A multi-section lifting mechanism for a solar wing and its assembly and use method

Abstract

The application provides a multi-section lifting mechanism of a solar wing and an assembling method and a using method thereof, and belongs to the field of solar wing lifting mechanisms. The application solves the problems of large space occupation and complex structure of the existing solar wing lifting mechanism. The lifting mechanism comprises lifting arm assemblies, a top assembly, a base, an unlocker and a rope. The two lifting arm assemblies are symmetrically arranged. The upper and lower ends of each lifting arm assembly are connected with the top assembly and the base respectively. The top assembly is connected with a solar wing driving mechanism. The solar wing driving mechanism is connected with the solar wing. The base is connected with a satellite body. The unlocker is connected with the base. When the lifting arm assembly is in a compressed state, the rope passes through the unlocker and is connected with the top assembly and the base at two ends respectively. The lifting arm assembly is in a straightened state after being lifted to a position. The application is mainly used for lifting the solar wing to a position far away from the satellite body.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of solar wing lifting mechanism, in particular to a multi-section lifting mechanism of solar wing and its assembling method and using method. BACKGROUND

[0002] In order to adapt to the increasing demand of satellite power, the design of solar wing is constantly improving the power supply capacity through various ways. At present, the use of foldable solar wing which can be oriented to the sun becomes the mainstream. This type of solar wing realizes the orientation to the sun through the solar wing driving mechanism, and increases the area of the sheet through multiple folds, so as to achieve the effect of folding in the launch state and high-efficiency power supply in the orbit. However, after the solar wing is unfolded in the orbit, due to its large area, it may cause the occlusion of the field of view of some equipment. The closer the distance between the solar wing and the satellite body, the greater the occlusion probability. At the same time, if the solar wing is too close to the satellite body, the radiation behind the sailboard after being illuminated by sunlight may cause the temperature of some equipment in the orbit to be too high. Therefore, it is necessary to lift the solar wing to a position far away from the satellite body through the lifting mechanism after entering the orbit.

[0003] The existing solar wing lifting mechanism generally includes axial lifting mechanism and three-dimensional lifting mechanism. The lifting arm of the axial lifting mechanism only has axial movement ability, so the lifting height is limited. If a high enough lifting effect is needed, the height of the mechanism before lifting is often high, which causes the satellite axial envelope size to be large. Or the lifting mechanism needs to be inserted into the satellite cabin before lifting, which affects the layout in the satellite cabin and reduces the utilization rate of the space in the cabin. The three-dimensional lifting mechanism realizes the effect of converting the lateral size into the axial height by changing the configuration of the lifting arm in the orbit. The commonly used three-dimensional lifting mechanism often has only single-section or double-section lifting arm. In order to achieve a high enough lifting effect, the size of the single-section or double-section lifting arm needs to be designed to be relatively long. Therefore, the lifting arm needs to be fixed on the surface of the cabin plate with a large area before lifting, and occupies a large layout space, which limits the satellite configuration and affects the layout of other equipment. At the same time, the driving force of the commonly used three-dimensional lifting mechanism is arranged at the connection between the lifting arm and the cabin plate or at the mutual connection of the lifting arms, and the force arm is short. In order to realize the lifting, a large driving force is needed, which causes the design of the driving mechanism to be complex, the weight of the driving mechanism to be heavy, and the structural strength requirement of the lifting arm to be high, which is one of the reasons affecting the multi-section design of the mechanism. SUMMARY

[0004] Therefore, the present application aims to provide a multi-section lifting mechanism of solar wing and its assembling method and using method, which is mainly used for lifting the solar wing to a position far away from the satellite body. The problem of large space occupation and complex structure of the existing solar wing lifting mechanism is solved.

[0005] In order to achieve the above object, the application adopts the following technical scheme: a multi-section lifting mechanism of a solar wing, comprising a lifting arm assembly, a top assembly, a base, an unlocker and a rope, the lifting arm assembly is two groups, the two groups of lifting arm assemblies are symmetrically arranged, the upper and lower ends of each group of lifting arm assemblies are connected with the top assembly and the base respectively, the top assembly is connected with a solar wing driving mechanism, the solar wing driving mechanism is connected with the solar wing, the base is connected with a satellite body, the unlocker is connected with the base, the rope passes through the unlocker when the lifting arm assembly is in a compressed state, and the two ends of the rope are connected with the top assembly and the base respectively, the lifting arm assembly is in a straightened state after being lifted into position, the lifting arm assembly comprises a first lifting arm, a second lifting arm and a lifting torsion spring, the first lifting arm and the second lifting arm are both multi-section, the multi-section first lifting arm and the second lifting arm are connected in sequence by hinging, the two ends of the lifting torsion spring are connected with two adjacent second lifting arms respectively, the top assembly comprises a solar wing mounting seat, a locking spring and a locking sleeve, the locking sleeve is sleeved on the solar wing mounting seat, the two ends of the locking spring are connected with the solar wing mounting seat and the locking sleeve respectively, the first lifting arm is connected with the lower part of the solar wing mounting seat by hinging, the locking spring is compressed when the lifting arm assembly is in the compressed state, the locking sleeve is axially perpendicular to the first lifting arm, the first lifting arm is below the locking sleeve, the locking spring is stretched when the lifting arm assembly is in the straightened state, the locking sleeve is axially parallel to the first lifting arm, and the locking sleeve is nested with the first lifting arm.

