Manned spaceflight emergency escape device with entrance close to cabin and directly reaching ground

Abstract

The invention relates to the technical field of manned spaceflight launching facilities, in particular to a manned spaceflight emergency escape device with an entrance close to a cabin and directly reaching the ground. The technical problems that in the prior art, an astronaut wears a space suit and other complex equipment, and long escape time is consumed in the escape process are solved, and an emergency escape device connecting part is connected to the side close to a rocket and arranged adjacent to the rocket; the emergency escape device connecting part at least comprises an emergency escape device entrance; the main body section used for escaping is in a channel shape, and an internal path is formed; one end of the main body section is connected with an emergency escape device entrance, and the other end is connected with a main body section end point; the main body section is hung on the service tower and is arranged in a winding manner from the near arrow side to the far arrow side; the system further comprises a plurality of signal collectors arranged at the main body section and the entrance of the emergency escape device and used for sensing information such as positions of carrying personnel in real time. The system has the advantages that the escape entrance is close, the carrying is convenient, and the system bypasses the outer side of the service tower and directly reaches the ground.

Description

Technical Field

[0001] The invention relates to the technical field of manned space launch facilities, and in particular to a manned space emergency escape device with a near-cabin entrance directly reaching the ground. Background Art

[0002] During the emergency escape process of manned space activities, astronauts and related personnel quickly reach the ground through devices located inside or connected to the service tower and are further transferred to the shelter by vehicles and other tools to avoid being injured by the explosion. The primary indicator of emergency escape is the speed at which the escapees can evacuate the service tower and reach the shelter facility while ensuring their survival. The way of evacuating the service tower greatly affects the efficiency of escape.

[0003] At present, the main means of evacuating the service tower include taking elevators, slides, zip lines, etc. The entrances to the slides and zip lines are generally located at the far end of the service tower away from the rocket on the level where the rocket's manned cabin is located, and the elevator is located inside the service tower. This type of design can quickly send the escapees to the ground after the escapees enter the entrance of the escape device or carry the corresponding escape tools. However, escapees, especially astronauts, will wear complex equipment such as space suits. After leaving the cabin, they need to rely on their own physical strength to pass through the service tower to board the evacuation device, which will consume a long escape time and increase the threat to survival. Summary of the invention

[0004] The present invention aims to solve the technical problem in the prior art that astronauts have to wear complex equipment such as space suits, which consumes a long time in the escape process, and provides a manned space emergency escape device with a near-cabin entrance directly reaching the ground.

[0005] In order to solve the above technical problems, the technical solutions of the present invention are as follows:

[0006] A manned space emergency escape device with a near-cabin entrance directly reaching the ground, applied to a service tower, wherein the service tower has a near-arrow side and a far-arrow side;

[0007] The emergency escape device connection part is connected to the near-rocket side and arranged adjacent to the rocket;

[0008] Wherein, the emergency escape device connection portion includes at least one emergency escape device entrance; and

[0009] The main body section used for escape is constructed in a channel shape and forms an internal path;

[0010] One end of the main body section is connected to the entrance of the emergency escape device, and the other end is used to connect to the end point of the main body section;

[0011] The end point of the main body section is connected to a terminal position on the ground at the distal arrow side;

[0012] The terminal location is the ground surface or underground or a passage in a bunker;

[0013] The main body section is hung on the service tower and arranged in a winding manner from the near-arrow side to the far-arrow side;

[0014] It also includes: a plurality of signal collectors arranged at the main body section and the entrance of the emergency escape device for real-time sensing of information such as the position of the passengers.

[0015] Furthermore, the main body section is adopted to bypass the service tower body and forms a fixed installation connection at the junction of the facade of the service tower body;

[0016] The fixed installation connection uses a reinforcement piece to support the bend of the main body section during the winding process as a reinforcement measure.

[0017] Furthermore, a stop device is arranged at each end of the main body segment near the main body segment;

[0018] The stopping device is: one or both of a blocking net and a buffer pad.

[0019] Furthermore, the main body section can be configured as one of a closed slide, a semi-closed slide or a cableway with guiding capability.

[0020] Furthermore, the emergency escape device connection portion is connected to a revolving corridor of a service tower or a revolving platform of a service tower.

[0021] Furthermore, the entrance of the emergency escape device is configured to be within a close range of the exit of the manned cabin.

[0022] Furthermore, the inner path can be configured with a flexible deceleration material layer or a rigid deceleration structure.

[0023] Furthermore, the main body section can operate synchronously with the closing or opening action of the rotary mechanism.

