Device for realizing supergravity rotating environment by annular double helix orbit and method thereof

Abstract

The application provides a device for realizing a supergravity rotating environment by a ring-shaped double helix track and a use method, and relates to the technical field of spaceflight. The device comprises a space cabin, an outer arm of the space cabin, a rotating system, a cabin computer and a ring-shaped double helix track. The ring-shaped double helix track is fixedly installed on the ground. The cabin computer is arranged in the space cabin. The space cabin is rotationally connected with the rotating system through the outer arm of the space cabin. One end of the rotating system, which is away from the outer arm of the space cabin, is movably connected with the ring-shaped double helix track. The rotating system and the cabin computer are in communication connection. The rotating system is used for driving the space cabin to rotate circumferentially on the ring-shaped double helix track. The cabin computer is used for controlling the thrust of the rotating system so as to control the speed of the space cabin in the double helix track. The application uses the double helix track to drive the space cabin to rotate along the track in the double helix track, so as to simulate a supergravity environment and a self-rotating environment.

Description

Technical Field

[0001] This application belongs to the field of aerospace technology, specifically relating to a ring-shaped spiral track-type device for realizing a hypergravity rotational environment and its usage method. Background Technology

[0002] With the rapid development of the aerospace industry, human enthusiasm for lunar exploration is growing, and exploration activities on the Moon and other extraterrestrial planets are becoming increasingly frequent. Aerospace engineering involves complex dynamic environments, and the reentry process during atmospheric re-entry poses a significant environmental challenge to astronauts, seriously affecting their working conditions and even their lives. Therefore, environmental simulation of this reentry process, which is completely different from Earth's environment, is essential.

[0003] Currently, there are various types of aerospace environment simulation equipment, such as impact towers, swing swings, and centrifuges. For simulating hypergravity environments, large manned centrifuges are typically used. A boom drives a pod to rotate around a main axis on a horizontal plane. As the pod moves in a circular motion, it generates centrifugal inertial forces outward along the radius, subjecting the subject to the combined effect of horizontal inertial forces and vertical gravity, creating a hypergravity effect. However, this method can only simulate a single, specific motion environment. For example, the recurrent motion coupling during reentry cannot provide simulated training for astronauts.

[0004] Application content

[0005] To overcome the shortcomings of the prior art, this application proposes a ring-shaped spiral track-type device for realizing a hypergravity rotational environment, comprising: a space capsule 3, a space capsule outer arm 5, a rotation system, an in-cabin computer 4, and a ring-shaped double spiral track 11. The ring-shaped double spiral track 11 is fixedly installed on the ground. The in-cabin computer 4 is disposed inside the space capsule 3. The space capsule 3 is rotatably connected to the rotation system through the space capsule outer arm 5. The end of the rotation system away from the space capsule outer arm 5 is movably connected to the ring-shaped double spiral track 11. The rotation system and the in-cabin computer 4 are communicatively connected.

[0006] The rotation system is used to drive the space capsule 3 to rotate circumferentially on the annular double helix track 11;

[0007] The in-cabin computer 4 is used to control the thrust of the rotation system, thereby controlling the speed at which the spacecraft 3 moves within the double helix track 11.

[0008] Preferably, there are two space capsule outer arms 5, which are symmetrically arranged on both sides of the space capsule 3.

[0009] Preferably, the rotation system includes: a guide plate 8, a guide wheel 1, an air jet assembly 2, and a rotating shaft assembly;

[0010] One end of the rotating shaft assembly is connected to the outer arm 5 of the space capsule, and the other end of the rotating assembly is connected to the guide plate 8. A guide wheel 1 is installed on the end of the guide plate 8 away from the rotating shaft assembly. The guide wheel 1 is movably connected to the annular double helix track 11. The jet assembly 2 is connected to the guide plate and is communicatively connected to the in-cabin computer 4.

[0011] Preferably, both the guide wheel 1 and the jet assembly 2 are rigidly fixed to the guide plate 8.

