Expansion testing device in thermal vacuum environment

Abstract

The invention relates to the technical field of spaceflight, in particular to an unfolding test device in a thermal vacuum environment, which comprises a supporting mechanism, a sliding mechanism and a pressing and releasing mechanism, the supporting mechanism is placed on the fixed face, the sliding mechanism is arranged on the upper surface of the supporting mechanism, the lifting mechanism is arranged at one end of the supporting mechanism and connected with the sliding mechanism, and the sliding mechanism is used for guiding the lifting mechanism when the lifting mechanism is unfolded. The at least one pressing and releasing mechanism is arranged on the supporting mechanism and communicated with the power source, at the beginning, the pressing and releasing mechanism is used for pressing the lifting mechanism, and after being powered on, the pressing and releasing mechanism releases the lifting mechanism. According to the unfolding test device in the thermal vacuum environment, the accuracy and the reliability of a test result are remarkably improved, and a powerful guarantee is provided for the effectiveness of solar wing on-orbit unfolding.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically to a testing device for deployment under a thermal vacuum environment. Background Technology

[0002] A solar array is a device that collects solar energy to power satellites and spacecraft; in other words, the primary energy source for satellites and spacecraft is the sun. Therefore, the ability of the solar array to deploy and lock synchronously in orbit is extremely important for the effective operation of satellites and spacecraft.

[0003] The lifting mechanism is part of the solar array's deployment. Currently, the existing method for verifying the lifting mechanism is to use a truss and ropes to suspend it and then deploy it. However, because testing by truss suspension cannot guarantee that the deployment direction of the lifting mechanism is in the preset straight line, and the deployment speed and stability cannot be guaranteed, the verification results are not accurate enough and cannot effectively guarantee the reliability of the solar array in subsequent use. Summary of the Invention

[0004] (i) The technical problem to be solved by the present invention is that the existing method of testing the lifting mechanism of the solar array by truss suspension cannot guarantee whether the deployment direction of the lifting mechanism is in the preset straight direction, and the deployment speed and deployment stability cannot be guaranteed. The results obtained by the verification are not accurate enough and cannot effectively guarantee the reliability of the solar array in subsequent use.

[0005] (II) Technical Solution To address the aforementioned technical problems, embodiments of the present invention provide a deployment testing device under a thermal vacuum environment for testing the lifting mechanism of a solar array, comprising a support mechanism, a sliding mechanism, and a clamping and releasing mechanism; The support mechanism is placed on a fixed surface, the sliding mechanism is located on the upper surface of the support mechanism, and the lifting mechanism is located at one end of the support mechanism and connected to the sliding mechanism. The sliding mechanism is used to guide the lifting mechanism when it is deployed. At least one clamping release mechanism is provided on the support mechanism and connected to the power supply. Initially, the clamping release mechanism is used to clamp the lifting mechanism. After power is applied, the clamping release mechanism releases the lifting mechanism.

[0006] Furthermore, the support mechanism includes a base and a fixing plate arranged perpendicularly to each other, and the clamping release mechanism includes a load-bearing cylinder, a memory metal cylinder, and a torsion spring; The sliding mechanism is located on the upper surface of the base, and one end of the lifting mechanism along its unfolding direction is fixed to the side wall of the fixed plate. One end of the support cylinder is fixed to the side wall of the fixed plate. The axis of the support cylinder is parallel to the unfolding direction of the lifting mechanism. The other end of the support cylinder is connected to the memory metal cylinder. A first hinge plate is provided on the side wall of the support cylinder, and a second hinge plate is provided at the bottom of the memory metal cylinder. The first hinge plate and the second hinge plate are hinged by a pin. The torsion spring is sleeved on the outside of the pin. The memory metal cylinder is connected to the power source via a lead wire. Initially, the end of the second hinge plate facing away from the first hinge plate is in contact with the outer wall of the lifting mechanism. After power is applied, the memory metal cylinder disconnects from the load-bearing cylinder, and the torsion spring causes the second hinge plate to flip, releasing the lifting mechanism.

[0007] Furthermore, the clamping release mechanism also includes a locking screw and a slotted bolt. The slotted bolt is located inside the memory metal cylinder, and one end of it passes through the second hinge plate. One end of the locking screw passes through the fixing plate and the load-bearing cylinder and is connected to the slotted bolt. The diameter of the end face of the slotted bolt at the connection between the shape memory metal cylinder and the load-bearing cylinder is smaller than the diameter of the end face of the rest of the bolt.

