support frame is also provided with a limiting block for constraining the tail fin of the aircraft. When the aircraft is loaded into the box, the tail fin of the aircraft is folded and locked onto the limiting block.

[0014] Optionally, at least two rollers are provided, and two mounting plates are provided on the first support frame. The bottom of the mounting plates and the first support frame are each provided with three elliptical mounting holes. The rollers pass through the connecting shaft and are installed between the two mounting plates through the mounting holes.

[0015] Optionally, the first support frame is further provided with an adjustment mechanism for adjusting the rollers. The adjustment mechanism includes an adjustment block, an adjustment rod, and a synchronization block. The synchronization block is located on one side of the two mounting plates that are far apart from each other. The connecting shaft passes through the synchronization block, the mounting hole of the mounting plate, and the mounting hole of the first support frame in sequence to install the rollers on the first support frame. The adjustment block passes through the adjustment rod, and the adjustment rod passes through the synchronization block, the mounting hole of the mounting plate, and the mounting hole of the first support frame in sequence to install the adjustment block on the first support frame. The adjustment block is located between the two rollers.

[0016] Optionally, the adjusting block is provided with a first adjusting member and a second adjusting member. The first adjusting member passes through the adjusting block and is movably mounted on the first support frame. The second adjusting member is fixed to the adjusting block. The position of the adjusting rod on the mounting hole is adjusted by the first adjusting member or the second adjusting member, so as to adjust the position of the connecting shaft on the mounting hole.

[0017] In the lateral limiting and release mechanism provided in this application, the aircraft is first loaded into the housing, and the aircraft is clamped and positioned in the housing by inserting a positioning pin into the fixing hole of the aircraft. The first support frame moves in the housing by the rolling of rollers on the track inside the housing, thereby moving the aircraft. After the aircraft leaves the housing, the lateral limiting and release mechanism will follow the aircraft out of the housing. The elastic elements and release blocks on both sides of the aircraft will disengage the positioning pin from the fixing hole and release it from the aircraft, completing the launch of the aircraft. The movement of the aircraft in the housing does not require the use of sliders, which reduces the use of sliders in the housing launch process, reduces the impact of friction on the launch of the aircraft, and improves the boost launch efficiency. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of the first support frame of the lateral limiting and disengagement mechanism shown in one embodiment of this application;

[0019] Figure 2 This is a schematic diagram of the structure of the first and second support frames of the lateral limiting and disengagement mechanism according to an embodiment of this application;

[0020] Figure 3 This is a schematic diagram of the disengagement component of a lateral limiting disengagement mechanism according to an embodiment of this application;

[0021] Figure 4 This is a partial structural schematic diagram of a lateral limiting and disengaging mechanism according to an embodiment of this application.

[0022] Part Number Explanation

[0023] 1-First support frame; 2-Second support frame; 3-Roller; 4-Connecting shaft; 5-Mounting plate; 6-Adjusting block; 7-Adjusting rod; 8-Synchronizing block; 9-Limiting component; 10-Second ball; 11-Limiting block; 12-First adjusting component; 13-Second adjusting component; 14-First conforming block; 15-Second conforming block; 16-Bending part; 17-First ball; 18-Guide sleeve; 19-Disengagement block; 20-Positioning pin; 21-Elastic component; 22-Mounting hole. Detailed Implementation

[0024] The following specific embodiments illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification.

[0025] It should be understood that the structures, proportions, sizes, etc., illustrated in the accompanying drawings are merely for illustrative purposes to aid those skilled in the art and are not intended to limit the scope of this application. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to size, without affecting the effectiveness or purpose of this application, should still fall within the scope of the technical content disclosed herein. Furthermore, the terms such as "front," "back," "left," "right," "middle," and "one" used in this specification are merely for clarity and not intended to limit the scope of this application. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of this application.

[0026] It should be noted that traditional box-type launch structures rely on sliders for the positioning, installation, and boosted launch of aircraft. For example, sliders are used to lock onto tracks within the box for movement, and to fold the aircraft's wings and tail fins to constrain the aircraft. This requires a large number of sliders. After the aircraft exits the box, the sliders detach from it due to gravity. The heavy weight and high friction of the sliders can affect the boosted launch effect. High friction can affect the aircraft's initial velocity, and heavy weight can prevent the sliders from detaching from the aircraft in time, all of which affect the launch. Furthermore, aircraft are usually made of composite materials, and their dimensions are subject to manufacturing deviations and cannot be standardized. The sliders lack adjustability. If the aircraft's dimensions are too small, gaps can easily occur during installation, leading to damage. If the aircraft's dimensions are too large, it may be impossible to fit it into the box.

