Microgravity simulation device for reel type flexible solar wing

Abstract

The invention discloses a microgravity simulation device for a reel type flexible solar wing. The microgravity simulation device comprises a hanging platform, a guide rail, a gravity unloading assembly, a first supporting table and a second supporting table. Two parallel guide rails are installed below the hanging platform in the unfolding direction of the solar wing, a gravity unloading assembly is connected between the guide rails, the first supporting table is used for installing the solar wing, the second supporting table is used for unfolding the solar wing, the second supporting table has a downward slope, and the weight of the solar wing is gradually reduced in the unfolding process. The gravity unloading assembly and the solar wing are linked through a pulley and a rope, in the unfolding process of the solar wing, the rope rotates in the direction opposite to the unfolding direction of the solar wing, the weight of the rotating rope is equivalent to the weight of the unfolding part of the solar wing, and zero-gravity simulation of unfolding of the solar wing is achieved.

Description

Technical Field

[0001] The invention relates to the field of space experiments, in particular to a microgravity simulation device for a reel-type flexible solar wing. Background Art

[0002] The design of the roll-up flexible solar wing allows it to be rolled up and unfolded like a carpet. It has the advantages of efficient folding and unfolding, lightweight, and efficient energy conversion. The roll-up solar wing has a large folding arm, which means that it can occupy a smaller space in the folded state, which is convenient for storage and transportation. At the same time, due to the flexible design of its substrate, it is lighter than the traditional rigid or semi-rigid solar wing, which reduces the overall weight of the spacecraft and reduces the launch cost; the roll-up solar wing uses efficient solar cell technology, which can efficiently convert solar energy into electrical energy. Based on the above advantages, the roll-up flexible solar wing has become a very important energy supply solution in the aerospace field, but its reliability in orbit requires microgravity simulation on the ground to ensure its normal operation in space. The roll-up solar wing has two characteristics. One is that it rolls up and unfolds like a carpet, and the other is that the solar blanket is unfolded on a slope. The weight of the solar wing is constantly decreasing during the unfolding process, which brings difficulty to its microgravity simulation. The traditional suspension method or air flotation method cannot be used. The traditional microgravity unloading device is only applicable to the situation where the weight of the solar wing remains unchanged during the movement. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to more realistically simulate the on-orbit operation of a roll-up solar wing, to provide real and reliable test data for the design, testing and evaluation of flexible solar wings, and to provide a microgravity simulation device for a roll-up flexible solar wing to achieve zero-gravity simulation of the unfolding of the solar wing.

[0004] The technical solution of the present invention 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 platform and a second support platform;

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

[0006] Furthermore, the gravity unloading component includes a connecting and adjusting component, a transverse axis, a pulley, a rope and a counterweight; the transverse axis is installed under the two guide rails through the connecting and adjusting component, and the installation direction is perpendicular to the guide rails and parallel to the reel of the solar wing. A pulley is connected at each end of the transverse axis, and a pulley is also installed at each end of the reel of the solar wing. At the two pulleys at the same end, the rope passes around the transverse axis pulley, 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.

[0007] Furthermore, the connection and adjustment assembly includes a pulley, a beam body and an adjustment member; the beam body is connected to the bottom of the two guide rails through the pulley, and the bottom of the beam body is connected to the horizontal axis through multiple adjustment members, and each adjustment member is used to adjust the parallelism between the horizontal axis and the winding axis of the solar wing.

[0008] Furthermore, the adjusting member adopts an adjusting screw which is symmetrically distributed around the center of the horizontal axis. The parallelism between the horizontal axis and the winding axis of the solar wing can be adjusted by adjusting the length of the adjusting screw.

[0009] Furthermore, a bearing is provided between the pulley outer shaft and the pulley core shaft of the pulley, and when the rope moves, the pulley outer shaft is driven to rotate together.

[0010] Furthermore, the hanging platform is constructed by a number of cubic units consisting of truss rods and ball heads, and the size of the hanging platform is larger than the unfolded size envelope of the solar wing.

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

[0012] Furthermore, adjacent cube units of the hanging platform along the deployment direction of the solar wing are all installed with C-shaped beams.

[0013] Furthermore, the height of the second support platform is lower than that of the first support platform, and one or more tubes are laid obliquely on the top to support the unfolding of the solar wing.

[0014] Furthermore, the slope of the second support platform ranges from 0° to 90°.

