CN109764025B - Carrier rocket and multistage pneumatic support cylinder for recycling carrier rocket - Google Patents
Carrier rocket and multistage pneumatic support cylinder for recycling carrier rocket Download PDFInfo
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- CN109764025B CN109764025B CN201910068004.6A CN201910068004A CN109764025B CN 109764025 B CN109764025 B CN 109764025B CN 201910068004 A CN201910068004 A CN 201910068004A CN 109764025 B CN109764025 B CN 109764025B
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- cylinder barrel
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- recovering
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- 238000004064 recycling Methods 0.000 title description 4
- 239000000872 buffer Substances 0.000 claims abstract description 29
- 238000013016 damping Methods 0.000 claims abstract description 15
- 238000000034 method Methods 0.000 claims abstract description 9
- 230000003139 buffering effect Effects 0.000 claims description 7
- 238000007599 discharging Methods 0.000 claims description 5
- 230000008602 contraction Effects 0.000 claims description 2
- 239000004215 Carbon black (E152) Substances 0.000 claims 1
- 229930195733 hydrocarbon Natural products 0.000 claims 1
- 150000002430 hydrocarbons Chemical class 0.000 claims 1
- 238000011084 recovery Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Classifications
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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
Landscapes
- 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)
- Actuator (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides a carrier rocket and a multistage pneumatic support cylinder for recovering the carrier rocket, wherein the multistage pneumatic support cylinder comprises: the cylinder barrel comprises a master cylinder barrel and a plurality of sub cylinder barrels sleeved together and arranged in the master cylinder barrel; the main cylinder barrel forms a fixed part of the cylinder barrel, and the plurality of sub cylinder barrels form telescopic parts of the cylinder barrel; the gas generator is arranged in the female cylinder barrel; and a buffer device arranged on the telescopic part. The multistage pneumatic support cylinder for recovering the carrier rocket has the advantages of safety, reliability and light overall weight, and can meet the requirements of quick opening, supporting, damping and centralizing deviation correction of a rocket landing device in the using process.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a carrier rocket and a multistage pneumatic support cylinder for recycling the carrier rocket.
Background
At present, fewer rocket landing devices are arranged in China, and the existing landing devices adopt fixed supporting legs and electric cylinders as landing supporting legs. The fixed support leg is only suitable for recovery tests and is not suitable for rocket recovery landing. The electric cylinder is used as a landing leg, can accurately open a rocket landing device and can provide support, and landing recovery can be realized in principle, but because the electric cylinder is heavy in weight and is additionally provided with a buffer device, the whole recovery landing device is heavy, the carrying capacity of a rocket is reduced, and the explosion-proof level requirement of the liquid rocket on the electric cylinder is higher.
Therefore, how to provide a safe, reliable, light-weight multi-stage pneumatic support cylinder for recovering a carrier rocket is a technical problem to be solved by those skilled in the art.
Disclosure of Invention
In order to solve at least part of the above technical problems, the present invention provides a multistage pneumatic support cylinder for recovering a carrier rocket, wherein the multistage pneumatic support cylinder comprises: the cylinder barrel comprises a master cylinder barrel and a plurality of slave cylinder barrels sleeved together and arranged in the master cylinder barrel; the main cylinder barrel forms a fixed part of the cylinder barrel, and the plurality of sub cylinder barrels form telescopic parts of the cylinder barrel; the gas generator is arranged in the female cylinder barrel; and a buffer device provided in the expansion part; the gas generator is used for pushing the plurality of sub-cylinders to extend along the axial direction of the main cylinder through forming gas when starting, and the buffer device is used for buffering the stress of the landing rocket.
In some embodiments, in the multistage pneumatic supporting cylinder for recovering a carrier rocket, the cylinder further includes a limiting device disposed between two adjacent sub-cylinders or between the main cylinder and the adjacent sub-cylinders, and after the sub-cylinders extend to a predetermined position of the adjacent sub-cylinder or main cylinder, the limiting device selectively fixes the sub-cylinders at the predetermined position.
In some embodiments, the limiting device is a locking pin, a locking block, a locking ball, a ratchet wheel or an eccentric wheel in the multistage pneumatic supporting cylinder for recovering the carrier rocket.
