WO2020151718A1 - 运载火箭及用于回收运载火箭的多级气动支撑缸 - Google Patents

运载火箭及用于回收运载火箭的多级气动支撑缸 Download PDF

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Publication number
WO2020151718A1
WO2020151718A1 PCT/CN2020/073597 CN2020073597W WO2020151718A1 WO 2020151718 A1 WO2020151718 A1 WO 2020151718A1 CN 2020073597 W CN2020073597 W CN 2020073597W WO 2020151718 A1 WO2020151718 A1 WO 2020151718A1
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WIPO (PCT)
Prior art keywords
cylinder
sub
cavity
launch vehicle
pneumatic support
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PCT/CN2020/073597
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English (en)
French (fr)
Inventor
张彦杰
赵立乔
张瑜
吴雪
李永俊
韩召洋
张亚民
南铁玲
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 JP2021543118A priority Critical patent/JP7253061B2/ja
Publication of WO2020151718A1 publication Critical patent/WO2020151718A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
    • F15B15/08—Characterised by the construction of the motor unit
    • F15B15/14—Characterised by the construction of the motor unit of the straight-cylinder type
    • F15B15/16—Characterised by the construction of the motor unit of the straight-cylinder type of the telescopic type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
    • F15B15/20—Other details, e.g. assembly with regulating devices
    • F15B15/22—Other details, e.g. assembly with regulating devices for accelerating or decelerating the stroke
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
    • F15B15/20—Other details, e.g. assembly with regulating devices
    • F15B15/24—Other details, e.g. assembly with regulating devices for restricting the stroke

Definitions

  • the invention relates to the field of aerospace, and in particular to a launch vehicle and a multi-stage pneumatic support cylinder for recovering the launch vehicle.
  • Some existing landing devices use fixed outriggers, and some use electric cylinders as landing outriggers.
  • the fixed outriggers are only suitable for recovery tests, not for rocket recovery and landing.
  • the electric cylinder can accurately open the rocket landing device and provide support. In principle, it can realize the landing recovery.
  • the entire recovery landing device is bulky, which reduces the rocket The load capacity of the liquid rocket, and the explosion-proof level of the electric cylinder is relatively high.
  • the present invention provides a multi-stage pneumatic support cylinder for recovery of a launch vehicle, wherein the multi-stage pneumatic support cylinder includes a cylinder tube, which includes a mother cylinder tube and a sleeve set together and arranged together.
  • the buffer device is used to buffer the force of the landing rocket.
  • the cylinder further includes a cylinder arranged between two adjacent sub-cylinders or between the mother cylinder and the adjacent one.
  • the limiting device is a locking pin, a locking block, a locking ball, a ratchet wheel or an eccentric wheel.
  • the inner wall of the mother cylinder is provided with a first protrusion structure
  • the outer wall of one end of the sub-cylinder is provided with a first Two convex structures
  • the inner wall of the other end of the sub-cylinder is provided with a third convex structure; wherein, between the mother cylinder and the adjacent sub-cylinder, the first convex structure and the The second protrusion structure is matched with each other, and the two adjacent sub-cylinders are matched with the second protrusion structure through the third protrusion structure.
  • a first through hole is opened on the first protrusion structure, and a first through hole is provided on the second protrusion structure.
  • a blind hole is located at the corresponding position of the hole, and a second through hole is opened on the third protrusion structure; wherein, between the mother cylinder and the adjacent sub-cylinder, the limiting device is clamped in the The first through hole extends into the blind hole; between the adjacent sub-cylinders, the limiting device is clamped in the second through hole of the sub-cylinder and extends to the same In the blind hole of the adjacent sub-cylinder.
  • Multi-stage pneumatic support cylinder for recovery of launch vehicle Multi-stage pneumatic support cylinder for recovery of launch vehicle Multi-stage pneumatic support cylinder for recovery of launch vehicle Multi-stage pneumatic support cylinder for recovery of launch vehicle Multi-level pneumatic support cylinder for recovery of launch vehicle Multi-stage pneumatic support cylinder
  • the buffer device in the multi-stage pneumatic support cylinder for recovering a launch vehicle, is an oil-air buffer.