[0024] The present invention has the following beneficial effects:

[0025] The present invention ensures the rapidity of emergency escape of escapees, and designs the overall configuration mainly taking the escape efficiency of escapees with the worst mobility, namely astronauts wearing space suits, into consideration. The invention has the characteristics of being close to the entrance of the escape device, convenient boarding, and directly reaching the ground by circling the outside of the service tower. After leaving the manned cabin, the astronauts can reach the entrance in a short time and easily board the emergency escape device, thus saving the time of moving from the manned cabin to the remote entrance of the emergency escape device, and further shortening the time required to reach the ground. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0027] Figure 1 It is a general schematic diagram of the present invention;

[0028] Figure 2 It is a front schematic diagram of the present invention;

[0029] Figure 3 It is the schematic diagram behind the present invention;

[0030] Figure 4 It is a side schematic diagram of the present invention.

[0031] The reference numerals in the figures indicate:

[0032] 10. Service tower, 101. Near arrow side, 102. Far arrow side;

[0033] 20. Emergency escape device connection, 1. Rocket, 201. Emergency escape device entrance;

[0034] 30. Main body paragraph;

[0035] 210. At the end of the main section;

[0036] 2. Ground, 3. Terminal location, 40. Signal collector;

[0037] 31. Reinforcement. DETAILED DESCRIPTION

[0038] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0039] The present invention proposes a near-cabin type direct-to-ground emergency escape device. In order to ensure the rapidity of the emergency escape of the escapee, the overall configuration design is mainly considered with the escape efficiency of the escapee with the worst mobility, that is, the astronaut wearing a space suit. The main structure includes:

[0040] The two parts of the emergency escape device connection part 20 and the main body section 30 are a configuration that is hung on the outside of the service tower 10, and have the characteristics of being close to the entrance of the escape device, convenient to board, and bypassing the outside of the service tower to directly reach the terminal position 3 on the ground;

[0041] The entrance 201 of the emergency escape device can be arranged in a close range of the manned cabin exit by means of an opening, such as the side of a nearby rotating corridor, rotating platform, etc.;

[0042] After leaving the manned cabin, the astronauts can reach the entrance in a short time and easily board the emergency escape device connection part 20, saving the time of moving from the manned cabin to the remote emergency escape device entrance, further shortening the time required to reach the ground.

[0043] The main section 30 is configured to bypass the outside of the service tower 10, and a reinforcement member 31 is installed at the junction with the outer facade of the service tower 10, and a reinforcement measure of a fake reinforcement member 31 can be taken at the overloaded corner;

[0044] After entering or riding the emergency escape device connection part 20, the escapee can directly reach a safer place on the far arrow side 102 of the back of the service tower 10 to carry out further transfer;

[0045] The main body section 30 of the present invention may be provided in a manner including but not limited to a closed or semi-closed slideway or a cableway with a guiding capability;

[0046] The internal path may be provided with deceleration means including but not limited to deceleration materials, deceleration mechanisms and the like, and may use a rigid or flexible enveloping method.

[0047] The main body section 30 can be operated synchronously with the closing or opening action of the rotary mechanism, and can adopt a structural composition method including but not limited to a segmented type according to the movement path of the rotary mechanism, or a flexible material can be used at a corresponding position corresponding to the movement of the rotary mechanism to ensure that the escape path is unobstructed when the rotary mechanism is closed, and can be disconnected or folded at a corresponding position when opening, without limiting or interfering with the operation of the rotary mechanism and the drift range of the rocket launch;

[0048] A signal collection device may be provided inside the entrance 20 and the main body section 30 of the emergency escape device, configured as a signal collector 40, to sense information such as the position of the passengers in real time.

[0049] The end point 210 of the main section is located on the ground surface or underground of the ground 2 outside the service tower 10 away from the rocket 1 side, or is connected to a passage leading directly to the shelter. After landing, the escaped personnel can directly transfer to the shelter quickly by taking a car or the like.

[0050] At the end point 210 of the main section, a stopping device including but not limited to a blocking net, a buffer pad, a spring, etc. may be provided, and a deceleration means including but not limited to a deceleration material, a deceleration mechanism, etc. may also be provided;

[0051] In addition, a mechanism capable of receiving landed personnel can be set up at terminal position 3 to further achieve seamless connection between the landing of escaped personnel and their transfer to the shelter;

[0052] The scope of the present invention is limited to the overall configuration design of the emergency escape device that is externally mounted on the service tower and directly reaches the ground, and the launch platform, rotating platform, swing arm and other devices with low relevance are omitted in each figure. The rotating mechanism refers to the schematic rectangular structure between the rocket and the service tower corresponding to 20 in the figure, which can generally be the rotating platform of the service tower that wraps the rocket, or the rotating corridor for astronauts to enter the rocket from the service tower.