[0006] Furthermore, the surface of the first lifting arm is provided with a first storage groove, the surface of the second lifting arm is provided with a second storage groove, and the lifting torsion spring is embedded in the first storage groove and the second storage groove when the lifting arm assembly is in the compressed state and the straightened state.

[0007] Furthermore, the first lifting arm and the second lifting arm are both long rod structures, one end of the second lifting arm is provided with a limiting table, the front end of the limiting table and the end face of the second storage groove are provided with torsion spring fixing holes, and the torsion spring fixing holes are used for mounting the two ends of the lifting torsion spring.

[0008] Furthermore, the material of the lifting torsion spring is spring steel, the lifting torsion spring is in a straightened state in a natural state, two torsion spring structures are arranged on the lifting torsion spring, the two ends of the lifting torsion spring are straight torsion arms, and the straight torsion arms are inserted into the torsion spring fixing holes.

[0009] Furthermore, the first lifting arm and the second lifting arm are connected by a hinge, two first shaft connecting holes are formed in the hinge, first shaft fixing holes are formed on the two sides of the first lifting arm, second shaft fixing holes are formed on the two sides of the second lifting arm, the two first shaft connecting holes are respectively butted with the first shaft fixing holes and the second shaft fixing holes and pass through a shaft rivet.

[0010] Further, the solar wing mounting seat comprises a solar wing mounting surface, a third rotating shaft fixing hole and a locking support rod, the solar wing mounting surface is connected with the solar wing driving mechanism, the third rotating shaft fixing hole is connected with the first lifting arm, the locking support rod is sleeved with a locking sleeve outside, and the bottom of the solar wing mounting seat is provided with a rope hook used for connecting a rope.

[0011] Further, the base is provided with a second rotating shaft connecting hole, a base fixing hole and a rope fixing hole, the base is connected with the second lifting arm through the second rotating shaft connecting hole, the base is connected with the satellite body through the base fixing hole, and the rope is connected on the rope fixing hole.

[0012] Further, the unlocking device comprises a hot knife, a shell and a control line, the hot knife is arranged in the shell, the control line is connected with the hot knife, the shell is provided with a rope hole, the rope passes through the rope hole, and the rope corresponds to the position of the hot knife.

[0013] The application further provides an assembling method of the multi-section lifting mechanism of the solar wing.

[0014] Step 1: sequentially connecting the multi-section first lifting arm with the second lifting arm through hinging, connecting the two ends of the lifting torsional spring with the two adjacent second lifting arms respectively, and completing the installation of the lifting arm combination;

[0015] Step 2: sleeving the locking sleeve on the solar wing mounting seat, connecting the two ends of the locking spring with the solar wing mounting seat and the locking sleeve respectively, pushing the locking sleeve upward to compress the locking spring, exposing the lower part of the solar wing mounting seat, symmetrically and side by side approaching the two lifting arm combinations, hinging the first lifting arm with the lower part of the solar wing mounting seat, and hinging the lower ends of the two lifting arm combinations with the base;

[0016] Step 3: pushing the locking sleeve upward to compress the locking spring, exposing the lower part of the solar wing mounting seat, at this time, the lifting mechanism is in the unlocking state, pressing the lifting mechanism downward as a whole, the lifting torsional spring is deformed under stress, the first lifting arm and the second lifting arm rotate around the hinge shaft until they are attached, connecting one end of the rope on the base, then passing the rope through the unlocking device, connecting the other end of the rope on the top combination, completing the locking of the compression state of the lifting mechanism, and finally connecting the unlocking device with the base;

[0017] Step 4: connecting the base with the satellite body and connecting the top combination with the solar wing driving mechanism.

[0018] The application further provides a method for using the multi-section lifting mechanism of the solar wing, specifically comprising the following steps: disconnecting the rope through the unlocking device, unlocking and releasing the lifting mechanism, lifting the lifting arm combination under the driving of the lifting torsion spring, and locking the straight state of the lifting arm combination through the locking spring and the locking sleeve.

[0019] Compared with the prior art, the application has the following beneficial effects:

[0020] (1) The multi-section lifting mechanism of the solar wing occupies a smaller space in the compressed state, thereby avoiding the waste of the layout space of the cabin plate on which the mechanism is installed.

