WO2021088817A1 - 火箭后支点支撑调整系统 - Google Patents

火箭后支点支撑调整系统 Download PDF

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Publication number
WO2021088817A1
WO2021088817A1 PCT/CN2020/126219 CN2020126219W WO2021088817A1 WO 2021088817 A1 WO2021088817 A1 WO 2021088817A1 CN 2020126219 W CN2020126219 W CN 2020126219W WO 2021088817 A1 WO2021088817 A1 WO 2021088817A1
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WIPO (PCT)
Prior art keywords
support
rocket
cylinder
rear fulcrum
seat
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PCT/CN2020/126219
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English (en)
French (fr)
Inventor
张瑜
张彦杰
韩召洋
韦银利
杨俊�
吴雪
Original Assignee
蓝箭航天空间科技股份有限公司
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Application filed by 蓝箭航天空间科技股份有限公司 filed Critical 蓝箭航天空间科技股份有限公司
Priority to JP2021572674A priority Critical patent/JP7339366B2/ja
Publication of WO2021088817A1 publication Critical patent/WO2021088817A1/zh

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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

Definitions

  • the application belongs to the technical field of rocket auxiliary support adjustment systems, and specifically relates to a rocket rear fulcrum support adjustment system.
  • the present application provides a rocket rear fulcrum support adjustment system.
  • the present application provides a rocket rear fulcrum support adjustment system, including two rocket rear fulcrum support adjustment devices, and along the width direction of the vertical arm, the two rocket rear fulcrum support adjustment devices are fixedly arranged at On both sides of the erecting arm, and the two rocket rear fulcrum supporting and adjusting devices are symmetrical with respect to the central axis of the erecting arm in the length direction;
  • the rocket rear fulcrum support and adjustment device includes a rotary support, a rotary push unit, a support unit, and a pulling unit; wherein the rotary push unit is arranged between the rotary support and the erecting arm, and is used in the rocket After being supported by the launching platform, the rotary support is pushed to rotate to allow the rocket to take off space; the support unit is arranged on the rotary support and is used to support the rear fulcrum of the rocket; the pulling unit Connected with the slewing support and the supporting unit, during the rocket erection process, the support of the supporting unit to the rocket is gradually converted into the pulling of the rocket by the pulling unit.
  • the rotary pushing unit includes a rotary pin shaft, a limit support block and a driving cylinder;
  • the rotary support is hinged with the vertical arm through the rotary pin, the limit support block is used to position the position of the rotary support, and the drive cylinder is used to drive the rotary support Rotate around the rotary pin shaft.
  • the rotation pushing unit further includes a first connecting plate and a second connecting plate
  • the first connecting plate is arranged on the erecting arm, the second connecting plate is arranged on the end surface of the turning support near the erecting arm; the first connecting plate and the second connecting plate are used in pairs, and It is hinged through the pivot pin.
  • the support unit includes a support lift cylinder and an end journal seat, one end of the support lift cylinder is fixedly connected to the vertical arm, and the other end is fixedly connected to the end journal seat;
  • the central axis of the support lift cylinder along its length direction is perpendicular to the central axis of the end journal seat along its length direction, and the support lift cylinder is used to adjust the length of the end journal seat along the support lift cylinder.
  • the end journal seat is used to support the rocket along the width direction of the erecting arm.
  • the supporting lifting cylinder includes a supporting cylinder tube, a lifting screw, a scroll bar, a turbine, and a lifting cylinder rod;
  • the end of the supporting cylinder connected with the erecting arm is provided with a threaded plugging cap
  • the lifting screw is rotatably arranged in the supporting cylinder
  • the end of the lifting screw close to the threaded plugging cap is provided with a deep Groove ball bearing
  • a retaining ring is arranged between the deep groove ball bearing and the threaded plug cover
  • a limit nut is arranged above the deep groove ball bearing, the turbine is arranged above the limit nut, and the turbine is connected to a lifting screw.
  • a thrust bearing is provided at the top and bottom ends of the turbine, and a limit baffle is provided above the thrust bearing;
  • the opposite end of the lifting screw rod close to the end of the screw cap is connected with one end of the lifting cylinder rod through a screw thread, and the end of the lifting cylinder rod connected with the lifting screw rod is slidably arranged in the supporting cylinder;
  • the supporting cylinder is provided with a first supporting flange cover at the opposite end of one end of the threaded blocking cover, the first supporting flange cover is provided with a through hole, and the other end of the lifting cylinder rod passes through the After the through hole is connected with the end journal seat through a transition flange.
  • a first guide groove is opened on the inner wall of the support cylinder between the limit baffle and the first support flange cover, and a first limit block is provided in the first guide groove
  • One end of the first limit block is fixedly connected with the lifting cylinder rod, and the other end slides in the first guide groove.
  • the end journal seat includes a seat tube, a driving screw, a hand wheel and a supporting cylinder rod, and the seat tube is fixedly arranged on the top end of the supporting lift cylinder along the horizontal radial direction of the rocket;
  • a support flange is provided at one end of the seat tube away from the rocket, one end of the drive screw is located outside the seat tube and connected with the hand wheel, and the other end passes through the support flange and is inside the seat tube It is connected with one end of the supporting cylinder rod through a thread;
  • a tapered roller bearing is provided between the inner wall of the supporting flange and the driving screw rod;
  • a limit nut is provided on the side of the tapered roller bearing close to the hand wheel;
  • a protective cover is provided on the side of the limiting nut close to the hand wheel, and the protective cover is fixedly connected with the seat tube.
  • a second support flange cover is provided at one end of the seat tube close to the rocket, and the opposite end of the connecting end of the support cylinder rod and the driving screw rod passes through the second support flange cover and is connected to the end journal.
  • a second guide groove is provided on the inner wall of the seat tube between the support flange and the second support flange cover, and a second limit block is provided in the second guide groove, so One end of the second limit block is fixedly connected with the supporting cylinder rod, and the other end slides in the second guide groove.
  • the end of the supporting cylinder rod connected with the end journal is provided with a compression cover, and the compression cover adopts a cylindrical structure with a side wall that can be opened and closed.
  • the compression cover includes an upper arc plate and a lower arc plate, and along the radial direction of the compression cover, one end of the upper arc plate and the corresponding end of the lower arc plate are connected by a pin;
  • the other end of the upper arc plate can be opened or closed by rotating around the pin shaft, and the other end of the upper arc plate is tightly connected with the other end of the lower arc plate by a fastening screw.
  • the pulling unit includes an adjusting screw, a first tie rod seat and a second tie rod seat;
  • one end of the adjusting screw is connected to the rotary support through the first tie rod seat, and the other end is connected to the end journal seat through the second tie rod seat; the adjusting screw is sleeved with an adjusting nut and a lock Nut.
  • the supporting lift cylinder is provided with a mounting flange at one end connected to the revolving support, the mounting flange is provided with an adjustment slot, and the support lift cylinder is connected to the revolving device through the adjustment slot and bolts.
