Electrically-driven quick harpoon device for assisting helicopter in landing and landing on ship and using method

Abstract

The invention discloses an electrically-driven quick harpoon device for assisting a helicopter to land on a ship and take off, and relates to auxiliary landing of the helicopter. The device comprises a harpoon device actuating mechanism and a harpoon device controller, wherein the harpoon device actuating mechanism comprises a gearbox assembly, an outer cylinder assembly, an inner cylinder assembly and a lock head assembly; the upper end of the outer cylinder assembly is located in the cabin. The inner cylinder assembly is located in the outer cylinder assembly. The lower end of the inner cylinder assembly is connected with the lock head assembly. The input end of the gearbox assembly is connected with the brushless direct current motor, and the output end of the gearbox assembly is connected with the inner cylinder assembly. According to the invention, the tensioning force is not less than 40kN, the take-off and landing time is not more than 2s, multiple technical difficulties of high-speed movement, impact resistance, corrosion resistance, electromagnetism resistance, low power consumption, low weight, high reliability and the like are solved, and the blank of an electric drive rapid carrier landing technology of a harpoon-grid auxiliary carrier landing system of a heavy-duty helicopter at home and abroad is filled. The invention further relates to a using method of the electrically-driven quick harpoon device for assisting the helicopter to land on the ship and take off and land.

Description

Technical Field

[0001] The present invention relates to helicopter assisted landing, and more specifically, it is an electric drive rapid harpoon device for helicopter assisted landing takeoff and landing. The present invention also relates to a usage method of such an electric drive rapid harpoon device for helicopter assisted landing takeoff and landing. Background Art

[0002] Currently, the shipborne helicopter assisted landing systems globally include: harpoon-grid assisted landing system, pull-down RAST system, and shipborne helicopter integrated operation ASIST system; the harpoon-grid assisted landing system is further divided into pneumatic drive, hydraulic drive, and electric drive in terms of drive mode.

[0003] Currently, all domestic and foreign electric drive harpoon-grid assisted landing systems are for light helicopters; when taking off and landing in complex sea conditions, the maximum tension force generally does not exceed 15 kN, and the takeoff and landing time does not exceed 2 s. In addition, due to power supply limitations and weight requirements on the aircraft, this requires the landing device to have multiple technical difficulties such as high-speed movement, shock resistance, corrosion resistance, electromagnetic resistance, low power consumption, low weight, and high reliability.

[0004] Therefore, it is necessary to develop a heavy-duty helicopter harpoon-grid assisted landing system with a tension force of not less than 40 kN and a takeoff and landing time of not more than 2 s. Summary of the Invention

[0005] The first object of the present invention is to overcome the deficiencies of the above background art, and provide an electric drive rapid harpoon device for helicopter assisted landing takeoff and landing.

[0006] The second object of the present invention is to overcome the deficiencies of the above background art, and provide a usage method of an electric drive rapid harpoon device for helicopter assisted landing takeoff and landing.

[0007] To achieve the above first object, the technical solution of the present invention is: an electric drive rapid harpoon device for helicopter assisted landing takeoff and landing, characterized in that: it includes a harpoon device actuating mechanism and a harpoon device controller, and the harpoon device actuating mechanism includes a gearbox assembly, an outer cylinder assembly, an inner cylinder assembly, and a lock head assembly;

[0008] The gearbox assembly is located inside the cabin; the upper end of the outer cylinder assembly is located inside the cabin and the lower end is located outside the cabin; the inner cylinder assembly is located inside the outer cylinder assembly, the lower end of the inner cylinder assembly is connected to the lock head assembly, and the lock head assembly is located outside the cabin;

[0009] The input end of the gearbox assembly is connected to a brushless DC motor, the output end of the gearbox assembly is connected to the inner cylinder assembly, and the lock head assembly matches the grid;

[0010] The brushless DC motor is controlled by a harpoon device controller.