[0008] Furthermore, the support mechanism includes a vertical beam, which is vertically disposed at one end of the base, and the fixing plate is fixed to the side of the vertical beam facing the base.

[0009] Furthermore, the base includes a support beam and a connecting beam; At least two support beams are arranged at intervals and parallel to each other. Multiple connecting beams are provided between two adjacent support beams. The multiple connecting beams are arranged at intervals along the extension direction of the support beams. The connecting beams and the support beams, as well as the vertical beams and the support beams, are all fixed by angle steel.

[0010] Furthermore, the fixing plate has two positioning grooves that extend along the length of the vertical beam. Nuts are provided on the vertical beam, and fixing bolts pass through the positioning grooves and are threadedly connected to the nuts to fix the fixing plate and the vertical beam.

[0011] Furthermore, the sliding mechanism includes a slide rail and a slide plate; The slide rail is disposed on the upper surface of the support beam along the extension direction of the support beam, the slide plate is disposed above the slide rail, the slide plate is movable along the extension direction of the slide rail, and the end of the lifting mechanism opposite to the fixed plate is fixed to the upper surface of the slide plate.

[0012] Furthermore, the sliding mechanism also includes a slider, which is disposed at the bottom of the slide plate and is slidably connected to the slide rail to drive the slide plate to move along the extension direction of the slide rail.

[0013] Furthermore, the fixing plate is provided with a connecting recess, and the end of the lifting mechanism is provided with a flange, which is fixedly connected to the connecting recess by countersunk bolts.

[0014] Furthermore, the thermal vacuum environment deployment test device also includes a thermal vacuum tank, and the support mechanism, the sliding mechanism, the clamping and releasing mechanism and the lifting mechanism are all located inside the thermal vacuum tank.

[0015] The beneficial effects of this invention are: This invention provides a deployment test device under a thermal vacuum environment. By rationally dividing the functions of the support mechanism, sliding mechanism, and clamping and releasing mechanism, it achieves accurate simulation and testing of the deployment process of the solar array lifting mechanism. The support mechanism provides a stable installation foundation for the entire device, ensuring the overall structural rigidity of the device during testing and preventing the impact of foundation shaking on test data, thus ensuring the stability of the overall test. The sliding mechanism can strictly limit the deployment path of the lifting mechanism, ensuring that the deployment direction is always on a preset straight line, while also effectively controlling the deployment speed. The clamping and releasing mechanism achieves controllable switching between "clamping" and "releasing" through connection with the power supply. In the initial state, it reliably clamps the lifting mechanism, simulating the folded clamping state. After power is applied, it accurately releases, replicating the unlocking process after orbit insertion. Its control method is simple, efficient, and responsive, avoiding interference factors such as rope slack and entanglement in traditional suspension tests, significantly improving the accuracy and reliability of test results, and providing strong support for the effectiveness of solar array in-orbit deployment. Attached Figure Description

[0016] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the overall structure of the thermal vacuum environment deployment test device provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the lifting mechanism pressing of the unfolding test device under thermal vacuum environment provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the compression and release mechanism of the thermal vacuum environment deployment test device provided in an embodiment of the present invention; Figure 4 A cross-sectional view of the compression and release mechanism of the thermal vacuum environment deployment test device provided in an embodiment of the present invention; Figure 5 A schematic diagram of the flipping of the clamping and releasing mechanism of the thermal vacuum environment unfolding test device provided in an embodiment of the present invention; Figure 6 This is a schematic diagram of the lifting mechanism of the unfolding test device under thermal vacuum provided in an embodiment of the present invention. Figure 7 This is a schematic diagram showing the lifting mechanism of the thermal vacuum environment deployment test device provided in an embodiment of the present invention in its deployed position.

