On-orbit spinning parabolic antenna locking release and locking device

Abstract

This invention provides an on-orbit rotating parabolic antenna locking, releasing, and locking device, including a satellite platform mounting surface, a main parabolic reflector, a connecting cylinder, a secondary reflector, a carbon fiber support tube, a No. 1 pyrotechnic component, a secondary V-shaped connector, a pyrotechnic component support cover, a carbon fiber support tube, an unfolding and locking device, a No. 1 motor, a rotating connector, a No. 1 locking and releasing device, and a No. 2 locking and releasing device. This invention employs two sets of locking and releasing devices, each with axial, radial, and unidirectional circumferential limiting designs. These two sets of circumferential limiting directions are opposite and form a 45° angle with the antenna reflector's rotation axis, balancing strength and rotational interference. During release and unfolding, a torsion spring provides the driving force and clamping force, featuring simple structure, low cost, good locking performance, and high load-bearing capacity. The device also employs a combination of three sets of locking pins and compression springs, providing axial, radial, and circumferential three-way locking capabilities, offering advantages such as simple structure, low cost, and good locking effect.

Description

Technical Field

[0001] This invention relates to the field of electrical components technology, and more specifically to an on-orbit rotating parabolic antenna locking, releasing and locking device. Background Technology

[0002] Parabolic antennas are a type of spaceborne antenna, characterized by their simple structure, strong directivity, and wide operating bandwidth. To meet the specific requirements of spaceborne radar systems, the primary and secondary reflectors of a spaceborne parabolic antenna must rotate synchronously during on-orbit operation. Furthermore, due to limitations imposed by rocket launch and satellite size, the secondary reflector in a spaceborne parabolic antenna needs to be designed as a deployable structure.

[0003] For spaceborne parabolic antennas, a locking and releasing mechanism needs to be added so that the parabolic antenna can be locked in the retracted state, the main reflector and sub-reflector can be released in the on-orbit state, the sub-reflector can be unfolded and locked, and finally the whole system can rotate synchronously.

[0004] Therefore, a locking, releasing, and locking device that meets the operational requirements of parabolic antennas is needed. Summary of the Invention

[0005] This invention addresses the need for a smooth locking, deployment, and positioning of a parabolic antenna during both the transmission and on-orbit phases. It provides an on-orbit rotating parabolic antenna locking, release, and locking device. This device employs two sets of locking and release mechanisms, each with axial, radial, and unidirectional circumferential limiting designs. The two sets of circumferential limiting directions are opposite and at a 45° angle to the antenna reflector's rotation axis, balancing strength and rotational interference. During release and deployment, a torsion spring provides both driving and clamping forces. This device features a simple structure, low cost, good locking performance, and high load-bearing capacity. Furthermore, it utilizes a combination of three sets of locking pins and compression springs, providing axial, radial, and circumferential locking capabilities, and offering advantages such as simple structure, low cost, and excellent locking effect.

[0006] This invention provides an on-orbit rotating parabolic antenna locking, releasing, and locking device, including a satellite platform mounting surface, a main parabolic reflector disposed on the satellite platform mounting surface, a linkage cylinder connected to the bottom of the main parabolic reflector, a secondary reflector disposed on the upper part of the main parabolic reflector, a carbon fiber support tube connected to the main parabolic reflector, a No. 1 pyrotechnic device connected to the upper surface of the main parabolic reflector, a secondary reflector V-shaped connector connected to the upper part of the No. 1 pyrotechnic device and the rear part of the secondary reflector, a pyrotechnic device support cover connected to the bottom of the No. 1 pyrotechnic device, an unfolding and locking device connected between the carbon fiber support tube and the main parabolic reflector, a No. 1 motor connected to the satellite platform mounting surface, a rotating connector connected between the linkage cylinder and the No. 1 motor, and a No. 1 locking and releasing device and a No. 2 locking and releasing device, one end of which is connected to the satellite platform mounting surface and the other end of which is connected to the side of the linkage cylinder.

[0007] The rotating connector is connected to the bottom of the main parabolic reflector, the secondary reflector is set on the right side of the satellite platform mounting surface through a carbon fiber support tube, and the pyrotechnic support cover is connected to the bottom of the main parabolic reflector.

[0008] During the rocket launch phase, the on-orbit rotating parabolic antenna is in a retracted and locked state. One end of the secondary reflector is connected to a carbon fiber support tube, and the other end is fixedly connected to the No. 1 pyrotechnic component via a secondary reflector V-shaped connector, thus locking the secondary reflector. The No. 1 and No. 2 locking and releasing devices fix the linkage cylinder to the main parabolic reflector, thus locking the main parabolic reflector.

[0009] During the on-orbit deployment phase, the on-orbit rotating parabolic antenna consists of two phases. During the first phase of deployment, the No. 1 pyrotechnic device is unlocked, the motor of the locking device works and drives the carbon fiber support tube and the sub-reflector to move upward until they are in place. Then the locking device locks the carbon fiber support tube so that the sub-reflector is locked in the axial, radial and circumferential directions.

[0010] During the second phase, the pyrotechnic components of locking release devices 1 and 2 are unlocked, and both locking release devices 1 and 2 are disconnected from the pyrotechnic components. The side fixed to the satellite platform mounting surface is disconnected from the connecting cylinder, and the side fixed to the connecting cylinder rotates to a position close to the connecting cylinder. Motor 1 is activated, and the on-orbit rotating parabolic antenna rotates at a constant speed and operates under the drive of motor 1.

[0011] The on-orbit rotating parabolic antenna locking, releasing, and locking device of the present invention, in a preferred embodiment, includes: a left motor fixing connector and a right motor fixing connector respectively connected to a preset embedded part on the satellite platform mounting surface; a support connector disposed outside the right motor fixing connector; a No. 1 locking pin disposed inside the support connector and extending to the left; a No. 1 compression spring disposed between the No. 1 locking pin and the support connector; a No. 2 locking pin contacting the left motor fixing connector and / or the right motor fixing connector; a No. 2 compression spring disposed at the bottom of the No. 2 locking pin; a No. 2 motor disposed between the left motor fixing connector and the right motor fixing connector; a support rod fixing connector connected to the top of the support connector; a bearing disposed in the left circular hole of the support rod fixing connector; and a bearing end cap fixedly connected to the support rod fixing connector and contacting and limiting the bearing.

