Multi-working-condition multi-attitude solar wing ground follow-up type two-dimensional gravity compensation device for lunar probe

Abstract

The invention provides a multi-working-condition multi-attitude solar wing ground follow-up type two-dimensional gravity compensation device for a lunar probe. The multi-working-condition multi-attitude solar wing ground follow-up type two-dimensional gravity compensation device comprises a fixing assembly, a pulley assembly, a pulley assembly, a weight assembly and a steel wire rope. The fixing assembly fixes one end of the steel wire rope. The upper end of the pulley assembly is matched with the cylindrical guide rail of the unfolding frame, and the lower end of the pulley assembly is fixedly connected with the pulley assembly. The pulley assembly comprises a fixed pulley assembly and a movable pulley assembly; the fixed pulley assembly is fixedly connected with the pulley assembly, the solar wing is hoisted below the movable pulley assembly to implement gravity unloading, and the fixed pulley assembly and the movable pulley assembly are connected through a steel wire rope to meet the vertical movement of the movable pulley assembly and the solar wing relative to the fixed pulley assembly; the steel wire rope is led out from the fixed assembly and bypasses the fixed pulley assembly and the movable pulley assembly, the tail end is connected with a weight in the weight assembly, and the gravity compensation amount of the solar wing is adjusted through the weight.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of gravity compensation device design, and particularly relates to a multi-working-condition and multi-pose solar wing ground follow-up type two-dimensional gravity compensation device for a lunar probe. BACKGROUND

[0002] Zero gravity, also known as weightlessness or reduced gravity, is one of the most important features of the space environment, and 1 / 6 gravity is an important feature of the lunar environment. Before the in-orbit flight of a lunar probe, in order to ensure the high precision and reliability of the system, the dynamics test of each subsystem of the space mechanism of the lunar probe must be carried out on the ground. However, the gravity environment on the ground will result in that the performance characteristics of the mechanism cannot be obtained through conventional test methods. Therefore, the ground test of the space deployment mechanism needs to accurately simulate the zero gravity or 1 / 6 gravity environment in which the mechanism is located.

[0003] The deployment trajectory of the multi-working-condition and multi-pose solar wing of the lunar probe is complex. The solar wing of the lunar probe needs to complete the deployment and folding actions during the lunar transfer period and the lunar surface period, and the actions and gravity environment during the two deployment and folding processes are quite different. Therefore, the ground deployment test is divided into the following three parts and is introduced respectively.

[0004] During the lunar transfer period, the inner plate and the outer plate of the solar wing are deployed along the +Z direction of the probe, and during the lunar surface working period, the inner plate, the outer plate and the connecting frame of the solar wing are deployed along the +X direction of the probe. According to the state that the +X direction of the probe is perpendicular to the ground during the ground test of the probe, the deployment of the solar wing along the +Z direction of the probe is defined as horizontal deployment and folding test, as shown in Figure 1 .

[0005] The deployment of the solar wing along the +X direction of the probe from folding to deployment is defined as vertical deployment test, as shown in Figure 2 .

[0006] The conversion of the solar wing along the +X direction of the probe from the plume avoidance state to the deployment state is defined as plume avoidance test, as shown in Figure 3 .

[0007] Due to the deployment requirements of the multi-working-condition solar wing, a new type of two-dimensional gravity compensation device needs to be designed on the basis of the deployment frame structure to unload the gravity of the solar wing, so as to eliminate the assembly stress influence caused by the gravity. At the same time, due to the requirement of 1 / 6 gravity, the gravity compensation value of the device needs to be accurately adjusted. Since there is no control measure for the low-gravity assembly of the multi-working-condition solar wing, the debugging process often appears overshoot, repetition and other phenomena, which seriously reduces the assembly efficiency and prolongs the product development cycle. The implementation of the multi-working-condition and multi-pose solar wing ground follow-up type two-dimensional gravity compensation device is of great significance to ensure the high efficiency of the assembly of the solar wing. SUMMARY

[0008] In order to overcome the deficiencies in the prior art, the inventors have made intensive research and provided a multi-working-condition and multi-posture solar wing ground follow-up type two-dimensional gravity compensation device for a lunar explorer, which solves the problems of low efficiency and poor gravity compensation precision in solar wing ground deployment test adjustment.