[0021] (2) The multi-section lifting mechanism of the solar wing has multi-section lifting arms, and the two groups of lifting arm combinations are mutually attached and completely straightened when the lifting is in place, thereby having a higher lifting height than the common solar wing lifting mechanism and more effectively avoiding the problem of shielding the field of view of the satellite equipment and the solar wing radiation equipment.

[0022] (3) The multi-section lifting mechanism of the solar wing adopts a single-point unlocking and no-rim driving mode, thereby reducing the occupation of power and electrical interface resources.

[0023] (4) The multi-section lifting mechanism of the solar wing drives the lifting through the lifting torsion spring connected to the lifting arms at intervals, the second lifting arms on both sides of the torsion spring are always parallel to each other during the entire lifting process, and the lifting consistency of the multi-section lifting arms is high.

[0024] (5) The force point of the lifting torsion spring of the multi-section lifting mechanism of the solar wing is located at the middle section of the lifting arm on the surface of the lifting arm, the force arm is long, and the lifting can be realized without designing a larger torsion force for the lifting torsion spring, thereby making the mechanism design simple, the weight light, and the strength requirement of the lifting arm low compared with the common lifting mechanism.

[0025] (6) In the compressed state, all the lifting arms are mutually attached and closely attached to the cabin plate, thereby having high rigidity and being beneficial to resisting the mechanical environment of the ascending stage of the carrier.

[0026] (7) After the lifting is completed, the multi-section lifting mechanism of the solar wing has multiple modes of top locking, side auxiliary locking and external skeleton type strengthening of the lifting torsion spring to guarantee the structural rigidity and strength.

[0027] (8) The multi-section lifting mechanism of the solar wing has simple design of each component part, small size of the parts and low precision requirement, thereby reducing the processing cost and shortening the processing period.

[0028] (9) The multi-section lifting mechanism of the solar wing can be repeatedly compressed and released, thereby reducing the cost of ground test.

[0029] (10) The multi-section lifting mechanism of the solar wing is independent of each other, and can be secondarily designed and selected according to the specific requirements of the satellite, thereby having high adaptability. BRIEF DESCRIPTION OF DRAWINGS

[0030] The accompanying drawings, which form a part of the present application, are used to provide further understanding of the present application, and serve as an explanation of the illustrative embodiments of the present application, and are not intended to limit the present application. In the drawings:

[0031] Figure 1 A structure schematic view of the multi-section lifting mechanism of the solar wing according to the present application;

[0032] Figure 2 A structure schematic view of the combined whole of the lifting arm according to the present application;

[0033] Figure 3 A structure schematic view of the combined local of the lifting arm according to the present application;

[0034] Figure 4 A structure schematic view of the first lifting arm according to the present application;

[0035] Figure 5 A structure schematic view of the second lifting arm according to the present application;

[0036] Figure 6 A structure schematic view of the lifting torsion spring according to the present application;

[0037] Figure 7 A structure schematic view of the hinge according to the present application;

[0038] Figure 8 A structure schematic view of the combined whole of the top according to the present application;

[0039] Figure 9 A structure schematic view of the combined section of the top according to the present application;

[0040] Figure 10 A structure schematic view of the base according to the present application;

[0041] Figure 11 A structure schematic view of the unlocking device according to the present application;

[0042] Figure 12 A structure schematic view of the assembly method of the multi-section lifting mechanism of the solar wing according to the present application Figure 1 ;

[0043] Figure 13Assembly method of multi-section lifting mechanism of solar wing Figure 2 ;

[0044] Figure 14 Assembly method of multi-section lifting mechanism of solar wing Figure 3 ;

[0045] Figure 15 Assembly method of multi-section lifting mechanism of solar wing Figure 4 ;

[0046] Figure 16 Assembly method of multi-section lifting mechanism of solar wing Figure 5 ;

[0047] Figure 17 Assembly method of multi-section lifting mechanism of solar wing Figure 6 ;

[0048] Figure 18 Assembly method of multi-section lifting mechanism of solar wing Figure 7 ;

[0049] Figure 19 Assembly method of multi-section lifting mechanism of solar wing Figure 8 ;

[0050] Figure 20 Lifting process diagram of using method of multi-section lifting mechanism of solar wing

[0051] Figure 21 Lifting-in-place diagram of using method of multi-section lifting mechanism of solar wing

[0052] Figure 22 Locking diagram of lifting-in-place of using method of multi-section lifting mechanism of solar wing

[0053] Explanation of reference numerals in the drawings

[0054] 1: lifting arm assembly, 2: top assembly, 3: base, 4: unlocker, 5: rope, 6: satellite body, 7: solar wing driving mechanism, 8: solar wing, 1-1: first lifting arm, 1-1-1: first rotating shaft fixing hole, 1-1-2: first storage groove, 1-2: second lifting arm, 1-2-1: second rotating shaft fixing hole, 1-2-2: second storage groove, 1-2-3: limiting table, 1-2-4: torsional spring fixing hole, 1-3: lifting torsional spring, 1-3-1: torsional spring structure, 1-3-2: straight torsional arm, 1-4: hinge, 1-4-1: first rotating shaft connecting hole, 1-5: rotating shaft rivet, 2-1: solar wing mounting seat, 2-1-1: solar wing mounting surface, 2-1-2: third rotating shaft fixing hole, 2-1-3: locking support rod, 2-2: locking spring, 2-3: locking sleeve, 2-4: rope hook, 3-1: second rotating shaft connecting hole, 3-2: base fixing hole, 3-3: rope fixing hole, 4-1: hot knife, 4-2: shell, 4-2-1: rope hole, 4-3: control line. DETAILED DESCRIPTION

[0055] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present application, not all the embodiments.

