Deployment mechanism and spacecraft

Abstract

The present invention belongs to the technical field of aerospace equipment, and discloses an unfolding mechanism and a spacecraft, wherein the unfolding mechanism is used for retracting and unreeling a curling arm, and comprises a carrier, a rotating shaft, and a plurality of guide portions. The rotating shaft is rotatably arranged on the carrier, and one end of the curling arm is fixed on the rotating shaft, and the rotating shaft is used for retracting and unreeling the curling arm. A plurality of guide portions are distributed on the carrier along the periphery of the rotating shaft, and the plurality of guide portions are used for providing guidance during the process of retracting and unreeling the curling arm. The curling arm is wound around the rotating shaft, and the curling arm can be unfolded or folded by rotating the rotating shaft, so that the overall structure of the solar wing using the above-mentioned unfolding mechanism is simple and small in size, which can meet the space requirements of small spacecraft. The spacecraft including the above-mentioned unfolding mechanism is small in size and can meet the requirements of miniaturized design.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace equipment, and in particular to a deployment mechanism and a spacecraft. Background Art

[0002] During long-term in-orbit operations, spacecraft rely primarily on solar panels to provide electrical energy. During launch, the panels are stowed to minimize their footprint. Once in orbit, they deploy to generate electricity.

[0003] Traditional solar wings generally come in two types: rigid and foldable. With technological advancements, flexible solar wings made of coiled arms are being explored and applied. Compared to traditional rigid solar wings, coiled arms offer significant advantages such as light weight, compact size, and high storage efficiency, demonstrating their enormous potential for development.

[0004] However, most of the current curling arms use a scissor-fork type unfolding mechanism, but the use of this unfolding mechanism will make the overall structure of the solar wing complex and bulky, which cannot meet the space requirements of small spacecraft.

[0005] Therefore, the above problems need to be solved urgently. Summary of the Invention

[0006] The purpose of the present invention is to provide a deployment mechanism and a spacecraft to simplify the overall structure of the solar wing and reduce the volume of the solar wing, thereby meeting the space requirements of small spacecraft.

[0007] To achieve this object, the present invention adopts the following technical solutions:

[0008] A deployment mechanism for retracting and unreeling a curling arm, the deployment mechanism comprising:

[0009] bearing members;

[0010] A rotating shaft, rotatably disposed on the carrier, one end of the curling arm is fixed on the rotating shaft, and the rotating shaft is used to retract and unreel the curling arm;

[0011] A plurality of guide parts are distributed on the supporting member along the outer periphery of the rotating shaft, and the plurality of guide parts are used to provide guidance during the process of retracting and unreeling the curling arm.

[0012] Preferably, the unfolding mechanism further comprises a speed control member provided on the supporting member, and the speed control member is used to control the rotation speed of the rotating shaft so that the curling arm unfolds at a uniform speed.

[0013] Preferably, the speed control component includes a rotation damper, and the rotation damper acts on the rotating shaft.

[0014] Preferably, the deployment mechanism comprises a locking assembly configured to lock the curling arm in the deployed state.

[0015] Preferably, the locking assembly comprises:

[0016] A locking hole is provided on the rotating shaft;

[0017] A locking pin is slidably arranged on the carrier, and the locking pin can be inserted into the locking hole.

[0018] Preferably, at least one guide wheel is provided on the guide portion.

[0019] Preferably, the bearing member includes two oppositely arranged support plates, the two support plates are arranged on the main body of the spacecraft, and the two ends of the rotating shaft are respectively mounted on the two support plates.

[0020] Preferably, the supporting member also includes a top plate and a side plate, the upper sides of the two support plates are connected through the top plate, and the same side of the two support plates is connected through the side plate, so that the two support plates, the top plate and the side plates enclose a accommodating space, and the curling arm is located in the accommodating space after being rolled up.

[0021] Preferably, the unfolding mechanism further comprises a sleeve sleeved on the rotating shaft, and the sleeve is used to roll up the curling arm.

[0022] A spacecraft comprises a driving member and the above-mentioned deployment mechanism, wherein the driving member is used to drive the rotation axis of the deployment mechanism to rotate.

