Devices and systems for locking and releasing aircraft

Abstract

This application provides a device and system for locking and releasing an aircraft, including: a fixed frame, a locking and releasing mechanism, a recovery box, and a parallelogram mechanism; the locking and releasing mechanism includes: a pyrotechnic bolt, a pyrotechnic bolt mounting bracket, and a locking nut; the parallelogram mechanism includes: an adapter rod, a connecting rod, a rotating shaft, and an arc-shaped baffle; the pyrotechnic bolt mounting bracket is connected to the fixed frame via fasteners, and the pyrotechnic bolt is connected to the pyrotechnic bolt mounting bracket via its own thread; the pyrotechnic bolt includes a pyrotechnic bolt body and a pyrotechnic bolt thread, both of which are threaded; the adapter rod is located at the top of the fixed frame, and the connecting rod has three through holes sequentially opened from top to bottom, with the connecting rod connected to the adapter rod via a rotating shaft that mates with the upper through hole. This application has a simple structure and effectively solves the design problem of locking and releasing devices under constrained installation positions of unmanned aerial vehicles.

Description

Technical Field

[0001] This application relates to the field of spacecraft structural design, and more specifically, to a device and system for locking and releasing a spacecraft. Background Technology

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

[0003] The prior art, patent number CN111426242B, discloses a fracture-resistant, non-detachable axial locking and release assembly for unmanned aerial vehicles (UAVs). It includes a support pin, a mounting frame, and a translational rod. The translational rod is rotatably mounted on a swing arm seat via a first and a second swing arm, respectively, with a connecting plate at the end near the second swing arm. The mounting frame is mounted on the second swing arm or the swing arm seat. The support pin fixes the connecting plate to the mounting frame, allowing for both locked and unlocked states. In the locked state, the translational rod is not allowed to move relative to the swing arm seat. When the UAV is launched, the launch thrust breaks the support pin, unlocking the assembly. At this time, both ends of the support pin remain on the mounting frame and the connecting plate, respectively. This invention effectively solves the problem of high-speed debris ejected during UAV launch, overcoming the hazards to surrounding products and personnel caused by debris, and significantly improving launch safety. However, it is located at the tail of the UAV and is fixed to the rear end of the mounting frame, thus providing a locking and release function for the UAV. This makes it unsuitable for structures requiring installation in the middle of the mounting frame.

[0004] The prior art, patent number CN113237395B, discloses a missile-locking 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. The positioning seat is detachably mounted on the support frame; the support arm mechanism is rotatably mounted on the support frame, with one end of the support arm mechanism connected to one end of the elastic mechanism for locking the missile, and the other end of the elastic mechanism mounted on the positioning seat. The missile has a locked state and a launch state. When the locking mechanism is broken, one end of the support arm mechanism rotates around an axis under the drive of the elastic mechanism, thereby causing the other end of the support arm mechanism to drive the other end of the locking mechanism to move to a second position, thus putting the missile into the launch state. This invention can effectively achieve axial fixation and rapid unlocking of the missile and has an unlocking signal feedback function. It has advantages such as high reliability and large load-bearing capacity. It is located in the middle of the aircraft and is also installed in the middle area of ​​the fixed frame to realize the locking and releasing function of the aircraft. However, it occupies the internal space of the fixed frame, reducing the space utilization efficiency of the fixed frame itself. None of the aforementioned technologies meet the structural requirement of installing the locking and releasing device in the middle of the fixed frame without occupying the internal space of the fixed frame. Therefore, developing a new type of locking and releasing device for unmanned aerial vehicles is of great significance. Summary of the Invention

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

[0006] According to this application, a device and system for locking and releasing an aircraft includes: a mounting frame, a locking and releasing mechanism, a recovery box, and a parallelogram mechanism.

[0007] The locking and releasing mechanism includes: a fire bolt, a fire bolt mounting bracket, and a locking nut;

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

[0009] The pyrotechnic bolt mounting bracket is connected to the fixing bracket by fasteners, and the pyrotechnic bolt is connected to the pyrotechnic bolt mounting bracket by its own thread.

