Space film storage and unfolding test integrated device

Abstract

The invention relates to a space thin film storage and unfolding test integrated device which comprises a flexible thin film rotating and fixing mechanism, a guide rail and sliding block mechanism, a pulley block mechanism and a test tool table. The flexible thin film rotating and fixing mechanism is used for installing a flexible thin film mechanism and controlling the flexible thin film mechanism to be unfolded and stored. A damper and a knob can be mounted at the upper part of the upper end rotary fixing piece for adjusting two modes of an unfolding test and a folding test; the elastic mast unfolding guide rail and sliding block mechanism is used for being connected with a mast of a flexible film and guiding the mast of the flexible film to move linearly. The pulley block mechanism is used for providing guiding force for linear motion of the mast; a movable pulley block is composed of a fixed pulley, a movable pulley and a rope, and required guiding force is provided below the movable pulley by hoisting a heavy object through the rope; the test bed tool serves as a mechanism framework to achieve mechanism mounting and fixing effects. The test bed has the advantages of integration of storage and unfolding tests, controllable unfolding resistance, high reliability and the like.

Description

Technical Field

[0001] This invention relates to the field of aerospace deployment testing technology, and in particular to a space membrane storage and ground deployment test. Background Technology

[0002] The deployment methods of flexible space membrane mechanisms mainly include active deployment driven by motors and passive deployment relying on the release of elastic potential energy stored in the elastic mast itself. Currently, the most studied passive deployment structures for space membranes include radially supported membrane structures and peripherally tensioned membrane structures. Radially supported membrane structures include limiting and clamping mechanisms, but the sail cannot be directly stored in the deployment mechanism; the mast and sail must be stored separately, resulting in low storage efficiency. Peripherally tensioned membrane structures have a simpler structure, allowing the mast and sail to be stored within the same sail compartment, leading to high storage efficiency.

[0003] In their article "Development and On-orbit Verification of the PW-Sat2 CubeSat Deorbit Sail," Li Yide et al. described the PW-Sat2 CubeSat deorbit sail as employing a peripherally tensioned thin-film structure. This deorbit sail is a rectangular flexible thin film with a side length of 2 m and an unfolded area of ​​4 m². 2 The entire sail is secured by a pod-like rod made of a measuring tape, which is folded and wound around its central axis and stored inside the sail hold. The sail hold is 51mm high and 90mm in outer diameter, resulting in extremely high storage efficiency. However, this deployment method suffers from high deployment resistance during ground testing due to its self-rotation around the central axis via an elastic mast. The deployment process is difficult to predict and analyze, and there are many experimental variables. Therefore, there is an urgent need for a low-cost ground testing scheme with low deployment resistance and a predictable deployment process.

[0004] Ground testing of space membranes is a crucial step in ensuring the normal operation of drag sails in space, with ground deployment testing being particularly important. However, the ground environment differs significantly from the space environment, presenting challenges such as high deployment resistance, difficulty in controlling the deployment process, stringent environmental requirements, and low consistency in repeatable tests.

[0005] Current research on space-based membrane ground deployment test mechanisms mainly focuses on reducing deployment resistance. Because the mast tends to bend towards the ground during deployment under gravity, friction between the mast, membrane, and ground creates significant resistance.

[0006] Existing space membrane deployment test systems developed by the European Space Agency (ESA) and the German Aerospace Center (DLR) counteract gravity by suspending helium balloons at the end of a flexible mast.

[0007] Hiraku Sakamoto and other scholars added a lighter air cushion to the end of the elastic mast to prevent it from bending under gravity.

[0008] The flexible film in the LightSail project achieves the effect of reducing friction by unfolding it on a low-friction platform.

[0009] ATK uses a negative spring at the end of the elastic mast to counteract gravity in a vacuum environment of 10⁻⁵ Torr.

[0010] The European Space Agency's DLR-ESA-INVENT project conducts tests on an air-bearing platform and uses helium balloons to counteract gravity and reduce deployment drag during the deployment test.

