Self-release solar wing unfolding mechanism

Abstract

The utility model relates to the technical field of solar wing unfolding mechanisms, in particular to a self-release solar wing unfolding mechanism. According to the self-releasing solar wing unfolding mechanism, the first elastic pieces in the compressed state are adopted to provide unfolding elastic force for the corresponding shear fork units; a scroll constant-force spring, a fixed pulley and a synchronous linkage assembly are adopted to link each scissor unit to unfold at a constant speed; and when the shear fork unit is unfolded to a target position, the shear fork unit and the synchronous linkage assembly are limited and locked by adopting the limiting and locking assembly. The utility model relates to a passive unfolding mechanism capable of completing self-release unfolding operation, belongs to a solar wing battery, and solves the problem that an active driving unfolding machine in the prior art is complex in structure and heavy in weight, so that the launching cost is increased.

Description

Technical Field

[0001] The utility model relates to the technical field of solar wing unfolding mechanisms, in particular to a self-releasing solar wing unfolding mechanism. Background Art

[0002] The solar wing deployment mechanism has the functions of deployment and structural support. Its main function is to collect solar energy to provide energy for spacecraft (such as satellites). It is one of the most important components of spacecraft. At present, the most commonly used solar wing deployment mechanisms are mainly active drive deployment machines. Such active drive deployment machines use heavy driving components (such as motors) and multi-stage transmission gears, which not only makes the structure of the active drive deployment machine complex, but also makes it heavy, thereby increasing the launch cost. Therefore, miniaturization and lightweight solar wing deployment mechanisms are the trend of future development.

[0003] In summary, there is a need to provide a self-releasing solar wing deployment mechanism to solve the problem of complex structure and heavy mass of the active drive deployment machine in the prior art, which increases the launch cost. Utility Model Content

[0004] The utility model aims to provide a self-releasing solar wing deployment mechanism, and the specific technical scheme is as follows:

[0005] A self-release solar wing deployment mechanism, comprising a scissor assembly, a fixed pulley, a first elastic member, a synchronous linkage assembly, a scroll constant force spring and a limit locking assembly;

[0006] The scissor assembly comprises a plurality of scissor units hingedly arranged in sequence along the unfolding direction of the solar wing; each of the scissor units comprises a first connecting rod and a second connecting rod cross-arranged and hinged at the intersection; the first connecting rods in all the scissor units are arranged parallel to each other, and the second connecting rods in all the scissor units are arranged parallel to each other;

[0007] The number of the fixed pulleys is one more than the number of the scissor-type units, and the fixed pulleys are arranged on both ends of the first connecting rod or on both ends of the second connecting rod in all the scissor-type units;

[0008] The number of the first elastic members is the same as the number of the fixed pulleys, and the first elastic members are arranged between the first connecting rod and the second connecting rod in each of the scissor-type fork units; the first elastic members are in a compressed state;

[0009] The synchronous linkage components are in two groups, and are respectively hinged to the scissor units at both ends of the scissor assembly;

[0010] The scroll constant force spring is arranged on the synchronous linkage assembly on one end of the scissor-fork assembly, and the free end of the spring passes through each of the fixed pulleys in sequence and is fixedly connected to the synchronous linkage assembly on the other end of the scissor-fork assembly;

[0011] The limit locking assembly is arranged at a position where the scissor-fork unit of the scissor-fork assembly is hinged to the synchronous linkage assembly away from one end of the spiral constant force spring.

[0012] Optionally, each group of the synchronous linkage components includes an opening and closing connecting piece and a synchronous linkage piece; the opening and closing connecting piece includes a third connecting rod and a fourth connecting rod, one end of the third connecting rod is hinged to the first connecting rod in the scissors-type unit, and the other end is connected to the synchronous linkage piece; one end of the fourth connecting rod is hinged to the second connecting rod in the scissors-type unit, and the other end is connected to the synchronous linkage piece.