[0056] Reference is made to Figures 1-11This embodiment describes a multi-section lifting mechanism for a solar array, comprising a lifting arm assembly 1, a top assembly 2, a base 3, an unlocking device 4, and a rope 5. The lifting arm assemblies 1 are arranged in two sets symmetrically. The upper and lower ends of each lifting arm assembly 1 are connected to the top assembly 2 and the base 3, respectively. The top assembly 2 is connected to a solar array drive mechanism 7, which is connected to the solar array 8. The base 3 is connected to the satellite body 6, and the unlocking device 4 is connected to the base 3. When the lifting arm assembly 1 is in a compressed state, the rope 5 passes through the unlocking device 4, and both ends of the rope 5 are connected to the top assembly 2 and the base 3, respectively. After being lifted to the designated position, the lifting arm assembly 1 is in a straightened state. The lifting arm assembly 1 includes a first lifting arm 1-1, a second lifting arm 1-2, and a lifting torsion spring 1-3. Both the first lifting arm 1-1 and the second lifting arm 1-2 are multi-sectioned. A lifting arm 1-1 and a second lifting arm 1-2 are sequentially hinged together. The two ends of the lifting torsion spring 1-3 are respectively connected to the two adjacent second lifting arms 1-2. The top assembly 2 includes a solar panel mounting base 2-1, a locking spring 2-2, and a locking sleeve 2-3. The locking sleeve 2-3 is fitted onto the solar panel mounting base 2-1. The two ends of the locking spring 2-2 are respectively connected to the solar panel mounting base 2-1 and the locking sleeve 2-3. The first lifting arm 1-1 is hinged to the lower part of the solar panel mounting base 2-1. When the lifting arm assembly 1 is in the compressed state, the locking spring 2-2 is compressed, and the locking sleeve 2-3 is perpendicular to the axis of the first lifting arm 1-1. The first lifting arm 1-1 is located below the locking sleeve 2-3. When the lifting arm assembly 1 is in the extended state, the locking spring 2-2 is extended, and the locking sleeve 2-3 is parallel to the axis of the first lifting arm 1-1. The locking sleeve 2-3 is nested with the first lifting arm 1-1.

[0057] The specific details of this embodiment are as follows:

[0058] like Figures 2 to 5 As shown, the first lifting arm 1-1 and the second lifting arm 1-2 are connected by a hinge 1-4 and then fixed by a pivot rivet 1-5. Both the first lifting arm 1-1 and the second lifting arm 1-2 are long rod-shaped structures, connected by a hinge 1-4, as shown... Figure 7As shown, the hinge 1-4 is provided with two first shaft connecting holes 1-4-1, the first lifting arm 1-1 is provided with first shaft fixing holes 1-1-1 on both sides for the connection of the shaft rivet 1-5, the second lifting arm 1-2 is provided with second shaft fixing holes 1-2-1 on both sides for the connection of the shaft rivet 1-5, and the two first shaft connecting holes 1-4-1 are respectively connected with the first shaft fixing hole 1-1-1 and the second shaft fixing hole 1-2-1 and pass through the shaft rivet 1-5, so as to realize the connection of the hinge 1-4 with the first lifting arm 1-1 and the second lifting arm 1-2; the hinge 1-4 can rotate around the shaft rivet 1-5 through the first shaft connecting hole 1-4-1, so as to realize the structure change of the lifting arm combination 1.

[0059] As shown in Figures 2 to 5 , the surface of the first lifting arm 1-1 is provided with a first storage groove 1-1-2, the surface of the second lifting arm 1-2 is provided with a second storage groove 1-2-2, and the lifting torsional spring 1-3 is embedded in the first storage groove 1-1-2 and the second storage groove 1-2-2 when the lifting arm combination 1 is in the compressed state and the straightened state. One end of the second lifting arm 1-2 is provided with a limiting table 1-2-3, the front end of the limiting table 1-2-3 and the end face of the second storage groove 1-2-2 are provided with a torsional spring fixing hole 1-2-4, and the torsional spring fixing hole 1-2-4 is used for the installation of both ends of the lifting torsional spring 1-3.