[0011] However, these experimental methods have drawbacks such as limited effectiveness and high cost. There is an urgent need for a low-cost, low-resistance, and highly reliable space thin film deployment test platform. Summary of the Invention

[0012] In response to the urgent need for ground testing of space film deployment mechanisms, the purpose of this invention is to provide an integrated device for space film storage and deployment testing, including but not limited to a spin-deployed space film deployment mechanism for ground deployment testing and space film folding and storage.

[0013] The technical solution for realizing the present invention is as follows: a space film storage and deployment test integrated device, including a flexible film rotation and fixing mechanism, a test fixture and four sets of deployment mechanisms. The four sets of deployment mechanisms are fixed on the test fixture in a cross shape, and the flexible film rotation and fixing mechanism is fixed at the center of the four sets of deployment mechanisms. Each set of deployment mechanisms includes an elastic mast deployment guide rail and slider mechanism, and a pulley block mechanism.

[0014] Compared with the prior art, the significant advantages of this invention are:

[0015] (1) The space film storage and unfolding test integrated device of the present invention can realize the advantage of the space film storage and unfolding test mechanism by replacing the component installed on the upper rotating fixing part.

[0016] (2) The space film storage and unfolding test integrated device of the present invention uses a damper, adjustable slide rail friction and suspended weight to make the unfolding resistance controllable.

[0017] (3) The space film storage and deployment test integrated device of the present invention can be adapted to the ground deployment test of different space film deployment mechanisms by changing the sail module.

[0018] (4) The space film storage and deployment test integrated device of the present invention can be transformed into a straight deployment by pulling the mast of the rotating deployment sail module by a heavy object, which conforms to the principle of rotating deployment. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments 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. In the drawings:

[0020] Figure 1 A schematic diagram of a space film storage and deployment test mechanism provided for a preferred embodiment of the present invention.

[0021] Figure 2 An exploded view of a flexible film rotation and fixing mechanism provided in a preferred embodiment of the present invention.

[0022] Figure 3 The schematic diagram shows a flexible film rotation fixing mechanism provided in a preferred embodiment of the present invention, in which the rotating fixing component is equipped with a knob in the stored state.

[0023] Figure 4 A schematic diagram of a flexible film rotation fixing mechanism provided in a preferred embodiment of the present invention, wherein the rotation fixing component is equipped with a damper in the unfolding test state.

[0024] Figure 5 A schematic diagram of the elastic mast deployment guide rail and slider mechanism provided in a preferred embodiment of the present invention.

[0025] Figure 6 This is a schematic diagram of the slider and slider eccentric wheel design provided for a preferred embodiment of the present invention.

[0026] Figure 7 A schematic diagram of the test fixture structure provided in a preferred embodiment of the present invention.

[0027] Figure 8 This is a schematic diagram of the various test mechanisms installed on the test fixture, which is a preferred embodiment of the present invention.

[0028] Figure 9 This is a schematic diagram of a pulley block mechanism provided for a preferred embodiment of the present invention.

[0029] Figure 10 This is a schematic diagram of the mast being deployed on track, provided as a preferred embodiment of the present invention.

[0030] Figure 11 A schematic diagram of the constrained rear mast deployment provided for a preferred embodiment of the present invention.

[0031] Figure 12 A force analysis diagram of a mast constrained by traction force is provided for a preferred embodiment of the present invention. Detailed Implementation

[0032] The following will describe in detail, with reference to the accompanying drawings, a space film storage and deployment test integrated device provided by the present invention. This embodiment is implemented under the premise of the technical solution of the present invention, and provides detailed implementation methods and specific operation processes. However, the protection scope of the present invention is not limited to the following embodiment. Those skilled in the art can modify and refine it without changing the spirit and content of the present invention.

[0033] Combination Figures 1-12 A space film storage and deployment test integrated device includes a flexible film rotation and fixing mechanism 1, a test fixture 4, and four deployment mechanisms. The four deployment mechanisms are fixed on the test fixture 4 in a cross shape, and the flexible film rotation and fixing mechanism 1 is fixed at the center of the four deployment mechanisms. Each deployment mechanism includes an elastic mast deployment guide rail and slider mechanism 2, and a pulley block mechanism 3.