In some embodiments, in the multistage pneumatic supporting cylinder for recovering the carrier rocket, a first protruding structure is arranged on the inner wall of the mother cylinder, a second protruding structure is arranged on the outer wall of one end of the sub cylinder, and a third protruding structure is arranged on the inner wall of the other end of the sub cylinder; the main cylinder barrel and the adjacent sub cylinder barrels are mutually matched through the first protruding structures and the second protruding structures, and the adjacent sub cylinder barrels are mutually matched through the third protruding structures and the second protruding structures.
In some embodiments, in the multistage pneumatic supporting cylinder for recovering a carrier rocket, a first through hole is formed in the first protruding structure, a blind hole is formed in a position, corresponding to the through hole, of the second protruding structure, and a second through hole is formed in the third protruding structure; the limiting device is clamped in the first through hole and extends into the blind hole between the main cylinder barrel and the adjacent sub cylinder barrel; and the limiting device is clamped in the second through hole of the sub cylinder barrel and extends into the blind hole of the adjacent sub cylinder barrel.
Multistage pneumatic support cylinder for recovering carrier rocket multistage pneumatic support cylinder
In some embodiments, the buffer device is an oil-gas type buffer in the multistage pneumatic supporting cylinder for recovering the carrier rocket.
In some embodiments, in the multistage pneumatic supporting cylinder for recovering a carrier rocket, the oil-gas type buffer comprises a cylinder rod sleeved in the sub-cylinder barrel of the telescopic part, and the cylinder rod can move along the inner wall of the sub-cylinder barrel.
In some embodiments, in the multistage pneumatic supporting cylinder for recovering the carrier rocket, the cylinder rod is a hollow structure with one end open, the opening is positioned in the sub-cylinder barrel, and the hollow structure of the cylinder rod is communicated with the inner cavity of the sub-cylinder barrel to form a first cavity; the opening of the cylinder rod is provided with a connecting plate for connecting the outer wall of the sub-cylinder rod with the inner wall of the cylinder barrel, and the outer wall of the cylinder rod, the inner wall of the cylinder barrel and the connecting plate form a second cavity.
In some embodiments, the first cavity stores oil in the multi-stage pneumatic supporting cylinder for recovering the carrier rocket;
the movable piston is arranged in the second cavity, the second cavity is divided into a first subcavity and a second subcavity by the piston, and pressurized gas is stored in the second subcavity.
In some embodiments, in the multistage pneumatic supporting cylinder for recovering the carrier rocket, the first subchamber is provided with a check valve and a damping hole;
the damping hole is used for discharging oil in the first cavity into the first subchamber;
the one-way valve is used for discharging oil in the first subchamber into the first chamber.
In another aspect the invention provides a launch vehicle comprising a multistage pneumatic support cylinder as described above.
The carrier rocket and the multistage pneumatic support cylinder for recovering the carrier rocket have at least one of the following beneficial effects:
in the multistage pneumatic supporting cylinder for recovering the carrier rocket, the gas in the gas generator drives the plurality of sub cylinders to extend and fix, and the multistage pneumatic supporting cylinder plays a supporting role when the rocket is recovered and landed.
In the multistage pneumatic supporting cylinder for recovering the carrier rocket, after the sub-cylinder is extended, the sub-cylinder is fixed by the limiting device, so that the multistage pneumatic supporting cylinder has excellent buffering and damping performance, the sealing requirements among the multistage sub-cylinders are low, and the production and processing cost is low.
In the multistage pneumatic supporting cylinder for recovering the carrier rocket, the oil-gas type buffer is arranged at the telescopic part of the cylinder barrel, and the pneumatic principle in the oil-gas type buffer pushes the supporting cylinder, so that the weight of the supporting cylinder can be effectively reduced, the whole weight of a rocket recovering and landing device is reduced, and the carrying capacity of the rocket is enhanced.
In the using process of the multistage pneumatic supporting cylinder for recovering the carrier rocket, four legs of the multistage pneumatic supporting cylinder are grounded successively, when the first leg of the multistage pneumatic supporting cylinder is grounded, the multistage pneumatic supporting cylinder plays roles in supporting, damping and buffering the multistage pneumatic supporting cylinder, and along with the reduction of the pressure born by the first leg along with the second leg, the third leg and the fourth leg, the oil-gas type buffer stretches out the cylinder rod to quickly straighten the inclined posture of the rocket, so that the centralizing and rectifying effects are achieved.
