Device and system for locking and releasing aircraft

Abstract

The invention provides a device and system for locking and releasing an aircraft. The device comprises a fixing frame, a locking and releasing mechanism, a recycling box and a parallelogram mechanism. The locking and releasing mechanism comprises a firework bolt, a firework bolt mounting frame and a locking nut; the parallelogram mechanism comprises an adapter rod, a connecting rod, a rotating shaft and an arc-shaped baffle plate; the firework bolt mounting frame is connected with the fixing frame through a fastener, and the firework bolt is connected with the firework bolt mounting frame through a thread of the firework bolt; the firework bolt comprises a firework bolt body and a firework bolt screw rod, and threads are arranged on the firework bolt body and the firework bolt screw rod; the adapter rod is arranged at the top of the fixing frame, the connecting rod is sequentially provided with three through holes from top to bottom, and the connecting rod is connected with the adapter rod through a rotating shaft matched with the upper through holes. The locking and releasing device is simple in structure, and the design problem of the locking and releasing device under the condition that the installation position of the unmanned aerial vehicle is restrained is effectively solved.

Description

Technical Field

[0001] The present application relates to the field of spacecraft structure design, and in particular, to a device and system for locking and releasing an aircraft. Background Art

[0002] As an important component of the spacecraft launch system, the locking and releasing device locks the spacecraft during storage and transportation, and needs to effectively adapt to various mechanical environmental loads during the storage and transportation process. When the spacecraft is launched and separated, it needs to be unlocked and released in advance according to the launch sequence to achieve safe launch and separation of the spacecraft.

[0003] The prior art with patent number CN111426242B discloses an axial locking and releasing assembly of a break-and-not-fall-off unmanned aerial vehicle, comprising a bearing pin, a mounting frame and a translation rod, wherein both ends of the translation rod are rotatably mounted on a swing rod seat through a first swing rod and a second swing rod respectively, and an end close to the second swing rod has a connecting plate, the mounting frame is mounted on the second swing rod or on the swing rod seat, the bearing pin fixes the connecting plate on the mounting frame, and has two states, locked and unlocked. In the locked state, the translation rod is not allowed to move relative to the swing rod seat; when the unmanned aerial vehicle is launched, the bearing pin can be pulled off and enter the unlocked state under the launch thrust of the unmanned aerial vehicle, at which time the two ends of the bearing pin stay on the mounting frame and the connecting plate respectively. The present invention effectively solves the problem of high-speed flying objects during the launch of the unmanned aerial vehicle, overcomes the harm of the falling objects to surrounding products and personnel during the launch process, and greatly improves the launch safety, but it is located at the tail of the aircraft and is installed and fixed at the rear end of the fixing frame to realize the locking and releasing function of the aircraft, and cannot be applied to the structural requirements of being installed in the middle of the fixing frame.

[0004] The prior art with patent number CN113237395B discloses a fixed missile device based on a lever mechanism, including a support frame, a positioning seat, an elastic mechanism, a support arm mechanism, a locking mechanism and a signal feedback mechanism, wherein the positioning seat is detachably mounted on the support frame; the support arm mechanism is rotatably mounted on the support frame, one end of the support arm mechanism is connected to one end of the elastic mechanism for locking the missile, and the other end of the elastic mechanism is mounted on the positioning seat, the missile includes a locking state and a launching state, when the locking mechanism is destroyed, one end of the support arm mechanism rotates around the axis under the drive of the elastic mechanism so that the other end of the support arm mechanism drives the other end of the locking mechanism to move to a second position so that the missile is in the launching state, the present invention can effectively realize the axial fixing and rapid unlocking of the missile and has an unlocking signal feedback function, has the advantages of high reliability and large bearing capacity, etc., it is located in the middle of the aircraft and is installed in the middle area of ​​the fixing frame at the same time, to realize the locking and releasing function of the aircraft, but it occupies the internal space of the fixing frame, reducing the space utilization efficiency of the fixing frame itself. The above technical achievements cannot meet the structural requirement that the locking and releasing device is installed in the middle of the fixing frame and does not occupy the internal space of the fixing frame. Therefore, it is of great significance to develop a new type of locking and releasing device for unmanned aerial vehicles. Summary of the invention

[0005] In view of the defects in the prior art, the purpose of the present application is to provide a device and system for locking and releasing an aircraft.