[0011] In the above technical solution, there are two brushless DC motors. The gearbox assembly includes a high-speed transmission system and a low-speed transmission system. One brushless DC motor drives the high-speed transmission system, and the other brushless DC motor drives the low-speed transmission system;

[0012] The high-speed transmission system includes a first bevel gear pair, a second bevel gear pair, a first worm and worm gear pair, a second worm and worm gear pair, a first external meshing gear pair, and a second external meshing gear pair. The first bevel gear pair is sleeved on the first worm and worm gear pair, the second bevel gear pair meshes with the first bevel gear pair, the first worm and worm gear pair meshes with the second worm and worm gear pair, the first external meshing gear pair is sleeved on the second worm and worm gear pair, the second external meshing gear pair meshes with the first external meshing gear pair, the second external meshing gear pair is sleeved on the NGW type planetary gear pair, and the NGW type planetary gear pair is the output end, and the second bevel gear pair is the input end.

[0013] In the above technical solution, a roller type slip clutch is arranged on the first worm and worm gear pair, and the first bevel gear pair and the second bevel gear pair are connected to the roller type slip clutch;

[0014] A manual control retracting and releasing interface is arranged on the first worm and worm gear pair.

[0015] In the above technical solution, the low-speed transmission system includes a first-stage NGW type planetary gear pair, a second-stage NGW type planetary gear pair, a third external meshing gear pair, and a fourth external meshing gear pair. The first-stage NGW type planetary gear pair is connected in series with the second-stage NGW type planetary gear pair. The third external meshing gear pair is sleeved on the second-stage NGW type planetary gear pair, the fourth external meshing gear pair is sleeved on the NGW type planetary gear pair, and the third external meshing gear pair meshes with the fourth external meshing gear pair; the NGW type planetary gear pair is the output end, and the first-stage NGW type planetary gear pair is the input end;

[0016] A differential transmission system is arranged at the output end of the gearbox assembly, and the differential transmission system is connected to a potentiometer.

[0017] In the above technical solution, a multi-disc friction type clutch for adjusting torque is arranged between the second-stage NGW type planetary gear pair and the third external meshing gear pair; the protective cover of the harpoon device covers the gearbox assembly and the harpoon device controller.

[0018] In the above technical solution, the lock head assembly includes a locking mechanism and an electromagnet assembly. A locking pin is fixedly arranged on the armature of the electromagnet assembly; two claw hooks arranged in parallel are hinged on the shell of the locking mechanism through two rotating shafts, and the two claw hooks cooperate with the locking pin to realize the locking and unlocking of the grid.

[0019] In the above technical solution, an unlocking rod is provided on the locking mechanism.

[0020] In the above technical solution, two position switches with double margins are provided above the inside of the lock head assembly.

[0021] In the above technical solution, the mounting assembly is mounted on the outer cylinder assembly. The mounting assembly is connected to the airframe outside the cabin through a spherical surface and a fixing nut, and the mounting assembly is connected to the outer cylinder assembly inside the cabin through a spring. The spherical surface enables the actuating mechanism of the harpoon device to work normally within a yaw angle of 0-7°, and the spring enables the actuating mechanism of the harpoon device to return to the vertical state.

[0022] In order to achieve the above second object, the technical solution of the present invention is: a usage method of an electric drive rapid harpoon device for helicopter assisted ship landing and takeoff, which is characterized in that it includes the following steps:

[0023] Step 1, inside the gearbox assembly, the Hall signal of the brushless DC motor, the power supply signal of the brushless DC motor, and the potentiometer signal are integrated and filtered through a filter and then output. The filtered signal is transmitted to the harpoon device controller through a cable;

[0024] Two position switches with double margins judge the signal of the locking pin in place, and the signal is collected and the state is judged by the harpoon device controller;

[0025] Step 2, according to the communication signal provided on the aircraft, the harpoon device controller combines self-checking, judges the position state of the actuating mechanism of the harpoon device, and sends an action instruction for takeoff and landing. By controlling the brushless DC motor, high-speed movement or low-speed movement is achieved, and the function of the harpoon device for takeoff and landing is realized. Cooperating with the locking and unlocking of the lock head assembly, the function of helicopter mooring is realized.

[0026] Compared with the prior art, the present invention has the following advantages:

[0027] 1) The present invention has a tension force of not less than 40 kN and a takeoff and landing time of not more than 2 s, solves a number of technical difficulties such as high-speed movement, impact resistance, corrosion resistance, electromagnetic resistance, low power consumption, low weight, and high reliability, and fills the gap in the electric drive rapid ship landing technology of the harpoon-grid assisted ship landing system for heavy helicopters at home and abroad.