[0012] The upper outer side of the support rod fixing connector is provided with a slot for connecting the carbon fiber support tube, and the inner side is provided with an installation groove for installing the No. 2 locking pin and the No. 2 compression spring. The upper surface of the left motor fixing connector and / or the right motor fixing connector is provided with a sliding groove and a cylindrical hole connected to the end of the sliding groove. The left motor fixing connector is located between the lower left side of the support rod fixing connector and the No. 2 motor. The right motor fixing connector is located between the No. 2 motor and the support connector. The right outer side of the right motor fixing connector is provided with a sliding groove and a cylindrical hole connected to the end of the sliding groove. The output shaft of the No. 2 motor is connected to the support connector.

[0013] During the rocket launch phase, locking pin 1 contacts the groove of the right motor fixing connector, and locking pin 2 contacts the groove of the left motor fixing connector and / or the right motor fixing connector.

[0014] During the on-orbit deployment phase, motor 2 operates, driving the support connector, locking pin 1, compression spring 1, locking pin 2, compression spring 2, support rod fixing connector, bearing and bearing end cap to rotate. The sub-reflector, carbon fiber support tube, and sub-reflector V-shaped connector rotate along with the support rod fixing connector until locking pins 1 and 2 are inserted into the round hole at the end of the slide groove, completing the first stage of deployment. The sub-reflector is locked in three directions—axial, radial, and circumferential—under the action of locking pins 1 and 2.

[0015] In the preferred embodiment of the on-orbit rotating parabolic antenna locking, releasing and locking device of the present invention, there are two sets of locking pins and compression springs No. 2, which are respectively set on both sides of motor No. 2. Two mounting grooves are provided on the inner side of the support rod fixing connector. The upper surfaces of the left motor fixing connector and the right motor fixing connector are provided with sliding grooves and cylindrical holes connected to the ends of the sliding grooves.

[0016] In a preferred embodiment of the on-orbit rotating parabolic antenna locking, releasing, and locking device of the present invention, the slots of the left motor fixing connector and the right motor fixing connector are located at the top, and the outer slot of the right motor fixing connector is located at the lower outer part.

[0017] The present invention discloses an on-orbit rotating parabolic antenna locking, releasing and locking device. In a preferred embodiment, the support connector includes a base connected to the support rod fixing connector, a side plate perpendicular to the base, a through mounting hole on the side plate and a mounting groove on the inner side of the side plate offset from the mounting hole. The output shaft of motor No. 2 extends out of the mounting hole through the right motor fixing connector. Locking pin No. 1 and compression spring No. 1 are both disposed in the mounting groove.

[0018] The on-orbit rotating parabolic antenna locking, releasing and locking device of the present invention, in a preferred embodiment, includes a No. 1 locking and releasing device comprising a No. 1 supporting curved column connected to the satellite platform mounting surface, a No. 2 pyrotechnic component and a No. 1 rotating linkage component connected in sequence to the No. 1 supporting curved column, a No. 1 torsion spring with one end inserted into the top circular hole of the No. 1 rotating linkage component, a No. 1 round rod sleeved in the body of the No. 1 torsion spring, and a No. 2 round rod connected to the other end of the No. 1 torsion spring.

[0019] The linkage cylinder is connected to rod No. 1 and rod No. 2 via mounting parts set on the outer surface;

[0020] After the No. 2 pyrotechnic component is unlocked, the No. 1 rotating linkage component rotates under the drive of the No. 1 torsion spring, and the No. 1 rotating linkage component is pressed tightly against the linkage cylinder under the clamping force of the No. 1 torsion spring.

[0021] In a preferred embodiment of the on-orbit rotating parabolic antenna locking, releasing, and locking device of the present invention, the bottom of the No. 1 support column is a vertical structure and the upper part is inclined inward. The part of the No. 1 rotating linkage connected to the No. 2 pyrotechnic component is a flat plate structure, and the front end is a plate-shaped structure that is inclined upward along the flat plate structure. An angle is formed between the front end of the flat plate structure and the inclined plate-shaped structure. A circular hole connected to one end of the No. 1 torsion spring is provided on the side of the angle.

[0022] The on-orbit rotating parabolic antenna locking, releasing and locking device of the present invention, in a preferred embodiment, includes a No. 2 locking and releasing device comprising a No. 2 supporting curved column connected to the satellite platform mounting surface, a No. 3 pyrotechnic component and a No. 2 rotating linkage component connected in sequence to the No. 2 supporting curved column, a No. 2 torsion spring with one end inserted into the top circular hole of the No. 2 rotating linkage component, a No. 4 round rod sleeved in the body of the No. 2 torsion spring, and a No. 3 round rod connected to the other end of the No. 2 torsion spring.

[0023] The linkage cylinder is connected to rods No. 3 and No. 4 via mounting parts set on its outer surface;

[0024] After the No. 3 pyrotechnic device is unlocked, the No. 2 rotating linkage rotates under the drive of the No. 2 torsion spring, and the No. 2 rotating linkage is pressed tightly against the linkage cylinder under the clamping force of the No. 2 torsion spring.

[0025] The length and height of support bend No. 2 are both greater than those of support bend No. 1.

[0026] After assembly, the circumferential limiting directions of locking and releasing device No. 1 and locking and releasing device No. 2 are opposite.

[0027] In a preferred embodiment of the on-orbit rotating parabolic antenna locking, releasing, and locking device of the present invention, the bottom of the No. 1 support column is a vertical structure, the upper part is inclined inward, and the end is inclined downward. The part of the No. 1 rotating linkage connected to the No. 2 pyrotechnic component is a flat plate structure, and the front end is a plate-shaped structure inclined downward along the flat plate structure. An angle is formed between the front end of the flat plate structure and the inclined plate-shaped structure. A circular hole connected to one end of the No. 1 torsion spring is provided on the side of the angle.

[0028] In the preferred embodiment of the on-orbit rotating parabolic antenna locking, releasing and locking device of the present invention, there are two sets of locking and releasing devices No. 1 and No. 2, which are arranged alternately.

[0029] After assembly, the No. 1 support bend forms a 45° angle with the lower part of the connecting cylinder, and the No. 2 rotating connecting part forms a 135° angle with the lower part of the connecting cylinder.

