Antenna Deployment and Positioning Mechanism Test Assembly and Verification of In-Orbit Unlocking State Linkage Device

Abstract

The present invention provides a linkage device for testing and assembling an antenna deployment and positioning mechanism and verifying an unlocked state on track, comprising a connection disk and an unlocking lever, wherein the bottom of the connection disk is connected to a positioning base through a support rod, the bottom of the positioning base is connected to a test platform, a plurality of connection hole groups for installing a tested object are evenly distributed above the connection disk, a ratchet turntable is provided above the connection disk, and the two are coaxially arranged, a plurality of gears are evenly distributed on the ratchet turntable, each gear is fixedly connected to an unlocking lever, the unlocking lever is used to verify the unlocking function of the on-track state, the bottom of the ratchet turntable is fixed to the rotating shaft of the rotating unit motor, and the housing of the rotating unit motor is fixedly arranged, and the rotating unit motor is powered by an external power supply. The linkage device for testing and assembling an antenna deployment and positioning mechanism and verifying an unlocked state on track described in the present invention effectively verifies the smoothness of the friction pair during the reciprocating motion, improves the efficiency of batch production assembly, debugging and running-in, and improves the on-track stability.

Description

Technical Field

[0001] The invention belongs to the technical field of precise assembly and testing of aerospace microwave antennas, and particularly relates to a linkage device for testing, assembling and verifying the on-orbit unlocking state of an antenna deployment positioning mechanism. Background Art

[0002] In the aerospace field, microwave products are essential equipment for various spacecraft to achieve communication and data transmission. The antenna is in a retracted state during the satellite launch phase. After the satellite enters the orbit, the locking device is released, and the antenna deployment positioning mechanism drives the antenna to slowly deploy. The main function of the deployment positioning mechanism is to lock the antenna in the working position and send out the antenna locking telemetry signal. The assembly, testing accuracy and the smoothness of the reciprocating motion of this component directly affect the reliability of the on-board antenna product. Whether it can be normally deployed and locked is the key factor for the antenna to work properly.

[0003] Traditional antenna deployment positioning mechanisms mainly verify the assembly accuracy and the smoothness of the friction pair during the reciprocating motion by manually pushing and pulling and running-in after the assembly is completed. However, due to the inconsistent pulling force applied each time during the manual pushing and pulling process and the different force application directions of the components, the reliability of the assembly and test verification is poor and the manual consumption is large. Therefore, it has become an urgent problem to improve the accuracy of part assembly and post-assembly accuracy verification, verify the on-orbit unlocking state of the product and the unlocking function during the assembly test process, reduce the inconsistency of manual operations, and reduce the labor intensity of personnel.

[0004] Currently, there are various specifications for antenna deployment positioning mechanisms, and the antenna deployment positioning mechanisms required for each antenna are mostly used in pairs. Therefore, the state compliance and consistency of the antenna deployment positioning mechanisms used in pairs are crucial. Therefore, the linkage test of antenna deployment positioning mechanisms with different specifications also increases the difficulty of the assembly and testing process. Summary of the Invention

[0005] In view of this, the present invention aims to provide a linkage device for testing, assembling and verifying the on-orbit unlocking state of an antenna deployment positioning mechanism to solve the problems of poor reliability, large manual consumption and easy occurrence of inconsistencies in the prior art.

[0006] To achieve the above object, the technical solution of the present invention is realized as follows:

[0007] An antenna deployment positioning mechanism test assembly and verification on-orbit unlocking state linkage device, including a connection disk and an unlocking lever. The connection disk is connected to a positioning base through a support rod below. The bottom of the positioning base is connected to a test platform. A plurality of connection hole groups for installing test pieces are evenly distributed above the connection disk. A ratchet turntable is provided above the connection disk, and the two are coaxially arranged. A plurality of gears are evenly distributed on the ratchet turntable, and each gear is fixedly connected to an unlocking lever. The unlocking lever is used to verify the unlocking function of the on-orbit state. The ratchet turntable is fixedly connected to the rotating shaft of the rotating unit motor below, and the housing of the rotating unit motor is fixedly arranged. The rotating unit motor is powered by an external power supply.

[0008] Further, the connection disk is a circular ring structure with a central hole in the center. A plurality of second connection holes are evenly distributed circumferentially on the inner edge of the connection disk, and a plurality of first connection holes are evenly distributed on the outer edge.

[0009] Further, a plurality of countersunk screw holes are evenly distributed on the upper plane of the positioning base, and a plurality of connection threaded holes are evenly distributed on the lower plane.

[0010] Further, there is a threaded hole at each end of the support rod.