[0012] Preferably, the rotating shaft assembly includes a bearing 6 and a rotating shaft 7, wherein the bearing 6 is installed inside the rotating shaft 7, and the two ends of the rotating shaft 7 are respectively connected to the space capsule outer arm 5 and the guide plate 8.

[0013] Preferably, the jet assembly 2 is provided in one or more sets, and the one or more sets of jet assemblies 2 are connected at intervals on the guide plate 8.

[0014] Preferably, the space capsule 3 is also provided with an entrance / exit and a space capsule door 9 corresponding to the entrance / exit. When environmental simulation begins, the space capsule door 9 seals the space capsule 3.

[0015] Preferably, an annular double helix track 11 is connected to an annular double helix track mounting rod 10, one end of which is vertically fixed to the ground and the other end is connected to the outer surface of the annular double helix track 11.

[0016] Preferably, multiple sets of the annular double helix track mounting and fixing rods 10 are arranged in parallel, and the multiple sets of the annular double helix track mounting and fixing rods 10 vertically install the annular double helix track 11 in a vertical plane.

[0017] Based on the same concept, this application also provides a method for using a ring-shaped double-helix track-type device for achieving a hypergravity rotational environment, including:

[0018] When the rotation system is started, the in-cabin computer 4 controls the magnitude of the thrust provided by the rotation system. The rotation system drives the space cabin 3 to rotate axially on the annular double helix track 11 through the space cabin outer arm 5.

[0019] When the rotation system is shut down, the onboard computer 4 controls the rotation system to stop providing thrust, and the space capsule 3 decelerates under the action of gravity and friction, falling back to the bottom of the annular double helix track 11;

[0020] The aforementioned annular double-helix track-type hypergravity rotation environment device is the same as described above.

[0021] Compared with the closest prior art, the beneficial effects of this application are as follows:

[0022] This application provides a ring-shaped double-helix track-type device for achieving a hypergravity rotational environment, comprising: a space capsule 3, a space capsule outer arm 5, a rotation system, an in-cabin computer 4, and a ring-shaped double-helix track 11. The ring-shaped double-helix track 11 is fixedly installed on the ground. The in-cabin computer 4 is disposed inside the space capsule 3. The space capsule 3 is rotatably connected to the rotation system via the space capsule outer arm 5. One end of the rotation system away from the space capsule outer arm 5 is movably connected to the ring-shaped double-helix track 11. The rotation system and the in-cabin computer 4 are communicatively connected. The rotation system is used to: drive the space capsule 3 in the ring-shaped double-helix track 11. The spiral orbit 11 rotates circumferentially; the in-cabin computer 4 is used to control the thrust of the rotation system, thereby controlling the speed of the space capsule 3 within the double helix orbit 11; the device described in this application utilizes a circular double helix orbit structure to enable the space capsule to simultaneously experience prolonged hypergravity and self-rotation environments, compared to previous aerospace test equipment that could only achieve a single type of motion, providing a good method for simulating the reentry process; the device has a simple structure, is easy to control, occupies a small space, and can simultaneously place multiple environmental simulation systems on the circular double helix orbit, enabling simultaneous simulation of multiple astronauts and making efficient use of time and space. Attached Figure Description

[0023] Figure 1 A front structural schematic diagram of a ring-shaped double-helix track-type device for simulating a hypergravity rotational environment provided in this application;

[0024] Figure 2 An enlarged schematic diagram of the environmental simulation system structure at point A of the annular double-helix track-type simulation device for realizing a hypergravity rotational environment, provided in this application;

[0025] Figure 3 A schematic diagram of a circular double-helix track structure for simulating a hypergravity rotational environment, provided in this application;

[0026] Figure 4 A magnified schematic diagram of a partial structure at point A of a ring-shaped double-helix track-type device for simulating a hypergravity rotational environment, provided in this application;

[0027] Figure 5 A flowchart illustrating the usage of a ring-shaped double-helix track-type device for simulating a hypergravity rotational environment, as provided in this application.