[0006] According to the present application, a device and system for locking and releasing an aircraft include: a fixing frame, a locking and releasing mechanism, a recovery box, and a parallelogram mechanism;

[0007] The locking and releasing mechanism comprises: a pyrotechnic bolt, a pyrotechnic bolt mounting frame and a locking nut;

[0008] The parallelogram mechanism comprises: a transfer rod, a connecting rod, a rotating shaft and an arc-shaped baffle;

[0009] The pyrotechnic bolt mounting frame is connected to the fixing frame via a fastener, and the pyrotechnic bolt is connected to the pyrotechnic bolt mounting frame via its own thread;

[0010] The pyrotechnic bolt comprises a pyrotechnic bolt body and a pyrotechnic bolt screw, and both the pyrotechnic bolt body and the pyrotechnic bolt screw are provided with threads;

[0011] The transfer rod is arranged on the top of the fixing frame, the connecting rod has three through holes in sequence from top to bottom, the connecting rod is connected to the transfer rod via a rotating shaft matched with the upper through hole, the connecting rod is connected to the fixing frame via a rotating shaft matched with the middle through hole, and the connecting rod is connected to the arc baffle via a rotating shaft matched with the lower through hole;

[0012] The pyrotechnic bolt body is threadedly connected to the pyrotechnic bolt mounting frame, the pyrotechnic bolt screw rod passes through the middle part of the adapter frame, and the locking nut cooperates with the pyrotechnic bolt screw rod and is recovered and covered inside.

[0013] Preferably, a boss is provided at the rear end of the arc-shaped baffle, and when the locking nut is tightened, one end face of the adapter rod fits with the end face of the pyrotechnic bolt mounting frame, and the other end face of the adapter rod fits with the end face of the locking nut, so that the boss at the rear end of the arc-shaped baffle fits and locks with the tail end face of the aircraft.

[0014] Preferably, the pyrotechnic bolt screw and the pyrotechnic bolt body are detachable structures. The pyrotechnic bolt separates the pyrotechnic bolt screw with the locking nut and hits the recovery box according to the system launch instruction. The parallelogram mechanism overturns under the impact and releases the restraint on the aircraft. The pyrotechnic bolt screw and the locking nut fall into the recovery box.

[0015] Preferably, the transfer rod is an H-shaped three-dimensional symmetrical structure, and a total of four connecting rods are provided, and the connecting rods are symmetrically distributed on the left and right sides of the fixing frame with the fixing frame as the center.

[0016] Preferably, the distance between the upper through hole and the middle through hole, and the distance between the middle through hole and the lower through hole of the connecting rod can be flexibly adjusted.

[0017] Preferably, the aircraft is installed on a fixing frame by hoisting.

[0018] Preferably, the fixing frame is completely fixed in the launching device.

[0019] Preferably, the arc-shaped baffle is divided into a left arc-shaped baffle and a right arc-shaped baffle.

[0020] Preferably, the transfer rod, the connecting rod, the rotating shaft, the left arc-shaped baffle plate and the right arc-shaped baffle plate together form a parallelogram mechanism and a lever mechanism.

[0021] The present application also provides a system for realizing aircraft locking and releasing, comprising the above-mentioned device for aircraft locking and releasing.

[0022] Compared with the prior art, this application has the following beneficial effects:

[0023] 1. This application effectively solves the design problem of the locking and releasing device when the installation position of the unmanned aerial vehicle is constrained by setting a parallelogram mechanism, and is suitable for the structural requirements of being installed in the middle of the fixed frame.

[0024] 2. This application adopts a multifunctional integrated design, has a simple structure, is easy to apply in engineering, does not occupy the internal space of the fixing frame, and improves the space utilization efficiency of the fixing frame itself. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Other features, objects and advantages of the present application will become more apparent by reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0026] Figure 1 This is a schematic diagram of the overall structure of the device for locking and releasing an aircraft, which is mainly embodied in this application;

[0027] Figure 2 This is a schematic diagram of the side view of the device used for locking and releasing an aircraft, which is mainly embodied in this application;

[0028] Figure 3 This is a schematic diagram of the locking section of the AA surface of the device for locking and releasing an aircraft, which is mainly embodied in this application;

[0029] Figure 4 This is a schematic diagram of the release structure of the device used for locking and releasing the aircraft, which is mainly embodied in this application;

[0030] Figure 5 This is a schematic diagram of the release section of the AA surface of the device for locking and releasing an aircraft, which is mainly embodied in this application;

[0031] Figure 6 This application mainly embodies a schematic diagram of the connecting rod structure of a device for locking and releasing an aircraft.