[0060] As shown in Figure 6 , the lifting torsional spring 1-3 is made of spring steel and has high elasticity and toughness after heat treatment, the lifting torsional spring 1-3 is in a straightened state in a natural state, the lifting torsional spring 1-3 is provided with two torsional spring structures 1-3-1, and both ends of the lifting torsional spring 1-3 are straight torsional arms 1-3-2 which are inserted into the torsional spring fixing hole 1-2-4.

[0061] As shown in Figure 8 and Figure 9 , the solar wing mounting seat 2-1 includes a solar wing mounting surface 2-1-1, a third shaft fixing hole 2-1-2 and a locking support rod 2-1-3, the solar wing mounting surface 2-1-1 is connected with the solar wing driving mechanism 7 and can change the structure design according to the mechanical interface of the solar wing driving mechanism 7, the third shaft fixing hole 2-1-2 is connected with the first lifting arm 1-1 of the first section at the uppermost end of the lifting arm combination 1, the locking support rod 2-1-3 is sleeved with the locking sleeve 2-3 on the outside, and the locking support rod 2-1-3 is used for the support and guidance of the locking sleeve 2-3, and the bottom of the solar wing mounting seat 2-1 is provided with a rope hook 2-4 which is used for connecting the rope 5.

[0062] As shown in Figure 10As shown in the drawings, the base 3 is provided with a second pivot connection hole 3-1, a base fixing hole 3-2 and a rope fixing hole 3-3, the base 3 is connected to the second lifting arm 1-2 through the second pivot connection hole 1-2, the base 3 is connected to the satellite body 6 through the base fixing hole 3-2, and the two rope fixing holes 3-3 are holes with a bottom, and the rope 5 is connected to the rope fixing hole 3-3.

[0063] As shown in the drawings, Figure 11 The unlocking device 4 includes a hot knife 4-1, a shell 4-2 and a control line 4-3, the hot knife 4-1 is arranged in the shell 4-2, the control line 4-3 is connected to the hot knife 4-1, the shell 4-2 is provided with a rope hole 4-2-1 at the top, the rope 5 passes through the rope hole 4-2-1, the rope 5 corresponds to the position of the hot knife 4-1, and the hot knife 4-1 can be fused to break the rope 5 under the instruction.

[0064] As shown in the drawings, Figures 12-19 The embodiment is a method for assembling a multi-section lifting mechanism of a solar wing, which comprises the following steps:

[0065] Step 1: sequentially connect the multi-section first lifting arm 1-1 and the second lifting arm 1-2 to each other through a hinge, connect the two ends of the lifting torsional spring 1-3 to the adjacent two second lifting arms 1-2 respectively, and complete the installation of the lifting arm combination 1;

[0066] Step 2: fit the locking sleeve 2-3 on the solar wing mounting seat 2-1, connect the two ends of the locking spring 2-2 to the solar wing mounting seat 2-1 and the locking sleeve 2-3 respectively, push the locking sleeve 2-3 upwards to compress the locking spring 2-2, expose the lower part of the solar wing mounting seat 2-1, symmetrically and side by side close the two sets of lifting arm combinations 1, connect the first lifting arm 1-1 to the lower part of the solar wing mounting seat 2-1 through a hinge, and connect the lower ends of the two sets of lifting arm combinations 1 to the base 3 through a hinge;

[0067] Step 3: push the locking sleeve 2-3 upwards to compress the locking spring 2-2, expose the lower part of the solar wing mounting seat 2-1, at this time, the lifting mechanism is in an unlocked state, press the lifting mechanism downwards as a whole, the lifting torsional spring 1-3 is deformed under stress, the first lifting arm 1-1 and the second lifting arm 1-2 rotate around the hinge shaft until they are attached, one end of the rope 5 is connected to the base 3, the rope 5 passes through the unlocking device 4, the other end of the rope 5 is connected to the top combination 2, the locking of the compressed state of the lifting mechanism is completed, and finally the unlocking device 4 is connected to the base 3;

[0068] Step 4: connect the base 3 to the satellite body 6, and connect the top combination 2 to the solar wing driving mechanism 7.

[0069] The embodiment is as follows:

[0070] Step 1: asFigure 12 and Figure 13 As shown, the first lifting arm 1-1 and the second lifting arm 1-2 are connected end to end by hinges 1-4 and connected by pivot rivets 1-5. During the connection process, the lifting torsion spring 1-3 is embedded in the first storage slot 1-1-2 of the first lifting arm 1-1 and the second storage slot 1-2-2 of the second lifting arm 1-2, and the two ends of the lifting torsion spring 1-3 are inserted into the torsion spring fixing holes 1-2-4 to complete the fixation. In this way, the installation of all the first lifting arms 1-1, the second lifting arms 1-2 and the lifting torsion spring 1-3 is completed, thus completing the assembly of the lifting arm assembly 1; after assembly, the lifting arm assembly 1 is as follows. Figure 14 As shown;

