CN112249365B

CN112249365B - Reusable spacecraft

Info

Publication number: CN112249365B
Application number: CN202011182179.9A
Authority: CN
Inventors: 杨庆; 黄震; 杨雷; 吴文瑞; 郭斌; 田政; 苏令; 余抗
Original assignee: Beijing Institute of Spacecraft System Engineering
Current assignee: Beijing Institute of Spacecraft System Engineering
Priority date: 2020-10-29
Filing date: 2020-10-29
Publication date: 2022-09-06
Anticipated expiration: 2040-10-29
Also published as: CN112249365A

Abstract

The invention relates to a reusable spacecraft, comprising: the device comprises a return capsule (1) and a propulsion capsule (2) detachably connected with the return capsule (1); the return capsule (1) comprises: the device comprises a main body (11) of the recoverable capsule and a heat insulation structure (12) which is detachably connected with the main body (11) of the recoverable capsule and is used for wrapping the main body (11) of the recoverable capsule. The scheme of the invention realizes the maximization of the reusable efficiency of the spacecraft and effectively reduces the development cost.

Description

Reusable spacecraft

Technical Field

The invention relates to the field of aerospace, in particular to a reusable spacecraft.

Background

With the more frequent and larger space activities, the cost of the spacecraft becomes a very important factor for restricting the space development. For example, in the field of manned space where personnel and goods need to be transported to and from the sky, high space transportation cost has become a major factor restricting large-scale space application. As commercial capital enters the aerospace field, cost-effective low-cost operations have become an inevitable requirement for sustainable health development of aerospace in the future. Reusability is an important way to reduce the cost of spacecraft. By utilizing the reusable technology, cost control can be performed in the aspects of system design, task planning, operation maintenance and the like, so that the project development and operation cost is reduced.

The reusable spacecraft is characterized in that after the spacecraft performs a flight task once and returns to the earth, the whole or part of the spacecraft can be reused after certain detection and maintenance on the ground, and the spacecraft can be reused for the flight task without replacement. And the recoverable capsule lateral wall heat-proof structure of recoverable spacecraft in the past generally uses recoverable capsule metallic structure to carry out shaping, solidification and processing as the basement in the production course of working, and after heat-proof structure accomplished production, can not unpack apart with inside metallic structure, and after the recoverable capsule returned ground, heat-proof structure could not dismantle, and recoverable capsule metallic structure also can not used repeatedly.

Meanwhile, the conventional recoverable spacecraft generally adopts an engine to buffer and land, and the equipment on the capsule can be damaged due to the fact that the capsule is prone to rollover in the landing process.

In addition, in the conventional reentry and return spacecraft, the external heat-proof structure and the internal metal structure of the return capsule are designed integrally, which brings certain limitation to the layout of sensor equipment which needs to be installed on the surface of the capsule body on the return capsule, so that the equipment is generally installed on the propulsion capsule. Since the propulsion capsule is burned down during the reentry of the spacecraft, these devices cannot be brought back to the ground.

Disclosure of Invention

The invention aims to provide a reusable spacecraft, which realizes the reuse of the spacecraft.

To achieve the above object, the present invention provides a reusable spacecraft, comprising: the propelling module is detachably connected with the returning module;

the return capsule includes: the recoverable capsule comprises a recoverable capsule main body and a heat insulation structure, wherein the recoverable capsule main body is detachably connected with the recoverable capsule main body and is used for wrapping the recoverable capsule main body.

According to one aspect of the invention, the heat insulation structure is arranged to match the shape of the external shape of the main body of the return capsule.

According to one aspect of the invention, the insulation structure comprises: a hood, sidewalls and outsole;

the hood and the outsole are respectively arranged at two opposite ends of the side wall;

the side wall is detachably connected to the return capsule main body.

According to one aspect of the invention, the hood is in openable, closable, movable connection with the side wall or in fixedly, detachably connected connection with the side wall;

the outsole is detachably connected with the side wall.

According to one aspect of the invention, the side wall comprises: connecting the support and the insulating wall;

the heat insulating wall is detachably connected to the side wall of the main body of the return capsule via the connecting support.

