Anti-falling force bearing lock for aircraft covering cap

Abstract

The invention discloses an anti-falling force bearing lock for an aircraft covering cap, and relates to the technical field of anti-falling force bearing locks for aircraft covering caps, the anti-falling force bearing lock comprises a fixing box, one side of the top end of the fixing box is fixedly connected with a motor box, the interior of the motor box is fixedly connected with a servo motor, and the output end of the servo motor is in spline connection with a transmission rod; a fixing block is fixedly connected to one end of the transmission rod, a protection box is fixedly connected to the interior of the fixing block, a storage battery is fixedly connected to the interior of the protection box, a transmission line is fixedly connected to the top end of the storage battery, and a damping expansion piece is fixedly connected to one end of the front face of the fixing block; one end of the damping expansion piece is fixedly connected with a connecting block; through the arrangement of the servo motor, the transmission rod and the fixing block, when a worker operates the device to use the device, the device can be effectively, rapidly and automatically closed, and therefore the problems that the device is loosened in closing due to manual closing and the like are reduced.

Description

Technical Field

[0001] The invention relates to the technical field of anti-detachment load-bearing locks for aircraft hatches, and in particular to an anti-detachment load-bearing lock for aircraft hatches. Background Art

[0002] The anti-drop load-bearing lock of the aircraft door cover is a safety device used to ensure that the aircraft fuselage door cover will not accidentally open or fall off during flight. This lock has high strength and reliability, and can withstand airflow pressure, vibration and other external forces during flight, thereby keeping the door cover safely closed and preventing it from accidentally opening, which ensures the safety of passengers and crew members during flight.

[0003] Most of the anti-drop load-bearing locks used for aircraft covers need to be closed manually when in use, which can easily cause the load-bearing lock to loosen due to insufficient force, thus easily creating a safety hazard and affecting the use effect. In addition, when closing, it is easy to cause friction and damage between the load-bearing lock and the aircraft cover, thus affecting the use effect.

[0004] In view of the above problems, the present invention provides an anti-dropping load-bearing lock for an aircraft cover. Summary of the invention

[0005] The object of the present invention is to provide an anti-dropping load-bearing lock for an aircraft cover, which can be effectively closed automatically and can prevent friction damage during closing, thereby solving the problems in the background technology.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: an anti-detachment load-bearing lock for an aircraft cover, comprising a fixed box, a motor box is fixedly connected to one side of the top of the fixed box, a servo motor is fixedly connected to the inside of the motor box, a transmission rod is splined to the output end of the servo motor, one end of the transmission rod is fixedly connected to a fixed block, a protection box is fixedly connected to the inside of the fixed block, a battery is fixedly connected to the inside of the protection box, a transmission line is fixedly connected to the top of the battery, one end of the front of the fixed block is fixedly connected to a damping retractor, one end of the damping retractor is fixedly connected to a connecting block, an electromagnetic suction is fixedly connected to the inside of the connecting block, and the other end of the transmission line is fixedly connected to the top of the connecting block.

[0007] Preferably, a support plate is fixedly connected to the middle of the top of the fixing box, and a support strip is fixedly connected to the back of the support plate, thereby achieving the function of supporting the aircraft cover.

[0008] Preferably, a card slot is provided in the middle of the front side of the fixing box, and a sponge pad is fixedly connected to the inside of the card slot, so as to reduce the friction between the device and the aircraft cover.

[0009] Preferably, the bottom end of the fixing box is fixedly connected to a base, and the surface of the base is threadedly connected to fixing screws, thereby achieving the effect of fixing the device in a proper position.

[0010] Preferably, a storage box is fixedly connected to the other side of the top of the fixed box, and a storage drawer is slidably connected to the middle of the front side of the storage box, so as to achieve the function of placing maintenance parts.

[0011] Preferably, a handle is fixedly connected to the middle of the front face of the storage drawer, and anti-slip grooves are fixedly connected to the surface of the handle, thereby achieving the effect of controlling the storage drawer to be pulled out.

[0012] Preferably, a circular ring is fixedly connected to the bottom of the motor box surface, and matching mounting holes are provided on the surface of the circular ring and the top of the fixed box, and bolts are connected to the internal threads of the mounting holes.

[0013] Preferably, the working steps of the anti-dropping load-bearing lock for aircraft cover are as follows:

[0014] S1, first fix the fixing box 1 in a proper position by means of the fixing screws 16 on the base 15;

[0015] S2. When the aircraft cover is needed, the servo motor 3 can be started through the motor box 2 and the external power supply, and the fixed block 5 can be driven to rotate through the transmission rod 4 so that the fixed block 5 reaches the appropriate position;

[0016] S3. Then, the battery 7 in the protection box 6 causes the electromagnetic suction 11 in the connection block 10 to generate suction, and the electromagnetic suction 11 generating suction will be adsorbed on the aircraft cover to be fixed.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The present invention provides an anti-drop load-bearing lock for an aircraft cover.

[0019] (1) The present invention can effectively and quickly close automatically when a person operates the device by setting up a servo motor, a transmission rod and a fixed block, thereby reducing the occurrence of problems such as loose closing of the device due to manual closing.