[0013] Optionally, the synchronous linkage includes a first gear, a second gear, a first connecting shaft, a second connecting shaft, a first connecting block, a second connecting block and a mounting seat; the first connecting shaft and the second connecting shaft can be rotatably set on the mounting seat; the first gear is fixedly connected to the first connecting shaft; the second gear is fixedly connected to the second connecting shaft; the first gear is meshing with the second gear; one end of the first connecting block is fixedly connected to the first connecting shaft, and the other end is connected to the third connecting rod; one end of the second connecting block is fixedly connected to the second connecting shaft, and the other end is connected to the fourth connecting rod; the volute constant force spring is arranged on the mounting seat on one group of the synchronous linkage components, and the spring free end of the volute constant force spring is arranged on the mounting seat on another group of the synchronous linkage components.

[0014] Optionally, the limit locking assembly includes a first hinge, a second hinge and a limit locking component; the first hinge is connected to the first connecting rod or the second connecting rod, and the second hinge is connected to the third connecting rod or the fourth connecting rod; a first ear plate is arranged on the first hinge, and a second ear plate is arranged on the second hinge, and the first ear plate and the two ear plates are axially rotatably connected; a countersunk hole for accommodating the limit locking component is arranged on the first ear plate, and a through hole adapted to the countersunk hole is arranged on the second ear plate; the limit locking component is in a compressed state before penetrating the through hole, and the through hole and the countersunk hole are staggered.

[0015] Optionally, the limiting locking component includes a second elastic member and a limiting pin; one end of the second elastic member is connected to the bottom of the countersunk hole, and the other end is connected to the limiting pin; the second elastic member is in a compressed state before the limiting pin passes through the through hole.

[0016] Optionally, the limiting pin is a T-shaped column structure, with a small diameter end arranged close to the through hole and a large diameter end arranged close to the second elastic member; the large diameter end of the limiting pin has a diameter larger than an inner diameter of the through hole.

[0017] Optionally, both the first elastic member and the second elastic member include springs.

[0018] Optionally, a limiting groove is provided on the first hinge, and one end of the second ear plate of the second hinge is accommodated in the limiting groove.

[0019] Optionally, a plurality of first mounting holes are provided on the first hinge, a first connecting hole adapted to the first mounting hole is provided on the first connecting rod or the second connecting rod; and a first connecting member is provided in the first mounting hole and the first connecting hole.

[0020] Optionally, a plurality of second mounting holes are provided on the second hinge, and a second connecting hole matched with the second mounting hole is provided on the third connecting rod or the fourth connecting rod; and a second connecting member is provided in the second mounting hole and the second connecting hole.

[0021] The application of the technical solution of the utility model has at least the following beneficial effects:

[0022] The utility model provides a self-release solar wing deployment mechanism that can complete the self-release deployment operation. It is a passive deployment mechanism of the solar wing battery, which solves the problem of complex structure and heavy mass in the active drive deployment machine in the prior art, which increases the launch cost. Specifically, in the self-release deployment operation, the utility model uses each first elastic member in a compressed state to provide deployment elastic force for each corresponding scissor unit; uses a volute constant force spring, a fixed pulley and a synchronous linkage assembly to link each scissor unit to deploy at a uniform speed; when deployed to the target position, a limit locking assembly is used to achieve limit locking between the scissor unit and the synchronous linkage assembly.

[0023] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings:

[0025] Figure 1 It is a structural schematic diagram of a self-releasing solar wing deployment mechanism in an embodiment of the utility model;

[0026] Figure 2 yes Figure 1 The structural diagram of the synchronous linkage component;

[0027] Figure 3 yes Figure 1 A perspective structural diagram of the middle limit locking assembly;

[0028] Among them, 1. fixed pulley, 2. first elastic member, 3. synchronous linkage assembly, 3.1. third connecting rod, 3.2. fourth connecting rod, 3.3. first gear, 3.4. second gear, 3.5. first connecting block, 3.6. second connecting block, 3.7. mounting seat, 4. scroll constant force spring, 5. limit locking assembly, 5.1. first hinge, 5.1.1. limit groove, 5.2. second hinge, 5.3. second elastic member, 5.4. limit pin, 6. scissors unit, 6.1. first connecting rod, 6.2. second connecting rod. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of the utility model.