[0010] The pyrotechnic bolt includes a pyrotechnic bolt body and a pyrotechnic bolt shank, both of which are threaded.

[0011] The adapter rod is located on the top of the fixed frame. The connecting rod has three through holes from top to bottom. The connecting rod is connected to the adapter rod through a rotating shaft that mates with the upper through hole. The connecting rod is connected to the fixed frame through a rotating shaft that mates with the middle through hole. The connecting rod is connected to the arc-shaped baffle through a rotating shaft that mates with the lower through hole.

[0012] The pyrotechnic bolt body is threadedly connected to the pyrotechnic bolt mounting bracket, the pyrotechnic bolt shank passes through the middle of the adapter bracket, and the locking nut engages with the pyrotechnic bolt shank and is enclosed inside by a recyclable cover.

[0013] Preferably, the arc-shaped baffle has a boss at its rear end. When the locking nut is tightened, one end face of the adapter rod is in contact with the end face of the pyrotechnic bolt mounting bracket, and the other end face of the adapter rod is in contact with the end face of the locking nut. The boss at the rear end of the arc-shaped baffle is in contact with and locked to the tail end face of the aircraft.

[0014] Preferably, the pyrotechnic bolt screw and the pyrotechnic bolt body are separable structures. According to the system launch command, the pyrotechnic bolt screw, along with the locking nut, separates and impacts the recovery box. The parallelogram mechanism overturns upon impact, thereby releasing the restraint on the aircraft. The pyrotechnic bolt screw and the locking nut fall into the recovery box.

[0015] Preferably, the adapter rod has an H-shaped three-dimensional symmetrical structure, and there are four connecting rods in total, which 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 fixed frame by means of hoisting.

[0018] Preferably, the mounting bracket is completely fixed inside 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 adapter rod, connecting rod, rotating shaft, left arc-shaped baffle, and right arc-shaped baffle together form a parallelogram mechanism and a lever mechanism.

[0021] This application also provides a system for realizing aircraft locking and releasing, including the above-described means 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 locking and releasing device under the condition of constrained installation position of unmanned aerial vehicle by setting up a parallelogram mechanism, which is suitable for the structural requirements of installation in the middle of the fixed frame.

[0024] 2. This application features a multi-functional integrated design, a simple structure, and is easy to apply in engineering. It does not occupy the internal space of the mounting frame and improves the space utilization efficiency of the mounting frame itself. Attached Figure Description

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

[0026] Figure 1 This application mainly illustrates the overall structure of the device used for locking and releasing aircraft;

[0027] Figure 2 This application mainly illustrates the side view of the device for locking and releasing an aircraft.

[0028] Figure 3 This application primarily illustrates a cross-sectional view of the locking mechanism on the AA side for use in locking and releasing aircraft.

[0029] Figure 4 This application mainly illustrates the release structure of a device for locking and releasing an aircraft;

[0030] Figure 5 This application primarily illustrates a cross-sectional view of the AA-side release mechanism for an aircraft locking release device;

[0031] Figure 6 This application primarily illustrates a schematic diagram of a linkage structure for locking and releasing devices used in aircraft.

[0032] The following components are shown in the diagram: 1. Fixing frame; 2. Pyrotechnic bolt; 201. Pyrotechnic bolt body; 202. Pyrotechnic bolt thread; 3. Pyrotechnic bolt mounting bracket; 4. Recycling box; 5. Adapter rod; 6. Rotating shaft; 7. Aircraft; 8. Connecting rod; 9. Left arc-shaped baffle; 10. Right arc-shaped baffle; 11. Locking nut. Detailed Implementation

[0033] The present application will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These all fall within the protection scope of the present application.

