CN113212783B - Straightening mechanism and straightening method of carrier-based helicopter - Google Patents
Straightening mechanism and straightening method of carrier-based helicopter Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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- B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
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Abstract
The invention discloses a straightening mechanism and a straightening method of a ship-borne helicopter, wherein the straightening mechanism comprises a hydraulic cylinder group fixedly arranged on a shell, and the hydraulic cylinder group comprises a first fine cylinder with a telescopic rod facing one side and a second fine cylinder with a telescopic rod facing the other side, and a coarse cylinder; the end parts of the telescopic rods of the first fine cylinder and the second fine cylinder are respectively provided with a first movable pulley trolley and a second movable pulley trolley which move along with the telescopic rods, and the end parts of the telescopic rods of the coarse cylinders are also fixed with the second movable pulley trolley; the first movable pulley trolley and the second movable pulley trolley are respectively connected with the first speed doubling mechanism and the second speed doubling mechanism to drive the first paw and the second paw to rapidly move; meanwhile, a cable is not required to be connected with the aircraft in the straightening process, so that the operation is convenient, and the labor is saved.
Description
Technical Field
The invention relates to a straightening mechanism and a straightening method of a carrier-based helicopter, and belongs to the technical field of mechanical transmission.
Background
The ship-based helicopter takes a ship as a base, and performs activities such as anti-diving, reconnaissance and the like on the sea. When the ship sails on the sea or stays still, the ship is always in a swinging, lifting and fluctuating state under the action of sea surge, so that the helicopter is easy to sideslip or overturn when landing the ship. In order to improve the landing safety of the helicopter under complex sea conditions and enable the helicopter to stay on the ship relatively smoothly, the helicopter must be provided with a corresponding mooring and landing aid. Therefore, some methods are researched, and the methods such as a harpoon grid method (a deck fixing device) and a pull-down method are put into use at present, but a great amount of manual assistance is not needed, and when a descending guide is connected with a pull-down cable on a deck in severe weather conditions, the descending guide is influenced by factors such as ship body shaking, so that great potential safety hazards exist.
Disclosure of Invention
The technical problem to be solved by the invention is to provide the straightening mechanism of the ship-borne helicopter, which can realize rapid capturing of the helicopter by the paw and meet the capturing speed requirement; and when the helicopter is straightened, the claws cannot fall off the axle, thereby meeting the safety requirement.
Simultaneously, the straightening method of the carrier-based helicopter is provided, a cable is not required to be connected to the helicopter in the straightening process, the operation is convenient, and meanwhile, the labor is saved.
In order to solve the technical problems, the invention adopts the following technical scheme:
the straightening mechanism of the ship-borne helicopter comprises a hydraulic cylinder group fixedly arranged on a shell, wherein the hydraulic cylinder group comprises a first fine cylinder, a second fine cylinder and a coarse cylinder, wherein the first fine cylinder faces one side of a telescopic rod, and the second fine cylinder faces the other side of the telescopic rod; the end parts of the telescopic rods of the first fine cylinder and the second fine cylinder are respectively provided with a first movable pulley trolley and a second movable pulley trolley which move along with the telescopic rods, and the end parts of the telescopic rods of the coarse cylinders are also fixed with the second movable pulley trolley; the first movable pulley trolley and the second movable pulley trolley are respectively connected with the first speed doubling mechanism and the second speed doubling mechanism to drive the first claw and the second claw to rapidly move.
The technical scheme of the invention is further improved as follows: one side of the second movable pulley trolley is further provided with a fixed-length rod which sequentially penetrates through the hydraulic cylinder group and the first movable pulley trolley, one side of the first movable pulley trolley is provided with an electric push rod which is matched with the fixed-length rod to realize locking, and the end part of the fixed-length rod is provided with a pin hole corresponding to the position of the electric push rod.
The technical scheme of the invention is further improved as follows: the first movable pulley trolley and the second movable pulley trolley are respectively provided with pulleys which move along with the first movable pulley trolley and the second movable pulley trolley.