[0030] Example:

[0031] See also Figure 1-Figure 3 , a self-release solar wing deployment mechanism, comprising a scissor assembly, a fixed pulley 1, a first elastic member 2 (specifically a spring), a synchronous linkage assembly 3, a scroll constant force spring 4 and a limit locking assembly 5;

[0032] The scissor assembly comprises a plurality of scissor units 6 hingedly arranged in sequence along the unfolding direction of the solar wing; each of the scissor units 6 comprises a first connecting rod 6.1 and a second connecting rod 6.2 which are cross-arranged and hinged at the intersection; the first connecting rods 6.1 in all the scissor units 6 are arranged parallel to each other, and the second connecting rods 6.2 in all the scissor units 6 are arranged parallel to each other;

[0033] The number of the fixed pulleys 1 is one more than the number of the scissor-type units 6, and the fixed pulleys 1 are arranged on both ends of the first connecting rods 6.1 in all the scissor-type units 6;

[0034] The number of the first elastic members 2 is the same as the number of the fixed pulleys 1, and the first elastic member 2 is arranged between the first connecting rod 6.1 and the second connecting rod 6.2 in each of the scissor-type units 6; the first elastic member 2 is in a compressed state;

[0035] The synchronous linkage components 3 are divided into two groups, and are respectively hinged to the scissor units 6 at both ends of the scissor assembly;

[0036] The scroll constant force spring 4 is arranged on the synchronous linkage assembly 3 on one end of the scissor-fork assembly, and the free end of the spring passes through each of the fixed pulleys 1 in sequence and is fixedly connected to the synchronous linkage assembly 3 on the other end of the scissor-fork assembly;

[0037] The limit locking assembly 5 is arranged at a position where the scissor unit 6 of the scissor assembly away from one end of the spiral constant force spring 4 is hinged to the synchronous linkage assembly 3.

[0038] See also Figure 2 Each group of the synchronous linkage components 3 includes an opening and closing connection member and a synchronous linkage member; the opening and closing connection member includes a third connecting rod 3.1 and a fourth connecting rod 3.2, one end of the third connecting rod 3.1 is hinged to the first connecting rod 6.1 in the scissors-type unit 6, and the other end is connected to the synchronous linkage member; one end of the fourth connecting rod 3.2 is hinged to the second connecting rod 6.2 in the scissors-type unit 6, and the other end is connected to the synchronous linkage member.

[0039] See also Figure 2 The synchronous linkage comprises a first gear 3.3, a second gear 3.4, a first connecting shaft, a second connecting shaft, a first connecting block 3.5, a second connecting block 3.6 and a mounting seat 3.7; the first connecting shaft and the second connecting shaft can be rotatably arranged on the mounting seat 3.7; the first gear 3.3 is fixedly connected to the first connecting shaft; the second gear 3.4 is fixedly connected to the second connecting shaft; the first gear 3.3 is meshed with the second gear 3.4; one end of the first connecting block 3.5 is fixedly connected to the first connecting shaft, and the other end is connected to the third connecting rod 3.1; one end of the second connecting block 3.6 is fixedly connected to the second connecting shaft, and the other end is connected to the fourth connecting rod 3.2; the volute constant force spring 4 is arranged on the mounting seat 3.7 on one group of the synchronous linkage components 3, and the spring free end of the volute constant force spring 4 is arranged on the mounting seat 3.7 on another group of the synchronous linkage components 3.

[0040] See also Figure 3The limit locking assembly 5 includes a first hinge 5.1, a second hinge 5.2 and a limit locking component; the first hinge 5.1 is connected to the first connecting rod 6.1, and the second hinge 5.2 is connected to the third connecting rod 3.1; a first ear plate is arranged on the first hinge 5.1, and a second ear plate is arranged on the second hinge 5.2, and the first ear plate and the two ear plates are axially connected; a countersunk hole for accommodating the limit locking component is arranged on the first ear plate, and a through hole adapted to the countersunk hole is arranged on the second ear plate; the limit locking component is in a compressed state before penetrating the through hole, and the through hole and the countersunk hole are staggered.

[0041] See also Figure 3 The limit locking component includes a second elastic member 5.3 (specifically a spring) and a limit pin 5.4; one end of the second elastic member 5.3 is connected to the bottom of the countersunk hole, and the other end is connected to the limit pin 5.4; before the limit pin 5.4 passes through the through hole, the second elastic member 5.3 is in a compressed state, which is convenient for providing elastic force for the limit pin 5.4. When the through hole and the countersunk hole move to the same axis, the limit pin 5.4 can pass through the through hole with the help of elastic force to achieve limit locking between the scissor unit 6 and the synchronous linkage assembly 3.