  • the support is fixedly connected.
  • a central arrow is provided on the mounting flange, and a prefabricated centerline is provided on the revolving support; when the supporting lift cylinder is installed on the revolving support, the center arrow is the same as the prefabricated center.
  • the line is used for alignment calibration.
  • the application can effectively reduce the support risk of rocket transport and erection, and avoid the additional additional force generated on the rocket due to the deformation of the erection arm structure;
  • this application can adjust the rocket in multiple degrees of freedom, effectively reducing the difficulty of docking and adjusting the rocket during reloading, and significantly improving the efficiency of docking the rocket with the launch pad after it is erected.
  • the compression cover adopts a cylindrical structure with a side wall that can be opened and closed, which can effectively improve the operation efficiency of positioning, compression and loosening of the end journal, shorten the launch time of the rocket, and improve the launch efficiency.
  • Figure 1 is a schematic structural diagram of a rocket rear fulcrum support adjustment system provided by an embodiment of the application.
  • Fig. 2 is a side view of a rocket rear fulcrum support adjustment system provided by an embodiment of the application.
  • FIG. 3 is a schematic diagram of the internal structure of a supporting lift cylinder in a rocket rear fulcrum support adjustment system provided by an embodiment of the application.
  • FIG. 4 is a schematic diagram of the internal structure of the journal seat in the rear fulcrum support adjustment system of a rocket provided by an embodiment of the application.
  • Fig. 5 is a schematic view of the structure of the pressing cover viewed from the direction B-B in Fig. 3.
  • Fig. 6 is a schematic diagram of an open state of the compression cover in a rocket rear fulcrum support adjustment system provided by an embodiment of the application.
  • Fig. 7 is a structural diagram of the mounting flange viewed from the direction A-A in Fig. 3.
  • Rotary pushing unit 21. The first connecting plate; 22. The second connecting plate; 23. Rotary pin shaft; 24. Limit support block; 25. Drive cylinder;
  • the present application provides a rocket rear fulcrum support adjustment system, which includes two rocket rear fulcrum support adjustment devices, along the width direction of the vertical arm, the two rocket rear fulcrum support adjustment devices are fixedly arranged at the start Both sides of the vertical arm, and the two rocket rear fulcrum support adjustment devices are symmetrical with respect to the central axis of the vertical arm length direction.
  • the rocket rear fulcrum support adjustment device includes a rotary support 1, a rotary pushing unit 2, a supporting unit 3 and a pulling unit 4.
  • the rotary pushing unit 2 is arranged between the rotary support 1 and the erecting arm 5, which is used to push the rotary support 1 to rotate after the rocket is supported by the launch pad to allow the rocket take-off space to realize the support of the rocket.
  • the supporting unit 3 is arranged on the revolving support 1 and is used to support the rear fulcrum of the rocket.
  • the pulling unit 4 is connected with the revolving support 1 and the supporting unit 3, and during the rocket erection process, the support of the supporting unit 3 on the rocket is gradually converted into the pulling of the rocket by the pulling unit 4.
  • the rotary pushing unit 2 includes a first connecting plate 21, a second connecting plate 22, a rotary pin shaft 23, a limit support block 24 and a driving cylinder 25.
  • the first connecting plate 21 is arranged on the erecting arm 5
  • the second connecting plate 22 is arranged on the end surface of the revolving support 1 close to the erecting arm 5.
  • the first connecting plate 21 and the second connecting plate 22 are used in a pair, and are hinged through a pivot pin 23.
  • the limit support block 24 is arranged between the vertical arm 5 and the bottom surface of the rotary support 1, and is used for positioning the position of the rotary support 1.
  • One end of the driving cylinder 25 is hinged with the vertical arm 5, and the other end is hinged with the bottom surface of the rotary support 1.
  • the driving cylinder 25 is used to drive the rotary support 1 to rotate around the rotary pin 23 toward or away from the rocket supported on the erecting arm 5.
  • the driving cylinder 25 may be a driving oil cylinder or a driving hydraulic cylinder.
  • the supporting unit 3 includes a supporting lifting cylinder 31 and an end journal seat 33.
  • One end of the supporting lifting cylinder 31 is fixedly connected with the erecting arm 5, and the other end thereof is fixedly connected with the end journal seat 33.
  • the support lift cylinder 31 and the end journal seat 33 are arranged in a T shape, that is, the central axis of the support lift cylinder 31 along its length direction is perpendicular to the central axis of the end journal seat 33 along its length direction.
  • the supporting lifting cylinder 31 is used to adjust the displacement of the end journal seat 33 along the length direction of the supporting lifting cylinder 31.
  • the end journal seat 33 is used to support the rocket along the width direction of the erecting arm 5.
  • the supporting lifting cylinder 31 includes a supporting cylinder 311, a lifting screw 312, a scroll bar 313, a turbine 314 and a lifting cylinder rod 315. among them,
  • a screw cap 316 is provided at one end of the supporting cylinder 311 connected with the erecting arm 5.
  • the lifting screw 312 is rotatably arranged in the supporting cylinder 311.
  • a deep groove ball bearing 317 is arranged at one end of the lifting screw 312 close to the threaded plug 316.
  • a retaining ring 318 is arranged between the deep groove ball bearing 317 and the threaded plug 316. The retaining ring 318 limits the position of the deep groove ball bearing 317.
  • a limit nut 319 is arranged above the deep groove ball bearing 317, and a turbine 314 is arranged above the limit nut 319.
  • the turbine 314 is connected to the lifting screw 312 through a flat key.
  • One end of the worm 313 passes through the supporting cylinder 311 and then connects to the turbine 314. connection.
  • the limit nut 319 cooperates with the step on the lifting screw 312 to compress and position the turbine 314 on the lifting screw 312.
  • a thrust bearing 320 is provided at the top and bottom ends of the turbine 314, and the thrust bearing 320 is used to bear the force of the lifting cylinder rod 315 in the upper and lower directions.
  • a limit baffle 321 is provided above the thrust bearing 320, and the limit baffle 321 is used to restrict the lifting screw 312 from moving in a direction away from the erecting arm 5.
  • the opposite end of the lifting screw 312 close to one end of the threaded plug 316 is connected with one end of the lifting cylinder rod 315 through a thread, and the end of the lifting cylinder rod 315 is slidably arranged in the supporting cylinder 311.
  • the supporting cylinder 311 is provided with a threaded blocking cover 316.
  • the opposite end is provided with a first supporting flange cover 322.
  • the first supporting flange cover 322 is provided with a through hole.
  • the inner wall of the through hole is provided with a guide belt 323.
  • the lifting cylinder The other end of the rod 315 passes through the through hole and is connected to the end journal seat 33 through a transition flange 324.
  • the guide belt 323 is used to support and guide the lifting cylinder rod 315.
  • a first guide groove is provided on the inner wall of the supporting cylinder 311 between the limit baffle 321 and the first supporting flange cover 322.
