An air launch locking mechanism with dual working states

Abstract

This invention discloses an aircraft launch locking mechanism with dual operating states, comprising a launcher, a hydraulic catapult, a hydraulic catapult safety, and a position shift lock, with two operating positions. In flight mode, the position shift lock is always in position one, meaning the hook at the end of the launcher where the object is placed is linked to the launcher. When launching an object, the hydraulic catapult safety is released, and the launch command is issued from the control terminal. The launcher immediately launches under the pressure of the hydraulic catapult, simultaneously rotating the hook, causing the object to detach from the hook and be launched downwards, completing the launch mission. In ground mode, the position shift lock is always in position two, meaning the hook at the end of the launcher where the object is placed is not linked to the launcher. When maintenance or object placement is required, the hydraulic catapult safety is released, and the hydraulic catapult actuation command is issued. The launcher launches under the pressure of the hydraulic catapult, but the hook holding the object does not rotate.

Description

Technical Field

[0001] This invention relates to the field of aircraft launch locks, and more particularly to an aircraft launch lock mechanism with dual operating states. Background Technology

[0002] The increasing richness and rapid development of modern society's production and lifestyle have led to a surge in demand for specialized equipment. Among these, aerial work platforms, which do not rely on land, are widely used in many fields such as agriculture, transportation, fire fighting, and earthquake relief. In modern large-scale mechanized agricultural operations, non-contact aerial operations, such as pesticide spraying, are required. This necessitates the installation of launch and locking mechanisms on low-altitude aircraft to perform agricultural operations under specific working conditions. In modern society, with the strengthening of commercial trade, the transportation of goods worldwide increasingly relies on aerial work platforms such as aircraft and drones. When transporting goods by air, it is essential to deliver them safely and reliably, switching between different working modes depending on whether delivery is required. In the field of fire and rescue, in sudden emergencies such as fires, many disaster sites present urgent situations and complex building structures, making manual rescue extremely dangerous. This necessitates the use of drones and other aircraft to replace or assist manual operations, reducing the risks to firefighters. Therefore, aircraft and other mechanical flying equipment need to be equipped with controllable ejection locking mechanisms to safely and reliably deliver fire and rescue equipment and drive water cannons for operations in emergencies. In critical situations such as earthquake relief, due to the high destructiveness and danger of disasters like earthquakes, the fastest way to urgently provide relief supplies and other necessities to disaster areas is also by air. This means that controllable object projection mechanisms also need to be installed on aircraft to control the transportation of relief supplies and related matters. Summary of the Invention

[0003] This invention overcomes the shortcomings of existing technologies and addresses the problems of cumbersome and complex launcher locking mechanisms and low reliability during catapult launches by proposing a dual-operation-state aircraft launch locking mechanism. This locking mechanism consists of four parts: the launcher, the hydraulic catapult, the hydraulic catapult safety, and the gear shift lock, enabling the aircraft to operate in both flight and ground-based modes.

[0004] The technical solution adopted in this invention is:

[0005] An aircraft launch locking mechanism with dual working states, the locking mechanism consists of four parts: launcher, hydraulic catapult, hydraulic catapult safety and gear shift lock;

[0006] The launcher is mainly composed of an upper truss 1, a front upper truss 14, a rear upper truss 3, a front lower truss 15, an output rod 5, a central truss 6, and a lower truss 7.

[0007] The upper truss 1 is fixed to the aircraft by mounting bolts. The upper ends of the front upper truss 14 and the rear upper truss 3 are hinged to the front and rear ends of the upper truss 1, respectively. The front end of the center truss 6 is hinged to the lower end of the front upper truss 14 and the upper end of the front lower truss 15. The rear end of the center truss 6 is hinged to the lower end of the rear upper truss 3 and the middle of the output rod 5. The front end of the lower truss 7 is hinged to the lower end of the front lower truss 15, and the rear end of the lower truss 7 is hinged to the lower end of the output rod 5. A lateral hole is provided on the outer side of the lower end of the front lower truss 15.

[0008] The hydraulic catapult mainly consists of a hydraulic cylinder 9 and a Y-type connector 2;

[0009] The rear cover of hydraulic cylinder 9 is hinged to the front end of upper truss 1; the piston rod of hydraulic cylinder 9 is bolted to the rear side of Y-type connector 2; the front ears of Y-type connector 2 are hinged to the upper end of output rod 5.