The technical scheme of the invention is further improved as follows: the first speed doubling mechanism comprises a third fixed pulley and a fourth fixed pulley which are respectively arranged at two sides of the first paw, the outer side of the first paw is connected with the end part of a fourth driving rope, and the fourth driving rope sequentially bypasses the fourth fixed pulley and a pulley on the first movable pulley trolley to be connected with the first tensioning device; the inner side of the first claw is connected with the end part of a third driving rope, and the third driving rope sequentially bypasses a third fixed pulley and a pulley on the first movable pulley trolley to be connected with a hydraulic cylinder group;
the second speed doubling mechanism comprises a first fixed pulley and a second fixed pulley which are respectively arranged at two sides of the second hand claw, the outer side of the second hand claw is connected with the end part of a first transmission rope, and the first transmission rope sequentially bypasses the first fixed pulley and a pulley on a second movable pulley trolley to be connected with a second tensioning device; the inner side of the second claw is connected with the end part of a second driving rope, and the second driving rope sequentially bypasses the second fixed pulley and the pulley on the second movable pulley trolley to be connected with the hydraulic cylinder group.
The technical scheme of the invention is further improved as follows: the first driving rope and the fourth driving rope are arranged as steel wire ropes, and the second driving rope and the third driving rope are arranged as driving chains.
The technical scheme of the invention is further improved as follows: the first and second fine cylinders have smaller inner diameters than the coarse cylinder, and the first and second fine cylinders are provided with instantaneous large flow by the accumulator, and the coarse cylinder is provided with stable small flow by the hydraulic pump.
In order to solve the technical problems, the invention adopts the following technical scheme:
a straightening method of a ship-borne helicopter utilizes a transverse transmission mechanism and two windlass which apply force to two sides of the transverse transmission mechanism to straighten the helicopter, and the straightening process comprises the following steps:
after landing, helicopters are divided into two cases:
first case: the centers of the two main wheels of the helicopter are not on the track center line, the central line of the helicopter is not parallel to the central line of the naval vessel, the front wheel of the helicopter is positioned at the point A, the centers of the two main wheels are positioned at the point o, and the straightening process comprises the following steps:
s1, rotating a front wheel of a helicopter by 90 degrees towards the direction of a track center line;
s2, pulling a winch positioned on one deflection side of a helicopter nose towards the front end at a pulling speed v 1 The method comprises the steps of carrying out a first treatment on the surface of the The winch at the other side pulls towards the rear end at a pulling speed v 2 The method comprises the steps of carrying out a first treatment on the surface of the Control winch v according to landing position of helicopter 1 And v 2 The instantaneous centers of the speed of the helicopter are all o points, so that two main wheels of the helicopter rotate around the central o point until the included angle between the central line of the helicopter and the central line of the naval vessel is 15 degrees, and at the moment, the front wheel of the helicopter reaches the point B;
s3, turning the front wheel of the helicopter back to a straight running position, and pulling the windlass at the two sides to the front end at a pulling speed upsilon 3 The method comprises the steps of carrying out a first treatment on the surface of the At the moment, the coarse cylinder of the transverse transmission mechanism moves to push the helicopter to move, so that the centers of two main wheels of the helicopter move to the central line of the ship, and the movement speed v of the coarse cylinder 4 The method comprises the steps of carrying out a first treatment on the surface of the The center of two main wheels of the helicopter runs from o point to P point by the combined motion of the winch and the coarse cylinder, and the front wheel of the helicopter reaches C point;
s4, rotating the front wheel of the helicopter by 90 degrees towards the direction of the central line of the track;
s5, pulling the winch positioned on one deflection side of the helicopter head to the front end at the pulling speed v 5 The method comprises the steps of carrying out a first treatment on the surface of the The winch at the other side pulls towards the rear end at a pulling speed v 5 The method comprises the steps of carrying out a first treatment on the surface of the The centers of two main wheels of the helicopter rotate around the point P until the center line of the helicopter coincides with the center line of the naval vessel; at the moment, the front wheel of the helicopter reaches the point D, and the front wheel of the helicopter is aligned to finish the alignment process;
second case: the centers of the two main wheels of the helicopter are positioned on the track center line, the central line of the helicopter is not parallel to the central line of the naval vessel, the front wheel of the helicopter is positioned at the point C, the centers of the two main wheels are positioned at the point P, and the helicopter is directly straightened according to the steps S4 and S5.
The technical scheme of the invention is further improved as follows: said velocity v 1 And v 2 The instantaneous centers of the speed of the helicopter are all o points, so that the two main wheels of the helicopter rotate around the central o point; said velocity v 3 And v 4 The synthesized speed v direction is from o point to P point, so that the helicopter moves linearly along the oP direction; the two partsSpeed v of hoist 5 The two main wheels of the helicopter rotate around the center P point due to the fact that the two main wheels are equal in size and opposite in direction.
