Time sequence control structure and hinge mechanism matched with same
By introducing a timing control structure into the hinge mechanism, the expansion sequence of the expansion plate is controlled by using the timing cam and timing roller components, the collision problem of the expansion plate caused by the inability to control the hinge mechanism is solved, and the attitude control accuracy of the satellite platform is improved.
Patent Information
- Application Number
- CN202421883559.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-06
- Publication Date
- 2025-06-03
- Estimated Expiration
- 2034-08-06
AI Technical Summary
The existing hinge mechanism cannot be controlled during the satellite deployment process, resulting in collisions between the internal and external deployment plates and cannot meet the requirements of high attitude control accuracy.
A timing control structure is designed, including two sets of expansion timing control mechanisms, which are installed on the low hinge mechanism and the high hinge mechanism respectively. The timing cam and timing roller assembly are used to control the expansion order of the expansion plate through the contact and disengagement of the timing roller assembly with the timing cam to avoid collisions.
The deployment process is controlled, which avoids collisions caused by the simultaneous deployment of the inner and outer deployment boards, improves the attitude control accuracy of the satellite platform, and enhances practicality.
Smart Images
Figure CN222934095U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the field of deployment mechanisms for planar phased array antennas, and in particular relates to a timing control structure and a matching hinge mechanism therefor. Background Art
[0002] The hinge mechanism is a key component of the satellite deployment mechanism, which can realize two functions of rotational motion and in-place locking. The hinge is mainly used for the connection between antenna panels or solar cell wings. It can be folded during the launch section, withstand and transmit the mechanical loads during the active section of satellite launch, realize the deployment and locking functions after entering the orbit, and have a certain locking stiffness to meet the frequency requirements.
[0003] Currently, when the hinge mechanism deploys the satellite deployment mechanism, the hinge mechanism cannot control the deployment process, resulting in the problem that the inner and outer deployment plates deploy simultaneously and collide. In addition, due to the large size and weight of the SAR antenna itself, the general single array size is greater than 1 meter and the weight is greater than 20 kg. When imaging the ground in orbit, higher requirements are imposed on the attitude control accuracy of the satellite platform, while the existing hinges cannot meet the above requirements. Summary of the Utility Model
[0004] In view of this, the present utility model aims to provide a timing control structure and a matching hinge mechanism therefor to solve at least one of the problems existing in the above-mentioned prior art.
[0005] To achieve the above object, the technical solution of the present utility model is realized as follows:
[0006] In a first aspect, the present utility model provides a timing control structure, which includes two sets of deployment timing control mechanisms, and the two sets of deployment timing control mechanisms are respectively installed on two sets of low hinge mechanisms and two sets of high hinge mechanisms;
[0007] The deployment timing control mechanism includes a timing cam and a timing roller assembly. The timing cam is installed on the high hinge mechanism, and the timing roller assembly is installed on the low hinge mechanism.
[0008] Further, one end of the timing roller assembly is installed with a roller, and the roller can roll relatively after contacting the timing cam to reduce the frictional resistance.
[0009] Further, there is at least a 5 mm gap reserved between the timing roller assembly and the timing cam.
[0010] In a second aspect, based on the same inventive concept, the present utility model also provides a hinge mechanism, which includes two sets of low hinge mechanisms and two sets of high hinge mechanisms. The two sets of low hinge mechanisms and two sets of high hinge mechanisms are all installed on the phased array antenna subarray; the timing cam is installed on the high hinge mechanism, and the timing roller assembly is installed on the low hinge mechanism.
[0011] Further, the phased array antenna subarray includes a body-mounted subarray, an inner deployment plate, and an outer deployment plate arranged in sequence from top to bottom. The inner deployment plate is mounted to the satellite platform through two sets of symmetrically distributed low hinge mechanisms, and the outer deployment plate is mounted to the satellite platform through two sets of symmetrically distributed high hinge mechanisms.