[0010] The hydraulic ejection safety device consists of a guide rail 10, a slider 11, a safety actuator 12, a connecting rod 13, and a safety hook 4. Figure 3 As shown;

[0011] There are two guide rails 10, symmetrically distributed on both sides of the upper truss 1, and connected by bolts; each guide rail 10 is equipped with two sliders 11, symmetrically distributed; there are two safety actuators 12, symmetrically distributed on both sides of the upper truss 1, and located above the guide rails 10; there are four connecting rods 13, located on both sides of the upper truss 1, symmetrically distributed; the lower side of the safety actuator 12 is bolted to the slider 11, and the outer side is hinged to the upper end of the connecting rod 13; the lower end of the connecting rod 13 is engaged with the upper end of the safety hook 4; there are four safety hooks 4, symmetrically distributed; the upper end of the safety hook 4 is hinged to the lifting lugs 21 at the lower ends of both sides of the upper truss 1, and when the launcher is retracted, the safety hook 4 is responsible for lifting the hanging rods 20 extending from both sides of the lower truss 7.

[0012] The gear shift lock is divided into two parts, front and rear. Each part consists of an end actuation hook 16, a stop pin 17, a linkage rod 18 and a connector 19, and the two parts share a gear shifter 8.

[0013] In the front part, the end-effector hook 16 is hinged to the lower end of the front lower truss 15 and the front end of the lower truss 7; the middle part of the stop pin 17 is hinged to the outer side of the front end of the lower truss 7, and the upper end of the stop pin 17 is provided with a sliding groove, which cooperates with the connector 19 through the sliding groove; the linkage rod 18 is arranged horizontally, the middle part of which is hinged to the connector 19, the outer end of which is welded to the inner side of the front end of the gear shifter 8, and the inner end of which is opposite to the lateral hole at the lower end of the front lower truss 15. When performing the launch mission, it is inserted into the lateral hole to ensure that the end-effector hook 16 is linked with the front lower truss 15.

[0014] In the rear section, the end-effector hook 16 is hinged to the rear side of the lower truss 7 and the lower side of the output rod 5; the middle part of the stop pin 17 is hinged to the outer end of the rear end of the lower truss 7, and the upper end of the stop pin 17 is provided with a sliding groove, which cooperates with the connector 19 through the sliding groove; the linkage rod 18 is arranged horizontally, the middle part of which is hinged to the connector 19, the outer end of which is welded to the inner side of the front end of the gear shifter 8, and the inner end of which is opposite to the lateral hole at the lower end of the output rod 5. When performing the launch mission, it is inserted into the lateral hole to ensure that the end-effector hook 16 is linked with the output rod 5.

[0015] The locking mechanism has two working positions: position one (flying state) and position two (working state) under two different working conditions.

[0016] In flight mode, the shift lock is always in position one, meaning the hook at the end of the launcher is linked to the launcher. When launching an object, the hydraulic ejection safety is released, and the launch command (hydraulic ejector actuation command) is issued from the control terminal. The launcher immediately ejects under the pressure of the hydraulic ejector, simultaneously rotating the end-effector hook 16, causing the object to detach from the hook. The object is then launched downwards, completing the launch mission. In ground mode, the shift lock is always in position two, meaning the hook at the end of the launcher is not linked to the launcher. When maintenance or object placement is required, the hydraulic ejection safety is released, and the hydraulic ejector actuation command is issued. The launcher ejects under the pressure of the hydraulic ejector, but the hook for placing the object does not rotate. This ensures that even if an object is placed on the hook, it will not fall off, guaranteeing the safe and smooth conduct of ground maintenance and repair work.

[0017] The beneficial effects of the present invention are as follows: The locking mechanism of the present invention has a reasonable structure, is simple to operate, and has high reliability. It ensures that the gear switching between the two working states can be achieved through simple operation. This has important practical significance for improving the emergency rescue and disaster relief capabilities of aircraft, reducing the impact of launch locking mechanism problems on emergency missions, and even improving the overall level of rescue and disaster relief. Attached Figure Description

[0018] Figure 1 This is an isometric view of the overall three-dimensional structure of an air launch locking mechanism in dual working states according to the present invention.

[0019] Figure 2 This is a schematic diagram of a hydraulic catapult.

[0020] Figure 3 This is a schematic diagram of the hydraulic ejection safety mechanism.

[0021] Figure 4 This is a schematic diagram showing the location of the safety hook.

[0022] Figure 5 This is a schematic diagram of the front part of the gear shift lock.

[0023] Figure 6 This is a schematic diagram of the rear part of the gear shift lock.

