CN110030874B - Swing rod withdrawing system for automatic zero-second swinging of rocket during takeoff - Google Patents
Swing rod withdrawing system for automatic zero-second swinging of rocket during takeoff Download PDFInfo
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- CN110030874B CN110030874B CN201910251607.XA CN201910251607A CN110030874B CN 110030874 B CN110030874 B CN 110030874B CN 201910251607 A CN201910251607 A CN 201910251607A CN 110030874 B CN110030874 B CN 110030874B
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- swing rod
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- locking
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
Abstract
A rocket take-off zero-second automatic swinging rod withdrawing system comprises: the device comprises a primary withdrawing mechanism, a secondary withdrawing mechanism, a swing rod and a locking buffer device. The first-stage withdrawing mechanism is arranged on the umbilical tower, and one end of the swing rod is fixedly connected with the first-stage withdrawing mechanism; the swing rod is provided with a pipeline for filling operation to the rocket, and the other end of the swing rod is attached to the rocket core stage during filling operation; in the launching process of the rocket, the first-stage withdrawing mechanism drives the swing rod to rotate in a vertical plane, so that the other end of the swing rod is attached to the umbilical tower; the rotation plane of the swing rod passes through the axis of the rocket; a locking buffer device is arranged at the position where the other end of the swing rod is attached to the umbilical tower; the locking buffer device is used for absorbing impact force generated by rotation of the swing rod and locking and fixing the other end of the swing rod on the umbilical tower. The invention can quickly and safely realize the withdrawing and locking, avoids the flying and drifting space of the rocket in the swinging process of the oscillating bar, and has high reliability and a redundant swinging mechanism.
Description
Technical Field
The invention relates to a swing rod withdrawing system capable of automatically swinging back in zero second during taking off of a rocket, and belongs to the technical field of rocket launching devices.
Background
The existing rocket withdrawing system adopts an encircling horizontal swinging mode, swinging movement is completed within 1-2 minutes before the rocket is ignited to take off from two sides of the rocket within a safety range, the swinging angle is larger than 90 degrees, requirements on running time and speed are low, and a redundant withdrawing mechanism and an automatic locking mechanism are not provided.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the swing rod withdrawing system can provide installation and support for various pipeline lines such as filling, air supply, cables and the like; and in the rocket launching stage, the rocket launching channel is quickly and reliably swung back to be made free, and the buffering and automatic locking functions are realized after the rocket launching channel is in place.
The technical scheme of the invention is as follows:
a rocket take-off zero-second automatic swinging rod withdrawing system comprises: the primary withdrawing mechanism, the secondary withdrawing mechanism, the swing rod and the locking buffer device;
the first-stage withdrawing mechanism is arranged on the umbilical tower, and one end of the swing rod is fixedly connected with the first-stage withdrawing mechanism; the swing rod is provided with a pipeline for filling operation to the rocket, and the other end of the swing rod is attached to the core stage of the rocket during filling operation; in the launching process of the rocket, the first-stage withdrawing mechanism drives the swing rod to rotate in a vertical plane, so that the other end of the swing rod is attached to the umbilical tower; the rotation plane of the swing rod passes through the axis of the rocket;
a locking buffer device is arranged at the position where the other end of the swing rod is attached to the umbilical tower; the locking buffer device is used for absorbing the impact force generated by the rotation of the swing rod and locking and fixing the other end of the swing rod on the umbilical tower;
during filling operation, the safe included angle alpha between the oscillating bar and the horizontal plane meets the following requirements:
wherein, x (h)0) The takeoff drift amount h of the rocket in the horizontal direction0The vertical height difference from the top end of the rocket booster to the axis of the rotating shaft of the swing rod is shown, S is a safety distance design value, the range of S is 1-3 m, L is the length of the swing rod, and D is the horizontal distance from the axis of the rotating shaft of the swing rod to the outer wall of the core stage of the rocket.
