A microgravity simulation device for a reel-type flexible solar wing

Abstract

The application discloses a micro-gravity simulation device for a reel type flexible solar wing, which comprises a hanging platform, guide rails, a gravity unloading assembly, a first supporting table and a second supporting table; two guide rails parallel to each other are arranged below the hanging platform along the solar wing unfolding direction, the gravity unloading assembly is connected between the guide rails, the first supporting table is used for solar wing installation, and the second supporting table is used for solar wing unfolding; the second supporting table has a downward slope, and the weight of the solar wing gradually decreases during the unfolding process; the gravity unloading assembly and the solar wing are connected through a pulley and a rope linkage, and during the solar wing unfolding process, the rope rotates in the opposite direction of the solar wing unfolding, and the weight of the rotating rope is equivalent to the weight of the unfolded part of the solar wing, so that zero-gravity simulation of the solar wing unfolding is realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of space experiment, in particular to a microgravity simulation device for a reel type flexible solar wing. BACKGROUND

[0002] The design of the reel type flexible solar wing allows it to be rolled up and unfolded like a carpet, and it has the advantages of efficient folding and unfolding, light weight, and efficient energy conversion. The reel type solar wing has a larger folding and unfolding arm, which means that it can occupy a smaller space in the stowed state, facilitating storage and transportation. At the same time, due to the flexible design of its substrate, it is lighter than traditional rigid or semi-rigid solar wings, reducing the overall weight of the spacecraft and reducing launch costs. The reel type solar wing uses high-efficiency solar cell technology to efficiently convert solar energy into electrical energy. Based on the above advantages, the reel type flexible solar wing has become an important energy supply solution in the field of space travel, but its reliability in orbit needs to be simulated on the ground to ensure its normal operation in space. The reel type solar wing has two characteristics: it is rolled up and unfolded like a carpet, and it is unfolded on a slope. The weight of the solar wing is always decreasing during the unfolding process, which makes it difficult to simulate its microgravity. Traditional suspension or air floating methods cannot be used, and traditional microgravity unloading devices are only suitable for situations where the weight remains unchanged during the movement of the solar wing. SUMMARY

[0003] The technical problem solved by the present application is to overcome the shortcomings of the prior art and more realistically simulate the on-orbit operation of the reel type solar wing, providing real and reliable test data for the design, testing and evaluation of flexible solar wings. The present application provides a microgravity simulation device for a reel type flexible solar wing, which realizes zero gravity simulation of solar wing unfolding.

[0004] The technical solution of the present application is a microgravity simulation device for a reel type flexible solar wing, comprising a hanging platform, a guide rail, a gravity unloading assembly, a first support table and a second support table.

[0005] Two guide rails parallel to each other are installed below the hanging platform along the solar wing unfolding direction, and the gravity unloading assembly is connected between the guide rails. The first support table is used for solar wing installation, and the second support table is used for solar wing unfolding. The second support table has a downward slope, and the weight of the solar wing gradually decreases during the unfolding process. The gravity unloading assembly and the solar wing are linked through pulleys and ropes. During the unfolding process of the solar wing, the rope rotates in the opposite direction of the solar wing unfolding, and the weight of the rotating rope is equivalent to the weight of the unfolded part of the solar wing, realizing zero gravity simulation of solar wing unfolding.

[0006] Further, the gravity unloading assembly comprises a connecting adjusting assembly, a horizontal shaft, a pulley, a rope and counterweights; the horizontal shaft is installed below the two guide rails through the connecting adjusting assembly, the installation direction is perpendicular to the guide rails and parallel to the reel of the solar wing, one pulley is connected to each end of the horizontal shaft, one pulley is also installed at each end of the reel of the solar wing, the rope is wound around the horizontal shaft pulleys at the same end, one end of the rope is connected to a counterweight and the other end is connected to the reel pulley; the total weight of the two counterweights is equal to the total weight of the solar wing.

[0007] Further, the connecting adjusting assembly comprises a trolley, a beam body and adjusting pieces; the beam body is connected below the two guide rails through the trolley, the beam body is connected to the horizontal shaft below through a plurality of adjusting pieces, and each adjusting piece is used for adjusting the parallelism between the horizontal shaft and the reel of the solar wing.