[0009] The technical scheme provided by the present application is as follows: A multi-working-condition and multi-posture solar wing ground follow-up type two-dimensional gravity compensation device for a lunar explorer, comprising a fixing assembly, a trolley assembly, a pulley assembly, a weight assembly and a steel wire rope; The fixing assembly is installed at a fixed position of a deployment frame and fixes one end of the steel wire rope; The upper end of the trolley assembly is matched with a cylindrical guide rail of the deployment frame, and the lower end is fixedly connected with the pulley assembly, so that the pulley assembly can be driven to move linearly along the cylindrical guide rail during solar wing deployment and retraction; The pulley assembly comprises a fixed pulley assembly and a movable pulley assembly; the fixed pulley assembly is fixedly connected with the trolley assembly, the movable pulley assembly is used for hoisting the solar wing below, gravity unloading is implemented, the fixed pulley assembly and the movable pulley assembly are connected through the steel wire rope, and the movable pulley assembly and the solar wing can move up and down relative to the fixed pulley assembly; The weight assembly is installed at a fixed position of the deployment frame, the steel wire rope is led out from the fixing assembly, passes through the fixed pulley assembly and the movable pulley assembly, and is connected with the weights in the weight assembly at the end, so that the gravity compensation amount of the solar wing is adjusted through the weight of the weights.

[0010] The multi-working-condition and multi-posture solar wing ground follow-up type two-dimensional gravity compensation device for a lunar explorer provided by the present application has the following beneficial effects: (1) The multi-working-condition and multi-posture solar wing ground follow-up type two-dimensional gravity compensation device for a lunar explorer provided by the present application cooperates with the pulley assembly and the trolley assembly, solves the problem of two-dimensional motion gravity compensation during the multi-working-condition and multi-posture solar wing ground deployment test of the lunar explorer, has a clever structure, and improves the reliability and convenience of the solar wing ground deployment test.

[0011] (2) The multi-working-condition and multi-posture solar wing ground follow-up type two-dimensional gravity compensation device for a lunar explorer provided by the present application adjusts the up-down and left-right height through the waist hole of the fixing assembly, so as to ensure that the steel wire rope does not introduce the influence of side wall friction on the counterweight value during use. The steel wire rope is led out from the fastening assembly, the height of the fixing assembly, the pulley assembly and the weight assembly is adjusted to be adaptive, and the steel wire rope is always substantially parallel or perpendicular to the ground.

[0012] (3) The present invention provides a two-dimensional gravity compensation device for a multi-condition, multi-attitude solar array on a lunar probe, which is ground-based and follows the motion of the trolley assembly to simulate horizontal movement, and the device, the fixing device, the pulley assembly, and the weight assembly to simulate vertical movement. This device can meet the gravity compensation requirements of three ground deployment tests in one device. By using the weight assembly, the need for precise adjustment of gravity compensation value is met to the maximum extent. The device includes modules such as a fixing device, a trolley assembly, a pulley assembly, a weight assembly, and a steel wire rope, which is of great significance for improving the assembly performance of space deployable mechanisms. Attached Figure Description

[0013] Figure 1 Schematic diagram of solar array deployment and retraction in the Z direction Figure 2 A schematic diagram of the solar array's deployment and retraction in the X direction; Figure 3 A schematic diagram of the expansion and contraction of solar wing feathers; Figure 4 This is a schematic diagram of the gravity compensation device of the present invention; Figure 5 A schematic diagram of the trolley assembly and pulley assembly; Figure 6 A schematic diagram of the trolley assembly and pulley assembly; Figure 7 This is a structural diagram of the trolley assembly and pulley assembly. Detailed Implementation

[0014] The features and advantages of the present invention will become clearer and more apparent from the following detailed description.

[0015] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments.

[0016] The purpose of this invention is to overcome the problems of low assembly and adjustment efficiency and poor gravity compensation accuracy in ground deployment tests of solar arrays. It proposes a device that uses a trolley assembly to simulate horizontal movement and a fixing device, pulley assembly, and weight assembly to simulate vertical movement. This device can meet the gravity compensation requirements of three ground deployment tests with one set of equipment. By using the weight assembly, the need for precise adjustment of gravity compensation values ​​can be met to the maximum extent.