[0023] Beneficial effects of the present invention:

[0024] 1. The unfolding mechanism provided by the present invention winds the curling arm through a rotating shaft, and the curling arm can be unfolded or folded by rotating the rotating shaft. As a result, the solar wing using the above-mentioned unfolding mechanism has a simpler overall structure and a smaller size than the solar wing using a scissor-fork type unfolding mechanism, which can meet the space requirements of small spacecraft.

[0025] 2. When the unfolding mechanism provided by the present invention unfolds the curling arm, that is, when the rotating shaft rotates the curling arm, multiple guide parts distributed on the outer circumference of the rotating shaft can limit the curling arm, thereby preventing the curling arm from producing excessive displacement and unloading force.

[0026] 3. The spacecraft including the above-mentioned deployment mechanism is small in size and can meet the needs of miniaturization design. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the structure of the deployment mechanism provided by the present invention. Figure 1 ;

[0028] Figure 2 This is a schematic diagram of the structure of the deployment mechanism provided by the present invention. Figure 2 ;

[0029] Figure 3 It is a structural schematic diagram of the rotating shaft and the guide portion provided by the present invention;

[0030] Figure 4 It is a structural schematic diagram of the rotating shaft and locking assembly provided by the present invention.

[0031] In the picture:

[0032] 100. Curl arms;

[0033] 1. Bearing member; 11. Support plate; 12. Top plate; 13. Side plate;

[0034] 2. Rotating shaft; 21. Angular contact ball bearing; 22. Sleeve;

[0035] 3. Guide part; 31. Guide wheel;

[0036] 4. Speed ​​control parts;

[0037] 5. Locking assembly; 51. Locking hole; 52. Locking pin. DETAILED DESCRIPTION

[0038] Before any embodiments of the present application are explained in detail, it is to be understood that the application is not limited in its application to the details of construction and the arrangement of components set forth in the following description or illustrated in the foregoing drawings.

[0039] In this application, the terms "comprises," "includes," "has," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not preclude the presence of additional identical elements in the process, method, article, or apparatus that includes the element.

[0040] In this application, the term "and / or" is a description of the association relationship between related objects, indicating that three relationships can exist. For example, a centrifugal vortex magnetic pump and / or a centrifugal vortex magnetic pump can represent three situations: the existence of a centrifugal vortex magnetic pump alone, the existence of a centrifugal vortex magnetic pump and a centrifugal vortex magnetic pump at the same time, and the existence of a centrifugal vortex magnetic pump alone. In addition, the character " / " in this application generally indicates that the related objects are in an "and / or" relationship.

[0041] In this application, the terms "connect," "combine," "couple," and "install" may refer to direct connection, combination, coupling, or installation, or indirect connection, combination, coupling, or installation. For example, a direct connection refers to two parts or components being connected together without an intermediary, and an indirect connection refers to two parts or components being connected to at least one intermediary, with the two parts or components being connected via the intermediary. Furthermore, "connect" and "couple" are not limited to physical or mechanical connections or couplings and may include electrical connections or couplings.

[0042] In this application, it will be understood by those skilled in the art that relative terms (e.g., "about," "approximately," "substantially," etc.) used in conjunction with quantities or conditions include the values ​​and have the meaning indicated by the context. For example, the relative terms include at least the degree of error associated with the measurement of a specific value, the tolerance caused by manufacturing, assembly, use, etc. associated with a specific value. Such terms should also be considered to disclose a range defined by the absolute values ​​of the two endpoints. Relative terms may refer to plus or minus a certain percentage (e.g., 1%, 5%, 10% or more) of the indicated value. Numerical values ​​that do not use relative terms should also be disclosed as specific values ​​with tolerances. In addition, "substantially" may refer to plus or minus a certain degree (e.g., 1 degree, 5 degrees, 10 degrees or more) on the basis of the indicated angle when expressing a relative angular position relationship (e.g., substantially parallel, substantially perpendicular).

[0043] In this application, it will be understood by those skilled in the art that the function performed by an assembly can be performed by one assembly, multiple assemblies, one part, or multiple parts. Similarly, the function performed by a part can also be performed by one part, one assembly, or a combination of multiple parts.

