CN112357118A - Manned lunar surface lander based on truss structure - Google Patents
Manned lunar surface lander based on truss structure Download PDFInfo
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- CN112357118A CN112357118A CN202011173132.6A CN202011173132A CN112357118A CN 112357118 A CN112357118 A CN 112357118A CN 202011173132 A CN202011173132 A CN 202011173132A CN 112357118 A CN112357118 A CN 112357118A
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64G1/00—Cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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Abstract
The invention discloses a manned lunar surface lander based on a truss structure, which relates to the technical field of spacecrafts, can realize test launching and orbital transfer and comprises the following components: the connection and separation mechanism can realize the connection of the upper upgrading stage and the lower upgrading stage in the descending stage and the separation of the upper upgrading stage before ascending and the lower upgrading stage; the descending stage adopts a truss structure, can support and upgrade, serves as a landing leg, and can serve as an instrument cabin; the upgrade can be manned.
Description
Technical Field
The invention relates to the technical field of spacecrafts, in particular to a manned lunar surface lander based on a truss structure.
Background
The manned lunar landing is a technical fusion and innovative development of a lunar exploration project and a manned aerospace project, is also a first step to be taken out in future manned deep space exploration in China, and is a key aircraft for finishing manned lunar exploration in order to realize manned lunar landing. Compared with an unmanned lunar surface lander, the manned lunar surface lander needs to meet the living and working requirements of spacemen in the stages of lunar surface landing, rising and the like, the safety of the spacemen is ensured, necessary loads and equipment related to detection are installed, and the difficulty of the manned lunar surface lander is greatly improved compared with that of an unmanned lunar surface detection project.
At present, lunar landers which successfully realize manned lunar landing tasks at home and abroad only adopt American moon landing landers in Apollo project, and launch by adopting a carrier rocket in Saturn-five, so that the carrying capacity at home and abroad still far cannot reach the capacity in the Saturn-five. With the continuous development and the increase of the demand of the aerospace technology in China, based on the actual requirement and capacity of people carrying on the moon in China, a lunar lander with large bearing capacity and light weight is needed to be designed to adapt to the requirement and capacity of people carrying on the aerospace in China.
Disclosure of Invention
In view of the above, the invention provides a manned lunar surface lander based on a truss structure, which can meet the requirement that astronauts land and leave the lunar surface, and provide a space for the astronauts to live and work; in turn, can provide mounting space for including tank structures, landing gear, engines, and other load devices.
The technical scheme of the invention is as follows: a manned lunar surface lander based on a truss structure, the lander can realize experimental launch and orbit transfer, and the lander comprises: the connection and separation mechanism can realize the connection of the upper upgrading stage and the lower upgrading stage in the descending stage and the separation of the upper upgrading stage before ascending and the lower upgrading stage; the descending stage adopts a truss structure, can support and upgrade, serves as a landing leg, and can serve as an instrument cabin; the upgrade can be manned.
Preferably, the rising stage includes: the engine comprises a sealed cabin, a butt joint mechanism and an engine bracket;
the sealed cabin is a cylindrical cabin body, the top of the sealed cabin is provided with a docking mechanism and a docking cabin door, and a spacecraft is in the sealed cabin in the lunar descent stage and the lunar ascent stage and can enter an external spacecraft from the docking cabin door and the docking mechanism; the outer circumferential surface of the sealed cabin is uniformly connected with an even number of ascending engines through engine supports and is used for providing power for ascending.
Preferably, four ascending engines are uniformly arranged on the outer circumferential surface of the sealed cabin, four installation areas are formed among the four ascending engines, a group of storage tanks I are respectively arranged in the two opposite installation areas, and each group of storage tanks I comprises two symmetrically arranged storage tanks I; more than one exit cabin door is arranged in the other two opposite installation areas and is used for sealing the astronauts in the cabin to exit the cabin.
Preferably, the sealed cabin adopts a wall plate type structure or a combination structure of a stringer and a skin or a metal welding structure or a structure formed by composite materials.