The locking buffer device comprises: the locking device comprises an unlocking cylinder, a spring, a locking pin, a locking seat, a movable cushion pad, a fixed cushion pad, a buffer cylinder and a sleeve;
the locking seat and the movable buffer cushion are fixed on the swing rod;
a fixed cushion pad is arranged at the position where the locking seat is attached to the umbilical tower, and the buffer cylinder is fixed on the fixed cushion pad; in the process that the swing rod is attached to the umbilical tower, a piston rod of the buffer cylinder pushes against the movable buffer pad to absorb the impact force generated by the rotation of the swing rod;
one end of the lock pin is sleeved with a spring and then is connected with the unlocking cylinder; the spring is sleeved with a sleeve, and the other end of the lock pin extends out of the sleeve under the action of the elastic force of the spring; the sleeve and the unlocking cylinder are respectively and fixedly connected with the umbilical tower;
the locking seat is provided with a guide slideway and a blind hole, in the process that the swing rod is attached to the umbilical tower, the other end of the lock pin slides into the blind hole along the guide slideway, and meanwhile, the cylinder is unlocked to lock the lock pin.
The first-stage withdrawing mechanism comprises: a gear, a rack and a driving oil cylinder;
the driving oil cylinder is fixed on the umbilical tower, the gear and the rack are meshed with each other, and the gear is fixedly connected with one end of the oscillating bar; the driving oil cylinder is used for driving the rack to enable the gear to rotate.
The secondary withdrawing mechanism is arranged on the umbilical tower; the secondary withdrawing mechanism comprises: the device comprises a winch, a fixed pulley, a movable pulley and a steel wire rope;
the winch and the fixed pulley are fixed on the umbilical tower, and the movable pulley is fixed at the other end of the oscillating bar; one end of the steel wire rope is connected with the winch, and the other end of the steel wire rope is fixed on the umbilical tower after sequentially passing around the fixed pulley and the movable pulley.
The swing rod is of a truss structure formed by welding pipe profiles, the width of the cross section of the swing rod is larger than 1m, the height of the cross section of the swing rod is larger than 2m, the swing rod is used for installing a filling pipeline, and an operator can pass through the interior of the swing rod.
A method for withdrawing the swing rod by using the swing rod withdrawing system comprises the following steps:
1) when the swing rod receives a withdrawing signal, the driving oil cylinder drives the rack to move, the rack drives the gear to rotate, and then the swing rod rotates towards the umbilical tower;
2) the piston rod of the buffer cylinder is contacted with the movable buffer cushion, and the fixed buffer cushion is contacted with the locking seat, so that the impact force generated by the rotation of the swing rod is absorbed; meanwhile, the lock pin slides into the blind hole along the guide slideway by using the elasticity of the spring;
3) and locking the lock pin by using an unlocking cylinder to finish the withdrawing work of the swing rod.
A method for withdrawing the swing rod by using the swing rod withdrawing system comprises the following steps:
1) when the oscillating bar receives a withdrawing signal, the oil cylinder is driven to drive the rack to move, the rack drives the gear to rotate, whether the rack is driven to move or not is judged within 0-0.2 s after the oscillating bar receives the withdrawing signal, if the rack is driven to move, the step 3) is carried out, and if the rack is not driven to move, the step 2) is carried out;
2) starting a winch to contract the steel wire rope, enabling the swing rod to rotate towards the umbilical tower, and entering the step 3);
3) the push rod of the buffer cylinder is contacted with the movable buffer cushion, and the fixed buffer cushion is contacted with the locking seat, so that the impact force generated by the rotation of the swing rod is absorbed; meanwhile, the lock pin slides into the blind hole along the guide slideway, and the step 4) is carried out;
4) and locking the lock pin by using an unlocking cylinder to finish the withdrawing work of the swing rod.