[0044] In the present application, the terms "upper", "lower", "left", "right", "front", "back" and other directional words are described based on the orientation and positional relationship shown in the accompanying drawings, and should not be understood as limiting the embodiments of the present application. In addition, in the context, it is also necessary to understand that when it is mentioned that an element is connected to another element "upper" or "lower", it can not only be directly connected to the other element "upper" or "lower", but also be indirectly connected to the other element "upper" or "lower" through an intermediate element. It should also be understood that directional words such as upper side, lower side, left side, right side, front side, back side, etc. not only represent the positive orientation, but can also be understood as the lateral orientation. For example, below can include directly below, lower left, lower right, lower front and lower back, etc.

[0045] See also Figures 1 to 4This embodiment provides an unwinding mechanism for retracting and unwinding a roll-up arm 100, which is equipped with a solar cell panel. The unwinding mechanism includes a carrier 1, a rotating shaft 2, and multiple guides 3. The rotating shaft 2 is rotatably mounted on the carrier 1, and one end of the roll-up arm 100 is fixed to the rotating shaft 2. The rotating shaft 2 is used to retract and unwind the roll-up arm 100. The multiple guides 3 are distributed along the outer periphery of the rotating shaft 2 on the carrier 1 to provide guidance during the retraction and unwinding of the roll-up arm 100.

[0046] It is understood that by winding the curling arm 100 around the rotating shaft 2, the curling arm 100 can be deployed or retracted by rotating the rotating shaft 2. As a result, the solar wing using the above-mentioned deployment mechanism has a simpler overall structure and smaller size than a solar wing using a scissor-fork deployment mechanism, which can meet the space requirements of small spacecraft. It is also understood that when the curling arm 100 is deployed, that is, when the rotating shaft 2 is rotated to rotate the curling arm 100, the multiple guide portions 3 distributed around the outer periphery of the rotating shaft 2 can limit the curling arm 100, thereby preventing the curling arm 100 from excessive displacement and unloading the force.

[0047] It should be noted that the curling arm 100 is typically made of high-performance composite materials, such as carbon fiber reinforced composite materials. Carbon fiber has high specific strength (strength to density ratio) and high specific modulus (modulus to density ratio). This allows the curling arm 100 to withstand the various mechanical loads during the deployment and retraction of the solar wing while reducing its own weight. In addition, the outer layer may also have a protective coating to protect against high-energy particle radiation and atomic oxygen corrosion in the space environment.

[0048] It should also be noted that solar panels are typically attached directly to the surface of the curling arm 100. This is typically done using a special high-performance adhesive that offers high bond strength, excellent weather and temperature resistance, and is suitable for the complex conditions of the space environment. Adhesives are typically epoxy resins or silicone rubbers, which ensure a secure attachment of the panels while also providing some cushioning and shock absorption.

[0049] The unfolding speed of the solar wing is a crucial factor affecting its working stability. For this reason, the unfolding mechanism also includes a speed control component 4 arranged on the carrier 1. The speed control component 4 is used to control the rotation speed of the rotating shaft 2 so that the curling arm 100 unfolds at a uniform speed. When the curling arm 100 unfolds too quickly, the speed control component 4 increases the resistance applied to the rotating shaft 2 to limit the rotation speed of the rotating shaft 2, thereby limiting the unfolding speed. Conversely, when the curling arm 100 unfolds too slowly, the speed control component 4 reduces the resistance applied to the rotating shaft 2 to ensure the unfolding speed. With this arrangement, the speed control component 4 controls the rotation speed of the rotating shaft 2 in real time, which can ensure that the curling arm 100 unfolds at a uniform speed.

[0050] Specifically, speed control element 4 includes a rotary damper, which acts on rotating shaft 2. The rotary damper primarily consists of damping oil and a reduction plate, which is coaxially mounted at the end of rotating shaft 2. During deployment, friction between the damping oil and the reduction plate generates resistance. It should be noted that rotary dampers are conventional technology and will not be described in detail.

[0051] To ensure the stability of the curling arm 100 after unfolding, the rotating shaft 2 in the unloaded state needs to be fixed to prevent it from rotating. To this end, in this embodiment, the unfolding mechanism includes a locking assembly 5, which is configured to lock the curling arm 100 in the unfolded state.

