CN110671977A - Reusable carrier rocket landing buffering device - Google Patents
Reusable carrier rocket landing buffering device Download PDFInfo
- Publication number
- CN110671977A CN110671977A CN201911001691.6A CN201911001691A CN110671977A CN 110671977 A CN110671977 A CN 110671977A CN 201911001691 A CN201911001691 A CN 201911001691A CN 110671977 A CN110671977 A CN 110671977A
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- buffer
- lock
- shell
- unfolding
- cylinder barrel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
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- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a reusable carrier rocket landing buffer device, which comprises: at least three sets of buffer mechanisms; at least three sets of buffer mechanisms are circumferentially and uniformly distributed around the tail end of the arrow body and are connected with the arrow body; a cushioning mechanism comprising: the device comprises N compaction release mechanisms, main strut unfolding joints, auxiliary unfolding devices, shell unfolding joints, foldable main struts, a shell and a buffer; the top end of the main strut capable of being unfolded and folded is connected with the arrow body through the main strut unfolding joint; the bottom end of the extensible main strut is fixedly connected with one end of a buffer through a flange, and the other end of the buffer is hinged with the head of the shell; the tail part of the shell is connected with the arrow body through a shell unfolding joint; one end of the auxiliary unfolding device is connected with the arrow body, and the other end of the auxiliary unfolding device points to the outer side of the arrow body at a certain angle; n compaction release mechanisms are uniformly distributed on the outer side of the arrow body. The invention solves the problems of small buffer capacity, poor landing stability, low unfolding speed and the like of the conventional landing buffer device.
Description
Technical Field
The invention belongs to the technical field of carrier rocket soft landing buffering, and particularly relates to a reusable carrier rocket landing buffering device.
Background
The lander bears a large impact acceleration at the landing moment, and if the impact load is too large, the detection equipment carried on the lander is damaged, so that the detection task fails. Therefore, whether the landing device can realize soft landing on the surface of the planet has important significance for the development of space science and technology.
At present, the landing buffer device can be roughly divided into an air bag type and a leg type, the air bag buffer takes an inflatable air bag as a landing buffering energy absorption element, the first lander which successfully lands on the surface of the moon by human, namely the Luna 9 lunar probe in the former Soviet Union, is the air bag buffer, and in addition, the air bag type lander is successfully utilized in the United states in 2003 to be matched with a parachute to realize the soft landing of the two probes of Spirit and Opportunit at Mars. The leg type lander is usually provided with a buffer inside a landing leg, absorbs impact energy through the compression deformation of the buffer in the landing process, and has the advantages of stable landing posture, high reliability, easy control, no rebound and adjustability in landing and the like. Landing leg type landing cushions have been used in Apollo manned landers in the United states, Luna 16 in the former Soviet Union, Hiten in Japan, and Euromoon 2000 for the European Bureau of Engineers project.
Most of the prior art is only suitable for the planet detector with smaller landing load and has no repeated use function.
Disclosure of Invention
The technical problem of the invention is solved: the landing buffer device overcomes the defects of the prior art, provides a reusable carrier rocket landing buffer device, and solves the problems of small buffer capacity, poor landing stability, low unfolding speed and the like of the conventional landing buffer device.
In order to solve the technical problem, the invention discloses a reusable carrier rocket landing buffer device, which is characterized by comprising the following components: at least three sets of buffer mechanisms have the same structure; the at least three sets of buffer mechanisms are uniformly distributed around the tail end of the arrow body in the circumferential direction and are connected with the arrow body;
a cushioning mechanism comprising: the device comprises N compaction release mechanisms, main strut unfolding joints, auxiliary unfolding devices, shell unfolding joints, foldable main struts, a shell and a buffer;
the top end of the main strut capable of being unfolded and folded is connected with the arrow body through a main strut unfolding joint, and the main strut capable of being unfolded and folded can rotate around the main strut unfolding joint;
the bottom end of the extensible main strut is fixedly connected with one end of a buffer through a flange, and the other end of the buffer is hinged with the head of the shell;
the tail part of the shell is connected with the arrow body through a shell unfolding joint, and the shell can rotate around the shell unfolding joint;
one end of the auxiliary unfolding device is connected with the arrow body, and the other end of the auxiliary unfolding device points to the outer side of the arrow body according to a certain angle theta;
the N pressing release mechanisms are uniformly distributed on the outer side of the arrow body and press the buffer mechanism on the arrow body in a furled state of the buffer mechanism.