[0020] (2) The present invention, through the arrangement of a battery, a transmission line, a damping retractor, a connecting block and an electromagnetic suction, can effectively adsorb the device to the aircraft cover when a person operates the device, thereby reducing the occurrence of the problem of mutual friction during the bonding process and thus damaging the connection. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the device of the present invention;

[0022] Figure 2 This is a schematic diagram of the closed state of the present invention;

[0023] Figure 3 It is a cross-sectional schematic diagram of the motor box of the present invention;

[0024] Figure 4 It is a cross-sectional schematic diagram of the fixing block of the present invention.

[0025] In the figure: 1. fixing box; 2. motor box; 3. servo motor; 4. transmission rod; 5. fixing block; 6. protection box; 7. battery; 8. transmission line; 9. damping retractor; 10. connecting block; 11. electromagnetic suction; 12. support plate; 13. support bar; 14. sponge pad; 15. base; 16. fixing screw; 17. storage box; 18. storage drawer; 19. handle. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "two ends", "one end", "the other end" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0028] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0029] An embodiment provided by the present invention:

[0030] A load-bearing lock for an aircraft cover, comprising a fixing box 1, a motor box 2 is fixedly connected to one side of the top of the fixing box 1, and the setting of the motor box 2 can effectively protect the servo motor 3 when the personnel operate the device. The motor box 2 is fixedly connected to the servo motor 3 inside, and the setting of the servo motor 3 can control the rotation of the fixing block 5 during use. The output end of the servo motor 3 is spline-connected with a transmission rod 4, and the setting of the transmission rod 4 can connect the servo motor 3 and the fixing block 5 during use. One end of the transmission rod 4 is fixedly connected to the fixing block 5, and the setting of the servo motor 3, the transmission rod 4 and the fixing block 5 can effectively and quickly close automatically when the personnel operate the device, thereby reducing the occurrence of problems such as loose closure of the device due to manual closure. The fixing block 5 is fixedly connected to the inside of the fixing block 5, and the setting of the protection box 6 can protect the internal battery 7 during use. The protection box 6 is fixedly connected to the inside of the battery 7, and the setting of the battery 7 can prevent the servo motor 3 and the fixing block 5 from being locked during use. The process plays the effect of providing power to the electromagnetic suction 11 in the connecting block 10. The top of the battery 7 is fixedly connected with a transmission line 8. Through the setting of the transmission line 9, the power in the battery 7 in the protection box 6 is transmitted to the electromagnetic suction 11 in the connecting block 10 during use. One end of the front of the fixed block 5 is fixedly connected with a damping retractor 9. Through the setting of the damping retractor 9, a shock absorption effect is achieved during use. One end of the damping retractor 9 is fixedly connected with a connecting block 10. Through the setting of the connecting block 10, the electromagnetic suction 11 is protected during use. Through the setting of the electromagnetic suction 11, the aircraft cover is adsorbed during use. The inside of the connecting block 10 is fixedly connected with the electromagnetic suction 11. Through the setting of the battery 7, the transmission line 8, the damping retractor 9, the connecting block 10 and the electromagnetic suction 11, when the personnel operate the device, the device can be effectively adsorbed to the aircraft cover, reducing the occurrence of problems such as mutual friction and damage during the fitting process. The other end of the transmission line 8 is fixedly connected to the top of the connecting block 10.

[0031] Specifically, when in use, first start the servo motor 3, and drive the fixed block 5 to rotate through the transmission rod 4, so that the fixed block 5 reaches the appropriate position, and then the battery 7 in the protection box 6 makes the electromagnetic suction 11 in the connecting block 10 generate suction, and the electromagnetic suction 11 generating suction will be adsorbed on the aircraft cover for fixation.

[0032] A support plate 12 is fixedly connected to the middle of the top of the fixing box 1 , and a support bar 13 is fixedly connected to the back of the support plate 12 .

[0033] Specifically, the purpose of such design is to achieve the effect of fitting the aircraft cover during use through the setting of the support plate 12, and to achieve the effect of stabilizing the support plate 12 during use through the setting of the support strip 13.

[0034] A slot is provided in the middle of the front side of the fixing box 1 , and a sponge pad 14 is fixedly connected inside the slot.

[0035] Specifically, the purpose of such a design is to facilitate the placement of the sponge pad 14 during use through the provision of the card slot, and to reduce friction during use through the provision of the sponge pad 14.

[0036] The bottom end of the fixing box 1 is fixedly connected with a base 15 , and the surface of the base 15 is threadedly connected with a fixing screw 16 .

[0037] Specifically, the purpose of such design is to fix the device in a proper position during use through the arrangement of the base 15 and the fixing screws 16 .

[0038] A storage box 17 is fixedly connected to the other side of the top of the fixed box 1, and a storage drawer 18 is slidably connected to the middle of the front side of the storage box 17.

[0039] Specifically, the purpose of such design is to protect the storage drawer 18 during use through the provision of the storage box 17, and to place the maintenance parts during use through the provision of the storage drawer 18.

