Simulation cabin with variable structure for light environment test of manned spacecraft

Abstract

The invention discloses a structure-variable simulation cabin for a light environment test of a manned spacecraft, and relates to the technical field of environment simulation of manned spacecrafts. Comprising a simulation cabin main body composed of replaceable functional wall plates, the outer wall of the simulation cabin main body is provided with a top ring frame, a side ring frame and a bottom ring frame which are used for limiting the spatial configuration of the simulation cabin main body and are detachably connected with the functional wall plates, and the side ring frame comprises a plurality of arc-shaped frame strips; the device further comprises an outer frame provided with a top ring frame installation rod and a telescopic mechanism, and the telescopic mechanism is vertically and movably installed on the outer frame and can adjust the positions of the arc-shaped frame strips in the radial direction of the side ring frame. According to the simulation cabin with the variable structure for testing the light environment of the manned spacecraft, provided by the invention, the simulation cabin can simulate the in-cabin environments of different manned spacecrafts by quickly adjusting the geometric configuration of the internal space of the simulation cabin; therefore, a ground verification platform which is efficient, economical and high in adaptability is provided for in-cabin light environment testing and man-machine work efficiency evaluation.

Description

Technical Field

[0001] This invention relates to the field of manned spacecraft environment simulation technology, and in particular to a structurally variable simulation cabin for testing the optical environment of manned spacecraft. Background Technology

[0002] In manned spaceflight programs, the cabin lighting environment and ergonomic design of spacecraft such as spacecraft and space stations have a crucial impact on astronauts' work efficiency, physical and mental health, and mission safety. To ensure the scientific validity and rationality of the cabin lighting system, display layout, warning sign visibility, and overall space layout, thorough environmental simulation tests must be conducted on the ground.

[0003] Currently, testing of the cabin environment of manned spacecraft mainly relies on the following two methods: One approach is to use a real spacecraft prototype module for testing. While this method provides the most realistic testing environment, the prototype module is extremely expensive; at the same time, the testing schedule is constrained by the overall module development milestones, and testing opportunities are scarce; furthermore, it is difficult to conduct destructive or iterative design verification using a prototype module, which limits the rapid optimization of the design. Second, constructing a fixed 1:1 physical simulation module. This method is currently a commonly used ground testing approach and can simulate the real cabin environment to a certain extent. However, manned spacecraft have diverse cabin structures—for example, the Shenzhou return capsule has a bell-shaped structure, while the space station experimental module has a barrel-shaped structure. Constructing a dedicated fixed simulation module for each cabin configuration would not only result in a long construction period, large financial investment, and significant land consumption, but also severely lack flexibility. Furthermore, when spacecraft mission requirements change or the cabin design is iterated, the existing fixed simulation module will be unable to adapt to the new testing requirements, leading to resource idleness and waste.

[0004] Therefore, when conducting ground tests for manned spaceflight, there is an urgent need for an in-cabin environment simulation device with rapid reconfiguration capabilities, controllable costs, and strong adaptability to support the development and verification needs of spacecraft with multiple models, configurations, and rapid iterations. Summary of the Invention

[0005] The purpose of this invention is to provide a structurally variable simulation cabin for testing the light environment of manned spacecraft. This simulation cabin can simulate the cabin environment of different manned spacecraft by rapidly adjusting its internal spatial geometry, thereby providing an efficient, economical and highly adaptable ground verification platform for cabin light environment testing and human-machine ergonomics evaluation.

[0006] The technical solution of the present invention to solve the above-mentioned technical problems is: a structurally variable simulation cabin for testing the light environment of manned spacecraft, comprising a main body of the simulation cabin composed of multiple replaceable functional wall panels that can be detachably spliced ​​together. The outer wall of the main body of the simulation cabin is provided with a top ring frame, a side ring frame and a bottom ring frame for limiting its spatial configuration and detachably connected to the functional wall panels. The side ring frame includes multiple arc-shaped frame strips arranged sequentially along its circumference. It also includes an outer frame surrounding the main body of the simulation cabin. The top of the outer frame is detachably and vertically mounted with a top ring frame mounting rod that is detachably connected to the top ring frame at its lower end. The middle of the outer frame is provided with multiple telescopic mechanisms that correspond one-to-one with the arc-shaped frame bars and are detachably connected. The telescopic mechanisms are vertically and movably mounted on the outer frame and can adjust the position of each arc-shaped frame bar radially along the side ring frame.

