CN119554364A - Reliable recoil and rebound-free recoil buffer cylinder for rocket launch - Google Patents
Reliable recoil and rebound-free recoil buffer cylinder for rocket launch Download PDFInfo
- Publication number
- CN119554364A CN119554364A CN202411527468.6A CN202411527468A CN119554364A CN 119554364 A CN119554364 A CN 119554364A CN 202411527468 A CN202411527468 A CN 202411527468A CN 119554364 A CN119554364 A CN 119554364A
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- buffer
- cylinder
- piston
- cylinder body
- rod
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Classifications
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F13/00—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs
- F16F13/005—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising both a wound spring and a damper, e.g. a friction damper
- F16F13/007—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising both a wound spring and a damper, e.g. a friction damper the damper being a fluid damper
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
The invention relates to a cylinder, in particular to a reliable backward-tilting and rebound-free backward-tilting buffer cylinder for rocket launching, which comprises a cylinder body, a cylinder piston rod, a cylinder piston, a spring, a buffer cylinder body, a buffer piston, a throttle rod and a connecting piece, wherein one end of the cylinder body is provided with an air inlet, the buffer cylinder body, the buffer piston and the throttle rod are all positioned in a rodless cavity of the cylinder body, the center lines of the cylinder piston, the throttle rod and the buffer piston are on the same straight line, hydraulic oil is filled in the rodless cavity of the buffer cylinder body, a pressure measuring port is arranged on the buffer cylinder body, one end part of the buffer piston, which is positioned in the buffer cylinder body, is provided with a through hole, the other end part of the throttle rod is arranged in the through hole, a gap is reserved between the through hole and the throttle rod, and the gap forms an annular throttle oil duct. The invention can drive the support arm to reliably and quickly fall back after the rocket is ignited and has no rebound after falling back.
Description
Technical Field
The invention relates to a cylinder, in particular to a reliable backward tilting buffer cylinder without rebound for rocket launching.
Background
In the technical field of aerospace launching, the supporting arm is an important structure for supporting a rocket body, and for the rocket supporting arm for waist supporting, backward falling measures are needed to be adopted to avoid that after an aircraft takes off and separates, the supporting arm supports a part of the supporting arm to interfere with structures such as the rocket body, a spray pipe and the like. The requirements of aerospace engineering on reliability and safety are extremely high, and the supporting arm needs to be reliably and quickly tilted back after rocket ignition. Because the main body of the supporting arm is generally heavy and has larger kinetic energy in the rapid backward tilting process, the supporting arm is easy to generate larger rebound after being tilted in place, and the rebound supporting arm can collide with an arrow body after taking off in severe cases, thereby influencing the taking off safety. Thus, there is a need for a support arm that does not bounce.
Disclosure of Invention
The technical problem to be solved by the invention is to provide the reliable backward dumping buffer cylinder for rocket launching, which can drive the supporting arm to reliably and rapidly backward dump after rocket ignition and has no rebound after backward dumping.
In order to solve the technical problems, the application provides the following technical scheme:
The invention discloses a reliable backward-tilting and rebound-free backward-tilting buffer cylinder for rocket launching, which comprises a cylinder body, a cylinder piston rod, a cylinder piston, a spring, a buffer cylinder body, a buffer piston, a throttle rod and a connecting piece, wherein the cylinder piston is connected to one end of the cylinder piston rod, the spring is sleeved on the cylinder piston rod, the spring is positioned between the front end of the cylinder body and the cylinder piston, an air inlet is arranged at one end of a rodless cavity of the cylinder body, the buffer piston and the throttle rod are all positioned in a rodless cavity of the cylinder body, the buffer cylinder body is connected to the rear end of the cylinder body, the buffer piston is a hollow piece, the throttle rod and one end of the buffer piston are all arranged in the buffer cylinder body, the throttle rod is arranged along the length direction of the buffer cylinder body, the center lines of the cylinder piston, the throttle rod and the buffer piston are positioned on the same straight line, one end of the throttle rod is connected to the buffer cylinder body, the rodless cavity is provided with a hydraulic oil gap, the buffer piston is provided with an annular gap, the other end is provided with a through hole, and the buffer piston is provided with a through hole.
Further, the cylinder piston comprises a piston seat and a piston ring, wherein the piston seat is connected to the cylinder piston rod, the piston ring is connected to the outer wall of the piston seat, and the piston ring is in contact with the inner wall of the cylinder body.