[0034] The locking and releasing device and system for the aircraft 7 provided in this application include: a fixed 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 bracket 3, and a locking nut 11; the parallelogram mechanism includes: an adapter rod 5, a connecting rod 8, a rotating shaft 6, and an arc-shaped baffle; the pyrotechnic bolt mounting bracket 3 is connected to the fixed frame 1 by fasteners, and the pyrotechnic bolt 2 is connected to the pyrotechnic bolt mounting bracket 3 by its own thread; the pyrotechnic bolt 2 includes a pyrotechnic bolt body 201 and a pyrotechnic bolt screw 202, both of which are threaded;

[0035] The adapter rod 5 is set on the top of the fixed frame 1. The connecting rod 8 has three through holes from top to bottom. The connecting rod 8 is connected to the adapter rod 5 through the rotating shaft 6 that cooperates with the upper through hole. The connecting rod 8 is connected to the fixed frame 1 through the rotating shaft 6 that cooperates with the middle through hole. The connecting rod 8 is connected to the arc-shaped baffle through the rotating shaft 6 that cooperates with the lower through hole.

[0036] The pyrotechnic bolt body 201 is threadedly connected to the pyrotechnic bolt mounting bracket 3. The pyrotechnic bolt shank 202 passes through the middle of the adapter bracket. The locking nut 11 engages with the pyrotechnic bolt shank 202 and is enclosed by the retraction cover. A boss is provided at the rear end of the arc-shaped baffle. When the locking nut 11 is tightened, one end face of the adapter rod 5 is in contact with the end face of the pyrotechnic bolt mounting bracket 3, and the other end face of the adapter rod 5 is in contact with the end face of the locking nut 11. The boss at the rear end of the arc-shaped baffle is in contact with and locked to the tail end face of the aircraft 7.

[0037] The pyrotechnic bolt 202 and the pyrotechnic bolt body 201 are separable structures. According to the system's launch command, the pyrotechnic bolt 202, along with the locking nut 11, separates and impacts the recovery box 4. The parallelogram mechanism overturns upon impact, releasing the spacecraft 7. The pyrotechnic bolt 202 and locking nut 11 fall into the recovery box 4. The adapter rod 5 has an H-shaped, three-dimensional symmetrical structure. Four connecting rods 8 are provided, symmetrically distributed on the left and right sides of the fixed frame 1.

[0038] The distance between the upper and middle through holes of connecting rod 8, and the distance between the middle and lower through holes, can be flexibly adjusted. The aircraft 7 is mounted on the fixed frame 1 using a hoisting method. The fixed frame 1 is completely fixed inside the launching device. The arc-shaped baffle is divided into a left arc-shaped baffle 9 and a right arc-shaped baffle 10. The adapter rod 5, connecting rod 8, rotating shaft 6, left arc-shaped baffle 9, and right arc-shaped baffle 10 together form a parallelogram mechanism and a lever mechanism.

[0039] This application also provides a system for locking and releasing an aircraft, comprising the aforementioned locking and releasing device for an aircraft.