  • the oil-air buffer in the multi-stage pneumatic support cylinder for recovering a launch vehicle, includes a cylinder rod sleeved in the sub-cylinder of the telescopic part, so The cylinder rod can move along the inner wall of the sub-cylinder.
  • the cylinder rod in the multi-stage pneumatic support cylinder for recovering a launch vehicle, is a hollow structure with an opening at one end, the opening is located inside the sub-cylinder, and the cylinder rod
  • the hollow structure communicates with the inner cavity of the sub-cylinder to form a first cavity;
  • the opening of the cylinder rod is provided with a connecting plate connecting the outer wall of the sub-cylinder rod and the inner wall of the cylinder, and the cylinder rod
  • the outer wall, the inner wall of the cylinder and the connecting plate constitute a second cavity.
  • the first cavity stores oil
  • a movable piston is arranged in the second cavity, and the piston divides the second cavity into a first sub-cavity and a second sub-cavity, and pressurized gas is stored in the second sub-cavity.
  • the first sub-cavity is provided with a one-way valve and a damping hole;
  • the orifice is used to discharge the oil in the first cavity into the first sub-cavity
  • the one-way valve is used to discharge the oil in the first sub-cavity into the first cavity.
  • Another aspect of the present invention also provides a launch vehicle, which includes the above-mentioned multi-stage pneumatic support cylinder.
  • the gas in the gas generator pushes multiple sub-cylinders to extend and fix.
  • the multi-stage pneumatic support cylinder plays a supporting role.
  • the multi-stage pneumatic support cylinder used for the recovery of the launch vehicle of the invention has the advantages of simple structure, safety and reliability and light overall weight.
  • the sub-cylinder when the sub-cylinder is extended, the sub-cylinder is fixed by a limit device, which has excellent cushioning and shock absorption performance.
  • the sealing requirements are low, and the production and processing costs are low.
  • an oil-air buffer is arranged on the telescopic part of the cylinder barrel.
  • the pneumatic principle in the oil-air buffer can effectively reduce the weight of the support cylinder , Thereby reducing the overall weight of the rocket recovery landing device and enhancing the carrying capacity of the rocket.
  • the multi-stage pneumatic support cylinder for the recovery of the carrier rocket of the present invention, during the rocket recovery and landing process, its four legs touch the ground sequentially.
  • the multi-stage pneumatic support cylinder lifts it up
  • the pressure on the first leg is reduced, and the oil-gas buffer extends the cylinder rod to quickly straighten the rocket's tilt posture and play a role of righting and correcting.
  • FIG. 1 is a schematic structural diagram of a multi-stage pneumatic support cylinder used to recover a launch vehicle in a retracted state in one of the embodiments of the present invention
  • FIG. 2 is a first structural schematic diagram of the extended state of the multi-stage pneumatic support cylinder for the recovery of the launch vehicle described in one of the embodiments of the present invention
  • Fig. 3 is a second structural schematic diagram of the extended state of the multi-stage pneumatic support cylinder for the recovery launch vehicle described in one of the embodiments of the present invention
  • Figure 4 is a partial enlarged view of the connection structure between adjacent sub-cylinders or between the mother cylinder and adjacent sub-cylinders in Figure 3;
  • Fig. 5 is a schematic structural diagram of a buffer device in a multi-stage pneumatic support cylinder for recovering a launch vehicle according to one embodiment of the present invention.
  • 1 represents the cylinder
  • 10 represents the mother cylinder
  • 101 represents the first raised structure
  • 102 represents the first through hole
  • 11 represents the child cylinder
  • 111 represents the first raised structure
  • 112 represents the second raised structure
  • 113 represents Blind hole
  • 114 represents the second through hole
  • 12 represents the limit device
  • 2 represents the gas generator
  • 3 represents the buffer device
  • 31 represents the cylinder rod
  • 32 represents the first cavity
  • 33 represents the connecting plate
  • 34 represents the second cavity
  • 341 represents the piston
  • 342 represents the first sub-cavity
  • 343 represents the second sub-cavity
  • 35 represents the one-way valve
  • 36 represents the orifice
  • 4 represents the adjustment airbag.