[0008] Further, the adjusting piece adopts an adjusting screw, which is symmetrically distributed around the center of the horizontal shaft, and the parallelism between the horizontal shaft and the reel of the solar wing is adjusted by adjusting the length of the adjusting screw.

[0009] Further, a bearing is arranged between the pulley outer shaft and the pulley core shaft of the pulley, and the rope moves to drive the pulley outer shaft to rotate.

[0010] Further, the hanging platform is built by a plurality of cube units composed of truss rods and ball heads, and the size of the hanging platform is greater than the unfolding size envelope of the solar wing.

[0011] Further, the hanging platform and the guide rail are connected through a plurality of C-shaped cross beams, and the length of the C-shaped cross beam is consistent with the length of the reel of the solar wing.

[0012] Further, the adjacent cube units of the hanging platform along the unfolding direction of the solar wing are each provided with a C-shaped cross beam.

[0013] Further, the height of the second support table is lower than that of the first support table, and one or more pipe bodies are laid on the upper inclined surface of the second support table for supporting the solar wing to unfold.

[0014] Further, the slope range of the second support table is 0°< slope < 90°.

[0015] Compared with the prior art, the advantages of the present application are that:

[0016] (1) The micro-gravity simulation device for the reel type flexible solar wing is proposed, and the implementation manner is that one pulley is respectively installed at each end of the reel of the flexible solar wing, when the reel is unfolded, the weight of the solar wing is gradually reduced, the rope rotates to the other side, the reduced weight of the solar wing is equal to the weight of the rope rotating, and the solar wing can also be unfolded on a 15° slope, so that the zero-gravity simulation of the weight of the reel type flexible solar wing being always reduced during the unfolding process is realized.

[0017] (2) the present application adds bearing between the outer shaft of the pulley and the pulley core shaft, when the rope rotates on the pulley, the friction between the pulley core shaft and the outer shaft of the pulley is reduced, so that the rope moves downward, drives the outer shaft of the pulley to rotate, avoids the relative rotation between the rope and the pulley, thereby generating friction. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is the overall schematic diagram of the simulation device of the present application;

[0019] Figure 2 It is the structural schematic diagram of the gravity unloading assembly of the present application;

[0020] Figure 3 It is the principle diagram of the gravity unloading of the present application. DETAILED DESCRIPTION

[0021] In order to better understand the technical scheme of the present application, the specific embodiment of the present application will be specifically described below in combination with the drawings.

[0022] The microgravity simulation device of the present application is used for the 15° expansion of the reel type flexible solar wing, and the present application includes but is not limited to the 15° expansion of the solar wing, and can be applied to the solar wing expanded between 0° and 90°.

[0023] As shown in Figure 1 , the simulation device includes a hanging platform 1, a C-shaped beam 2, a guide rail 3, a gravity unloading assembly 4, a support platform 5, a 15° support table 6, and a reel type flexible solar wing 7.

[0024] As shown in Figure 2 , the gravity unloading assembly 4 includes a trolley 2-1, an I-shaped beam 2-2, an adjusting screw 2-3, a cross shaft 2-4, a pulley 2-5, a rope 2-6, and a counterweight 2-7.

[0025] The hanging platform 1 adopts a 500mm*500mm*500mm unit composed of a truss rod with a diameter of 30mm and a ball head with a diameter of 50mm, and is built into a hanging platform with a length of 7.5m*5.5m*height of 5m, the expansion of the solar wing is completed under the hanging platform, the size of the hanging platform is larger than the expansion size envelope of the solar wing, and the hanging platform is composed of several truss units.

[0026] The C-shaped beam 2 is threadedly connected with the ball head of the hanging platform 1, is used for connecting the guide rail 3, the length of the C-shaped beam 2 is consistent with the length of the 7-flexible solar wing reel, the adjacent units of the hanging platform 1 are all installed with the C-shaped beam 2, and the main function of the C-shaped beam 2 is to connect the guide rail 3 and the hanging platform 1.

