Aircraft locking device

Abstract

The present invention discloses an aircraft locking device, which belongs to the field of aircraft locking technology. The device includes a base and two limiting fastening frames. The base is provided with a through hole A and a notch, and the notch is connected to the through hole A. An eccentric locking mechanism is provided in the notch. The two limiting fastening frames are symmetrically arranged on the inner side of the through hole A and are movably connected to the base respectively. By utilizing the characteristic of the eccentric wheel to automatically find a stable center of gravity, the aircraft is automatically locked and unlocked, thereby improving the reliability of the locking device. The locking device does not need to be driven by a related driving mechanism, which simplifies the structure of the locking device and reduces the external dimensions of the locking device. It can be installed in a limited space, which helps to increase the number of locking devices installed on the launch device and improve the number of aircraft carrying capacity and application efficiency of the launch device.

Description

Technical Field

[0001] The invention relates to an aircraft locking device and belongs to the technical field of aircraft locking. Background Art

[0002] In recent years, with the advancement of science and technology, the demand for launchers for cylindrical aircraft has become increasingly demanding both domestically and internationally. However, the locking mechanisms used to secure the aircraft on existing launchers suffer from complex structures and large dimensions, significantly reducing the number of aircraft they can carry and significantly impacting their effectiveness.

[0003] Chinese patent document with publication number CN207551735U discloses an eccentric wheel locking and lifting device for plate lifting. The device can be used to lock and lift the plate, but it cannot achieve locking of cylindrical aircraft.

[0004] Therefore, how to simplify the locking device structure and reduce its external dimensions to increase the aircraft carrying capacity and application efficiency of the launch device is a technical problem that needs to be urgently solved by those skilled in the art. Summary of the Invention

[0005] In order to solve the above technical problems, the present invention provides an aircraft locking device.

[0006] The present invention is achieved through the following technical solutions:

[0007] An aircraft locking device includes a base and two limiting fastening frames. The base is provided with a through hole A and a notch, and the notch is connected to the through hole A. An eccentric locking mechanism is provided in the notch. The two limiting fastening frames are symmetrically arranged on the inner side of the through hole A and are respectively movably connected to the base.

[0008] The upper and lower parts of the base are both provided with T-shaped sliding grooves along the axial direction of the through hole A, and the two limiting fastening frames are slidably connected to the T-shaped sliding grooves of the upper and lower parts of the base in a one-to-one correspondence.

[0009] Two extended slides are provided on one side of the base, one end of one extended slide is connected to the T-shaped slide groove on the upper part of the base, and one end of the other extended slide is connected to the T-shaped slide groove on the lower part of the base.

[0010] The position limiting fastening frame comprises an arc-shaped plate, a T-shaped sliding block is provided on the outer circumferential surface of the arc-shaped plate, and a clamping block is provided on the outer circumferential surface of the end portion of the arc-shaped plate.

[0011] A rubber pad is provided on the inner circular surface of the arc-shaped plate, and both end surfaces of the clamping block are arc surfaces.

[0012] Two notches are evenly distributed on the outside of the through hole A on the base, and an eccentric locking mechanism is provided in each of the two notches.

[0013] The eccentric locking mechanism includes a support frame and an eccentric wheel. The eccentric wheel is rotatably connected to the support frame through a rotating shaft. The eccentric wheel is provided with a counterweight block and a limiting groove arranged along the circumference, and one end of the limiting groove is connected to one end of the counterweight block. The middle part of the support frame is located on the inner side of the limiting groove, and a gear lever is provided on the support frame below the rotating shaft.

[0014] The counterweight block is in an arc shape, and the outer circumferential surface of the counterweight block coincides with the outer circumferential surface of the eccentric wheel, and the support frame is in an I-shape.

[0015] The end surfaces of both ends of the support frame are located in a horizontal position, and when the counterweight block contacts the support frame, the center of gravity of the eccentric wheel is located on the left side of the rotating shaft, and the eccentric wheel rotates counterclockwise to contact the gear lever.

[0016] The end faces of both ends of the support frame are in a vertical position, and when the eccentric wheel contacts the shift lever, the center of gravity of the eccentric wheel is located on the right side of the rotating shaft, and the eccentric wheel rotates clockwise until the counterweight block contacts the support frame.