[0042] See also Figure 3 The limit pin 5.4 is a T-shaped column structure, with its small diameter end being arranged close to the through hole and its large diameter end being arranged close to the second elastic member 5.3; the diameter of the large diameter end of the limit pin 5.4 is larger than the inner diameter of the through hole, so as to avoid the risk of the limit pin 5.4 falling off when completely passing through the through hole.

[0043] A limiting groove 5.1.1 is provided on the first hinge 5.1, and one end of the second ear plate of the second hinge 5.2 is accommodated in the limiting groove 5.1.1, which facilitates the rapid installation of the second hinge 5.2 and ensures the stability of the second hinge 5.2 when rotating relative to the first hinge 5.1.

[0044] A plurality of first mounting holes are arranged on the first hinge 5.1, and a first connecting hole adapted to the first mounting hole is arranged on the first connecting rod 6.1; a first connecting member (specifically a bolt) is arranged in the first mounting hole and the first connecting hole to achieve a stable connection between the first hinge 5.1 and the first connecting rod 6.1.

[0045] A plurality of second mounting holes are arranged on the second hinge 5.2, and a second connecting hole adapted to the second mounting hole is arranged on the third connecting rod 3.1; a second connecting member (specifically a bolt) is arranged in the second mounting hole and the second connecting hole to achieve a stable connection between the second hinge 5.2 and the third connecting rod 3.1.

[0046] The self-release unfolding operation process of the self-release solar wing unfolding mechanism is as follows:

[0047] Each first elastic member 2 in a compressed state is used to provide an unfolding elastic force for each corresponding scissor-type unit 6; the volute constant force spring 4, the fixed pulley 1 and the synchronous linkage assembly 3 are used to link each scissor-type unit 6 to unfold at a uniform speed; when unfolded to the target position, the limit locking assembly 5 is used to achieve the limit locking between the scissor-type unit 6 and the synchronous linkage assembly 3.

[0048] The above description is only the preferred embodiment of the utility model, and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. A self-releasing solar wing deployment mechanism, characterized in that: It comprises a scissor-type fork assembly, a fixed pulley (1), a first elastic member (2), a synchronous linkage assembly (3), a scroll constant force spring (4) and a limit locking assembly (5); The scissor assembly comprises a plurality of scissor units (6) hingedly arranged in sequence along the unfolding direction of the solar wing; each of the scissor units (6) comprises a first connecting rod (6.1) and a second connecting rod (6.2) which are cross-arranged and hinged at the intersection; the first connecting rods (6.1) in all the scissor units (6) are arranged parallel to each other, and the second connecting rods (6.2) in all the scissor units (6) are arranged parallel to each other; The number of the fixed pulleys (1) is one more than the number of the scissor-type units (6), and the fixed pulleys (1) are arranged on both ends of the first connecting rod (6.1) or on both ends of the second connecting rod (6.2) in all the scissor-type units (6); The number of the first elastic members (2) is the same as the number of the fixed pulleys (1), and the first elastic member (2) is arranged between the first connecting rod (6.1) and the second connecting rod (6.2) in each of the scissor-type units (6); the first elastic member (2) is in a compressed state; The synchronous linkage components (3) are divided into two groups, and are respectively hinged to the scissor-fork units (6) at both ends of the scissor-fork component; The scroll constant force spring (4) is arranged on the synchronous linkage assembly (3) on one end of the scissor-fork assembly, and the free end of the spring passes through each of the fixed pulleys (1) in sequence and is fixedly connected to the synchronous linkage assembly (3) on the other end of the scissor-fork assembly; The limit locking assembly (5) is arranged at a position of the scissor-fork assembly away from one end of the spiral constant force spring (4) where the scissor-fork unit (6) and the synchronous linkage assembly (3) are hinged.