  • a first limiting block 325 is provided in the guide groove. One end of the first limiting block 325 is fixedly connected with the lifting cylinder rod 315, and the other end slides in the first guide groove.
  • the end journal seat 33 includes a seat tube 331, a driving screw 332, a hand wheel 333 and a supporting cylinder rod 334.
  • the seat tube 331 is fixedly arranged on the top end of the supporting lifting cylinder 31 along the horizontal radial direction of the rocket. Specifically, the seat tube 331 is connected to the lifting cylinder rod 315 through a transition flange 324.
  • a supporting flange 335 is provided at one end of the seat tube 331 away from the rocket.
  • One end of the driving screw 332 is located outside the seat tube 331 and connected to the hand wheel 333, and the other end passes through the supporting flange 335 and then is threadedly connected to one end of the supporting cylinder rod 334 in the seat tube 331.
  • the driving screw 332 is rotated by the hand wheel 333, and the rotation of the driving screw 332 can drive the supporting cylinder rod 334 to make a telescopic movement in the seat tube 331.
  • a tapered roller bearing 336 is provided between the inner wall of the supporting flange 335 and the driving screw 332. Among them, the tapered roller bearings 336 are arranged in pairs and installed back to back to support and guide the driving screw 332.
  • a limiting nut 337 is provided on the side of the tapered roller bearing 336 close to the hand wheel 333, and the limiting nut 337 is matched with a step on the driving screw 332, and the tapered roller bearing 336 is fixedly connected to the driving screw 332.
  • a protective cover 338 is provided on the side of the limiting nut 337 close to the handwheel 333, and the protective cover 338 is fixedly connected to the seat tube 331, which is used to protect the limiting nut 337, the tapered roller bearing 336, etc. in the seat tube 331. .
  • a backing plate 339 is provided between the restriction nut 337 and the tapered roller bearing 336 along the length direction of the driving screw 332.
  • a second supporting flange cover 340 is provided at one end of the seat tube 331 close to the rocket.
  • the opposite end of the connecting end of the supporting cylinder rod 334 and the driving screw 332 passes through the second supporting flange cover 340 and then is connected to the end journal 341.
  • a second guide groove is provided on the inner wall of the seat tube 331 between the support flange 335 and the second support flange cover 340.
  • a second limit block 343 is provided in it. One end of the second limiting block 343 is fixedly connected with the supporting cylinder rod 334, and the other end slides in the second guide groove.
  • a compression cover 342 is provided at one end of the supporting cylinder rod 334 connected to the end journal 341.
  • the compression cover 342 adopts a cylindrical structure with a side wall that can be opened and closed. It includes an upper arc plate 3421 and a lower arc plate 3422. Along the radial direction of the compression cover 342, one end of the upper arc plate 3421 corresponds to one end of the lower arc plate 3422.
  • the other end of the upper arc plate 3421 can be rotated around the pin 3423 to open or close, and the other end of the upper arc plate 3421 can be fastened to the other end of the lower arc plate 3422 through a fastening screw 3424, thereby achieving
  • the support cylinder rod 334 and the end journal 341 are quickly connected or opened.
  • a mounting flange 11 is provided at one end of the supporting lifting cylinder 31 connected to the rotary support 1, and the mounting flange 11 is provided with an adjusting long hole 111 to support the lifting cylinder 31 It is fixedly connected with the revolving support 1 by adjusting the long holes 111 and bolts.
  • the setting of the adjustment slot 111 can finely adjust the position of the support lift cylinder 31 on the swing support 1 along the length direction of the rocket.
  • a center arrow 112 is provided on the mounting flange 11, and a prefabricated centerline 113 is provided on the revolving support 1.
  • the center arrow 112 can be aligned with the prefabricated centerline 113, so as to ensure that the support lift cylinders 31 on both sides of the rocket are symmetrical with respect to the vertical center plane in the length direction of the rocket. .
  • the pulling unit 4 includes an adjusting screw 41, a first pulling rod seat 42, a second pulling rod seat 43, an adjusting nut 44 and a lock nut 45.
  • one end of the adjusting screw 41 is connected to the rotary support 1 through the first tie rod seat 42, and the other end is connected to the end journal seat 33 through the second tie rod seat 43.
  • the adjusting screw 41 is sleeved with an adjusting nut 44 and a locking nut 45. By rotating the adjusting nut 44, the length of the adjusting screw 41 can be changed.
  • the adjusting screw 41 is adjusted to a preset length, the adjusting screw 41 can be locked by the locking nut 45 so that the length of the adjusting screw 41 no longer changes.
  • the first tie rod seat 42 is fixedly connected to the rotary support 1 through a positioning pin 46.
  • the supporting lifting cylinder 31 drives the end journal seat 33 to perform a lifting action, and the adjusting screw 41 pulls the end journal seat 33 through the second tie rod seat 43 to adapt to the different height positions supported by the end journal seat 33.
  • the end journal seat 33 has a certain level of adjustment capability, which can drive the rocket to adjust the position in the horizontal direction.
  • the center arrow 112 on the mounting flange 11 is aligned with the prefabricated center line 113 on the rotary support 1 to adjust the position of the supporting lift cylinder 31.
  • the supporting lifting cylinders 31 on both sides of the rocket are symmetrical with respect to the vertical center plane of the rocket length direction.
  • the rocket is slowly hoisted by the overhead crane until the end journal 341 is directly above the rear fulcrum, and then the rocket is slowly lowered so that the end journal 341 falls into the semi-groove of the supporting cylinder rod 334 away from the handwheel end 333 for pre-positioning. If the lateral position deviation is large, fine adjustment of the lateral position of the end journal 341 is performed by adjusting the hand wheel 333. Then cover the pressing cover 342, and tighten the fastening screw 3424. At the same time, the front fulcrum of the rocket is reliably supported, the adjusting nut 44 is adjusted so that the adjusting screw 41 is slightly tightened, and finally the locking nut 45 is tightened, so that the rocket hoisting and docking work is completed.
  • the rocket rear fulcrum support adjustment system of the present application can reliably support the rear fulcrum of the rocket body without displacement.
  • the end journal 341 can rotate around the pivot point, some uncertain movement or rotation during transportation is compensated.
  • the rocket will have a certain bowing rotation.
  • the end journal 341 will rotate in the groove of the supporting cylinder rod 334 to compensate for the deformation and avoid the rocket rotation to the rocket body. Additional additional force.
  • the direction of the supporting force of the opposite end journal 341 will change.
  • the fulcrum of the rocket is mainly supported by the supporting lift cylinder 31, and gradually switched to being pulled by the adjusting screw 41, and this pulling force gradually increases.
  • the gravity is basically achieved by the pulling of the joint screw 41.
  • both sides adjust the worm 313 at the same time to make the rocket move forward and backward, and adjust the hand wheel 333 on both sides at the same time to make the rocket move left and right to meet the docking positioning of the rocket and the launch pad.
  • raise the support plate of the launch pad's arrow foot, and the docking of the launch pad is now complete.
