Unfolding device of satellite-borne phased-array antenna and assembling and working method of unfolding device

Abstract

The invention provides an unfolding device of a satellite-borne phased-array antenna and an assembling and working method of the unfolding device, and belongs to the technical field of space product structure and mechanism design. The problem that the unfolding capacity of an existing unfolding type phased-array antenna is limited is solved. The unfolding device comprises a phased-array antenna unfolding part, unfolding locking mechanisms and a pressing releasing mechanism, in a pressing state, the phased-array antenna unfolding part is located below a satellite bottom plate, and the side edge of the phased-array antenna unfolding part is connected with a main frame of a satellite through the unfolding locking mechanisms which are symmetrically arranged; a plurality of pressing points are arranged on the phased-array antenna unfolding part, each pressing point is connected with a satellite through a pressing releasing mechanism, phased-array antenna sub-arrays are arranged on the phased-array antenna unfolding part and a satellite bottom plate, and the unfolding locking mechanism comprises an unfolding arm, an unfolding arm support, a torsion spring and a locking hook. The two ends of the two unfolding arms are rotationally connected with the two ends of the two unfolding arm supports. The satellite-borne phased-array antenna unfolding device is mainly used for unfolding satellite-borne phased-array antennas.

Description

Technical Field

[0001] The present invention belongs to the technical field of space product structure and mechanism design, and particularly relates to a deployment device for a spaceborne phased array antenna, as well as its assembly and working methods. Background Art

[0002] Compared with passive phased array antennas, active phased array antennas have the advantages of flexible beam, high reliability, high power efficiency, strong anti-interference ability, etc. Therefore, communication satellites often adopt active phased array antennas as their spaceborne communication payloads. Each antenna unit of an active phased array antenna has an independent transmit / receive module, independent control of phase and amplitude, which also results in its characteristic of large weight. For example, the spaceborne antenna of Starlink is expected to be about 50 kg / m 2 , and currently, the spaceborne phased array antennas under research are often several square meters in size and weigh in the hundreds of kilograms; at the same time, active phased array antennas also have relatively high requirements for their flatness. Failure to meet the flatness will cause a significant decline in the performance of the antenna. For the above reasons, currently, communication satellite constellations usually adopt a flat plate configuration, which uses a complete installation surface to layout the phased array antenna to meet the requirements of load-bearing capacity and flatness.

[0003] With the continuous increase in the size of spaceborne phased array antennas, the launch fairing can no longer meet the body installation requirements of some antennas. Therefore, deployable phased array antennas have gradually become a research hotspot. Currently, the common deployable phased array antenna is: the body installation part of the phased array antenna is laid out on a complete installation surface of the satellite, and the deployable part of the phased array antenna is installed at the bottom of the body installation part through a root hinge and a clamping mechanism. After the clamping mechanism is unlocked, the deployable part rotates and unfolds around the hinge axis under the drive of the root hinge, and after unfolding in place, it is locked by the locking component of the root hinge.

[0004] The above-mentioned deployable phased array antenna has the following defects: First, in the stowed state, the array surfaces of the body installation part and the deployable part of the phased array antenna face each other. At this time, there is no exposed array surface on the satellite, so no load test work can be carried out before the antenna is deployed; once the mechanism fails to deploy, the entire phased array antenna will lose its function; Second, in the stowed state, the array surfaces of the body installation part and the deployable part of the phased array antenna face each other. If the distance between the array surfaces is small or the mechanical conditions during the launch ascent stage are harsh, there is a risk of mutual collision and damage between the array surfaces; Third, the spaceborne active phased array antenna is heavy and has a large inertia during flipping and unfolding. Therefore, when the antenna unfolds, it causes a large disturbance to the entire satellite, and requires a large driving force from the root hinge; Fourth, the large driving force of the root hinge further increases the requirements for the pre-deployment clamping force of the antenna and the strength of the drive mechanism structural components, and the large driving force will cause a large locking impact; V. It is very difficult to ensure that the rotation angle of the flipped and deployed antenna array is exactly coplanar with the body-mounted array. The deviation of the rotation angle will cause the flatness problem of the antenna array and affect the antenna performance. VI. The locking force arm at the root hinge position is short, and the locking effect is poor. The slight angular changes in the root hinge part are amplified on the antenna array, which will also cause the flatness problem of the array and affect the antenna performance. Summary of the Invention

[0005] In view of this, the present invention aims to provide a deployment device for a spaceborne phased array antenna and its assembly and working methods to solve the problems existing in the deployment ability of the existing deployable phased array antenna.