[0052] Specifically, the locking assembly 5 includes a locking hole 51 and a locking pin 52. The locking hole 51 is provided on the rotating shaft 2. The locking pin 52 is slidably provided on the carrier 1 and can be inserted into the locking hole 51. This arrangement secures the rotating shaft 2 by inserting the locking pin 52 into the locking hole 51, resulting in a simple structure and low cost.

[0053] To prevent wear on the curling arm 100 when the guide portion 3 limits the position of the curling arm 100 during deployment, the guide portion 3 is provided with at least one guide wheel 31. In this embodiment, four guide portions 3 are provided, each with a guide wheel 31. It will be appreciated that the guide wheels 31 convert the sliding friction between the curling arm 100 and the guide portion 3 into rolling friction, significantly reducing friction and thereby reducing wear.

[0054] It is worth noting that the guide wheel 31 is preferably set to a cylindrical shape so that when it contacts the guided object (that is, the curling arm 100 in this embodiment), it is line contact or point contact. Compared with the contact of a larger area when the object slides directly on a plane, the contact mode of the guide wheel 31 enables the pressure and friction to be dispersed at multiple points on the circumference or on a line. In addition, the guide wheel 31 is usually made of a material with good wear resistance. For example, high-strength alloy steel, ceramic material or oil-containing bearing material is used. The alloy steel guide wheel 31 has high hardness and strength, and can withstand greater pressure and friction without being easily deformed and worn. The ceramic guide wheel 31 has higher hardness and good chemical stability, and can maintain a low wear rate even in some corrosive environments. The guide wheel 31 made of oil-containing bearing material contains lubricating oil inside, which can automatically lubricate during operation to further reduce friction and wear.

[0055] In this embodiment, the supporting member 1 includes two support plates 11 arranged opposite to each other, and the two support plates 11 are arranged on the main body of the spacecraft, and the two ends of the rotating shaft 2 are respectively mounted on the two support plates 11. It can be understood that the rotating shaft 2 is supported by two support plates 11 arranged opposite to each other, which has a simple structure and occupies a small space. In addition, by placing the rotating shaft 2 on two support plates 11 arranged opposite to each other, the weight of the rotating shaft 2 can be evenly shared by the two support plates 11, thereby avoiding structural deformation or fatigue damage caused by excessive local force. It can also be understood that the two support plates 11 restrict the rotating shaft 2 from opposite directions, which can effectively prevent the rotating shaft 2 from tilting or offsetting in the horizontal direction, so as to curb the rotating shaft 2 from being offset by various external forces, such as axial force, radial force, etc.

[0056] Furthermore, the carrier 1 also includes a top plate 12 and a side plate 13. The upper sides of the two support plates 11 are connected through the top plate 12, and the same side of the two support plates 11 is connected through the side plate 13, so that the two support plates 11, the top plate 12 and the side plates 13 enclose a accommodating space, and the curling arm 100 is located in the accommodating space after being rolled up.

[0057] With such an arrangement, the accommodation space enclosed by the two support plates 11, the top plate 12 and the side plates 13 accommodates the rolled-up curling arm 100, which can provide certain protection for the curling arm 100. Specifically, they can prevent the curling arm 100 from being damaged by collision or squeezing of external objects. For example, during transportation, if there is a bump or impact by other objects, the accommodation space can serve as a barrier to buffer the external impact force and protect the curling arm 100 from damage. At the same time, in some harsh working environments, such as in an outdoor environment with sand, dust and flying stones or in an industrial processing environment with debris and particles, the accommodation space can prevent these foreign objects from entering, avoiding erosion and damage to the curling arm 100.

[0058] In addition, the space enclosed by the two support plates 11, the top plate 12, and the side plates 13 can be customized according to the shape and size of the rolled-up arm 100, so that the rolled-up arm 100 can be tightly placed in this accommodating space. This compact layout method effectively utilizes space, especially when the overall structure of the equipment has high space requirements. It is more suitable for limited internal spaces such as spacecraft and can avoid space waste. For example, in the design of the solar wing storage of a satellite, by rationally designing these support plates 11, the top plate 12, and the side plates 13, the rolled-up solar wing can be neatly stored in the limited spacecraft, leaving enough space for other equipment.