[0012] Compared with the prior art, the timing control structure and its adapted hinge mechanism of the present invention have the following advantages:
[0013] For the timing control structure and its adapted hinge mechanism of the present invention, the timing control structure can control the deployment process, solve the problem of collision when the inner and outer deployment plates are deployed simultaneously, and the hinge mechanism can improve the attitude control accuracy of the satellite platform by installing the timing control structure, with strong practicability. Description of the Drawings
[0014] The drawings forming a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments and descriptions thereof of the present invention are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:
[0015] Figure 1 Schematic diagram of installing the timing control structure and its adapted hinge mechanism described in the embodiment of the present invention to the phased array antenna subarray;
[0016] Figure 2 Schematic diagram of the deployment timing control mechanism described in the embodiment of the present invention;
[0017] Figure 3 Schematic diagram of the first process of the deployment timing control mechanism described in the embodiment of the present invention controlling the deployment sequence of the inner deployment plate and the outer deployment plate;
[0018] Figure 4 Schematic diagram of the second process of the deployment timing control mechanism described in the embodiment of the present invention controlling the deployment sequence of the inner deployment plate and the outer deployment plate;
[0019] Figure 5 Schematic diagram of the third process of the deployment timing control mechanism described in the embodiment of the present invention controlling the deployment sequence of the inner deployment plate and the outer deployment plate;
[0020] Figure 6 Schematic diagram of the first process of the unlocking and releasing process of the spaceborne planar phased array antenna described in the embodiment of the present invention;
[0021] Figure 7 Schematic diagram of the second process of the unlocking and releasing process of the spaceborne planar phased array antenna described in the embodiment of the present invention;
[0022] Figure 8These are the three schematic diagrams of the unlocking and releasing process of the spaceborne planar phased array antenna according to the embodiments of the present invention;
[0023] Figure 9 These are the four schematic diagrams of the unlocking and releasing process of the spaceborne planar phased array antenna according to the embodiments of the present invention.
[0024] Explanation of reference numerals:
[0025] 1. Satellite platform; 2. Lower hinge mechanism; 3. Upper hinge mechanism; 4. Inner deployment plate; 5. Outer deployment plate; 6. Deployment timing control mechanism; 61. Timing cam; 62. Timing roller assembly; 7. Body-mounted sub-array. Detailed implementation manners
[0026] It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments may be combined with each other.
[0027] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more.
[0028] In the description of the present invention, it should be noted that, unless otherwise clearly defined and limited, the terms "mounted", "connected", "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood through specific situations.
[0029] The present invention will be described in detail below with reference to the drawings and in combination with the embodiments.
[0030] As Figures 1 to 9As shown in the figure, a timing control structure includes two sets of unfolding timing control mechanisms 6, and the two sets of unfolding timing control mechanisms 6 are respectively installed on two sets of low hinge mechanisms 2 and two sets of high hinge mechanisms 3;
[0031] The unfolding timing control mechanism 6 includes a timing cam 61 and a timing roller assembly 62. The timing cam 61 is installed on the high hinge mechanism 3, and the timing roller assembly 62 is installed on the low hinge mechanism 2.
[0032] In a preferred embodiment of the present invention, a roller is installed at one end of the timing roller assembly 62, and relative rolling can occur after the roller contacts the timing cam 61 to reduce the frictional resistance.
[0033] In a preferred embodiment of the present invention, when the phased array antenna is in the retracted and compressed state, there is at least a 5 mm gap between the timing roller assembly 62 and the timing cam 61 to prevent the two from colliding during the launch vibration process.