Compared with the prior art, the invention has the beneficial effects that:
1) the swing rod rotating plane of the withdrawing system passes through the axis of the rocket, namely the projection of the swing rod on the horizontal plane is in the radial direction of the rocket; meanwhile, the withdrawing system comprises a locking buffer device, the swinging back of the rocket can be realized within 3.42s from the ignition of the rocket by 45 degrees so as to avoid the takeoff interference of the swing rod and the rocket body, and meanwhile, the swing rod is automatically and reliably locked with the umbilical tower after being withdrawn in place, so that the high-reliability and high-safety withdrawing of the connector driven by the swing rod is realized;
2) the withdrawing system comprises a primary withdrawing mechanism and a secondary withdrawing mechanism, if the primary withdrawing mechanism fails, the primary withdrawing mechanism is provided with a standby secondary withdrawing mechanism, the swing rod is forcibly swung back, and the primary withdrawing mechanism has high reliability;
3) the locking buffer device is provided with the buffer pad for absorbing impact force, and the lock pin is locked and fixed after sliding into the blind hole along the guide slideway, so that the locking buffer device has a guide positioning function and is safe and reliable.
Drawings
FIG. 1 is a schematic view of a swing link retracting system according to the present invention;
FIG. 2 is a schematic diagram of a first level withdrawal mechanism of the present invention;
FIG. 3 is a schematic diagram of a secondary retraction mechanism of the present invention;
FIG. 4 is a schematic view of the locking buffer of the present invention;
FIG. 5 is a schematic view of the pendulum rod and rocket core stage retraction positions of the present invention.
Detailed Description
The invention relates to a swing rod withdrawing system capable of automatically swinging back in zero second during taking off of a rocket, which is an important component device of a launch platform of a carrier rocket. The swing rod 3 is used for laying various pipeline lines such as filling, air supply, cables, air conditioners and the like, and the swing rod 3 is positioned in the middle of one side of the umbilical tower 5, which faces the rocket 6, and corresponds to the position of a core stage of the rocket 6. One end of the swing rod 3 is fixed on the umbilical tower 5, the other end of the swing rod 3 is attached to the core level of the rocket 6, and each pipeline is connected with the rocket 6 through a connector. The swing rod 3 keeps the connection state of various pipelines, connectors and cables unchanged in the transportation process, and drives the detached connectors, pipelines, joints and the like to swing within a safety range in the rocket takeoff process.
The invention can meet the requirement that a part of connectors required by a novel carrier rocket keep a connection working state until the rocket takes off. The swing rod 3 swings back to the driving system to start when the rocket takes off for zero second, and drives the fallen connector to automatically swing back to the designated position of the umbilical tower 5 and be completely locked. The zero-second swing rod needs to strictly meet the requirement of a takeoff time sequence of the rocket, quickly and safely swings back to a locking position, avoids a takeoff drift space of the rocket in the swinging back process, and has high reliability and a redundant swinging back mechanism. Meanwhile, the requirement that the connector is not required to be butted and filled again when the propellant is discharged can be met, the zero-second swing rod is required to strictly meet the requirement of the takeoff time sequence of the rocket, and the high-reliability and redundant swing mechanism is provided.
A system for withdrawing a swing rod automatically swinging back in zero second during taking off of a rocket comprises: a primary withdrawing mechanism 1, a secondary withdrawing mechanism 2, a swing rod 3 and a locking buffer device 4. The primary withdrawing mechanism 1 adopts a driving oil cylinder 103 to push a rack 102 connected with the primary withdrawing mechanism, a driving gear 101 rotates, and the gear 101 drives the swing rod 3 to swing around a main shaft 105 in a vertical plane. The second-stage withdrawing mechanism 2 is arranged on the umbilical tower 5, and a reel steel wire rope traction mode is adopted to realize the withdrawing redundancy arrangement. The locking buffer device 4 is arranged on one side of the umbilical tower 5 facing the rocket 6 and used for absorbing impact generated when the swing rod 3 automatically swings back;
after the swing rod 3 swings to the umbilical tower 5 in place, the automatic locking of the position between the swing rod 3 and the umbilical tower 5 is realized by the spring 402 and the lock pin 403; during unlocking, the unlocking cylinder 401 drives the lock pin 403 to be pulled out, so that automatic unlocking of the swing rod structure is realized; the swinging motion of the swing rod 3 can avoid the takeoff interference space of the rocket body, and a safety distance S is reserved between the swing rod and the rocket 6.