[0032] As shown in the figure: 1. fixing frame; 2. pyrotechnic bolt; 201. pyrotechnic bolt body; 202. pyrotechnic bolt screw; 3. pyrotechnic bolt mounting frame; 4. recovery box; 5. adapter rod; 6. rotating shaft; 7. aircraft; 8. connecting rod; 9. left arc baffle; 10. right arc baffle; 11. locking nut. DETAILED DESCRIPTION

[0033] The present application is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present application. These all belong to the protection scope of the present application.

[0034] The locking and releasing device and system for the aircraft 7 provided by the present application include: a fixing frame 1, a locking and releasing mechanism, a recovery box 4 and a parallelogram mechanism; the locking and releasing mechanism includes: a pyrotechnic bolt 2, a pyrotechnic bolt mounting frame 3 and a locking nut 11; the parallelogram mechanism includes: a transfer rod 5, a connecting rod 8, a rotating shaft 6 and an arc-shaped baffle; the pyrotechnic bolt mounting frame 3 is connected to the fixing frame 1 through a fastener, and the pyrotechnic bolt 2 is connected to the pyrotechnic bolt mounting frame 3 through its own thread; the pyrotechnic bolt 2 includes a pyrotechnic bolt body 201 and a pyrotechnic bolt screw 202, and both the pyrotechnic bolt body 201 and the pyrotechnic bolt screw 202 are provided with threads;

[0035] The transfer rod 5 is arranged on the top of the fixing frame 1, and the connecting rod 8 has three through holes in sequence from top to bottom. The connecting rod 8 is connected to the transfer rod 5 through the rotating shaft 6 matched with the upper through hole, the connecting rod 8 is connected to the fixing frame 1 through the rotating shaft 6 matched with the middle through hole, and the connecting rod 8 is connected to the arc baffle through the rotating shaft 6 matched with the lower through hole;

[0036] The pyro bolt body 201 is threadedly connected with the pyro bolt mounting frame 3, the pyro bolt screw 202 passes through the middle of the adapter frame, and the locking nut 11 cooperates with the pyro bolt screw 202 and is recovered and covered inside. A boss is provided at the rear end of the arc baffle, and the locking nut 11 is tightened, so that the end face of one side of the adapter rod 5 fits with the end face of the pyro bolt mounting frame 3, and the end face of the other side of the adapter rod 5 fits with the end face of the locking nut 11, and the boss at the rear end of the arc baffle is fitted and locked with the end face of the tail of the aircraft 7.

[0037] The pyrotechnic bolt screw 202 and the pyrotechnic bolt body 201 are detachable structures. The pyrotechnic bolt 2 separates the pyrotechnic bolt screw 202 with the locking nut 11 and hits the recovery box 4 according to the system launch command. The parallelogram mechanism overturns under the impact and releases the aircraft 7. The pyrotechnic bolt screw 202 and the locking nut 11 fall into the recovery box 4. The adapter rod 5 is an H-shaped three-dimensional symmetrical structure. There are four connecting rods 8, which are symmetrically distributed on the left and right sides of the fixing frame 1 with the fixing frame 1 as the center.

[0038] The distance between the upper through hole and the middle through hole of the connecting rod 8, and the distance between the middle through hole and the lower through hole can be flexibly adjusted. The aircraft 7 is installed on the fixing frame 1 by hoisting. The fixing frame 1 is completely fixed in the launching device. The arc baffle is divided into a left arc baffle 9 and a right arc baffle 10. The transfer rod 5, the connecting rod 8, the rotating shaft 6, the left arc baffle 9 and the right arc baffle 10 together form a parallelogram mechanism and a lever mechanism.

[0039] The present application also provides a system for locking and releasing an aircraft, comprising the above-mentioned device for locking and releasing an aircraft.

[0040] Specifically, a specific embodiment is provided for this application below.