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

[0041] like Figure 1 As shown, the present invention is installed inside the launching device and includes a fixing frame 1, a pyrotechnic bolt 2, a pyrotechnic bolt body 201, a pyrotechnic bolt screw 202, a pyrotechnic bolt mounting bracket 3, a recovery box 4, an adapter rod 5, a rotating shaft 6, a spacecraft 7, a connecting rod 8, a left arc-shaped baffle 9, a right arc-shaped baffle 10, and a locking nut 11. The mounting bracket 1 is completely fixed inside the launching device. The aircraft 7 is hoisted onto the mounting bracket 1. The pyrotechnic bolt mounting bracket 3 is connected to the mounting bracket 1 via fasteners. The pyrotechnic bolt 2 includes a pyrotechnic bolt body 201 and a pyrotechnic bolt thread 202. Both the pyrotechnic bolt body 201 and the pyrotechnic bolt thread 202 are threaded. The pyrotechnic bolt 2 is fixed to the pyrotechnic bolt mounting bracket 3 via its own threads. When locked, the two are a single structure. When unlocked, they become separate structures. There are four connecting rods 8, which are symmetrically distributed on the left and right sides of the mounting bracket 1. The rotating shaft 6 passes through the through hole in the middle of the connecting rod 8 and is connected to the mounting bracket 1. The left arc-shaped baffle 9 and the right arc-shaped baffle 10 are symmetrically distributed on the left and right sides of the mounting bracket 1, and each is connected to the lower end of the two connecting rods 8 on the left and right sides respectively via two rotating shafts 6. The left and right arc-shaped baffles 9 and 10 are arc-shaped and fit against the outer surface of the aircraft 7. The rear ends of the left and right arc-shaped baffles 9 and 10 are provided with bosses. When locked, the inner surface of the bosses fits against the tail end face of the aircraft 7. The two sides of the adapter rod 5 are connected to the upper through holes of the four connecting rods 8 through four rotating shafts 6 respectively, and the pyrotechnic bolt 202 passes through the through hole in the middle of the adapter rod 5. The locking nut 11 is connected to the thread on the pyrotechnic bolt 202 through the thread. After the locking nut 11 is tightened, the locking nut 11 fits against the front end face of the adapter rod 5, and the rear end face of the adapter rod 5 fits against the front end face of the pyrotechnic bolt mounting bracket 3. The recovery box 4 is fixed to the adapter rod 5 through fasteners and covers the locking nut 11 and the pyrotechnic bolt 202 inside the recovery box 4.

[0042] like Figure 3As shown in the diagram, the arrows indicate the heading. After fixing the mounting frame 1 inside the launching device, the aircraft 7 is loaded onto the mounting frame 1 and pushed forward into place. The parallelogram mechanism composed of the adapter rod 5, connecting rod 8, rotating shaft 6, left arc-shaped baffle 9, and right arc-shaped baffle 10 is installed as a whole at the middle position of the mounting 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. The connecting rods 8 are symmetrically distributed on the left and right sides of the mounting frame 1 and do not occupy the internal space of the mounting frame 1. After the pyrotechnic bolt 2 is installed onto the pyrotechnic bolt mounting bracket 3, it is fixed to the mounting frame 1 as a whole by fasteners. The locking release device is locked by the locking nut 11. After locking, the arc surfaces of the left arc-shaped baffle 9 and the right arc-shaped baffle 10 are in contact with the outer surface of the aircraft 7, and the inner surface of the boss at the rear end of the left arc-shaped baffle 9 and the right arc-shaped baffle 10 is in contact with the tail end face of the aircraft 7, thus achieving effective locking of the aircraft. By adjusting the ratio between the dimensions L1 and L2 of the connecting rod 8, a certain amplification factor can be used to improve the load-bearing capacity, achieving a high load-bearing capacity in a small volume.

[0043] like Figure 4 , Figure 5 As shown in the diagram, the arrows indicate the heading. When the spacecraft 7 is launched and separated, according to the system launch command, the pyrotechnic bolt 2 is unlocked and released. The pyrotechnic bolt screw 202, along with the locking nut 11, separates and impacts the recovery box 4 at high speed. Under the explosive impact of the pyrotechnic bolt 2, the parallelogram mechanism composed of the adapter rod 5, connecting rod 8, rotating shaft 6, left arc-shaped baffle 9, and right arc-shaped baffle 10 begins to rotate and unfold counterclockwise. The mechanism flips to the right and upward. The arc-shaped baffle 9 and the right arc-shaped baffle 10 effectively open up the movement space of the spacecraft 7, realizing the unlocking and release of the mechanism. After unlocking and releasing, the pyrotechnic bolt screw 202 and the locking nut 11 fall into the recovery box 4, effectively preventing excess materials from falling after unlocking. The pyrotechnic bolt body 201 is still fixed on the pyrotechnic bolt mounting bracket 3. After the constraint is released, the spacecraft 7 begins to launch and separate safely.