[0071] Step 2: As Figure 15 As shown, screw the rope hook 2-4 into the threaded hole at the bottom of the solar panel mounting base 2-1 to complete the fixation. Place the locking spring 2-2 onto the locking support rod 2-1-3 of the solar panel mounting base 2-1. Weld one end of the locking spring 2-2 to the solar panel mounting base 2-1 for fixation. Then, place the locking sleeve 2-3 on the outside, welding the other end of the locking spring 2-2 to the locking sleeve 2-3 for fixation. Push the locking sleeve 2-3 upwards to compress the locking spring 2-2, exposing the third pivot fixing hole 2-1-2 of the solar panel mounting base 2-1. Arrange the two sets of lifting arm assemblies 1 symmetrically side-by-side. The pivot rivet 1-5 passes through the first pivot fixing hole 1-1-1 of the uppermost first section of the first lifting arm 1-1 and the third pivot fixing hole 2-1-2 of the solar panel mounting base 2-1 to complete the connection. After connection, the solar panel mounting base 2-1 can rotate around the pivot rivet 1-5. Figure 16 As shown, the assembled assembly is assembled with the base 3. The specific operation is as follows: use the pivot rivet 1-5 to pass through the second pivot fixing hole 1-2-1 of the last section of the bottom second lifting arm 1-2 and the second pivot connecting hole 3-1 of the base 3 to complete the connection.

[0072] Step 3: Push the locking sleeve 2-3 upwards to compress the locking spring 2-2 until the third pivot fixing hole 2-1-2 of the solar panel mounting base 2-1 is exposed. At this time, the lifting mechanism is in the unlocked state. Press the entire lifting mechanism downwards, and the lifting torsion spring 1-3 will deform under force. The first lifting arm 1-1 and the second lifting arm 1-2 will rotate around the hinge axis until they are in contact. Figure 17 As shown, at this time, the lifting torsion spring 1-3 is completely embedded in the first storage slot 1-1-2 and the second storage slot 1-2-2, which will not affect the tight fit between the lifting arms. One end of the rope 5 is fixed to the base 3 through the rope fixing hole 3-3. Then, the rope 5 is passed through the rope hole 4-2-1 of the unlocker 4 and tightened and fixed to the rope hook 2-4 of the top assembly 2 to complete the locking of the lifting mechanism in the pressed state. Finally, the unlocker 4 is pasted on the surface of the base 3.

[0073] Step 4: Fix the base 3 on the surface of the satellite body 6, connect the top combination 2 with the solar wing driving mechanism 7 through standard parts, connect the solar wing 8 on the solar wing driving mechanism 7, and complete the fixation of the whole lifting mechanism, as shown in Figure 18 After installation, the lifting arms of the lifting mechanism are in close contact with each other and the cabin plate, having high rigidity, which is conducive to resisting the mechanical environment of the ascending stage of the carrier.

[0074] Referring to Figures 20-22 The present application also provides a use method of the multi-section lifting mechanism of the solar wing, specifically: disconnect the rope 5 through the unlocking device 4, unlock and release the lifting mechanism, lift the lifting arm combination 1 under the driving of the lifting torsional spring 1-3, when the lifting mechanism is lifted into place, the lifting torsional spring 1-3 is in a straightened state, the two sets of lifting arm combinations 1 are straightened and in close contact with each other, in the lifting process, the locking spring 2-2 pushes the locking sleeve 2-3 to move downward, after the two sets of lifting arm combinations 1 are in close contact, the locking sleeve 2-3 is sleeved outside the two first lifting arms 1-1, and the locking of the straightened state of the lifting arm combination 1 is realized.

[0075] The embodiment is specifically as follows:

[0076] The hot knife 4-1 of the unlocking device 4 is powered on, the hot knife 4-1 melts the rope 5, the lifting mechanism is unlocked and released, and the lifting mechanism is lifted under the driving of the lifting torsional spring 1-3, as shown in Figure 20 When the lifting mechanism is lifted into place, the lifting torsional spring 1-3 is in a straightened state, the two sets of lifting arm combinations 1 are straightened and in close contact with each other, and then the solar wing 8 is unfolded, the solar wing driving mechanism 7 controls the solar wing 8 to face the sun, as shown in Figure 21 In the lifting process, the locking spring 2-2 pushes the locking sleeve 2-3 to move downward, after the two sets of lifting arm combinations 1 are in close contact, the locking sleeve 2-3 is sleeved outside the two first lifting arms 1-1, as shown in Figure 22 The locking of the straightened state of the lifting arm combination 1 is realized. The limiting table 1-2-3 of the second lifting arm 1-2 is in close contact with the outside of the first lifting arm 1-1, which has an auxiliary locking effect.