Further, the spring is divided into a first spring section and a second spring section, the outer wall of the piston rod of the cylinder is connected with a spring partition plate, a first rigid support plate and a second rigid support plate, the first rigid support plate and the second rigid support plate are respectively positioned on two sides of the spring partition plate, the first spring section is sleeved on the first rigid support plate, the second spring section is sleeved on the second rigid support plate, the width of the first rigid support plate is equal to the length of the first spring section after being fully compressed, and the width of the second rigid support plate is equal to the length of the second spring section after being fully compressed.
Further, the cylinder body comprises a front end cover, a rear end cover and a cylinder barrel which are connected with each other, the inner ring of the front end cover is in contact with the piston rod of the cylinder, and the air inlet is formed in the rear end cover.
Further, the piston rod assembly further comprises a bushing, wherein the bushing is connected to the inner ring of the front end cover, and the bushing is in contact with the piston rod of the cylinder.
Further, the device further comprises a connecting piece, wherein the connecting piece is connected to one end part of the cylinder piston rod, which is positioned outside the cylinder body, and is used for connecting a supported piece, and the connecting piece is a rod end bearing.
Further, the device also comprises a mounting piece, wherein the mounting piece is a supporting lug arranged on the rear end cover, and the cylinder body is connected with the supported piece through the supporting lug.
Further, a pressure measuring channel is arranged on the rear end cover and is communicated with the pressure measuring port.
Further, the outer wall of the throttle lever is stepped, and the diameter of one end of the throttle lever, which is far away from the buffer piston, is larger than the diameter of one end, which is close to the buffer piston.
Further, a central hole extending along the length direction is formed in the throttle rod, the pressure measuring channel is communicated with the central hole, and a pressure measuring joint is arranged at the tail end of the pressure measuring channel.
Compared with the prior art, the reliable backward tilting and rebound-free backward tilting buffer cylinder for rocket launching has at least the following beneficial effects:
the invention relates to a reliable backward tilting buffer cylinder without rebound for rocket launching, which comprises a buffer cylinder body, a buffer piston and a throttle rod, wherein the buffer piston is a hollow piece, a gap is reserved between a through hole at the end part of the buffer piston and the throttle rod, the gap forms an annular throttle oil duct, and the central lines of the cylinder piston, the throttle rod and the buffer piston are on the same straight line.
The reliable backward tilting and rebound-free backward tilting buffer cylinder for rocket launching according to the invention is further described below with reference to the accompanying drawings.
Drawings
FIG. 1 is a front view of a reliable back-dump, non-bouncing back-dump surge tank for rocket launch according to the present invention;
FIG. 2 is an isometric view of a reliable back-dump buffer cylinder for rocket launch without bounce according to the present invention;
FIG. 3 is a cross-sectional view of a reliable, back-dump surge tank for rocket launching of the present invention without bouncing;
FIG. 4 is a cross-sectional view of a reliable, back-up, non-bouncing, back-up buffer cylinder of the present invention in a retracted position for rocket launch;
FIG. 5 is a schematic view of the structure of the reliable backward tilting and non-bouncing backward tilting buffer cylinder for rocket launching in a supporting state after being mounted on a supporting arm;
FIG. 6 is a schematic view of the structure of the reliable backward tilting and bouncing-free backward tilting buffer cylinder for rocket launching in the invention in a backward tilting in-place state after being mounted on a supporting arm.