[0028] 2) The gearbox assembly of the present invention includes a high-speed transmission system and a low-speed transmission system, which are respectively driven by two brushless DC motors to realize the high-speed small-load movement and low-speed large-load movement of the actuating mechanism of the harpoon device.

[0029] 3) A differential transmission system is provided at the output end of the two transmission systems of the gearbox assembly of the present invention, which is connected to a potentiometer for recording and feedback of the movement stroke of the actuating mechanism of the harpoon device.

[0030] 4) The lock head assembly of the present invention is realized by the mutual cooperation of a locking mechanism and an electromagnet assembly; the lock pin is fixedly arranged on the armature of the electromagnet assembly; on the locking mechanism housing, two claw hooks arranged side by side are hinged through two rotating shafts, and the two claw hooks cooperate with the lock pin to realize the locking action of the actuating mechanism of the harpoon device and the grid.

[0031] 5) The present invention mainly uses electricity for driving. Through the harpoon device controller, the actuating mechanism of the harpoon device is quickly engaged with the grid, achieving the purpose of safely mooring a heavy-lift helicopter in high sea states, ensuring the takeoff and landing safety of the helicopter, and solving multiple technical difficulties in the electric drive and quick landing of the harpoon-grid assisted landing system for heavy-lift helicopters in the background technology. Brief Description of the Drawings

[0032] Figure 1 It is a structural schematic diagram of the present invention.

[0033] Figure 2 It is a structural schematic diagram of the actuating mechanism of the harpoon device.

[0034] Figure 3 It is a structural schematic diagram of the high-speed transmission system.

[0035] Figure 4 It is a structural schematic diagram of the low-speed transmission system.

[0036] Figure 5 It is a structural schematic diagram of the differential transmission system.

[0037] Figure 6 It is a structural schematic diagram of the lock head assembly.

[0038] Wherein, A - actuating mechanism of the harpoon device, B - harpoon device controller, C - grid, D - harpoon device protective cover, 1 - gearbox assembly, 11 - high-speed transmission system, 111 - first bevel gear pair, 112 - second bevel gear pair, 113 - first worm and worm gear pair, 114 - second worm and worm gear pair, 115 - first external meshing gear pair, 116 - second external meshing gear pair, 117 - roller type slipping clutch, 118 - manual control retracting and extending interface, 12 - low-speed transmission system, 121 - first-stage NGW type planetary gear pair, 122 - second-stage NGW type planetary gear pair, 123 - third external meshing gear pair, 124 - fourth external meshing gear pair, 125 - multi-disc friction clutch, 13 - NGW type planetary gear pair, 2 - outer cylinder assembly, 3 - inner cylinder assembly, 4 - lock head assembly, 41 - locking mechanism, 42 - electromagnet assembly, 43 - lock pin, 44 - rotating shaft, 45 - claw hook, 46 - unlocking lever, 47 - position switch, 5 - brushless DC motor, 6 - differential transmission system, 61 - potentiometer, 7 - cable, 8 - mounting assembly, 81 - spherical surface, 82 - fixing nut, 83 - spring. Detailed implementation mode

[0039] The following will describe in detail the implementation of the present invention in conjunction with the attached drawings. However, they do not constitute a limitation to the present invention and are only for illustration purposes. At the same time, the advantages of the present invention will become clearer and easier to understand through the description.

[0040] Referring to the attached drawings, it can be seen that for the electric drive rapid harpoon device for helicopter assisted landing and takeoff, it is characterized in that: it includes a harpoon device actuation mechanism A and a harpoon device controller B. The harpoon device actuation mechanism A includes a gearbox assembly 1, an outer cylinder assembly 2, an inner cylinder assembly 3 and a lock head assembly 4;

[0041] The gearbox assembly 1 is located inside the cabin; the upper end of the outer cylinder assembly 2 is located inside the cabin and the lower end is located outside the cabin; the inner cylinder assembly 3 is located inside the outer cylinder assembly 2, and the lower end of the inner cylinder assembly 3 is connected to the lock head assembly 4, and the lock head assembly 4 is located outside the cabin;

[0042] The input end of the gearbox assembly 1 is connected to the brushless DC motor 5, the output end of the gearbox assembly 1 is connected to the inner cylinder assembly 3, and the lock head assembly 4 is matched with the grid C;

[0043] The brushless DC motor 5 is controlled by the harpoon device controller B.