[0007] As a further improvement of the present invention, the telescopic mechanism includes a fixed ring rod that extends horizontally along the radial direction of the side ring frame. One end of the fixed ring rod is detachably connected to the arc-shaped frame strip, and the other end is provided with a power support arm through which the fixed ring rod moves axially. The power support arm is provided with a drive motor that can drive the fixed ring rod axially.

[0008] As a further improvement of the present invention, a non-powered support arm is also provided horizontally on the side of the powered support arm away from the arc-shaped frame bar, and the non-powered support arm is provided with a guide tube that is sleeved and cooperates with the fixed ring rod.

[0009] As a further improvement of the present invention, anti-torsion parallel arms are provided on both sides of the fixed ring rod, and the anti-torsion parallel arms are arranged opposite to each other; the anti-torsion parallel arms include arm a and arm b arranged coaxially, the near ends of arm a and arm b are hinged together, and the opposite ends of arm a and arm b are respectively hinged to the power support arm and the arc-shaped frame bar.

[0010] As a further improvement of the present invention, the outer wall of the fixed ring rod is provided with transmission teeth arranged sequentially along its extension direction, and the power output end of the drive motor is connected to the transmission teeth through a drive gear.

[0011] As a further improvement of the present invention, both the powered and unpowered outriggers are vertically and movably mounted on the outer frame via lugs and mounting screws at their ends.

[0012] As a further improvement of the present invention, the outer frame includes a plurality of support column frames for vertically movable installation of the telescopic mechanism. The top of each of the plurality of support column frames is connected to the upper top frame, and the upper end of the top ring frame mounting rod is detachably connected to the upper top frame. The bottom of each of the plurality of support column frames is connected to the lower bottom frame, and the bottom ring frame is mounted on the lower bottom frame.

[0013] As a further improvement of the present invention, the support column frame is a rectangular frame, which includes four vertical steel sections. The powered support arm is disposed between two vertical steel sections on the side closer to the arc-shaped frame, and the unpowered support arm is disposed between two vertical steel sections on the side farther from the arc-shaped frame.

[0014] As a further improvement of the present invention, the outer wall of the vertical steel section is provided with a mounting groove for the nut end of the mounting screw to be inserted and moved vertically, and the screw end of the mounting screw passes through the lug and is threadedly connected to a locking nut.

[0015] Beneficial effects Compared with existing technologies, the advantages of the structurally variable simulation cabin for manned spacecraft optical environment testing according to the present invention are as follows: 1. Achieves high flexibility of "one cabin for multiple uses": By combining the adjustable height of the top ring frame with the radially movable side ring frame arc strip, this simulation cabin can quickly and accurately reconstruct the interior space of manned spacecraft of various configurations (such as bell-shaped, column-shaped, etc.) on a single physical device, completely changing the fixed mode of "one type, one cabin" and greatly improving the utilization rate and applicability of the equipment. 2. Significantly reduced costs and resource consumption: There is no need to build a dedicated full-size fixed simulation cabin for every new model or configuration of spacecraft, saving a lot of construction funds, time costs and site space, resulting in a significant reduction in total cost of ownership; 3. It greatly accelerates the development and iteration process: When the design of the spacecraft cabin changes, this simulation cabin can complete the adjustment of the space configuration and the reconfiguration of the functional panels within hours or days, so that the ground verification test can closely follow the design iteration and significantly shorten the entire development cycle. 4. Provides a high-fidelity and stable testing environment: The spatial skeleton built based on the ring-frame system can accurately reproduce the geometric boundaries of the target cabin, providing a reliable benchmark for light environment testing. Modularly assembled functional wall panels can highly simulate the surface characteristics of the actual cabin interior. Under the stable support of the outer frame and the precise drive of the telescopic mechanism, the entire structure can ensure the stability of the configuration during testing, guaranteeing the reliability and validity of the test data; 5. Excellent maintainability and expandability: Modular functional panels and standardized ring frame and drive unit design make local maintenance, component replacement or function upgrades simple and quick, extending the service life of the equipment and adapting to possible new testing needs in the future.

[0016] The invention will become clearer from the following description, taken in conjunction with the accompanying drawings, which are used to explain embodiments of the invention. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a perspective view of the present invention; Figure 2 This is a perspective view of the main body of the simulation cabin of the present invention; Figure 3 This is a schematic diagram of the assembly principle of the main body of the simulation cabin of the present invention; Figure 4 This is a schematic diagram of the telescopic mechanism of the present invention.