Drawings
FIG. 1 is a schematic view of a contracted state in a multi-stage pneumatic support cylinder for recovering a launch vehicle according to one embodiment of the present invention;
FIG. 2 is a first schematic view of an extended configuration of a multi-stage pneumatic support cylinder for recovering a launch vehicle according to one embodiment of the present invention;
FIG. 3 is a second schematic view of an extended configuration of a multi-stage pneumatic support cylinder for recovering a launch vehicle according to one embodiment of the present invention;
FIG. 4 is an enlarged view of a portion of the connection structure between adjacent sub-cylinders or between a parent cylinder and adjacent sub-cylinders in FIG. 3;
fig. 5 is a schematic structural view of a buffer device in a multistage pneumatic support cylinder for recovering a carrier rocket according to one embodiment of the present invention.
Reference numerals:
1. representing cylinder, 10 representing master cylinder, 101 representing first bump structure, 102 representing first through hole, 11 representing slave cylinder, 111 representing second bump structure, 112 representing third bump structure, 113 representing blind hole, 114 representing second through hole, 12 representing stop device, 2 representing gas generator, 3 representing buffer device, 31 representing cylinder rod, 32 representing first cavity, 33 representing connecting plate, 34 representing second cavity, 341 representing piston, 342 representing first sub-cavity, 343 representing second sub-cavity, 35 representing check valve, 36 representing damping hole, 4 representing regulating air bag.
Detailed Description
Various exemplary embodiments of the invention will now be described in detail, which should not be considered as limiting the invention, but rather as more detailed descriptions of certain aspects, features and embodiments of the invention.
It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. In addition, for numerical ranges in the present invention, it is understood that the upper and lower limits of the ranges and each intermediate value therebetween are specifically disclosed. Every smaller range between any stated value or stated range, and any other stated value or intermediate value within the stated range, is also encompassed within the invention. The upper and lower limits of these smaller ranges may independently be included or excluded in the range.
Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Although only preferred methods and materials are described herein, any methods and materials similar or equivalent to those described herein can be used in the practice or testing of the present invention. All documents mentioned in this specification are incorporated by reference for the purpose of disclosing and describing the methods and/or materials associated with the documents. In case of conflict with any incorporated document, the present specification will control.
It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the invention described herein without departing from the scope or spirit of the invention. The specification and examples are exemplary only.
As used herein, the terms "comprising," "including," "having," "containing," and the like are intended to be inclusive and mean an inclusion, but not limited to.
As used herein, "and/or" includes any or all combinations of such things.
The invention is further described below by means of specific embodiments in connection with the accompanying drawings.
As shown in fig. 1 to 4, the present invention provides a multistage pneumatic support cylinder for recovering a carrier rocket, wherein the multistage pneumatic support cylinder comprises:
the cylinder barrel 1 comprises a master cylinder barrel 10 and a plurality of slave cylinder barrels 11 sleeved together and arranged in the master cylinder barrel 10; the master cylinder barrel forms a fixed part of the cylinder barrel 1, and the plurality of slave cylinder barrels form telescopic parts of the cylinder barrel 1; a gas generator 2 disposed inside the parent cylinder; and a buffer device 3 provided in the expansion and contraction section; the gas generator 2 is used for pushing the plurality of sub-cylinders 11 to extend along the axial direction of the main cylinder by forming gas when starting, and the buffer device 3 is used for buffering the stress of the landing rocket.
In the using process of the multistage pneumatic supporting cylinder for recovering the carrier rocket, the gas generator 2 can be arranged at the bottom of the master cylinder 10, the gas generator 2 ignites under the control of a control signal, the gas generator 2 generates gas with certain pressure, and the power generated by the gas pushes the plurality of slave cylinders 11 to stretch out and fix. The buffer device 3 is arranged inside the telescopic part, and the buffer device 3 is positioned inside the sub cylinder barrel far away from the bottom of the main cylinder barrel. When the rocket is recovered and landed, the cylinder barrel 1 in the extending state plays a role in supporting the rocket, and the buffer device 3 positioned at the telescopic part plays a role in damping and buffering the rocket.