Preferably, the down stage comprises: a main truss, an adapter and a landing engine;
the main truss is a regular polygon prism-shaped frame structure which is formed by connecting an even number of landing buffer mechanism installation modules and is provided with supporting legs, the adapter and the connection and separation mechanism are arranged at the top end of the main truss, an even number of node balls are arranged at the bottom end of the main truss and are used as installation interfaces of the storage box II and can be connected with the carrying butt joint frame, and a landing engine is arranged in the center of the bottom end and is used for providing power for descending landing; the storage boxes II are arranged in the main truss, each landing buffer mechanism installation module comprises more than two storage box installation modules which are connected into a whole through a node ball and a landing buffer mechanism which is used as a supporting leg, and the landing buffer mechanism transmits landing load to the main truss through the node ball.
Preferably, each storage tank installation module is a symmetrical structure which is formed by connecting a longitudinal rod system, a transverse rod system, a short beam and a node ball and has two installation spaces, so that an even number of installation spaces can be provided inside the main truss and are used for installing the storage tank II or the functional cabin.
Preferably, the longitudinal bar system and the transverse bar system both adopt a spindle-shaped structure.
Preferably, the spindle-shaped structure comprises: the spindle-shaped rod body and connecting threads arranged at two ends of the spindle-shaped rod body; the spindle-shaped rod body is thick in the middle and thin at two ends and is made of carbon fiber composite materials; and the connecting threads at the two ends are used for being connected with the node ball.
Preferably, the adapter is of a truss structure, the lower end of the adapter is connected to the node ball of the main truss, the upper end of the adapter is provided with the ascending stage butt-joint frame, and the ascending stage butt-joint frame and the descending main truss are connected together through a cross rod system arranged in a crossed mode.
Preferably, by adjusting the length or angle or both length and angle of the cross-bar system, it is possible to accommodate different upgraded loads and interface requirements.
Has the advantages that:
1. the manned lunar surface lander adopts a two-cabin type structure up-down layout, separates the functions of the ascending part and the descending part, is respectively realized by the ascending stage and the descending stage, and can be separated during ascending, thereby better ensuring the realization of the two functions of the ascending part and the descending part and reducing the takeoff weight during ascending; meanwhile, the landing gear can be separated to realize different upgrading selections, and further can realize the matching of different tasks of the landing gear, so that the whole landing gear is multipurpose, for example, the moon landing of large-scale goods can be realized by replacing an ascending grade with a freight module.
2. The ascending stage sealed cabin is arranged above, the view field of the astronaut in the landing and ascending stages is good, the pollution of lunar dust in the landing and ascending stages can be better avoided, and the good working environment of equipment and the sealing performance of the cabin body are ensured; the storage box I and the lifting engine are hung outside the sealed cabin, and the storage box I and the lifting engine are uniformly and symmetrically arranged, so that stable flight in the landing and lifting stages can be ensured, and the control is convenient; through the combined design of the sealed cabin and the external hanging equipment, the requirements of various load layouts and carrying equipment in the ascending stage of astronauts and cabin sections can be met, and the lightweight structure is realized.
3. The cabin door design for sealing the top end and the side surface of the cabin can ensure that astronauts can smoothly enter and exit the spacecraft.
4. The descending stage adopts a symmetrical truss structure, can realize the characteristics of large bearing capacity (the launching weight can reach 35 t-40 t), light structure weight and the requirement of installation of various platform equipment such as a storage box II and the like, and the main truss, the storage box II, a landing engine, a landing buffer mechanism and the like realize the reasonable layout of the descending stage in the integral structure of the lander through an integrated configuration design, can be reliably connected with a carrying stage and an ascending stage, and is favorable for realizing the light weight of the structure; meanwhile, the main truss can adapt to different installation loads, such as an air lock cabin for cabin exit and the like can be replaced in the installation area of the storage box II.
5. The descending main truss adopts a symmetrical modular configuration, so that the types of parts can be greatly reduced, and the production cost and the production period are reduced; meanwhile, the verification of the whole truss structure can be realized through the verification of a single module, and the test verification difficulty and the verification period are greatly reduced.