The technical scheme of the invention is further improved as follows: in the straightening process of the helicopter, the electric push rod locks the fixed-length rod, so that the distance between the first movable pulley trolley and the second movable pulley trolley is limited to be unchanged, namely, the first claw and the second claw are fixed on the shaft of the helicopter, and the first claw and the second claw are prevented from falling off.
By adopting the technical scheme, the invention has the following technical progress:
the straightening mechanism of the ship-based helicopter can realize rapid capture of the helicopter by the paw, and meets the requirement of capturing speed; when the helicopter is straightened, the claws cannot fall off the axle, so that the safety requirement is met; simultaneously, the helicopter straightening method is provided, a mooring rope is not required to be connected to an airplane in the straightening process, the operation is convenient, and meanwhile, the labor is saved; the computer can intelligently match the traction speed of the winch according to the landing position of the helicopter, so that the automation degree is high; the straightening path consists of two parts of fixed-point rotation and linear motion, is simple to operate, has low professional requirements on staff, and is favorable for improving the success rate of traction.
According to the invention, after the claws capture the wheel shafts, the fixed length rod can be locked by the electric push rod, so that the distance between the two movable pulley trolleys is limited, the two movable pulley trolleys are fixed with each other, and the double claws are prevented from falling off from the wheel shafts.
The speed doubling mechanism can realize double amplification of the speed and the stroke of the hydraulic cylinder group so as to meet the requirement of capturing speed and save the installation space; the transmission structure of combining the transmission chain and the steel wire rope is adopted, the inner side of the hand claw is wound by the transmission chain, the hand claw clamping force is provided, the rigidity of the chain is high, the chain is not easy to deform due to stretching, and the clamping wheel shaft is reliable; the outer sides of the claws are wound by steel wire ropes, the steel wire ropes are high in strength and stable in work, the pull resistance is superior to that of a chain, and sudden fracture is avoided; in addition, the head end of the steel wire rope is provided with a tensioning device, when the steel wire rope is loosened, the tensioning device is used for tensioning, and the speed doubling mechanism is kept in an optimal state all the time; the two claws can move independently and do not interfere with each other.
The invention adopts hydraulic drive, has large power, compact structure, small volume, light weight and good impact resistance, and can well finish the capturing, straightening and releasing of the double-claw quick mooring device to the helicopter under complex sea conditions.
The small cylinder has small inner diameter, the energy accumulator provides instantaneous large flow, the action speed is high, and the rapid capturing action of the paw can be realized; the coarse cylinder has large inner diameter, the hydraulic pump supplies stable small flow, the action speed is low, the large straightening force is provided, and the transverse straightening process of the ship-borne helicopter can be realized by matching with the longitudinal traction of the external winch.
Drawings
FIG. 1 is a schematic view of the assembly of the present invention;
FIG. 2 is a schematic diagram of the structure of the present invention;
FIG. 3 is an assembled view of the hydraulic cylinder of the present invention;
FIG. 4 is a schematic illustration of the present invention for unlocking and locking a fixed length lever;
FIG. 5 is a schematic view of a captured helicopter hub of the present invention;
FIG. 6 is a schematic illustration of a position of the helicopter of the invention after landing;
FIG. 7A is a schematic illustration of the front wheel at point A of the helicopter alignment process of the present invention;
FIG. 7B is a schematic view of the front wheel at point B of the helicopter alignment process of the present invention;
FIG. 7C is a schematic view of the front wheel at point C of the helicopter alignment process of the present invention;
FIG. 7D is a schematic view of the front wheel at point D of the helicopter alignment process of the present invention;
wherein, 1, a first tensioning device, 2, an electric push rod, 3, a first movable pulley trolley, 4, a fixed length rod, 5, a hydraulic cylinder group, 5-1, a coarse cylinder, 5-2, a second fine cylinder, 5-3, a first fine cylinder, 6, a second movable pulley trolley, 7, a second tensioning device, 8, a first fixed pulley, 9, a first driving rope, 10, a second claw, 11, a second driving rope, 12, a second fixed pulley, 13, a third fixed pulley, 14, a third driving rope, 15, a first claw, 16, a fourth driving rope, 17, a fourth fixed pulley, 18 and a winch.