[0044] The present invention relates to a device for locking and releasing an aircraft 7, which can effectively lock and release the aircraft 7. This device can be installed on both sides of the middle of the mounting frame 1 without occupying the internal space of the mounting frame 1. It achieves locking and a certain proportion of load-bearing capacity enhancement through a lever mechanism, improving the locking reliability of the aircraft 7 during storage and transportation. During the launch and separation of the aircraft 7, the device is unlocked and released by the pyrotechnic bolts 2, with extremely high unlocking and release reliability. The invention has been verified in multiple transportation and launch tests, confirming that the device meets the design and usage requirements.

[0045] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0046] The specific embodiments of this application have been described above. It should be understood that this application is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the substantive content of this application. Unless otherwise specified, the embodiments and features described in the embodiments of this application can be arbitrarily combined with each other.

Claims

1. A device for locking and releasing an aircraft, characterized in that, include: The fixture (1), locking and releasing mechanism, recycling box (4), and parallelogram mechanism; The locking and releasing mechanism includes: a fire bolt (2), a fire bolt mounting bracket (3), and a locking nut (11); The parallelogram mechanism includes: a transition rod (5), a connecting rod (8), a rotating shaft (6), and an arc-shaped baffle; The pyrotechnic bolt mounting bracket (3) is connected to the fixing bracket (1) by fasteners, and the pyrotechnic bolt (2) is connected to the pyrotechnic bolt mounting bracket (3) by its own thread; The fire bolt (2) includes a fire bolt body (201) and a fire bolt shank (202), both of which are threaded. The adapter rod (5) is located on the top of the fixed frame (1). The connecting rod (8) has three through holes from top to bottom. The connecting rod (8) is connected to the adapter rod (5) through a rotating shaft (6) that cooperates with the upper through hole. The connecting rod (8) is connected to the fixed frame (1) through a rotating shaft (6) that cooperates with the middle through hole. The connecting rod (8) is connected to the arc-shaped baffle through a rotating shaft (6) that cooperates with the lower through hole. The pyrotechnic bolt body (201) is threadedly connected to the pyrotechnic bolt mounting bracket (3), the pyrotechnic bolt shank (202) passes through the middle of the adapter rod, and the locking nut (11) cooperates with the pyrotechnic bolt shank (202) and is covered inside by the recycling box.

2. The device for locking and releasing an aircraft as described in claim 1, characterized in that, The arc-shaped baffle is provided with a boss at the rear end. When the locking nut (11) is tightened, one end face of the adapter rod (5) is in contact with the end face of the pyrotechnic bolt mounting bracket (3), and the other end face of the adapter rod (5) is in contact with the end face of the locking nut (11). The boss at the rear end of the arc-shaped baffle is in contact with and locked to the tail end face of the aircraft (7).

3. The device for locking and releasing an aircraft as described in claim 1, characterized in that, The pyrotechnic bolt screw (202) and the pyrotechnic bolt body (201) are separable structures. According to the system launch command, the pyrotechnic bolt (2) causes the pyrotechnic bolt screw (202) to separate with the locking nut (11) and impact the recovery box (4). The parallelogram mechanism overturns under impact, thereby releasing the constraint 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 as described in claim 1, characterized in that, The adapter rod (5) has an H-shaped three-dimensional symmetrical structure. There are four connecting rods (8) in total. The connecting rods (8) are symmetrically distributed on the left and right sides of the fixed frame (1) with the fixed frame (1) as the center.

5. The device for locking and releasing an aircraft as described in 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 as claimed in claim 1, characterized in that, The aircraft (7) is installed on the fixed frame (1) by means of hoisting.

7. The device for locking and releasing an aircraft as described in claim 1, characterized in that, The mounting bracket (1) is completely fixed inside the launching device.

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

10. A system for locking and releasing an aircraft, characterized in that, It includes the means for locking and releasing an aircraft as described in any one of claims 1-9.

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