[0024] In the diagram, 1-upper truss, 2-Y-joint, 3-rear upper truss, 4-safety hook, 5-output rod, 6-center truss, 7-lower truss, 8-gear shifter, 9-hydraulic cylinder, 10-guide rail, 11-slider, 12-safety actuator, 13-connecting rod, 14-front upper truss, 15-front lower truss, 16-end actuator hook, 17-stop pin, 18-linkage rod, 19-connector, 20-hanging rod, 21-lifting lug. Detailed Implementation

[0025] The specific embodiments of the present invention will now be described in detail with reference to the accompanying drawings and technical solutions.

[0026] This example demonstrates an aircraft launch locking mechanism operating in dual-mode, comprising four parts: a launcher, a hydraulic ejector, a hydraulic ejection safety, and a shift lock. A three-dimensional isometric view of the structure is shown below. Figure 1 As shown, the components are described below;

[0027] The launcher is mainly composed of an upper truss 1, a front upper truss 14, a rear upper truss 3, a front lower truss 15, an output rod 5, a central truss 6, and a lower truss 7.

[0028] The upper truss 1 is fixed to the aircraft by mounting bolts. The upper ends of the front upper truss 14 and the rear upper truss 3 are hinged to the front and rear ends of the upper truss 1, respectively. The front end of the center truss 6 is hinged to the lower end of the front upper truss 14 and the upper end of the front lower truss 15. The rear end of the center truss 6 is hinged to the lower end of the rear upper truss 3 and the middle of the output rod 5. The front end of the lower truss 7 is hinged to the lower end of the front lower truss 15, and the rear end of the lower truss 7 is hinged to the lower end of the output rod 5. A lateral hole is provided on the outer side of the lower end of the front lower truss 15.

[0029] The hydraulic catapult mainly consists of a hydraulic cylinder 9 and a Y-type connector 2, such as Figure 2 As shown;

[0030] The rear cover of hydraulic cylinder 9 has two ears that are hinged to the front end of upper truss 1; the piston rod of hydraulic cylinder 9 is bolted to the rear side of Y-type connector 2; the front ears of Y-type connector 2 are hinged to the upper end of output rod 5.

[0031] The hydraulic ejection safety device consists of a guide rail 10, a slider 11, a safety actuator 12, a connecting rod 13, and a safety hook 4. Figure 3 As shown;

[0032] There are two guide rails 10, symmetrically distributed on both sides of the upper truss 1, and connected by bolts; each guide rail 10 is equipped with two sliders 11, symmetrically distributed; there are two safety actuators 12, symmetrically distributed on both sides of the upper truss 1, and located above the guide rails 10; there are four connecting rods 13, located on both sides of the upper truss 1, symmetrically distributed; the lower side of the safety actuator 12 is bolted to the slider 11, and the outer side is hinged to the upper end of the connecting rod 13; the lower end of the connecting rod 13 is engaged with the upper end of the safety hook 4; there are four safety hooks 4, symmetrically distributed; the lower end of the safety hook 4 is hinged to the lifting lugs 21 welded to the lower ends of both sides of the upper truss 1 (front and back are consistent), and the safety hooks 4 are responsible for lifting the hanging rods 20 welded to both sides of the lower truss 7 (front and back are consistent), such as... Figure 4 As shown.

[0033] like Figure 2 As shown, the gear shift lock is divided into two parts, front and rear. Each part consists of an end actuation hook 16, a stop pin 17, a linkage rod 18 and a connector 19, and the two parts share a gear shifter 8.

[0034] In the front section, the end actuating hook 16 is hinged to the lower end of the front lower truss 15 and the front end of the lower truss 7; the middle part of the stop pin 17 is hinged to the outer side of the front end of the lower truss 7 (see detailed drawing of the front end of the lower truss 7). Figure 4 The upper end of the stop pin 17 has a sliding groove, which mates with the sliding groove of the connector 19. The linkage rod 18 is horizontally arranged, with its middle part hinged to the connector 19. Its outer end is welded to the inner side of the front end of the gear shifter 8, and its front end is opposite to the lateral hole at the lower end of the front lower truss 15. When performing a launch mission, it is inserted into the lateral hole to ensure that the end effector hook 16 is linked with the front lower truss 15. Figure 5 As shown;