[0030] After unlocking, both rotary linkage No. 1 and rotary linkage No. 2 rotate 45°.

[0031] A locking, releasing, and locking device for an on-orbit rotating parabolic antenna includes a satellite platform mounting surface, a main parabolic reflector, a linkage cylinder, a secondary reflector, a carbon fiber support tube, a No. 1 pyrotechnic device, a secondary V-shaped connector, a pyrotechnic device support cover, an unfolding and locking device, a No. 1 motor, a rotating connector, a No. 1 locking and releasing device, and a No. 2 locking and releasing device.

[0032] The main parabolic reflector is fixedly connected to the linkage cylinder; the secondary reflector is fixedly connected to the carbon fiber support tube; the secondary reflector is fixedly connected to the secondary reflector V-shaped connector; the secondary reflector V-shaped connector is fixedly connected to pyrotechnic item No. 1; the pyrotechnic item support cover is fixedly connected to pyrotechnic item No. 1; the pyrotechnic item support cover is fixedly connected to the main parabolic reflector; the carbon fiber support tube is fixedly connected to the support rod fixing connector; the left motor fixing connector and the right motor fixing connector are respectively fixedly connected to the embedded parts on the main parabolic reflector; the support connector is respectively fixedly connected to motor No. 2 and the support rod fixing connector; spring No. 1 is placed inside locking pin No. 1; locking pin No. 1 is placed in the cylindrical hole of the support connector; the head of locking pin No. 1 contacts the bottom surface of the groove of the right motor fixing connector; motor No. 2 is fixedly connected to the left motor fixing connector and the right motor fixing connector; two sets of spring No. 2 are placed inside locking pin No. 2; two sets of locking pins No. 2 are placed in the cylindrical hole of the support rod fixing connector; the heads of the two sets of locking pins No. 2 are respectively fixedly connected to the left motor fixing connector and the right motor fixing connector. The fixed connector contacts the bearing, which is placed inside the cylindrical hole of the support rod fixed connector. The bearing end cap is fixedly connected to the support rod fixed connector and contacts and limits the bearing. Motor No. 1 is fixedly connected to the satellite platform mounting surface. The rotating connector is fixedly connected to the linkage cylinder and Motor No. 1 respectively. Support column No. 1 is fixedly connected to the satellite platform mounting surface. Pyrotechnic item No. 2 is fixedly connected to support column No. 1 and rotating linkage No. 1 respectively. Round rod No. 1 and round rod No. 2 are fixedly connected to the linkage cylinder respectively. Rotating linkage No. 1 is fitted onto No. 1. A circular rod is formed, with the main body of torsion spring #1 fitted onto it. One end of torsion spring #1 is fitted onto circular rod #2, and the other end is inserted into the circular hole of rotating linkage #1. Support column #2 is fixedly connected to the satellite platform mounting surface. Pyrotechnic component #3 is fixedly connected to support column #2 and rotating linkage #2 respectively. Circular rods #3 and #4 are fixedly connected to the linkage cylinder. Rotating linkage #2 is fitted onto circular rod #4, and the main body of torsion spring #2 is fitted onto circular rod #4. One end of torsion spring #2 is fitted onto circular rod #3, and the other end is inserted into the circular hole of rotating linkage #2. This on-orbit rotating parabolic antenna locking, releasing, and locking device can effectively realize the functions of sub-reflector deployment and locking, main parabolic reflector locking and releasing, and on-orbit interference-free rotation. During rocket launch, the spaceborne parabolic antenna is in a retracted and locked state. One end of the secondary reflector is connected to a carbon fiber support tube, and the other end is fixedly connected to the No. 1 pyrotechnic component through a secondary V-shaped connector, so that the secondary reflector has a locking effect. One end of the two sets of No. 1 support columns and the two sets of No. 2 support columns are fixed to the satellite platform mounting surface. The two sets of No. 1 rotating linkages use No. 1 round rod to achieve axial and radial limiting, and No. 2 round rod to achieve unidirectional circumferential limiting. The two sets of No. 2 rotating linkages use No. 4 round rod to achieve axial and radial limiting, and No. 3 round rod to achieve unidirectional circumferential limiting. The circumferential limiting directions of the two are opposite, taking into account both non-interference deployment and structural strength, thereby realizing the locking function of the main parabolic reflector.

[0033] During the in-orbit deployment phase, the spaceborne parabolic antenna is deployed in its first stage. Pyrotechnic component #1 is unlocked, and motor #2 operates. The sub-reflector, carbon fiber support tube, sub-reflector V-shaped connector, support connector, locking pin #1, compression spring #1, two sets of locking pins #2, two sets of compression springs #2, support rod fixing connector, bearing, and bearing end cap rotate under the drive of motor #2. Locking pins #1 and #2 slide along the groove. After rotating to the designed angle, locking pins #1 and #2 are inserted into the groove's circular hole under the force of compression springs #1 and #2, respectively. The sub-reflector, etc., achieve a three-way locking effect in the axial, radial, and circumferential directions under the action of locking pins #1 and #2.

[0034] During the in-orbit deployment phase, the spaceborne parabolic antenna is deployed in the second stage. Two sets of No. 2 pyrotechnic devices and two sets of No. 3 pyrotechnic devices are unlocked. Two sets of No. 1 rotating linkages rotate about 45° around No. 1 rod under the action of two sets of No. 1 torsion springs, and are pressed tightly against the surface of the linkage cylinder by the clamping force of No. 1 torsion springs. Two sets of No. 2 rotating linkages rotate about 45° around No. 4 rod under the action of two sets of No. 2 torsion springs, and are pressed tightly against the surface of the linkage cylinder by the clamping force of No. 2 torsion springs. After that, No. 1 motor is turned on, and the spaceborne parabolic antenna rotates at a constant speed and operates under the action of No. 1 motor.

[0035] The combination of two sets of No. 1 locking and release devices and two sets of No. 2 locking and release devices integrates omnidirectional locking and deployment functions, and can achieve the goal of interference-free rotation when the parabolic antenna is working. In the two sets of No. 1 locking and release devices, the No. 1 rotating linkage uses the No. 1 round rod to achieve axial and radial limiting, and the No. 2 round rod to achieve unidirectional circumferential limiting. In the two sets of No. 2 locking and release devices, the No. 2 rotating linkage uses the No. 4 round rod to achieve axial and radial limiting, and the No. 3 round rod to achieve unidirectional circumferential limiting. The circumferential limiting directions of the two are opposite. The No. 1 and No. 2 rotating linkages are at 45° with the axis of the linkage cylinder, which takes into account both interference-free deployment and structural strength, and achieves high locking capacity of the locking device to meet the requirements of locking and rotating the main parabolic reflector on the track.