[0053] Before the rocket is launched, this type of mechanism rotates outwards around the connection with the service tower, away from the rocket.

[0054] The present invention is not limited to the design and installation of a single escape device. In specific circumstances, multiple paths and path conversion mechanisms can be arranged in parallel or in a branching manner as needed for simultaneous use by multiple people.

[0055] The present invention does not limit the specific materials, rigid or flexible forms, interface methods, connection forms, control methods and means, endpoint buffering methods and means, etc. used in the emergency escape device.

[0056] After receiving the emergency escape command, the astronaut leaves the manned cabin and moves to the emergency escape device entrance 201 of the emergency escape device connection part of the present invention, enters the main section 30, quickly detours and slides down along its path to the end point, and makes further transfer.

[0057] Through the above description of configuration and application, technical and engineering personnel in this field can clearly understand the configuration of the near-cabin direct-to-ground emergency escape device described in the present invention, so as to carry out specific design and construction work. Based on such understanding, the content of the present invention can provide a faster means for emergency escape during the waiting phase of manned space activities, so that the escaped personnel can reach the ground as soon as possible for further transfer.

[0058] The present invention discloses a near-cabin direct-to-ground emergency escape device configuration, which does not specifically limit the design tools and system software and hardware selection used in the specific design, construction and application processes, and has certain universality and adaptability.

[0059] The design configuration described above further elaborates on the purpose, scheme and beneficial effects of the present invention. It is only a configuration scheme of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

[0060] Finally, it should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, for those skilled in the art, once the basic creative concept of the present invention is known, several improvements and modifications can be made without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A manned space emergency escape device with an entrance near the cabin directly reaching the ground, applied to a service tower (10), characterized in that: The service tower (10) has a near-arrow side (101) and a far-arrow side (102); The emergency escape device connection part (20) is connected to the near-arrow side (101) and is arranged adjacent to the rocket (1); The emergency escape device connection part (20) is arranged on a rotary mechanism of an astronaut corridor connecting a service tower and the rocket (1), and comprises at least one emergency escape device entrance (201); and A main body section (30) for escape, which is channel-shaped and forms an internal path; One end of the main body section (30) is connected to the entrance (201) of the emergency escape device, and the other end is used to connect to the end point (210) of the main body section; The end point (210) of the main body section is connected to a terminal position (3) on the ground (2) on the distal arrow side (102); The terminal location (3) is the surface of the ground (2) or underground or a passage in a bunker; The main body section (30) is hung on the service tower (10) and is arranged in a winding manner from the near-arrow side (101) to the far-arrow side (102); It also includes: a plurality of signal collectors (40) arranged at the main body section (30) and the entrance (201) of the emergency escape device for real-time sensing of information such as the position of the passengers.

2. The manned space emergency escape device with a near-cabin entrance and direct access to the ground according to claim 1 is characterized in that: The main body section (30) adopts a bypass service tower body (10) and forms a fixed installation connection at the joint of the outer facade of the service tower body (10); The fixed installation connection uses a reinforcement piece (31) to support the bending part of the main body section (30) during the winding process.

3. The manned space emergency escape device with a near-cabin entrance and direct access to the ground according to claim 1 is characterized in that: A stop device is arranged near the end point (210) of the main body section (30); The stopping device is: one or both of a blocking net and a buffer pad.

4. The manned space emergency escape device with a near-cabin entrance and direct access to the ground according to claim 1 is characterized in that: The main body section (30) can be configured as one of a closed slide, a semi-closed slide or a cableway with guiding capability.

5. The manned space emergency escape device with a near-cabin entrance and direct access to the ground according to claim 1 is characterized in that: The emergency escape device connection part (20) is connected to the revolving corridor of the service tower or the revolving platform of the service tower.

6. The manned space emergency escape device with a near-cabin entrance and direct access to the ground according to claim 4 is characterized in that: The emergency escape device entrance (201) is configured to be within a close range of the manned cabin exit.

7. The manned space emergency escape device with a near-cabin entrance and direct access to the ground according to claim 1 is characterized in that: The inner path can be configured with a flexible deceleration material layer or a rigid deceleration structure.

8. The manned space emergency escape device with a near-cabin entrance and direct access to the ground according to claim 7 is characterized in that: The main body section (30) can operate synchronously with the closing or opening action of the rotary mechanism.

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