[0018] icon: 100 - Lifting mechanism; 200-Support mechanism; 201-Base; 202-Fixing plate; 203-Vertical beam; 204-Support beam; 205-Connecting beam; 206-Angle steel; 207-Positioning groove; 208-Connecting recess; 300 - Sliding mechanism; 301 - Slide rail; 302 - Slide plate; 303 - Slider; 400 - Compression release mechanism; 401 - Load-bearing cylinder; 402 - Memory metal cylinder; 403 - Torsion spring; 404 - First hinge plate; 405 - Second hinge plate; 406 - Pin; 407 - Lead wire; 408 - Locking screw; 409 - Grooved bolt. Detailed Implementation

[0019] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] In the description of this invention, it should be noted that the terms "upper" and "lower," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

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

[0022] Example 1 like Figures 1 to 7 As shown, the present invention provides a deployment test device under a thermal vacuum environment for testing the lifting mechanism 100 of a solar array, including a support mechanism 200, a sliding mechanism 300 and a clamping and releasing mechanism 400. The support mechanism 200 is placed on a fixed surface, the sliding mechanism 300 is located on the upper surface of the support mechanism 200, and the lifting mechanism 100 is located at one end of the support mechanism 200 and connected to the sliding mechanism 300. The sliding mechanism 300 is used to guide the lifting mechanism 100 when it is deployed. At least one clamping release mechanism 400 is provided on the support mechanism 200 and connected to the power supply. Initially, the clamping release mechanism 400 is used to clamp the lifting mechanism 100. After power is applied, the clamping release mechanism 400 releases the lifting mechanism 100.

[0023] In this embodiment, by rationally dividing the functions of the support mechanism 200, the sliding mechanism 300, and the clamping and releasing mechanism 400, accurate simulation and testing of the deployment process of the solar wing lifting mechanism 100 are achieved. The support mechanism 200 provides a stable installation foundation for the entire device, ensuring the overall structural rigidity of the device during testing, avoiding the impact of foundation shaking on test data, and ensuring the stability of the overall test. The sliding mechanism 300 can strictly limit the deployment path of the lifting mechanism 100, ensuring that the deployment direction is always on a preset straight line, while also effectively controlling the deployment speed. The clamping and releasing mechanism 400 achieves controllable switching between "clamping" and "releasing" through connection with the power supply. In the initial state, it reliably clamps the lifting mechanism 100, simulating the folded clamping state. After power is applied, it releases accurately, restoring the unlocking process after entering the orbit. Its control method is simple, efficient, and responsive, avoiding interference factors such as rope slack and entanglement in traditional suspension tests, significantly improving the accuracy and reliability of test results, and providing strong support for the effectiveness of the solar wing's on-orbit deployment.

[0024] Preferably, there are two clamping and releasing mechanisms 400, which are symmetrically arranged on both sides of the support mechanism 200 along the unfolding direction of the lifting mechanism 100, so that the lifting mechanism 100 can be in a clamped state in the initial state. Of course, the clamping and releasing mechanism 400 can also be set to one, three or more, which can be set according to the actual use.

[0025] During testing, sensors are used to collect data such as the deployment force, deployment speed, and deployment displacement of the lifting mechanism 100. It is also used to determine whether the lifting mechanism 100 can be locked after being fully deployed. After data processing, the deployment performance parameters of the lifting mechanism 100 are obtained and compared with the design requirements to determine whether the lifting mechanism 100 meets the requirements for on-orbit use.

[0026] According to one embodiment provided by the present invention, such as Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 and Figure 7 As shown, the support mechanism 200 includes a base 201 and a fixing plate 202 arranged perpendicularly to each other, and the pressing and releasing mechanism 400 includes a load-bearing cylinder 401, a memory metal cylinder 402 and a torsion spring 403. The sliding mechanism 300 is located on the upper surface of the base 201, and one end of the lifting mechanism 100 along its unfolding direction is fixed to the side wall of the fixed plate 202. One end of the support cylinder 401 is fixed to the side wall of the fixed plate 202. The axis of the support cylinder 401 is parallel to the unfolding direction of the lifting mechanism 100. The other end of the support cylinder 401 is connected to the memory metal cylinder 402. A first hinge plate 404 is provided on the side wall of the support cylinder 401. A second hinge plate 405 is provided at the bottom of the memory metal cylinder 402. The first hinge plate 404 and the second hinge plate 405 are hinged by a pin 406. A torsion spring 403 is sleeved on the outside of the pin 406. The memory metal cylinder 402 is connected to the power supply through the lead wire 407. Initially, the end of the second hinge plate 405 facing away from the first hinge plate 404 is in contact with the outer wall of the lifting mechanism 100. After the power is turned on, the memory metal cylinder 402 disconnects from the load-bearing cylinder 401, and the torsion spring 403 drives the second hinge plate 405 to flip, and the second hinge plate 405 releases the lifting mechanism 100.