[0028] Among them, 1-guide wheel, 2-jet assembly, 3-space cabin, 4-in-cabin computer, 5-space cabin outer arm, 6-bearing, 7-rotating shaft, 8-guide plate, 9-space cabin door, 10-annular double helix track mounting rod, 11-annular double helix track. Detailed Implementation

[0029] The specific embodiments of this application will be further described in detail below with reference to the accompanying drawings.

[0030] Example 1:

[0031] To address the problems existing in the current technology, this application provides a method such as... Figure 1 The circular spiral track-type device for realizing a hypergravity rotational environment includes: a space capsule 3, a space capsule outer arm 5, a rotation system, an in-cabin computer 4, and a circular double spiral track 11. The circular double spiral track 11 is fixedly installed on the ground. The in-cabin computer 4 is installed inside the space capsule 3. The space capsule 3 is rotatably connected to the rotation system through the space capsule outer arm 5. The end of the rotation system away from the space capsule outer arm 5 is movably connected to the circular double spiral track 11. The rotation system and the in-cabin computer 4 are communicatively connected.

[0032] The rotation system is used to drive the space capsule 3 to rotate circumferentially on the annular double helix track 11;

[0033] The in-cabin computer 4 is used to control the thrust of the rotation system, thereby controlling the speed at which the spacecraft 3 moves within the double helix track 11.

[0034] The space capsule 3 is used to carry simulated test personnel and is rigidly connected to the outer arm 5 of the space capsule.

[0035] The space capsule 3, space capsule outer arm 5, rotation system, and in-cabin computer 4 together constitute the following: Figure 2 The environmental simulation system shown, the Figure 2 for Figure 1 The enlarged view of the environmental simulation system structure shown at point A shows the experimenters experiencing a hypergravity environment in the environmental simulation system.

[0036] The use of a circular double-helix orbit structure allows the spacecraft to simultaneously experience prolonged hypergravity and self-rotating environments, unlike previous spacecraft experimental devices that could only achieve a single type of motion. This provides an excellent method for simulating the reentry process. The device has a simple structure, is easy to control, occupies a small space, and can simultaneously place multiple environmental simulation systems on the circular double-helix orbit, enabling multiple astronauts to simulate simultaneously and making efficient use of time and space.

[0037] Preferably, there are two space capsule outer arms 5, which are symmetrically arranged on both sides of the space capsule 3.

[0038] The spacecraft is positioned on both sides of the space capsule 3 to maintain balance on both sides of the space capsule 3. The forces on the outer arm 5 of the space capsule can achieve balance on the horizontal plane, so that the space capsule 3 will not shift or rotate under the action of external forces.

[0039] The rotation system includes: a guide plate 8, a guide wheel 1, an air jet assembly 2, and a rotating shaft assembly;

[0040] One end of the rotating shaft assembly is connected to the outer arm 5 of the space capsule, and the other end of the rotating assembly is connected to the guide plate 8. A guide wheel 1 is installed on the end of the guide plate 8 away from the rotating shaft assembly. The guide wheel 1 is movably connected to the annular double helix track 11. The jet assembly 2 is connected to the guide plate 8 and is communicatively connected to the in-cabin computer 4.

[0041] The in-cabin computer 4 controls the jet assembly 2 to start jetting, which is a combination of centrifugal motion around the center of the annular double helix track 11 and self-rotation in a radial plane with the center of the annular double helix track 11 as the radius.

[0042] The guide wheel 1, guide plate 8, jet device 2, and rotating shaft 7 form a rotating system in the same direction. The function of rotating shaft 7 and bearing 6 is to cut off the torsional torque generated by the guide plate 8 moving along the annular double helix track 11, so that the space capsule 3 and the space capsule outer arm 5 can maintain their direction of movement and keep the head and tail of the space capsule in the horizontal plane.

[0043] Preferably, both the guide wheel 1 and the jet assembly 2 are rigidly fixed to the guide plate 8.

[0044] The guide wheel 1 is placed on the annular double helix track 11, and under the power of the jet device 2, it moves forward along the annular double helix track 11.

[0045] The jet assembly 2 is the power source for realizing the hypergravity rotation environment and is connected to the in-cabin computer 4.