[0011] Further, the two ends of the support rod are respectively connected to the countersunk screw holes and the first connection holes.

[0012] Further, the ratchet turntable is provided with a ratchet connection hole and a boss in the center. A plurality of first ratchet connection holes are evenly distributed circumferentially on the boss. A plurality of gears are evenly distributed outside the ratchet turntable, and each gear is provided with a second ratchet connection hole.

[0013] Further, the unlocking lever includes a left part and a right part of an integral structure, and a step is formed at the junction of the left part and the right part. An unlocking lever connection hole is provided on the left part, and the unlocking lever connection hole is used for bolt connection with the second ratchet connection hole.

[0014] Compared with the prior art, the antenna deployment positioning mechanism test assembly and verification on-orbit unlocking state linkage device of the present invention has the following advantages:

[0015] (1) The test assembly and verification in-orbit unlocking state linkage device of the antenna deployment positioning mechanism described in the present invention makes full use of the levelness of the upper end face of the connecting plate. The ratchet turntable, the rotating unit motor, and the connecting plate can be accurately and reliably connected with the cooperation of set screws and positioning pins. With the support rod, connecting plate, rotating unit motor, ratchet turntable, unlocking lever, connecting screw, and set pin in this structure, it can meet the assembly accuracy of the installation dimensions of different series of antenna deployment positioning mechanisms, enabling the paired antenna deployment positioning mechanisms to simultaneously conduct in-orbit verification deployment tests, ensuring that the driving forces and sliding resistances of the two tested parts are the same. It has the advantages of high assembly accuracy, simple operation, quick clamping, reliable positioning, strong stability, high safety factor, and greatly reducing the labor intensity of operators.

[0016] (2) The test assembly and verification in-orbit unlocking state linkage device of the antenna deployment positioning mechanism described in the present invention verifies the smoothness of the friction pair during the reciprocating motion process, improves the batch production assembly, debugging, and running-in efficiency, and enhances the in-orbit stability.

[0017] (3) The test assembly and verification in-orbit unlocking state linkage device of the antenna deployment positioning mechanism described in the present invention is provided with threaded holes on the support rod. In the case of thread wear, it is convenient for local replacement. That is, the support rod can be replaced without affecting and replacing the connecting plate and the positioning base, reducing the maintenance cost. Moreover, after the thread specification is adjusted, the specification of the support rod is also convenient to adjust, facilitating the cooperation with antenna deployment positioning mechanisms of different numbers and weights, and expanding the scope of application.

[0018] (2) The test assembly and verification in-orbit unlocking state linkage device of the antenna deployment positioning mechanism described in the present invention connects the positioning base and the connecting plate through the support rod, optimizes the overall weight, reduces the handling work intensity, and at the same time, the rotating unit motor can be embedded in the middle, making the tooling structure compact and avoiding interference during the process of fixing the positioning base to the test platform connecting plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0020] Figure 1 is a side view of the test assembly and verification in-orbit unlocking state linkage device of the antenna deployment positioning mechanism described in the embodiment of the present invention;

[0021] Figure 2 is a front view of the test assembly and verification in-orbit unlocking state linkage device of the antenna deployment positioning mechanism described in the embodiment of the present invention;

[0022] Figure 3Top view of the connection plate described in the embodiments of the present invention;

[0023] Figure 4 Bottom view of the connection plate described in the embodiments of the present invention;

[0024] Figure 5 Cross-sectional view of the support rod described in the embodiments of the present invention;

[0025] Figure 6 Top view of the positioning base described in the embodiments of the present invention;

[0026] Figure 7 Schematic diagram of the ratchet turntable described in the embodiments of the present invention;

[0027] Figure 8 Schematic diagram of the unlocking lever described in the embodiments of the present invention.

[0028] Explanation of reference numerals:

[0029] 1 - Test piece; 2 - Connection plate; 3 - Support rod; 4 - Positioning base; 5 - Rotating unit motor; 6 - Power supply lead; 7 - Ratchet turntable; 8 - Set screw; 9 - Screw; 10 - Unlocking lever; 11 - Connecting screw. Detailed implementation manners

[0030] 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.

[0031] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "up", "down", "front", "back", "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 number 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.