6. The specific arrangement of the storage tank installation module has strong structural expansion and load-adapting capability, the number of truss rods (longitudinal rod systems, transverse rod systems and short beams) among the node balls can be increased or reduced, and the bearing capacity of the whole lander can be adjusted by adjusting the section size and the material of the truss rods so as to adapt to different load requirements.
7. The longitudinal rod system and the transverse rod system are arranged specifically, so that the bearing capacity is strong, the bearing efficiency is high, and the structure is light in weight.
8. The landing device adopts the spindle-shaped rod and the bolt node ball, the spindle-shaped rod body is thick in the middle and thin at two ends, the structure is light in weight and high in rigidity; the node ball is in a spherical shape, and is provided with a plurality of threaded holes as required to provide a spindle-shaped rod connection interface; the lattice structure is filled in the node ball, the skin is arranged outside the node ball, the threaded connection part is reinforced, the spindle-shaped rod and the bolt node ball are adopted, the structure is few in types, light in weight and high in rigidity, and high efficiency and light weight of the structure can be realized.
9. The adapter adopts a truss structure, is simple to process and assemble, has high structural bearing efficiency and has strong adaptability.
10. According to the invention, by adjusting the length, the angle, the number, the section parameters and the like of the crossed rod system, different bearing capacities can be adjusted, and different installation interface requirements can be met.
Drawings
FIG. 1 is a front view of the overall structure of the manned lunar surface lander of the present invention.
FIG. 2 is a top view of the entire structure of the landing gear for manned moon surface.
Fig. 3 is a schematic structural diagram of an ascending stage according to the present invention, (1) a perspective view, and (2) a top view.
FIG. 4 is a schematic diagram of the downgrade structure in the present invention.
Fig. 5 is a schematic structural view of a main truss structure according to the present invention.
FIG. 6 shows the general modules of the present invention for downgrading, (1) the tank mount module, and (2) the landing gear mount module.
Fig. 7 is a schematic structural diagram of an adapter in the present invention.
Fig. 8 is a schematic structural view of the main bearing rod system in the invention.
Wherein, 1-up upgrade, 2-down downgrade, 3-sealed cabin, 4-docking mechanism, 5-docking cabin door, 6-ascending engine, 7-engine bracket, 8-tank I, 9-out cabin door, 10-main truss, 11-adapter, 12-tank II, 13-landing engine, 14-landing buffer mechanism, 15-node ball, 16-longitudinal rod system, 17-transverse rod system, 18-short beam, 19-carrying docking frame, 20-ascending docking frame, 21-cross rod system, 22-spindle rod body, and 23-connecting screw thread.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides a manned lunar surface lander based on a truss structure, which can meet the requirement that astronauts land and leave the moon surface, and provides a space for the astronauts to live and work; in turn, can provide mounting space for including tank structures, landing gear, engines, and other load devices.
As shown in fig. 1 and 2, the manned lunar surface lander includes: an up-stage 1 and a down-stage 2; as shown in fig. 3, the upgrade 1 includes: the sealing cabin 3, the butt joint mechanism 4 and the engine bracket 7; as shown in fig. 4, downgrading 2 includes: a main truss 10 and a landing engine 13; as shown in fig. 5, the main girder 10 includes: node ball 15, longitudinal bar system 16, transverse bar system 17, short beam 18 and carrying butt frame 19.