[0036] The unfolding and locking device integrates unfolding and omnidirectional locking functions. The sub-reflective surface, carbon fiber support tube, and support rod fixing connector rotate under the drive of motor No. 2. Locking pin No. 1 and two sets of No. 2 locking pins slide in their respective grooves. After the sub-reflective surface rotates to the designed angle, locking pin No. 1 and two sets of No. 2 locking pins are inserted into the groove holes under the action of compression springs No. 1 and No. 2, respectively. This achieves a locking effect in the axial, radial, and circumferential directions, realizing the omnidirectional locking function and improving the reliability of the product.

[0037] The present invention has the following advantages:

[0038] (1) The present invention employs two sets of locking and releasing devices, each with axial limiting, radial limiting and unidirectional circumferential limiting design. The two sets of circumferential limiting directions are opposite and are 45° to the rotation axis of the antenna reflector. This takes into account both strength and rotational interference. When the device is released and unfolded, a torsion spring is used to provide driving force and clamping force. It has the characteristics of simple structure, low cost, good locking performance and large load-bearing capacity.

[0039] (2) The present invention adopts a combination of three sets of locking pins and compression springs, which has the ability to lock in three directions: axial, radial and circumferential. It has the advantages of simple structure, low cost and good locking effect. Attached Figure Description

[0040] Figure 1 A schematic diagram of a locking, releasing, and retracting device for an on-orbit rotating parabolic antenna;

[0041] Figure 2 This is a schematic diagram of a locking, releasing and locking device for an on-orbit rotating parabolic antenna, showing the first stage of deployment after the sub-reflector is deployed and locked.

[0042] Figure 3 A schematic diagram of the two-stage deployment of a locking, releasing, and locking device for an on-orbit rotating parabolic antenna.

[0043] Figure 4 This is an enlarged schematic diagram of the retracted state of a locking, releasing, and locking device for an on-orbit rotating parabolic antenna.

[0044] Figure 5 An exploded view of the retracted state of a locking, releasing, and locking device for an on-orbit rotating parabolic antenna;

[0045] Figure 6 This is an enlarged schematic diagram of the locking, releasing, and locking device for an on-orbit rotating parabolic antenna in its deployed state.

[0046] Figure 7 This is an enlarged schematic diagram of the retracted state of locking device 1 and locking device 2 of an on-orbit rotating parabolic antenna locking, releasing and locking device;

[0047] Figure 8 An exploded view of the retracted state of locking device 1 and locking device 2 of an on-orbit rotating parabolic antenna locking, releasing and locking device;

[0048] Figure 9 This is an enlarged schematic diagram of the retracted state of locking device 1 and locking device 2 of an on-orbit rotating parabolic antenna locking, releasing and locking device.

[0049] Figure label:

[0050] 1. Satellite platform mounting surface; 2. Main parabolic reflector; 3. Linkage cylinder; 4. Secondary reflector; 5. Carbon fiber support tube; 6. No. 1 pyrotechnic device; 7. Secondary V-shaped reflector connector; 8. Pyrotechnic device support cover; 9. Deployment and locking device; 9-1. Left motor fixing connector; 9-2. Right motor fixing connector; 9-3. Support connector; 9-4. No. 1 locking pin; 9-5. No. 1 compression spring; 9-6. No. 2 locking pin; 9-7. No. 2 compression spring; 9-8. No. 2 motor; 9-9. Support rod fixing connector; 9-10. Bearing; 9-11, Bearing end cap; 10, Motor No. 1; 11, Rotating connecting part; 12, Locking release device No. 1; 12-1, Supporting column No. 1; 12-2, Pyrotechnic item No. 2; 12-3, Rotating linkage No. 1; 12-4, Torsion spring No. 1; 12-5, Round rod No. 1; 12-6, Round rod No. 2; 13, Locking release device No. 2; 13-1, Supporting column No. 2; 13-2, Pyrotechnic item No. 3; 13-3, Rotating linkage No. 2; 13-4, Torsion spring No. 2; 13-5, Round rod No. 3; 13-6, Round rod No. 4. Detailed Implementation

[0051] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0052] Example 1

[0053] like Figure 1 As shown, an on-orbit rotating parabolic antenna locking, releasing, and locking device includes a satellite platform mounting surface 1, a main parabolic reflector 2 disposed on the satellite platform mounting surface 1, a connecting cylinder 3 connected to the bottom of the main parabolic reflector 2, a secondary reflector 4 disposed on the upper part of the main parabolic reflector 2, a carbon fiber support tube 5 connected to the main parabolic reflector 2, a No. 1 pyrotechnic device 6 connected to the upper surface of the main parabolic reflector 2, a secondary reflector V-shaped connector 7 connected to the upper part of the No. 1 pyrotechnic device 6 and the rear part of the secondary reflector 4, a pyrotechnic device support cover 8 connected to the bottom of the No. 1 pyrotechnic device 6, an unfolding and locking device 9 connected between the carbon fiber support tube 5 and the main parabolic reflector 2, a No. 1 motor 10 connected to the satellite platform mounting surface 1, a rotating connector 11 connected between the connecting cylinder 3 and the No. 1 motor 10, and a No. 1 locking and releasing device 12 and a No. 2 locking and releasing device 13 connected at one end to the satellite platform mounting surface 1 and at the other end to the side of the connecting cylinder 3.

[0054] The rotating connector 11 is connected to the bottom of the main parabolic reflector 2. The secondary reflector 4 is set on the right side of the satellite platform mounting surface 1 through the carbon fiber support tube 5. The pyrotechnic support cover 8 is connected to the bottom of the main parabolic reflector 2. The angle between the secondary reflector 4 and the carbon fiber support tube 5 is 90°.