The withdrawal process is roughly:
1) the rocket system sends a takeoff zero second signal, the connector for connecting each filling pipeline with the rocket receives the falling-off signal, and the filling pipelines and the rocket 6 are separated;
2) the withdrawing system receives the swing back signal, the driving system of the swing rod 3 responds to the swing back signal, the swing rod 3 is driven to swing back in an accelerated mode, and the takeoff drift space of the rocket 6 is avoided according to the specified time sequence and the speed curve;
3) under the condition that the primary withdrawing mechanism 1 works effectively, the secondary withdrawing mechanism 2 winds the steel wire rope 204 in a follow-up manner and keeps the steel wire rope 204 tensioned; under the condition that the primary withdrawing mechanism 1 is in fault, the secondary withdrawing mechanism 2 is immediately switched to a working state from a hot backup/follow-up state to perform swinging withdrawing of the swing rod 3;
4) the swing rod 3 is completely retracted to a designated position after swinging back to 45 degrees within 3.42 seconds from the rocket ignition, before being flushed by the rocket gas flow, after the impact is absorbed by the buffer cylinder 408 and the movable buffer pad 406, the in-place signal is detected, and the locking pin 403 and the locking seat 405 are automatically locked.
The present invention is described in further detail below with reference to the attached drawings.
As shown in fig. 1, a primary withdrawing mechanism 1 is installed on an umbilical tower 5, and one end of a swing rod 3 is fixedly connected with the primary withdrawing mechanism 1; the swing rod 3 is provided with a pipeline for filling operation to the rocket 6, and the other end of the swing rod 3 is attached to the core level of the rocket 6 during the filling operation; in the launching process of the rocket, the primary withdrawing mechanism 1 drives the swing rod 3 to rotate in a vertical plane, so that the other end of the swing rod 3 is attached to the umbilical tower 5; the rotation plane of the swing rod 3 passes through the axis of the rocket 6; the swing rod 3 is of a truss structure formed by welding pipe profiles, the section width of the swing rod 3 is larger than 1m, the section height of the swing rod 3 is larger than 2m, the swing rod 3 is used for installing a filling pipeline, and an operator can pass through the interior of the swing rod 3.
A locking buffer device 4 is arranged at the position where the other end of the swing rod 3 is attached to the umbilical tower 5; the locking buffer device 4 is used for absorbing impact force generated by rotation of the swing rod 3 and locking and fixing the other end of the swing rod 3 on the umbilical tower 5;
during filling operation, as shown in fig. 5, the safe included angle α between the swing rod 3 and the horizontal plane satisfies:
wherein, x (h)0) The takeoff drift amount h of the rocket in the horizontal direction0The vertical height difference from the top end of the rocket booster to the axis of the rotating shaft of the swing rod 3 is shown, S is a safety distance design value, the range of S is 1 m-3 m, the value in the embodiment of the invention is 2m, L is the length of the swing rod 3, and D is the horizontal distance from the axis of the rotating shaft of the swing rod 3 to the outer wall of the core stage of the rocket 6.
As shown in fig. 4, the locking buffer device 4 includes: an unlocking cylinder 401, a spring 402, a locking pin 403, a locking seat 405, a movable cushion 406, a fixed cushion 407, a buffer cylinder 408 and a sleeve 409;
the locking seat 405 and the movable buffer cushion 406 are fixed on the swing rod 3;
a fixed cushion 407 is arranged at the position where the locking seat 405 is attached to the umbilical tower 5, and the cushion cylinder 408 is fixed on the fixed cushion 407; in the process that the swing rod 3 is attached to the umbilical tower 5, a piston rod of the buffer cylinder 408 pushes against the movable buffer pad 406 to absorb the impact force generated by the rotation of the swing rod 3.