  • the fastening screw 3424 is loosened, and the compression cover 342 is opened. Loosen the bolt connecting the end journal 341 and the rocket, remove the end journal 341, the drive cylinder 25 extends, and pushes the rotary support 1 to rotate about 45° to allow the rocket take-off space. The rapid disassembly of the rocket's rear support is realized.
  • the rocket When the launch mission is cancelled, the rocket needs to be re-supported and positioned. At this time, the end journal 341 is reconnected to the rocket, the driving cylinder 25 is retracted and locked, and the rotary support 1 and the limit support block 24 are in contact and positioned again. At this time, loosen the lock nut 45, adjust the adjustment nut 44, adjust the scroll 313 and the handwheel 333, and coordinate the lifting of the legs of the launching platform, so that the end journal 341 falls into the groove of the support cylinder rod 334 again, and then press Tighten the pressing cover 342 of the end journal 341, and tighten the fastening screw 3424. Finally, slightly tighten the adjustment nut 44 and tighten the lock nut 45.
  • the rocket rear fulcrum support adjustment system has completed the support and positioning of the rocket again.
  • the rocket can be safely rolled back to a horizontal state. According to this operation process, multiple positioning and disassembly of the rocket and the vertical arm 5 can be realized.
  • the rocket rear fulcrum support adjustment system of the present application can effectively reduce the support risk of rocket transfer and erection, and avoid the additional additional force generated on the rocket due to the structural deformation of the erecting arm 5.
  • this application can adjust the rocket with multiple degrees of freedom, effectively reducing the difficulty of docking and adjusting the rocket during reloading, and effectively improving the efficiency of docking with the launch pad after the rocket is erected. .
  • the compression cover 342 provided at one end of the supporting cylinder rod 334 connected with the end journal 341 adopts a cylindrical structure with a side wall that can be opened and closed, which can effectively improve the operation efficiency of positioning, pressing and loosening the end journal 341 , Shorten the launch time of the rocket and improve the launch efficiency.

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Abstract

一种火箭后支点支撑调整系统，包括两个沿起竖臂(5)的宽度方向固定设置在起竖臂(5)的两侧的火箭后支点支撑调整装置，且二者关于起竖臂(5)长度方向的中轴线对称；火箭后支点支撑调整装置包括回转支座(1)、旋转推动单元(2)、支撑单元(3)和牵拉单元(4)；旋转推动单元(2)设置在回转支座(1)与起竖臂(5)之间，其用于推动回转支座(1)旋转以让开火箭起飞空间；支撑单元(3)设置在回转支座(1)上，其用于对火箭的后支点进行支撑；牵拉单元(4)与回转支座(1)和支撑单元(3)连接，在火箭起竖过程中，支撑单元(3)对火箭的支撑逐步转换为牵拉单元(4)对火箭的牵拉。该系统能够对火箭进行多自由度的调节，有效地降低火箭在转载时的对接和调整难度，显著地提高火箭在起竖后与发射台对接的效率。

Description

火箭后支点支撑调整系统 技术领域
本申请属于火箭辅助支撑调整系统技术领域，具体涉及一种火箭后支点支撑调整系统。
背景技术