Detailed Description
As shown in fig. 1,2, 3 and 4, the reliable backward-tilting and rebound-free backward-tilting buffer cylinder for rocket launching comprises a cylinder body 01, a cylinder piston rod 02, a cylinder piston 03, a spring 04, a buffer cylinder body 05, a buffer piston 06, a throttle rod 07, a connecting piece 08 and a mounting piece, wherein the cylinder piston 03 is connected with one end of the cylinder piston rod 02, a sealing device is arranged between the cylinder piston 03 and the cylinder body 01, the spring 04 is sleeved on the cylinder piston rod 02, the spring 04 is positioned between the front end of the cylinder body 01 and the cylinder piston 03, one end of a rodless cavity of the cylinder body 01 is provided with an air inlet 14, the connecting piece 08 is connected with one end of the cylinder piston rod 02, which is positioned outside the cylinder body 01, the connecting piece 08 is used for connecting a supported piece, the mounting piece is connected with one end of the cylinder body 01, which is far away from the cylinder piston rod 02, and the cylinder body 01 are connected with the supported piece through the mounting piece, the buffer cylinder body 05, the buffer piston 06 and the throttle rod 07 are all positioned in a rodless cavity of the cylinder body 01, the buffer cylinder body 05 is connected with the rear end part of the cylinder body 01, the buffer piston 06 is a hollow part, one end of the throttle rod 07 and one end of the buffer piston 06 are both arranged in the buffer cylinder body 05, the buffer piston 06 is suitable for sliding along the axial direction relative to the buffer cylinder body 05, the throttle rod 07 is arranged along the length direction of the buffer cylinder body 05, the center lines of the cylinder piston 03, the throttle rod 07 and the buffer piston 06 are on the same straight line, one end of the throttle rod 07 is connected with the buffer cylinder body 05, the rodless cavity of the buffer cylinder body 05 is filled with hydraulic oil and high-pressure gas, a pressure measuring port is arranged on the buffer cylinder body 05, one end part of the buffer piston 06 positioned in the buffer cylinder body 05 is provided with a through hole 61, the other end part of the throttle rod 07 is arranged in the through hole 61, a gap is left between the through hole 61 and the throttle lever 07, and the gap forms an annular throttle oil passage. In this embodiment, as shown in fig. 5, when the rocket launching device of the present invention is connected to the support arm 10 by using the reliable backward and rebound-free backward buffer cylinder, the connecting member 08 and the mounting member are hinged to the upper and lower hinged ends of the support arm 10 respectively.
The reliable backward tilting and non-rebound backward tilting buffer cylinder for rocket launching has the following use flow:
1) The supporting arm is erected by filling high-pressure gas into a rodless cavity of the cylinder body 01 through the gas inlet 14, and when the pressure in the rodless cavity of the cylinder body 01 is larger than the sum of the pressure of a spring 04 in the rod cavity and the axial component force of gravity of the supporting arm 10, the supporting arm 10 is erected, as shown in fig. 5, and meanwhile the spring 04 is continuously compressed to store elastic potential energy until the supporting arm 10 is erected to 90 degrees;
2) Before rocket is launched, the pressure in the buffer cylinder 05 is required to be measured, the specific method is that a handheld pressure gauge or an online pressure sensor is connected to a pressure measuring port, the air pressure value in the buffer cylinder 05 can be directly read, and when the air pressure does not meet the minimum pressure requirement, the air pressure is supplemented by an air charging device;
3) The high-pressure gas in the rodless cavity of the cylinder body 01 is discharged before the rocket is launched, so that the backward tilting buffer cylinder continuously exerts a pulling load effect on the supporting arm 10 under the tensile force of the spring 04, and the supporting arm 10 cannot tilt backward when the rocket is not separated from the supporting arm 10;
4) Realizing backward movement of the supporting arm, namely, after the rocket leaves the supporting arm 10, the supporting arm 10 falls backward around the lugs at the lower end of the supporting arm under the action of the tension of the springs 04;
5) The buffer braking is realized, namely when the supporting arm 10 is nearly and afterwards poured into place, the end face of the rear end of the cylinder piston rod 02 is in contact with the end face of the front end of the buffer piston 06 and compresses the buffer piston 06, hydraulic oil in the buffer cylinder 05 is forced to flow through an annular throttle oil duct between the buffer piston 06 and the buffer throttle rod 07 to generate flow resistance, so that buffer braking force on the cylinder piston rod 02 is formed, the buffer braking force can be provided for the cylinder piston rod 02 in the whole travel range of the buffer piston 06, and when the supporting arm 10 is reversely poured into place, the kinetic energy of the supporting arm 10 is completely converted into liquid internal energy in the buffer cylinder 05, so that the back pouring of the supporting arm 10 is realized without rebound, as shown in fig. 6.