[0035] In the rear section, the end-effector hook 16 is hinged to the rear side of the lower truss 7 and the lower side of the output rod 5; the middle part of the stop pin 17 is hinged to the outer rear end of the lower truss 7, and the upper end of the stop pin 17 is provided with a sliding groove, which engages with the sliding groove of the connector 19; the linkage rod 18 is arranged horizontally, with its middle part hinged to the connector 19, its outer end engaging with the inner side of the gear shifter 8, and its front end facing the lateral hole at the lower end of the output rod 5. When performing a launch mission, it is inserted into the lateral hole to ensure that the end-effector hook 16 is linked with the output rod 5. Figure 6 As shown;

[0036] The working principle of the locking mechanism is as follows: The upper truss 1 is fixed to the aircraft by mounting bolts. In flight mode, the gear shift lock is in gear position one, that is, the gear shifter 8 is pushed towards the lower truss 15. The linkage rod 18 is inserted into the lateral hole of the lower truss 15, so that the end actuation hook 16 is linked with the lower truss 15 (the same applies to the rear side, the end actuation hook 16 is linked with the output rod 5 accordingly); at the same time, the linkage rod 18 drives the stop pin 17 through the connector 19, so that the upper end (slide end) of the stop pin 17 rotates around the hinge with the middle of the rear side of the lower truss 7, so that the lower end of the stop pin 17 and the end actuation hook 16 are angularly misaligned to avoid contact, so that the end actuation hook 16 can be actuated (the same applies to the front and rear sides). When launch is required, the aircraft issues a command, which is transmitted hierarchically to the end-effector 12, causing it to move forward. This drives the linkage 13, which in turn actuates the safety hook 4, thus releasing the safety of the hydraulic catapult. The hydraulic cylinder 9 then actuates, driving the output rod 5, which causes the locking mechanism to launch downwards. This changes the angle between the lower front truss 15 and the upper truss 1, which in turn changes the angle of the end-effector 16 (the same applies to the front and rear sides), completing the launch mission.

[0037] In ground position, the gear shift lock is in gear two. Pulling the gear shifter 8 outward towards the front lower truss 15 causes the linkage rod 18 to move outward, disengaging the end effector hook 16 from the front lower truss 15 (the same applies to the front and rear sides). Simultaneously, the linkage rod 18, through the connector 19, drives the stop pin 17, causing the stop pin 17 to contact the end effector hook 16, ensuring that the end effector hook 16 remains inactive (the same applies to the front and rear sides). When maintenance is required, the aircraft issues a command, which is relayed hierarchically to the end safety actuator 12, causing it to move forward. This drives the linkage rod 13, actuating the safety hook 4, thus disengaging the safety of the hydraulic ejector. The hydraulic cylinder 9 then actuates, driving the output rod 5, causing the locking mechanism to eject downward. Since it is in the ground state, the gear shift lock is in the second gear position, and the angle of the end actuation hook 16 does not change (the same applies to the front and rear sides). That is, only the device is ejected downwards while the end actuation hook 16 does not move, and the object it is carrying will not be thrown off. During maintenance, the entire device is in the ejection state, which facilitates maintenance operations by maintenance personnel.