[0055] like Figure 1 As shown, during the rocket launch phase, the on-orbit rotating parabolic antenna is in a retracted and locked state. One end of the sub-reflector 4 is connected to the carbon fiber support tube 5, and the other end is fixedly connected to the No. 1 pyrotechnic component 6 via the sub-reflector V-shaped connector 7, thus locking the sub-reflector 4. The No. 1 locking release device 12 and the No. 2 locking release device 13 fix the linkage tube 3 to the main parabolic reflector 2, thus locking the main parabolic reflector 2.

[0056] like Figure 2 As shown, during the on-orbit deployment phase, the on-orbit rotating parabolic antenna involves two-stage deployment. During the first stage of deployment, the No. 1 pyrotechnic item 6 is unlocked, and the motor of the locking device 9 operates, driving the carbon fiber support tube 5 and the sub-reflector 4 to move upward until they are in place. Then, the locking device 9 locks the carbon fiber support tube 5 so that the sub-reflector 4 is locked in the axial, radial, and circumferential directions. After deployment, the sub-reflector 4 is parallel to the axial direction of the main parabolic reflector 2.

[0057] like Figure 3 As shown, during the second stage of deployment, the pyrotechnic devices of locking release device 12 and locking release device 23 are unlocked, and both locking release device 12 and locking release device 23 are disconnected from the pyrotechnic devices. The side fixed to the satellite platform mounting surface 1 is disconnected from the connecting cylinder 3, and the side fixed to the connecting cylinder 3 is rotated to a position close to the connecting cylinder 3. Motor 10 is turned on, and the on-orbit rotating parabolic antenna rotates at a constant speed and works under the drive of motor 10.

[0058] like Figures 4-6 As shown, the deployment and locking device 9 includes: a left motor fixing connector 9-1 and a right motor fixing connector 9-2 respectively connected to the preset embedded parts of the satellite platform mounting surface 1; a support connector 9-3 located outside the right motor fixing connector 9-2; a locking pin 9-4 extending to the left inside the support connector 9-3; a compression spring 9-5 located between the locking pin 9-4 and the support connector 9-3; a locking pin 9-6 in contact with the left motor fixing connector 9-1 and / or the right motor fixing connector 9-2; a compression spring 9-7 located at the bottom of the locking pin 9-6; a motor 9-8 located between the left motor fixing connector 9-1 and the right motor fixing connector 9-2; a support rod fixing connector 9-9 connected to the top of the support connector 9-3; a bearing 9-10 located in the left circular hole of the support rod fixing connector 9-9; and a bearing end cap 9-11 fixedly connected to the support rod fixing connector 9-9 and in contact with and limited by the bearing 9-10.

[0059] The upper outer side of the support rod fixing connector 9-9 is provided with a slot for connecting the carbon fiber support tube 5, and the inner side is provided with an installation groove for installing the No. 2 locking pin 9-6 and the No. 2 compression spring 9-7. The upper surface of the left motor fixing connector 9-1 and / or the right motor fixing connector 9-2 is provided with a sliding groove and a cylindrical hole connected to the end of the sliding groove. The left motor fixing connector 9-1 is located between the lower left side of the support rod fixing connector 9-9 and the No. 2 motor 9-8. The right motor fixing connector 9-2 is located between the No. 2 motor 9-8 and the support connector 9-3. The right outer side of the right motor fixing connector 9-2 is provided with a sliding groove and a cylindrical hole connected to the end of the sliding groove. The output shaft of the No. 2 motor 9-8 is connected to the support connector 9-3.

[0060] During the rocket launch phase, locking pin 1 9-4 contacts the groove of right motor fixing connector 9-2, and locking pin 2 9-6 contacts the groove of left motor fixing connector 9-1 and / or right motor fixing connector 9-2.

[0061] During the on-orbit deployment phase, motor 2 (9-8) operates, driving the support connector 9-3, locking pin 1 (9-4), compression spring 1 (9-5), locking pin 2 (9-6), compression spring 2 (9-7), support rod fixing connector 9-9, bearing 9-10, and bearing end cap 9-11 to rotate. The secondary reflector 4, carbon fiber support tube 5, and secondary reflective V-shaped connector 7 rotate with the support rod fixing connector 9-9 until locking pin 1 (9-4) and locking pin 2 (9-6) are inserted into the round hole at the end of the slide groove, completing the first stage of deployment. The secondary reflector 4 is locked in three directions—axial, radial, and circumferential—under the action of locking pin 1 (9-4) and locking pin 2 (9-6).

[0062] Locking pin 9-6 and spring 9-7 are in two sets, respectively set on both sides of motor 9-8. The inner side of the support rod fixing connector 9-9 is provided with two mounting grooves. The upper surfaces of the left motor fixing connector 9-1 and the right motor fixing connector 9-2 are provided with sliding grooves and cylindrical holes connected to the ends of the sliding grooves.

[0063] The slots for the left motor fixing connector 9-1 and the right motor fixing connector 9-2 are located at the top, and the outer slot of the right motor fixing connector 9-2 is located at the lower outer part;

[0064] The support connector 9-3 includes a base connected to the support rod fixing connector 9-9, a side plate perpendicular to the base, a through mounting hole on the side plate, and a mounting groove on the inner side of the side plate offset from the mounting hole. The output shaft of motor 2 9-8 extends out of the mounting hole through the right motor fixing connector 9-2. Locking pin 1 9-4 and compression spring 1 9-5 are both set in the mounting groove.

[0065] like Figures 7-9As shown, the No. 1 locking and releasing device 12 includes a No. 1 support bend 12-1 connected to the satellite platform mounting surface 1, a No. 2 pyrotechnic component 12-2 and a No. 1 rotating linkage component 12-3 connected in sequence to the No. 1 support bend 12-1, a No. 1 torsion spring 12-4 with one end inserted into the top round hole of the No. 1 rotating linkage component 12-3, a No. 1 round rod 12-5 sleeved in the body of the No. 1 torsion spring 12-4, and a No. 2 round rod 12-6 connected to the other end of the No. 1 torsion spring 12-4;

[0066] The linkage cylinder 3 is connected to the No. 1 round rod 12-5 and the No. 2 round rod 12-6 through the mounting parts set on the outer surface;

[0067] After the No. 2 pyrotechnic component 12-2 is unlocked, the No. 1 rotating linkage component 12-3 rotates under the drive of the No. 1 torsion spring 12-4, and the No. 1 rotating linkage component 12-3 is pressed tightly against the linkage cylinder 3 under the clamping force of the No. 1 torsion spring 12-4.