According to one aspect of the invention, the heat insulation wall is formed by splicing a plurality of splicing assemblies along the side wall of the main body of the return capsule in sequence.

According to an aspect of the invention, the return capsule further comprises: a concave chamber;

the concave cabin is arranged between the main body of the returning capsule and the side wall and is respectively connected with the main body of the returning capsule and the side wall in a sealing way.

According to an aspect of the invention, the return capsule further comprises: a parachute;

the parachute is received in the concave cabin.

According to an aspect of the invention, the return capsule further comprises: the buffering air bag is connected with the returning capsule main body;

the buffer air bag can be folded and compressed to be contained in the outsole.

According to one aspect of the invention, the side wall is also provided with an insulating observation opening, and insulating glass is hermetically arranged on the insulating observation opening;

the heat insulation observation port is arranged on the complete splicing assembly, and the heat insulation glass is connected with the splicing assembly in a sealing mode.

According to the scheme of the invention, through reasonable reusable system design of the return capsule, the situation that as much valuable equipment as possible is arranged on the return capsule is ensured, the equipment arranged on the return capsule can be safely and nondestructively brought back to the ground as possible is realized, the reusable efficiency of the spacecraft is further maximized, and the development cost is effectively reduced.

According to the scheme of the invention, the hood design is adopted, so that the equipment such as the docking mechanism, the rendezvous and docking sensor and the like on the spacecraft, which has the rendezvous and docking task requirement, can be effectively protected, and the reuse efficiency of the equipment is favorably improved.

According to one scheme of the invention, the metal structure of the main body of the spacecraft reentry capsule can be reused by adopting a detachable heat insulation structure design.

According to the scheme of the invention, the airbag landing buffer design is adopted, so that lossless or loss-reducing landing of the returnable capsule can be realized, the damage of equipment on the capsule in the landing process of the returnable capsule is avoided, and a good foundation is created for realizing the reusability of more equipment.

According to one scheme of the invention, the design of the local observation window on the heat insulation structure of the return cabin lays a foundation for realizing that sensor equipment arranged on the surface of the cabin body is arranged on the return cabin so as to realize repeated use.

According to the scheme of the invention, the design of the local sealing concave cabin on the re-entry cabin can avoid the influence of the surrounding environment on equipment on the re-entry cabin in the landing process of the re-entry cabin, thereby laying a foundation for realizing the repeated use of the equipment.

Drawings

FIG. 1 is a block diagram schematically illustrating a reusable spacecraft in accordance with one embodiment of the present invention;

fig. 2 is a structural view schematically showing a return module according to an embodiment of the present invention;

fig. 3 is a block diagram schematically showing a return capsule according to another embodiment of the present invention;

FIG. 4 is a block diagram schematically illustrating a sidewall according to an embodiment of the present invention;

FIG. 5 is a block diagram schematically illustrating a splice assembly according to one embodiment of the present invention;

FIG. 6 is a block diagram schematically illustrating a landing process for a reusable spacecraft in accordance with one embodiment of the present invention;

FIG. 7 is a schematic view showing a structure in which a side wall is provided with an insulating observation port according to an embodiment of the present invention.

Detailed Description

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can also be derived from them without inventive effort.

In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.

The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.

As shown in fig. 1, according to one embodiment of the present invention, a reusable spacecraft of the present invention comprises: a re-entry capsule 1 and a propulsion capsule 2 detachably connected to the re-entry capsule 1. In the embodiment, the returning capsule 1 adopts a blunt body structure, has the capability of returning to the earth again, and is mainly used for providing energy and power required by the on-orbit flight of the spacecraft. In the present embodiment, the return capsule 1 includes: the main body 11 of the reentry module, and the heat insulation structure 12 detachably connected with the main body 11 of the reentry module and used for wrapping the main body 11 of the reentry module. In the present embodiment, the heat insulation structure 12 in the returning capsule 1 is used for realizing high-temperature thermal protection of equipment on the capsule during the process that the returning capsule 1 enters the atmosphere again. In the present embodiment, the heat insulating structure 12 is provided to match the external shape of the capsule main body 11.