[0046] Preferably, the rotating shaft assembly includes a bearing 6 and a rotating shaft 7, wherein the bearing 6 is installed inside the rotating shaft 7, and the two ends of the rotating shaft 7 are respectively connected to the space capsule outer arm 5 and the guide plate 8.

[0047] Both the guide wheel 1 and the jet assembly 2 are rigidly fixed on the guide plate 8, meaning that all three rotate simultaneously in the same direction. Since the guide plate 8 and the outer arm of the space capsule 5 are movably connected through the bearing 6 and the rotating shaft 7 of the rotating shaft assembly, the space capsule 3 is guaranteed not to rotate.

[0048] Preferably, the jet assembly 2 is provided in one or more sets, and the one or more sets of jet assemblies 2 are connected at intervals on the guide plate 8.

[0049] The jet assembly 2 is arranged in one or more different configurations on both sides of the guide plate 8.

[0050] The jet assembly 2 determines the jet volume based on the position of the guide wheel 1, thereby controlling the forward speed of the guide wheel 1 along the annular double helix track 11. The purpose of this operation is to ensure that both guide wheels are within a radial plane centered on the annular double helix track 11.

[0051] Preferably, the space capsule 3 is also provided with an entrance / exit and a space capsule door 9 corresponding to the entrance / exit. When environmental simulation begins, the space capsule door 9 seals the space capsule 3.

[0052] The entrances and exits and the space hatch 9 on the space capsule 3 allow test personnel to enter and exit to conduct tests.

[0053] The structure of the annular double helix track 11 is as follows: Figure 3 As shown, an enlarged view of the partial structure for the installation and fixing of its annular double helix track 11 is as follows. Figure 4 As shown, an annular double helix track 11 is connected to an annular double helix track mounting rod 10. One end of the annular double helix track mounting rod 10 is vertically fixed to the ground, and the other end is connected to the outer surface of the annular double helix track 11.

[0054] The annular double helix track 11 is placed on the ground and rigidly connected, and its installation method is vertical installation.

[0055] Preferably, multiple sets of the annular double helix track mounting and fixing rods 10 are arranged in parallel, and the multiple sets of the annular double helix track mounting and fixing rods 10 vertically install the annular double helix track 11 in a vertical plane.

[0056] The parallel installation of multiple sets of annular double helix track mounting rods 10 can more stably stabilize the annular double helix track 11, thereby enabling multiple tests and increasing the safety of the device.

[0057] Example 2:

[0058] A method for using a ring-shaped double-helix track-type device to achieve a hypergravity rotational environment, such as... Figure 5 As shown, it includes:

[0059] When the rotation system is started, the in-cabin computer 4 controls the magnitude of the thrust provided by the rotation system. The rotation system drives the space cabin 3 to rotate axially on the annular double helix track 11 through the space cabin outer arm 5.

[0060] When the rotation system is shut down, the onboard computer 4 controls the rotation system to stop providing thrust, and the space capsule 3 decelerates under the action of gravity and friction, falling back to the bottom of the annular double helix track 11;

[0061] The aforementioned annular double-helix track-type hypergravity rotation environment device is the same as described above.

[0062] The simulated personnel enter the space capsule through hatch 9, then activate the in-cabin computer 4, which in turn activates the jet propulsion system 2, driving the guide plate 8 and guide wheel 1. The guide wheel 1 moves forward along the circular double helix track, thus advancing the environmental simulation system composed of the space capsule 3, guide wheel 1, guide plate 8, jet propulsion system 2, in-cabin computer 4, and space capsule outer arm 5. The central part of the system, namely the space capsule and space capsule outer arm 5, moves in a circular direction centered on the circular double helix track 11. Figure 1 The direction shown is clockwise.

[0063] The experiment simulates the kinematic environment of the personnel in the space capsule 3 as centrifugal motion around the center of the annular double helix track 11 and rotational motion around the space capsule itself in the radial plane formed by the three points of the two guide wheels 1 and the center of the annular double helix track 11.

[0064] This device simulates the complex motion environment that astronauts experience during spaceflight, which includes both hypergravity and their own rotation.