The invention relates to a reliable backward tilting and rebound-free backward tilting buffer cylinder for rocket launching, which comprises a buffer cylinder body 05, a buffer piston 06 and a throttle rod 07, wherein the buffer piston 06 is a hollow piece, a gap is reserved between a through hole 61 at the end part of the buffer piston 06 and the throttle rod 07, the gap forms an annular throttle oil duct, and the central lines of the cylinder piston 03, the throttle rod 07 and the buffer piston 06 are on the same straight line, so that when a support arm 10 is tilted backward, the cylinder piston 03 compresses the buffer piston 06, the backward tilting energy dissipation of the support arm 10 is realized by adopting liquid throttling, the kinetic energy of the support arm 10 is converted into liquid internal energy, the support arm is enabled to be tilted backward fast and rebound-free, one end of a rodless cavity of the cylinder body 01 is provided with an air inlet 14, and a pressure measuring port is arranged on the buffer cylinder body 05, so that the air inlet and the pressure measuring port are separated.
Alternatively, the cylinder piston 03 comprises a piston seat 31, a piston ring 32, the piston seat 31 being connected to the cylinder piston rod 02, the piston ring 32 being connected to the outer wall of the piston seat 31, the piston ring 32 being in contact with the inner wall of the cylinder block 01. Specifically, the piston seat 31 is made of steel, and is used for bearing spring load and buffering load, the piston ring 32 is made of copper and is used for sliding in cooperation with the inner wall of the cylinder body, the piston seat 31 is connected to the cylinder piston rod 02 through the lock nut 33, the piston ring 32 is connected to the piston seat 31 in a threaded manner, and a sealing ring and a dust ring are arranged on the outer surface of the piston ring 32.
Optionally, the spring 04 is divided into a first spring section 41 and a second spring section 42, the outer wall of the cylinder piston rod 02 is provided with a spring partition 21, a first rigid support plate 22 and a second rigid support plate 23, the spring partition 21, the first rigid support plate 22 and the second rigid support plate 23 are overlapped with the cylinder piston rod 02, the first rigid support plate 22 and the second rigid support plate 23 are respectively positioned at two sides of the spring partition 21, the first spring section 41 is sleeved on the first rigid support plate 22, the second spring section 42 is sleeved on the second rigid support plate 23, the first spring section 41 and the second spring section 42 form a series spring, the width of the first rigid support plate 22 is equal to the length of the first spring section 41 after being fully compressed, and the width of the second rigid support plate 23 is equal to the length of the second spring section 41 after being fully compressed. Specifically, the first rigid support plate 22 and the second rigid support plate 23 are annular plates connected to the outer wall of the cylinder piston rod 02, and the spring separator 21 is a radial boss connected to the outer wall of the cylinder piston rod 02. In the process of erecting the supporting arm, when high-pressure gas is filled into the rodless cavity of the cylinder body 01, the pressure in the rodless cavity of the cylinder body 01 is larger than the sum of the pressure of the spring 04 in the rod cavity and the axial component force of the gravity of the supporting arm 10, the first spring section 41 and the second spring section 42 are continuously compressed to store elastic potential energy until the supporting arm 10 is erected to 90 degrees, the two ends of the first rigid supporting plate 22 and the second rigid supporting plate 23 are pressed by the front end part of the cylinder body 01, the spring partition plate 21 and the piston seat 31, after the rocket leaves the supporting arm 10, the supporting arm 10 is reversed around the supporting lug at the lower end of the supporting arm under the action of the tension of the first spring section 41 and the second spring section 42, if one section of springs fails, the failed springs still keep the initial working height due to the supporting action of the first rigid supporting plate 22 and the second rigid supporting plate 23, the backward reversing action of the supporting arm 10 can still be realized under the action of the tension of the other section of the non-failed springs, and the backward reversing action of the supporting arm 10 is realized, and the high reliability requirements of space engineering are met.
Alternatively, the cylinder block 01 includes a front end cover 11, a rear end cover 12, and a cylinder tube 13 connected to each other, the inner ring of the front end cover 11 is in contact with the cylinder piston rod 02, and an intake port 14 is provided on the rear end cover 12. Specifically, the cylinder 13 is connected with the front end cover 11 through bolts, and a dust ring is arranged on the inner ring of the front end cover 11. The damper cylinder 05 includes a damper front end cover 51 and a damper cylinder 52 connected to each other.
Optionally, a bushing 15 is further included, the bushing 15 is connected to the inner ring of the front end cover 11, and the bushing 15 contacts and slides in cooperation with the cylinder piston rod 02. The bushing 15 is made of copper.
Alternatively, the connection 08 is a rod end bearing. The rod end bearing is connected with one lug of the supporting arm 10, so that the supporting arm 10 can conveniently perform actions such as rising, falling and the like.