Referring to fig. 1 and 2, according to one embodiment of the present invention, the thermal insulation structure 12 includes: head cap 121, side walls 122, and outsole 123. In the present embodiment, the head cap 121 and the outsole 123 are provided at opposite ends of the side wall 122, respectively; the side wall 122 is detachably connected to the return tank main body 11.

Referring to FIGS. 1, 2 and 3, according to one embodiment of the present invention, the hood 121 is removably or fixedly attached to the side wall 122; outsole 123 is removably attached to sidewall 122. In this embodiment, the hood may be designed to be either fixedly mounted removable (as in FIG. 2) or in-orbit retractable (as in FIG. 3) depending on the spacecraft mission requirements. For a spacecraft with meeting and docking task requirements, a meeting and docking mechanism and a meeting and docking related sensor are often required to be installed in a head cover 121 of a return capsule, so that the head cover can be unfolded (as shown in fig. 3) before meeting and docking, the meeting and docking task is completed and the head cover is folded before returning to the earth, and the butt mechanism and the meeting and docking sensor in the head cover can not be burnt during the process that the return capsule enters the atmosphere again. For a spacecraft which does not meet the requirement of a docking task, the hood can be designed to be fixedly installed and detachably connected, the hood is fixed before launching, is always in a fixed state during the orbit period, and is detached after returning to the ground.

In this embodiment, the space formed by the outsole 123 and the interior of the sidewall 122 can be used for installing the related equipment.

As shown in fig. 1, according to an embodiment of the present invention, the sidewall 122 includes: connecting the support and insulating walls 1221. In the present embodiment, the connecting supports are disposed along the side walls of the return tank main body 11, and the insulating wall 1221 is detachably connected to the side walls of the return tank main body 11 by being detachably connected to the connecting supports, thereby realizing the detachable connection of the insulating wall 1221 to the side walls of the return tank main body 11. In the present embodiment, the insulating wall 1221 is formed to conform to the shape of the side wall of the return tank main body 11 after the installation.

As shown in fig. 4 and 5, according to an embodiment of the present invention, the insulating wall 1221 is formed by sequentially splicing a plurality of splice assemblies 1221a along the side wall of the return tank main body 11. In this embodiment, each of the splicing assemblies 1221a is shaped according to the installation position of the splicing assembly 1221, and a connection structure is provided on the splicing assembly 1221a for detachable connection with the connection support. In this embodiment, the connection structure may be a mounting hole, a mounting buckle, a connector fixed with the splice assembly 1221a, or the like. As shown in fig. 5, in the present embodiment, the connection structure on the splice assembly 1221a is configured as a mounting hole, and can be connected with the connection support by screwing. After the return capsule 1 returns to the ground, the external ablated splice assembly 1221a can be removed, providing a basis for the reuse of structures such as the connection supports on the side walls 122.

According to an embodiment of the invention, the return capsule 1 further comprises: a recessed compartment. In the embodiment, the design of environmental protection around the landing process of the re-entry capsule is realized, and in the process that the re-entry capsule 1 returns to the landing, in order to prevent dust, sand, water and the like in the landing area from entering the re-entry capsule 1, the equipment on the re-entry capsule 1 is damaged, so that the equipment is influenced to be reused. Furthermore, a concave cabin is arranged in an area enclosed between the side wall of the return cabin and the side wall 122, and the concave cabin is designed to be sealed with other areas to realize the sealing connection with the main body 11 of the return cabin and the side wall 122 respectively. In this embodiment, the recess is a small space separately partitioned between the main body 11 of the return capsule and the side wall 122 by a structural plate or related material, sealed against the surroundings. When equipment or a mechanism arranged in the concave cabin works, the sealing performance with the surrounding structure cannot be damaged. Further, in the present embodiment, a mechanism product, such as a parachute, a beacon antenna, or the like, which acts during the reentry and return to landing and which deteriorates the integrity and sealing performance of the heat insulating structure 12, is installed in the recessed portion.

In order to ensure that the re-entry capsule is not damaged in the process of returning to landing as far as possible, the re-entry capsule can adopt an air bag buffering landing scheme after being decelerated by the parachute.

As shown in fig. 6, according to an embodiment of the present invention, the return capsule 1 further includes: a parachute 13. In this embodiment, the parachute 13 is housed in the well.