[0027] The guide rail 3 is installed on the suspended platform 1 via the C-shaped crossbeam 2. The guide rail 3 is made of stainless steel and has a diameter of 30mm. The main function of the guide rail 3 is to connect the gravity unloading component. It is the suspension track for the roll-type flexible solar panel 7 to unfold forward. Therefore, stainless steel is used to ensure that the guide rail 3 is rust-proof and corrosion-proof, and the smooth surface reduces friction. There are two guide rails 3, which are connected to the C-shaped crossbeam 2 respectively.

[0028] Support platform 5 is the installation platform for the roll-up flexible solar panel 7. It is constructed using profiles and its height and width are adjustable.

[0029] The 15° support platform 6 is a platform that allows the roll-up flexible solar panel 7 to unfold at 15°. It is composed of truss units with three aluminum tubes laid on top to support the roll-up flexible solar panel 7. The height of the support platform is lower than that of the support platform to avoid interference when the roll-up flexible solar panel 7 unfolds. Both platforms have simple, stable and reliable designs and are easy to move.

[0030] The gravity unloading assembly 4 connects to the reel-type flexible solar array. This assembly consists of a trolley 2-1, an I-beam 2-2, adjusting screws 2-3, a horizontal shaft 2-4, pulleys 2-5, ropes 2-6, and counterweights 2-7. It is the core component simulating the zero-gravity deployment of the reel-type flexible solar array 7. The gravity unloading assembly 4 is connected to the guide rail 3 via the trolley 2-1. The trolley 2-1 is connected to the I-beam 2-2 below. The horizontal shaft 2-4 is connected to the I-beam 2-2 below the I-beam 2-2 via several adjusting screws 2-3. The function of the adjusting screws 2-3 is to adjust the parallelism between the horizontal shaft 2-4 and the reel of the reel-type flexible solar array 7. A pulley 2-5 is connected to each end of shaft 2-4. Rope 2-6 passes over pulley 2-5. One end of rope 2-6 is connected to counterweight 2-7. A pulley 2-5 is also installed at each end of the flexible solar wing reel. The other end of rope 2-6 is connected to pulley 2-5 at the end of the reel of the reel-type flexible solar wing 7. As the solar blanket of the reel-type flexible solar wing 7 is unfolded forward, its weight continuously decreases. Rope 2-6 will rotate to the other side, and the length of the two sides of the rope changes. The difference in length is the part of the rope that is rotating. Its weight is equivalent to the decrease in weight of the solar blanket.

[0031] like Figure 3 As shown, let the total weight of the solar array be m. 太阳翼 =m 太阳毯 +m 卷轴 Assume the total weight of the rope is divided into three parts: m 转动的绳索质量左侧 m 转动的绳索质量右侧 m 固定的绳索质量 m 固定的绳索质量 Neglecting the mass, the mass of the counterweight is: m 配重块 According to the principle of balance pulleys:

[0032] The initial force balance equation is:

[0033] m 配重块 +m 转动的绳索质量左侧 =m 太阳毯 +m 卷轴 +m 转动的绳索质量右侧

[0034] The final state force balance equation is:

[0035] m 配重块 =m 卷轴 +m 转动的绳索质量

[0036] Then:

[0037] m 转动的绳索质量 =m 太阳毯

[0038] m 配重块 =m 卷轴 +m 太阳毯

[0039] According to the above formula, the weight of the counterweight is required to be equal to the total weight of the solar wing, the weight of the solar blanket is reduced during the unfolding process, and the rotating rope mass is equivalent to the weight of the solar blanket. In the final state, the weight of the solar blanket disappears completely, at this time, one side of the pulley 2-5 is the mass of the counterweight 2-7, and the other side is the mass of the rotating rope and the mass of the reel of the flexible solar wing 7, because the weight of the counterweight 2-7 is equivalent to the mass of the rotating rope and the mass of the reel of the flexible solar wing 7, the balance of the center of mass can be maintained, and the unloading is realized.

[0040] The rope selected by the application is equivalent in weight to the weight of the unfolded part of the solar wing, so it is necessary to select a suitable rope, and the thickness and density of the rope need to be strictly controlled. The diameter of the rope is not allowed to exceed the gap between the pulley tracks, and the rope cannot have elastic tension to avoid affecting the unloading efficiency.