  • the present invention provides a multi-stage pneumatic support cylinder for recovering a launch vehicle, wherein the multi-stage pneumatic support cylinder includes:
  • the cylinder tube 1 which includes a mother cylinder tube 10 and a plurality of sub-cylinder tubes 11 sleeved together and arranged in the mother cylinder tube 10; the mother cylinder tube constitutes the fixed part of the cylinder tube 1, and the plurality of The sub-cylinders constitute the telescopic part of the cylinder 1; the gas generator 2 provided inside the mother cylinder; and the buffer device 3 provided in the telescopic part; the gas generator 2 is used to pass through When starting, gas is formed to push the plurality of sub-cylinders 11 to extend along the axial direction of the mother cylinder, and the buffer device 3 is used to buffer the force of the landing rocket.
  • the gas generator 2 can be arranged at the bottom of the mother cylinder 10, and the gas generator 2 is ignited under the control of the control signal.
  • the generator 2 generates gas with a certain pressure, and the power generated by the gas pushes a plurality of sub-cylinders 11 to extend and fix.
  • the buffer device 3 is arranged inside the telescopic part, and the buffer device 3 is located inside the sub-cylinder away from the bottom of the mother cylinder.
  • the gas generator 2 is used to provide power to the cylinder tube 1, and the gas generator 2 can be replaced by other gas sources generated by chemical reactions or externally drawn gas sources.
  • the cylinder tube 1 further includes a limiting device arranged between two adjacent sub-cylinder tubes 11 or between the mother cylinder tube and the adjacent sub-cylinder tube 11 12. After the sub-cylinder 11 extends to a predetermined position of the adjacent sub-cylinder 11 or the mother cylinder, the limiting device 12 selectively fixes the sub-cylinder 11 at the predetermined position .
  • the cylinder tube 1 in the extended state will be fixed in the predetermined position by the limit device 12 to the mother cylinder tube 10 and the adjacent sub-cylinder tube 11, and at the same time, the two adjacent cylinder tubes will be fixed by the limit device 12
  • Each sub-cylinder 11 is fixed at a predetermined position to ensure that the cylinder 1 is in an extended state.
  • the inner wall of the mother cylinder 10 is provided with a first protrusion structure 101
  • the outer wall of one end of the sub cylinder 11 is provided with a second protrusion structure 111
  • the other end of the sub cylinder 11 A third protrusion structure 112 is provided on the inner wall of the inner wall, wherein the mother cylinder tube 10 and the adjacent sub-cylinder tube 11 pass through the first protrusion structure 101 and the second protrusion structure 111.
  • the two adjacent sub-cylinders 11 cooperate with each other through the third protrusion structure 112 and the second protrusion structure 111.
  • a first through hole 102 is opened on the first protruding structure 101
  • a blind hole 113 is provided on the second protruding structure 112 corresponding to the through hole 102
  • the third protruding structure is A second through hole 114 is opened; wherein, between the mother cylinder tube 10 and the adjacent child cylinder tube 11, the limiting device 12 is clamped in the first through hole 102 and extends to the In the blind hole 113, the mother cylinder 10 and the adjacent sub-cylinder 11 are fixed at a predetermined position; between the adjacent sub-cylinders 11, the limiting device 12 is clamped in the sub-cylinder 11
  • the second through hole 114 extends into the blind hole 113 of the adjacent sub-cylinder 11, so that the two adjacent sub-cylinders 11 are fixed at a predetermined position.
  • the limiting device 12 is a locking pin, a locking block, a locking ball, a ratchet wheel or an eccentric wheel.
  • the buffer device 3 is a hydraulic damping device, an air spring or a mechanical spring.
  • the buffer device 3 is an oil-air buffer.
  • the oil-air buffer includes a cylinder rod 31 sleeved in the sub-cylinder 11 of the telescopic part, and the cylinder rod 31 can move along the inner wall of the sub-cylinder 11.
  • the cylinder rod 31 is a hollow structure with an open end, the opening is located inside the sub-cylinder 11, and the hollow structure of the cylinder rod 31 communicates with the inner cavity of the sub-cylinder 11 to form a first cavity 32;
  • the opening of the cylinder rod 31 is provided with a connecting plate 33 connecting the outer wall of the sub-cylinder rod 31 and the inner wall of the sub-cylinder 11, the outer wall of the cylinder rod 31, the inner wall of the sub-cylinder 11 and the The connecting plate 33 constitutes a second cavity 34.