[0015] The advantages of the present invention compared with the prior art are:

[0016] (1) The present invention proposes a microgravity simulation device for a reel-type flexible solar wing, which is implemented by installing a pulley at each end of the flexible solar wing reel. When the reel is unfolded, the weight of the solar wing gradually decreases, and the rope rotates to the other side. The reduced weight of the solar wing is equal to the weight of the rope rotation. At the same time, it can also adapt to a 15° slope unfolding, thereby realizing zero gravity simulation in which the weight of the reel-type flexible solar wing is constantly reduced during the unfolding process.

[0017] (2) In the design structure of the pulley of the present invention, a bearing is added between the pulley outer shaft and the pulley core shaft. When the rope rotates on the pulley, the friction between the pulley core shaft and the pulley outer shaft is reduced, so that when the rope moves downward, it drives the pulley outer shaft to rotate together, thereby avoiding relative rotation between the rope and the pulley, thereby generating friction. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0019] Figure 2 This is a schematic diagram of the structure of the gravity unloading assembly of the present invention;

[0020] Figure 3 This is a schematic diagram of the gravity unloading principle of the present invention. DETAILED DESCRIPTION

[0021] In order to better understand the technical solution of the present invention, the specific implementation mode of the present invention is described in detail below with reference to the accompanying drawings.

[0022] This embodiment takes a microgravity simulation device for a 15° unfolded roll-up flexible solar wing as an example. The present invention includes but is not limited to a 15° unfolded solar wing, and can be applied to a solar wing unfolded between 0° and 90°.

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

[0024] like Figure 2 As shown, the gravity unloading assembly 4 includes a pulley 2-1, an I-beam 2-2, an adjusting screw 2-3, a transverse axis 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 30mm diameter truss rod and a 50mm diameter ball head, which is then built into a 7.5m long×5.5m high hanging platform. The deployment of the solar wing is completed under the hanging platform. The size of the hanging platform is larger than the deployment size envelope of the solar wing. The hanging platform is composed of several truss units.

[0026] The C-shaped crossbeam 2 is connected to the ball head of the hanging platform 1 through threads and is used to connect the guide rail 3. The length of the C-shaped crossbeam 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 crossbeam 2. The main function of the C-shaped crossbeam 2 is to connect the guide rail 3 to the hanging platform 1.

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

[0028] The supporting platform 5 is a mounting platform for the reel-type flexible solar wing 7, which is constructed with profiles and has adjustable height and width.

[0029] The 15° support platform 6 is a platform for the roll-up flexible solar wing 7 to be unfolded 15°. It is composed of a truss unit with three aluminum tubes laid on it to support the roll-up flexible solar wing 7. The height is lower than the supporting platform to avoid interference when the roll-up flexible solar wing 7 is unfolded. The design structure of the two platforms is simple, stable and reliable, and easy to move.

[0030] The gravity unloading component 4 is connected to the reel flexible solar wing, which is composed of a pulley 2-1, an I-beam 2-2, an adjusting screw 2-3, a transverse axis 2-4, a pulley 2-5, a rope 2-6, and a counterweight 2-7. It is a core component that simulates the zero-gravity deployment of the reel-type flexible solar wing 7. The gravity unloading component 4 is connected to the guide rail 3 through the pulley 2-1, and the lower part of the pulley 2-1 is connected to the I-beam 2-2. The lower part of the I-beam 2-2 is connected to the transverse axis 2-4 through several adjusting screws 2-3. The function of the adjusting screw 2-3 is to adjust the parallelism of the transverse axis 2-4 and the reel of the reel-type flexible solar wing 7. A pulley 2-5 is connected to each end of the shaft 2-4, and a rope 2-6 is passed around the pulley 2-5. One end of the rope 2-6 is connected to the counterweight 2-7. A pulley 2-5 is also installed at each end of the flexible solar wing reel. The other end of the rope 2-6 is connected to the pulley 2-5 at the end of the reel-type flexible solar wing 7 reel. During the process of the solar blanket of the reel-type flexible solar wing 7 being rolled out forward, the weight is constantly decreasing, and the rope 2-6 will rotate to the other side. The length of both sides of the rope changes, and the difference in the rope is the rotating rope, and its weight is equivalent to the reduced weight of the solar blanket.