[0034] Combination Figure 2 The flexible film rotating fixing mechanism 1 includes a sail module mounting base 101, a base 102, a central screw 103, a washer 104, a central shaft 106, an upper rotating fixing part 107, a knob base 108, a knob 109, a damper 110, a damper knob 111, and several bearings 105. The sail module mounting base 101 is a second-order frustum, the diameter of the first frustum on its top surface is smaller than the diameter of the second frustum on its bottom surface, and a groove is provided in the center of the first frustum. The central screw 103 passes through the base 102 and is fixedly connected to the groove of the sail module mounting base 101. The base 102 is connected and pressed to the module mounting plate 101 by fixing bolts. The washer 104, several bearings 105, and the central shaft 106 are sequentially sleeved on the screw of the central screw 103.

[0035] Combination Figure 2 , Figure 3 In the installed and stored state, the upper rotating fixing component 107 has four first through holes 1071, and the bottom surface of the knob base 108 has four second through holes 1081. The upper rotating fixing component 107, the knob base 108, and the knob 109 are sequentially arranged on the central shaft 106. The top surface of the central shaft 106 has a first threaded blind hole 1061 facing downwards. The knob base 108 and the upper rotating fixing component 107 are threadedly connected to the first threaded blind hole 1061 of the central shaft through the first through holes 1071 and the second through holes 1081. The knob base 108 has a second threaded blind hole 1082 at the center of its top surface, and the knob 109 has a third through hole 1091 at the center of its top surface and fourth through holes 1092 at both ends of its top surface. The third through holes 1091 are threadedly connected to the second threaded blind holes 1082 of the knob base. The fourth through holes 1092 on both sides of the knob 109 are used to install a knob extension rod as needed. The center screw 103 passes upward through the center of the upper rotating fixing member 107 and extends into the blind hole at the center of the bottom surface of the knob base 108. The center screw 103 and the aforementioned blind hole are in clearance fit.

[0036] Combination Figure 4 In the experimental deployment state, the upper rotating fixing part 107 is connected to the first threaded blind hole 1061 of the central shaft through the first through hole 1071. The damper base 111 is set on the top surface of the upper rotating fixing part 107. The damper base 111 is connected to the central screw 103 through the first threaded through hole 1111 in its center. The damper 110 is assembled with the damper base 111 through the internal hexagonal through hole 1101. The fifth through holes 1102 at both ends of the damper 110 are threadedly connected to the second threaded through holes 1072 at both ends of the upper rotating fixing part 107.

[0037] Combination Figure 1 , Figure 5 , Figure 6 The four elastic mast deployment guide rails and the slider mechanism 2 are arranged in a cross-shaped symmetrical distribution, wherein the elastic mast deployment guide rails and the slider mechanism 2 at any point are as follows: Figure 5 As shown in the embodiment, taking any one of the elastic mast deployment guide rails and slider mechanisms 2 as an example, the elastic mast deployment guide rail and slider mechanism 2 includes a guide rail 21, a slider 22, a mast connector 23, and two guide rail mounting plates 24. The guide rail 21 is equipped with guide rail mounting plates 24 at both ends. The slider 22 is assembled with the guide rail 21. The top surface of the slider 22 is fixed to the mast connector 23 by screws.

[0038] In this embodiment, the slider 22 and the mast connector 23 are connected by screws. The third threaded blind hole 226, which is 18.5mm apart in the same row as the slider, is threadedly connected to the sixth through hole 231 of the mast connector 23, which is at the same spacing.

[0039] In this embodiment, combined with Figure 7 The test fixture 4 includes a first profile 41, two second profiles 42, four third profiles 43, four fixed legs 44 with bases, and several fixed legs 45 without bases. The first profile 41 and the two second profiles 42 are symmetrically connected to form a cross-shaped frame. The third profiles 43 are respectively installed at the ends of the cross-shaped frame. The third profiles 43 are then assembled with the fixed legs 44 with bases. The fixed legs 45 without bases are installed at intervals below the cross-shaped frame for support and fixation.