[0059] Furthermore, the size and shape of the storage space can be adjusted to accommodate the different sizes and shapes of the curling arms 100. By varying parameters such as the spacing between the support plates 11 and the height and length of the top plate 12 and side plates 13, the storage space can be tailored to accommodate various curling arms 100. This is like customizing a unique "storage box" to accommodate any small, simple curling arm 100 or a large, complex one.

[0060] In this embodiment, each end of the rotating shaft 2 is mounted on two support plates 11 via an angular contact ball bearing 21 to ensure smooth rotation. Furthermore, the unfolding mechanism further includes a sleeve 22 that is sleeved onto the rotating shaft 2 and is used to wind the curling arm 100. With this arrangement, when the rotating shaft 2 rotates during operation, the sleeve 22 can serve as an intermediate isolation layer, preventing direct friction between the rotating shaft 2 and the curling arm 100, thereby preventing wear and damage to the curling arm 100. It should be noted that in this embodiment, the locking hole 51 is provided on the sleeve 22. Of course, in other embodiments where the sleeve 22 is not provided, the locking hole 51 is provided directly on the rotating shaft, so this will not be described in detail.

[0061] This embodiment further provides a spacecraft comprising a drive element and the aforementioned deployment mechanism. The drive element is configured to rotate the rotation axis 2 of the deployment mechanism. It will be appreciated that the spacecraft including the aforementioned deployment mechanism is compact, meeting the requirements of miniaturized design. It should be noted that the drive element may employ any type of rotary drive mechanism, such as a servo motor, and this embodiment imposes no specific requirements or limitations thereon.

[0062] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention and are not intended to limit the embodiments of the present invention. A person skilled in the art would be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is not necessary and impossible to enumerate all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. An unfolding mechanism for retracting and unreeling a curling arm (100), characterized in that: The deployment mechanism comprises: Carrying member (1); A rotating shaft (2) is rotatably mounted on the carrier (1), one end of the curling arm (100) is fixed on the rotating shaft (2), and the rotating shaft (2) is used to retract and unreel the curling arm (100); A plurality of guide portions (3) are distributed on the carrier (1) along the periphery of the rotating shaft (2), and the plurality of guide portions (3) are used to provide guidance during the process of retracting and unreeling the curling arm (100); The unfolding mechanism further comprises a speed control component (4) provided on the carrier (1), wherein the speed control component (4) is used to control the rotation speed of the rotating shaft (2); The deployment mechanism comprises a locking assembly (5), the locking assembly (5) being configured to lock the curling arm (100) in a deployed state; The locking assembly (5) comprises: A locking hole (51) is provided on the rotating shaft (2); A locking pin (52) is slidably disposed on the carrier (1), and the locking pin (52) can be inserted into the locking hole (51); The bearing member (1) comprises two supporting plates (11) arranged opposite to each other, the two supporting plates (11) being arranged on the main body of the spacecraft, and the two ends of the rotating shaft (2) being respectively mounted on the two supporting plates (11); The unfolding mechanism further comprises a sleeve (22) sleeved on the rotating shaft (2), and the sleeve (22) is used to roll up the curling arm (100).

2. The deployment mechanism according to claim 1, characterized in that: The speed control component (4) comprises a rotation damper, and the rotation damper acts on the rotating shaft (2).

3. The deployment mechanism according to claim 1, characterized in that: At least one guide wheel (31) is provided on the guide portion (3).

4. The deployment mechanism according to claim 1, characterized in that: The carrier (1) further comprises a top plate (12) and a side plate (13), wherein the upper sides of the two support plates (11) are connected via the top plate (12), and the same side of the two support plates (11) is connected via the side plate (13), so that the two support plates (11), the top plate (12) and the side plate (13) enclose a receiving space, and the curling arm (100) is located in the receiving space after being rolled up.

5. A spacecraft, characterized in that: It comprises a driving member and the unfolding mechanism according to any one of claims 1 to 4, wherein the driving member is used to drive the rotating shaft (2) of the unfolding mechanism to rotate.

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