The invention has the following advantages:
(1) in the invention, the main telescopic strut, the pressing release mechanism, the auxiliary unfolding device and the like all adopt a single fluid driving source, and the advantages of high unfolding speed, light weight, less resource requirement, high reliability and the like are realized
(2) In the launching section, the reusable carrier rocket landing buffer device is uniformly folded and attached to the periphery of the tail section of the rocket body, and has good pneumatic performance so as to reduce pneumatic influence; after the landing buffer device is unfolded, the main support, the shell and the arrow body can be unfolded and folded to form a stable triangular structure, so that the landing stability and the bearing capacity are improved.
(3) The same landing buffer devices are uniformly distributed around the arrow body, the peripheral space of the arrow body can be fully utilized by the structural form of the outward swinging type, the supporting area after the arrow body is unfolded is increased to the maximum extent, and the landing stability is improved.
Drawings
FIG. 1 is a schematic structural diagram of a reusable launch vehicle landing gear in an embodiment of the invention in an expanded state;
FIG. 2 is a schematic view of a reusable launch vehicle landing gear in a collapsed configuration in accordance with an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a collapsible main column according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a compression release mechanism according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the embodiments of the present invention will be described in detail with reference to the accompanying drawings.
The invention discloses a reusable carrier rocket landing buffering device which comprises a plurality of sets of same buffering mechanisms arranged on a rocket body, wherein each set of buffering mechanism comprises a retractable main support, an auxiliary unfolding device, a pressing and releasing mechanism, a buffer and a shell. One end of the telescopic main strut is rotatably connected with the arrow body, the other end of the telescopic main strut is fixedly connected with the buffer through the flange, and the other end of the buffer is rotatably connected with the shell; the shell is in a triangular structure, two hinges on the short side are rotatably connected with the arrow body, and the rest hinge is rotatably connected with the buffer. During deployment, the collapsible main struts are deployed from a collapsed state, such as in figure 2, to deploy the landing gear from a collapsed state to a deployed state, such as in figure 1.
Specifically, as shown in fig. 1 and 2, the reusable launch vehicle landing buffer device comprises: at least three sets of buffer mechanisms 100, wherein the three sets of buffer mechanisms 100 have the same structure; wherein, three at least sets of buffer gear 100 circumference equipartitions are around the arrow body 1 tail end, are connected with the arrow body 1.
Preferably, the buffer mechanism may specifically include: the device comprises N compaction release mechanisms 2, a main strut unfolding joint 3, an auxiliary unfolding device 4, a shell unfolding joint 5, a foldable main strut 6, a shell 7 and a buffer 8. Wherein, the top end of the main strut 6 which can be unfolded and folded is connected with the arrow body 1 through the main strut unfolding joint 3, and the main strut 6 which can be unfolded and folded can rotate around the main strut unfolding joint 3; the bottom end of the extensible main strut 6 is fixedly connected with one end of a buffer 8 through a flange, and the other end of the buffer 8 is hinged with the head of the shell 7; the tail part of the shell 7 is connected with the arrow body 1 through the shell unfolding joint 5, and the shell 7 can rotate around the shell unfolding joint 5; one end of the auxiliary unfolding device 4 is connected with the arrow body 1, and the other end of the auxiliary unfolding device points to the outer side of the arrow body 1 according to a certain angle theta; the N pressing and releasing mechanisms 2 are uniformly distributed on the outer side of the arrow body 1, and press the buffer mechanism on the arrow body 1 in a furled state of the buffer mechanism.
Preferably, in the present embodiment, the housing 7 is turned up in the rocket launching section and is fixed to the rocket body by a plurality of compression release mechanisms. The outer surface of the shell 7 is specially designed, so that the shell has good aerodynamic characteristics and heat insulation characteristics; the inner cavity of the shell 7 is used for coating the extensible main support, the auxiliary unfolding device, the buffer and the like in a relatively closed space, so that the adverse effect of the tail flame of the engine on the product is prevented.