[0040] In this embodiment, combined with Figure 8 The sail module mounting base 101 is installed at the center of the cross-shaped frame through the seventh through hole 1011 distributed in a cross-shaped symmetrical manner at R=55mm, and the guide rail mounting plate 24 is connected to the profile through the guide rail mounting plate through hole 242.

[0041] Combination Figure 9The pulley block mechanism 3 includes a connecting rod 31, a fixed pulley 32, a rope 33, a movable pulley 34, and a weight 35. The connecting rod 31 is mounted on the seventh through hole 441 of the fixed bracket 44 with a base. The fixed pulley 32 is mounted at the center of the connecting rod 31. The movable pulley 34 is connected to the fixed pulley 32 via the rope 33. The weight 35 is connected to the movable pulley 34, and the other end of the rope is connected to the mast connector 23.

[0042] Combination Figures 10-12 The experimental principle of this embodiment is as follows: (Combined with...) Figure 10 The energy stored in the on-orbit elastic mast drives the mast to deploy, combined with Figure 11 To facilitate the experiment, the movement mode was changed from constraining the mast's rotation to rotating the central axis: a constraint was applied to the extended end of the elastic mast, and the energy stored in the elastic mast drove the central axis to rotate, thus achieving the linear extension and deployment of the mast as shown in the figure below. However, since the sail of the sail module is connected to the mast, constraining it at the mast would cause the sail to come into contact with the constraint device, resulting in sail damage. Therefore, this experiment chose the following... Figure 12 The constraint method is as follows: a traction force is applied to the end of the elastic mast to prevent the elastic mast from being extended. The energy stored in the elastic mast then drives the central axis to rotate, thereby enabling the mast to extend and unfold in a straight line. Figure 12 The traction force It can be divided into forces that suppress the vertical direction. Forces that favor rotational motion By applying directional damping torque, balance .

[0043] Combination Figures 10-12 It can be determined that this experiment only changed the relative rotation direction of the device, without changing its deployment principle, and can achieve the simulation of the real working state.

[0044] Combination Figures 1-9 The following describes the experimental deployment method of this embodiment: the flexible film mechanism is fixed by the flexible film rotation and fixing mechanism 1, the four masts are connected to the mast connectors 23 on the slider, and the pulley block mechanism 3 is connected to the mast connectors by ropes after hoisting the heavy object, so as to pull the masts in the deployment direction.

[0045] This explains how to eliminate the influence of external kinetic energy from the hoisted heavy object on the test results. By analyzing the on-orbit deployment process of the flexible membrane, it can be concluded that during deployment, the release of elastic potential energy stored in the elastic mast drives the mast and flexible membrane to accelerate and rotate from a tightened state. The energy absorbed by the resistance overcome during on-orbit deployment mainly includes:

[0046] 1) Frictional resistance during the unfolding process between films and between films and mast;

[0047] 2) The frictional force generated by the contact between the film and the upper and lower end caps;

[0048] 3) Friction between the rotating central shaft and the bearing;

[0049] During ground-based testing, the influence of gravity and air resistance means that direct deployment on the ground would result in excessive friction and air resistance, leading to incomplete mast deployment and hindering verification of the flexible membrane's deployment performance. Constructing a ground-based test platform reduces friction between the flexible membrane and the ground. Furthermore, the addition of guide rails during testing allows for controllable deployment of the flexible membrane. The guide rail friction can be tested and adjusted using a force gauge, and combined with a damper, the traction force is balanced. The main resistances overcome during the flexible membrane's deployment in this test were:

[0050] 1) Frictional resistance during the unfolding process between films and between films and mast;

[0051] 2) The frictional force generated by the contact between the film and the upper and lower end caps;

[0052] 3) The frictional force between the rotation of the central shaft and the bearing;

[0053] 4) The frictional force generated at the contact point between the sail module and the guide rail;

[0054] 5) Friction between the guide rails and pulley system;

[0055] 6) The resistance generated by the constant damping of the damper;

[0056] Wherein 5) and 6) represent resistance magnitudes that can be directly obtained through calculation and adjustment; 4) represents a significant reduction compared to direct ground deployment; and 1), 2), and 3) represent resistances that must be overcome during in-orbit deployment. Therefore, compared to the in-orbit state, the gravitational potential energy of the traction force introduced in this experiment is balanced through items 5) and 6), ensuring that the gravitational potential energy of the suspended load satisfies:

[0057] The traction potential energy of the heavy object is less than the energy required to overcome the rotation of the damper plus the energy of friction from the guide rail and pulley system (small amount).