[0031] like Figure 3 As shown, the total weight of the solar wing is m 太阳翼 =m 太阳毯 +m 卷轴 , assuming 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 Ignoring, the mass of the counterweight is: m 配重块 , according to the principle of balance pulley:

[0032] The initial state 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] but:

[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, it is necessary to ensure that the weight of the counterweight block is equal to the total weight of the solar wing, and the weight of the solar blanket is constantly decreasing during the unfolding process, during which the force is kept balanced, and the mass of the rotating rope is equivalent to the weight of the solar blanket. In the final state, the weight of the solar blanket completely disappears. At this time, one side of the pulley 2-5 is the mass of the counterweight block 2-7, and the other side is the mass of the rotating rope and the mass of the reel-type flexible solar wing 7 reel. Because the weight of the counterweight block 2-7 is equivalent to the mass of the rotating rope and the mass of the reel-type flexible solar wing 7 reel, the balance of the center of mass can be maintained to achieve unloading.

[0040] The weight of the rope selected in the present invention is completely equivalent to the weight of the unfolded part of the solar wing. Therefore, a suitable rope needs to be selected, 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. At the same time, the rope cannot have elastic tension to avoid affecting the unloading efficiency.

[0041] It is to be understood that the present invention is described by way of embodiments, and it is known to those skilled in the art that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention. In addition, under the teachings of the present invention, these features and embodiments may be modified to adapt to specific circumstances without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed herein, and embodiments that can fall within the scope of the claims of this application all fall within the scope protected by the present invention.

[0042] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A microgravity simulation device for a reel-type flexible solar wing, characterized in that: It includes a hanging platform, a guide rail, a gravity unloading assembly, a first supporting platform and a second supporting platform; Two parallel guide rails are installed below the hanging platform along the deployment direction of the solar wing, and a gravity unloading assembly is connected between the guide rails. The first support platform is used for installing the solar wing, and the second support platform is used for deploying the solar wing. The second support platform has a downward slope, and the weight of the solar wing gradually decreases during the deployment process. The gravity unloading assembly and the solar wing are linked by pulleys and ropes. During the deployment of the solar wing, the rope rotates in the opposite direction of the solar wing deployment. The weight of the rotating rope is equivalent to the weight of the deployed part of the solar wing, realizing zero-gravity simulation of the deployment of the solar wing.

2. The microgravity simulation device for a roll-up flexible solar wing according to claim 1, characterized in that: The gravity unloading assembly includes a connecting and adjusting assembly, a transverse axis, a pulley, a rope and a counterweight; the transverse axis is installed under the two guide rails through the connecting and adjusting assembly, and the installation direction is perpendicular to the guide rails and parallel to the reel of the solar wing. A pulley is connected at each end of the transverse axis, and a pulley is also installed at each end of the reel of the solar wing. At the two pulleys at the same end, the rope passes around the transverse axis pulley, 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 roll-up flexible solar wing according to claim 2, characterized in that: The connection and adjustment assembly includes a pulley, a beam body and an adjustment member; the beam body is connected to the bottom of the two guide rails through the pulley, and the bottom of the beam body is connected to the horizontal axis through multiple adjustment members, and each adjustment member is used to adjust the parallelism between the horizontal axis and the winding axis of the solar wing.

4. The microgravity simulation device for a roll-up flexible solar wing according to claim 3, characterized in that: The adjusting member adopts an adjusting screw which is symmetrically distributed around the center of the horizontal axis. The parallelism between the horizontal axis and the winding axis of the solar wing can be adjusted by adjusting the length of the adjusting screw.

5. The microgravity simulation device for a roll-up flexible solar wing according to claim 2, characterized in that: A bearing is arranged between the pulley outer shaft and the pulley core shaft of the pulley. When the rope moves, the pulley outer shaft is driven to rotate together.

6. The microgravity simulation device for a roll-up flexible solar wing according to claim 1, characterized in that: The hanging platform is constructed by using a plurality of cubic units consisting of truss rods and ball heads, and the size of the hanging platform is larger than the unfolded size envelope of the solar wing.

7. The microgravity simulation device for a roll-up flexible solar wing according to claim 6, characterized in that: The hanging platform and the guide rails are connected by multiple C-shaped beams, and the length of the C-shaped beams is consistent with the length of the solar wing's reel.

8. The microgravity simulation device for a roll-up flexible solar wing according to claim 7, characterized in that: Adjacent cube units of the hanging platform along the deployment direction of the solar wing are all installed with C-shaped beams.

9. The microgravity simulation device for a roll-up flexible solar wing according to claim 1, characterized in that: The height of the second support platform is lower than that of the first support platform, and one or more tubes are laid obliquely on the top to support the unfolding of the solar wing.

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

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