[0068] The bottom of the No. 1 support column 12-1 is a vertical structure and the upper part is inclined inward. The part of the No. 1 rotating linkage 12-3 connected to the No. 2 pyrotechnic item 12-2 is a flat plate structure and the front end is a plate-shaped structure that is inclined upward along the flat plate structure. An angle is formed between the front end of the flat plate structure and the inclined plate-shaped structure. A round hole is provided on the side of the angle that is connected to one end of the No. 1 torsion spring 12-4.

[0069] The No. 2 locking and releasing device 13 includes a No. 2 support bend 13-1 connected to the satellite platform mounting surface 1, a No. 3 pyrotechnic component 13-2 and a No. 2 rotating linkage component 13-3 connected in sequence to the No. 2 support bend 13-1, a No. 2 torsion spring 13-4 with one end inserted into the top round hole of the No. 2 rotating linkage component 13-3, a No. 4 round rod 13-6 sleeved in the body of the No. 2 torsion spring 13-4, and a No. 3 round rod 13-5 connected to the other end of the No. 2 torsion spring 13-4;

[0070] The linkage cylinder 3 is connected to the No. 3 round rod 13-5 and the No. 4 round rod 13-6 through the mounting parts set on the outer surface;

[0071] After the No. 3 pyrotechnic component 13-2 is unlocked, the No. 2 rotating linkage component 13-3 rotates under the drive of the No. 2 torsion spring 13-4, and the No. 2 rotating linkage component 13-3 is pressed tightly against the linkage cylinder 3 under the clamping force of the No. 2 torsion spring 13-4.

[0072] The length and height of support bend 13-1 (No. 2) are both greater than the length and height of support bend 12-1 (No. 1).

[0073] After assembly, the circumferential limiting directions of locking and releasing device 12 and locking and releasing device 13 are opposite;

[0074] The bottom of the No. 1 support column 12-1 is a vertical structure, the upper part is inclined inward and the end is inclined downward. The part of the No. 1 rotating linkage 12-3 connected to the No. 2 pyrotechnic item 12-2 is a flat plate structure, and the front end is a plate-shaped structure that is inclined downward along the flat plate structure. An angle is formed between the front end of the flat plate structure and the inclined plate-shaped structure. A round hole is provided on the side of the angle that is connected to one end of the No. 1 torsion spring 12-4.

[0075] There are two sets of locking and releasing devices 12 and 13, which are interspersed.

[0076] After assembly, the No. 1 support bend 12-1 forms a 45° angle with the lower part of the connecting cylinder 3, and the No. 2 rotating connecting part 13-3 forms a 135° angle with the lower part of the connecting cylinder 3.

[0077] After unlocking, both rotary linkage 12-3 and rotary linkage 13-3 rotate 45°.

[0078] Example 2

[0079] like Figure 1 As shown, an on-orbit rotating parabolic antenna locking, releasing, and locking device includes a satellite platform mounting surface 1, a main parabolic reflector 2, a linkage cylinder 3, a secondary reflector 4, a carbon fiber support tube 5, a No. 1 pyrotechnic component 6, a secondary V-shaped connector 7, a pyrotechnic component support cover 8, an unfolding and locking device 9, a No. 1 motor 10, a rotating connector 11, a No. 1 locking and releasing device 12, and a No. 2 locking and releasing device 13.

[0080] like Figure 1 As shown, during the rocket launch phase, the spaceborne parabolic antenna is in a retracted and locked state. One end of the sub-reflector 4 is connected to the carbon fiber support tube 5, and the other end is fixedly connected to the No. 1 pyrotechnic component 6 through the sub-reflector V-shaped connector 7, so that the sub-reflector 4 has a limiting and locking effect. One end of the two sets of No. 1 support curved columns 12-1 and the two sets of No. 2 support curved columns 13-1 are fixed to the satellite platform mounting surface 1. The two sets of No. 1 rotating linkage components 12-3 use No. 2 round rod 12-6 to achieve unidirectional circumferential limiting, and the two sets of No. 2 rotating linkage components 13-3 use No. 3 round rod 13-5 to achieve unidirectional circumferential limiting. The two are combined and the limiting directions are opposite, while taking into account non-interference deployment and structural strength, thereby achieving high locking performance of the main parabolic reflector 2.

[0081] like Figure 2As shown, during the first stage of the deployment of the spaceborne parabolic antenna, pyrotechnic component 6 (No. 1) is unlocked, motor 9-8 (No. 2) operates, and the sub-reflector 4, carbon fiber support tube 5, sub-reflector V-shaped connector 7, support connector 9-3, locking pin 9-4 (No. 1), compression spring 9-5 (No. 1), two sets of locking pins 9-6 (No. 2), two sets of compression springs 9-7 (No. 2), support rod fixing connector 9-9, bearing 9-10, and bearing end cap 9-11 rotate under the drive of motor 9-8. Locking pin 9-4 (No. 1) and locking pin 9-6 (No. 2) slide along their respective grooves. After rotating to the designed angle, locking pin 9-4 (No. 1) and locking pin 9-6 (No. 2) are inserted into the circular holes of the grooves under the force of compression springs 9-5 (No. 1) and 9-7 (No. 2), respectively. Under the combined action of locking pin 9-4 (No. 1) and locking pin 9-6 (No. 2), the sub-reflector 4 achieves a three-way locking effect in the axial, radial, and circumferential directions.

[0082] like Figure 3 As shown, the spaceborne parabolic antenna unfolds in two stages. Two sets of No. 2 pyrotechnic components 12-2 and 2 sets of No. 3 pyrotechnic components 13-2 are unlocked. Two sets of No. 1 rotating linkage components 12-3, driven by two sets of No. 1 torsion springs 12-4, rotate approximately 45° around No. 1 round rod 12-5 and are pressed tightly against the surface of the linkage cylinder 3 using the torsion spring's clamping force. Two sets of No. 2 rotating linkage components 13-3, driven by two sets of No. 2 torsion springs 13-4, rotate approximately 45° in the opposite direction around No. 4 round rod 13-6 and are pressed tightly against the surface of the linkage cylinder 3 using the torsion spring's clamping force. Afterwards, No. 1 motor 10 is activated, and the spaceborne parabolic antenna rotates without interference at a uniform speed and begins operation under the drive of No. 1 motor 10.