  • the first cavity 32 stores oil;
  • the second cavity 34 is provided with a movable piston 341 that divides the second cavity 34 into first sub-cavities Body 342 and a second sub-cavity 343 in which pressurized gas is stored.
  • the first sub-cavity 342 is provided with a one-way valve 35 and a damping hole 36; the damping hole 36 is used to discharge the oil in the first cavity 32 to the first sub-cavity In the cavity 342; the one-way valve 35 is used to discharge the oil in the first sub-cavity 342 into the first cavity 32.
  • an adjustment airbag 4 is provided on the outer wall of the second subcavity 343, and the adjustment airbag 4 is used to adjust the pressure value of the air in the second subcavity 343.
  • the four landing legs will land in sequence.
  • the oil and gas buffer device on the multi-stage pneumatic support cylinder is impacted, and the cylinder rod 31 moves downward under force, pushing the first leg to the ground.
  • the oil in a cavity 32 enters the first sub-cavity 342 through the orifice 36, and the oil is accumulated in the first sub-cavity 342 to push the piston 341 to move to the second sub-cavity 343, compressing the second sub-cavity
  • the gas in the second sub-cavity 343 increases the pressure in the second sub-cavity 343, and the oil damping and pressurized gas play a shock-absorbing and buffering effect on the rocket landing; then the second, third, and fourth outriggers touch the ground.
  • the pressure on the legs is reduced, the piston 341 in the oil-air buffer device moves to the first sub-cavity 342 under the action of the compressed air in the second sub-cavity 343, and the oil in the first sub-cavity 342 passes through the single
  • the valve 35 is discharged into the first cavity 32, the oil accumulates in the first cavity 32 and pushes the cylinder rod 31 to extend, quickly correcting the tilting posture of the rocket.
  • the oil-gas buffer device plays a role of righting and correcting.