Detailed Description
The application of the present invention to a dual claw quick mooring device for a helicopter on board is described in detail below with reference to the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, and the protection scope of the present invention is more clearly and definitely defined.
As shown in fig. 1 and 2, the design concept of the straightening mechanism of the ship-based helicopter is that the helicopter falls directly onto a preset area of a deck, is then quickly locked by a double-claw quick mooring device, and then is straightened, and the operation is automatically completed without deck staff. The hydraulic cylinder assembly 5 is fixed at the middle position of the shell.
As shown in fig. 3, the hydraulic cylinder group 5 includes a first fine cylinder 5-3 with a telescopic rod facing one side and a second fine cylinder 5-2 with a telescopic rod facing the other side, and a coarse cylinder 5-1, wherein the coarse cylinder 5-1 is arranged above, and the first fine cylinder 5-3 and the second fine cylinder 5-2 are arranged below the coarse cylinder 5-1 side by side in one embodiment of the present invention; the inner diameters of the first fine cylinder 5-3 and the second fine cylinder 5-2 are small, the energy accumulator provides instantaneous large flow, the action speed is high, and the rapid capturing action of the paw can be realized; the inner diameter of the coarse cylinder 5-1 is large, the hydraulic pump supplies stable small flow, the action speed is low, a large straightening force is provided, and the transverse straightening process of the carrier-based helicopter can be realized by matching with the longitudinal traction of the external winch.
The first movable pulley trolley 3 is fixedly connected with the piston rod of the first fine cylinder 5-3, the second movable pulley trolley 6 is fixedly connected with the piston rods of the coarse cylinder 5-1 and the second fine cylinder 5-2, and the first movable pulley trolley 3 and the second movable pulley trolley 6 can slide independently along with the corresponding piston rods.
The electric push rod 2 is fixed on the side wall of the first movable pulley trolley 3; one end of the fixed length rod 4 is fixed on the second movable pulley trolley 6, the fixed length rod can sequentially pass through the hydraulic cylinder group 5 and the first movable pulley trolley 3 along with the sliding of the second movable pulley trolley 6, a pin hole is formed in the other end of the fixed length rod, when the capturing of a helicopter wheel shaft is completed, the fixed length rod can be locked by the electric push rod 2, the distance between the first movable pulley trolley 3 and the second movable pulley trolley 6 is fixed, the distance between the first claw 15 and the second claw 10 is further limited, and the first claw 15 and the second claw 10 are prevented from falling off from a wheel shaft; fig. 4 is a schematic diagram showing the unlocking and locking states of the fixed-length rod.
The two sides of the first claw 15 are respectively provided with a third fixed pulley 13 and a fourth fixed pulley 17; the outer side of the first claw 15 is connected with the end part of a fourth driving rope 16, and the fourth driving rope 16 sequentially bypasses a fourth fixed pulley 17 and a pulley on the first movable pulley trolley 3 to be connected with the first tensioning device 1; the inner side of the first claw 15 is connected with the end part of a third driving rope 14, and the third driving rope 14 sequentially bypasses the third fixed pulley 13 and the pulley on the first movable pulley trolley 3 to be connected with the hydraulic cylinder group 5.
The two sides of the second paw 10 are respectively provided with a first fixed pulley 8 and a second fixed pulley 12, the outer side of the second paw 10 is connected with the end part of a first driving rope 9, and the first driving rope 9 sequentially bypasses the pulleys on the first fixed pulley 8 and the second movable pulley trolley 6 and is connected with a second tensioning device 7; the inner side of the second claw 10 is connected with the end part of a second driving rope 11, and the second driving rope 11 sequentially bypasses a second fixed pulley 12 and a pulley on a second movable pulley trolley 6 to be connected with the hydraulic cylinder group 5.
The first driving rope 9 and the fourth driving rope 16 are provided as steel wire ropes, and the second driving rope 11 and the third driving rope 14 are provided as driving chains.
The basic principle of the invention is that under the action of the hydraulic cylinder group 5, the two claws can independently finish capturing the axle of the helicopter within a limited time through the speed doubling and range increasing effect of the speed doubling mechanism, as shown in fig. 5, then the distance between the two claws is limited under the action of the fixed length rod 4, the claws are ensured not to fall off from the axle, and then the transverse alignment of the ship-borne helicopter is realized under the comprehensive action of the coarse cylinder 5-1 and the external winch 18, and finally the ship-borne helicopter is towed and put in storage.