Preferably, in the present embodiment, the main expandable/contractible strut 6 is composed of an expandable air inlet, a collapsible air inlet, a multi-stage support sleeve, a strut locking/unlocking assembly and a sealing member; the multi-stage supporting sleeve is formed by mutually nesting a plurality of stages of coaxial sleeve structures with different diameters, the sleeves at all stages can slide mutually, and the sleeves at all stages are locked under the action of the strut locking and unlocking assembly after sliding in place; the main expandable/contractible strut 6 can realize the functions of repeatedly expanding, locking, unlocking and contracting under the action of air pressure drive or gravity. Furthermore, the number of nesting layers of the supporting sleeve can be designed according to the expanding or contracting length and the contracting envelope of the supporting legs.
Preferably, the auxiliary unfolding device 4 is formed by mutually nesting multiple levels of unfolding sleeves, the unfolding sleeves at all levels can slide mutually and are driven to unfold by an air pressure or hydraulic driving working medium, and a sealing ring is arranged between every two adjacent unfolding sleeves to prevent the leakage of an internal high-pressure driving working medium. After the pressing and releasing mechanism 2 unlocks the shell 7, the shell 7 is in a vertical state, and if the supporting legs are unfolded, clamping stagnation is generated due to the fact that dead points exist, so that the shell 7 is pushed away from an arrow body by a certain angle by the aid of an auxiliary unfolding device, the main supporting column 6 can be unfolded and folded after the supporting legs rotate past the dead points, and the shell 7 and the supporting legs are moved to an unfolding state.
Preferably, the compression release mechanism 2 consists of a compression release locking and unlocking assembly, a pre-tightening assembly, a mounting support and an adapter piece; the bottom of the compression release mechanism 2 is connected with the arrow body 1 through a mounting support, and the top of the compression release mechanism presses the shell 7 on the arrow body 1 through a pre-tightening assembly; the compression release mechanism 2 changes the position relation between two cylinders with different diameters and a locking ball in the compression release locking and unlocking assembly by controlling the magnitude relation between the spring force and the air pressure driving force to realize locking and unlocking, and can be recycled for many times, thereby realizing the compression and cold separation between the shell 7 and the arrow body 1.
Preferably, the buffer 8 can adopt a gas-liquid buffer or a honeycomb buffer or a series connection of the gas-liquid buffer and the honeycomb buffer for buffering and absorbing energy.
Example 2
As shown in fig. 3, in the present embodiment, the main expandable/contractible strut 6 may specifically include: a bottom end cover 10, a cylinder barrel inner lock and a top end cover 18; wherein, the cylinder includes: the cylinder barrel I11, the cylinder barrel II 13, the cylinder barrel III 15 and the cylinder barrel IV 17; the cylinder internal lock includes: cylinder inner lock I12, cylinder inner lock II 14 and cylinder inner lock III 16.
Preferably, the bottom end cover 10 is fixedly connected with a cylinder barrel I11, the cylinder barrel I11 is connected with a cylinder barrel II 13 through a cylinder barrel inner lock I12, the cylinder barrel II 13 is connected with a cylinder barrel III 15 through a cylinder barrel inner lock II 14, the cylinder barrel III 15 is connected with a cylinder barrel IV 17 through a cylinder barrel inner lock III 16, and the top end cover 18 is installed at the end part of the cylinder barrel IV 17 to form a four-stage pneumatic telescopic mechanism; the bottom head cover 10 is provided with a deployment inlet 101, and the top head cover 18 is provided with a release inlet 181.
In this embodiment, the collapsible main column 6 may further include: a strut lock and unlock assembly. The support locking and unlocking assembly can be installed between adjacent supporting sleeves, and is a wedge-shaped block locking assembly capable of automatically locking under the action of elastic force, wherein the wedge-shaped block is embedded between a lock cylinder and a piston of the cylinder inner lock and is uniformly installed along the circumferential direction, and the function of in-place locking of the multi-stage cylinder barrel is realized as a lock cylinder.
Specifically, this pillar locking and unlocking subassembly includes: support ring 19, sealing ring 20, lock cylinder 21, wedge 22, first piston 23, lock spring 24 and unlocking ring 25. Wherein, the supporting ring 19 and the sealing ring 20 are installed at the end of the first piston 23, the locking spring 24 and the unlocking ring 25 are installed at the tail part of the first piston 23, and the wedge block 22 is positioned between the lock cylinder 21 and the first piston 23.