Alternatively, the mounting member is a support lug 121 provided on the rear end cover 12, and the cylinder block 01 is mounted and connected to the supported member through the support lug 121.
Optionally, a pressure measuring channel 122 is provided on the rear end cap 12, and the pressure measuring channel 122 is in communication with a pressure measuring port on the damper cylinder 05.
Alternatively, the outer wall of the throttle lever 07 is stepped, and the diameter of the end of the throttle lever 07 remote from the damper piston 06 is larger than the diameter of the end close to the damper piston 06. The diameter change of the throttle lever 07 can ensure that the buffer load changes with the compression stroke according to the required rule.
Optionally, a central hole extending in the length direction is provided in the throttle lever 07, and the pressure measuring channel 122 communicates with the central hole, and the end of the pressure measuring channel 122 is provided with a pressure measuring joint 123. When the pressure in the buffer cylinder 05 is required to be measured, the pressure measuring connector 123 is connected by using a handheld pressure gauge or an online pressure sensor, so that the method is convenient and quick.
The above examples are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solution of the present invention should fall within the scope of protection defined by the claims of the present invention without departing from the spirit of the present invention.
Claims (10)
1. The reliable backward tilting and rebound-free backward tilting buffer cylinder for rocket launching is characterized by comprising a cylinder body (01), a cylinder piston rod (02), a cylinder piston (03), a spring (04), a buffer cylinder body (05), a buffer piston (06), a throttle rod (07) and a connecting piece (08), wherein the cylinder piston is connected to one end of the cylinder piston rod (02), the spring (04) is sleeved on the cylinder piston rod (02) and is positioned between the front end part of the cylinder body (01) and the cylinder piston (03), one end of a rodless cavity of the cylinder body (01) is provided with an air inlet (14), the buffer cylinder body (05), the buffer piston (06) and the throttle rod (07) are all positioned in a rodless cavity of the cylinder body (01), the buffer cylinder body (05) is connected with the rear end part of the cylinder body (01), the buffer piston (06) is a hollow part, one ends of the throttle rod (07) and the buffer piston (06) are all arranged in the buffer cylinder body (05), the throttle rod (07) is arranged along the length direction of the buffer cylinder body (05), the center lines of the cylinder piston (03), the throttle rod (07) and the buffer piston (06) are on the same straight line, the hydraulic oil buffer is characterized in that one end of the throttle rod (07) is connected to the buffer cylinder body (05), hydraulic oil is filled in a rodless cavity of the buffer cylinder body (05), a pressure measuring port is formed in the buffer cylinder body (05), a through hole (61) is formed in one end part of the buffer piston (06) located in the buffer cylinder body (05), the other end part of the throttle rod (07) is arranged in the through hole (61), a gap is reserved between the through hole (61) and the throttle rod (07), and an annular throttle oil duct is formed in the gap.
2. A reliable, rebound-free, and backfall-buffering cylinder for rocket launching according to claim 1, wherein the cylinder piston (03) comprises a piston seat (31), a piston ring (32), the piston seat (31) being connected to the cylinder piston rod (02), the piston ring (32) being connected to the outer wall of the piston seat (31), the piston ring (32) being in contact with the inner wall of the cylinder block (01).
3. A reliable backward tilting and rebound-free backward tilting buffer cylinder for rocket launching according to claim 1, wherein the spring (04) is divided into a first spring section (41) and a second spring section (42), the outer wall of the cylinder piston rod (02) is connected with a spring partition plate (21), a first rigid support plate (22) and a second rigid support plate (23), the first rigid support plate (22) and the second rigid support plate (23) are respectively positioned at two sides of the spring partition plate (21), the first spring section (41) is sleeved on the first rigid support plate (22), the second spring section (42) is sleeved on the second rigid support plate (23), the width of the first rigid support plate (22) is equal to the length of the first spring section (41) after being fully compressed, and the width of the second rigid support plate (23) is equal to the length of the second spring section (41) after being fully compressed.
4. A reliable backward tilting and bouncing-free backward tilting buffer cylinder for rocket launching according to claim 1, characterized in that the cylinder body (01) comprises a front end cover (11), a rear end cover (12) and a cylinder barrel (13) which are connected with each other, the inner ring of the front end cover (11) is contacted with the cylinder piston rod (02), and the air inlet (14) is arranged on the rear end cover (12).