[0027] In this embodiment, in the initial state, the end of the second hinge plate 405 facing away from the first hinge plate 404 is in contact with the outer wall of the lifting mechanism 100 to achieve tight clamping; after power is applied, the memory metal cylinder 402 disconnects from the support cylinder 401 and separates from the end face of the support cylinder 401. The torsion spring 403 drives the second hinge plate 405 to rotate around the pin 406, and the second hinge plate 405 is completely disengaged from the lifting mechanism 100, releasing the lifting mechanism 100.

[0028] The support mechanism 200 uses mutually perpendicular bases 201 and fixing plates 202 to achieve stable installation of the lifting mechanism 100, while ensuring the consistency between the unfolding direction of the lifting mechanism 100 and the guiding direction of the sliding mechanism 300. The pressing and releasing mechanism 400 innovatively adopts a structure in which a memory metal cylinder 402 and a torsion spring 403 cooperate. The memory metal cylinder 402 can quickly disconnect from the load-bearing cylinder 401 after being energized. With the elastic driving force of the torsion spring 403, it drives the second hinge plate 405 to quickly flip and release the lifting mechanism 100. The memory metal cylinder 402 is made of memory metal, which has stable performance in a hot vacuum environment and will not fail to release due to environmental factors. Through the hinged cooperation of the first hinge plate 404, the second hinge plate 405 and the pin 406, and the preload setting of the torsion spring 403, the tight fit between the second hinge plate 405 and the outer wall of the lifting mechanism 100 is ensured in the initial state, the pressing effect is reliable, and the loosening and displacement of the lifting mechanism 100 before testing is avoided.

[0029] According to one embodiment provided by the present invention, such as Figure 3 , Figure 4 and Figure 5 As shown, the clamping release mechanism 400 also includes a locking screw 408 and a slotted bolt 409. The slotted bolt 409 is located inside the memory metal cylinder 402, and one end passes through the second hinge plate 405. One end of the locking screw 408 passes through the fixing plate 202 and the load-bearing cylinder 401 and is connected to the slotted bolt 409. The end face diameter of the slotted bolt 409 at the connection between the shape memory metal cylinder 402 and the load-bearing cylinder 401 is smaller than the end face diameter of the rest of the bolt.

[0030] In this embodiment, when the shape memory metal cylinder 402 is not energized, the slotted bolt 409 is in good condition, and together with the locking screw 408, it fixes the connection between the shape memory metal cylinder 402 and the load-bearing cylinder 401, preventing them from separating due to vibration. When the shape memory metal cylinder 402 is energized, it heats up and the crystal structure undergoes a reversible phase transition. The shape memory metal cylinder 402 spontaneously recovers to its inherent shape at high temperature, thereby releasing a huge phase transition extrusion force to achieve the effect of breaking the slotted bolt 409, allowing its end face to separate from the load-bearing cylinder 401. Since the end face diameter of the slotted bolt 409 at the connection is small, the shape memory metal cylinder 402 can break the slotted bolt 409 more smoothly without obstruction, ensuring a smooth release process.

[0031] By adding a locking screw 408 and a slotted bolt 409 to the clamping and releasing mechanism 400, the clamping reliability of the device is further optimized without affecting the release lifting mechanism 100. One end of the locking screw 408 passes through the fixing plate 202 and the support cylinder 401 and is connected to the slotted bolt 409, preventing accidental separation of the shape memory metal cylinder 402 from the support cylinder 401 due to installation or environmental vibration. Furthermore, the diameter of the end face of the slotted bolt 409 at the connection point between the shape memory metal cylinder 402 and the support cylinder 401 is smaller than the rest, making it easier to disconnect the shape memory metal cylinder 402 from the support cylinder 401 when energized, ensuring a smooth release process. In addition, the coaxial design of the support cylinder 401, the shape memory metal cylinder 402, and the slotted bolt 409 ensures that the direction of the release force is consistent with the unfolding direction of the lifting mechanism 100, further reducing additional interference forces during unfolding and improving the accuracy of the test data.

[0032] According to one embodiment provided by the present invention, such as Figure 1 , Figure 2 , Figure 6 and Figure 7 As shown, the support mechanism 200 includes a vertical beam 203, which is vertically disposed at one end of the base 201, and a fixing plate 202 is fixed to the side of the vertical beam 203 facing the base 201.