[0034] A hinge mechanism adapted to the timing control structure includes two sets of low hinge mechanisms 2 and two sets of high hinge mechanisms 3. The two sets of low hinge mechanisms 2 and two sets of high hinge mechanisms 3 are both installed on the phased array antenna subarray; the timing cam 61 is installed on the high hinge mechanism 3, and the timing roller assembly 62 is installed on the low hinge mechanism 2;
[0035] The phased array antenna subarray includes a body-mounted subarray 7, an inner unfolding plate 4, and an outer unfolding plate 5 arranged in sequence from top to bottom. The inner unfolding plate 4 is installed on the satellite platform 1 through 2 sets of symmetrically distributed low hinge mechanisms 2, and the outer unfolding plate 5 is installed on the satellite platform 1 through 2 sets of symmetrically distributed high hinge mechanisms 3.
[0036] In this embodiment, the low hinge mechanism 2 and the high hinge mechanism 3 are mainly passive unfolding hinges most commonly used in aerospace. The hinge mechanism is used for the connection between the antenna plates; the retracted configuration of the antenna determines that after unlocking by the existing compression release device, the outermost outer unfolding plate 5 needs to be unfolded first, and then the middle inner unfolding plate 4 is unfolded. The unfolding timing control mechanism 6 can control the outer unfolding plate 5 to be unfolded by more than 90° first, and then the inner unfolding plate 4 starts to unfold to prevent collision during simultaneous unfolding.
[0037] Figure 3 、 Figure 4 、 Figure 5 When it is the process of the unfolding timing control mechanism 6 controlling the unfolding sequence of the inner unfolding plate 52 and the outer unfolding plate 5. It is mainly divided into three steps: The first step is as Figure 3, after the compression release device is unlocked and released, both the inner deployment plate 4 and the outer deployment plate 5 are deployed under the action of the hinge mechanism. However, when the timing roller assembly 62 installed on the low hinge mechanism 2 contacts the timing cam 61 installed on the high hinge mechanism 3, the timing cam 61 will block the movement of the timing roller assembly 62, and the inner deployment plate 4 cannot be deployed; The second step is as follows Figure 4 , the outer deployment plate 5 continues to deploy. Within the first 90° of deployment, the timing cam 61 will continuously block the movement of the timing roller assembly 62, and the rollers of the timing roller assembly 62 will roll relative to the timing cam 61 to maintain low resistance, and the inner deployment plate 4 cannot be deployed; The third step is as follows Figure 5 , after the outer deployment plate 5 continues to deploy beyond the 90° range, the timing cam 61 disengages from blocking the timing roller assembly 62, and other components of the high hinge mechanism 3 will not block the timing roller assembly 62 during its deployment, and the inner deployment plate 4 is deployed.
[0038] Figure 6 、 Figure 7 、 Figure 8 、 Figure 9 is the unlocking and releasing process of the entire spaceborne planar phased array antenna. It is mainly divided into four steps. The first step is to unlock through the compression release device; The second step is as follows Figure 6 , the outer deployment plate 5 is deployed under the action of the high hinge mechanism 3. Within the first 90° of deployment, the timing cam 61 will continuously block the movement of the timing roller assembly 62, and the inner deployment plate 4 cannot be deployed; The third step is as follows Figure 7 and 8 , after the outer deployment plate 5 continues to deploy beyond the 90° range, the timing cam 61 disengages from blocking the timing roller assembly 62, and other components of the high hinge mechanism 3 will not block the timing roller assembly 62 during its deployment, and the inner deployment plate 4 is deployed under the action of the low hinge mechanism 2; The fourth step is as follows Figure 9 , after the inner deployment plate 4 and the outer deployment plate 5 are successively deployed in place, they are locked in place by their respective hinge mechanisms. At this time, the body-mounted subarray 51, the inner deployment plate 4, and the outer deployment plate 5 form a coplanar surface.