[0019] The components are: 1-Simulation cabin main body; 11-Top ring frame; 12-Bottom ring frame; 13-Side ring frame; 131-Arc-shaped frame strip; 14-Functional wall panel; 2-Support column frame; 21-Vertical steel; 22-Mounting groove; 3-Upper top frame; 31-Top ring frame mounting rod; 4-Lower bottom frame; 5-Telescopic mechanism; 51-Powered outrigger; 511-Fixed ring rod; 512-Drive motor; 513-Drive gear; 514-Anti-torsion parallel arm; 52-Non-powered outrigger; 521-Guide tube; 53-Ear plate; 531-Mounting screw; 532-Locking nut. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0021] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; of course, they can also refer to a mechanical connection or an electrical connection; furthermore, they can refer to a direct connection, an indirect connection through an intermediate medium, or a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0022] Embodiments of the present invention will now be described with reference to the accompanying drawings.

[0023] Example: Specific embodiments of the present invention are as follows: Figure 1-4 As shown, a structurally variable simulation cabin for testing the optical environment of manned spacecraft is presented. This simulation cabin can rapidly change the geometry of its internal space through its unique mechanical structure to simulate the cabin environment of different manned spacecraft with high precision. The simulation cabin consists of three core parts: the main body of the simulation cabin 1, the ring frame system, and the outer frame.

[0024] The main body 1 of the simulation cabin is composed of multiple replaceable functional wall panels 14, which can be detachably assembled using wall panel mounting screws. The functional wall panels 14 can simulate the characteristics of different areas inside a real spacecraft cabin according to the test requirements, such as wall panels with simulated portholes, equipment interfaces, cable channels, or specific surface materials.

[0025] On the outer wall of the main body 1 of the simulation cabin, a ring frame system is provided to restrict its spatial configuration. The system includes a top ring frame 11, a bottom ring frame 12, and side ring frames 13. These ring frames are detachably connected to the outer wall of the functional wall panel 14 through connectors, and together they form the geometric boundary of the simulation cabin. Among them, the side ring frame 13 is composed of multiple arc-shaped frame strips 131 arranged sequentially along its circumference. These arc-shaped frame strips 131 are independent moving units that realize the radial deformation of the side ring frame 13.

[0026] The simulation chamber also includes an outer frame surrounding the main body 1 of the simulation chamber. A top ring frame mounting rod 31 is vertically mounted on the top of this outer frame via a detachable connection, and the lower end of the top ring frame mounting rod 31 is detachably connected to the top ring frame 11. The vertical height of the top ring frame 11 can be quickly adjusted by replacing the top ring frame mounting rods 31 of different lengths. In the middle of the outer frame, there are multiple telescopic mechanisms 5 that correspond one-to-one with the arc-shaped frame bars 131 of the side ring frames 13 and are detachably connected. These telescopic mechanisms 5 are vertically movable on the outer frame and can drive the arc-shaped frame bars 131 connected to them to move radially along the side ring frames 13, thereby changing the lateral profile of the simulation chamber.

[0027] In this embodiment, each telescopic mechanism 5 includes a fixed ring rod 511 extending horizontally along the radial direction of the side ring frame 13. One end of the fixed ring rod 511 is detachably connected to the corresponding arc-shaped frame strip 131, and the other end axially extends through a power support arm 51. A drive motor 512 is mounted on the power support arm 51, which can drive the fixed ring rod 511 to perform precise telescopic movements along its axial direction.

[0028] To enhance the stability of the fixed ring rod 511 during movement, a horizontally parallel, unpowered support arm 52 is also provided on the side of the powered support arm 51 facing away from the arc-shaped frame bar 131. A guide tube 521 is fixedly installed on the unpowered support arm 52, through which the fixed ring rod 511 passes and forms a sleeve fit, thereby providing effective auxiliary support for the fixed ring rod 511 and preventing it from deflecting.

[0029] To constrain the posture of the arc-shaped frame 131 and prevent it from twisting during radial movement, anti-torsion parallel arms 514 are provided on both sides of the fixed ring rod 511, and the two are arranged opposite each other. Each anti-torsion parallel arm 514 includes an arm a and an arm b arranged coaxially. The proximal ends of arms a and b are connected by a hinge shaft to form a movable joint. The opposite ends of arms a and b are respectively hinged to the power support arm 51 and the arc-shaped frame 131. In this way, the anti-torsion parallel arms 514, the power support arm 51, and the arc-shaped frame 131 form a parallelogram mechanism, ensuring that the arc-shaped frame 131 always maintains the correct normal direction during movement.