[0065] At the end of the test, the in-cabin computer 4 was shut down, and the jet device 2 stopped jetting. The environmental simulation system lost its power source and gradually decelerated under the action of gravity and friction, finally falling back to the bottom of the circular double helix track, which is the position closest to the ground.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application and not to limit its protection scope. Although this application has been described in detail with reference to the above embodiments, those skilled in the art should understand that after reading this application, they can still make various changes, modifications or equivalent substitutions to the specific implementation of the application, but these changes, modifications or equivalent substitutions are all within the protection scope of the claims pending approval.

Claims

1. A ring-shaped double-helix track-type device for achieving a hypergravity rotational environment, characterized in that, include: The spacecraft comprises a space capsule (3), a space capsule outer arm (5), a rotation system, an in-cabin computer (4), and a circular double helix track (11). The circular double helix track (11) is fixedly installed on the ground. The in-cabin computer (4) is located inside the space capsule (3). The space capsule (3) is rotatably connected to the rotation system through the space capsule outer arm (5). One end of the rotation system away from the space capsule outer arm (5) is movably connected to the circular double helix track (11). The rotation system and the in-cabin computer (4) are communicatively connected. The rotation system is used to drive the space capsule (3) to rotate circumferentially on the annular double helix track (11); The in-cabin computer (4) is used to: control the thrust of the rotation system to control the speed of the space capsule (3) moving within the double helix track (11); The rotation system includes: a guide plate (8), a guide wheel (1), an air jet assembly (2), and a rotating shaft assembly; One end of the rotating shaft assembly is connected to the outer arm (5) of the space cabin, and the other end of the rotating shaft assembly is connected to the guide plate (8). A guide wheel (1) is installed on the end of the guide plate (8) away from the rotating shaft assembly. The guide wheel (1) is movably connected to the annular double helix track (11). The jet assembly (2) is connected to the guide plate. The jet assembly (2) is communicatively connected to the in-cabin computer (4). Both the guide wheel (1) and the jet assembly (2) are rigidly fixed to the guide plate (8); The rotating shaft assembly includes a bearing (6) and a rotating shaft (7). The bearing (6) is installed inside the rotating shaft (7). The two ends of the rotating shaft (7) are respectively connected to the space capsule outer arm (5) and the guide plate (8).

2. The apparatus as claimed in claim 1, characterized in that, The space capsule has two outer arms (5), which are symmetrically arranged on both sides of the space capsule (3).

3. The apparatus as described in claim 1, characterized in that, The jet assembly (2) is provided with one or more sets, and the one or more sets of jet assemblies (2) are connected at intervals on the guide plate (8).

4. The apparatus as claimed in claim 1, characterized in that, The space capsule (3) is also provided with an entrance and an exit and a space capsule door (9) corresponding to the entrance and exit. When the environmental simulation begins, the space capsule door (9) seals the space capsule (3).

5. The apparatus as claimed in claim 1, characterized in that, The annular double helix track (11) is connected to an annular double helix track mounting rod (10). One end of the annular double helix track mounting rod (10) is vertically fixed to the ground and the other end is connected to the outer surface of the annular double helix track (11).

6. The apparatus as claimed in claim 5, characterized in that, Multiple sets of the annular double helix track mounting rods (10) are arranged in parallel, and the multiple sets of the annular double helix track mounting rods (10) vertically install the annular double helix track (11) in a vertical plane.

7. A method of using a ring-shaped double-helix track-type device for achieving a hypergravity rotational environment, characterized in that, include: When the rotation system is started, the in-cabin computer (4) controls the magnitude of the thrust provided by the rotation system. The rotation system drives the space cabin (3) to rotate axially on the annular double helix track (11) through the space cabin outer arm (5). When the rotation system is shut down, the in-cabin computer (4) controls the rotation system to stop providing thrust, and the spacecraft (3) decelerates under the action of gravity and friction, falling back to the bottom of the circular double helix track (11); The aforementioned annular double-helix track-type hypergravity rotation environment device is the annular double-helix track-type hypergravity rotation environment device as described in any one of claims 1-6.

Images