[0083] In this embodiment, spring 9-5 (set 1) and spring 9-7 (set 2) are made of 65Mn material and are nickel-plated.

[0084] In this embodiment, the two sets of No. 1 torsion springs 12-4 and the two sets of No. 2 torsion springs 13-4 are made of 65Mn material and are nickel-plated on the surface.

[0085] In this embodiment, the left motor fixing connector 9-1, the right motor fixing connector 9-2, the support connector 9-3, the No. 1 locking pin 9-4, the two sets of No. 2 locking pins 9-6, and the support rod fixing connector 9-9 are coated with MoS2 film to prevent cold welding.

[0086] In this embodiment, bearings 9-10 are coated with a MoS2 film to prevent cold welding.

[0087] In this embodiment, the No. 1 rotating linkage 12-3, the No. 1 round rod 12-5, the No. 2 round rod 12-6, the No. 2 rotating linkage 13-3, the No. 3 round rod 13-5, and the No. 4 round rod 13-6 are coated with MoS2 film to prevent cold welding.

[0088] In this embodiment, the connecting cylinder 3 is coated with a MoS2 film to prevent cold welding.

[0089] In this embodiment, the main parabolic reflector 2 and the secondary reflector 4 are designed with carbon fiber skin and full carbon honeycomb sandwich material to reduce weight and improve surface accuracy under thermal deformation.

[0090] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. An on-orbit rotating parabolic antenna locking, releasing and locking device, comprising a satellite platform mounting surface (1), a main parabolic reflector (2) disposed on the satellite platform mounting surface (1), a connecting cylinder (3) connected to the bottom of the main parabolic reflector (2), a secondary reflector (4) disposed on the upper part of the main parabolic reflector (2), a carbon fiber support tube (5) connected to the main parabolic reflector (2), a No. 1 pyrotechnic device (6) connected to the upper surface of the main parabolic reflector (2), a secondary V-shaped connector (7) connected to the upper part of the No. 1 pyrotechnic device (6) and the rear part of the secondary reflector (4), and a pyrotechnic device support cover (8) connected to the bottom of the No. 1 pyrotechnic device (6), characterized in that: It also includes an unfolding and locking device (9) connected between the carbon fiber support tube (5) and the main parabolic reflector (2), a No. 1 motor (10) connected to the satellite platform mounting surface (1), a rotating connector (11) connected between the linkage cylinder (3) and the No. 1 motor (10), and a No. 1 locking and releasing device (12) and a No. 2 locking and releasing device (13) with one end connected to the satellite platform mounting surface (1) and the other end connected to the side of the linkage cylinder (3). The rotating connector (11) is connected to the bottom of the main parabolic reflector (2), the secondary reflector (4) is set on the upper part of the main parabolic reflector (2) through the carbon fiber support tube (5), and the pyrotechnic support cover (8) is connected to the bottom of the main parabolic reflector (2). During the rocket launch phase, the on-orbit rotating parabolic antenna is in a retracted and locked state. One end of the sub-reflector (4) is connected to the carbon fiber support tube (5), and the other end is fixedly connected to the No. 1 pyrotechnic item (6) on the main parabolic reflector (2) through the sub-reflector V-shaped connector (7), so that the sub-reflector (4) is in a locked state. The No. 1 locking release device (12) and the No. 2 locking release device (13) fix the connecting cylinder (3) to the main parabolic reflector (2), so that the main parabolic reflector (2) is in a locked state. During the on-orbit deployment phase, the on-orbit rotating parabolic antenna includes two-stage deployment. During the first stage of deployment, the No. 1 pyrotechnic item (6) is unlocked, and the No. 2 motor (9-8) of the locking device (9) works and drives the carbon fiber support tube (5) and the sub-reflector (4) to move upward until they are in place. Then, the locking device (9) locks the carbon fiber support tube (5) so that the sub-reflector (4) is locked in the axial, radial and circumferential directions. When the second stage is unfolded, the pyrotechnics of the No. 1 locking release device (12) and the No. 2 locking release device (13) are unlocked, the No. 1 locking release device (12) and the No. 2 locking release device (13) are disconnected from the pyrotechnics, the side fixed to the satellite platform mounting surface (1) is disconnected from the connecting cylinder (3), the side fixed to the connecting cylinder (3) is rotated to a position close to the connecting cylinder (3), the No. 1 motor (10) is turned on, and the on-orbit rotating parabolic antenna rotates at a constant speed and works under the drive of the No. 1 motor (10).

2. The on-orbit rotating parabolic antenna locking, releasing, and locking device according to claim 1, characterized in that: The unfolding and locking device (9) includes: a left motor fixing connector (9-1) and a right motor fixing connector (9-2) respectively connected to the pre-embedded parts of the satellite platform mounting surface (1); a support connector (9-3) disposed outside the right motor fixing connector (9-2); a No. 1 locking pin (9-4) disposed inside the support connector (9-3) and extending to the left; a No. 1 compression spring (9-5) disposed between the No. 1 locking pin (9-4) and the support connector (9-3); and a locking pin (9-1) and a locking pin (9-2) respectively connected to the left motor fixing connector (9-1) and the right motor fixing connector (9-2). The following components are included: a locking pin (9-6) in contact with the locking pin (9-6); a compression spring (9-7) at the bottom of the locking pin (9-6); a motor (9-8) between the left motor fixing connector (9-1) and the right motor fixing connector (9-2); a support rod fixing connector (9-9) connected to the top of the support connector (9-3); a bearing (9-10) in the left circular hole of the support rod fixing connector (9-9); and a bearing end cap (9-11) fixedly connected to the support rod fixing connector (9-9) and in contact with and limited by the bearing (9-10). The upper outer side of the support rod fixing connector (9-9) is provided with a slot for connecting the carbon fiber support tube (5), and the inner side is provided with an installation groove for installing the No. 2 locking pin (9-6) and the No. 2 compression spring (9-7). The upper surfaces of the left motor fixing connector (9-1) and the right motor fixing connector (9-2) are provided with a sliding groove and a cylindrical hole connected to the end of the sliding groove. The left motor fixing connector (9-1) is located between the lower left side of the support rod fixing connector (9-9) and the No. 2 motor (9-8). The right motor fixing connector (9-2) is located between the No. 2 motor (9-8) and the support connector (9-3). The right outer side of the right motor fixing connector (9-2) is provided with a sliding groove and a cylindrical hole connected to the end of the sliding groove. The output shaft of the No. 2 motor (9-8) is connected to the support connector (9-3). During the rocket launch phase, the No. 1 locking pin (9-4) contacts the groove of the right motor fixing connector (9-2), and the No. 2 locking pin (9-6) contacts the grooves of the left motor fixing connector (9-1) and the right motor fixing connector (9-2). During the on-orbit deployment phase, the No. 2 motor (9-8) operates, driving the support connector (9-3), the No. 1 locking pin (9-4), the No. 1 compression spring (9-5), the No. 2 locking pin (9-6), the No. 2 compression spring (9-7), the support rod fixing connector (9-9), the bearing (9-10), and the bearing end cap (9-11) to rotate. The sub-reflective surface (4), the carbon fiber support tube (5), and the sub-reflective V-shaped connector (7) rotate along with the support rod fixing connector (9-9) until the No. 1 locking pin (9-4) and the No. 2 locking pin (9-6) are inserted into the round hole at the end of the slide groove, completing one stage of deployment. The sub-reflective surface (4) is locked in three directions—axial, radial, and circumferential—under the action of the No. 1 locking pin (9-4) and the No. 2 locking pin (9-6).