As shown in fig. 6, according to an embodiment of the present invention, the return capsule 1 further includes: and a buffer air bag 14 connected to the return capsule main body 11. In the present embodiment, the cushion airbag 14 is stored in the outsole 123 so as to be foldable and compressible. In this embodiment, the cushion bladder is mounted in the outsole 123 by folding and compressing prior to launch of the spacecraft. And after the returning capsule enters the atmosphere again and is decelerated by the parachute, the outsole 123 is separated, the airbag is inflated and unfolded, and the inflated airbag is used as the returning capsule to realize buffer landing. In order to improve the buffering performance and the side-turn resistance of the airbag to the cabin body in the landing buffering process, the shape of the airbag can be designed, and the airbag is ensured to be well matched with the appearance of the large bottom area of the re-entry cabin after being inflated.

As shown in FIG. 7, an insulating observation port 1222 and an insulating glass 1223 hermetically mounted on the insulating observation port 1222 are further provided on the sidewall 122 according to an embodiment of the present invention. In this embodiment, the insulating observation port 1222 is provided on a complete splice assembly 1221a, and the insulating glass 1223 is hermetically connected to the splice assembly 1221 a. In order to realize the installation layout of the devices such as the sensor on the return cabin, a local opening (an insulated observation port 1222) is further arranged on the splicing component 1221a of the side wall 122, and a special insulated glass 1223 is used to provide a window for the lens of the sensor to observe outwards, so that the optical performance of the insulated glass 1223 is matched with the performance of the lens of the sensor, and the on-track use requirement of the sensor is met.

The foregoing is merely exemplary of particular aspects of the present invention and devices and structures not specifically described herein are understood to be those of ordinary skill in the art and are intended to be implemented in such conventional ways.

The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. 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

1. A reusable spacecraft, comprising: the device comprises a return capsule (1) and a propulsion capsule (2) detachably connected with the return capsule (1);

the return capsule (1) comprises: the device comprises a main returning capsule body (11) and a heat insulation structure (12) which is detachably connected with the main returning capsule body (11) and used for wrapping the main returning capsule body (11);

the heat insulation structure (12) comprises a side wall (122), a head cover (121) and a bottom (123), wherein the side wall (122) is detachably connected with the main body (11) of the return tank;

the return capsule (1) further comprises: a concave cabin;

the concave cabin is arranged between the main body (11) of the returning cabin and the side wall (122) and is respectively connected with the main body (11) of the returning cabin and the side wall (122) in a sealing way, and the concave cabin is used for installing equipment which acts during the process of returning to the landing again and destroys the integrity and the tightness of the heat insulation structure (12);

the return capsule (1) further comprises: a buffer air bag (14) connected with the return capsule main body (11);

the buffer air bag (14) can be folded and compressed to be contained in the outsole (123);

the side wall (122) is also provided with an insulating observation opening (1222), and insulating glass (1223) hermetically mounted on the insulating observation opening (1222);

the side wall (122) includes: connecting the support and insulation walls (1221); the heat insulation wall (1221) is formed by sequentially splicing a plurality of splicing assemblies (1221 a) along the side wall of the main body (11) of the return capsule;

the heat insulation observation opening (1222) is arranged on the complete splicing assembly (1221 a), and the heat insulation glass (1223) is connected with the splicing assembly (1221 a) in a sealing mode.

2. A reusable spacecraft as claimed in claim 1, wherein the insulation structure (12) is arranged to match the shape of the reentry module body (11).

3. A reusable spacecraft as claimed in claim 2, wherein said hood (121) and said sole (123) are disposed respectively at opposite ends of said side wall (122).

4. A reusable spacecraft as claimed in claim 3, wherein the hood (121) is releasably or fixedly mounted to the side wall (122);

the outsole (123) is detachably connected with the side wall (122).

5. A reusable spacecraft according to claim 3 or 4,

the heat insulating wall (1221) is detachably connected to the side wall of the main return tank body (11) via the connecting support.

6. A reusable spacecraft as claimed in claim 5, wherein the return capsule (1) further comprises: a parachute (13);

the parachute (13) is accommodated in the concave chamber.