[0044] There are two brushless DC motors 5. The gearbox assembly 1 includes a high-speed transmission system 11 and a low-speed transmission system 12. One brushless DC motor 5 drives the high-speed transmission system 11, and the other brushless DC motor 5 drives the low-speed transmission system 12;

[0045] The high-speed transmission system 11 includes a first bevel gear pair 111, a second bevel gear pair 112, a first worm and worm gear pair 113, a second worm and worm gear pair 114, a first external meshing gear pair 115 and a second external meshing gear pair 116. The first bevel gear pair 111 is sleeved on the first worm and worm gear pair 113, the second bevel gear pair 112 meshes with the first bevel gear pair 111, the first worm and worm gear pair 113 meshes with the second worm and worm gear pair 114, the first external meshing gear pair 115 is sleeved on the second worm and worm gear pair 114, the second external meshing gear pair 116 meshes with the first external meshing gear pair 115, the second external meshing gear pair 116 is sleeved on the NGW type planetary gear pair 13, and the NGW type planetary gear pair 13 is the output end and the second bevel gear pair 112 is the input end.

[0046] A roller type slipping clutch 117 is arranged on the first worm and worm gear pair 113, and the first bevel gear pair 111 and the second bevel gear pair 112 are connected to the roller type slipping clutch 117; it plays a role in overload protection;

[0047] A manual control retraction and extension interface 118 is provided on the first worm and worm gear pair 113, which is used to manually extend and retract the actuating mechanism A of the harpoon device in the case of power failure.

[0048] The low-speed transmission system 12 includes a first-stage NGW type planetary gear pair 121, a second-stage NGW type planetary gear pair 122, a third external meshing gear pair 123, and a fourth external meshing gear pair 124. The first-stage NGW type planetary gear pair 121 is in series with the second-stage NGW type planetary gear pair 122. The third external meshing gear pair 123 is sleeved on the second-stage NGW type planetary gear pair 122. The fourth external meshing gear pair 124 is sleeved on the NGW type planetary gear pair 13, and the third external meshing gear pair 123 meshes with the fourth external meshing gear pair 124. The NGW type planetary gear pair 13 is the output end, and the first-stage NGW type planetary gear pair 121 is the input end.

[0049] A differential transmission system 6 is provided at the output end of the gearbox assembly 1. The differential transmission system 6 is connected to a potentiometer 61 for recording and feedback of the movement stroke of the actuating mechanism A of the harpoon device.

[0050] A multi-disc friction clutch 125 for adjusting the torque is provided between the second-stage NGW type planetary gear pair 122 and the third external meshing gear pair 123, which plays a role in overload protection. The protection cover D of the harpoon device covers the gearbox assembly 1 and the harpoon device controller B.

[0051] The lock head assembly 4 includes a locking mechanism 41 and an electromagnet assembly 42. A locking pin 43 is fixedly arranged on the armature of the electromagnet assembly 42. Two claw hooks 45 arranged in parallel are hinged on the shell of the locking mechanism 41 through two rotating shafts 44. The two claw hooks 45 cooperate with the locking pin 43 to lock and unlock the grid C.

[0052] An unlocking rod 46 is provided on the locking mechanism 41, which plays a role in releasing the engagement between the lock head assembly 4 and the grid C during the manual retraction and extension process.

[0053] Two double-margin position switches 47 are provided above the interior of the lock head assembly 4.

[0054] The mounting assembly 8 is mounted on the outer cylinder assembly 2. The mounting assembly 8 is connected to the fuselage outside the cabin through a spherical surface 81 and a fixing nut 82. The mounting assembly 8 is connected to the outer cylinder assembly 2 inside the cabin through a spring 83. The spherical surface 81 enables the actuating mechanism A of the harpoon device to work normally within a yaw angle of 0 - 7°. The spring 83 enables the actuating mechanism A of the harpoon device to return to the vertical state.