[0017] The beneficial effects of the present invention are:

[0018] 1. The eccentric wheel automatically finds the stable center of gravity to achieve automatic locking and unlocking of the aircraft, improving the reliability of the locking device.

[0019] 2. The locking device does not need to be driven by a related driving mechanism, which simplifies the structure of the locking device and reduces the external dimensions of the locking device. It can be installed in a limited space, which helps to increase the number of locking devices installed on the launch device and improve the aircraft carrying capacity and application efficiency of the launch device. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the main structure of the present invention when the base is in a vertical position;

[0021] Figure 2 is an assembly diagram of the arc-shaped plate and the eccentric locking mechanism of the present invention when the base is in a vertical position;

[0022] Figure 3 It is a schematic diagram of the structure of the present invention from a top view when the base is in a horizontal position;

[0023] Figure 4 It is an assembly diagram of the arc-shaped plate and the eccentric locking mechanism of the present invention when the base is in a horizontal position;

[0024] Figure 5 It is a schematic diagram of the assembly structure of the base and the limiting fastening frame of the present invention;

[0025] Figure 6 It is a schematic diagram of the assembly structure of the base, eccentric locking mechanism and extended slideway of the present invention.

[0026] In the figure: 1-base, 10-slot, 2-limiting fastening frame, 20-arc plate, 21-T-shaped slider, 22-block, 3-eccentric locking mechanism, 30-support frame, 31-eccentric wheel, 310-limiting groove, 32-rotating shaft, 33-gear lever, 34-counterweight, 4-extended slide. DETAILED DESCRIPTION

[0027] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0028] like Figures 1 to 6 As shown, the present invention discloses a vehicle locking device comprising a base 1 and two position-limiting fastening frames 2. The base 1 is provided with a through-hole A and a notch 10, which communicates with the through-hole A. An eccentric locking mechanism 3 is mounted within the notch 10. The two position-limiting fastening frames 2 are symmetrically arranged inside the through-hole A and are slidably connected to the base 1. During use, the two position-limiting fastening frames 2 hold the cylindrical vehicle. One end of the T-shaped slot on the base 1 constrains the vehicle's backward movement. The eccentric locking mechanism 3 locks the two position-limiting fastening frames 2, constraining the vehicle's forward movement and thereby locking the vehicle. The locking device has a simple structure. The eccentric locking mechanism 3 automatically locates a stable center of gravity and locks the position-limiting fastening frames 2, eliminating the need for a drive mechanism. This reduces the overall dimensions of the locking device, facilitating the installation of more locking devices on a launcher, and improving the launcher's aircraft carrying capacity and operational efficiency.

[0029] The upper and lower portions of the base 1 are each provided with a T-shaped slot along the axial direction of the through hole A, and two position-limiting fastening frames 2 are slidably connected to the T-shaped slots on the upper and lower portions of the base 1, one for each other. When the position-limiting fastening frames 2 slide backward along the T-shaped slots and abut against the rear end of the T-shaped slots, the position-limiting fastening frames 2 cannot slide further backward, thereby constraining the position-limiting fastening frames 2 in their backward movement through the rear end of the T-shaped slots, thereby constraining the aircraft inside the position-limiting fastening frames 2 in their backward movement.

[0030] Two extended slides 4 are mounted on one side of the base 1. One end of one extended slide 4 is connected to the T-shaped slot on the upper portion of the base 1, while the other end of the extended slide 4 is connected to the T-shaped slot on the lower portion of the base 1. By lengthening the T-shaped slot on the base 1 by extending the slides 4, the two limiting fastening frames 2 can move with the aircraft for a certain distance during launch, thereby improving launch stability.

[0031] The position-limiting fastening frame 2 includes an arc-shaped plate 20, with a T-shaped slider 21 disposed on the outer circumference of the arc-shaped plate 20, and a clamping block 22 mounted on the outer circumference of the end of the arc-shaped plate 20. Both the upper and lower arc-shaped plates 20 are slidably connected to the T-shaped chute on the base 1 via the T-shaped slider 21. A mounting gap exists between the T-shaped slider 21 and the T-shaped chute. When the base 1 is in a vertical position, the lower arc-shaped plate 20 contacts the base 1, while the upper arc-shaped plate 20 does not, leaving a gap between them. This gap provides space for inserting the cylindrical aircraft into the inner sides of the upper and lower arc-shaped plates 20.