[0033] Furthermore, the fixing plate 202 has two positioning grooves 207, which extend along the length of the vertical beam 203. Nuts are provided on the vertical beam 203, and fixing bolts pass through the positioning grooves 207 and are threadedly connected to the nuts to fix the fixing plate 202 and the vertical beam 203.

[0034] In this embodiment, the fixing plate 202 has two positioning grooves 207, which are rectangular through grooves. The two positioning grooves 207 are symmetrically arranged on both sides of the fixing plate 202 and extend along the length of the vertical beam 203. The vertical beam 203 is provided with a T-nut, which is welded and fixed to the side wall of the vertical beam 203. The fixing bolt is a hexagon socket head cap screw. After passing through the positioning groove 207, the fixing bolt is threaded to the nut on the vertical beam 203. The fixing plate 202 and the vertical beam 203 are fixed by tightening the fixing bolt.

[0035] When the installation height of the lifting mechanism 100 needs to be adjusted, loosen the fixing bolts, push the fixing plate 202 along the length of the vertical beam 203, adjust it to the target height, and then tighten the fixing bolts again. This achieves the height adjustment function of the fixing plate 202 on the vertical beam 203, significantly improving the versatility and adaptability of the device. The positioning groove 207 extends along the length of the vertical beam 203, allowing the fixing plate 202 to move up and down along the vertical beam 203, thereby adjusting the installation height of the lifting mechanism 100. This can meet the testing needs of lifting mechanisms 100 with different specifications and different unfolding height requirements. Furthermore, the operation is simple and convenient, and the locking is reliable. It can quickly fix the fixing plate 202 after it is adjusted to the target height, avoiding displacement of the fixing plate 202 during testing. In addition, the design of the positioning groove 207 also facilitates fine-tuning of the installation position of the fixing plate 202. By fine-tuning the height of the fixing plate 202, the relative positional accuracy between the lifting mechanism 100 and the sliding mechanism 300 can be ensured, further improving the accuracy and repeatability of the test.

[0036] In this embodiment, the vertical beam 203 is vertically mounted at one end of the base 201, forming a stable L-shaped support structure. Compared to directly mounting the fixing plate 202 onto the base 201, this better matches the installation height and deployment requirements of the lifting mechanism 100, making the installation position of the lifting mechanism 100 more consistent with actual on-orbit working conditions. The vertical beam 203 also provides an independent and stable mounting carrier for the fixing plate 202, reducing the impact of base 201 deformation on the installation accuracy of the fixing plate 202, ensuring the relative positional accuracy between the lifting mechanism 100 and the sliding mechanism 300, and thus ensuring the accuracy of the deployment guidance. In addition, the structural design of the vertical beam 203 facilitates subsequent adjustments to the height and angle of the fixing plate 202, improving the versatility and adaptability of the device, and meeting the testing requirements of lifting mechanisms 100 of different specifications.

[0037] According to one embodiment provided by the present invention, such as Figure 1 , Figure 2 , Figure 6 and Figure 7 As shown, the base 201 includes a support beam 204 and a connecting beam 205; At least two support beams 204 are arranged at intervals and parallel to each other. Multiple connecting beams 205 are provided between two adjacent support beams 204. The multiple connecting beams 205 are arranged at intervals along the extension direction of the support beams 204. The connecting beams 205 and the support beams 204, and the vertical beams 203 and the support beams 204 are all fixed by angle steel 206.

[0038] In this embodiment, the base 201 includes a support beam 204 and a connecting beam 205. Preferably, there are two support beams 204, both made of rectangular steel. Multiple connecting beams 205 are provided between the two support beams 204. The connecting beams 205 are also made of rectangular steel and are evenly spaced along the extension direction of the support beams 204. The connecting beams 205 and the support beams 204, as well as the vertical beams 203 and the support beams 204, are all fixed by angle steel 206. The angle steel 206 is an equilateral angle steel, which is used to fix it at 90°, providing a foundation for the subsequent installation of the lifting mechanism 100.

[0039] Adjacent support beams 204 are connected by multiple connecting beams 205 spaced along the extension direction of the support beams 204, forming a mesh frame structure. This effectively disperses the load transmitted by the lifting mechanism 100 during the test, avoids local deformation of the base 201, and ensures the structural stability of the device throughout the test. The connecting beams 205 and support beams 204, as well as the vertical beams 203 and support beams 204, are all fixed by angle steel 206. The angle steel 206 connection method has the characteristics of high connection strength and convenient assembly, which can further enhance the overall structural integrity of the base 201 and avoid structural stress concentration problems that may be caused by welding and other connection methods, providing a reliable structural guarantee for the smooth conduct of the test.