随着航天技术的发展，特别是最近几年商业航天的蓬勃兴起，传统的“三垂”发射模式由于需要固定的发射塔架，其基础设施建设周期较长、维护成本较高的缺点逐渐显露出来，因此，需要一种快速、灵活、低成本的发射模式来适应现阶段商业航天的发射需求。
国外成功的商业航天企业大多采用“三平”的测发模式，即水平组装、水平转运、水平测试、起竖发射的发射模式。因此，在火箭转载、转运和起竖过程中可靠地支撑箭体，使箭体不受除自身重力以外的其他附加力就显得尤为重要和关键。特别是起竖臂与发射场区的回转支点对接起竖后，需要与地面上固定的发射台进行精确对接。由于回转支点和发射台位置存在偏差，起竖后火箭底面与发射台支撑面就存在一定的位置偏差，因此箭体需要进行多自由度的调整，来实现与发射台的精确对接，同时还要求用于支撑火箭后支点的装置具有一定的快速拆解能力。
发明内容
为至少在一定程度上克服相关技术中存在的问题，本申请提供了一种火箭后支点支撑调整系统。
根据本申请实施例，本申请提供了一种火箭后支点支撑调整系统，包括两个火箭后支点支撑调整装置，沿起竖臂的宽度方向，两个所述火箭后支点支撑调整装置固定设置在起竖臂的两侧，且两个所述火箭后支点支撑调整装置关于起竖臂长度方向的中轴线对称；
所述火箭后支点支撑调整装置包括回转支座、旋转推动单元、支撑单元 和牵拉单元；其中，所述旋转推动单元设置在所述回转支座与起竖臂之间，其用于在火箭转由发射台支撑后，推动所述回转支座旋转以让开火箭起飞空间；所述支撑单元设置在所述回转支座上，其用于对火箭的后支点进行支撑；所述牵拉单元与回转支座和支撑单元连接，在火箭起竖过程中，所述支撑单元对火箭的支撑逐步转换为所述牵拉单元对火箭的牵拉。
上述火箭后支点支撑调整系统中，所述旋转推动单元包括回转销轴、限位支撑块和驱动缸；
其中，所述回转支座通过所述回转销轴与起竖臂铰接，所述限位支撑块用于对所述回转支座的位置进行定位，所述驱动缸用于驱动所述回转支座绕所述回转销轴旋转。
进一步地，所述旋转推动单元还包括第一连接板和第二连接板；
所述第一连接板设置在起竖臂上，所述第二连接板设置在所述回转支座靠近起竖臂的端面上；所述第一连接板与第二连接板成对使用，且通过所述回转销轴铰接。
上述火箭后支点支撑调整系统中，所述支撑单元包括支撑升降缸和端轴颈座，所述支撑升降缸的一端与起竖臂固定连接，其另一端与所述端轴颈座固定连接；
所述支撑升降缸沿其长度方向的中轴线与所述端轴颈座沿其长度方向的中轴线垂直，所述支撑升降缸用于调节所述端轴颈座沿所述支撑升降缸的长度方向的位移，所述端轴颈座用于沿起竖臂的宽度方向对火箭进行支撑。
进一步地，所述支撑升降缸包括支撑缸筒、升降丝杆、涡杆、涡轮和升降缸杆；
其中，所述支撑缸筒与起竖臂连接的一端设置有螺纹堵盖，所述升降丝杆转动设置在所述支撑缸筒中，所述升降丝杆靠近所述螺纹堵盖的一端设置有深沟球轴承，所述深沟球轴承与螺纹堵盖之间设置有挡圈；
所述深沟球轴承上方设置有限位螺母，所述限位螺母的上方设置有所述涡轮，所述涡轮与升降丝杆连接，所述涡杆的一端穿过所述支撑缸筒后与所 述涡轮连接；
沿所述升降丝杆的长度方向，在所述涡轮的顶端和底端均设置有推力轴承，在所述推力轴承的上方设置有限位挡板；
所述升降丝杆靠近所述螺纹堵盖一端的相对端与所述升降缸杆的一端通过螺纹连接，所述升降缸杆与升降丝杆连接的一端滑动设置在所述支撑缸筒中；
所述支撑缸筒设置有所述螺纹堵盖一端的相对端设置有第一支撑法兰盖，所述第一支撑法兰盖上设置有通孔，所述升降缸杆的另一端穿过所述通孔后通过过渡法兰与所述端轴颈座连接。
更进一步地，在所述限位挡板与第一支撑法兰盖之间的所述支撑缸筒的内壁上开设有第一导向槽，所述第一导向槽中设置有第一限位块；所述第一限位块的一端与所述升降缸杆固定连接，另一端在所述第一导向槽中滑动。
进一步地，所述端轴颈座包括座筒、驱动丝杆、手轮和支撑缸杆，所述座筒沿火箭的水平径向固定设置在所述支撑升降缸的顶端；
所述座筒远离火箭的一端设置有支撑法兰，所述驱动丝杆的一端位于所述座筒外，并与手轮连接，另一端穿过所述支撑法兰后在所述座筒内与所述支撑缸杆的一端通过螺纹连接；
所述支撑法兰的内壁与所述驱动丝杆之间设置有圆锥滚子轴承；
在所述圆锥滚子轴承靠近所述手轮的一侧设置有限制螺母；
在所述限制螺母靠近所述手轮的一侧设置有保护罩，所述保护罩与座筒固定连接。
所述座筒靠近火箭的一端设置有第二支撑法兰盖，所述支撑缸杆与驱动丝杆连接端的相对端穿过所述第二支撑法兰盖后与端轴颈连接。
更进一步地，在所述支撑法兰与第二支撑法兰盖之间的所述座筒的内壁上开设有第二导向槽，所述第二导向槽中设置有第二限位块，所述第二限位块的一端与所述支撑缸杆固定连接，另一端在第二导向槽中滑动。
更进一步地，，所述支撑缸杆与端轴颈连接的一端设置有压紧盖，所述 压紧盖采用侧壁可开合的筒状结构。
更进一步地，所述压紧盖包括上弧板和下弧板，沿所述压紧盖的径向，所述上弧板的一端与所述下弧板对应的一端通过销轴连接；所述上弧板的另一端能够绕所述销轴旋转打开或闭合，所述上弧板的另一端通过紧固螺钉与所述下弧板的另一端紧固连接。
进一步地，所述牵拉单元包括调节螺杆、第一拉杆座和第二拉杆座；
其中，所述调节螺杆的一端通过所述第一拉杆座与回转支座连接，另一端通过所述第二拉杆座与端轴颈座连接；所述调节螺杆上套设有调节螺母和锁紧螺母。
进一步地，所述支撑升降缸与回转支座连接的一端设置有安装法兰，所述安装法兰上开设有调整长孔，所述支撑升降缸通过所述调整长孔和螺栓与所述回转支座固定连接。
更进一步地，所述安装法兰上设置有中心箭头，所述回转支座上设置有预制中心线；将所述支撑升降缸安装在所述回转支座上时，所述中心箭头与预制中心线用于进行对齐标定。
根据本申请的上述具体实施方式可知，至少具有以下有益效果：本申请能够有效地降低火箭转运、起竖的支撑风险，避免由于起竖臂结构变形对火箭产生的额外附加力；特别是火箭在转载和对接过程中，本申请能够对火箭进行多自由度的调节，有效地降低火箭在转载时的对接和调整难度，显著地提高火箭在起竖后与发射台对接的效率。
另外，压紧盖采用侧壁可开合的筒状结构，能够有效地提高端轴颈的定位、压紧、松开的操作效率，缩短火箭的发射时间，提高发射效率。
应了解的是，上述一般描述及以下具体实施方式仅为示例性及阐释性的，其并不能限制本申请所欲主张的范围。
附图说明
下面的所附附图是本申请的说明书的一部分，其示出了本申请的实施例，所附附图与说明书的描述一起用来说明本申请的原理。
图1为本申请实施例提供的一种火箭后支点支撑调整系统的结构示意图。
图2为本申请实施例提供的一种火箭后支点支撑调整系统的侧视图。
图3为本申请实施例提供的一种火箭后支点支撑调整系统中支撑升降缸的内部结构示意图。
图4为本申请实施例提供的一种火箭后支点支撑调整系统中端轴颈座的内部结构示意图。