[0032] A rubber pad is mounted on the inner surface of the arc-shaped plate 20, and both end faces of the clamping block 22 are arc-shaped surfaces. The rubber pad protects the outer surface of the aircraft, preventing the arc-shaped plate 20 from scratching the aircraft. It also increases friction between the arc-shaped plate 20 and the aircraft, preventing relative movement between the two.

[0033] Two notches 10 are evenly distributed on the outside of the through hole A on the base 1 , and an eccentric locking mechanism 3 is installed in each of the two notches 10 . Figure 1 、 Figure 3 and Figure 6 Only one eccentric locking mechanism 3 is drawn in the figure.

[0034] The eccentric locking mechanism 3 includes a support frame 30 and an eccentric wheel 31. The eccentric wheel 31 is rotatably connected to the support frame 30 through a rotating shaft 32. The eccentric wheel 31 is provided with a counterweight block 34 and a limiting groove 310 opened along the circumference, and one end of the limiting groove 310 is connected to one end of the counterweight block 34. The middle part of the support frame 30 is located on the inner side of the limiting groove 310, and a gear lever 33 is installed on the support frame 30 below the rotating shaft 32.

[0035] The counterweight 34 is in an arc shape, and the outer surface of the counterweight 34 coincides with the outer surface of the eccentric wheel 31. The support frame 30 is in an I-shape. When in use, the end surfaces of the clamping block 22 are arc surfaces, and the inner surface of the counterweight 34 is also arc surface, so as to avoid interference between the clamping block 22 and the counterweight 34 when the eccentric wheel 31 rotates.

[0036] The end surfaces of the support frame 30 are in a horizontal position, and when the counterweight 34 contacts the support frame 30, the center of gravity of the eccentric wheel 31 is located on the left side of the rotating shaft 32, and the eccentric wheel 31 rotates counterclockwise and contacts the gear lever 33. Figure 1 and Figure 2 As shown, when the eccentric wheel 31 rotates counterclockwise and contacts the shift lever 33, the counterweight block 34 on the eccentric wheel 31 is opposite to the block 22 on the position-limiting fastening frame 2, constraining the position-limiting fastening frame 2 from moving forward, that is, constraining the aircraft inside the position-limiting fastening frame 2 from moving forward.

[0037] The end faces of the support frame 30 are in a vertical position, and when the eccentric wheel 31 contacts the gear lever 33, the center of gravity of the eccentric wheel 31 is located on the right side of the rotating shaft 32, and the eccentric wheel 31 rotates clockwise until the counterweight block 34 contacts the support frame 30. Figure 3 and Figure 4 As shown, when the counterweight 34 contacts the support frame 30, the counterweight 34 on the eccentric wheel 31 is misaligned with the block 22 on the limiting fastening frame 2, thereby releasing the constraint on the forward movement of the limiting fastening frame 2, that is, releasing the constraint on the forward movement of the aircraft, and the launching device can launch the aircraft.

[0038] The aircraft locking device of the present invention works as follows:

[0039] Move the two limiting fastening frames 2 to the end of the extended slide 4 away from the base 1, and install the aircraft on the inner side of the two limiting fastening frames 2. The aircraft can be held tightly by the two limiting fastening frames 2, and then the aircraft and the two limiting fastening frames 2 can be moved backward together. When the limiting fastening frames 2 come into contact with the rear end of the T-shaped slide groove on the base 1, the limiting fastening frames 2 cannot move further backward, thereby constraining the limiting fastening frames 2 and the aircraft inside the limiting fastening frames 2 to move backward through the rear end of the T-shaped slide groove.

[0040] like Figure 1 and Figure 2 As shown, after the position-limiting fastening frame 2 moves into the base 1, the eccentric wheel 31 automatically seeks a stable center of gravity and rotates counterclockwise around the rotating shaft 32 to a position in contact with the shift lever 33. At this time, the counterweight block 34 on the eccentric wheel 31 is directly opposite to the block 22 on the position-limiting fastening frame 2, constraining the position-limiting fastening frame 2 from moving forward, that is, constraining the aircraft inside the position-limiting fastening frame 2 from moving forward.