3. The on-orbit rotating parabolic antenna locking, releasing, and locking device according to claim 2, characterized in that: The No. 2 locking pin (9-6) and the No. 2 compression spring (9-7) are both in two sets, respectively located on both sides of the No. 2 motor (9-8), and the inner side of the support rod fixing connector (9-9) is provided with two mounting grooves.

4. The on-orbit rotating parabolic antenna locking, releasing, and locking device according to claim 2, characterized in that: The slots of the left motor fixing connector (9-1) and the right motor fixing connector (9-2) are located at the top, and the outer slot of the right motor fixing connector (9-2) is located at the lower outer part.

5. The on-orbit rotating parabolic antenna locking, releasing, and locking device according to claim 2, characterized in that: The support connector (9-3) includes a base connected to the support rod fixing connector (9-9), a side plate perpendicular to the base, a through mounting hole on the side plate, and a mounting groove on the inner side of the side plate offset from the mounting hole. The output shaft of the No. 2 motor (9-8) passes through the right motor fixing connector (9-2) and extends out from the mounting hole. The No. 1 locking pin (9-4) and the No. 1 compression spring (9-5) are both disposed in the mounting groove.

6. The on-orbit rotating parabolic antenna locking, releasing, and locking device according to claim 1, characterized in that: The No. 1 locking and releasing device (12) includes a No. 1 support bend (12-1) connected to the satellite platform mounting surface (1), a No. 2 pyrotechnic component (12-2) and a No. 1 rotating linkage component (12-3) connected in sequence to the No. 1 support bend (12-1), a No. 1 torsion spring (12-4) with one end inserted into the top circular hole of the No. 1 rotating linkage component (12-3), a No. 1 round rod (12-5) sleeved in the body of the No. 1 torsion spring (12-4), and a No. 2 round rod (12-6) connected to the other end of the No. 1 torsion spring (12-4). The linkage cylinder (3) is connected to the No. 1 round rod (12-5) and the No. 2 round rod (12-6) through the mounting parts set on the outer surface; After the No. 2 pyrotechnic item (12-2) is unlocked, the No. 1 rotating linkage (12-3) rotates under the drive of the No. 1 torsion spring (12-4), and the No. 1 rotating linkage (12-3) is pressed tightly against the linkage cylinder (3) under the clamping force of the No. 1 torsion spring (12-4).

7. The on-orbit rotating parabolic antenna locking, releasing, and locking device according to claim 6, characterized in that: The bottom of the No. 1 support column (12-1) is a vertical structure and the upper part is inclined inward. The part of the No. 1 rotating linkage (12-3) connected to the No. 2 pyrotechnic item (12-2) is a flat plate structure and the front end is a plate-shaped structure that is inclined upward along the flat plate structure. An angle is formed between the front end of the flat plate structure and the inclined plate-shaped structure. A round hole is provided on the side of the angle that is connected to one end of the No. 1 torsion spring (12-4).

8. The on-orbit rotating parabolic antenna locking, releasing, and locking device according to claim 6, characterized in that: The No. 2 locking and releasing device (13) includes a No. 2 support column (13-1) connected to the satellite platform mounting surface (1), a No. 3 pyrotechnic component (13-2) and a No. 2 rotating linkage component (13-3) connected in sequence to the No. 2 support column (13-1), a No. 2 torsion spring (13-4) with one end inserted into the top round hole of the No. 2 rotating linkage component (13-3), a No. 4 round rod (13-6) sleeved in the body of the No. 2 torsion spring (13-4), and a No. 3 round rod (13-5) connected to the other end of the No. 2 torsion spring (13-4). The linkage cylinder (3) is connected to the No. 3 round rod (13-5) and the No. 4 round rod (13-6) through the mounting parts set on the outer surface; After the No. 3 pyrotechnic item (13-2) is unlocked, the No. 2 rotating linkage (13-3) rotates under the drive of the No. 2 torsion spring (13-4), and the No. 2 rotating linkage (13-3) is pressed tightly against the linkage cylinder (3) under the clamping force of the No. 2 torsion spring (13-4). The length and height of the No. 2 support bend (13-1) are both greater than the length and height of the No. 1 support bend (12-1); After assembly, the circumferential limiting directions of the No. 1 locking release device (12) and the No. 2 locking release device (13) are opposite.

9. The on-orbit rotating parabolic antenna locking, releasing, and locking device according to claim 8, characterized in that: The number of the No. 1 locking release device (12) and the No. 2 locking release device (13) are both 2 sets, which are interspersed; After assembly, the No. 1 support bend (12-1) forms a 45° angle with the lower part of the connecting cylinder (3), and the No. 2 rotating connecting part (13-3) forms a 135° angle with the lower part of the connecting cylinder (3); After unlocking, both the No. 1 rotating linkage (12-3) and the No. 2 rotating linkage (13-3) rotate 45°.

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