[0058] In other words, the elastic potential energy stored in the mast not only overcomes the conventional resistance during the deployment of the flexible film, but also the frictional resistance during ground testing.

[0059] The damper selected in this embodiment is a torque damper. The damper acts on a moving object or when the driving torque is greater than 1000 rpm. The output will be constant when on the object. The resistive torque, according to the formula for energy generated by torque.

[0060]

[0061] In the formula, For damper torque, The angle of rotation, The energy generated by the rotation of the damper is known to be the energy generated by the torque. The integral of the rotation angle is used to determine the energy generated by the damper. Therefore, to obtain the energy generated by the damper, it is necessary to first determine the angle of rotation of the central axis during the deployment of the thin film sail, that is, the number of times the thin film sail is wound around the central axis.

[0062] In this embodiment, during the folding process of the flexible film, the crease is formed by the contact force of the central axis. Caused by. The thickness of the layer to which the contact force is applied is defined as the crease thickness. For the encapsulated membrane, it is assumed that the contact area between the membrane and the central axis is small enough that the contact force is considered a concentrated force.

[0063] ,

[0064] ,

[0065] in, As an intermediate variable, For Young's modulus, For film thickness, Let be the integral variable. When assuming the membrane is a one-dimensional enclosure, considering the equilibrium of the small elements enclosing the membrane, the contact force can be derived as:

[0066]

[0067] in, For tensile force, The radius of the center hub, The crease interval length allows you to calculate the crease layer thickness. :

[0068]

[0069] The thickness of the flexible film after folding is calculated as follows: According to the formula for calculating the thickness of paper rolls:

[0070]

[0071] In the formula This refers to the axial storage area after the film is stored. For the outer radius after storage , The radius of the central axis , This represents the length of the flexible film after folding.

[0072] Set the number of rotations for storage to [number]. :

[0073]

[0074] The number of rotations for storage in this embodiment can then be calculated. .

[0075] Therefore, the rotation angle during the unfolding process of the folded thin-film sail can be calculated. for The energy generated by damping by the damper for:

[0076]

[0077] In this embodiment, the minimum measured traction force required to prevent the elastic mast from expanding during deployment is approximately [missing information]. .

[0078] Based on the length of the flexible mast It can be seen that the tensile force generated by the weight during the movement of the elastic mast from its retracted state to its fully extended state is... for Furthermore, the membrane sail is extended from four directions. To ensure that the gravitational potential energy generated by the traction force of the heavy object is less than the energy generated by the damper's damping and the sum of the energy generated by the slider and pulley system, thus obtaining the traction force... The scope is:

[0079]

[0080] In this embodiment, the traction force The driving force is provided by the heavy object hoisted by pulley block 3. and the friction between guide rail 21 and slider 22 The friction coefficient can be adjusted by adjusting the eccentricity of the pulley between the slider and the guide rail. Friction can be precisely adjusted Thus obtaining the required traction. .

[0081] The traction force selected in this embodiment for The traction force selection range is met, and the flexible film is fully deployed through the test scheme of this embodiment. The main influencing factors of the test scheme are controllable, the motion during the deployment process is predictable, and the influence of uncontrollable factors is greatly reduced, so that the test of this embodiment achieves the expected results and verifies the feasibility of this test scheme.

[0082] In this invention, the shape of the central shaft 106 is not specifically limited as long as it can be installed between the base 102 and the upper rotating fixing member 107. The shim 104 is not limited as long as it can prevent the sail membrane from rubbing against the base. The bearing 105 is not limited as long as it can be installed on the corresponding central shaft. The damper 110 is not specifically limited as long as it does not affect the sail module deployment test under specific test conditions.