[0006] To achieve the above object, the present invention adopts the following technical solutions: A deployment device for a spaceborne phased array antenna, which includes a phased array antenna deployment part, a deployment locking mechanism, and a pressing and releasing mechanism. In the pressed state, the phased array antenna deployment part is located below the satellite bottom plate. The side of the phased array antenna deployment part is connected to the main frame of the satellite through symmetrically arranged deployment locking mechanisms. A plurality of pressing points are provided on the phased array antenna deployment part, and each pressing point is connected to the satellite through a pressing and releasing mechanism. Phased array antenna sub-arrays are provided on both the phased array antenna deployment part and the satellite bottom plate. The deployment locking mechanism includes deployment arms, deployment arm brackets, torsion springs, and locking hooks. The two ends of the two deployment arms are rotationally connected to the two ends of the two deployment arm brackets to form a parallelogram structure. A torsion spring is provided at the connection between the deployment arm and the deployment arm bracket. One end of the torsion spring is connected to the deployment arm, and the other end is connected to the deployment arm bracket. A locking hook is rotationally connected to the opposite side of the two deployment arms. The side of the locking hook is connected to the deployment arm through a locking spring. One of the deployment arm brackets of the deployment locking mechanism is connected to the phased array antenna deployment part, and the other deployment arm bracket is connected to the main frame. The pressing and releasing mechanism includes a fixed seat, a tension cable, a fixed cover, and a thermal knife. The fixed seat is arranged on the satellite bottom plate, and the fixed cover is arranged on the phased array antenna deployment part. A rope passing hole is correspondingly opened on the phased array antenna deployment part. The tension cable passes through the rope passing hole, and the two ends of the tension cable are respectively connected to the fixed seat and the fixed cover. A thermal knife is provided on the fixed cover, and the thermal knife is in contact with the tension cable.

[0007] Furthermore, the number of the phased array antenna deployment parts is two, and the two phased array antenna deployment parts are symmetrically arranged, and the two phased array antenna deployment parts realize bilateral and bidirectional deployment.

[0008] Furthermore, the number of the phased array antenna deployment parts is multiple, and the multiple phased array antenna deployment parts are arranged layer by layer in the vertical direction. The adjacent phased array antenna deployment parts are connected through the deployment locking mechanism, and the multiple phased array antenna deployment parts realize multi-layer deployment.

[0009] Furthermore, the deployed part of the phased array antenna includes a deployed hatch panel and a deployed frame. One side of the deployed frame is provided with the deployed hatch panel, and the other side is in contact with the satellite bottom plate. The phased array antenna sub-array is arranged on the deployed hatch panel. The deployed frame is formed by connecting a plurality of carbon fiber tubes and a plurality of metal joints to each other, and the rope passing holes are arranged on the metal joints.

[0010] Furthermore, a cone body is arranged on the fixed seat. One end of the rope passing hole is a tapered hole, and the cone body is in shape fit with the tapered hole. The cone body is a cavity structure. One end of the tension cable is provided with a planar limit structure, and the other end is provided with an internal hexagonal external thread structure. The planar limit structure is clamped inside the cavity structure of the cone body, and the internal hexagonal external thread structure passes through the fixed cover and is screwed with a nut on the outside.

[0011] Furthermore, rotating shaft holes are opened at both ends of the deployment arm. Rotating shafts are arranged at both ends of the deployment arm bracket. The end of the rotating shaft is an external thread structure. The rotating shaft passes through the rotating shaft hole, and the external thread structure is screwed with a special-shaped nut. A torsion spring fixing hole is opened at the end of the deployment arm, and a torsion spring fixing platform is arranged on the deployment arm bracket. The torsion spring includes a first torsion spring fixing arm and a second torsion spring fixing arm. The first torsion spring fixing arm is inserted into the torsion spring fixing hole, and the second torsion spring fixing arm is connected to the torsion spring fixing platform.

[0012] Furthermore, a locking hook groove is opened on the deployment arm. The locking hook includes a rod body part and a hook. One end of the rod body part is a hook. The rod body part is located in the locking hook groove. Locking hook rotating shaft holes corresponding in position are opened on the rod body part and the deployment arm. A screw is inserted into the locking hook rotating shaft hole to realize the rotational connection between the deployment arm and the locking hook. A pin hole is opened on the side of the locking hook groove, and a spring fixing groove is opened on the rod body part. A pin is inserted into the pin hole, and one side of the locking spring is sleeved outside the pin, and the other side is inserted into the spring fixing groove.

[0013] Furthermore, the fixed seat and the fixed cover are made of titanium alloy, and the tension cable is a Dyneema fiber rope.