  • the present invention also provides a launch vehicle, which includes the above-mentioned multi-stage pneumatic support cylinder.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid-Damping Devices (AREA)
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Abstract

公开了一种运载火箭及用于回收运载火箭的多级气动支撑缸，该多级气动支撑缸包括：缸筒（1），其包括母缸筒（10）和套设在一起并设于母缸筒（10）内的多个子缸筒（11）；母缸筒（10）构成缸筒（1）的固定部，多个子缸筒（11）构成缸筒（1）的伸缩部；设置在母缸筒（10）内部的的燃气发生器（2）；设置在伸缩部的缓冲装置（3）。用于回收运载火箭的多级气动支撑缸具有提供安全可靠、总体重量轻的优点，在使用的过程中能够满足火箭着陆装置的快速打开、支撑、减震和扶正纠偏的要求。

Description

运载火箭及用于回收运载火箭的多级气动支撑缸 技术领域
本发明涉及航空航天领域，且特别涉及一种运载火箭及用于回收运载火箭的多级气动支撑缸。
背景技术
目前国内的火箭着陆装置较少，现有的着陆装置有的采用固定式支腿，也有的采用电动缸作为着陆支腿。固定式支腿仅适用于回收试验，不适用于火箭回收着陆。电动缸作为着陆支腿，可准确打开火箭着陆装置，并能够提供支撑，原理上可实现着陆回收，但由于电动缸自身重量重，又附加缓冲装置，导致整个回收着陆装置笨重，这降低了火箭的承载能力，并且液体火箭对电动缸的防爆等级要求较高。
因此，如何提供一种安全可靠、总体重量轻、可用于回收运载火箭的多级气动支撑缸是本领域技术人员亟待解决的技术问题。
发明内容
为了解决至少部分上述技术问题，本发明提供一种用于回收运载火箭的多级气动支撑缸，其中，该多级气动支撑缸包括：缸筒，其包括母缸筒和套设在一起并设于所述母缸筒内的多个子缸筒；所述母缸筒构成所述缸筒的固定部，所述多个子缸筒构成所述缸筒的伸缩部；设置在所述母缸筒内部的的燃气发生器；以及，设置在所述伸缩部的缓冲装置；所述燃气发生器用于通过在启动时形成气体以推动所述多个子缸筒沿所述母缸筒的轴向方向伸长，所述缓冲装置用于对着陆火箭的受力进行缓冲。
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所 述缸筒还包括设置在相邻两个所述子缸筒间或所述母缸筒与相邻的所述子缸筒间的限位装置，所述子缸筒伸出至相邻的所述子缸筒或母缸筒的预定位置后，所述限位装置选择地将所述子缸筒固定在所述预定位置。
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所述限位装置为锁止销、锁止块、锁止球、棘轮或偏心轮。
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所述母缸筒的内壁上设置有第一凸起结构，所述子缸筒一端的外壁设置有第二凸起结构，所述子缸筒另一端的内壁上设置有第三凸起结构；其中，所述母缸筒与其相邻的所述子缸筒间通过所述第一凸起结构和所述第二凸起结构相互配合，相邻的两个所述子缸筒间，通过所述第三凸起结构与所述第二凸起结构相互配合。
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所述第一凸起结构上开设有一第一通孔，所述第二凸起结构上与所述通孔对应位置处一盲孔，所述第三凸起结构上开设有第二通孔；其中，所述母缸筒与相邻的所述子缸筒间，所述限位装置卡设在所述第一通孔中并延伸至所述盲孔中；相邻的所述子缸筒间，所述限位装置卡设在所述子缸筒的所述第二通孔中并延伸至相邻的所述子缸筒的所述盲孔中。
用于回收运载火箭的多级气动支撑缸用于回收运载火箭的多级气动支撑缸用于回收运载火箭的多级气动支撑缸用于回收运载火箭的多级气动支撑缸用于回收运载火箭的多级气动支撑缸
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所述缓冲装置为油气式缓冲器。
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所述油气式缓冲器包括套设在位于所述伸缩部的所述子缸筒内的缸杆，所述缸杆可沿所述子缸筒内壁移动。