[0039] When the entire spaceborne planar phased array antenna is in the retraction and clamping operation: It is mainly divided into five steps. In the first step, the satellite platform 1 is erected using the attitude adjustment tooling, and the body-mounted sub-array 51 is installed on the satellite platform 1 and fixed with screws. In the second step, two sets of low hinge mechanisms 2 and two sets of high hinge mechanisms 3 are installed on the satellite platform 1, and the coaxiality of the hinge axes and the coaxiality of the hinges with respect to the axes are adjusted to meet the requirement of not greater than 0.1 mm, and then fixed with screws. In the third step, the inner deployment plate 4 and the outer deployment plate 5 are installed on the corresponding low hinge mechanism 2 and high hinge mechanism 3 under the condition of zero gravity using the zero-gravity device, and the flatness of the front mounting planes of the three antenna plates is adjusted to be not greater than 1.4 mm, and the seam distance is 1.5 ± 0.5 mm. After the adjustment is completed, they are fastened with screws. In the fourth step, the inner deployment plate 4 and the outer deployment plate 5 are manually retracted, the compression release device is installed and the position accuracy of the compression release device is adjusted. After the adjustment is in place, it is fastened with screws and the antenna is in a compressed state. In the fifth step, under the compressed state of the antenna, the deployment timing control mechanism 6 and other subsequent operations are installed.
[0040] The unlocking and releasing process of the entire spaceborne planar phased array antenna. It is mainly divided into four steps. In the first step, when release is required, unlocking is performed through the compression release device; in the second step, as Figure 6 , the outer deployment plate 5 is deployed under the action of the high hinge mechanism 3. Within the first 90° range of deployment, the timing cam 61 will always block the movement of the timing roller assembly 62, and the inner deployment plate 4 cannot be deployed; in the third step, as Figure 7 and 8 , after the outer deployment plate 5 continues to be deployed beyond the 90° range, the timing cam 61 disengages from blocking the timing roller assembly 62, and other components of the high hinge mechanism 3 will not block the timing roller assembly 62 during its deployment process, and the inner deployment plate 4 is deployed under the action of the low hinge mechanism 2; in the fourth step, as Figure 9 , after the inner deployment plate 4 and the outer deployment plate 5 are successively deployed in place, they are locked in place by their respective hinge mechanisms. At this time, the body-mounted sub-array 51, the inner deployment plate 4, and the outer deployment plate 5 form a coplanar surface.
[0041] The above are only the preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.
Claims
1. A timing control structure, characterized in that: It comprises two sets of unfolding timing control mechanisms (6), and the two sets of unfolding timing control mechanisms (6) are respectively installed on two sets of low hinge mechanisms (2) and two sets of high hinge mechanisms (3); The unfolding timing control mechanism (6) comprises a timing cam (61) and a timing roller assembly (62); the timing cam (61) is mounted on the high hinge mechanism (3), and the timing roller assembly (62) is mounted on the low hinge mechanism (2).
2. A timing control structure according to claim 1, characterized in that: A roller is installed at one end of the timing roller assembly (62), and after the roller contacts the timing cam (61), relative rolling can occur to reduce friction resistance.
3. A timing control structure according to claim 1, characterized in that: A clearance of at least 5 mm is retained between the timing roller assembly (62) and the timing cam (61).
4. A hinge mechanism, adapted for the timing control structure according to any one of claims 1 to 3, characterized in that: The invention comprises two sets of low hinge mechanisms (2) and two sets of high hinge mechanisms (3), wherein the two sets of low hinge mechanisms (2) and the two sets of high hinge mechanisms (3) are both installed on the phased array antenna subarray; a timing cam (61) is installed on the high hinge mechanism (3), and a timing roller assembly (62) is installed on the low hinge mechanism (2).
5. A hinge mechanism according to claim 4, characterized in that: The phased array antenna subarray comprises a body-mounted subarray (7), an inner expansion plate (4) and an outer expansion plate (5) which are arranged in sequence from top to bottom; the inner expansion plate (4) is mounted on the satellite platform (1) via two sets of symmetrically distributed low hinge mechanisms (2); and the outer expansion plate (5) is mounted on the satellite platform (1) via two sets of symmetrically distributed high hinge mechanisms (3).