[0041] like Figure 3 and Figure 4 As shown, when the locking device is erected about 90 degrees with the aircraft, the eccentric wheel 31 automatically finds a stable center of gravity again and rotates clockwise around the rotating shaft 32 to the position where the counterweight block 34 contacts the support frame 30. At this time, the counterweight block 34 on the eccentric wheel 31 is misaligned with the block 22 on the limiting fastening frame 2, releasing the constraint on the forward movement of the limiting fastening frame 2, that is, releasing the constraint on the forward movement of the aircraft, and the launching device can launch the aircraft.

[0042] The aircraft locking device provided by the present invention has the following beneficial effects:

[0043] 1. The eccentric wheel 31 automatically finds the stable center of gravity, so that the aircraft can be automatically locked and unlocked, thereby improving the reliability of the locking device.

[0044] 2. The locking device does not need to be driven by a related driving mechanism, which simplifies the structure of the locking device and reduces the external dimensions of the locking device. It can be installed in a limited space, which helps to increase the number of locking devices installed on the launch device and improve the aircraft carrying capacity and application efficiency of the launch device.

Claims

1. An aircraft locking device, characterized in that: It comprises a base (1) and two position-limiting fastening frames (2), wherein the base (1) is provided with a through hole A and a notch (10), and the notch (10) is communicated with the through hole A, an eccentric locking mechanism (3) is provided in the notch (10), and the two position-limiting fastening frames (2) are symmetrically arranged on the inner side of the through hole A and are respectively movably connected to the base (1); The upper and lower parts of the base (1) are both provided with T-shaped sliding grooves along the axial direction of the through hole A, and the two limiting fastening frames (2) are slidably connected to the T-shaped sliding grooves of the upper and lower parts of the base (1) in a one-to-one correspondence; Two extended slideways (4) are provided on one side of the base (1), one end of one extended slideway (4) is connected to the T-shaped slideway at the top of the base (1), and one end of the other extended slideway (4) is connected to the T-shaped slideway at the bottom of the base (1); The eccentric locking mechanism (3) comprises a support frame (30) and an eccentric wheel (31), the eccentric wheel (31) being rotatably connected to the support frame (30) via a rotating shaft (32), a counterweight (34) and a limiting groove (310) provided along a circumferential direction on the eccentric wheel (31), one end of the limiting groove (310) being connected to one end of the counterweight (34), a middle portion of the support frame (30) being located inside the limiting groove (310), and a shift lever (33) being provided on the support frame (30) below the rotating shaft (32); The end surfaces of both ends of the support frame (30) are located in a horizontal position, and when the counterweight (34) contacts the support frame (30), the center of gravity of the eccentric wheel (31) is located on the left side of the rotating shaft (32), and the eccentric wheel (31) rotates counterclockwise to contact the gear lever (33); The end surfaces of both ends of the support frame (30) are located in a vertical position, and when the eccentric wheel (31) contacts the shift lever (33), the center of gravity of the eccentric wheel (31) is located on the right side of the rotating shaft (32), and the eccentric wheel (31) rotates clockwise until the counterweight (34) contacts the support frame (30).

2. The aircraft locking device according to claim 1, characterized in that: The position limiting fastening frame (2) comprises an arc-shaped plate (20), a T-shaped slider (21) is provided on the outer circumferential surface of the arc-shaped plate (20), and a clamping block (22) is provided on the outer circumferential surface of the end of the arc-shaped plate (20).

3. The aircraft locking device according to claim 2, wherein: A rubber pad is provided on the inner circular surface of the arc-shaped plate (20), and both end surfaces of the clamping block (22) are arc surfaces.

4. The aircraft locking device according to claim 1, wherein: Two notches (10) are arranged on the base (1) on the outside of the through hole A, and an eccentric locking mechanism (3) is arranged in each of the two notches (10).

5. The aircraft locking device according to claim 1, wherein: The counterweight (34) is in an arc shape, and the outer circumferential surface of the counterweight (34) coincides with the outer circumferential surface of the eccentric wheel (31); the support frame (30) is in an I-shape.

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