[0040] According to one embodiment provided by the present invention, such as Figure 1 , Figure 2 , Figure 6 and Figure 7 As shown, the sliding mechanism 300 includes a slide rail 301 and a slide plate 302; The slide rail 301 is located on the upper surface of the support beam 204 along the extension direction of the support beam 204. The slide plate 302 is located above the slide rail 301 and can move along the extension direction of the slide rail 301. The end of the lifting mechanism 100 away from the fixed plate 202 is fixed to the upper surface of the slide plate 302.

[0041] In this embodiment, during installation, the device is first slidable to check for excessive damping and to avoid interference factors in subsequent tests. During testing, the lifting mechanism 100 unfolds and the sliding plate 302 moves along the slide rail 301. There are no jamming or deviation during the movement, ensuring that the lifting mechanism 100 unfolds in a straight line.

[0042] The use of a sliding rail 301 and a sliding plate 302 provides precise and stable guidance for the deployment of the lifting mechanism 100, avoiding the problem of deployment direction deviation in traditional truss suspension methods. The front end of the lifting mechanism 100 is fixedly connected to the sliding plate 302, enabling the lifting mechanism 100 to drive the sliding plate 302 to move synchronously along the sliding rail 301 when it is deployed. The rigid connection between the sliding plate 302 and the lifting mechanism 100 ensures the effective transmission of deployment force and prevents swaying at the end of the lifting mechanism 100. The lifting mechanism 100 can be deployed after release and locked after being deployed into position. These are all existing technologies, so their related structures and working principles will not be described further.

[0043] According to one embodiment provided by the present invention, such as Figure 1 , Figure 2 , Figure 6 and Figure 7 As shown, the sliding mechanism 300 also includes a slider 303, which is located at the bottom of the slide plate 302. The slider 303 is slidably connected to the slide rail 301 to drive the slide plate 302 to move along the extension direction of the slide rail 301.

[0044] In this embodiment, the slider 303 incorporates a linear precision steel ball, resulting in low sliding damping. Preferably, each slide plate 302 has four sliders 303 at its bottom, symmetrically arranged on both sides of the slide plate 302. The sliders 303 are slidably connected to the slide rail 301 and fixedly connected to the slide plate 302, ensuring long-term stable use of the device. Adding sliders 303 as sliding connectors between the slide plate 302 and the slide rail 301 further optimizes the motion performance of the sliding mechanism 300, reduces resistance to the unfolding of the lifting mechanism 100 during guidance, and more realistically simulates the unfolding conditions under microgravity. The structural design of the sliders 303 also facilitates replacement and maintenance. When the sliders 303 wear out, only the slider 303 can be replaced, without replacing the entire slide plate 302 or slide rail 301, reducing maintenance costs and extending the device's service life.

[0045] According to one embodiment provided by the present invention, such as Figure 1 , Figure 2 , Figure 6 and Figure 7 As shown, the fixing plate 202 is provided with a connecting recess 208, and the end of the lifting mechanism 100 is provided with a flange. The flange is fixedly connected to the connecting recess 208 by countersunk bolts.

[0046] In this embodiment, the fixing plate 202 has a connecting recess 208 on the side facing the lifting mechanism 100. The connecting recess 208 is a circular countersunk hole. The end of the lifting mechanism 100 is provided with a flange. The diameter of the center hole of the flange is the same as the outer diameter of the lifting mechanism 100. The flange is fixedly connected to the connecting recess 208 by countersunk bolts. The head of the countersunk bolt is sunk into the countersunk hole of the flange. The upper surface of the head is flush with the upper surface of the flange and has no protruding part, so as to avoid interference with the unfolding of the lifting mechanism 100.

[0047] By providing connecting recesses 208 on the fixed plate 202 and installing a flange at the end of the lifting mechanism 100, and using countersunk bolts for fixing, the reliability and installation accuracy of the connection between the lifting mechanism 100 and the fixed plate 202 are significantly improved. The design of the connecting recesses 208 can position the end of the lifting mechanism 100, facilitating the rapid installation and positioning of the lifting mechanism 100, and ensuring the coaxiality and perpendicularity accuracy of the lifting mechanism 100 after installation. The large contact surface between the flange and the connecting recesses 208 can evenly distribute the load generated when the lifting mechanism 100 is deployed, avoiding connection failure caused by local stress concentration. The use of countersunk bolts ensures that the bolt heads do not protrude from the flange surface, thus not interfering with the deployment of the lifting mechanism 100. At the same time, the uniform tightening force of the countersunk bolts ensures a tight fit between the flange and the connecting recesses 208, preventing displacement or vibration of the lifting mechanism 100 due to loose connections during testing, further improving the accuracy and reliability of the test data.