[0014] The present invention also provides an assembly method for a deployment device of a spaceborne phased array antenna, which includes the following steps: Step 1: Install the phased array antenna sub-array on the surface of the satellite bottom plate to form the body-mounted part of the phased array antenna. Connect one end of the tension cable to the fixed seat, and fix the fixed seat on the main frame by passing a screw through the through hole of the satellite bottom plate. Step 2: Install the phased array antenna sub-array and the fixed cover on the unfolded part of the phased array antenna, pass the tension rope through the rope threading hole of the unfolded part of the phased array antenna, stack the unfolded part of the phased array antenna and install it on the surface of the satellite bottom plate, adjust the pressing force to keep the pressing force of each pressing point consistent, and connect the tension rope to the fixed cover; Step 3: Fix the hot knife on one side of the fixed cover, extend the hot knife into the fixed cover cavity and contact the tension cable, complete the connection of all the pressing points, and realize the pressing and fixing of the unfolded part of the phased array antenna; Step 4: Install one deployment arm bracket of the deployment locking mechanism on the side of the main frame, pry open the locking hook, fold the deployment locking mechanism, and then fix the other deployment arm bracket on the side of the deployed part of the phased array antenna.

[0015] The present invention also provides a working method of a deployment device for a spaceborne phased array antenna, which is specifically as follows: During the launch ascent phase, the deployment device of the onboard phased array antenna is in a compressed state, and the deployed part of the phased array antenna is fixed on the satellite surface through the compression release mechanism; When the satellite needs to be deployed after entering orbit, the hot knife is powered on to heat and fuse the tension cable, and the compression release mechanism releases the deployed part of the phased array antenna; the deployed part of the phased array antenna begins to deploy under the drive of the torsion spring in the deployment locking mechanism. During the deployment process, the two deployment arms and the two deployment arm brackets always maintain a parallelogram structure, so that the deployed part of the phased array antenna is always parallel to the phased array antenna body until it is fully deployed; when the deployed part of the phased array antenna is coplanar with the phased array antenna body, the two deployment arms contact each other, and the locking hooks installed on the two deployment arms engage with each other to complete the locking.

[0016] Compared with the prior art, the invention has the following beneficial effects: the invention is a deployment solution for large-size and heavy-weight satellite-borne phased array antennas. The deployment device has an array face facing outward in the folded state, so the load test can be completed in the folded state; in addition, in extreme cases, if the mechanism fails and cannot be deployed, the phased array antenna can also have certain communication functions.

[0017] The deployment device of the satellite-borne phased array antenna described in the present invention has no working condition where the array surfaces are opposite to each other in the folded state, thereby avoiding the risk of collision and damage between the array surfaces. Even if the mechanical environment of the launch ascent phase is harsh, collision damage can be avoided by adding a protective pad at the bottom of the deployed part.

[0018] The deployment device of the satellite-borne phased array antenna of the present invention adopts a translational deployment method. Compared with the flip deployment, its rotational inertia is smaller, so the disturbance to the whole satellite is smaller and the driving force requirement is also smaller. The deployment locking mechanism is driven by the joint action of four torsion springs, avoiding the excessive driving force caused by a single driving force and the strict requirements on the strength of the structural parts.

[0019] During the entire process from being compressed to being deployed, the deployment locking mechanism of the on-board phased array antenna deployment device of the present invention always maintains a parallelogram state, ensuring that the deployed part of the phased array antenna and the body-mounted part are always parallel, and can effectively achieve the coplanar effect after being deployed in place. After being deployed in place, the deployment locking mechanism can complete three-point locking through the coordinated action of the locking hook and the deployment arm, and the locking effect is good.

[0020] The stiffness and strength of the deployed part of the phased array antenna of the on-board phased array antenna deployment device of the present invention are good, and it has good mechanical performance resistance during the emission state and the ability to maintain the shape after being deployed in orbit. The entire process of the on-board phased array antenna deployment device of the present invention from being retracted to being locked is driven passively, without the need for additional driving power supply, and will not cause an energy burden on the entire satellite.

[0021] The compression and release mechanism of the on-board phased array antenna deployment device of the present invention uses a thermal knife unlocking method, does not use pyrotechnics, has a low cost, can be reused, and is conducive to the development of ground deployment tests; the impact is small, there are no special requirements for the ground test environment, and the impact on the satellite during on-orbit deployment is small. The compression and release mechanism compresses the deployed part of the phased array antenna through a flexible tension cable, and after unlocking, it can effectively avoid the jamming of the unlocking mechanism components on the deployment.