Claims

1. An air launch locking mechanism with dual operating states, characterized in that, The locking mechanism comprises four parts: a launcher, a hydraulic ejector, a hydraulic ejection safety, and a gear shift lock. The launcher mainly includes an upper truss (1), a front upper truss (14), a rear upper truss (3), a front lower truss (15), an output rod (5), a central truss (6), and a lower truss (7). The upper truss (1) is fixed to the aircraft by mounting bolts. The upper ends of the front upper truss (14) and the rear upper truss (3) are respectively hinged to the front and rear ends of the upper truss (1). The front end of the center truss (6) is hinged to the lower end of the front upper truss (14) and the upper end of the front lower truss (15). The rear end of the center truss (6) is hinged to the lower end of the rear upper truss (3) and the middle of the output rod (5). The front end of the lower truss (7) is hinged to the lower end of the front lower truss (15), and the rear end of the lower truss (7) is hinged to the lower end of the output rod (5). A lateral hole is provided on the outer side of the lower end of the front lower truss (15). The hydraulic catapult mainly includes a hydraulic cylinder (9) and a Y-type connector (2). The rear cover of the hydraulic cylinder (9) is hinged to the front end of the upper truss (1); the piston rod of the hydraulic cylinder (9) is bolted to the rear side of the Y-type connector (2); the front ears of the Y-type connector (2) are hinged to the upper end of the output rod (5); The hydraulic ejection safety includes a guide rail (10), a slider (11), a safety actuator (12), a connecting rod (13), and a safety hook (4). There are two guide rails (10), symmetrically distributed on both sides of the upper truss (1) and connected by bolts; two sliders (11) are set on each guide rail (10), symmetrically distributed; there are two safety actuators (12), symmetrically distributed on both sides of the upper truss (1) and located above the guide rails (10); there are four connecting rods (13), located on both sides of the upper truss (1) and symmetrically distributed; the lower side of the safety actuator (12) is bolted to the slider (11), and the outer side is hinged to the upper end of the connecting rod (13); the lower end of the connecting rod (13) is engaged with the upper end of the safety hook (4); there are four safety hooks (4), symmetrically distributed; the upper end of the safety hook (4) is hinged to the lifting lugs (21) at the lower ends of both sides of the upper truss (1), and the safety hook (4) is responsible for lifting the hanging rods (20) extending from both sides of the lower truss (7); The gear shift lock is divided into two parts, front and rear. Each part includes an end actuation hook (16), a stop pin (17), a linkage rod (18) and a connector (19), and the two parts share a gear shifter (8). In the front part, the end-acting hook (16) is hinged to the lower end of the front lower truss (15) and the front end of the lower truss (7); the middle part of the stop pin (17) is hinged to the outer side of the front end of the lower truss (7), and the upper end of the stop pin (17) is provided with a sliding groove, and the upper end is engaged with the connector (19) through the sliding groove; the linkage rod (18) is arranged horizontally, the middle part of which is hinged to the connector (19), and its outer end is welded to the inner side of the front end of the gear shifter (8), and its inner end is opposite to the lateral hole at the lower end of the front lower truss (15). When performing the launch mission, it is inserted into the lateral hole to ensure that the end-acting hook (16) is linked with the front lower truss (15); In the rear part, the end-acting hook (16) is hinged to the rear side of the lower truss (7) and the lower side of the output rod (5); the middle part of the stop pin (17) is hinged to the outer end of the rear end of the lower truss (7), and the upper end of the stop pin (17) is provided with a sliding groove, and the upper end is connected to the connector (19) through the sliding groove; the linkage rod (18) is arranged horizontally, the middle part of which is hinged to the connector (19), and its outer end is welded to the inner side of the front end of the gear shifter (8), and its front end is opposite to the side hole at the lower end of the output rod (5). When performing the launch mission, it is inserted into the side hole to ensure that the end-acting hook (16) and the output rod (5) are linked.

2. The aircraft launch locking mechanism in dual working states according to claim 1, characterized in that, The locking mechanism has two working positions, position one and position two, for two different working conditions. In flight mode, the gear shift lock is in position one, i.e., the gear shifter (8) is pushed towards the lower front truss (15), and the linkage rod (18) is inserted into the lateral hole of the lower front truss (15), so that the end effector hook (16) is linked with the lower front truss (15); at the same time, the linkage rod (18) drives the stop pin (17) through the connector (19), so that the upper end of the stop pin (17) rotates around the hinge with the middle of the rear side of the lower truss (7), so that the lower end of the stop pin (17) and the end effector hook (16) are angled. The misalignment avoids contact, allowing the end effector hook (16) to actuate. When launch is required, the aircraft issues a command, which is transmitted hierarchically to the end safety actuator (12), causing it to move forward and drive the linkage (13), which in turn actuates the safety hook (4), thus opening the safety of the hydraulic catapult. The hydraulic cylinder (9) actuates, driving the output rod (5), causing the locking mechanism to launch downward. The angle between the lower front truss (15) and the upper truss (1) changes, which in turn changes the angle of the end effector hook (16), completing the launch mission. In ground mode, the gear shift lock is in position two, i.e., pulling the gear shifter (8) outward towards the front lower truss (15) causes the linkage rod (18) to move outward, disengaging the end effector hook (16) from the front lower truss (15); simultaneously, the linkage rod (18) drives the stop pin (17) through the connector (19), causing the stop pin (17) to contact the end effector hook (16), ensuring that the end effector hook (16) remains stationary; when maintenance is required, the aircraft issues a command, which is then passed hierarchically to the end safety actuator (1). 2) It moves forward, driving the connecting rod (13) to activate the safety hook (4), that is, to open the safety of the hydraulic ejector. The hydraulic cylinder (9) is activated, driving the output rod (5) to eject the locking mechanism downward. Since it is on the ground, the gear shift lock is in the second gear position. The angle of the end actuator hook (16) does not change. That is, only the device ejects downward and the end actuator hook (16) does not activate. The object it is carrying will not be thrown off. During maintenance, the entire device is in the ejection state, which is convenient for maintenance personnel to perform maintenance operations.

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