Preferably, the support ring 19 and the seal ring 20 are matched with the inner lock of the cylinder barrel for use and form a sliding kinematic pair with the inner wall or the outer wall of the cylinder barrel; the four-stage pneumatic telescopic mechanism can realize reliable unfolding and locking functions under the ventilation action of an unfolding air inlet of the bottom end cover 10; when the four-stage pneumatic telescopic mechanism is unfolded in place, the cylinder is locked in place under the elastic action of the upper locking spring 24, the wedge block 22 is automatically pushed to move along the axial direction and is nested between the lock cylinder 21 and the first piston 23, and the locking and locking functions are realized; the four-stage pneumatic telescoping mechanism can realize the unlocking function under the ventilation action of the unlocking air inlet of the top end cover 18.
As shown in fig. 4, in this embodiment, the pressing and releasing mechanism 2 may specifically include: the piston type hydraulic cylinder comprises a base 26, a second piston 27, a spring 28, a stop 29, a pull rod 30, a lock sleeve 31, an upper lock cap 32, a slide block 33, a lock nut 34, a lock ball 35 and a force bearing bowl 36. The second piston 27 is mounted inside the base 26, the spring 28 is located between the base 26 and the stopper 29, the pull rod 30 is mounted in the lock sleeve 31 and contacts with the lock ball 35, the lock ball 35 is mounted on the lock sleeve 31, the upper lock cap 32 and the slide block 33 are mounted on the shell 7, and the lock nut 34 and the bearing bowl 36 are mounted at the end of the pull rod 30 and contact with the slide block 33.
Preferably, the compression release mechanism 2 locks the housing 7 on the arrow body 1 through the positional constraint of the upper lock cap 32, the base 26 and the lock ball 35, and exerts a constraint force through the lock nut 34 and the force bearing bowl 36, and the compression force transmission path are provided by the upper lock cap 32 and the base 26. Before landing, the air inlet between the base 26 and the secondary piston 27 starts to vent, pushing the secondary piston 27 to slide to the right against the pressure of the spring 28. The groove position on the second piston 27 reaches the lock ball 35, and the lock ball 35 enters the groove of the second piston 27 through the inner hole of the lock sleeve 31 under the pushing action of the pull rod 30 to release the restraint on the pull rod 30, so that the unlocking is realized. When the housing 7 moves the pull rod 30 from the right during rotation of the housing 7, the stopper 29 moves to the right to fix the lock ball 35 in the groove of the second piston 27.
In an embodiment of the present invention, the reusable launch vehicle landing buffer may further comprise: the foot pad 9 is landed. Wherein, the landing foot pad 9 is arranged at the end part 7 of the shell and connected with the shell 7.
Wherein, the value range of N is 3-9; the value range of theta is 30-60 degrees.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (10)
1. A reusable launch vehicle landing cushioning device, comprising: at least three sets of buffer mechanisms (100), wherein the three sets of buffer mechanisms (100) have the same structure; wherein, the at least three sets of buffer mechanisms (100) are uniformly distributed around the tail end of the arrow body (1) in the circumferential direction and are connected with the arrow body (1);
a cushioning mechanism comprising: the device comprises N compaction release mechanisms (2), main strut unfolding joints (3), auxiliary unfolding devices (4), shell unfolding joints (5), foldable main struts (6), a shell (7) and a buffer (8);
the top end of the main strut (6) which can be unfolded and folded is connected with the arrow body (1) through the main strut unfolding joint (3), and the main strut (6) which can be unfolded and folded can rotate around the main strut unfolding joint (3);
the bottom end of the extensible main strut (6) is fixedly connected with one end of a buffer (8) through a flange, and the other end of the buffer (8) is hinged with the head of the shell (7);
the tail part of the shell (7) is connected with the arrow body (1) through the shell unfolding joint (5), and the shell (7) can rotate around the shell unfolding joint (5);
one end of the auxiliary unfolding device (4) is connected with the arrow body (1), and the other end of the auxiliary unfolding device points to the outer side of the arrow body (1) according to a certain angle theta;
the N pressing and releasing mechanisms (2) are uniformly distributed on the outer side of the arrow body (1), and press the buffer mechanism on the arrow body (1) in a furled state of the buffer mechanism.
2. The reusable launch vehicle landing buffer of claim 1, further comprising: a landing foot pad (9); the landing foot pad (9) is arranged at the end part (7) of the shell and is connected with the shell (7).