[0041] like Figure 1 As shown, the present invention is arranged in a launching device, including a fixing frame 1, a pyrotechnic bolt 2, a pyrotechnic bolt body 201, a pyrotechnic bolt screw 202, a pyrotechnic bolt mounting frame 3, a recovery box 4, a transfer rod 5, a rotating shaft 6, an aircraft 7, a connecting rod 8, a left arc baffle 9, a right arc baffle 10, and a locking nut 11. The fixing frame 1 is completely fixed in the launching device, the aircraft 7 is hoisted on the fixing frame 1, the pyrotechnic bolt mounting frame 3 is connected to the fixing frame 1 through fasteners, the pyrotechnic bolt 2 includes a pyrotechnic bolt body 201 and a pyrotechnic bolt screw 202, both of which are provided with threads, the pyrotechnic bolt 2 is fixedly connected to the pyrotechnic bolt mounting frame 3 through its own threads, the two are an integrated structure when locked, and the two become a separate structure after unlocking and releasing; there are 4 connecting rods 8 in total, and they are symmetrically distributed on the left and right sides of the fixing frame 1, the rotating shaft 6 passes through the middle through hole of the connecting rod 8 and is connected to the fixing frame 1; the left arc baffle 9 and the right arc baffle 10 are symmetrically distributed on the left and right sides of the fixing frame 1, and each is connected to the lower ends of the two connecting rods 8 on the left and right sides through two rotating shafts 6 respectively. The through holes are connected, the left arc baffle 9 and the right arc baffle 10 are arc structures and fit with the outer surface of the aircraft 7, and the rear ends of the left arc baffle 9 and the right arc baffle 10 are provided with bosses, and the inner surfaces of the bosses fit with the tail end face of the aircraft 7 when locked; the two sides of the transfer rod 5 are respectively connected with the through holes on the upper ends of the four connecting rods 8 through four rotating shafts 6, and the pyrotechnic bolt screw 202 passes through the through hole in the middle of the transfer rod 5; the locking nut 11 is connected with the thread on the pyrotechnic bolt screw 202 through a thread, and after the locking nut 11 is tightened, the locking nut 11 fits with the front end face of the transfer rod 5, and the rear end face of the transfer rod 5 fits with the front end face of the pyrotechnic bolt mounting frame 3; the recovery box 4 is fixedly connected to the transfer rod 5 through fasteners and covers the locking nut 11 and the pyrotechnic bolt screw 202 inside the recovery box 4.

[0042] like Figure 3As shown, the arrow in the figure indicates the heading. After the fixing frame 1 is fixed in the launching device, the aircraft 7 is loaded onto the fixing frame 1 and pushed forward to the position. The parallelogram mechanism composed of the transfer rod 5, the connecting rod 8, the rotating shaft 6, the left arc baffle 9, and the right arc baffle 10 is installed as a whole to the middle position of the fixing frame 1. After the rotating shaft 6 in the middle of each connecting rod 8 is installed in place, the device also constitutes a lever mechanism with a certain load-bearing capacity amplification, wherein the connecting rod 8 is symmetrically distributed on the left and right sides of the fixing frame 1 and does not occupy the internal space of the fixing frame 1. After the pyrotechnic bolt 2 is installed on the pyrotechnic bolt mounting frame 3, it is fixed to the fixing frame 1 as a whole by fasteners, and the locking release device is locked by the locking nut 11. After locking, the arc surface of the left arc baffle 9 and the right arc baffle 10 fits with the outer surface of the aircraft 7, and the inner surface of the boss at the rear end of the left arc baffle 9 and the right arc baffle 10 fits with the tail end face of the aircraft 7, so that the aircraft is effectively locked. By adjusting the ratio between the sizes L1 and L2 of the connecting rod 8, it is possible to increase the load-bearing capacity by a certain magnification factor, thereby achieving a small volume and high load-bearing effect.

[0043] like Figure 4 , Figure 5 As shown in the figure, the arrow indicates the heading. When the launch and separation of the aircraft 7 is implemented, the pyrotechnic bolt 2 is unlocked and released according to the system launch instruction, and the pyrotechnic bolt screw 202 separates with the locking nut 11 and hits the recovery box 4 at high speed. Under the explosion impact of the pyrotechnic bolt 2, the parallelogram mechanism composed of the transfer rod 5, the connecting rod 8, the rotating shaft 6, the left arc baffle 9, and the right arc baffle 10 begins to rotate counterclockwise and unfold, and the mechanism flips over to the right and upward, and the arc baffle 9 and the right arc baffle 10 effectively make way for the movement space of the aircraft 7, realizing the unlocking and release of the mechanism, and after unlocking and releasing, the pyrotechnic bolt screw 202 and the locking nut 11 fall into the recovery box 4, effectively preventing the excess objects from falling after unlocking, and the pyrotechnic bolt body 201 is still fixedly connected to the pyrotechnic bolt mounting frame 3. After the constraint is released, the aircraft 7 begins to be safely launched and separated.