[0048] According to one embodiment of the present invention, the test device for unfolding under a thermal vacuum environment further includes a thermal vacuum chamber, and the support mechanism 200, the sliding mechanism 300, the clamping and releasing mechanism 400 and the lifting mechanism 100 are all located inside the thermal vacuum chamber.

[0049] In this embodiment, the thermal vacuum chamber adopts a horizontal cylindrical structure. The support mechanism 200, sliding mechanism 300, clamping and releasing mechanism 400, and lifting mechanism 100 are all installed inside the thermal vacuum chamber. The bracket is fixedly connected to the bottom of the chamber by bolts. The chamber door of the thermal vacuum chamber adopts a quick-opening structure, which facilitates the installation, debugging, and maintenance of the device. The chamber is equipped with testing elements such as temperature sensors, pressure sensors, displacement sensors, and force sensors. The sensor signals are led out of the chamber through a vacuum-sealed connector and connected to the data acquisition system. Correspondingly, the lead wire 407 of the shape memory metal cylinder 402 is also led out of the chamber through a dedicated connector.

[0050] During testing, the vacuum level and temperature inside the hot vacuum tank were first adjusted to the on-orbit working design parameters of the lifting mechanism 100. After stabilization, the power supply of the clamping release mechanism 400 was turned on to release the lifting mechanism 100. At the same time, data acquisition was performed to collect the deployment performance data of the lifting mechanism 100, and to test its deployment status, speed, and whether it can be locked after deployment. This achieved accurate simulation and testing of the solar wing lifting mechanism deployment process in a hot vacuum environment.

[0051] By adding a hot vacuum chamber, the support mechanism 200, sliding mechanism 300, clamping and releasing mechanism 400, and lifting mechanism 100 are all placed inside the hot vacuum chamber, achieving a realistic simulation of the on-orbit hot vacuum environment and significantly improving the authenticity and effectiveness of the test. Placing all core test components inside the hot vacuum chamber avoids interference from external environmental factors such as airflow and vibration, further ensuring the accuracy of the test data. In addition, the hot vacuum chamber also facilitates the adjustment of environmental parameters during the test process. According to different on-orbit mission requirements, parameters such as vacuum degree and temperature inside the hot vacuum chamber can be adjusted to test the deployment performance of the lifting mechanism 100 under different operating conditions, improving the versatility and test range of the device.

[0052] In summary, the specific working principle of the testing device is as follows: By installing the lifting mechanism 100 and the clamping and releasing mechanism 400 onto the fixed plate 202, the lifting mechanism 100 is first clamped using the clamping and releasing structure and kept in a clamped state. The entire device is then placed inside a hot vacuum chamber. Once the environment inside the hot vacuum chamber reaches the expected design parameters, the shape memory metal cylinder 402 is energized through the lead wire 407. After being energized, the shape memory metal cylinder 402 unlocks and flips, and the lifting mechanism 100 automatically unfolds. After unfolding and extending to its full position, it locks. This process can verify the important parameters of the lifting mechanism 100 that require attention.

[0053] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A deployment test device under thermal vacuum environment, used to test the lifting mechanism (100) of a solar array, characterized in that, It includes a support mechanism (200), a sliding mechanism (300), and a pressure release mechanism (400); The support mechanism (200) is placed on a fixed surface, the sliding mechanism (300) is located on the upper surface of the support mechanism (200), the lifting mechanism (100) is located at one end of the support mechanism (200) and connected to the sliding mechanism (300), and the sliding mechanism (300) is used to guide the lifting mechanism (100) when it is deployed. At least one clamping release mechanism (400) is provided on the support mechanism (200) and connected to the power supply. Initially, the clamping release mechanism (400) is used to clamp the lifting mechanism (100). After power is applied, the clamping release mechanism (400) releases the lifting mechanism (100).