[0055] A method for using an electric drive rapid harpoon device for helicopter assisted landing and takeoff is characterized by including the following steps:

[0056] Step 1: Inside the gearbox assembly 1, the Hall signal of the brushless DC motor 5, the power signal of the brushless DC motor 5, and the signal of the potentiometer 61 are integrated and output after being filtered by a filter. The filtered signal is transmitted to the harpoon device controller B through the cable 7.

[0057] Two double-margin position switches 47 are used to judge the signal of the locking pin 43 in place, and the signal is collected and the state is judged by the harpoon device controller B.

[0058] Step 2: According to the communication signal provided on the aircraft, the harpoon device controller B combines self-checking to judge the position state of the actuating mechanism A of the harpoon device, and sends the action instruction for takeoff and landing. By controlling the brushless DC motor 5, high-speed movement or low-speed movement is achieved, and the function of the harpoon device taking off and landing is realized. Cooperating with the locking and unlocking of the locking head assembly 4, the function of helicopter mooring is realized.

[0059] In actual use, the actuating mechanism A of the harpoon device, the harpoon device controller B, and the harpoon device protective cover D can be replaced separately; the actuating mechanism A of the harpoon device is installed on the airframe and is divided into two parts: inside the cabin and outside the cabin; the output end of the gearbox assembly 1 is connected to the inner cylinder assembly 3 to realize the retracting and extending actions; the outside of the lower end of the inner cylinder assembly 3 is connected through the locking head assembly 4 to realize the meshing locking and unlocking with the grid C.

[0060] The high-speed transmission system 11 and the low-speed transmission system 12 share a set of NGW type planetary gear pairs 13.

[0061] The electromagnet assembly 42 and two brushless DC motors 5 are controlled by the harpoon device controller B. The harpoon device signal integrates voltage signals, current signals, electromagnet signals, position switch signals, potentiometer signals, brushless DC motor Hall signals, etc. through the cable 7, and then communicates and transfers information with the harpoon device controller B through the cable 7.

[0062] The cables of the harpoon device controller B include a DC on-aircraft power cable, an AC on-aircraft power cable, and an on-aircraft communication cable.

[0063] Other parts not described belong to the prior art.

Claims

1. Electrically-driven rapid harpoon device for helicopter-assisted ship landing and takeoff, characterized in that: It includes a harpoon device actuating mechanism (A) and a harpoon device controller (B). The harpoon device actuating mechanism (A) includes a gearbox assembly (1), an outer cylinder assembly (2), an inner cylinder assembly (3), and a lock head assembly (4). The gearbox assembly (1) is located inside the cabin; the upper end of the outer cylinder assembly (2) is located inside the cabin and the lower end is located outside the cabin; the inner cylinder assembly (3) is located inside the outer cylinder assembly (2), the lower end of the inner cylinder assembly (3) is connected to the lock head assembly (4), and the lock head assembly (4) is located outside the cabin. The input end of the gearbox assembly (1) is connected to a brushless DC motor (5), the output end of the gearbox assembly (1) is connected to the inner cylinder assembly (3), and the lock head assembly (4) matches the grid (C). The brushless DC motor (5) is controlled by the harpoon device controller (B).

2. The electric-driven rapid harpoon device for helicopter-assisted landing and takeoff according to claim 1, characterized in that: There are two brushless DC motors (5). The gearbox assembly (1) includes a high-speed transmission system (11) and a low-speed transmission system (12). One brushless DC motor (5) drives the high-speed transmission system (11), and the other brushless DC motor (5) drives the low-speed transmission system (12). The high-speed transmission system (11) includes a first bevel gear pair (111), a second bevel gear pair (112), a first worm and worm gear pair (113), a second worm and worm gear pair (114), a first external meshing gear pair (115), and a second external meshing gear pair (116). The first bevel gear pair (111) is sleeved on the first worm and worm gear pair (113), the second bevel gear pair (112) meshes with the first bevel gear pair (111), the first worm and worm gear pair (113) meshes with the second worm and worm gear pair (114), the first external meshing gear pair (115) is sleeved on the second worm and worm gear pair (114), the second external meshing gear pair (116) meshes with the first external meshing gear pair (115), the second external meshing gear pair (116) is sleeved on an NGW type planetary gear pair (13), and the NGW type planetary gear pair (13) is the output end and the second bevel gear pair (112) is the input end.