In the above-mentioned solution, the gas generator 2 is used to power the cylinder 1, and the gas generator 2 may be replaced by other gas sources or external gas sources generated by chemical reactions.
In the above-mentioned scheme, as shown in fig. 4, the cylinder 1 further includes a limiting device 12 disposed between two adjacent sub-cylinders 11 or between the main cylinder and the adjacent sub-cylinders 11, and after the sub-cylinders 11 extend to a predetermined position of the adjacent sub-cylinders 11 or main cylinder, the limiting device 12 selectively fixes the sub-cylinders 11 at the predetermined position.
When the rocket is recovered and landed, the cylinder barrel 1 in the extending state is fixed at a preset position by the main cylinder barrel 10 and the adjacent sub cylinder barrels 11 through the limiting device 12, and meanwhile, the adjacent two sub cylinder barrels 11 are fixed at the preset position through the limiting device 12, so that the cylinder barrel 1 is ensured to be in the extending state.
In the above-mentioned scheme, wherein, be provided with first protruding structure 101 on the inner wall of parent cylinder 10, the outer wall of son cylinder 11 one end is provided with second protruding structure 111, be provided with third protruding structure 112 on the inner wall of son cylinder 11 other end, wherein, parent cylinder 10 with its adjacent between son cylinder 11 pass through first protruding structure 101 with second protruding structure 111 mutually support, adjacent two between son cylinder 11, pass through third protruding structure 112 mutually support with second protruding structure 111.
Meanwhile, a first through hole 102 is formed in the first protruding structure 101, a blind hole 113 is formed in the second protruding structure 111 at a position corresponding to the through hole 102, and a second through hole 114 is formed in the third protruding structure; wherein, the limiting device 12 is clamped in the first through hole 102 and extends into the blind hole 113 between the master cylinder 10 and the adjacent slave cylinder 11, so as to fix the master cylinder 10 and the adjacent slave cylinder 11 at a predetermined position; between adjacent sub-cylinders 11, the limiting device 12 is clamped in the second through hole 114 of the sub-cylinder 11 and extends into the blind hole 113 of the adjacent sub-cylinder 11, so as to fix the two adjacent sub-cylinders 11 at a predetermined position.
In the above embodiments, the limiting device 12 is, for example, a locking pin, a locking block, a locking ball, a ratchet, or an eccentric.
In the above scheme, the buffer device 3 is a hydraulic damping device, an air spring or a mechanical spring.
As shown in fig. 5, in one embodiment of the multi-stage pneumatic support cylinder for recovering a carrier rocket according to the present invention, the buffer device 3 is an oil-gas type buffer.
The oil-gas type buffer comprises 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 opening at one end, the opening is positioned in the sub-cylinder 11, and the hollow structure of the cylinder rod 31 is communicated 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 for connecting the outer wall of the sub cylinder rod 31 and the inner wall of the sub cylinder 11, and the outer wall of the cylinder rod 31, the inner wall of the sub cylinder 11 and the connecting plate 33 form a second cavity 34.
In the above solution, the first cavity 32 stores oil; a movable piston 341 is disposed in the second cavity 34, the piston 341 divides the second cavity 34 into a first sub-cavity 342 and a second sub-cavity 343, and pressurized gas is stored in the second sub-cavity 343.
In the above solution, the first subchamber 342 is provided with a check valve 35 and a damping hole 36; the damping hole 36 is used for discharging the oil in the first cavity 32 into the first subchamber 342; the check valve 35 is configured to discharge the oil in the first sub-chamber 342 into the first chamber 32.
In the above-mentioned scheme, the adjusting air bag 4 is disposed on the outer wall of the second subchamber 343, and the pressure value of the air in the second subchamber 343 is adjusted by using the adjusting air bag 4.