One end of the lock pin 403 is sleeved with a spring 402 and then connected with an unlocking cylinder 401; a sleeve 409 is sleeved outside the spring 402, and the other end of the lock pin 403 extends out of the sleeve 409 under the elastic force of the spring 402; the sleeve 409 and the unlocking cylinder 408 are respectively and fixedly connected with the umbilical tower 5;
the locking seat 405 is provided with a guide slideway and a blind hole, when the swing rod 3 is attached to the umbilical tower 5, the other end of the lock pin 403 slides into the blind hole along the guide slideway, and meanwhile, the unlocking cylinder 401 locks the lock pin 403.
The specific working process of the locking buffer device 4 is as follows:
in the process that the swing rod 3 swings back quickly and approaches the umbilical tower 5, a piston rod of a buffer cylinder 408 is firstly contacted with a movable buffer cushion 406, part of impact load is absorbed by the piston rod of the buffer cylinder 408 and the movable buffer cushion 406, a lock pin 403 then slides into a guide slideway of a locking seat 405, a spring 402 is compressed under the action of the guide slideway, the lock pin 403 is driven to be recovered towards a sleeve 409, the lock pin 403 is fixedly connected with the head of the piston rod of an unlocking cylinder 401, and when the lock pin 403 is recovered, the piston rod is passively recovered into the cylinder; until the blind hole of the locking seat 405 is aligned, the lock pin 403 is inserted into the blind hole under the action of the restoring force of the spring 402, and the locking action is completed. After the unlocking cylinder 401 receives the unlocking signal, the piston rod drives the lock pin 403 to pull out the locking seat 405, and the unlocking action is completed.
As shown in fig. 2, the primary retraction mechanism 1 includes: the device comprises a gear 101, a rack 102, a driving oil cylinder 103, a guide wheel 104, a main shaft 105, a hoop plate 106 and a mounting support 107;
the driving oil cylinder 103 and the guide wheel 104 are fixed on the umbilical tower 5 through a mounting support 107, and the driving oil cylinder 103 is used for driving the rack 102 to rotate the gear 101. The swing rod 3 performs a withdrawing task, when the swing rod is attached to the umbilical tower 5, the axis of the rotating shaft is coaxial with the axis of the main shaft 105, the swing rod 3 is fixed with the main shaft 105 through the hoop plate 106, the gear 101 is installed on one side of the main shaft 105, the driving oil cylinder 103 pushes the rack 102 to move, the rack 102 pushes the gear 101 to rotate under the guiding of the guide wheel 104, the gear 101 drives the main shaft 105 to rotate, and therefore the swing rod vertically swings around the main shaft 105.
The second-stage withdrawing mechanism 2 is arranged on one side of the umbilical tower 5 facing the rocket 6 and is higher than the first-stage withdrawing mechanism 1. As shown in fig. 3, the secondary retraction mechanism 2 includes: a winch 201, a fixed pulley 202, a movable pulley 203, a steel wire rope 204 and an installation platform 205;
the winch 201 is fixed on the umbilical tower 5, the fixed pulley 202 is fixed on the umbilical tower 5 through the mounting platform 205, and the movable pulley 203 is fixed on the other end of the swing rod 3; one end of a steel wire rope 204 is connected with the winch 201, and the other end of the steel wire rope 204 is fixed on the umbilical tower 5 after sequentially passing around the fixed pulley 202 and the movable pulley 203. After the electrical system identifies a signal that the primary withdrawing mechanism 1 fails, a winch 201 of the secondary withdrawing mechanism 2 for hot backup is started, a steel wire rope 204 is pulled to bypass a fixed pulley 202 fixed on a mounting platform 205, a movable pulley 203 with the far end mounted on the swing rod 3 is pulled to drive the swing rod 3 to swing back around a main shaft 105 quickly, a take-off safety space of the firing arrow 6 is avoided, and emergency withdrawing of the swing rod 3 under the condition that the primary withdrawing mechanism 1 fails is realized.