[0017] This invention provides a ground-based, two-dimensional gravity compensation device for multi-condition, multi-attitude solar arrays on lunar probes, such as... Figure 4 As shown, it includes five parts: a fixing component 1, a trolley component 2, a pulley component 3, a weight component 4, and a steel wire rope 5.

[0018] likeFigure 4 As shown, the fixing component 1 is installed at a fixed position on the unfolding frame to fix one end of the steel wire rope 5. The fixing component 1 includes a triangular support and a lifting eye screw. The triangular support is welded from three angle irons and its size is adapted to the dimensions of the unfolding frame. A slotted hole is drilled at the front and back of the horizontal face of the triangular support to allow for left-right adjustment on the unfolding frame. A slotted hole is drilled at the connection point between the vertical face of the triangular support and the lifting eye screw to allow for up-down adjustment of the lifting eye screw. One end of the lifting eye screw is fixed to the triangular support, and the other end is used to fix the steel wire rope.

[0019] like Figures 5-7 As shown, the trolley assembly 2 cooperates with the cylindrical guide rail of the unfolding frame, allowing it to move linearly along the cylindrical guide rail. Furthermore, the trolley assembly 2 provides an interface for mounting pulley assemblies. The trolley assembly 2 includes a trolley seat 21, bearing fixing screws 22, a 625 deep groove ball bearing 23, a pressure block, a fixing bushing 24, a guide post 25, and an adapter plate 26. The trolley seat 21 has a "Y"-shaped structure. At the upper two forks of the "Y"-shaped structure, each of the four Φ5 through holes I is opened, and the bearing fixing screws 22 are used to fix the 625 deep groove ball bearing 23. A Φ26 through hole II is opened in the middle of the lower part of the trolley seat 21, and the Φ26 through hole II is used to connect the fixing bushing 24. The fixed bushing 24 has a three-section structure: a thick Φ26 cylinder in the middle and symmetrical thin Φ16 cylinders at both ends. The thin Φ16 cylinders are milled flat on both the top and bottom, and each milled surface has a Φ6.5 through hole III. The two Φ6.5 through holes III are used to install two guide posts 25. The guide post 25 has a three-section structure: the middle Φ6.5 cylinder is used to fit the fixed bushing 24; the upper section is threaded and is fixed with a pressure block and nut; the lower section is also threaded and is fixed to the adapter plate 26. The adapter plate 26 has several threaded holes, providing mounting interfaces for the two guide posts 25 and mounting interfaces for the fixed pulley bracket 311 in the pulley assembly 3. The two sets of trolley assemblies 2 are mounted one after the other on a pulley assembly 3.

[0020] like Figures 5-7As shown, the pulley assembly 3 includes a fixed pulley assembly 31 and a movable pulley assembly 32, which are connected by steel wire ropes 5 to allow the movable pulley assembly 32 to move up and down relative to the fixed pulley assembly 31. The fixed pulley assembly 31 includes a fixed pulley bracket 311, two fixed pulleys 312, two pulley shafts, two bushings, and four anti-derailment shafts I 313. The fixed pulley bracket 311 has an inverted triangular structure when viewed from the front and a "π"-shaped structure when viewed from the side. Several Φ6.5 through holes are opened on the flange surface above the fixed pulley bracket 311 for connecting to the adapter plates 26 of the two sets of trolley assemblies 2. Φ15.3 through holes are opened on the lower left and lower right of the fixed pulley bracket 311, and the distance between the two through holes is adapted to the size of the movable pulley to ensure that the steel wire ropes on both sides of the movable pulley are parallel. The two through holes fix the two fixed pulleys 312 through the pulley shafts and bushings. Four Φ2 anti-detachment shaft holes are drilled at the position where the fixed pulley is installed on the fixed pulley bracket 311. Anti-detachment shaft I 313 is installed here to prevent the wire rope 5 from coming off the fixed pulley 312.