The connection relationship of the manned lunar surface lander is as follows: the lander can realize test launching and orbit transfer, the ascending stage 1 and the descending stage 2 are arranged up and down and are connected or separated through the connection and separation mechanism, and the connection and separation mechanism can realize connection of the ascending stage 1 and the descending stage 2 in a descending stage and separation of the ascending stage 1 and the descending stage 2 before ascending; the sealed cabin 3 is a cylindrical cabin body as a main body of the upper upgrade 1, the top of the sealed cabin is provided with a docking mechanism 4 and a docking cabin door 5, and astronauts are both in the sealed cabin 3 in the lunar descent stage and the lunar ascent stage (the cabin can provide a sealed space for the astronauts to work and live), and can enter external astronauts from the docking cabin door 5 and the docking mechanism 4; an even number of ascending engines 6 (four ascending engines 6 are arranged in the embodiment) are uniformly connected to the outer circumferential surface of the sealed cabin 3 through engine supports 7 and used for providing power for ascending of the upper stage 1, four installation areas are formed among the four ascending engines 6, a group of storage tanks I8 are respectively arranged in two opposite installation areas, each group of storage tanks I8 comprises two symmetrically arranged storage tanks I8, and the storage tanks I8 are uniformly and symmetrically arranged and are favorable for reducing concentrated loads; more than one cabin exit door 9 is arranged between the two groups of ascending engines 6, and the astronauts in the sealed cabin 3 can exit and land on the lunar surface through the cabin exit doors 9;
the main truss 10 is used as a main structure of the downgrade 2 and is a regular polygon prism-shaped frame structure (a regular octagonal prism-shaped frame structure is preferred in the embodiment) with supporting legs, which is formed by connecting an even number of landing buffer mechanism installation modules, so that the bearing capacity of the structure is greatly improved, and the verification of the whole downgrade 2 can be realized by verifying a single landing buffer mechanism installation module; as shown in fig. 6, each landing buffer mechanism installation module includes more than two tank installation modules connected into a whole through a node ball 15 and a landing buffer mechanism 14 serving as a support leg, and the landing buffer mechanism 14 transmits landing load to the main truss 10 through the node ball 15, so that the whole manned lunar surface lander and the stable landing lunar surface of the astronaut can be ensured; each storage box installation module is a symmetrical structure which is formed by connecting a plurality of longitudinal rod systems 16, transverse rod systems 17, short beams 18 and node balls 15 and has two installation spaces, so that an even number of installation spaces (preferably eight installation spaces in the embodiment) can be provided inside the whole main truss 10 and are used for installing storage boxes II 12 or other functional cabin sections (such as air lock cabins, platform cabins and the like), wherein the arrangement of the longitudinal rod systems 16 and the transverse rod systems 17 can obviously reduce the structural weight and improve the structural bearing efficiency; the top end of the main truss 10 is provided with an adapter 11 which is used as an interface; an even number of node balls 15 (preferably eight node balls 15 in this embodiment) are arranged at the bottom of the main truss 10, an installation interface of the storage tank ii 12 is provided, and the storage tank ii 12 can be stably connected with the carrying butt-joint frame 19, the load of the storage tank ii 12 is transmitted to the carrying butt-joint frame 19 through the main truss 10, and the connection and separation of the carrying and descending stages 2 can be realized through the carrying butt-joint frame 19; a landing engine 13 (one engine with larger thrust or four engines with smaller thrust can be installed) is installed at the bottom center of the main truss 10 and used for providing power for landing of the descending stage 2;
the working principle of the manned lunar surface lander is as follows: the upper upgrade stage 1 and the lower stage 2 are separated, and the astronaut takes the upper stage 1 to leave the moon surface independently; when the manned lunar surface lander descends on the lunar surface, the descending stage 2 provides an engine and fuel required by descent, and provides buffer during landing so as to ensure that astronauts can safely and stably fall into the moon.
Further, the sealed cabin 3 is in the form of a wall plate structure or a combination structure of a stringer and a skin, or a metal welding structure or other structures formed by composite materials.
Further, a restraining component is arranged at the upper end of the main truss 10 and used for transversely restraining the storage tank II 12, and the restraining component is formed by connecting an even number of groups of short beams 18 and node balls 15.
Further, as shown in fig. 7, the adapter 11 is a truss structure, the lower end of which is connected to the node ball 15 of the main truss 10 of the lower stage 2, and the upper end of which is an ascending stage docking frame 20, and the ascending stage docking frame 20 and the main truss 10 of the lower stage 2 are connected together by a cross bar system 21 arranged crosswise.