In the process of rocket recycling landing, four landing legs are successively landed, when a first landing leg lands, an oil-gas buffer device on a multi-stage pneumatic supporting cylinder is impacted, a cylinder rod 31 is stressed to move downwards, oil in a first cavity 32 is pushed to enter a first subchamber 342 through a damping hole 36, the oil is accumulated in the first subchamber 342 so as to push a piston 341 to move towards a second subchamber 343, gas in the second subchamber 343 is compressed, the pressure in the second subchamber 343 is increased, and the oil damping and the gas with pressure play a role in damping and buffering the rocket landing; then the second, third and fourth supporting legs are grounded, at this time, the pressure born by the first supporting leg is reduced, the piston 341 in the oil-gas buffer device moves towards the first subchamber 342 under the action of compressed air in the second subchamber 343, oil in the first subchamber 342 is discharged into the first chamber 32 through the one-way valve 35, the oil accumulates in the first chamber 32 and pushes the cylinder rod 31 to extend out, the inclined posture of the rocket is quickly straightened, and in the process, the oil-gas buffer device plays a role in centralizing and rectifying.
The invention also provides a carrier rocket which comprises the multistage pneumatic support cylinder.
It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the invention described herein without departing from the scope or spirit of the invention. Other embodiments will be apparent to those skilled in the art from consideration of the specification of the present invention. The specification and examples are exemplary only.
Claims (8)
1. A multi-stage pneumatic support cylinder for recovering a launch vehicle, wherein the multi-stage pneumatic support cylinder comprises:
the cylinder barrel (1) comprises a master cylinder barrel (10) and a plurality of sub-cylinder barrels (11) sleeved together and at least partially arranged in the master cylinder barrel (10); the main cylinder barrel forms a fixed part of the cylinder barrel (1), and the plurality of sub cylinder barrels form telescopic parts of the cylinder barrel (1);
a gas generator (2) arranged inside the master cylinder; the method comprises the steps of,
a buffer device (3) provided in the expansion/contraction section;
the gas generator (2) is used for pushing the plurality of sub-cylinders (11) to extend along the axial direction of the main cylinder by forming gas when being started, and the buffer device (3) is used for buffering the stress of the landing rocket;
the buffer device comprises a cylinder rod (31) sleeved in the sub-cylinder (11) of the telescopic part, and the cylinder rod (31) moves along the inner wall of the sub-cylinder (11);
the cylinder rod (31) is of a hollow structure with one end open, the opening is positioned in the sub-cylinder barrel (11), a connecting plate (33) for connecting the outer wall of the sub-cylinder barrel (11) and the inner wall of the cylinder barrel (1) is arranged on the opening of the cylinder rod (31), the hollow structure of the cylinder rod (31) is communicated with the inner cavity of the sub-cylinder barrel (11) to form a first cavity (32), and the outer wall of the cylinder rod (31), the inner wall of the sub-cylinder barrel (11) and the connecting plate (33) form a second cavity (34); the first cavity (32) stores oil;
the cylinder barrel (1) further comprises limiting devices (12) arranged between two adjacent sub-cylinder barrels (11) or between the main cylinder barrel and the adjacent sub-cylinder barrels (11), and after the sub-cylinder barrels (11) extend to the preset positions of the adjacent sub-cylinder barrels (11) or the main cylinder barrel, the limiting devices (12) selectively fix the sub-cylinder barrels (11) at the preset positions.
2. Multistage pneumatic support cylinder for recovering a launch vehicle according to claim 1, wherein said limiting means (12) are a locking pin, a locking block, a locking ball, a ratchet or an eccentric.
3. The multistage pneumatic support cylinder for recovering a carrier rocket according to claim 1, wherein a first protruding structure (101) is provided on the inner wall of the parent cylinder (10), a second protruding structure (111) is provided on the outer wall of one end of the child cylinder (11), and a third protruding structure (112) is provided on the inner wall of the other end of the child cylinder (11);
the main cylinder barrel (10) is matched with the adjacent sub cylinder barrels (11) through the first bulge structures (101) and the second bulge structures (111), and the adjacent sub cylinder barrels (11) are matched with the second bulge structures (111) through the third bulge structures (112).