[0032] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0033] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0034] Test and assemble the antenna deployment positioning mechanism and verify the on-orbit unlocking state linkage device, such as Figures 1 to 8 As shown, it includes a connecting disk 2, a support rod 3, a positioning base 4, a rotating unit motor 5, a ratchet turntable 7, a locking pin 8, an unlocking lever 10, and a connecting screw 11. The lower part of the connecting disk 2 is connected to the positioning base 4 through the support rod 3. The bottom of the positioning base 4 is connected to the test platform. A plurality of connecting hole groups 22 for installing the tested piece 1 are evenly distributed above the connecting disk 2. A ratchet turntable 7 is provided above the connecting disk 2, and the connecting disk 2 and the ratchet turntable 7 are coaxially arranged. A plurality of gears are evenly distributed on the ratchet turntable 7, each gear is fixedly connected to an unlocking lever 10, and the unlocking lever 10 is used to verify the unlocking function of the on-track state. The lower part of the ratchet turntable 7 is fixed to the rotating shaft of the rotating unit motor 5, and the housing of the rotating unit motor 5 is fixedly installed between the positioning base 4 and the connecting disk 2. The rotating unit motor 5 is powered by an external power supply, and the external power supply provides a rotational torque for the rotating unit motor 5. The rotating unit motor 5 drives the ratchet turntable 7 to rotate, thereby driving the unlocking lever 10 to move the tested part to complete the unlocking function of verifying the on-track state.

[0035] This solution makes full use of the horizontality of the upper end surface of the connecting disk 2. The ratchet turntable 7 and the rotating unit motor 5 and the connecting disk 2 can be accurately positioned and reliably connected with the set screws and positioning pins. With the support rod 3, connecting disk 2, rotating unit motor 5, ratchet turntable 7, unlocking lever 10, connecting screws, and setting pins in this structure, the assembly accuracy of different series of antenna deployment positioning and installation size specifications can be met, and the paired antenna deployment positioning mechanisms can be simultaneously carried out on-orbit verification deployment tests to ensure that the driving force and sliding resistance of the two tested parts are the same, which can improve the matching accuracy, simple operation, fast clamping, reliable positioning, strong stability, high safety factor, and greatly reduce the labor intensity of the operator.

[0036] The lower end of the rotating unit motor 5 includes a power lead 6, which is connected to an external power source to provide power for the rotating unit motor 5, and is used to provide torque for the rotation of the ratchet turntable 7 for subsequent verification of the unlocking function.

[0037] The connecting plate 2 is a ring structure with a central hole 24 in the center. A number of second connecting holes 23 are circumferentially and evenly distributed on the inner edge of the connecting plate 2, and a number of first connecting holes 21 are evenly distributed on the outer edge.

[0038] Preferably, the number of the connecting hole groups 22 on the connecting plate 2 is 6 groups, and the connecting hole groups 22 are used to connect with the test piece 1.

[0039] A number of countersunk screw holes 41 are evenly distributed on the upper plane of the positioning base 4, and each countersunk screw hole 41 is used to fixedly connect with a support rod 3; a number of connecting threaded holes are evenly distributed on the lower plane of the positioning base 4, and the connecting threaded holes are used to connect with the test platform to ensure firm fixation in the tank body.

[0040] Preferably, the number of the countersunk screw holes 41 is 6.

[0041] There is a threaded hole at each end of the support rod 3. In this solution, threaded holes are provided on the support rod 3. In the case of thread wear, it is convenient to perform local replacement. In this way, without affecting and replacing the connecting plate and the positioning base, the support rod 3 can be replaced, reducing the maintenance cost. Moreover, after the thread specification is adjusted, the specification of the support rod 3 is also convenient to adjust, facilitating the cooperation with the antenna deployment positioning mechanism of different numbers and weights, and expanding the scope of application. In one or more embodiments, the two ends of the support rod 3 are respectively connected to the countersunk screw holes 41 and the first connecting holes 21 through an internal hexagon countersunk head screw.

[0042] In this solution, the positioning base 4 and the connecting plate 2 are connected through the support rod 3. For the overall weight optimization, the handling work intensity is reduced. At the same time, the rotating unit motor 5 can be embedded in the middle, making the tooling structure compact and avoiding interference during the process of fixing the positioning base 4 to the test platform connecting plate.

[0043] There is a ratchet connection hole 73 and a boss in the center of the ratchet turntable 7. A number of first ratchet connection holes 71 are circumferentially and evenly distributed on the boss. A number of gears are evenly distributed outside the ratchet turntable 7, and each gear is provided with a second ratchet connection hole 72. In this embodiment, the number of gears is 6. The inner diameters of the central hole 24 and the ratchet connection hole 73 are the same.

[0044] The unlocking lever 10 includes a left part 103 and a right part 102 of an integral structure, and a step 104 is formed at the junction of the left part 103 and the right part 102. An unlocking lever connection hole 101 is provided on the left part 103. The set step 104 can be in full contact with the retaining pins of the test piece 1, making the force-receiving surface of the unlocking lever 10 uniform.