[0022] The on-board phased array antenna deployment device of the present invention can be expanded into multiple layers based on the one-layer deployment of the phased array antenna according to the size requirements of the phased array antenna. Each part is independent and can be re-designed / selected according to the specific requirements of the satellite, and the device has strong adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings constituting 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: Figure 1 is a schematic structural diagram of the deployment device of the on-board phased array antenna with double-sided and two-way deployment of the present invention; Figure 2 is a schematic structural diagram of the deployed part of the phased array antenna of the present invention; Figure 3 is an exploded structural diagram of the deployed part of the phased array antenna of the present invention; Figure 4 is a schematic cross-sectional structural diagram at the rope-passing hole of the deployed part of the phased array antenna of the present invention; Figure 5 is a schematic structural diagram of the deployment locking mechanism of the present invention; Figure 6 is a schematic structural diagram at the locking hook of the deployment locking mechanism of the present invention; Figure 7 Schematic diagram of the deployment arm structure according to the present invention; Figure 8 Schematic diagram of the deployment arm bracket structure according to the present invention; Figure 9 Schematic diagram of the torsion spring structure according to the present invention Figure 1 ; Figure 10 Schematic diagram of the torsion spring structure according to the present invention Figure 2 ; Figure 11 Schematic diagram of the locking hook structure according to the present invention; Figure 12 Schematic diagram of the installation of the deployment locking mechanism according to the present invention Figure 1 ; Figure 13 Schematic diagram of the installation of the deployment locking mechanism according to the present invention Figure 2 ; Figure 14 Schematic diagram of the installation of the deployment locking mechanism according to the present invention Figure 3 ; Figure 15 Schematic diagram of the compression release mechanism structure according to the present invention; Figure 16 Schematic diagram of the cross-sectional structure of the compression release mechanism according to the present invention; Figure 17 Schematic diagram of the assembly process of the deployment device of a spaceborne phased array antenna according to the present invention Figure 1 ; Figure 18 Schematic diagram of the assembly process of the deployment device of a spaceborne phased array antenna according to the present invention Figure 2 ; Figure 19 Schematic diagram of the assembly process of the deployment device of a spaceborne phased array antenna according to the present invention Figure 3 ; Figure 20 Schematic diagram of the assembly process of the deployment device of a spaceborne phased array antenna according to the present invention Figure 4 ; Figure 21 Schematic diagram of the application of the deployment device of a spaceborne phased array antenna to a large-size and heavy-weight flat satellite stacking structure according to the present invention; Figure 22 Schematic diagram of the deployment process when the deployment device of a spaceborne phased array antenna according to the present invention is in use Figure 1 ; Figure 23 Schematic diagram of the deployment process when the deployment device of a spaceborne phased array antenna according to the present invention is in use Figure 2 ; Figure 24Schematic diagram of the fully deployed state of the deployment device of a spaceborne phased array antenna according to the present invention; Figure 25 Schematic diagram of the latching process of the locking hook according to the present invention; Figure 26 Schematic diagram of the locking effect of the deployment locking mechanism according to the present invention; Figure 27 Schematic diagram of the structure of the deployment device of a spaceborne phased array antenna with one-way deployment on one side according to the present invention; Figure 28 Schematic diagram of the deployment process of the deployment device of a spaceborne phased array antenna with one-way deployment on one side according to the present invention; Figure 29 Schematic diagram of the fully deployed state of the deployment device of a spaceborne phased array antenna with one-way deployment on one side according to the present invention.

[0024] In the figure: 1 - Deployment part of the phased array antenna, 2 - Deployment locking mechanism, 3 - Compression release mechanism, 4 - Sub - array of the phased array antenna, 5 - Deployment cabin panel, 6 - Deployment frame, 7 - First carbon fiber tube, 8 - Second carbon fiber tube, 9 - First metal joint, 10 - Second metal joint, 11 - Third metal joint, 12 - Installation hole for the deployment mechanism, 13 - Rope - passing hole, 14 - Tapered hole, 15 - Deployment arm, 16 - Deployment arm bracket, 17 - Special - shaped nut, 18 - Torsion spring, 19 - Locking hook, 20 - Locking spring, 21 - Pin, 22 - Rotating shaft hole, 23 - Torsion spring fixing hole, 24 - Locking hook groove, 25 - Locking hook rotating shaft hole, 26 - Pin hole, 27 - Rotating shaft, 28 - Torsion spring fixing platform, 29 - Installation counterbore, 30 - External thread structure, 31 - First torsion spring fixing arm, 32 - Second torsion spring fixing arm, 33 - Hook, 34 - Spring fixing groove, 35 - Fixed seat, 36 - Tension cable, 37 - Fixed cover, 38 - Hot knife, 39 - Cone body, 40 - Internal hexagon external thread structure, 41 - Plane limit structure, 42 - Satellite top plate, 43 - Main frame, 44 - Satellite bottom plate, 45 - Stacking column, 46 - Body - mounting part of the phased array antenna. Specific embodiments

[0025] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. It should be noted that, without conflict, the embodiments and features in the embodiments of the present invention can be combined with each other. The described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments.