[0027] Please see Figures 1 to 4 This application exemplarily provides a lateral limiting and disengagement mechanism, disposed within the housing of a box-type launcher, for mounting an aircraft within the housing, comprising:

[0028] At least two first support frames 1 are arranged opposite to each other inside the box;

[0029] The drive assembly is located on the side of the first support frame 1 away from the aircraft. The drive assembly includes a roller 3 and a connecting shaft 4. The roller 3 is connected to the first support frame 1 through the connecting shaft 4. The roller 3 can roll on the track inside the box to drive the first support frame 1 to move along the length direction inside the box.

[0030] The release assembly is located on the side of the first support frame 1 near the aircraft. The release assembly includes a positioning pin 20, a release block 19, and an elastic element 21. The release block 19 and the elastic element 21 are both sleeved on the positioning pin 20. The release block 19 is connected to the elastic element 21. When the aircraft is installed into the housing, the positioning pin 20 can at least partially extend into the fixing hole of the aircraft to clamp and position the aircraft in the housing. The release block 19 abuts against the fuselage of the aircraft and is squeezed by the fuselage to press the elastic element 21.

[0031] In the lateral limiting and release mechanism provided in this application, the aircraft is first loaded into the housing. The positioning pin 20 is inserted into the fixing hole of the aircraft to clamp and position the aircraft in the housing. The first support frame 1 is moved in the housing by the rolling of the roller 3 on the track inside the housing, thereby moving the aircraft. After the aircraft leaves the housing, the lateral limiting and release mechanism will follow the aircraft out of the housing. The elastic members 21 and the release block 19 on both sides of the aircraft will push the positioning pin 20 out of the fixing hole and separate it from the aircraft, completing the launch of the aircraft. The movement of the aircraft in the housing does not require the use of sliders, which reduces the use of sliders in the housing launch process, reduces the impact of friction on the launch of the aircraft, and improves the boost launch efficiency.

[0032] In this embodiment, the disengagement assembly further includes a guide sleeve 18, which surrounds the positioning pin 20, the disengagement block 19, and the elastic element 21. The positioning pin 20 and the disengagement block 19 extend at least partially out of the guide sleeve 18. Specifically, when the aircraft is not installed in the housing, the disengagement block 19 surrounds one end of the positioning pin 20. The guide sleeve 18 has a cylindrical structure and is used to guide the movement of the disengagement block 19 and protect the elastic element 21. When the aircraft is installed in the housing, the aircraft fuselage presses against the lateral limiting disengagement mechanism, and the disengagement block 19 is compressed, pressing against the elastic element 21. One end of the positioning pin 20 protrudes and extends into the fixing hole of the aircraft to clamp and position the aircraft, thereby installing the aircraft in the box. When the aircraft exits the box, the drive component disengages from the track and exits the box with the aircraft. Since the lateral limiting release mechanism is no longer restricted by the box, the elastic element 21 is stretched away from the aircraft. The release block 19 presses against the fuselage of the aircraft, causing the positioning pin 20 to disengage from the fixing hole of the aircraft. This achieves active release of the aircraft after it exits the box, preventing the positioning pin 20 from getting stuck in the fixing hole of the aircraft and causing the slider to be unable to fall off, which would affect flight safety.

[0033] In some embodiments, a second support frame 2 is also provided on any of the first support frames 1. The second support frame 2 is fixed to the top of the first support frame 1. The second support frame 2 is provided with a first conforming block 14 for constraining the side wings of the aircraft on the side near the aircraft. The first conforming block 14 is provided with a bending part 16 that matches the side wings of the aircraft on the side near the aircraft. Specifically, the first conforming block 14 is provided near the top of the second support frame 2. Since the side wings of the aircraft are large, they need to be folded when entering the box. After the side wings are folded, they will generate lateral thrust. It is necessary to constrain the thrust generated in the box. The bending part 16 of the first conforming block 14 is adapted to the side wings of the aircraft to fold and constrain the side wings, so as to facilitate the loading of the aircraft into the box.

[0034] In the above embodiment, the first conforming block 14 is provided with a first ball bearing 17 on the side away from the aircraft. After the aircraft folds its wings and is constrained by the first conforming block 14, the lateral thrust generated by the folding of the wings will squeeze the entire conforming block toward the inner wall of the box. By using the first ball bearing 17, the friction between the first conforming block 14 and the inner wall of the box can be reduced, further reducing the impact of friction on the launch of the aircraft during the launch process.