[0021] The movable pulley assembly 32 includes a movable pulley bracket 321, a movable pulley 322, a pulley shaft, a bushing, an anti-detachment shaft II 323, and a lifting eye bolt 324. The movable pulley bracket 321 has a U-shaped structure in side view. A threaded hole is drilled at the bottom of the movable pulley bracket 321, and a lifting eye bolt 324 is installed in the threaded hole. The lifting eye bolt is used to lift the solar panel product. A Φ15.3 through hole is drilled in the middle of the side of the movable pulley bracket 321. The movable pulley 322 is fixed by the pulley shaft and bushing. A Φ2 anti-detachment shaft hole is drilled at the location where the movable pulley is installed. The anti-detachment shaft II 323 is installed here to prevent the wire rope from slipping out of the movable pulley 322.

[0022] like Figure 4 As shown, the weight assembly 4 achieves precise adjustment of the gravity compensation value, mainly including a triangular support, a fixed pulley assembly II, and the weight. The structure of the triangular support is the same as that of the triangular support in the fixed assembly 1, and the structure of the fixed pulley assembly II is the same as that of the movable pulley assembly 32. During installation, the fixed pulley assembly II is connected to the vertical surface of the triangular support through the two threaded holes at the bottom. After connection, the wire rope 5 is led out from the eye bolt of the fixed assembly 1, and passes sequentially around the left pulley of the fixed pulley assembly, the movable pulley assembly, the right pulley of the fixed pulley assembly, and the movable pulley assembly of the weight assembly until the weight is connected.

[0023] When simulating a zero-gravity environment for the solar array, the weight of the weights is equal to the weight of the solar array; when simulating a 1 / 6 gravity environment for the solar array, the weight of the weights is 5 / 6 of the weight of the solar array. Of course, adjusting the weights can also achieve other gravity environment simulations.

[0024] The present invention has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and embodiments of the present invention without departing from the spirit and scope of the invention, and all such modifications and improvements fall within the scope of the present invention. The scope of protection of the present invention is defined by the appended claims.

[0025] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A multi-mission multi-attitude solar wing ground-following two-dimensional gravity compensation device for a lunar explorer, characterized in that, The fixed component (1), the pulley component (3), the weight component (4) and the steel wire rope (5); The fixed component (1) is installed at a fixed position of the deployment frame and fixes one end of the steel wire rope (5); The upper end of the trolley component (2) is matched with the cylindrical guide rail of the deployment frame, and the lower end is fixed with the pulley component (3), which can drive the pulley component (3) to move linearly along the cylindrical guide rail during the deployment and retraction of the solar wing. The pulley component (3) comprises a fixed pulley component (31) and a movable pulley component (32); the fixed pulley component (31) is fixed with the trolley component (2), the movable pulley component (32) is used for hoisting the solar wing, and the gravity unloading is implemented; the fixed pulley component (31) and the movable pulley component (32) are connected through the steel wire rope (5), and the relative up-down movement of the movable pulley component (32) and the solar wing relative to the fixed pulley component (31) is satisfied. The weight component (4) is installed at a fixed position of the deployment frame; the steel wire rope (5) is wound around the fixed pulley component (31) and the movable pulley component (32) after being led out from the fixed component (1), and the tail end is connected with the weight in the weight component (4), so that the gravity compensation of the solar wing is adjusted through the weight of the weight.

2. The multi-mission multi-posture solar wing ground-following two-dimensional gravity compensation device for lunar explorer of claim 1, characterized in that, The fixed component (1) comprises a triangular support and a lifting ring screw; the triangular support is welded by three angle irons; a waist hole is punched in the front and back of the horizontal plane of the triangular support, so that the left-right direction adjustment of the triangular support on the deployment frame is implemented; a waist hole is punched at the connection position of the vertical plane of the triangular support and the lifting ring screw, so that the up-down direction adjustment of the lifting ring screw is implemented; one end of the lifting ring screw is fixed on the triangular support, and the other end is used for fixing the steel wire rope.