3. The reusable launch vehicle landing buffer of claim 1,
the buffer (8) adopts a gas-liquid buffer or a honeycomb buffer or a series connection mode of the gas-liquid buffer and the honeycomb buffer to buffer and absorb energy.
4. A reusable launch vehicle landing buffer according to claim 1 wherein the retractable main struts (6) consist of a deployed air inlet, a stowed air inlet, a multi-stage support sleeve, strut locking and unlocking assemblies and seals; the multi-stage supporting sleeves are formed by mutually nesting a plurality of stages of coaxial sleeve structures with different diameters, can slide mutually and are locked under the action of the strut locking and unlocking assembly after sliding in place; the main extensible support (6) can be repeatedly unfolded, locked, unlocked and folded under the action of air pressure drive or gravity.
5. The reusable launch vehicle landing buffer of claim 1, wherein the auxiliary deployment device (4) is formed by nesting multiple stages of deployable sleeves, each stage of deployable sleeves can slide relative to each other and are driven to deploy by a pneumatic or hydraulic driving working medium, and a seal ring is installed between two adjacent stages of deployable sleeves to prevent leakage of an internal high-pressure driving working medium.
6. The reusable launch vehicle landing buffer of claim 1, wherein the compression release mechanism (2) consists of a compression release locking and unlocking assembly, a pretensioning assembly, a mounting bracket and an adaptor; the bottom of the pressing and releasing mechanism (2) is connected with the arrow body (1) through a mounting support, and the top of the pressing and releasing mechanism presses the shell (7) on the arrow body (1) through a pre-tightening assembly; the compression release mechanism (2) changes the position relation between two cylinders with different diameters and a locking ball in the compression release locking and unlocking assembly by controlling the magnitude relation between the spring force and the air pressure driving force to realize locking and unlocking, and can be recycled for many times, thereby realizing compression and cold separation between the shell (7) and the arrow body (1).
7. A reusable launch vehicle landing buffer according to claim 1 or 4, characterised by a retractable main strut (6) comprising: a bottom end cover (10), a cylinder barrel inner lock and a top end cover (18);
the cylinder section includes: a cylinder barrel I (11), a cylinder barrel II (13), a cylinder barrel III (15) and a cylinder barrel IV (17);
the cylinder internal lock includes: a cylinder inner lock I (12), a cylinder inner lock II (14) and a cylinder inner lock III (16);
the bottom end cover (10) is fixedly connected with a cylinder barrel I (11), the cylinder barrel I (11) is connected with a cylinder barrel II (13) through a cylinder barrel inner lock I (12), the cylinder barrel II (13) is connected with a cylinder barrel III (15) through a cylinder barrel inner lock II (14), the cylinder barrel III (15) is connected with a cylinder barrel IV (17) through a cylinder barrel inner lock III (16), and a top end cover (18) is installed at the end part of the cylinder barrel IV (17) to form a four-stage pneumatic telescopic mechanism;
the bottom end cover (10) is provided with an unfolding air inlet (101), and the top end cover (18) is provided with an unlocking air inlet (181).
8. The reusable launch vehicle landing buffer of claim 7, wherein the retractable main strut (6) further comprises: the locking device comprises a support ring (19), a sealing ring (20), a lock cylinder (21), a wedge block (22), a first piston (23), a locking spring (24) and an unlocking ring (25); the support ring (19) and the sealing ring (20) are mounted at the end part of the first piston (23), the locking spring (24) and the unlocking ring (25) are mounted at the tail part of the first piston (23), and the wedge block (22) is positioned between the lock cylinder (21) and the first piston (23);
the support ring (19) and the sealing ring (20) are matched with the inner lock of the cylinder barrel for use and form a sliding kinematic pair with the inner wall or the outer wall of the cylinder barrel;
the four-stage pneumatic telescopic mechanism can realize reliable unfolding and locking functions under the ventilation action of an unfolding air inlet of the bottom end cover (10); when the four-stage pneumatic telescopic mechanism is unfolded in place, the cylinder is locked in the cylinder under the elastic action of an upper locking spring (24), the wedge-shaped block (22) is automatically pushed to move along the axial direction and is nested between the lock cylinder (21) and the first piston (23), and the locking and locking functions are realized;
the four-stage pneumatic telescopic mechanism can realize the unlocking function under the ventilation action of the unlocking air inlet of the top end cover (18).