Further, by adjusting the length and/or angle of the cross-bar system 21, the load and interface requirements of different upgrades 1 can be accommodated.
Further, in order to reduce the installation space, reduce the weight and improve the bearing capacity, the longitudinal bar system 16 and the transverse bar system 17 in the main truss 10 both adopt a spindle-shaped structure, as shown in fig. 8, the spindle-shaped structure includes: a spindle-shaped rod body 22 and connecting threads 23 arranged at both ends thereof; wherein, the spindle-shaped rod body 22 has a thick middle part and thin two ends and is made of carbon fiber composite material; both ends connecting screw 23 is used for connection with node ball 15.
Furthermore, the arrangement, the number and the like of the longitudinal rod systems 16 and the transverse rod systems 17 in the main truss 10 can be adjusted to meet the load requirements of different weights, and the adaptability is strong.
Further, the node ball 15 is spherical in overall configuration, and three or more threaded holes are formed in the outer surface of the node ball as required to provide connection interfaces of the longitudinal rod system 16, the transverse rod system 17 and the short beam 18; the node ball 15 is filled with a lattice structure (light weight, high strength and high rigidity can be achieved), the outer portion of the node ball is covered with skin, and the position of the threaded hole is reinforced.
Further, the node ball 15 is produced by a combination of additive manufacturing and machining.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides a manned lunar surface lander based on truss structure, its characterized in that, experimental transmission and orbital transfer can be realized to the lander, and it includes: the system comprises an upper upgrade (1) and a lower upgrade (2), which are connected or separated through a connection and separation mechanism, wherein the connection and separation mechanism can realize the connection of the upper upgrade (1) and the lower upgrade (2) in a descending stage and the separation of the upper upgrade (1) and the lower upgrade (2) before ascending; the descending stage (2) adopts a truss structure, can support the upper upgrade (1), serves as a landing leg, and can serve as an instrument cabin; the upgrade (1) can be manned.
2. The truss structure-based manned lunar lander as claimed in claim 1, wherein the up-staging (1) comprises: the engine comprises a sealed cabin (3), a butt joint mechanism (4) and an engine bracket (7);
the sealed cabin (3) is a cylindrical cabin body, the top of the sealed cabin is provided with a docking mechanism (4) and a docking cabin door (5), and astronauts are in the sealed cabin (3) in the lunar descent stage and the lunar ascent stage and can enter external spacecrafts from the docking cabin door (5) and the docking mechanism (4); the outer circumferential surface of the sealed cabin (3) is uniformly connected with an even number of ascending engines (6) through engine supports (7) and used for providing power for ascending of the upper upgrading stage (1).
3. The truss structure-based manned lunar surface lander according to claim 2, wherein four ascending engines (6) are uniformly arranged on the outer circumferential surface of the sealed cabin (3), four installation areas are formed among the four ascending engines (6), two opposite installation areas are respectively provided with a group of storage tanks I (8), and each group of storage tanks I (8) comprises two symmetrically arranged storage tanks I (8); more than one exit door (9) is arranged in the other two opposite installation areas and is used for sealing the astronauts in the cabin (3) to exit.
4. The people mover based on truss structure as claimed in claim 2, wherein the capsule (3) is a structure formed by a wall plate structure or a combination of stringer and skin structure or a metal welded structure or a composite material.
5. The truss structure-based manned lunar lander as defined in claim 1 wherein the downgrade (2) comprises: a main truss (10), an adapter (11) and a landing engine (13);
the main truss (10) is a regular polygon prism-shaped frame structure which is formed by connecting an even number of landing buffer mechanism installation modules and is provided with supporting legs, an adapter (11) and the connection and separation mechanism are arranged at the top end of the main truss (10), the bottom end of the main truss (10) is provided with an even number of node balls (15) which are used as an installation interface of a storage box II (12) and can be connected with a carrying butt joint frame (19), and the center of the bottom end is provided with a landing engine (13) which is used for providing power for landing of the descending stage (2); the storage tanks II (12) are arranged inside the main truss (10), each landing buffer mechanism mounting module comprises more than two storage tank mounting modules which are connected into a whole through a node ball (15) and a landing buffer mechanism (14) serving as a supporting leg, and the landing buffer mechanism (14) transmits landing load to the main truss (10) through the node ball (15).