[0041] It can be understood that the present application is described by way of examples, and those skilled in the art know that various changes or equivalent replacements can be made to these features and examples without departing from the spirit and scope of the present application. In addition, under the guidance of the present application, these features and examples can be modified to adapt to specific conditions without departing from the spirit and scope of the present application. Therefore, the present application is not limited by the specific examples disclosed herein, and the embodiments falling within the scope of the claims of the present application are within the scope of protection of the present application.

[0042] The contents not described in detail in the specification of the present application are known to those skilled in the art.

Claims

1. A microgravity simulation device for a reelable flexible solar wing, characterized by: The hanging platform, the guide rail, the gravity unloading assembly, the first support table and the second support table are included. Two guide rails parallel to each other are installed below the hanging platform along the solar wing unfolding direction, the gravity unloading assembly is connected between the guide rails, the first support table is used for solar wing installation, the second support table is used for solar wing unfolding, the second support table has a downward slope, the weight of the solar wing gradually decreases during unfolding, the gravity unloading assembly and the solar wing are connected through a pulley and a rope, during solar wing unfolding, the rope rotates in the opposite direction of solar wing unfolding, the weight of the rotating rope is equivalent to the weight of the unfolded part of the solar wing, realizing zero gravity simulation of solar wing unfolding.

2. The microgravity simulation device for a reel-type flexible solar wing according to claim 1, characterized in that: The gravity unloading assembly includes a connection adjustment assembly, a horizontal shaft, a pulley, a rope and a counterweight; the horizontal shaft is installed below the two guide rails through the connection adjustment assembly, the installation direction is perpendicular to the guide rail and parallel to the reel of the solar wing, one pulley is connected to each end of the horizontal shaft, one pulley is also installed at each end of the reel of the solar wing, the rope passes through the horizontal shaft pulley at the same end of the two pulleys, one end is connected to the counterweight and the other end is connected to the reel pulley; the weight of the two counterweights is equal to the total weight of the solar wing.

3. The microgravity simulation device for a reel-type flexible solar wing according to claim 2, characterized in that: The connection adjustment assembly includes a trolley, a beam body and an adjustment piece; the beam body is connected below the two guide rails through the trolley, the beam body is connected to the horizontal shaft below through multiple adjustment pieces, and each adjustment piece is used for parallelism adjustment between the horizontal shaft and the reel of the solar wing.

4. The microgravity simulation device for a reel-type flexible solar wing according to claim 3, characterized in that: The adjustment piece adopts an adjustment screw, which is symmetrically distributed around the center of the horizontal shaft, and the parallelism between the horizontal shaft and the reel of the solar wing is adjusted by adjusting the length of the adjustment screw.

5. The microgravity simulation device for a reel-type flexible solar wing according to claim 2, characterized by: A bearing is arranged between the pulley outer shaft and the pulley core shaft of the pulley, and the rope moves to drive the pulley outer shaft to rotate.

6. The microgravity simulation device for a reel-based flexible solar wing of claim 1, wherein: The hanging platform is built by a plurality of cube units composed of truss rods and ball heads, and the size of the hanging platform is larger than the unfolding size envelope of the solar wing.

7. The microgravity simulation device for a reel-type flexible solar wing according to claim 6, characterized in that: The hanging platform and the guide rail are connected through multiple C-shaped cross beams, and the length of the C-shaped cross beam is consistent with the length of the reel of the solar wing.

8. The microgravity simulation device for a reel-type flexible solar wing according to claim 7, characterized in that: Adjacent cube units of the hanging platform along the solar wing unfolding direction are each provided with a C-shaped cross beam.

9. The microgravity simulation device for a reel-based flexible solar wing of claim 1, wherein: The second support table is lower than the first support table, and one or more pipe bodies are laid on the top of the second support table to support the solar wing unfolding.

10. The microgravity simulation device for a reel-type flexible solar wing according to any one of claims 1 to 9, characterized in that: The slope range of the second support table is 0°< slope < 90°.

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