9. A reusable launch vehicle landing buffer according to claim 1 or 6, characterised in that the compression release mechanism (2) comprises: the device comprises a base (26), a second piston (27), a spring (28), a stop block (29), a pull rod (30), a lock sleeve (31), an upper lock cap (32), a sliding block (33), a lock nut (34), a lock ball (35) and a force bearing bowl (36); the second piston (27) is arranged in the base (26), the spring (28) is positioned between the base (26) and the stop block (29), the pull rod (30) is arranged in the lock sleeve (31) and is contacted with the lock ball (35), the lock ball (35) is arranged on the lock sleeve (31), the upper lock cap (32) and the sliding block (33) are arranged on the shell (7), and the lock nut (34) and the bearing bowl (36) are arranged at the end part of the pull rod (30) and are contacted with the sliding block (33);
the compression release mechanism (2) locks the shell (7) on the arrow body (1) through the position constraint of the upper lock cap (32), the base (26) and the lock ball (35), and exerts constraint force through the lock nut (34) and the bearing bowl (36), and the transmission path of the compression force and the compression force is provided by the upper lock cap (32) and the base (26);
before landing, the air inlet between the base (26) and the second piston (27) starts to vent, pushing the second piston (27) to slide to the right against the pressure of the spring (28). The groove part on the second piston (27) reaches the position of the lock ball (35), and the lock ball (35) enters the groove of the second piston (27) through the inner hole of the lock sleeve (31) under the pushing action of the pull rod (30) to remove the restraint on the pull rod (30) and realize unlocking;
when the housing (7) drives the pull rod (30) to move from right in the rotation process of the housing (7), the stop block (29) moves to the right along with the pull rod to fix the lock ball (35) in the groove of the second piston (27).
10. The reusable launch vehicle landing buffer of claim 1,
the value range of N is 3-9; the value range of theta is 30-60 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911001691.6A CN110671977A (en) | 2019-10-21 | 2019-10-21 | Reusable carrier rocket landing buffering device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911001691.6A CN110671977A (en) | 2019-10-21 | 2019-10-21 | Reusable carrier rocket landing buffering device |
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| CN110671977A true CN110671977A (en) | 2020-01-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911001691.6A Pending CN110671977A (en) | 2019-10-21 | 2019-10-21 | Reusable carrier rocket landing buffering device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111521074A (en) * | 2020-05-06 | 2020-08-11 | 蓝箭航天空间科技股份有限公司 | Rocket body structure convenient for rocket recovery and liquid rocket |
| CN113295056A (en) * | 2021-04-30 | 2021-08-24 | 北京宇航系统工程研究所 | Large compensation small conduit layout structure |
| CN113804063A (en) * | 2021-08-20 | 2021-12-17 | 北京精密机电控制设备研究所 | Press locking and unlocking device and method for large spring force mortise lock |
| CN114111462A (en) * | 2021-10-29 | 2022-03-01 | 北京宇航系统工程研究所 | High light landing buffer gear of used repeatedly carrier rocket |
| CN115507710A (en) * | 2022-09-27 | 2022-12-23 | 北京星河动力装备科技有限公司 | Rocket landing telescopic arm and rocket recovery device |
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2019
- 2019-10-21 CN CN201911001691.6A patent/CN110671977A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111521074A (en) * | 2020-05-06 | 2020-08-11 | 蓝箭航天空间科技股份有限公司 | Rocket body structure convenient for rocket recovery and liquid rocket |
| CN111521074B (en) * | 2020-05-06 | 2020-11-03 | 蓝箭航天空间科技股份有限公司 | Rocket body structure convenient for rocket recovery and liquid rocket |
| CN113295056A (en) * | 2021-04-30 | 2021-08-24 | 北京宇航系统工程研究所 | Large compensation small conduit layout structure |
| CN113804063A (en) * | 2021-08-20 | 2021-12-17 | 北京精密机电控制设备研究所 | Press locking and unlocking device and method for large spring force mortise lock |
| CN114111462A (en) * | 2021-10-29 | 2022-03-01 | 北京宇航系统工程研究所 | High light landing buffer gear of used repeatedly carrier rocket |
| CN115507710A (en) * | 2022-09-27 | 2022-12-23 | 北京星河动力装备科技有限公司 | Rocket landing telescopic arm and rocket recovery device |
| 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 |
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