6. The truss structure-based manned lunar lander according to claim 5, wherein each of the tank installation modules is a symmetrical structure with two installation spaces formed by connecting longitudinal rod systems (16), transverse rod systems (17), short beams (18) and node balls (15), so that an even number of installation spaces can be provided inside the main truss (10) for installing tank II (12) or functional bay sections.
7. The truss structure-based manned lunar lander according to claim 6, wherein the longitudinal bar system (16) and the transverse bar system (17) are each in a spindle-shaped structure.
8. The truss structure-based manned lunar lander as defined in claim 7 wherein said fusiform structure comprises: a spindle-shaped rod body (22) and connecting threads (23) arranged at two ends of the spindle-shaped rod body; wherein the spindle-shaped rod body (22) is thick in the middle and thin at two ends and is made of carbon fiber composite material; the two ends of the connecting screw thread (23) are used for connecting with the node ball (15).
9. The truss structure-based manned lunar lander according to claim 5, wherein the adapter (11) is a truss structure, the lower end is connected to the node ball (15) of the main truss (10), the upper end is an ascending docking frame (20), and the ascending docking frame (20) is connected with the main truss (10) of the descending stage (2) through a crossed rod system (21).
10. The truss structure-based manned lunar landing gear according to claim 9, wherein the load and interface requirements of different upgrades (1) can be accommodated by adjusting the length or angle or both length and angle of the cross-bar system (21).
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113104236A (en) * | 2021-02-26 | 2021-07-13 | 北京空间飞行器总体设计部 | Lunar probe suitable for lunar surface automatic sampling return |
| CN114802815A (en) * | 2022-05-13 | 2022-07-29 | 南京航空航天大学 | On-orbit assembly-oriented shearing and hinging type universal module based on butt joint of water chestnut locks |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107585330A (en) * | 2016-07-06 | 2018-01-16 | 北京空间技术研制试验中心 | Multi-functional manned lunar surface's lander based on modularized design |
| CN108674693A (en) * | 2018-03-29 | 2018-10-19 | 北京空间技术研制试验中心 | Manned lunar surface's landing gear |
| CN110963079A (en) * | 2019-12-18 | 2020-04-07 | 南京航空航天大学 | Overhead crane type manned lunar landing aircraft, lunar landing method and application thereof |
-
2020
- 2020-10-28 CN CN202011173132.6A patent/CN112357118B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107585330A (en) * | 2016-07-06 | 2018-01-16 | 北京空间技术研制试验中心 | Multi-functional manned lunar surface's lander based on modularized design |
| CN108674693A (en) * | 2018-03-29 | 2018-10-19 | 北京空间技术研制试验中心 | Manned lunar surface's landing gear |
| CN110963079A (en) * | 2019-12-18 | 2020-04-07 | 南京航空航天大学 | Overhead crane type manned lunar landing aircraft, lunar landing method and application thereof |
Non-Patent Citations (1)
| Title |
|---|
| 白雪等: "集群化多功能载人月面着陆 /上升器概念设计", 《载人航天》 * |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113104236A (en) * | 2021-02-26 | 2021-07-13 | 北京空间飞行器总体设计部 | Lunar probe suitable for lunar surface automatic sampling return |
| CN114802815A (en) * | 2022-05-13 | 2022-07-29 | 南京航空航天大学 | On-orbit assembly-oriented shearing and hinging type universal module based on butt joint of water chestnut locks |
| CN114802815B (en) * | 2022-05-13 | 2024-05-24 | 南京航空航天大学 | Shear hinge type universal module based on water chestnut lock butt joint and oriented to on-orbit assembly |
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| CN112357118B (en) | 2022-04-05 |
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