[0044] The device for locking and releasing an aircraft involved in the present invention can effectively lock and release the aircraft 7. The device can be installed on both sides of the middle of the fixing frame 1, does not occupy the internal space of the fixing frame 1, and realizes the locking of the mechanism and a certain proportion of the load-bearing capacity through the lever mechanism, thereby improving the locking reliability of the aircraft 7 during storage and transportation. When the aircraft 7 is launched and separated, the device is unlocked and released by the pyrotechnic bolt 2, and the unlocking and releasing reliability is extremely high. The present invention has been verified in multiple transportation and launch test assessments, proving that the device meets the design and use requirements.

[0045] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0046] The above describes the specific embodiments of the present application. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the substantive content of the present application. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other.

Claims

1. A device for locking and releasing an aircraft, characterized in that: include: A fixing frame (1), a locking and releasing mechanism, a recovery box (4) and a parallelogram mechanism; The locking and releasing mechanism comprises: a pyrotechnic bolt (2), a pyrotechnic bolt mounting frame (3) and a locking nut (11); The parallelogram mechanism comprises: a transfer rod (5), a connecting rod (8), a rotating shaft (6) and an arc-shaped baffle; The pyrotechnic bolt mounting frame (3) is connected to the fixing frame (1) via a fastener, and the pyrotechnic bolt (2) is connected to the pyrotechnic bolt mounting frame (3) via a thread provided therewith; The pyrotechnic bolt (2) comprises a pyrotechnic bolt body (201) and a pyrotechnic bolt screw rod (202), and both the pyrotechnic bolt body (201) and the pyrotechnic bolt screw rod (202) are provided with threads; The transfer rod (5) is arranged on the top of the fixing frame (1), and the connecting rod (8) has three through holes in sequence from top to bottom. The connecting rod (8) is connected to the transfer rod (5) via a rotating shaft (6) matched with the upper through hole, the connecting rod (8) is connected to the fixing frame (1) via a rotating shaft (6) matched with the middle through hole, and the connecting rod (8) is connected to the arc baffle via a rotating shaft (6) matched with the lower through hole. The pyrotechnic bolt body (201) is threadedly connected to the pyrotechnic bolt mounting frame (3); the pyrotechnic bolt screw rod (202) passes through the middle of the adapter frame; the locking nut (11) cooperates with the pyrotechnic bolt screw rod (202) and is recovered and covered inside.

2. The device for locking and releasing an aircraft according to claim 1, characterized in that: The rear end of the arc-shaped baffle is provided with a boss, and when the locking nut (11) is tightened, the end face of one side of the transfer rod (5) fits with the end face of the pyrotechnic bolt mounting frame (3), and the end face of the other side of the transfer rod (5) fits with the end face of the locking nut (11), and the boss at the rear end of the arc-shaped baffle is fitted and locked with the tail end face of the aircraft (7).

3. The device for locking and releasing an aircraft according to claim 1, characterized in that: The pyrotechnic bolt screw (202) and the pyrotechnic bolt body (201) are detachable structures. The pyrotechnic bolt (2) causes the pyrotechnic bolt screw (202) to separate with the locking nut (11) and hit the recovery box (4) according to the system launch command. The parallelogram mechanism overturns under the impact and releases the restraint on the aircraft (7). The pyrotechnic bolt screw (202) and the locking nut (11) fall into the recovery box (4).

4. The device for locking and releasing an aircraft according to claim 1, characterized in that: The transfer rod (5) is an H-shaped three-dimensional symmetrical structure, and a total of four connecting rods (8) are provided. The connecting rods (8) are symmetrically distributed on the left and right sides of the fixing frame (1) with the fixing frame (1) as the center.

5. The device for locking and releasing an aircraft according to claim 2, characterized in that: The distance between the upper through hole and the middle through hole, and the distance between the middle through hole and the lower through hole of the connecting rod (8) can be flexibly adjusted.

6. The device for locking and releasing an aircraft according to claim 1, characterized in that: The aircraft (7) is installed on the fixing frame (1) in a hoisting manner.

7. The device for locking and releasing an aircraft according to claim 1, characterized in that: The fixing frame (1) is completely fixed in the launching device.

8. The device for locking and releasing an aircraft according to claim 1, characterized in that: The arc-shaped baffle is divided into a left arc-shaped baffle (9) and a right arc-shaped baffle (10).

9. The device for locking and releasing an aircraft according to claim 1, characterized in that: The transfer rod (5), the connecting rod (8), the rotating shaft (6), the left arc-shaped baffle plate (9) and the right arc-shaped baffle plate (10) together form a parallelogram mechanism and a lever mechanism.

10. A system for locking and releasing an aircraft, characterized in that: The invention comprises a device for locking and releasing an aircraft as described in any one of claims 1 to 9.

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