3. The multi-mission multi-posture solar wing ground-following two-dimensional gravity compensation device for lunar explorer of claim 1, characterized in that, The trolley component (2) comprises a trolley seat (21), a bearing fixing screw (22), a deep groove ball bearing (23), a pressing block, a fixed shaft sleeve (24), a guide column (25) and an adapter plate (26); The trolley seat (21) is a "Y" type structure; two through holes I are formed in the two branches of the upper part of the "Y" type structure; the four through holes I are matched with the bearing fixing screw (22) to fix the deep groove ball bearing (23); a through hole II is formed in the lower middle part of the trolley seat (21), and the through hole II is used for connecting the fixed shaft sleeve (24); the fixed shaft sleeve (24) is a three-section structure with a thick cylindrical middle section and two symmetrical thin cylindrical ends; the upper and lower edges of the thin cylindrical ends are milled flat, and a through hole III is formed in each of the milled flat surfaces; the two through holes III are used for installing two guide columns (25); the guide column (25) is a three-section structure; the middle section is a cylindrical section matched with the fixed shaft sleeve (24); the upper section is a threaded section matched with the pressing block and the nut; the lower section is also a threaded end fixed on the adapter plate (26); the adapter plate (26) is provided with a plurality of threaded holes, which provide the installation interfaces of the two guide columns (25) and the installation interface of the fixed pulley support (311) in the pulley component (3); two sets of trolley components (2) are installed in front of and behind one pulley component (3).

4. The multi-mission multi-posture solar wing ground-following two-dimensional gravity compensation device for lunar explorer of claim 1, wherein, The fixed pulley assembly (31) comprises a fixed pulley bracket (311), two fixed pulleys (312), two pulley shafts and two shaft sleeves; the fixed pulley bracket (311) is in the shape of an inverted triangle in front view and a "π" type structure in side view; a plurality of through holes are formed on the fixed pulley bracket (311) for connecting with the adapter plates (26) of the two sets of pulley assemblies (2); through holes are formed at the lower left and right of the fixed pulley bracket (311), respectively, and the distance between the two through holes is adapted to the size of the movable pulley to ensure that the steel wire ropes on both sides of the movable pulley are parallel, and the two through holes fix the two fixed pulleys (312) through the pulley shafts and the shaft sleeves.

5. The multi-mission multi-posture solar wing ground-following two-dimensional gravity compensation device for lunar explorer of claim 4, characterized in that, The fixed pulley assembly (31) further comprises a plurality of anti-coming-off shafts I (313) which are arranged at the positions where the fixed pulleys are installed on the fixed pulley bracket (311) to prevent the steel wire ropes (5) from coming off the fixed pulleys (312).

6. The multi-mission multi-posture solar wing ground-based follow-up two-dimensional gravity compensation device for lunar explorer of claim 1, wherein, The movable pulley assembly (32) comprises a movable pulley bracket (321), a movable pulley (322), a pulley shaft, a shaft sleeve and a lifting eye screw (324); the movable pulley bracket (321) is in the shape of a "U" type structure in side view, a threaded hole is formed at the bottom of the movable pulley bracket (321), the lifting eye screw (324) is installed on the threaded hole and used for lifting the solar wing; a through hole is formed at the middle position of the side edge of the movable pulley bracket (321) to fix the movable pulley (322) through the pulley shaft and the shaft sleeve.

7. The multi-mission multi-posture solar wing ground-based follow-up two-dimensional gravity compensation device for lunar explorer of claim 1, characterized in that, The movable pulley assembly (32) further comprises an anti-coming-off shaft II (323) which is arranged at the position where the movable pulley is installed on the movable pulley bracket (321) to prevent the steel wire ropes from coming off the movable pulley (322).

8. The multi-mission multi-posture solar wing ground-based follow-up two-dimensional gravity compensation device for lunar explorer of claim 1, characterized in that, The weight assembly (4) comprises a triangular support, a fixed pulley assembly II and weights; the triangular support has the same structure as the triangular support in the fixing assembly (1), and the fixed pulley assembly II has the same structure as the movable pulley assembly (32); during installation, the vertical surface of the triangular support is connected with the threaded hole at the bottom of the fixed pulley assembly II, after the connection, the steel wire rope (5) is led out from the lifting eye screw of the fixing assembly (1), and then sequentially passes through the left pulley of the fixed pulley assembly, the movable pulley assembly, the right pulley of the fixed pulley assembly, the movable pulley assembly of the weight assembly and finally connects with the weights.

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