图5为图3中从B-B方向看压紧盖的结构示意图。
图6为本申请实施例提供的一种火箭后支点支撑调整系统中压紧盖打开状态的示意图。
图7为图3中从A-A方向看安装法兰的结构示意图。
附图标记说明：
1、回转支座；11、安装法兰；111、调整长孔；112、中心箭头；113、预制中心线；
2、旋转推动单元；21、第一连接板；22、第二连接板；23、回转销轴；24、限位支撑块；25、驱动缸；
3、支撑单元；
31、支撑升降缸；311、支撑缸筒；312、升降丝杆；313、涡杆；314、涡轮；315、升降缸杆；316、螺纹堵盖；317、深沟球轴承；318、挡圈；319、限位螺母；320、推力轴承；321、限位挡板；322、支撑法兰盖；323、导向带；324、过渡法兰；325、第一限位块；
33、端轴颈座；331、座筒；332、驱动丝杆；333、手轮；334、支撑缸杆；335、支撑法兰；336、圆锥滚子轴承；337、限制螺母；338、保护罩；339、垫板；340、第二支撑法兰盖；341、端轴颈；342、压紧盖；3421、上弧板；3422、下弧板；3423、销轴；3424、紧固螺钉；343、第二限位块；
4、牵拉单元；41、调节螺杆；42、第一拉杆座；43、第二拉杆座；44、调节螺母；45、锁紧螺母；46、定位销；
5、起竖臂。
具体实施方式
为使本申请实施例的目的、技术方案和优点更加清楚明白，下面将以附图及详细叙述清楚说明本申请所揭示内容的精神，任何所属技术领域技术人员在了解本申请内容的实施例后，当可由本申请内容所教示的技术，加以改变及修饰，其并不脱离本申请内容的精神与范围。
本申请的示意性实施例及其说明用于解释本申请，但并不作为对本申请的限定。另外，在附图及实施方式中所使用相同或类似标号的元件/构件是用来代表相同或类似部分。
关于本文中所使用的“第一”、“第二”、…等，并非特别指称次序或顺位的意思，也非用以限定本申请，其仅为了区别以相同技术用语描述的元件或操作。
关于本文中所使用的方向用语，例如：上、下、左、右、前或后等，仅是参考附图的方向。因此，使用的方向用语是用来说明并非用来限制本创作。
关于本文中所使用的“包含”、“包括”、“具有”、“含有”等等，均为开放性的用语，即意指包含但不限于。
关于本文中所使用的“及/或”，包括所述事物的任一或全部组合。
关于本文中的“多个”包括“两个”及“两个以上”；关于本文中的“多组”包括“两组”及“两组以上”。
关于本文中所使用的用语“大致”、“约”等，用以修饰任何可以细微变化的数量或误差，但这些微变化或误差并不会改变其本质。一般而言，此类用语所修饰的细微变化或误差的范围在部分实施例中可为20％，在部分实施例中可为10％，在部分实施例中可为5％或是其他数值。本领域技术人员应当了解，前述提及的数值可依实际需求而调整，并不以此为限。
某些用以描述本申请的用词将于下或在此说明书的别处讨论，以提供本领域技术人员在有关本申请的描述上额外的引导。
如图1所示，本申请提供了一种火箭后支点支撑调整系统，其包括两个火箭后支点支撑调整装置，沿起竖臂的宽度方向，两个火箭后支点支撑调整 装置固定设置在起竖臂的两侧，且两个火箭后支点支撑调整装置关于起竖臂长度方向的中轴线对称。
其中，火箭后支点支撑调整装置包括回转支座1、旋转推动单元2、支撑单元3和牵拉单元4。其中，旋转推动单元2设置在回转支座1与起竖臂5之间，其用于在火箭转由发射台支撑后，推动回转支座1旋转以让开火箭起飞空间，实现火箭后支撑的快速拆解。支撑单元3设置在回转支座1上，其用于对火箭的后支点进行支撑。牵拉单元4与回转支座1和支撑单元3连接，在火箭起竖过程中，支撑单元3对火箭的支撑逐步转换为牵拉单元4对火箭的牵拉。
如图1所示，旋转推动单元2包括第一连接板21、第二连接板22、回转销轴23、限位支撑块24和驱动缸25。其中，第一连接板21设置在起竖臂5上，第二连接板22设置在回转支座1靠近起竖臂5的端面上。第一连接板21与第二连接板22成对使用，且通过回转销轴23铰接。限位支撑块24设置在起竖臂5与回转支座1的底面之间，其用于对回转支座1的位置进行定位。驱动缸25的一端起竖臂5铰接，其另一端与回转支座1的底面铰接。驱动缸25用于驱动回转支座1绕回转销轴23向靠近或远离起竖臂5上所支撑火箭的方向旋转。
具体地，驱动缸25可以采用驱动油缸或驱动液压缸。
如图1和图2所示，支撑单元3包括支撑升降缸31和端轴颈座33，支撑升降缸31的一端与起竖臂5固定连接，其另一端与端轴颈座33固定连接。支撑升降缸31与端轴颈座33呈T型设置，即支撑升降缸31沿其长度方向的中轴线与端轴颈座33沿其长度方向的中轴线垂直。支撑升降缸31用于调节端轴颈座33沿支撑升降缸31的长度方向的位移。端轴颈座33用于沿起竖臂5的宽度方向对火箭进行支撑。
具体地，如图3所示，支撑升降缸31包括支撑缸筒311、升降丝杆312、涡杆313、涡轮314和升降缸杆315。其中，
支撑缸筒311与起竖臂5连接的一端设置有螺纹堵盖316。升降丝杆312 转动设置在支撑缸筒311中，升降丝杆312靠近螺纹堵盖316的一端设置有深沟球轴承317，深沟球轴承317与螺纹堵盖316之间设置有挡圈318，挡圈318对深沟球轴承317进行限位。
深沟球轴承317上方设置有限位螺母319，限位螺母319的上方设置有涡轮314，涡轮314通过平键与升降丝杆312连接，涡杆313的一端穿过支撑缸筒311后与涡轮314连接。限位螺母319与升降丝杆312上的台阶配合，将涡轮314压紧定位在升降丝杆312上。
沿升降丝杆312的长度方向，在涡轮314的顶端和底端均设置有推力轴承320，推力轴承320用于承受升降缸杆315上下两个方向的作用力。在推力轴承320的上方设置有限位挡板321，限位挡板321用于限制升降丝杆312向远离起竖臂5的方向运动。
升降丝杆312靠近螺纹堵盖316一端的相对端与升降缸杆315的一端通过螺纹连接，升降缸杆315的该端滑动设置在支撑缸筒311中。
支撑缸筒311设置有螺纹堵盖316一端的相对端设置有第一支撑法兰盖322，第一支撑法兰盖322上设置有通孔，通孔的内壁上设置有导向带323，升降缸杆315的另一端穿过通孔后通过过渡法兰324与端轴颈座33连接。其中，导向带323用于对升降缸杆315进行支撑和导向。
为防止升降缸杆315在支撑缸筒311内滑动时发生转动，在限位挡板321与第一支撑法兰盖322之间的支撑缸筒311的内壁上开设有第一导向槽，第一导向槽中设置有第一限位块325。第一限位块325的一端与升降缸杆315固定连接，另一端在第一导向槽中滑动。
通过升降丝杆312的转动，实现升降缸杆315的上下运动。
如图4所示，端轴颈座33包括座筒331、驱动丝杆332、手轮333和支撑缸杆334。座筒331沿火箭的水平径向固定设置在支撑升降缸31的顶端，具体地，座筒331通过过渡法兰324与升降缸杆315连接。