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所述缸杆为一端开口的中空结构，所述开口位于所述子缸筒内部，所述缸杆的 中空结构与所述子缸筒的内腔连通构成第一腔体；所述缸杆的开口上设置连接所述子缸杆的外壁与所述缸筒的内壁的连接板，所述缸杆的外壁、所述缸筒的内壁与所述连接板构成第二腔体。
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所述第一腔体存储有油液；
所述第二腔体内设置有可移动的活塞，所述活塞将所述第二腔体分割成第一子腔体和第二子腔体，所述第二子腔体内存储有带压气体。
在某些实施方式中，所述的用于回收运载火箭的多级气动支撑缸中，所述第一子腔体上设置有单向阀和阻尼孔；
所述阻尼孔用于将所述第一腔体内的油液排放至所述第一子腔体内；
所述单向阀用于将所述第一子腔体内的油液排放至所述第一腔体内。
本发明另一方面还提供一种运载火箭，其包括上面所述的多级气动支撑缸。
本发明实施例的运载火箭及用于回收运载火箭的多级气动支撑缸至少具有如下之一的有益效果：
本发明所述的用于回收运载火箭的多级气动支撑缸中，燃气发生器内燃气推动多个子缸筒伸出并固定，当火箭回收着陆时，多级气动支撑缸起到支撑作用，本发明所述的用于回收运载火箭的多级气动支撑缸具有结构简单、安全可靠和总体重量轻的优点。
本发明所述的用于回收运载火箭的多级气动支撑缸中，当子缸筒伸出后，利用限位装置对子缸筒进行固定，缓冲减震性能优异，多级子缸筒间的密封要求低，生产加工成本较低。
本发明所述的用于回收运载火箭的多级气动支撑缸中，在缸筒的伸缩部设置有油气式缓冲器，油气式缓冲器内的气动原理推动，可有效地减轻的支撑缸的重量，从而减轻火箭回收着陆装置的整体重量，增强火箭的运载能力。
本发明所述的用于回收运载火箭的多级气动支撑缸在使用过程中，火箭 回收着地过程中，其四条腿着地有先后，其第一条腿着地时，多级气动支撑缸对其起到支撑和减震缓冲作用，随着第二、三、四条腿，第一条腿承受的压力减少，油气式缓冲器将缸杆伸出，迅速扶正火箭的倾斜姿势，起到扶正纠偏作用。
附图说明
图1是本发明其中一个实施方式中所述的用于回收运载火箭的多级气动支撑缸中收缩状态的结构示意图；
图2是本发明其中一个实施方式中所述的用于回收运载火箭的多级气动支撑缸中伸出状态的第一结构示意图；
图3是本发明其中一个实施方式中所述的用于回收运载火箭的多级气动支撑缸中伸出状态的第二结构示意图；
图4是图3中相邻子缸筒间或母缸筒与相邻子缸筒间连接结构的局部放大图；
图5是本发明其中一个实施方式中所述的用于回收运载火箭的多级气动支撑缸中缓冲装置的结构示意图。
附图标记：
1代表缸筒，10代表母缸筒，101代表第一凸起结构，102代表第一通孔，11代表子缸筒，111代表第一凸起结构，112代表第二凸起结构，113代表盲孔，114代表第二通孔，12代表限位装置，2代表燃气发生器，3代表缓冲装置，31代表缸杆，32代表第一腔体，33代表连接板，34代表第二腔体，341代表活塞，342代表第一子腔体，343代表第二子腔体，35代表单向阀，36代表阻尼孔，4代表调节气囊。
具体实施方式
现详细说明本发明的多种示例性实施方式，该详细说明不应认为是对本 发明的限制，而应理解为是对本发明的某些方面、特性和实施方案的更详细的描述。
应理解本发明中所述的术语仅仅是为描述特别的实施方式，并非用于限制本发明。另外，对于本发明中的数值范围，应理解为具体公开了该范围的上限和下限以及它们之间的每个中间值。在任何陈述值或陈述范围内的中间值以及任何其他陈述值或在所述范围内的中间值之间的每个较小的范围也包括在本发明内。这些较小范围的上限和下限可独立地包括或排除在范围内。
除非另有说明，否则本文使用的所有技术和科学术语具有本发明所述领域的常规技术人员通常理解的相同含义。虽然本发明仅描述了优选的方法和材料，但是在本发明的实施或测试中也可以使用与本文所述相似或等同的任何方法和材料。本说明书中提到的所有文献通过引用并入，用以公开和描述与所述文献相关的方法和/或材料。在与任何并入的文献冲突时，以本说明书的内容为准。
在不背离本发明的范围或精神的情况下，可对本发明说明书的具体实施方式做多种改进和变化，这对本领域技术人员而言是显而易见的。本申请说明书和实施例仅是示例性的。
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“和/或”，包括所述事物的任一或全部组合。
以下通过具体实施方式，并结合附图对本发明作进一步说明。
如图1至图4所示，本发明提供一种用于回收运载火箭的多级气动支撑缸，其中，该多级气动支撑缸包括：