[0045] The second ratchet connection hole 72 and the unlocking lever connection hole 101 are connected through a connection screw 9.

[0046] The rotating unit motor 5 can be a common servo motor or a stepper motor.

[0047] In this embodiment, after the upper part of the rotating unit motor 5 passes through the center hole 24 and the ratchet connecting hole 73 from bottom to top in sequence, a number of No. 1 motor connecting holes 51 are evenly distributed on the rotating shaft of the rotating unit motor 5, and each motor connecting hole 51 is aligned with a No. 1 ratchet connecting hole 71 and fixedly connected by a locking pin 8, so that the rotating unit motor 5 drives the ratchet turntable 7 to rotate, and a number of No. 2 motor connecting holes 52 are evenly distributed on the shell of the rotating unit motor 5, and each No. 2 motor connecting hole 52 is connected to a No. 2 connecting hole 23 by bolts or screws.

[0048] The working principle of the antenna deployment and positioning mechanism test assembly and verification on-track unlocking state linkage device is as follows: the tested piece 1 is connected to the connection hole group 22 through the fixing screw 11, so that the tested part of the tested piece 1 corresponds to the movement direction of the unlocking lever 10, the power lead 6 is connected to the external power supply, and the rotating unit motor 5 is powered, the rotating unit motor 5 drives the ratchet turntable 7 to rotate, and the ratchet turntable 7 drives the unlocking lever 10 to move the corresponding part of the tested piece 1, completing the unlocking function of verifying the on-track state. This scheme ensures assembly accuracy, simple operation, fast clamping, reliable positioning, strong stability, high safety factor, and greatly reduces the labor intensity of the operator. At the same time, it can verify the on-track unlocking function of the antenna deployment and positioning mechanism, thereby achieving the effect of precise assembly of the stop pin and the slider of the tested piece 1, and improving the on-track stability. A kind of antenna deployment and positioning mechanism test assembly and verification on-track unlocking state linkage device, which unifies the test conditions and unlocking driving force for the antenna deployment and positioning mechanism used in pairs.

[0049] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. Test and assemble the antenna deployment positioning mechanism and verify the on-orbit unlocking state linkage device, Features: It includes a connecting disk and an unlocking lever. The bottom of the connecting disk is connected to the positioning base through a supporting rod. The bottom of the positioning base is connected to the test platform. A plurality of connecting hole groups for installing the test piece are evenly distributed above the connecting disk. A ratchet turntable is provided above the connecting disk, and the two are coaxially arranged. A plurality of gears are evenly distributed on the ratchet turntable, and each gear is fixedly connected to an unlocking lever. The unlocking lever is used to verify the unlocking function of the on-track state. The bottom of the ratchet turntable is fixed to the rotating shaft of the rotating unit motor, and the housing of the rotating unit motor is fixedly arranged. The rotating unit motor is powered by an external power supply.

2. The antenna deployment positioning mechanism test assembly and verification on-orbit unlocking state linkage device according to claim 1, Features: The connecting disk is a circular ring structure with a center hole in the center. The inner edge of the connecting disk is evenly distributed with a number of No. 2 connecting holes in the circumferential direction, and the outer edge is evenly distributed with a number of No. 1 connecting holes.

3. The antenna deployment positioning mechanism test assembly and verification on-orbit unlocking state linkage device according to claim 2, Features: A plurality of countersunk screw holes are evenly distributed on the upper plane of the positioning base, and a plurality of connecting threaded holes are evenly distributed on the lower plane.

4. The antenna deployment positioning mechanism test assembly and verification on-orbit unlocking state linkage device according to claim 1, Features: There is a threaded hole at each end of the support rod.

5. The antenna deployment positioning mechanism test assembly and verification on-orbit unlocking state linkage device according to claim 3, Features: Both ends of the support rod are connected to the countersunk screw hole and the No. 1 connecting hole respectively.

6. The antenna deployment positioning mechanism test assembly and verification on-orbit unlocking state linkage device according to claim 1, Features: A ratchet connecting hole and a boss are arranged at the center of the ratchet turntable, a number of first ratchet connecting holes are evenly distributed around the boss, a number of gears are evenly distributed outside the ratchet turntable, and each gear is provided with a number two ratchet connecting hole.

7. The antenna deployment positioning mechanism test assembly and verification on-orbit unlocking state linkage device according to claim 6, Features: The unlocking lever comprises a left part and a right part of an integral structure, and a step is formed at the junction of the left part and the right part. An unlocking lever connecting hole is provided on the left part, and the unlocking lever connecting hole is used for bolt connection with the No. 2 ratchet connecting hole.

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