[0035] In some embodiments, the first support frame 1 is also provided with a second conformal block 15 for constraining the aircraft fuselage. The second conformal block 15 has an inclined portion that matches the aircraft fuselage. The second conformal block 15 increases the contact area with the aircraft fuselage, ensuring that the fuselage will not be damaged when subjected to force.

[0036] In this embodiment, the first support frame 1 is also provided with limiting members 9 on both sides of the roller 3. The two limiting members 9 are each provided with a second ball bearing 10 at their close ends. The side wall of the housing is provided with a protruding track. The roller 3 is locked onto the track by the limiting members 9. The second ball bearing 10 is in close contact with both sides of the track. Specifically, the first support frame 1 is locked onto the track on the side wall of the housing by the limiting members 9. The second ball bearing 10 is in contact with the side of the track, and the roller 3 is in contact with the surface of the track. Compared with the traditional slider structure, the roller 3 and the second ball bearing 10 can reduce the friction generated during movement and further improve the boost launch efficiency.

[0037] In some embodiments, the top of the first support frame 1 is also provided with a limiting block 11 for constraining the tail fin of the aircraft. When the aircraft is loaded into the box, the tail fin of the aircraft is folded and locked onto the limiting block 11. Specifically, the aircraft needs to fold the tail fin before it can be loaded into the box. The limiting block 11 constrains the folded tail fin and limits the tail of the aircraft, which facilitates the assembly of the aircraft. After the aircraft leaves the box, the tail fin unfolds as the lateral limiting release mechanism after leaving the box disengages and is thrown away.

[0038] In this embodiment, at least two rollers 3 are provided, and two mounting plates 5 are provided on the first support frame 1. The bottom of the mounting plates 5 and the first support frame 1 are provided with three elliptical mounting holes 22. The rollers 3 are passed through the connecting shaft 4 and installed between the two mounting plates 5 through the mounting holes 22. The two mounting plates 5 limit the rollers 3 to ensure that the rollers 3 will not deviate when rolling.

[0039] Specifically, the first support frame 1 is also provided with an adjustment mechanism for adjusting the roller 3. The adjustment mechanism includes an adjustment block 6, an adjustment rod 7, and a synchronization block 8. The synchronization block 8 is located on the side of the two mounting plates 5 that are far apart from each other. The connecting shaft 4 passes through the synchronization block 8, the mounting hole 22 of the mounting plate 5, and the mounting hole 22 of the first support frame 1 in sequence to install the roller 3 on the first support frame 1. The adjustment block 6 passes through the adjustment rod 7. The adjustment rod 7 passes through the synchronization block 8, the mounting hole 22 of the mounting plate 5, and the mounting hole 22 of the first support frame 1 in sequence to install the adjustment block 6 on the first support frame 1. The adjustment block 6 is located between the two rollers 3. By adjusting the position of the adjustment rod 7 in the mounting hole 22, the synchronization block 8 can synchronize the position change of the adjustment rod 7 in the mounting hole 22 to the connecting shaft 4, thereby changing the position of the connecting shaft 4 in the mounting hole 22.

[0040] In the above embodiment, the adjusting block 6 is provided with a first adjusting member 12 and a second adjusting member 13. The first adjusting member 12 passes through the adjusting block 6 and is movably mounted on the first support frame 1. The second adjusting member 13 is fixedly connected to the adjusting block 6. The position of the adjusting rod 7 on the mounting hole 22 is adjusted by the first adjusting member 12 or the second adjusting member 13 to adjust the position of the connecting shaft 4 on the mounting hole 22. Specifically, the first adjusting member 12 and the second adjusting member 13 are set as screws. Pressing the first adjusting member 12 can move the adjusting block 6 away from the side wall of the box, and pulling the second adjusting member 13 can move the adjusting block 6 closer to the side wall of the box. By moving the adjusting block 6 by the first adjusting member 12 or the second adjusting member 13, the adjusting rod 7 is driven to move synchronously on the mounting hole 22, thereby changing the distance between the roller 3 and the side wall of the box. Since the aircraft may have inconsistent body shape due to manufacturing process, the adjusting mechanism can make certain adjustments to avoid the situation where the aircraft cannot be packed.