[0030] The drive motor 512 drives the fixed ring rod 511 via gear transmission. Specifically, continuous transmission teeth (forming a rack structure) are arranged on the outer wall of the fixed ring rod 511 along its extension direction. A drive gear 513 is mounted on the power output end of the drive motor 512, which meshes with the transmission teeth on the fixed ring rod 511. By controlling the forward and reverse rotation of the drive motor 512, the extension and retraction of the fixed ring rod 511 can be precisely controlled.

[0031] Both the powered support arm 51 and the unpowered support arm 52 have lugs 53 at their ends. These lugs are vertically and movably mounted on the outer frame via mounting screws 531 passing through them and locking nuts 532. In this embodiment, the outer frame includes multiple support column frames 2 for vertically and movably mounting the telescopic mechanism 5. The tops of the multiple support column frames 2 are connected to the upper top frame 3, and the upper end of the top ring frame mounting rod 31 is detachably connected to the upper top frame 3. The bottoms of the multiple support column frames 2 are connected to the lower bottom frame 4, and the bottom ring frame 12 is mounted on the lower bottom frame 4.

[0032] Each support column frame 2 is a rectangular frame composed of four vertical steel sections 21. The powered support arm 51 is located between the two vertical steel sections 21 on the side closer to the curved frame bar 131, while the unpowered support arm 52 is located between the two vertical steel sections 21 on the side farther away from the curved frame bar 131, forming a stable portal support structure.

[0033] On the outer wall of each vertical steel section 21, a mounting groove 22 is vertically formed. During installation, the nut end of the mounting screw 531 is inserted into the mounting groove 22 and can move freely vertically within the groove. The screw end of the mounting screw 531 passes through the lug 53 and is finally tightened with the lock nut 532. When it is necessary to adjust the installation height of the telescopic mechanism 5, simply loosen the lock nut 532, and the entire mechanism can slide along the mounting groove 22, and then be tightened again after it is in place.

[0034] When using this simulation module, if it is necessary to switch from a simulated cylindrical experimental module to a simulated bell-shaped return module, the specific adjustment process is as follows: 1) Configuration preset: Based on the digital model of the target return capsule, determine the diameter of each height section and the horizontal height of the top ring frame 11.

[0035] 2) Height Adjustment: Loosen the locking nut 532, adjust the telescopic mechanism 5 of each layer to the preset height along the mounting groove 22 of the support column frame 2, and lock it. At the same time, replace the top ring frame mounting rod 31 of the corresponding length and lower the top ring frame 11 to the predetermined position.

[0036] 3) Diameter Adjustment: The control system drives all drive motors 512 according to a preset program. Through gear-rack transmission, the fixed ring rods 511 of each layer drive the connected arc-shaped frame bars 131 to move radially to the target diameter. The ring frames at different heights will form a bell-shaped profile from the smaller diameter at the bottom to the smaller diameter at the top.

[0037] 4) Wall panel installation: The pre-manufactured functional wall panels 14 corresponding to the inner surface of the bell-shaped return capsule are installed onto the deformed ring frame system (top ring frame 11, side ring frames 13 of each layer, and bottom ring frame 12) by screws.

[0038] 5) Test preparation: Connect the lighting, sensors and other test equipment, and a high-fidelity return capsule light environment test chamber is set up.

[0039] Therefore, compared with existing simulation cabins, the variable simulation cabin of this structure has the following advantages: "Multi-purpose use of one compartment" and "low cost": It can be achieved by simply adjusting the frame of one compartment and replacing the wall panels, without having to build multiple physical compartments, saving more than 90% of construction costs and space. "Accelerated Iteration": Mechanical adjustments and modular installation reduce reconfiguration time from months to days, enabling testing to keep pace with design changes; "High fidelity and stability": The ring frame system accurately reproduces the geometric boundaries of the cabin, providing an accurate basis for optical path analysis; the rigid drive and anti-torsion design of the telescopic mechanism ensure that the frame will not deform due to external forces or vibrations during the test, and the data is reliable; "Maintainable and expandable": Any damaged motor, fixed ring rod, or wall panel can be replaced quickly and individually; future new spacecraft models only need to be designed with a new set of ring frame position parameters and new wall panels to be adapted, making it highly expandable.