A method for withdrawing a swing rod by using a swing rod withdrawing system consisting of a primary withdrawing mechanism 1, a swing rod 3 and a locking buffer device 4 comprises the following steps:
1) when the swing rod 3 receives a withdrawing signal, the driving oil cylinder 103 drives the rack 102 to move, the rack 102 drives the gear 101 to rotate, and then the swing rod 3 rotates to the umbilical tower 5 for a certain angle; the rotation angle in the specific embodiment is 45 degrees;
2) the impact force generated by the rotation of the swing rod 3 is absorbed through the contact between the piston rod of the buffer cylinder 408 and the movable buffer pad 406 and the contact between the fixed buffer pad 407 and the locking seat 405; meanwhile, the lock pin 403 slides into the blind hole along the guide slideway by using the elastic force of the spring 402, and the driving oil cylinder 103 stops working after the swing rod 3 swings in place;
3) and (4) locking a lock pin 403 by using an unlocking cylinder 401 to finish the withdrawing work of the swing rod.
A method for withdrawing a swing rod by using a swing rod withdrawing system consisting of a primary withdrawing mechanism 1, a secondary withdrawing mechanism 2, a swing rod 3 and a locking buffer device 4 comprises the following steps:
1) when the swing rod 3 receives a withdrawing signal, the driving oil cylinder 103 drives the rack 102 to move, the rack 102 drives the gear 101 to rotate, whether the rack 102 is driven to move or not is judged within 0-0.2 s after the swing rod 3 receives the withdrawing signal, if the rack 102 is driven to move, the step 3) is carried out, and if the rack 102 is not driven to move, the step 2) is carried out;
2) starting a winch 201 to contract a steel wire rope 204, enabling the swing rod 3 to rotate towards the umbilical tower 5, and entering the step 3);
3) impact force generated by rotation of the swing rod 3 is absorbed through contact between a push rod of the buffer cylinder 408 and the movable buffer pad 406 and contact between the fixed buffer pad 407 and the locking seat 405; meanwhile, the lock pin 403 slides into the blind hole along the guide slideway, and the step 4) is carried out;
4) and (4) locking a lock pin 403 by using an unlocking cylinder 401 to finish the withdrawing work of the swing rod.
Those skilled in the art will appreciate that the details of the invention not described in detail in the specification are within the skill of those skilled in the art.
Claims (6)
1. The utility model provides a pendulum rod that rocket take-off zero second was automatic to be swung back removes and receives system which characterized in that includes: the primary withdrawing mechanism (1), the swing rod (3) and the locking buffer device (4);
the primary withdrawing mechanism (1) is arranged on the umbilical tower (5), and one end of the swing rod (3) is fixedly connected with the primary withdrawing mechanism (1); the swing rod (3) is provided with a pipeline for filling operation to the rocket (6), and the other end of the swing rod (3) is attached to the core stage of the rocket (6) during the filling operation; in the launching process of the rocket, the primary withdrawing mechanism (1) drives the swing rod (3) to rotate in a vertical plane, so that the other end of the swing rod (3) is attached to the umbilical tower (5); the rotation plane of the swing rod (3) passes through the axis of the rocket (6);
a locking buffer device (4) is arranged at the position where the other end of the swing rod (3) is attached to the umbilical tower (5); the locking buffer device (4) is used for absorbing impact force generated by rotation of the swing rod (3) and locking and fixing the other end of the swing rod (3) on the umbilical tower (5);
during the filling operation, the safe included angle alpha between the swing rod (3) and the horizontal plane meets the following requirements:
wherein, x (h)0) The takeoff drift amount h of the rocket in the horizontal direction0The vertical height difference from the top end of the rocket booster to the axis of a rotating shaft of the swing rod (3) is shown, S is a safety distance design value, the value range of S is 1-3 m, L is the length of the swing rod (3), and D is the horizontal distance from the axis of the rotating shaft of the swing rod (3) to the outer wall of a core stage of the rocket (6);