[0026] See Figure 1 - 29Description of this embodiment: A deployment device for a spaceborne phased array antenna, which includes a phased array antenna deployment part 1, a deployment locking mechanism 2, and a pressing and releasing mechanism 3. In the pressed state, the phased array antenna deployment part 1 is located below the satellite bottom plate 44. The side of the phased array antenna deployment part 1 is connected to the main frame 43 of the satellite through symmetrically arranged deployment locking mechanisms 2. A plurality of pressing points are provided on the phased array antenna deployment part 1, and each pressing point is connected to the satellite through a pressing and releasing mechanism 3. Phased array antenna sub-arrays 4 are provided on both the phased array antenna deployment part 1 and the satellite bottom plate 44. The phased array antenna sub-array 4 is installed on the surface of the satellite bottom plate 44 to form the phased array antenna body installation part 46. The deployment locking mechanism 2 includes a deployment arm 15, a deployment arm bracket 16, a torsion spring 18, and a locking hook 19. The two ends of the two deployment arms 15 are rotatably connected to the two ends of the two deployment arm brackets 16 to form a parallelogram structure. A torsion spring 18 is provided at the connection between the deployment arm 15 and the deployment arm bracket 16. One end of the torsion spring 18 is connected to the deployment arm 15, and the other end is connected to the deployment arm bracket 16. A locking hook 19 is rotatably connected to the opposite side of the two deployment arms 15. The side of the locking hook 19 is connected to the deployment arm 15 through a locking spring 20. One of the deployment arm brackets 16 of the deployment locking mechanism 2 is connected to the phased array antenna deployment part 1, and the other deployment arm bracket 16 is connected to the main frame 43. The pressing and releasing mechanism 3 includes a fixed seat 35, a cable 36, a fixed cover 37, and a thermal knife 38. The fixed seat 35 is provided on the satellite bottom plate 44. The fixed cover 37 is provided on the phased array antenna deployment part 1. A rope passing hole 13 is correspondingly opened on the phased array antenna deployment part 1. The cable 36 passes through the rope passing hole 13. The two ends of the cable 36 are respectively connected to the fixed seat 35 and the fixed cover 37. The fixed cover 37 is provided with a thermal knife 38. The thermal knife 38 contacts the cable 36. When the thermal knife 38 is powered on and heated, the cable 36 can be melted to achieve the release effect.

[0027] As Figures 27 - 29 shown, the structure of the deployment device of the spaceborne phased array antenna in this embodiment can be for unilateral and unidirectional deployment. Above the phased array antenna body installation part 46, a phased array antenna deployment part 1 covering the entire phased array antenna body installation part 46 is provided. Deployment locking mechanisms 2 are symmetrically arranged on both sides of one phased array antenna deployment part 1. After unlocking, the deployment locking mechanism 2 drives the phased array antenna deployment part 1 to deploy unidirectionally along one side. In this way, the utilization rate of the phased array antenna deployment part 1 is high, and more phased array antenna sub-arrays 4 can be arranged. Moreover, only two deployment locking mechanisms 2 are needed to achieve deployment in this way, and the lightweight design is better.

[0028] As Figure 1As shown in the figure, the number of the phased array antenna deployment parts 1 in this embodiment is two. The two phased array antenna deployment parts 1 are symmetrically arranged, and the two phased array antenna deployment parts 1 realize bilateral and bidirectional deployment. The two phased array antenna deployment parts 1 are both arranged above the phased array antenna body installation part 46. The two phased array antenna deployment parts 1 jointly cover the phased array antenna body installation part 46. Deployment locking mechanisms 2 are symmetrically arranged on both sides of the two phased array antenna deployment parts 1. After unlocking, the deployment locking mechanisms 2 drive the two phased array antenna deployment parts 1 to deploy bilaterally and bidirectionally. The bilateral and bidirectional deployment method causes less disturbance to the satellite, reduces the requirement for the satellite's attitude and orbit control ability, and improves the reliability of the device.

[0029] On the basis of the above embodiment, the number of the phased array antenna deployment parts 1 in this embodiment is multiple. The multiple phased array antenna deployment parts 1 are arranged layer by layer in the vertical direction. The adjacent phased array antenna deployment parts 1 are connected by the deployment locking mechanisms 2, and the multiple phased array antenna deployment parts 1 realize multi-layer deployment. This method expands the single-layer deployment scheme to a multi-layer deployment scheme. One or more layers of phased array antenna deployment parts 1 are added on the top of the existing single-layer deployed phased array antenna deployment parts 1, and the multi-layer deployment effect can be achieved, further improving the deployment ability of the phased array antenna. The satellite can select a specific deployment scheme according to its specific overall satellite indicators.