3. The electrically-driven rapid harpoon device for helicopter assisted landing and takeoff according to claim 2, wherein: A roller type slip clutch (117) is provided on the first worm and worm gear pair (113), and the first bevel gear pair (111) and the second bevel gear pair (112) are connected to the roller type slip clutch (117). A manual control retracting and extending interface (118) is provided on the first worm and worm gear pair (113).

4. The electrically-driven rapid harpoon device for helicopter assisted landing and takeoff according to claim 2, characterized in that: The low-speed transmission system (12) includes a first-stage NGW-type planetary gear pair (121), a second-stage NGW-type planetary gear pair (122), a third external meshing gear pair (123), and a fourth external meshing gear pair (124). The first-stage NGW-type planetary gear pair (121) is in series with the second-stage NGW-type planetary gear pair (122). The third external meshing gear pair (123) is sleeved on the second-stage NGW-type planetary gear pair (122). The fourth external meshing gear pair (124) is sleeved on the NGW-type planetary gear pair (13). The third external meshing gear pair (123) meshes with the fourth external meshing gear pair (124). The NGW-type planetary gear pair (13) is the output end, and the first-stage NGW-type planetary gear pair (121) is the input end. A differential transmission system (6) is provided at the output end of the gearbox assembly (1), and the differential transmission system (6) is connected to a potentiometer (61).

5. The electrically-driven rapid harpoon device for helicopter-assisted landing and takeoff according to claim 4, characterized in that: A multi-disc friction clutch (125) for adjusting torque is provided between the second-stage NGW-type planetary gear pair (122) and the third external meshing gear pair (123). The harpoon device protective cover (D) covers the gearbox assembly (1) and the harpoon device controller (B).

6. The electrically-driven rapid harpoon device for helicopter-assisted landing and takeoff according to claim 4, characterized in that: The lock head assembly (4) includes a locking mechanism (41) and an electromagnet assembly (42). A locking pin (43) is fixedly provided on the armature of the electromagnet assembly. Two claw hooks (45) arranged in parallel are hinged on the housing of the locking mechanism (41) through two rotating shafts (44). The two claw hooks (45) cooperate with the locking pin (43) to lock and unlock the grid (C).

7. The electrically-driven rapid harpoon device for helicopter assisted landing and takeoff according to claim 6, characterized in that: An unlocking rod (46) is provided on the locking mechanism (41).

8. The electrically-driven rapid harpoon device for helicopter assisted landing and takeoff according to claim 6, characterized in that: Two double-margin position switches (47) are provided above the interior of the lock head assembly (4).

9. The electrically-driven rapid harpoon device for helicopter assisted landing and takeoff according to claim 1, characterized in that: The mounting assembly (8) is mounted on the outer cylinder assembly (2). The mounting assembly (8) is connected to the body outside the cabin through a spherical surface (81) and a fixing nut (82). The mounting assembly (8) is connected to the outer cylinder assembly (2) inside the cabin through a spring (83). The spherical surface (81) enables the harpoon device actuating mechanism (A) to work normally within a yaw angle of 0 - 7°. The spring (83) enables the harpoon device actuating mechanism (A) to return to the vertical state.

10. The method of using the electric-driven rapid harpoon device for helicopter assisted landing and takeoff according to claim 8, characterized in that: It includes the following steps: Step 1, inside the gearbox assembly (1), the Hall signal of the brushless DC motor (5), the power signal of the brushless DC motor (5), and the signal of the potentiometer (61) are integrated and output after being filtered by a filter. The filtered signal is transmitted to the harpoon device controller (B) through a cable (7). Two double-margin position switches (47) judge the signal of the locking pin (43) in place, and the signal acquisition and status judgment are performed by the harpoon device controller (B). Step 2: According to the communication signal provided on the aircraft, the controller (B) of the harpoon device combines self-checking to judge the position state of the actuating mechanism (A) of the harpoon device, and sends out the action instructions for takeoff and landing. By controlling the brushless DC motor (5), high-speed movement or low-speed movement is achieved, and the function of the takeoff and landing of the harpoon device is realized. Cooperating with the locking and unlocking of the lock head assembly (4), the function of helicopter mooring is realized.

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