[0041] In summary, in the lateral limiting and release mechanism provided in this application, the aircraft is first loaded into the housing, and the positioning pin 20 is inserted into the fixing hole of the aircraft to clamp and position the aircraft in the housing. The first support frame 1 is moved in the housing by the rolling of the roller 3 on the track inside the housing, thereby moving the aircraft. After the aircraft exits the housing, the elastic members 21 and the release block 19 on both sides of the aircraft remove the positioning pin 20 from the fixing hole and separate it from the aircraft, completing the launch of the aircraft. The movement of the aircraft in the housing does not require the use of sliders, which reduces the use of sliders in the housing launch process, reduces the impact of friction on the launch of the aircraft, and improves the boost launch efficiency.

[0042] The above embodiments are merely illustrative of the principles and effects of this application and are not intended to limit this application. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this application should still be covered by the claims of this application.

Claims

1. A lateral limiting and release mechanism, disposed within the housing of a box-type launcher, for mounting an aircraft within the housing, characterized in that, include: At least two primary support frames are arranged opposite to each other inside the box; A drive assembly is disposed on the side of the first support frame away from the aircraft. The drive assembly includes a roller and a connecting shaft. The roller is connected to the first support frame through the connecting shaft. The roller can roll on a track inside the box to drive the first support frame to move along the length direction inside the box. The release assembly is located on the side of the first support frame near the aircraft. The release assembly includes a positioning pin, a release block, and an elastic element. The release block and the elastic element are both sleeved on the positioning pin. The release block is connected to the elastic element. When the aircraft is installed into the housing, the positioning pin can at least partially extend into the fixing hole of the aircraft to clamp and position the aircraft in the housing. The release block abuts against the fuselage of the aircraft and is squeezed by the fuselage to press the elastic element.

2. The lateral check unhooking mechanism according to claim 1, wherein The disengagement assembly further includes a guide sleeve that surrounds the locating pin, the disengagement block, and the elastic element, with the locating pin and the disengagement block extending at least partially beyond the guide sleeve.

3. The lateral check unhooking mechanism of claim 2, wherein, Each of the first support frames is further provided with a second support frame, the second support frame being fixed to the top of the first support frame, the second support frame having a first conforming block for constraining the side wing of the aircraft on the side near the aircraft, and the first conforming block having a bent portion matching the side wing of the aircraft on the side near the aircraft.

4. The lateral check unhooking mechanism of claim 3, wherein, The first conformal block has a first ball bearing on the side away from the aircraft.

5. The lateral check unhooking mechanism of claim 1, wherein, The first support frame is also provided with a second conforming block for constraining the aircraft fuselage, and the second conforming block has an inclined portion that matches the aircraft fuselage.

6. The lateral check unhooking mechanism of claim 1, wherein, The first support frame is also provided with limiting members on both sides of the roller. Each of the two limiting members is provided with a second ball at one end that is close to each other. The side wall of the box is provided with a protruding track. The roller is locked on the track by the limiting members, and the second ball is in close contact with both sides of the track.

7. The lateral check unhooking mechanism of claim 1, wherein, The top of the first support frame is also provided with a limiting block for constraining the tail fin of the aircraft. When the aircraft is loaded into the box, the tail fin of the aircraft is folded and locked onto the limiting block.

8. The lateral check unhooking mechanism of claim 1, wherein, The roller is provided with at least two, and the first support frame is provided with two mounting plates. The bottom of the mounting plate and the first support frame are provided with three elliptical mounting holes. The roller passes through the connecting shaft and is installed between the two mounting plates through the mounting holes.

9. The lateral check unhooking mechanism of claim 8, wherein, The first support frame is also provided with an adjustment mechanism for adjusting the rollers. The adjustment mechanism includes an adjustment block, an adjustment rod, and a synchronization block. The synchronization block is located on the side of the two mounting plates that are far apart from each other. The connecting shaft passes through the synchronization block, the mounting hole of the mounting plate, and the mounting hole of the first support frame in sequence to install the rollers on the first support frame. The adjustment block passes through the adjustment rod, and the adjustment rod passes through the synchronization block, the mounting hole of the mounting plate, and the mounting hole of the first support frame in sequence to install the adjustment block on the first support frame. The adjustment block is located between the two rollers.

10. The lateral check unhooking mechanism of claim 9, wherein, The adjusting block is provided with a first adjusting member and a second adjusting member. The first adjusting member passes through the adjusting block and is movably mounted on the first support frame. The second adjusting member is fixed to the adjusting block. The position of the adjusting rod on the mounting hole is adjusted by adjusting the first adjusting member or the second adjusting member, thereby adjusting the position of the connecting shaft on the mounting hole.

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