5. A reliable, rebound-free, recoil buffer cylinder for rocket launches according to claim 4, further comprising a bushing (15), said bushing (15) being connected to the inner ring of said front end cap (11), said bushing (15) being in contact with said cylinder piston rod (02).
6. A reliable, rebound-free, back-up buffer cylinder for rocket launch according to claim 1 further comprising a connecting member (08), said connecting member (08) being connected to an end of said cylinder piston rod (02) which is located outside said cylinder block (01), said connecting member (08) being for connecting a supported member, said connecting member (08) being a rod end bearing.
7. A reliable, non-bouncing, back-tipping buffer tank for rocket launch according to claim 4, characterized in that it further comprises a mounting member, said mounting member being a lug (121) provided on said rear end cap (12), said cylinder block (01) being connected to said supported member by means of said lug (121).
8. A reliable, rebound-free, back-dumping buffer cylinder for rocket launch according to claim 4 wherein said rear end cap (12) is provided with a pressure measuring channel (122), said pressure measuring channel (122) communicating with said pressure measuring port.
9. A reliable, rebound-free, back-dumping buffer cylinder for rocket launch according to claim 8 wherein the outer wall of said throttle lever (07) is stepped, the diameter of the end of said throttle lever (07) remote from said buffer piston (06) being greater than the diameter of the end near said buffer piston (06).
10. A reliable backward dumping buffer cylinder for rocket launching according to claim 9, characterized in that a central hole extending along the length direction is arranged in the throttle lever (07), the pressure measuring channel (122) is communicated with the central hole, and the end of the pressure measuring channel (122) is provided with a pressure measuring joint (123).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411527468.6A CN119554364B (en) | 2024-10-30 | 2024-10-30 | Reliable recoil and rebound-free recoil buffer cylinder for rocket launch |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411527468.6A CN119554364B (en) | 2024-10-30 | 2024-10-30 | Reliable recoil and rebound-free recoil buffer cylinder for rocket launch |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN119554364A true CN119554364A (en) | 2025-03-04 |
| CN119554364B CN119554364B (en) | 2025-10-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411527468.6A Active CN119554364B (en) | 2024-10-30 | 2024-10-30 | Reliable recoil and rebound-free recoil buffer cylinder for rocket launch |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US20070194506A1 (en) * | 2006-02-23 | 2007-08-23 | Barnes Group Inc., A Corporation Of Delaware | Force control strut |
| CN101639106A (en) * | 2009-08-25 | 2010-02-03 | 深圳市中车业成实业有限公司 | Piston-type hydro-pneumatic buffer |
| CN205446257U (en) * | 2016-03-30 | 2016-08-10 | 安徽合力股份有限公司 | Large -tonnage jack -up system buffering hydro -cylinder |
| CN108679305A (en) * | 2018-03-30 | 2018-10-19 | 北京航天发射技术研究所 | It is a kind of prevent connector from falling off after the support device that springs back |
| CN109573108A (en) * | 2018-12-29 | 2019-04-05 | 哈尔滨工业大学 | One kind is towards reusable rocket landing supporting leg formula two-stage buffer |
| CN114435617A (en) * | 2022-01-28 | 2022-05-06 | 北京航天发射技术研究所 | Launching platform supporting arm with backward falling function and method |
-
2024
- 2024-10-30 CN CN202411527468.6A patent/CN119554364B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070194506A1 (en) * | 2006-02-23 | 2007-08-23 | Barnes Group Inc., A Corporation Of Delaware | Force control strut |
| CN101639106A (en) * | 2009-08-25 | 2010-02-03 | 深圳市中车业成实业有限公司 | Piston-type hydro-pneumatic buffer |
| CN205446257U (en) * | 2016-03-30 | 2016-08-10 | 安徽合力股份有限公司 | Large -tonnage jack -up system buffering hydro -cylinder |
| CN108679305A (en) * | 2018-03-30 | 2018-10-19 | 北京航天发射技术研究所 | It is a kind of prevent connector from falling off after the support device that springs back |
| CN109573108A (en) * | 2018-12-29 | 2019-04-05 | 哈尔滨工业大学 | One kind is towards reusable rocket landing supporting leg formula two-stage buffer |
| CN114435617A (en) * | 2022-01-28 | 2022-05-06 | 北京航天发射技术研究所 | Launching platform supporting arm with backward falling function and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN119554364B (en) | 2025-10-24 |
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