[0083] In this embodiment, the central shaft 106 is the central shaft of the film deployment mechanism with a layered design on the upper and lower parts of the mast, and the thickness of the gasket 104 is... Damper torque .

[0084] This invention does not limit the magnitude of friction; it allows for adjustment of the driving force.

[0085] In this embodiment, the guide rail friction force for .

[0086] This invention does not impose specific limitations on the dimensions of the first profile 41 and the second profile 42, as long as they are suitable for unfolding the corresponding size of the canvas. It also does not impose specific limitations on the dimensions, installation height, and spacing of the third profile 43, the fixed legs 44 with bases, and the fixed legs 45 without bases, as long as the tooling test bench is installed stably and reliably.

[0087] In this embodiment, the length of the first profile 41 is... The second profile is 42mm long. The third profile is 43mm long. Mounting height of the fixed bracket 44 with base 45-inch baseless fixed stand Installation spacing .

[0088] This invention does not impose specific limitations on the weight of the object (35) or the number of movable pulleys (34), and these can be adjusted according to the experimental conditions.

[0089] Job Description

[0090] In the retracted state, the upper rotating fixing part 107 is equipped with a knob base 108 and a knob 109. The sail to be retracted is mounted on the central shaft 106. The knob 109 does not provide rotational resistance but can control the rotation and stop of the central shaft 106. The mast end on the sail is attached to the mast connector 23. There is no limit to the friction between the slider and the guide rail. One end of the tether is connected to the mast connector 23, and the other end is connected to the movable pulley 34. The weight 35 must be sufficient to provide a large enough preload. By rotating the central shaft through the knob, the mast end is subjected to preload, which causes the mast and sail to rotate tightly towards the central shaft for retraction.

[0091] 2) In the experimental deployment state, the upper rotating fixing part 107 is equipped with a damper 110 and a damper knob 111. The sail membrane to be stored is mounted on the central shaft 106. The damper 110 provides rotational resistance torque to balance most of the kinetic energy provided by the weight. The mast end on the sail membrane is mounted on the mast connector 23. The friction between the slider and the guide rail must be greater than the kinetic energy provided by the weight after the damper is balanced, so as to achieve the purpose of the external resistance of the test system being greater than the external force of the system. One end of the tether is connected to the mast connector 23, and the other end is connected to the movable pulley 34. The weight 35 must have sufficient preload. After the test begins, the flexible membrane relies on the kinetic energy stored by the elastic mast to overcome the resistance of the test system and the on-track resistance such as the electrostatic force between the sail membranes, thereby verifying the deployment performance of the flexible membrane.

Claims

1. A space film storage and deployment test integrated device, characterized in that: It includes a flexible film rotation fixing mechanism (1), a test fixture (4) and four sets of unfolding mechanisms. The four sets of unfolding mechanisms are fixed on the test fixture (4) in a cross shape. The flexible film rotation fixing mechanism (1) is fixed at the center of the four sets of unfolding mechanisms. Each set of unfolding mechanisms includes an elastic mast unfolding guide rail and slider mechanism (2) and a pulley block mechanism (3).

2. The integrated device for space film storage and deployment testing according to claim 1, characterized in that: The flexible film rotating fixing mechanism (1) includes a sail module mounting base (101), a base (102), a center screw (103), a washer (104), a central shaft (106), an upper rotating fixing part (107), a knob base (108), a knob (109), a damper (110), a damper knob (111), and several bearings (105). The sail module mounting base (101) is a second-order frustum. The diameter of the first frustum on its top surface is smaller than the diameter of the second frustum on its bottom surface. A groove is provided in the center of the first frustum. The center screw (103) passes through the base (102) and is fixedly connected to the groove of the sail module mounting base (101). The base (102) is connected and pressed to the module mounting plate (101) by the fixing bolts. The washer (104), several bearings (105), and the central shaft (106) are sequentially sleeved on the screw of the center screw (103). In the installed and stored state, the upper rotating fixing part (107), the knob base (108), and the knob (109) are sequentially arranged on the central shaft (106). The central screw (103) passes upward through the center of the upper rotating fixing part (107) and extends into the blind hole at the center of the bottom surface of the knob base (108). The central screw (103) and the aforementioned blind hole are in clearance fit. In the experimental deployment state, the damper base (111) is set on the top surface of the upper rotating fixing part (107). The damper base (111) is connected to the center screw (103) through the first threaded through hole (1111) in its center. The damper (110) is assembled with the damper base (111), and the two ends of the damper (110) are connected to the two ends of the upper rotating fixing part (107).