4. A multistage pneumatic support cylinder for recovering a launch vehicle according to claim 3, wherein a first through hole (102) is formed in the first protruding structure (101), a blind hole (113) is formed in the second protruding structure (111) at a position corresponding to the through hole (102), and a second through hole (114) is formed in the third protruding structure;
the limiting device (12) is clamped in the first through hole (102) and extends into the blind hole (113) between the main cylinder barrel (10) and the adjacent sub cylinder barrel (11); between two adjacent sub-cylinders (11), the limiting device (12) is clamped in the second through hole (114) of the sub-cylinder (11) and extends into the blind hole (113) of the adjacent sub-cylinder (11).
5. Multistage pneumatic support cylinder for recovering a launch vehicle according to claim 1, wherein said buffer means (3) are hydrocarbon buffers.
6. A multistage pneumatic support cylinder for recovering a launch vehicle according to any one of claims 1 to 5, wherein a movable piston (341) is provided inside said second cavity (34), said piston (341) dividing said second cavity (34) into a first sub-cavity (342) and a second sub-cavity (343), said second sub-cavity (343) storing a gas under pressure.
7. The multistage pneumatic support cylinder for recovering a launch vehicle according to claim 6, wherein said first subchamber (342) is provided with a check valve (35) and a damping hole (36);
the damping hole (36) is used for discharging oil in the first cavity (32) into the first subchamber (342);
the one-way valve (35) is used for discharging oil in the first subchamber (342) into the first chamber (32).
8. A launch vehicle comprising a multistage pneumatic support cylinder according to any one of claims 1 to 7.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910068004.6A CN109764025B (en) | 2019-01-24 | 2019-01-24 | Carrier rocket and multistage pneumatic support cylinder for recycling carrier rocket |
| PCT/CN2020/073597 WO2020151718A1 (en) | 2019-01-24 | 2020-01-21 | Launch vehicle and multi-stage pneumatic support cylinder for recovering launch vehicle |
| JP2021543118A JP7253061B2 (en) | 2019-01-24 | 2020-01-21 | Launch vehicle and multi-stage pneumatic support cylinders for retrieving the launch vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910068004.6A CN109764025B (en) | 2019-01-24 | 2019-01-24 | Carrier rocket and multistage pneumatic support cylinder for recycling carrier rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109764025A CN109764025A (en) | 2019-05-17 |
| CN109764025B true CN109764025B (en) | 2024-03-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910068004.6A Active CN109764025B (en) | 2019-01-24 | 2019-01-24 | Carrier rocket and multistage pneumatic support cylinder for recycling carrier rocket |
Country Status (3)
| Country | Link |
|---|---|
| JP (1) | JP7253061B2 (en) |
| CN (1) | CN109764025B (en) |
| WO (1) | WO2020151718A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109764025B (en) * | 2019-01-24 | 2024-03-26 | 蓝箭航天空间科技股份有限公司 | Carrier rocket and multistage pneumatic support cylinder for recycling carrier rocket |
| CN110844125B (en) * | 2019-12-17 | 2024-01-30 | 中国科学院沈阳自动化研究所 | Reusable leg type landing buffer device |
| CN111795034A (en) * | 2020-07-20 | 2020-10-20 | 北京航天发射技术研究所 | Gas actuator |
| CN113247313B (en) * | 2021-07-02 | 2022-08-19 | 中国人民解放军战略支援部队航天工程大学 | Flexible variant airship for recycling carrier rocket booster and recycling method |
| CN115507710B (en) * | 2022-09-27 | 2023-09-05 | 北京星河动力装备科技有限公司 | Rocket landing telescopic arm and rocket recovery device |
| CN117087877B (en) * | 2023-10-20 | 2024-01-30 | 北京凌空天行科技有限责任公司 | High-impact landing support and carrier rocket landing mechanism |
| CN117326102A (en) * | 2023-10-24 | 2024-01-02 | 北京林业大学 | Vertical recovery device for heavy carrier rocket |
| CN117963174B (en) * | 2024-03-28 | 2024-06-25 | 江苏深蓝航天有限公司 | Aircraft landing buffer device, aircraft landing control system and aircraft |
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Also Published As
| Publication number | Publication date |
|---|---|
| WO2020151718A1 (en) | 2020-07-30 |
| JP2022519029A (en) | 2022-03-18 |
| JP7253061B2 (en) | 2023-04-05 |
| CN109764025A (en) | 2019-05-17 |
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