座筒331远离火箭的一端设置有支撑法兰335。驱动丝杆332的一端位于座筒331外，并与手轮333连接，另一端穿过支撑法兰335后在座筒331 内与支撑缸杆334的一端通过螺纹连接。通过手轮333对驱动丝杆332进行旋转，驱动丝杆332的转动能够带动支撑缸杆334在座筒331内做伸缩运动。
支撑法兰335的内壁与驱动丝杆332之间设置有圆锥滚子轴承336。其中，圆锥滚子轴承336成对设置，并背对背安装，对驱动丝杆332起到支撑和导向的作用。
在圆锥滚子轴承336靠近手轮333的一侧设置有限制螺母337，限制螺母337与驱动丝杆332上的台阶配合，将圆锥滚子轴承336固定连接在驱动丝杆332上。
另外，在限制螺母337靠近手轮333的一侧设置有保护罩338，保护罩338与座筒331固定连接，其用于对座筒331内的限制螺母337、圆锥滚子轴承336等进行保护。
为便于限制螺母337更紧密地压紧圆锥滚子轴承336，沿驱动丝杆332的长度方向，在限制螺母337与圆锥滚子轴承336之间设置有垫板339。
座筒331靠近火箭的一端设置有第二支撑法兰盖340。支撑缸杆334与驱动丝杆332连接端的相对端穿过第二支撑法兰盖340后与端轴颈341连接。
可以理解的是，采用手轮333对驱动丝杆332进行驱动的方式也可以用马达驱动方式进行代替。
为防止支撑缸杆334在座筒331内做伸缩运动时发生转动，在支撑法兰335与第二支撑法兰盖340之间的座筒331的内壁上开设有第二导向槽，第二导向槽中设置有第二限位块343。第二限位块343的一端与支撑缸杆334固定连接，另一端在第二导向槽中滑动。
在一个具体的实施例中，如图5和图6所示，支撑缸杆334与端轴颈341连接的一端设置有压紧盖342。压紧盖342采用侧壁可开合的筒状结构，其包括上弧板3421和下弧板3422，沿压紧盖342的径向，上弧板3421的一端与下弧板3422对应的一端通过销轴3423连接；上弧板3421的另一端能够绕销轴3423旋转打开或闭合，上弧板3421的另一端可以通过紧固螺钉3424与下弧板3422的另一端紧固连接，从而实现支撑缸杆334与端轴颈341的 快速连接或打开。
在另一个具体的实施例中，如图7所示，支撑升降缸31与回转支座1连接的一端设置有安装法兰11，安装法兰11上开设有调整长孔111，支撑升降缸31通过调整长孔111和螺栓与回转支座1固定连接。调整长孔111的设置能够沿火箭的长度方向微调支撑升降缸31在回转支座1上的位置。
另外，安装法兰11上设置有中心箭头112，回转支座1上设置有预制中心线113。将支撑升降缸31安装在回转支座1上时，可以将中心箭头112与预制中心线113进行对齐标定，从而保证火箭两侧的支撑升降缸31相对于火箭长度方向的竖直中心面对称。
如图1所示，牵拉单元4包括调节螺杆41、第一拉杆座42、第二拉杆座43、调节螺母44和锁紧螺母45。其中，调节螺杆41的一端通过第一拉杆座42与回转支座1连接，另一端通过第二拉杆座43与端轴颈座33连接。调节螺杆41上套设有调节螺母44和锁紧螺母45。通过旋转调节螺母44，能够改变调节螺杆41的长度，当调节螺杆41调节到预设长度时，可以通过锁紧螺母45对调节螺杆41进行锁紧，以使调节螺杆41的长度不再变化。
具体地，第一拉杆座42通过定位销46与回转支座1固定连接。
支撑升降缸31带动端轴颈座33进行升降动作，调节螺杆41通过第二拉杆座43对端轴颈座33进行牵拉，以适应端轴颈座33支撑的不同高度位置。另外，端轴颈座33具有一定的水平调节能力，能够带动火箭进行水平方向的位置调节。
采用本申请提供的火箭后支点支撑调整系统对火箭在吊装对接、转运、起竖、对接发射台和后支撑解锁等过程中进行支撑时，其具体过程为：
S1、前期准备：
首先，将端轴颈341与火箭进行连接，对火箭上连接的端轴颈341的位置相对于地面同一水平基准进行精确测量，确定火箭两侧的两个端轴颈341在竖直方向上的高度差。
其次，调整限位支撑块24的高度，使火箭两侧的回转支座14与限位支 撑块24可靠接触并保持水平状态，驱动缸25缩回并使其处于锁紧状态。
通过调整安装法兰11，使安装法兰11上的中心箭头112与回转支座1上的预制中心线113对齐，以调整支撑升降缸31的位置。
通过调整支撑升降缸31与安装法兰11上调整长孔111的相对位置，使得火箭两侧的支撑升降缸31关于火箭长度方向的竖直中心面对称。
手动松开锁紧螺母45，同时配合调节螺母44的调整；手动调整涡杆313，使升降缸杆315升高，升降缸杆315带动端轴颈座升高，使支撑缸杆334的中心达到火箭后支撑理论中心点，并测量火箭两侧端轴颈座33的下安装面与支撑升降缸31的下安装面的高度差，使该高度差与火箭测量的端轴颈341高度保持一致。
最后手动调整手轮333，使火箭一侧的支撑缸杆334和火箭理论测量端轴颈341之间的距离与火箭另一侧的支撑缸杆334和火箭理论测量端轴颈341之间的距离保持一致，至此准备工作完成。
S2、火箭吊装对接；
火箭由天车缓慢起吊至端轴颈341位于后支点的正上方，然后缓慢下放火箭，使端轴颈341落入支撑缸杆334远离手轮端333的半凹槽内，进行预定位。如果横向位置偏差较大，则通过调整手轮333进行端轴颈341横向位置的微调。然后盖上压紧盖342，拧紧紧固螺钉3424。同时使火箭前支点可靠支撑，调整调节螺母44，使调节螺杆41微微拉紧，最后拧紧锁紧螺母45，至此火箭吊装对接工作完成。
S3、火箭转运；
火箭在转运过程中，由于驱动丝杆332和升降丝杆312的自锁作用，保证本申请火箭后支点支撑调整系统能够可靠地支撑箭体后支点，不发生位移。同时由于端轴颈341可绕回转支点旋转，补偿了一些在运输过程中的不确定移动或转动。
S4、火箭起竖：
在火箭起竖过程中，由于起竖臂5的变形，会使火箭有一定的低头转动， 端轴颈341会在支撑缸杆334的凹槽内旋转，补偿变形，避免火箭转动对箭体产生额外的附加力。起竖过程中，对端轴颈341支撑力的方向会发生改变，开始火箭后支点主要由支撑升降缸31支撑，逐渐转换到由调节螺杆41拉住，且此拉力逐渐增大，最后火箭的重力基本都由节螺杆41牵拉实现。
S5、对接发射台：
当火箭完成翻转起竖并和发射台对接时，由于起竖臂5回转点与发射台位置的误差，会使火箭箭脚与发射台承接盘存在一定位置偏差。此时两侧同时调整蜗杆313，使火箭做前后移动，两侧同时调整手轮333，使火箭做左右运动，满足火箭与发射台的对接定位。对接完成后，升起发射台箭脚支撑盘，至此对接发射台完成。
S6、后支撑解锁：
火箭转由发射台支撑后，松开紧固螺钉3424，打开压紧盖342。松开端轴颈341与火箭连接的螺栓，取下端轴颈341，驱动缸25伸出，推动回转支座1旋转约45°，让开火箭起飞空间。实现了火箭后支撑的快速拆解。