2. The thermal vacuum environment deployment test apparatus according to claim 1, characterized in that, The support mechanism (200) includes a base (201) and a fixing plate (202) arranged perpendicularly to each other, and the clamping release mechanism (400) includes a load-bearing cylinder (401), a memory metal cylinder (402), and a torsion spring (403). The sliding mechanism (300) is disposed on the upper surface of the base (201), and one end of the lifting mechanism (100) along its unfolding direction is fixed to the side wall of the fixing plate (202). One end of the support cylinder (401) is fixed to the side wall of the fixing plate (202). The axis of the support cylinder (401) is parallel to the unfolding direction of the lifting mechanism (100). The other end of the support cylinder (401) is connected to the memory metal cylinder (402). A first hinge plate (404) is provided on the side wall of the support cylinder (401). A second hinge plate (405) is provided at the bottom of the memory metal cylinder (402). The first hinge plate (404) and the second hinge plate (405) are hinged by a pin (406). The torsion spring (403) is sleeved on the outside of the pin (406). The memory metal cylinder (402) is connected to the power source via a lead wire (407). Initially, the end of the second hinge plate (405) facing away from the first hinge plate (404) is in contact with the outer wall of the lifting mechanism (100). After power is applied, the memory metal cylinder (402) disconnects from the load-bearing cylinder (401), and the torsion spring (403) drives the second hinge plate (405) to flip, releasing the lifting mechanism (100).

3. The testing apparatus for thermal vacuum environment according to claim 2, characterized in that, The clamping release mechanism (400) further includes a locking screw (408) and a slotted bolt (409). The slotted bolt (409) is located inside the memory metal cylinder (402), and one end passes through the second hinge plate (405). One end of the locking screw (408) passes through the fixing plate (202) and the load-bearing cylinder (401) and is connected to the slotted bolt (409). The end face diameter of the slotted bolt (409) located at the connection between the memory metal cylinder (402) and the load-bearing cylinder (401) is smaller than the end face diameter of the rest of the bolt.

4. The thermal vacuum environment deployment test apparatus according to claim 2, characterized in that, The support mechanism (200) includes a vertical beam (203), which is vertically disposed at one end of the base (201), and the fixing plate (202) is fixed to the side of the vertical beam (203) facing the base (201).

5. The thermal vacuum environment deployment test apparatus according to claim 4, characterized in that, The base (201) includes a support beam (204) and a connecting beam (205); At least two support beams (204) are arranged at intervals and parallel to each other. Multiple connecting beams (205) are provided between two adjacent support beams (204). The multiple connecting beams (205) are arranged at intervals along the extension direction of the support beams (204). The connecting beams (205) and the support beams (204), and the vertical beams (203) and the support beams (204) are all fixed by angle steel (206).

6. The thermal vacuum environment deployment test apparatus according to claim 4, characterized in that, The fixing plate (202) has two positioning grooves (207), which extend along the length of the vertical beam (203). The vertical beam (203) is provided with nuts, and fixing bolts pass through the positioning grooves (207) and are threadedly connected to the nuts to fix the fixing plate (202) and the vertical beam (203).

7. The thermal vacuum environment deployment test apparatus according to claim 5, characterized in that, The sliding mechanism (300) includes a slide rail (301) and a slide plate (302); The slide rail (301) is disposed on the upper surface of the support beam (204) along the extension direction of the support beam (204), the slide plate (302) is disposed above the slide rail (301), the slide plate (302) can move along the extension direction of the slide rail (301), and the lifting mechanism (100) is fixed to the upper surface of the slide plate (302) at one end away from the fixed plate (202).

8. The thermal vacuum environment deployment test apparatus according to claim 7, characterized in that, The sliding mechanism (300) further includes a slider (303), which is located at the bottom of the slide plate (302). The slider (303) is slidably connected to the slide rail (301) to drive the slide plate (302) to move along the extension direction of the slide rail (301).

9. The testing apparatus for thermal vacuum environment according to claim 2, characterized in that, The fixing plate (202) is provided with a connecting recess (208), and the end of the lifting mechanism (100) is provided with a flange. The flange is fixedly connected to the connecting recess (208) by countersunk bolts.

10. The thermal vacuum environment deployment test apparatus according to any one of claims 1-9, characterized in that, The thermal vacuum environment deployment test device also includes a thermal vacuum tank, and the support mechanism (200), the sliding mechanism (300), the clamping and releasing mechanism (400) and the lifting mechanism (100) are all located inside the thermal vacuum tank.

Images