The following description is made with reference to specific examples.
Example 1:
the ship-based helicopter falls in a preset area, the double-claw quick mooring device tracks to a capturable position, the piston rods of the first fine cylinder 5-3 and the second fine cylinder 5-2 are in a retracted state at the beginning, and the coarse cylinder 5-1 is in a follow-up state; the first fine cylinder 5-3 and the second fine cylinder 5-2 are driven by an energy accumulator to extend out of piston rods, so that the first movable pulley trolley 3 and the second movable pulley trolley 6 are respectively driven to slide to two sides, and the second claw 10 and the first claw 15 are driven by a first driving rope 9, a fourth driving rope 16, a second driving rope 11 and a third driving rope 14 to capture a wheel shaft; after the capturing action is finished, the fixed length rod 4 is locked under the action of the electric push rod 2, so that the distance between the first movable pulley trolley 3 and the second movable pulley trolley 6 is kept unchanged, namely the second claw 10 and the first claw 15 are fixed on a helicopter wheel shaft, and the first claw is prevented from falling off; then, as shown in fig. 6 and 7, the coarse cylinder 5-1 is driven by the hydraulic pump to drive the helicopter limited by the second paw 10 and the first paw 15 to do transverse movement, and the longitudinal traction movement of the external winch is matched, so that the combined movement of the two realizes the straightening action. After straightening, the helicopter is pulled and put in storage, the electric push rod 2 is retracted, the fixed-length rod 4 is unlocked, the piston rods of the first fine cylinder 5-3 and the second fine cylinder 5-2 are retracted, and the second paw 10 and the first paw 15 are driven by the speed doubling mechanism to release the helicopter.
Straightening:
the helicopter is straightened by using the transverse transmission mechanism and two windlass 18 respectively applied to the two sides of the transverse transmission mechanism, and the straightening process comprises the following steps:
after landing, helicopters are divided into two cases:
first case: as shown in fig. 6, the centers of two main wheels of the helicopter are not on the central line of the track, and the central line of the helicopter is not parallel to the central line of the ship, at this time, the front wheel of the helicopter is located at the point a, the centers of the two main wheels are located at the point o, and the straightening process comprises the following steps:
s1, rotating a front wheel of the helicopter by 90 degrees towards the direction of the central line of the track, as shown in FIG. 7A;
s2, a winch 18 positioned on one deflection side of a helicopter nose pulls towards the front end, namely the nose end, and the pulling speed upsilon 1 The method comprises the steps of carrying out a first treatment on the surface of the The windlass 18 at the other side pulls towards the rear end, namely the tail end, and the pulling speed v 2 The method comprises the steps of carrying out a first treatment on the surface of the Control winch v according to landing position of helicopter 1 And v 2 The instantaneous centers of the speed of the helicopter are o points, and the two main wheels of the helicopter are intelligently matched through a computer, so that the two main wheels of the helicopter rotate around the central o point until the included angle between the central line of the helicopter and the central line of the naval vessel is 15 degrees, and at the moment, the front wheel of the helicopter reaches the point B, as shown in fig. 7B;
s3, turning the front wheel of the helicopter back to a straight running position, and pulling the windlass 18 at both sides to the front end, namely the nose end, wherein the pulling speed v 3 The method comprises the steps of carrying out a first treatment on the surface of the At the moment, the coarse cylinder 5-1 of the transverse transmission mechanism moves to push the helicopter to move, so that the centers of two main wheels of the helicopter move towards the neutral line of the ship, and the movement speed v of the coarse cylinder 5-1 4 The method comprises the steps of carrying out a first treatment on the surface of the Velocity v 3 And v 4 The synthesized speed v direction is from o point to P point, the center of two main wheels of the helicopter runs from o point to P point by the synthesized motion of the winch 18 and the coarse cylinder 5-1, and the front wheel of the helicopter reaches C point as shown in fig. 7C;
s4, rotating the front wheel of the helicopter by 90 degrees towards the direction of the central line of the track;
s5, a winch 18 positioned on one deflection side of the helicopter nose pulls towards the front end, namely the nose end, and the pulling speed upsilon 5 The method comprises the steps of carrying out a first treatment on the surface of the The windlass 18 at the other side pulls towards the rear end, namely the tail end, and the pulling speed v 5 The method comprises the steps of carrying out a first treatment on the surface of the Velocity v of two windlass 5 The two main wheels of the helicopter rotate around the point P until the central line of the helicopter coincides with the central line of the naval vessel; at this time, the front wheel of the helicopter reaches the point D, and as shown in FIG. 7D, the front wheel of the helicopter is aligned to finish the alignment process;
second case: the centers of the two main wheels of the helicopter are positioned on the track center line, the central line of the helicopter is not parallel to the central line of the naval vessel, the front wheel of the helicopter is positioned at the point C, the centers of the two main wheels are positioned at the point P, and the helicopter is directly straightened according to the steps S4 and S5.