[0040] A handle 19 is fixedly connected to the middle of the front side of the storage drawer 18 , and anti-slip grooves are fixedly connected to the surface of the handle 19 .

[0041] Specifically, the purpose of such a design is to control the storage drawer 18 through the provision of the handle 19 during use so as to pull the plant drawer 18 out of the storage box 17.

[0042] A circular ring is fixedly connected to the bottom of the surface of the motor box 2, and matching mounting holes are provided on the surface of the circular ring and the top of the fixed box 1, and bolts are threadedly connected to the inner part of the mounting hole.

[0043] Specifically, the purpose of such design is to facilitate personnel to repair or replace the servo motor 3 and to facilitate personnel to open the motor box 2.

[0044] The working steps of the anti-drop load-bearing lock for aircraft cover are as follows:

[0045] S1, first fix the fixing box 1 in a proper position by means of the fixing screws 16 on the base 15;

[0046] S2. When the aircraft cover is needed, the servo motor 3 can be started through the motor box 2 and the external power supply, and the fixed block 5 can be driven to rotate through the transmission rod 4 so that the fixed block 5 reaches the appropriate position;

[0047] S3. Then, the battery 7 in the protection box 6 causes the electromagnetic suction 11 in the connection block 10 to generate suction, and the electromagnetic suction 11 generating suction will be adsorbed on the aircraft cover to be fixed.

[0048] Working principle: the servo motor 3 is fixedly connected to the inside of the motor box 2 for providing power and controlling mechanical movement, the transmission rod 4 is connected to the output end of the servo motor 3 through a spline, the fixed block 5 is fixedly connected to one end of the transmission rod 4 for transmitting power and realizing mechanical movement, the transmission line 8 is fixedly connected to the top of the battery 7 for transmitting electricity and signals, the damping retractor 9 is fixedly connected to one end of the front of the fixed block 5, the connecting block 10 is fixedly connected to the inside of the damping retractor 9, the electromagnetic suction 11 is fixedly connected to the inside of the connecting block 10 for realizing the functions of damping and adsorption, and the storage drawer 18 is connected to the middle of the front of the storage box 17 by sliding for storing and taking out items.

[0049] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

Claims

1. An anti-drop load-bearing lock for an aircraft cover, comprising a fixing box (1), characterized in that: A motor box (2) is fixedly connected to one side of the top of the fixed box (1), a servo motor (3) is fixedly connected inside the motor box (2), a transmission rod (4) is splined to the output end of the servo motor (3), one end of the transmission rod (4) is fixedly connected to a fixed block (5), a protection box (6) is fixedly connected inside the fixed block (5), a storage battery (7) is fixedly connected inside the protection box (6), a transmission line (8) is fixedly connected to the top of the storage battery (7), one end of the front of the fixed block (5) is fixedly connected to a damping expansion device (9), one end of the damping expansion device (9) is fixedly connected to a connecting block (10), an electromagnetic suction (11) is fixedly connected inside the connecting block (10), and the other end of the transmission line (8) is fixedly connected to the top of the connecting block (10).

2. The anti-drop load-bearing lock for an aircraft cover according to claim 1, characterized in that: A support plate (12) is fixedly connected to the middle of the top of the fixing box (1), and a support bar (13) is fixedly connected to the back of the support plate (12).

3. The anti-drop load-bearing lock for an aircraft cover according to claim 1, characterized in that: A slot is provided in the middle of the front side of the fixing box (1), and a sponge pad (14) is fixedly connected inside the slot.

4. The anti-drop load-bearing lock for an aircraft cover according to claim 1, characterized in that: The bottom end of the fixing box (1) is fixedly connected to a base (15), and the surface of the base (15) is threadedly connected to a fixing screw (16).

5. The anti-drop load-bearing lock for an aircraft cover according to claim 1, characterized in that: A storage box (17) is fixedly connected to the other side of the top of the fixed box (1), and a storage drawer (18) is slidably connected to the middle of the front of the storage box (17).

6. The anti-drop load-bearing lock for an aircraft cover according to claim 5, characterized in that: A handle (19) is fixedly connected to the middle of the front of the storage drawer (18), and anti-slip grooves are fixedly connected to the surface of the handle (19).

7. The anti-drop load-bearing lock for an aircraft cover according to claim 1, characterized in that: A circular ring is fixedly connected to the bottom of the surface of the motor box (2), and matching mounting holes are provided on the surface of the circular ring and the top of the fixed box (1), and bolts are threadedly connected inside the mounting holes.

8. The anti-drop load-bearing lock for aircraft cover according to claims 1-7, characterized in that: The working steps of the anti-drop load-bearing lock for aircraft cover are as follows: S1, first fix the fixing box 1 in a proper position by means of the fixing screws 16 on the base 15; S2. When the aircraft cover is needed, the servo motor 3 can be started through the motor box 2 and the external power supply, and the fixed block 5 can be driven to rotate through the transmission rod 4 so that the fixed block 5 reaches the appropriate position; S3. Then, the battery 7 in the protection box 6 causes the electromagnetic suction 11 in the connection block 10 to generate suction, and the electromagnetic suction 11 generating suction will be adsorbed on the aircraft cover to be fixed.

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