the locking buffer device (4) comprises: the device comprises an unlocking cylinder (401), a spring (402), a lock pin (403), a locking seat (405), a movable cushion pad (406), a fixed cushion pad (407), a buffer cylinder (408) and a sleeve (409);
the locking seat (405) and the movable buffer cushion (406) are fixed on the swing rod (3);
a fixed cushion pad (407) is arranged at the position where the locking seat (405) is attached to the umbilical tower (5), and the cushion cylinder (408) is fixed on the fixed cushion pad (407); in the process that the swing rod (3) is attached to the umbilical tower (5), a piston rod of a buffer cylinder (408) is pressed against a movable buffer pad (406) to absorb the impact force generated by the rotation of the swing rod (3);
one end of the lock pin (403) is sleeved with a spring (402) and then is connected with an unlocking cylinder (401); a sleeve (409) is sleeved outside the spring (402), and the other end of the lock pin (403) extends out of the sleeve (409) under the action of the elastic force of the spring (402); the sleeve (409) and the unlocking cylinder (401) are respectively and fixedly connected with the umbilical tower (5);
the locking seat (405) is provided with a guide slideway and a blind hole, in the process that the swing rod (3) is attached to the umbilical tower (5), the other end of the lock pin (403) slides into the blind hole along the guide slideway, and meanwhile, the unlocking cylinder (401) locks the lock pin (403).
2. The pendulum rod withdrawing system for rocket take-off zero-second automatic swinging back according to claim 1, wherein the primary withdrawing mechanism (1) comprises: a gear (101), a rack (102) and a driving oil cylinder (103);
the driving oil cylinder (103) is fixed on the umbilical tower (5), the gear (101) and the rack (102) are meshed with each other, and the gear (101) is fixedly connected with one end of the swing rod (3); the driving oil cylinder (103) is used for driving the rack (102) to enable the gear (101) to rotate.
3. The pendulum rod withdrawing system for rocket take-off zero-second automatic swinging back according to claim 2, characterized by further comprising a secondary withdrawing mechanism (2) installed on the umbilical tower (5);
the secondary withdrawing mechanism (2) comprises: the device comprises a winch (201), a fixed pulley (202), a movable pulley (203) and a steel wire rope (204);
the winch (201) and the fixed pulley (202) are fixed on the umbilical tower (5), and the movable pulley (203) is fixed at the other end of the swing rod (3); one end of the steel wire rope (204) is connected with the winch (201), and the other end of the steel wire rope (204) is fixed on the umbilical tower (5) after sequentially passing around the fixed pulley (202) and the movable pulley (203).
4. The rocket takeoff zero-second automatic swinging and retracting system of the rocket as claimed in any one of claims 1 to 3, wherein the swinging rod (3) is of a truss structure formed by welding pipe profiles, the section width of the swinging rod (3) is larger than 1m, the section height of the swinging rod (3) is larger than 2m, the swinging rod (3) is used for installing a filling pipeline, and an operator can pass through the inside of the swinging rod (3).
5. A method of retracting a swing link using the swing link retracting system of claim 2, comprising the steps of:
1) when the swing rod (3) receives a withdrawing signal, the driving oil cylinder (103) drives the rack (102) to move, the rack (102) drives the gear (101) to rotate, and then the swing rod (3) rotates towards the umbilical tower (5);
2) the impact force generated by the rotation of the swing rod (3) is absorbed through the contact between the piston rod of the buffer cylinder (408) and the movable buffer pad (406) and the contact between the fixed buffer pad (407) and the locking seat (405); meanwhile, a lock pin (403) slides into the blind hole along the guide slideway by using the elastic force of a spring (402);
3) and (3) locking a lock pin (403) by using an unlocking cylinder (401) to finish the withdrawing work of the swing rod.