The foregoing description is only illustrative of the present invention and is not intended to limit the scope of the invention, and all equivalent structures or equivalent processes or direct or indirect application in other related technical fields are included in the scope of the present invention.
Claims (7)
1. The utility model provides a straightening mechanism of carrier-borne helicopter which characterized in that: the hydraulic cylinder assembly comprises a hydraulic cylinder assembly (5) fixedly arranged on a shell, wherein the hydraulic cylinder assembly (5) comprises a first fine cylinder (5-3) with a telescopic rod facing one side, a second fine cylinder (5-2) with a telescopic rod facing the other side and a coarse cylinder (5-1); the ends of the telescopic rods of the first fine cylinder (5-3) and the second fine cylinder (5-2) are respectively provided with a first movable pulley trolley (3) and a second movable pulley trolley (6) which move along with the telescopic rods, and the ends of the telescopic rods of the coarse cylinder (5-1) are also fixed with the second movable pulley trolley (6); the first movable pulley trolley (3) and the second movable pulley trolley (6) are respectively connected with the first speed doubling mechanism and the second speed doubling mechanism to drive the first claw (15) and the second claw (10) to rapidly move;
pulleys which move along with the first movable pulley trolley (3) and the second movable pulley trolley (6) are respectively arranged on the first movable pulley trolley (3) and the second movable pulley trolley (6);
the first speed doubling mechanism comprises a third fixed pulley (13) and a fourth fixed pulley (17) which are respectively arranged at two sides of the first claw (15), the outer side of the first claw (15) is connected with the end part of a fourth transmission rope (16), and the fourth transmission rope (16) sequentially bypasses the fourth fixed pulley (17) and a pulley on the first movable pulley trolley (3) to be connected with the first tensioning device (1); the inner side of the first claw (15) is connected with the end part of a third driving rope (14), and the third driving rope (14) sequentially bypasses a third fixed pulley (13) and a pulley on the first movable pulley trolley (3) to be connected with the hydraulic cylinder group (5);
the second speed doubling mechanism comprises a first fixed pulley (8) and a second fixed pulley (12) which are respectively arranged at two sides of a second claw (10), the outer side of the second claw (10) is connected with the end part of a first transmission rope (9), and the first transmission rope (9) sequentially bypasses the first fixed pulley (8) and a pulley on a second movable pulley trolley (6) to be connected with a second tensioning device (7); the inner side of the second claw (10) is connected with the end part of a second driving rope (11), and the second driving rope (11) sequentially bypasses a second fixed pulley (12) and a pulley on a second movable pulley trolley (6) to be connected with a hydraulic cylinder group (5).
2. The straightening mechanism of a carrier-based helicopter according to claim 1, wherein: one side of the second movable pulley trolley (6) is further provided with a fixed length rod (4) which sequentially penetrates through the hydraulic cylinder group (5) and the first movable pulley trolley (3), one side of the first movable pulley trolley (3) is provided with an electric push rod (2) which is matched with the fixed length rod (4) to realize locking, and the end part of the fixed length rod (4) is provided with a pin hole corresponding to the position of the electric push rod (2).
3. The straightening mechanism of a carrier-based helicopter according to claim 1, wherein: the first driving rope (9) and the fourth driving rope (16) are arranged as steel wire ropes, and the second driving rope (11) and the third driving rope (14) are arranged as driving chains.
4. The straightening mechanism of a carrier-based helicopter according to claim 1, wherein: the first fine cylinder (5-3) and the second fine cylinder (5-2) have smaller inner diameters than the coarse cylinder (5-1), and the first fine cylinder (5-3) and the second fine cylinder (5-2) are provided with instantaneous large flow by an accumulator, and the coarse cylinder (5-1) is provided with stable small flow by a hydraulic pump.