3. The integrated device for space film storage and deployment testing according to claim 2, characterized in that: Four identical elastic mast deployment guide rails and slider mechanisms (2) are arranged in a cross-shaped symmetrical distribution. The elastic mast deployment guide rails and slider mechanisms (2) include guide rails (21), sliders (22), mast connectors (23) and two guide rail mounting plates (24). Guide rail mounting plates (24) are installed at both ends of the guide rails (21). The sliders (22) are mounted on the guide rails (21). The top surface of the sliders (22) is fixed to the mast connectors (23).

4. The integrated device for space film storage and deployment testing according to claim 3, characterized in that: The test fixture (4) includes a first profile (41), two second profiles (42), four third profiles (43), four fixed legs (44) with bases, and several fixed legs (45) without bases. The first profile (41) and the two second profiles (42) are symmetrically connected to form a cross-shaped frame. The third profiles (43) are installed at the ends of the cross-shaped frame. The third profiles (43) are then assembled with the fixed legs (44) with bases. The fixed legs (45) without bases are installed at intervals below the cross-shaped frame for support and fixation.

5. The integrated device for space film storage and deployment testing according to claim 4, characterized in that: The pulley block mechanism (3) includes a connecting rod (31), a fixed pulley (32), a rope (33), a movable pulley (34), and a weight (35). The connecting rod (31) is mounted on a fixed bracket (44) with a base. The fixed pulley (32) is mounted at the center of the connecting rod (31). The movable pulley (34) is connected to the fixed pulley (32) through the rope (33). The weight (35) is connected to the movable pulley (34). The other side of the rope is connected to the mast connector (23).

6. The integrated device for space film storage and deployment testing according to claim 5, characterized in that: In the on-orbit state, the energy stored in the elastic mast drives its deployment. To facilitate testing, the rotation of the mast is constrained, and the movement is changed to rotation of the central axis: applying a constraint at the deployed end of the elastic mast causes the stored energy to drive the central axis to rotate, thus achieving a straight extension and deployment of the mast. However, since the sail of the sail module is connected to the mast, constraining it at the mast would cause the sail to come into contact with the constraint device, resulting in sail damage. Therefore, the following constraint method is adopted: applying a traction force at the end of the elastic mast to prevent the elastic mast from being deployed, the stored energy of the elastic mast then drives the central axis to rotate, thus achieving a straight extension and deployment of the mast.

7. The integrated device for space film storage and deployment testing according to claim 6, characterized in that: During the folding process of flexible films, the creases are caused by the contact force along the central axis. The thickness of the layer to which the contact force is applied is defined as the crease thickness. ; For the encapsulated membrane, assuming the contact area between the membrane and the central axis is small enough, the contact force is considered as a concentrated force: ， ， in, As an intermediate variable, For Young's modulus, For film thickness, For integration variables; When assuming the membrane is a one-dimensional enclosure, considering the equilibrium of the small elements enclosing the membrane, the contact force is: ， in, For tensile force, The radius of the center hub, Calculate the crease layer thickness based on the crease interval length. : ， The thickness of the flexible film after folding is calculated as follows: According to the formula for calculating the thickness of paper rolls: ， In the formula This refers to the axial storage area after the film is stored. The outer radius after storage, The radius of the central axis, This refers to the length of the flexible film after folding. Set the number of rotations for storage to [number]. : 。

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