[0030] This embodiment takes the deployment device of a spaceborne phased array antenna with the phased array antenna deployment part 1 deploying bilaterally and bidirectionally as an example. As Figure 2 and Figure 3 shown, the phased array antenna deployment part 1 includes a deployment cabin plate 5 and a deployment frame 6. The deployment cabin plate 5 is arranged on one side of the deployment frame 6, and the other side is in contact with the satellite bottom plate 44. The phased array antenna sub-array 4 is arranged on the deployment cabin plate 5. The deployment frame 6 is formed by connecting a plurality of carbon fiber tubes and a plurality of metal joints. The carbon fiber tubes include a first carbon fiber tube 7 and a second carbon fiber tube 8. The metal joints include a first metal joint 9, a second metal joint 10, and a third metal joint 11.

[0031] As Figure 3 shown, the installation method of the phased array antenna deployment part 1 is as follows: the carbon fiber tubes and the metal joints are nested together and fixed with structural adhesive, and then the deployment cabin plate 5 is fixed on the surface of the deployment frame 6 by screws. Finally, the phased array antenna sub-array 4 is installed and fixed on the surface of the deployment cabin plate 5. There is a deployment mechanism installation hole 12 on the side of the phased array antenna deployment part 1 for the fixation of the deployment locking mechanism 2.

[0032] As Figure 4As shown, a rope passing hole 13 is provided at each metal joint of the phased array antenna deployment part 1. The rope passing hole 13 penetrates through the metal joint and the deployment cabin plate 5, and the tension cable 36 can pass through the rope passing hole 13. One end of the rope passing hole 13 is a tapered hole 14. As Figure 15 and 16 shown, a cone body 39 is provided on the fixed seat 35, and the cone body 39 is in shape fit with the tapered hole 14. The cone body 39 is a cavity structure. One end of the tension cable 36 is provided with a planar limiting structure 41, and the other end is provided with an internal hexagonal external thread structure 40. The planar limiting structure 41 is clamped inside the cavity structure of the cone body 39, and the internal hexagonal external thread structure 40 passes through the fixed cover 37 and is screwed with a nut on the outside. The planar limiting structure 41 and the internal hexagonal external thread structure 40 are respectively used for pressing and fixing the upper and lower sides of the pressing and releasing mechanism 3.

[0033] As Figure 5 and Figure 6 shown, the deployment locking mechanism 2 includes deployment arms 15, deployment arm brackets 16, torsion springs 18 and locking hooks 19. The two ends of the two deployment arms 15 are rotatably connected to the two ends of the two deployment arm brackets 16 to form a parallelogram structure. A torsion spring 18 is provided at the connection between the deployment arm 15 and the deployment arm bracket 16. One end of the torsion spring 18 is connected to the deployment arm 15, and the other end is connected to the deployment arm bracket 16. A locking hook 19 is rotatably connected to one side of the two deployment arms 15 opposite to each other. The side of the locking hook 19 is connected to the deployment arm 15 through a locking spring 20. One of the deployment arm brackets 16 of the deployment locking mechanism 2 is connected to the phased array antenna deployment part 1, and the other deployment arm bracket 16 is connected to the main frame 43.

[0034] As Figure 7 and Figure 8 shown, shaft holes 22 are provided at both ends of the deployment arm 15, and shafts 27 are provided at both ends of the deployment arm bracket 16. The ends of the shafts 27 are external thread structures 30. The shafts 27 pass through the shaft holes 22, and the external thread structures 30 are screwed with special-shaped nuts 17. Torsion spring fixing holes 23 are provided at the ends of the deployment arm 15, and torsion spring fixing platforms 28 are provided on the deployment arm brackets 16.

[0035] As Figure 9 and Figure 10 shown, the torsion spring 18 includes a first torsion spring fixing arm 31 and a second torsion spring fixing arm 32. The first torsion spring fixing arm 31 is inserted into the torsion spring fixing hole 23, and the second torsion spring fixing arm 32 is connected to the torsion spring fixing platform 28. The torsion spring 18 has two forms according to different angles of the torsion spring fixing arm. When the deployment locking mechanism 2 is assembled, different torsion springs 18 will be selected according to the requirements after deployment.