S7、二次支撑及回倒：
当发射任务取消后，需要对火箭进行重新支撑定位。此时，将端轴颈341与火箭重新连接，驱动缸25缩回锁紧，回转支座1与限位支撑块24重新接触定位。此时松开锁紧螺母45，调整调节螺母44，调整涡杆313和手轮333，配合发射台的支腿升降，使端轴颈341重新落入支撑缸杆334的凹槽内，然后压紧端轴颈341的压紧盖342，拧紧紧固螺钉3424。最后，微微拧紧调节螺母44，紧固锁紧螺母45，至此火箭后支点支撑调整系统重新完成了对火箭的支撑定位。可以安全地使火箭回倒至水平状态。按此操作流程，可以实现火箭与起竖臂5的多次定位和拆解。
本申请火箭后支点支撑调整系统能够有效地降低火箭转运、起竖的支撑风险，避免由于起竖臂5结构变形对火箭产生的额外附加力。特别是火箭在转载和对接过程中，本申请能够对火箭进行多自由度的调节，有效地降低火箭在转载时的对接和调整难度，使火箭起竖后与发射台对接的效率得到有效 地提高。
另外，支撑缸杆334与端轴颈341连接的一端设置的压紧盖342采用侧壁可开合的筒状结构，能够有效地提高端轴颈341的定位、压紧、松开的操作效率，缩短火箭的发射时间，提高发射效率。
以上所述仅为本申请示意性的具体实施方式，在不脱离本申请的构思和原则的前提下，任何本领域的技术人员所做出的等同变化与修改，均应属于本申请保护的范围。

Claims (12)

  1. 一种火箭后支点支撑调整系统，其特征在于，包括两个火箭后支点支撑调整装置，沿起竖臂的宽度方向，两个所述火箭后支点支撑调整装置固定设置在起竖臂的两侧；
    所述火箭后支点支撑调整装置包括回转支座、旋转推动单元、支撑单元和牵拉单元；其中，所述旋转推动单元设置在所述回转支座与起竖臂之间，其用于在火箭转由发射台支撑后，推动所述回转支座旋转以让开火箭起飞空间；所述支撑单元设置在所述回转支座上，其用于对火箭的后支点进行支撑；所述牵拉单元与回转支座和支撑单元连接，在火箭起竖过程中，所述支撑单元对火箭的支撑逐步转换为所述牵拉单元对火箭的牵拉。
  2. 根据权利要求1所述的火箭后支点支撑调整系统，其特征在于，所述旋转推动单元包括回转销轴、限位支撑块和驱动缸；
    其中，所述回转支座通过所述回转销轴与起竖臂铰接，所述限位支撑块用于对所述回转支座的位置进行定位，所述驱动缸用于驱动所述回转支座绕所述回转销轴旋转。
  3. 根据权利要求1或2所述的火箭后支点支撑调整系统，其特征在于，所述支撑单元包括支撑升降缸和端轴颈座，所述支撑升降缸的一端与起竖臂固定连接，其另一端与所述端轴颈座固定连接；
    所述支撑升降缸沿其长度方向的中轴线与所述端轴颈座沿其长度方向的中轴线垂直，所述支撑升降缸用于调节所述端轴颈座沿所述支撑升降缸的长度方向的位移，所述端轴颈座用于沿起竖臂的宽度方向对火箭进行支撑。
  4. 根据权利要求3所述的火箭后支点支撑调整系统，其特征在于，所述支撑升降缸包括支撑缸筒、升降丝杆、涡杆、涡轮和升降缸杆；
    其中，所述支撑缸筒与起竖臂连接的一端设置有螺纹堵盖，所述升降丝杆转动设置在所述支撑缸筒中，所述升降丝杆靠近所述螺纹堵盖的一端设置有深沟球轴承，所述深沟球轴承与螺纹堵盖之间设置有挡圈；
    所述深沟球轴承上方设置有限位螺母，所述限位螺母的上方设置有所述涡轮，所述涡轮与升降丝杆连接，所述涡杆的一端穿过所述支撑缸筒后与所 述涡轮连接；
    沿所述升降丝杆的长度方向，在所述涡轮的顶端和底端均设置有推力轴承，在所述推力轴承的上方设置有限位挡板；
    所述升降丝杆靠近所述螺纹堵盖一端的相对端与所述升降缸杆的一端通过螺纹连接，所述升降缸杆与升降丝杆连接的一端滑动设置在所述支撑缸筒中；
    所述支撑缸筒设置有所述螺纹堵盖一端的相对端设置有第一支撑法兰盖，所述第一支撑法兰盖上设置有通孔，所述升降缸杆的另一端穿过所述通孔后通过过渡法兰与所述端轴颈座连接。
  5. 根据权利要求4所述的火箭后支点支撑调整系统，其特征在于，在所述限位挡板与第一支撑法兰盖之间的所述支撑缸筒的内壁上开设有第一导向槽，所述第一导向槽中设置有第一限位块；所述第一限位块的一端与所述升降缸杆固定连接，另一端在所述第一导向槽中滑动。
  6. 根据权利要求3所述的火箭后支点支撑调整系统，其特征在于，所述端轴颈座包括座筒、驱动丝杆、手轮和支撑缸杆，所述座筒固定设置在所述支撑升降缸的顶端，且与火箭被支撑后的水平径向方向一致；
    所述座筒远离被支撑火箭的一端设置有支撑法兰，所述驱动丝杆的一端位于所述座筒外，并与手轮连接，另一端穿过所述支撑法兰后在所述座筒内与所述支撑缸杆的一端通过螺纹连接；
    所述支撑法兰的内壁与所述驱动丝杆之间设置有圆锥滚子轴承；
    在所述圆锥滚子轴承靠近所述手轮的一侧设置有限制螺母；
    所述座筒靠近被支撑火箭的一端设置有第二支撑法兰盖，所述支撑缸杆与驱动丝杆连接端的相对端穿过所述第二支撑法兰盖后与端轴颈连接。
  7. 根据权利要求6所述的火箭后支点支撑调整系统，其特征在于，在所述支撑法兰与第二支撑法兰盖之间的所述座筒的内壁上开设有第二导向槽，所述第二导向槽中设置有第二限位块，所述第二限位块的一端与所述支撑缸杆固定连接，另一端在第二导向槽中滑动。
  8. 根据权利要求6所述的火箭后支点支撑调整系统，其特征在于，所述支撑缸杆与端轴颈连接的一端设置有压紧盖，所述压紧盖采用侧壁可开合的筒状结构。
  9. 根据权利要求8所述的火箭后支点支撑调整系统，其特征在于，所述压紧盖包括上弧板和下弧板，沿所述压紧盖的径向，所述上弧板的一端与所述下弧板对应的一端通过销轴连接；所述上弧板的另一端能够绕所述销轴旋转打开或闭合，所述上弧板的另一端通过紧固螺钉与所述下弧板的另一端紧固连接。
  10. 根据权利要求3所述的火箭后支点支撑调整系统，其特征在于，所述牵拉单元包括调节螺杆、第一拉杆座和第二拉杆座；
    其中，所述调节螺杆的一端通过所述第一拉杆座与回转支座连接，另一端通过所述第二拉杆座与端轴颈座连接；所述调节螺杆上套设有调节螺母和锁紧螺母。
  11. 根据权利要求3所述的火箭后支点支撑调整系统，其特征在于，所述支撑升降缸与回转支座连接的一端设置有安装法兰，所述安装法兰上开设有调整长孔，所述支撑升降缸通过所述调整长孔和螺栓与所述回转支座固定连接。
  12. 根据权利要求11所述的火箭后支点支撑调整系统，其特征在于，所述安装法兰上设置有中心箭头，所述回转支座上设置有预制中心线；将所述支撑升降缸安装在所述回转支座上时，所述中心箭头与预制中心线用于进行对齐标定。
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