5. A method of straightening using a straightening mechanism of a carrier-based helicopter as claimed in any one of claims 1 to 4, characterized in that: the helicopter is straightened by utilizing a straightening mechanism and two windlass (18) which are respectively applied to two sides of the straightening mechanism, and the straightening process comprises the following steps:
after landing, helicopters are divided into two cases:
first case: the centers of the two main wheels of the helicopter are not on the track center line, the central line of the helicopter is not parallel to the central line of the naval vessel, the front wheel of the helicopter is positioned at the point A, the centers of the two main wheels are positioned at the point o, and the straightening process comprises the following steps:
s1, rotating a front wheel of a helicopter by 90 degrees towards the direction of a track center line;
s2, a winch (18) positioned on one deflection side of a helicopter nose pulls towards the front end, and the pulling speed v 1 The method comprises the steps of carrying out a first treatment on the surface of the The winch (18) at the other side pulls towards the rear end at a pulling speed v 2 The method comprises the steps of carrying out a first treatment on the surface of the Control winch v according to landing position of helicopter 1 And v 2 Velocity instant center of (2)The point is o, so that two main wheels of the helicopter rotate around the central point o until the included angle between the central line of the helicopter and the central line of the naval vessel is 15 degrees, and at the moment, the front wheel of the helicopter reaches the point B;
s3, turning the front wheel of the helicopter back to a straight running position, and pulling windlass (18) at two sides to the front end at a pulling speed v 3 The method comprises the steps of carrying out a first treatment on the surface of the At the moment, the coarse cylinder (5-1) of the straightening mechanism moves to push the helicopter to move, so that the centers of two main wheels of the helicopter move towards the center line of the ship, and the movement speed v of the coarse cylinder (5-1) is higher than that of the ship 4 The method comprises the steps of carrying out a first treatment on the surface of the The combined motion of the winch (18) and the coarse cylinder (5-1) enables the centers of two main wheels of the helicopter to run from o point to P point, and the front wheel of the helicopter reaches C point;
s4, rotating the front wheel of the helicopter by 90 degrees towards the direction of the central line of the track;
s5, a winch (18) positioned on one deflection side of the helicopter head drags towards the front end, and the traction speed v 5 The method comprises the steps of carrying out a first treatment on the surface of the The winch (18) at the other side pulls towards the rear end at a pulling speed v 5 The method comprises the steps of carrying out a first treatment on the surface of the The centers of two main wheels of the helicopter rotate around the point P until the center line of the helicopter coincides with the center line of the naval vessel; at the moment, the front wheel of the helicopter reaches the point D, and the front wheel of the helicopter is aligned to finish the alignment process;
second case: the centers of the two main wheels of the helicopter are positioned on the track center line, the central line of the helicopter is not parallel to the central line of the naval vessel, the front wheel of the helicopter is positioned at the point C, the centers of the two main wheels are positioned at the point P, and the helicopter is directly straightened according to the steps S4 and S5.
6. The method for straightening a carrier-borne helicopter according to claim 5, wherein the method comprises the following steps: said velocity v 1 And v 2 The instantaneous centers of the speed of the helicopter are all o points, so that the two main wheels of the helicopter rotate around the central o point; said velocity v 3 And v 4 The synthesized speed v direction is from o point to P point, so that the helicopter moves linearly along the oP direction; the speeds v of the two windlass 5 The two main wheels of the helicopter rotate around the center P point due to the fact that the two main wheels are equal in size and opposite in direction.
7. The method for straightening a carrier-borne helicopter according to claim 5, wherein the method comprises the following steps: in the straightening process of the helicopter, the electric push rod (2) locks the fixed-length rod (4), the distance between the first movable pulley trolley (3) and the second movable pulley trolley (6) is limited to be unchanged, namely, the first claw (15) and the second claw (10) are fixed on the shaft of the helicopter, and the first claw and the second claw are prevented from falling off.
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| US4529152A (en) * | 1982-09-13 | 1985-07-16 | Societe Nationale Industrielle Aerospatiale | Devices for maneuvering helicopters on a ship's deck |
| CN109850177A (en) * | 2018-11-29 | 2019-06-07 | 中国船舶工业系统工程研究院 | A method of being quickly tethered at operation on the sea helicopter |
| CN112340047A (en) * | 2020-10-20 | 2021-02-09 | 燕山大学 | Straight track-based automatic ship-based helicopter traction device and method |
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