[0036] As Figure 11 andFigure 12 As shown, a locking hook groove 24 is formed in the deployment arm 15. The locking hook 19 includes a rod body part and a hook 33. One end of the rod body part is the hook 33. The rod body part is located in the locking hook groove 24. Locking hook rotating shaft holes 25 corresponding in position are formed in the rod body part and the deployment arm 15. Screws are inserted into the locking hook rotating shaft holes 25 to realize the rotational connection between the deployment arm 15 and the locking hook 19. A pin hole 26 is formed on the side of the locking hook groove 24. A spring fixing groove 34 is formed in the rod body part. A pin 21 is inserted into the pin hole 26. One side of the locking spring 20 is sleeved outside the pin 21, and the other side is inserted into the spring fixing groove 34.

[0037] In the above embodiment, the materials of the fixed seat 35 and the fixed cover 37 are preferably titanium alloy to improve their strength. The cable 36 is preferably a Dyneema fiber rope, which has excellent tensile strength. The tensile strength of a single fiber rope can reach the level of kilonewtons, and several pressing points can bear the overload generated by the deployment device of the spaceborne phased array antenna in the ascending stage of launch vehicle transportation.

[0038] This embodiment is about the installation method of the deployment and locking mechanism 2, which specifically includes the following steps: Step 1: As Figure 12 shown, the pin 21 is fixed by applying glue and screwing it into the pin hole 26; the rod body part of the locking hook 19 is inserted into the locking hook groove 24, and the locking hook 19 is fixed by sequentially passing screws through the locking hook rotating shaft holes 25 of the deployment arm 15 and the rod body part; one side of the locking spring 20 is sleeved outside the pin 21, and the other side is inserted into the spring fixing groove 34.

[0039] Step 2: As Figure 13 shown, the first torsion spring fixing arm 31 of the torsion spring 18 is inserted into the torsion spring fixing hole 23 of the deployment arm 15 to complete the fixation. Then, the rotating shaft hole 22 is sleeved on the rotating shaft 27 of the deployment arm bracket 16. The second torsion spring fixing arm 32 of the torsion spring 18 is fixed on the surface of the torsion spring fixing platform 28. Then, the special-shaped nut 17 is screwed onto the external thread structure 30 to complete the fixation.

[0040] Step 3: Refer to Step 2 to complete the installation and fixation of the two deployment arms 15 and the two deployment arm brackets 16. After the installation is completed, the deployment and locking mechanism 2 is as Figure 14 shown, and the deployment and locking mechanism 2 is in the deployed state.

[0041] This embodiment is an assembly method for a deployment device of a spaceborne phased array antenna, which includes the following steps: The installation of the satellite top plate 42, the main frame 43, the satellite bottom plate 44, the stacking column 45 and the main equipment of the satellite is completed in advance. The satellite top plate 42 is installed on the top of the main frame 43, the satellite bottom plate 44 is installed on the bottom of the main frame 43, and the four stacking columns 45 are installed at the four corners of the main frame 43 respectively.

[0042] Step 1: Figure 17 As shown, the phased array antenna sub-array 4 is mounted on the surface of the satellite bottom plate 44 to form the phased array antenna body mounting part 46, one end of the tension cable 36 is connected to the fixing seat 35, the tension cable 36 is inserted into the cone 39 of the fixing seat 35, the plane limiting structure 41 is clamped in the cavity structure of the cone 39, and the fixing seat 35 is directly fixed on the main frame 43 by screws passing through the through holes of the satellite bottom plate 44. Specifically, the fixing strength of the fixing seat 35 and the satellite is ensured.

[0043] Step 2: If Figure 18 As shown, the phased array antenna sub-array 4 and the fixing cover 37 are installed on the phased array antenna deployment part 1, the tension rope 36 is passed through the rope threading hole 13 of the phased array antenna deployment part 1, the conical hole 14 of each metal joint is engaged with the conical body 39 of each fixing seat 35, and the phased array antenna deployment part 1 is stacked and installed on the surface of the satellite bottom plate 44, and the deployment frame 6 is in direct contact with the satellite bottom plate 44. Figure 19 As shown, after the tension cable 36 is passed through, the hexagonal external thread structure 40 of the tension cable 36 is led out and tightened with a nut. The tension cable 36 is connected to the fixed cover 37 by tightening the hexagonal external thread structure 40 and the nut. The clamping force of the tension cable 36 can be controlled by the torque of tightening the nut. The clamping force is adjusted to make the clamping force of each clamping point consistent, and then the nut and the hexagonal external thread structure 40 are sealed on the surface of the fixed cover 37 with glue.