[0040] The present invention has been described above in conjunction with the preferred embodiments, but the present invention is not limited to the embodiments disclosed above, but should cover various modifications and equivalent combinations made in accordance with the essence of the present invention.

Claims

1. A structurally variable simulation cabin for testing the optical environment of manned spacecraft, characterized in that, The simulation cabin body (1) is composed of multiple replaceable functional wall panels (14) that can be detachably spliced ​​together. The outer wall of the simulation cabin body (1) is provided with a top ring frame (11), a side ring frame (13) and a bottom ring frame (12) for limiting its spatial configuration and detachably connected to the functional wall panels (14). The side ring frame (13) includes multiple arc-shaped frame strips (131) arranged sequentially along its circumference. It also includes an outer frame surrounding the main body (1) of the simulation cabin. The top of the outer frame is detachably and vertically mounted with a top ring frame mounting rod (31) that is detachably connected to the top ring frame (11). The middle of the outer frame is provided with multiple telescopic mechanisms (5) that correspond one-to-one with the arc-shaped frame strips (131) and are detachably connected. The telescopic mechanism (5) is vertically and movable on the outer frame and can adjust the position of each arc-shaped frame strip (131) radially along the side ring frame (13).

2. The structurally variable simulation cabin for testing the optical environment of manned spacecraft according to claim 1, characterized in that, The telescopic mechanism (5) includes a fixed ring rod (511) that extends horizontally along the side ring frame (13) in the radial direction. One end of the fixed ring rod (511) is detachably connected to the arc-shaped frame strip (131), and the other end is provided with a power support arm (51) through which the fixed ring rod (511) moves axially. The power support arm (51) is provided with a drive motor (512) that can drive the fixed ring rod (511) axially.

3. The structurally variable simulation cabin for testing the optical environment of manned spacecraft according to claim 2, characterized in that, The power support arm (51) is also horizontally provided on the side away from the arc-shaped frame bar (131) with a non-powered support arm (52) parallel to the power support arm (51). The non-powered support arm (52) is provided with a guide tube (521) that is sleeved and cooperates with the fixed ring rod (511).

4. The structurally variable simulation cabin for testing the optical environment of manned spacecraft according to claim 2 or 3, characterized in that, The fixed ring rod (511) is provided with anti-torsion parallel arms (514) on both sides, and the anti-torsion parallel arms (514) are arranged opposite to each other; the anti-torsion parallel arms (514) include arm a and arm b arranged coaxially, the near ends of arm a and arm b are hinged together, and the opposite ends of arm a and arm b are respectively hinged to the power support arm (51) and the arc frame bar (131).

5. The structurally variable simulation cabin for testing the optical environment of manned spacecraft according to claim 2 or 3, characterized in that, The outer wall of the fixed ring rod (511) is provided with transmission teeth arranged sequentially along its extension direction, and the power output end of the drive motor (512) is connected to the transmission teeth through the drive gear (513).

6. The structurally variable simulation cabin for testing the optical environment of manned spacecraft according to claim 3, characterized in that, Both the powered support arm (51) and the unpowered support arm (52) are vertically and movably mounted on the outer frame by means of lugs (53) and mounting screws (531) at the ends.

7. The structurally variable simulation cabin for testing the optical environment of manned spacecraft according to claim 6, characterized in that, The outer frame includes multiple support column frames (2) for vertically movable installation of telescopic mechanism (5). The top of each of the multiple support column frames (2) is connected to the upper top frame (3), and the upper end of the top ring frame mounting rod (31) is detachably connected to the upper top frame (3). The bottom of each of the multiple support column frames (2) is connected to the lower bottom frame (4), and the bottom ring frame (12) is installed on the lower bottom frame (4).

8. The structurally variable simulation cabin for testing the optical environment of manned spacecraft according to claim 7, characterized in that, The support column frame (2) is a rectangular frame, which includes four vertical steel sections (21). The powered support arm (51) is located between two vertical steel sections (21) on the side close to the arc-shaped frame (131), and the unpowered support arm (52) is located between two vertical steel sections (21) on the side away from the arc-shaped frame (131).

9. The structurally variable simulation cabin for testing the optical environment of manned spacecraft according to claim 8, characterized in that, The outer wall of the vertical steel section (21) is provided with a vertical mounting groove (22) for the nut end of the mounting screw (531) to be inserted and moved vertically. The screw end of the mounting screw (531) passes through the lug (53) and is threadedly connected to a locking nut (532).

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