6. A method of retracting a swing link using the swing link retracting system of claim 3, comprising the steps of:
1) when the swing rod (3) receives a withdrawing signal, the driving oil cylinder (103) drives the rack (102) to move, the rack (102) drives the gear (101) to rotate, whether the rack (102) is driven to move or not is judged within 0-0.2 s after the swing rod (3) receives the withdrawing signal, if the rack (102) is driven to move, the step 3 is carried out, and if the rack (102) is not driven to move, the step 2 is carried out;
2) starting a winch (201) to contract a steel wire rope (204), so that the swing rod (3) rotates towards the umbilical tower (5), and entering the step 3);
3) the push rod of the buffer cylinder (408) is contacted with the movable buffer cushion (406), and the fixed buffer cushion (407) is contacted with the locking seat (405), so that the impact force generated by the rotation of the swing rod (3) is absorbed; meanwhile, the lock pin (403) slides into the blind hole along the guide slideway, and the step 4) is carried out;
4) and (3) locking a lock pin (403) by using an unlocking cylinder (401) to finish the withdrawing work of the swing rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910251607.XA CN110030874B (en) | 2019-03-29 | 2019-03-29 | Swing rod withdrawing system for automatic zero-second swinging of rocket during takeoff |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910251607.XA CN110030874B (en) | 2019-03-29 | 2019-03-29 | Swing rod withdrawing system for automatic zero-second swinging of rocket during takeoff |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110030874A CN110030874A (en) | 2019-07-19 |
| CN110030874B true CN110030874B (en) | 2021-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910251607.XA Active CN110030874B (en) | 2019-03-29 | 2019-03-29 | Swing rod withdrawing system for automatic zero-second swinging of rocket during takeoff |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112539679A (en) * | 2020-12-07 | 2021-03-23 | 北京航天发射技术研究所 | Heavy carrier rocket launching support system and use method |
| CN114132533B (en) * | 2021-10-29 | 2023-08-01 | 中国运载火箭技术研究院 | Connector forced disengaging mechanism and method with inconsistent disengaging and unwinding directions |
| CN115875345B (en) * | 2023-02-13 | 2023-08-08 | 东方空间技术(山东)有限公司 | Hydraulic control system of rocket swing rod |
| CN116929161B (en) * | 2023-06-30 | 2024-03-19 | 东方空间技术(山东)有限公司 | Rocket inserting and removing swing rod system |
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| CN104154817A (en) * | 2014-07-14 | 2014-11-19 | 北京航天发射技术研究所 | Swing rod mechanism of rocket launching platform and swing rod applied to mechanism |
| CN104236388A (en) * | 2014-07-18 | 2014-12-24 | 北京航天发射技术研究所 | Mechanical limiting mechanism for oscillating rod |
| JP5927459B1 (en) * | 2015-05-25 | 2016-06-01 | 敦 石原 | Launch pad for small rocket |
| CN107941085A (en) * | 2017-11-20 | 2018-04-20 | 中国运载火箭技术研究院 | A kind of integral type transmitting station |
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2019
- 2019-03-29 CN CN201910251607.XA patent/CN110030874B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104154817A (en) * | 2014-07-14 | 2014-11-19 | 北京航天发射技术研究所 | Swing rod mechanism of rocket launching platform and swing rod applied to mechanism |
| CN104236388A (en) * | 2014-07-18 | 2014-12-24 | 北京航天发射技术研究所 | Mechanical limiting mechanism for oscillating rod |
| JP5927459B1 (en) * | 2015-05-25 | 2016-06-01 | 敦 石原 | Launch pad for small rocket |
| CN107941085A (en) * | 2017-11-20 | 2018-04-20 | 中国运载火箭技术研究院 | A kind of integral type transmitting station |
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