缸筒1，其包括母缸筒10和套设在一起并设于所述母缸筒10内的多个子缸筒11；所述母缸筒构成所述缸筒1的固定部，所述多个子缸筒构成所述缸筒1的伸缩部；设置在所述母缸筒内部的的燃气发生器2；以及，设置在所述伸缩部的缓冲装置3；所述燃气发生器2用于通过在启动时形成气体以推动所 述多个子缸筒11沿所述母缸筒的轴向方向伸长，所述缓冲装置3用于对着陆火箭的受力进行缓冲。
本发明所述的用于回收运载火箭的多级气动支撑缸其在使用的过程中，燃气发生器2可以设置在母缸筒10的底部，燃气发生器2在控制信号的控制下点火，燃气发生器2产生具有一定压强的燃气，燃气产生的动力推动多个子缸筒11伸出并固定。缓冲装置3设置在伸缩部内部，且缓冲装置3位于子缸筒远离所述母缸筒底部的内部。当火箭回收着陆时，处于伸出状态的缸筒1起到支撑火箭的目的，且位于伸缩部的缓冲装置3对火箭起到减震缓冲的作用。
上述方案中，燃气发生器2用于向所述缸筒1提供动力，所述燃气发生器2可以使用其他经化学反应产生的气源或外引气源代替。
上述方案中，如图4所示，所述缸筒1还包括设置在相邻两个所述子缸筒11间或所述母缸筒与相邻的所述子缸筒11间的限位装置12，所述子缸筒11伸出至相邻的所述子缸筒11或母缸筒的预定位置后，所述限位装置12选择地将所述子缸筒11固定在所述预定位置。
当火箭回收着陆时，处于伸出状态的缸筒1，通过限位装置12将母缸筒10与相邻的子缸筒11固定在预定位置，同时，通过限位装置12将相邻的两个子缸筒11固定在预定位置，保障缸筒1处于伸出状态。
上述方案中，其中，所述母缸筒10的内壁上设置有第一凸起结构101，所述子缸筒11一端的外壁设置有第二凸起结构111，所述子缸筒11另一端的内壁上设置有第三凸起结构112，其中，所述母缸筒10与其相邻的所述子缸筒11间通过所述第一凸起结构101和所述第二凸起结构111相互配合，相邻的两个所述子缸筒11间，通过所述第三凸起结构112与所述第二凸起结构111相互配合。
同时，所述第一凸起结构101上开设有一第一通孔102，所述第二凸起结构112上与所述通孔102对应位置处一盲孔113，所述第三凸起结构上开设有第二通孔114；其中，所述母缸筒10与相邻的所述子缸筒11间，所述限位装置12卡设在所述第一通孔102中并延伸至所述盲孔113中，实现将母缸筒10和 相邻的子缸筒11固定在预定位置；相邻的所述子缸筒11间，所述限位装置12卡设在所述子缸筒11的所述第二通孔114中并延伸至相邻的所述子缸筒11的所述盲孔113中，实现将相邻的两个子缸筒11固定在预定位置。
上述方案中，例如，所述限位装置12为锁止销、锁止块、锁止球、棘轮或偏心轮。
上述方案中，所述缓冲装置3为液压阻尼装置、空气弹簧或机械弹簧。
如图5所示，在本发明所述的用于回收运载火箭的多级气动支撑缸的其中一实施方式中，所述缓冲装置3为油气式缓冲器。
所述油气式缓冲器包括套设在位于所述伸缩部的所述子缸筒11内的缸杆31，所述缸杆31可沿所述子缸筒11内壁移动。
所述缸杆31为一端开口的中空结构，所述开口位于所述子缸筒11内部，所述缸杆31的中空结构与所述子缸筒11的内腔连通构成第一腔体32；所述缸杆31的开口上设置连接所述子缸杆31的外壁与所述子缸筒11的内壁的连接板33，所述缸杆31的外壁、所述子缸筒11的内壁与所述连接板33构成第二腔体34。
上述方案中，所述第一腔体32存储有油液；所述第二腔体34内设置有可移动的活塞341，所述活塞341将所述第二腔体34分割成第一子腔体342和第二子腔体343，所述第二子腔体343内存储有带压气体。
上述方案中，所述第一子腔体342上设置有单向阀35和阻尼孔36；所述阻尼孔36用于将所述第一腔体32内的油液排放至所述第一子腔体342内；所述单向阀35用于将所述第一子腔体342内的油液排放至所述第一腔体32内。
上述方案中，在第二子腔体343的外壁上设置有调节气囊4，利用调节气囊4调节第二子腔体343内空气的压力值。
在火箭回收着陆过程中，四条着陆支腿落地会有先后，当第一条支腿着地时，其多级气动支撑缸上的油气缓冲装置受到冲击，缸杆31受力向下运动，推动第一腔体32内的油液经阻尼孔36进入第一子腔体342内，油液在第一子腔体342内累计进而推动活塞341向第二子腔体343运动，压缩第二子腔体343 内的气体，使第二子腔体343内压力增大，油液阻尼和带压气体对火箭着陆起到减震缓冲作用；随后第二、三、四条支腿着地，此时第一条支腿承受的压力减小，油气缓冲装置中活塞341在第二子腔体343中的压缩空气的作用下向第一子腔体342运动，第一子腔体342中的油液经由单向阀35排出至第一腔体32中，油液在第一腔体32中累计并推动缸杆31伸出，迅速扶正火箭的倾斜姿势，此过程中油气缓冲装置起扶正、纠偏作用。