[0077] As shown in Figure 20 The lifting torsional spring 1-3 is fixed on the two adjacent second lifting arms 1-2, and the first lifting arm 1-1 is connected between the two second lifting arms 1-2, therefore, the two second lifting arms 1-2 connected with the lifting torsional spring 1-3 are arranged at intervals, and in the whole lifting process, the two second lifting arms 1-2 are in a Z shape, which can ensure that the two second lifting arms 1-2 are always parallel to each other, thereby realizing the lifting consistency of all the lifting arms. The force point of the lifting torsional spring 1-3 on the surface of the lifting arm is located at the middle segment of the lifting arm, and the force arm is long, so that the lifting can be realized without designing a larger torsion force for the lifting torsional spring 1-3. As shown in Figure 22As shown, after the lifting is completed and locked, the lifting torsion spring 1-3 is embedded in the first storage groove 1-1-2 and the second storage groove 1-2-2, plays the effect of exoskeleton, and further improves the rigidity and locking effect of the whole lifting mechanism.

[0078] The embodiments disclosed above are only used to help explain the present application. The embodiments do not describe all the details and do not limit the present application to the specific embodiments described. Many modifications and variations can be made in light of the content of the present application. The present application selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present application, so that those skilled in the art can well understand and utilize the present application.

Claims

1. A multi-section lifting mechanism for solar panels, characterized in that: It includes a lifting arm assembly (1), a top assembly (2), a base (3), an unlocker (4), and a rope (5). The lifting arm assembly (1) consists of two sets, which are symmetrically arranged. The upper and lower ends of each lifting arm assembly (1) are connected to the top assembly (2) and the base (3), respectively. The top assembly (2) is connected to the solar wing drive mechanism (7), which is connected to the solar wing (8). The base (3) is connected to the satellite body (6). The unlocker (4) is... The lifting arm assembly (1) is connected to the base (3). When the lifting arm assembly (1) is in the compressed state, the rope (5) passes through the unlocker (4) and the two ends of the rope (5) are connected to the top assembly (2) and the base (3) respectively. The lifting arm assembly (1) is in the straightened state after being lifted into position. The lifting arm assembly (1) includes a first lifting arm (1-1), a second lifting arm (1-2), and a lifting torsion spring (1-3). The first lifting arm (1-1) and the second lifting arm (1-2) are both multi-section. The multi-section first lifting arm (1-1) is connected to the base (3). When the lifting arm assembly (1) is in the compressed state, the rope (5) passes through the unlocker (4) and the two ends of the rope (5) are connected to the top assembly (2) and the base (3) respectively. The lifting arm assembly (1) is in the straightened state after being lifted into position. The lifting arm assembly (1-1) includes a first lifting arm (1-1), a second lifting arm (1-2), and a lifting torsion spring (1-3). The first lifting arm (1-1) and the second lifting arm (1-2) are both multi-section. 1) Hinged sequentially with the second lifting arm (1-2), the two ends of the lifting torsion spring (1-3) are respectively connected to the two adjacent second lifting arms (1-2). The top assembly (2) includes a solar panel mounting base (2-1), a locking spring (2-2), and a locking sleeve (2-3). The locking sleeve (2-3) is fitted onto the solar panel mounting base (2-1). The two ends of the locking spring (2-2) are respectively connected to the solar panel mounting base (2-1) and the locking sleeve (2-3). The first lifting arm (1) -1) Hinged to the lower part of the solar panel mounting base (2-1), when the lifting arm assembly (1) is in the pressed state, the locking spring (2-2) is pressed, the locking sleeve (2-3) is perpendicular to the axis of the first lifting arm (1-1), the first lifting arm (1-1) is located below the locking sleeve (2-3), when the lifting arm assembly (1) is in the extended state, the locking spring (2-2) is extended, the locking sleeve (2-3) is parallel to the axis of the first lifting arm (1-1), and the locking sleeve (2-3) is nested with the first lifting arm (1-1).

2. The multi-section lifting mechanism for a solar array according to claim 1, characterized in that: The surface of the first lifting arm (1-1) is provided with a first storage groove (1-1-2), and the surface of the second lifting arm (1-2) is provided with a second storage groove (1-2-2). When the lifting arm assembly (1) is in the pressed state and the extended state, the lifting torsion spring (1-3) is embedded in the first storage groove (1-1-2) and the second storage groove (1-2-2).

3. The multi-section lifting mechanism for a solar array according to claim 2, characterized in that: The first lifting arm (1-1) and the second lifting arm (1-2) are both long rod-shaped structures. One end of the second lifting arm (1-2) is provided with a limiting platform (1-2-3). The front end of the limiting platform (1-2-3) and the end face of the second storage groove (1-2-2) are provided with torsion spring fixing holes (1-2-4). The torsion spring fixing holes (1-2-4) are used for the installation of the two ends of the lifting torsion spring (1-3).