2. The self-release solar wing deployment mechanism according to claim 1, characterized in that: Each group of the synchronous linkage components (3) comprises an opening and closing connection member and a synchronous linkage member; the opening and closing connection member comprises a third connecting rod (3.1) and a fourth connecting rod (3.2); one end of the third connecting rod (3.1) is hinged to the first connecting rod (6.1) in the scissor-type unit (6), and the other end is connected to the synchronous linkage member; one end of the fourth connecting rod (3.2) is hinged to the second connecting rod (6.2) in the scissor-type unit (6), and the other end is connected to the synchronous linkage member.

3. The self-release solar wing deployment mechanism according to claim 2, characterized in that: The synchronous linkage comprises a first gear (3.3), a second gear (3.4), a first connecting shaft, a second connecting shaft, a first connecting block (3.5), a second connecting block (3.6) and a mounting seat (3.7); the first connecting shaft and the second connecting shaft are both rotatably arranged on the mounting seat (3.7); the first gear (3.3) is fixedly connected to the first connecting shaft; the second gear (3.4) is fixedly connected to the second connecting shaft; the first gear (3.3) is meshed with the second gear (3.4); One end of the first connecting block (3.5) is fixedly connected to the first connecting shaft, and the other end is connected to the third connecting rod (3.1); one end of the second connecting block (3.6) is fixedly connected to the second connecting shaft, and the other end is connected to the fourth connecting rod (3.2); the volute constant force spring (4) is arranged on the mounting seat (3.7) on one group of the synchronous linkage components (3), and the spring free end of the volute constant force spring (4) is arranged on the mounting seat (3.7) on the other group of the synchronous linkage components (3).

4. The self-releasing solar wing deployment mechanism according to claim 2, characterized in that: The position limiting locking assembly (5) comprises a first hinge (5.1), a second hinge (5.2) and a position limiting locking component; the first hinge (5.1) is connected to the first connecting rod (6.1) or the second connecting rod (6.2), and the second hinge (5.2) is connected to the third connecting rod (3.1) or the fourth connecting rod (3.2); a first ear plate is arranged on the first hinge (5.1), and a second ear plate is arranged on the second hinge (5.2), and the first ear plate and the two ear plates are axially rotatably connected; a countersunk hole for accommodating the position limiting locking component is arranged on the first ear plate, and a through hole adapted to the countersunk hole is arranged on the second ear plate; the position limiting locking component is in a compressed state before penetrating the through hole, and the through hole and the countersunk hole are arranged in an offset manner.

5. The self-releasing solar wing deployment mechanism according to claim 4, characterized in that: The limiting locking component comprises a second elastic member (5.3) and a limiting pin (5.4); one end of the second elastic member (5.3) is connected to the bottom of the countersunk hole, and the other end is connected to the limiting pin (5.4); before the limiting pin (5.4) passes through the through hole, the second elastic member (5.3) is in a compressed state.

6. The self-releasing solar wing deployment mechanism according to claim 5, characterized in that: The limiting pin (5.4) is a T-shaped column structure, with a small diameter end arranged close to the through hole and a large diameter end arranged close to the second elastic member (5.3); the large diameter end of the limiting pin (5.4) has a diameter greater than the inner diameter of the through hole.

7. The self-releasing solar wing deployment mechanism according to claim 5, characterized in that: The first elastic member (2) and the second elastic member (5.3) both comprise springs.

8. The self-release solar wing deployment mechanism according to any one of claims 4 to 7, characterized in that: A limiting groove (5.1.1) is provided on the first hinge (5.1), and one end of the second ear plate of the second hinge (5.2) is accommodated in the limiting groove (5.1.1).

9. The self-releasing solar wing deployment mechanism according to claim 8, characterized in that: A plurality of first mounting holes are arranged on the first hinge (5.1); a first connecting hole matching the first mounting hole is arranged on the first connecting rod (6.1) or the second connecting rod (6.2); and a first connecting member is arranged in the first mounting hole and the first connecting hole.

10. The self-releasing solar wing deployment mechanism according to claim 8, characterized in that: A plurality of second mounting holes are arranged on the second hinge (5.2); a second connecting hole matching the second mounting hole is arranged on the third connecting rod (3.1) or the fourth connecting rod (3.2); and a second connecting member is arranged in the second mounting hole and the second connecting hole.

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