本发明还提供一种运载火箭，其包括上述所述的多级气动支撑缸。
在不背离本发明的范围或精神的情况下，可对本发明说明书的具体实施方式做多种改进和变化，这对本领域技术人员而言是显而易见的。由本发明的说明书得到的其他实施方式对技术人员而言是显而易见得的。本申请说明书和实施例仅是示例性的。

Claims (11)

  1. 一种用于回收运载火箭的多级气动支撑缸，其中，该多级气动支撑缸包括：
    缸筒(1)，其包括母缸筒(10)和套设在一起并至少部分设于所述母缸筒(10)内的多个子缸筒(11)；所述母缸筒构成所述缸筒(1)的固定部，所述多个子缸筒构成所述缸筒(1)的伸缩部；
    设置在所述母缸筒内部的的燃气发生器(2)；以及，
    设置在所述伸缩部的缓冲装置(3)；
    所述燃气发生器(2)用于通过在启动时形成气体以推动所述多个子缸筒(11)沿所述母缸筒的轴向方向伸长，所述缓冲装置(3)用于对着陆火箭的受力进行缓冲。
  2. 根据权利要求1所述的用于回收运载火箭的多级气动支撑缸，其中，所述缸筒(1)还包括设置在相邻两个所述子缸筒(11)间或所述母缸筒与相邻的所述子缸筒(11)间的限位装置(12)，所述子缸筒(11)伸出至相邻的所述子缸筒(11)或母缸筒的预定位置后，所述限位装置(12)选择地将所述子缸筒(11)固定在所述预定位置。
  3. 根据权利要求2所述的用于回收运载火箭的多级气动支撑缸，其中，所述限位装置(12)为锁止销、锁止块、锁止球、棘轮或偏心轮。
  4. 根据权利要求2所述的用于回收运载火箭的多级气动支撑缸，其中，所述母缸筒(10)的内壁上设置有第一凸起结构(101)，所述子缸筒(11)一端的外壁设置有第二凸起结构(111)，所述子缸筒(11)另一端的内壁上设置有第三凸起结构(112)；
    其中，所述母缸筒(10)与其相邻的所述子缸筒(11)间通过所述第一凸起结构(101)和所述第二凸起结构(111)相互配合，相邻的两个所述子缸筒(11)间，通过所述第三凸起结构(112)与所述第二凸起结构(111)相互配合。
  5. 根据权利要求4所述的用于回收运载火箭的多级气动支撑缸，其中，所述第一凸起结构(101)上开设有一第一通孔(102)，所述第二凸起结构 (112)上与所述通孔(102)对应位置处一盲孔(113)，所述第三凸起结构上开设有第二通孔(114)；
    其中，所述母缸筒(10)与相邻的所述子缸筒(11)间，所述限位装置(12)卡设在所述第一通孔(102)中并延伸至所述盲孔(113)中；相邻的两个所述子缸筒(11)间，所述限位装置(12)卡设在所述子缸筒(11)的所述第二通孔(114)中并延伸至相邻的所述子缸筒(11)的所述盲孔(113)中。
  6. 根据权利要求1所述的用于回收运载火箭的多级气动支撑缸，其中，所述缓冲装置(3)为油气式缓冲器。
  7. 根据权利要求6所述的用于回收运载火箭的多级气动支撑缸，其中，所述油气式缓冲器包括套设在位于所述伸缩部的所述子缸筒(11)内的缸杆(31)，所述缸杆(31)沿所述子缸筒(11)内壁移动。
  8. 根据权利要求7所述的用于回收运载火箭的多级气动支撑缸，其中，所述缸杆(31)为一端开口的中空结构，所述开口位于所述子缸筒(11)内部，所述缸杆(31)的开口上设置连接所述子缸筒(11)的外壁与所述缸筒(1)的内壁的连接板(33)，所述缸杆(31)的中空结构与所述子缸筒(11)的内腔连通构成第一腔体(32)，所述缸杆(31)的外壁、所述子缸筒(11)的内壁与所述连接板(33)构成第二腔体(34)。
  9. 根据权利要求8所述的用于回收运载火箭的多级气动支撑缸，其中，所述第一腔体(32)存储有油液；
    所述第二腔体(34)内设置有可移动的活塞(341)，所述活塞(341)将所述第二腔体(34)分割成第一子腔体(342)和第二子腔体(343)，所述第二子腔体(343)内存储有带压气体。
  10. 根据权利要求9所述的用于回收运载火箭的多级气动支撑缸，其中，所述第一子腔体(342)上设置有单向阀(35)和阻尼孔(36)；
    所述阻尼孔(36)用于将所述第一腔体(32)内的油液排放至所述第一子腔体(342)内；
    所述单向阀(35)用于将所述第一子腔体(342)内的油液排放至所述第一腔体(32)内。
  11. 一种运载火箭，其特征在于，包括如权利要求1-10任一项所述的多级气动支撑缸。
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