4. The multi-section lifting mechanism for a solar array according to claim 3, characterized in that: The lifting torsion spring (1-3) is made of spring steel. The lifting torsion spring (1-3) is in a straight state in its natural state. The lifting torsion spring (1-3) has two torsion spring structures (1-3-1). The two ends of the lifting torsion spring (1-3) are straight torsion arms (1-3-2), which are inserted into the torsion spring fixing holes (1-2-4).

5. The multi-section lifting mechanism for a solar array according to claim 1, characterized in that: The first lifting arm (1-1) and the second lifting arm (1-2) are connected by a hinge (1-4). The hinge (1-4) has two first pivot connection holes (1-4-1). The first lifting arm (1-1) has first pivot fixing holes (1-1-1) on both sides, and the second lifting arm (1-2) has second pivot fixing holes (1-2-1) on both sides. The two first pivot connection holes (1-4-1) are respectively connected to the first pivot fixing holes (1-1-1) and the second pivot fixing holes (1-2-1) and pivot rivets (1-5) are inserted.

6. The multi-section lifting mechanism for a solar array according to claim 1, characterized in that: The solar wing mounting base (2-1) includes a solar wing mounting surface (2-1-1), a third rotating shaft fixing hole (2-1-2), and a locking support rod (2-1-3). The solar wing mounting surface (2-1-1) is connected to the solar wing drive mechanism (7). The third rotating shaft fixing hole (2-1-2) is connected to the first lifting arm (1-1). The locking support rod (2-1-3) is fitted with a locking sleeve (2-3) on its outer side. The bottom of the solar wing mounting base (2-1) is provided with a rope hook (2-4), which is used to connect a rope (5).

7. The multi-section lifting mechanism for a solar array according to claim 1, characterized in that: The base (3) is provided with a second pivot connection hole (3-1), a base fixing hole (3-2) and a rope fixing hole (3-3). The base (3) is hinged to the second lifting arm (1-2) through the second pivot connection hole (3-1). The base (3) is connected to the satellite body (6) through the base fixing hole (3-2). The rope (5) is connected to the rope fixing hole (3-3).

8. The multi-section lifting mechanism for a solar array according to claim 1, characterized in that: The unlocker (4) includes a hot knife (4-1), a housing (4-2), and a control line (4-3). The hot knife (4-1) is disposed inside the housing (4-2), and the control line (4-3) is connected to the hot knife (4-1). The housing (4-2) is provided with a rope hole (4-2-1), and the rope (5) passes through the rope hole (4-2-1). The position of the rope (5) corresponds to that of the hot knife (4-1).

9. An assembly method for a multi-section lifting mechanism based on the solar array as described in claim 1, characterized in that: It includes the following steps: Step 1: Connect the multiple sections of the first lifting arm (1-1) and the second lifting arm (1-2) sequentially by hinge, and connect the two ends of the lifting torsion spring (1-3) to the two adjacent second lifting arms (1-2) respectively to complete the installation of the lifting arm assembly (1); Step 2: Place the locking sleeve (2-3) onto the solar panel mounting base (2-1), connect the two ends of the locking spring (2-2) to the solar panel mounting base (2-1) and the locking sleeve (2-3) respectively, push the locking sleeve (2-3) upward to compress the locking spring (2-2), expose the lower part of the solar panel mounting base (2-1), symmetrically place the two sets of lifting arm assemblies (1) together, hinge the first lifting arm (1-1) to the lower part of the solar panel mounting base (2-1), and hinge the lower ends of the two sets of lifting arm assemblies (1) to the base (3); Step 3: Push the locking sleeve (2-3) upward to compress the locking spring (2-2), exposing the lower part of the solar panel mounting base (2-1). At this time, the lifting mechanism is in the unlocked state. Press the entire lifting mechanism downward, and the lifting torsion spring (1-3) will deform under force. The first lifting arm (1-1) and the second lifting arm (1-2) will rotate around the hinge axis until they fit together. Connect one end of the rope (5) to the base (3), then pass the rope (5) through the unlocker (4), and then connect the other end of the rope (5) to the top assembly (2) to complete the locking of the lifting mechanism in the pressed state. Finally, connect the unlocker (4) to the base (3). Step 4: Connect the base (3) to the satellite body (6) and connect the top assembly (2) to the solar wing drive mechanism (7).

10. A method of using a multi-section lifting mechanism based on the solar array as described in claim 1, characterized in that: The rope (5) is disconnected by the unlocker (4), the lifting mechanism is unlocked and released, and the lifting arm assembly (1) is lifted under the drive of the lifting torsion spring (1-3). When the lifting mechanism is lifted to the position, the lifting torsion spring (1-3) is in the straight state, and the two sets of lifting arm assemblies (1) are straight and close to each other. During the lifting process, the locking spring (2-2) pushes the locking sleeve (2-3) to move downward. After the two sets of lifting arm assemblies (1) are close together, the locking sleeve (2-3) is put on the outside of the two first lifting arms (1-1) to lock the lifting arm assembly (1) in the straight state.

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