[0044] Step 3: Fix the hot knife 38 on one side of the fixed cover 37, extend the hot knife 38 into the cavity of the fixed cover 37 and contact the tension cable 36, repeat the above operation to complete the connection of all the pressing points, and realize the pressing and fixing of the phased array antenna deployment part 1; Step 4: Figure 20 As shown, the deployment arm bracket 16 is provided with a mounting countersunk hole 29, and a countersunk screw is passed through the mounting countersunk hole 29 and connected to the deployment mechanism mounting hole 12, and one deployment arm bracket 16 of the deployment locking mechanism 2 is installed on the side of the main frame 43, and the locking hook 19 is opened to fold the deployment locking mechanism 2, and then the other deployment arm bracket 16 is fixed to the side of the phased array antenna deployment part 1. Repeat the above operation to complete the installation of all deployment locking mechanisms 2, thereby completing all assembly work of the deployment device of the satellite-borne phased array antenna. The effect after assembly is as follows Figure 1 or Figure 27 shown.

[0045] After the flat satellite is assembled, multi-satellite stacking can be completed through the stacking column 45, as Figure 21 shown. The combined body is launched in the form of multi-satellite stacking, thereby improving the utilization rate of the carrying space. Figure 21 The multi-satellite stacking state is shown, which is also the normal installation state, that is, the satellite bottom plate 44 is located below the main frame 43, the satellite top plate 42 is located above the main frame 43, the deployed part 1 of the phased array antenna is arranged below the satellite bottom plate 44, and the phased array antenna sub-array 4 faces the ground during operation. The attached drawings of the remaining assembly structures are flipped for clear display of the structure.

[0046] The present embodiment is a working method of a deployment device for a spaceborne phased array antenna, which is as follows: During the ascending stage of the launch vehicle, the deployment device of the spaceborne phased array antenna is in a compressed state. Through the compression release mechanism 3, the deployed part 1 of the phased array antenna is fixed on the satellite surface. The tension cable 36 tightens the fixed seat 35 and the fixed cover 37 to realize the longitudinal fixation of the deployed part 1 of the phased array antenna on the satellite surface; the tapered holes 14 of each metal joint are engaged with the tapered bodies 39 of each fixed seat 35 to realize the transverse fixation of the deployed part 1 of the phased array antenna on the satellite surface. The tensile strength of a single cable can reach the level of thousands of Newtons, and several compression points can bear the overload generated by the deployment device of the spaceborne phased array antenna during the ascending stage of the launch vehicle.

[0047] When deployment is required after the satellite is in orbit, the hot knife 38 is powered on to heat and fuse the tension cable 36, and the compression release mechanism 3 releases the deployed part 1 of the phased array antenna; since the longitudinal fixation method is realized through a flexible rope and the transverse fixation is realized through a tapered structure, no jamming problem will occur during the release process.

[0048] As Figure 22 and Figure 23 shown, after the deployed part 1 of the phased array antenna is released, the deployed part 1 of the phased array antenna starts to deploy under the drive of the torsion spring 18 in the deployment locking mechanism 2. During the deployment process, since the deployment locking mechanism 2 is composed of a pair of deployment arms 15 and a pair of deployment arm brackets 16, during the entire deployment process, the two deployment arms 15 and the two deployment arm brackets 16 always maintain a parallelogram structure state, so that the deployed part 1 of the phased array antenna is always parallel to the phased array antenna body-mounted part 46 until it is fully deployed.

[0049] As Figure 24 shown, when the deployed part 1 of the phased array antenna is deployed to be coplanar with the phased array antenna body-mounted part 46, the two deployment arms 15 contact each other. On the basis of realizing the limit to avoid excessive deployment, the double-point symmetric contact further ensures the flatness of the deployed part 1 of the phased array antenna and the phased array antenna body-mounted part 46. At the same time, the locking hooks 19 installed on the two deployment arms 15 are buckled with each other to complete the locking. The buckling process is as Figure 25 shown. After buckling, asFigure 26 As shown, the locking hook 19 engages and locks with the contact and cooperation of the deployment arm 15 to jointly achieve the three-point locking effect of the device after deployment, which can prevent the relative displacement between the deployed part 1 of the phased array antenna and the phased array antenna body mounting part 46 when the flat satellite maneuvers.

[0050] The specific embodiments of the present invention disclosed above are only used to help explain the present invention. The specific embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. According to the content of this specification, many modifications and changes can be made. These embodiments are selected and specifically described in this specification to better explain the principle and practical application of the present invention, so that those skilled in the relevant technical field can well understand and utilize the present invention.

Claims

1. A deployment device for a spaceborne phased array antenna, characterized in that: It includes a phased array antenna deployment part (1), a deployment locking mechanism (2), and a pressing and releasing mechanism (3). In the pressed state, the phased array antenna deployment part (1) is located below the satellite bottom plate (44). The side of the phased array antenna deployment part (1) is connected to the main frame (43) of the satellite through symmetrically arranged deployment locking mechanisms (2). Multiple pressing points are provided on the phased array antenna deployment part (1), and each pressing point is connected to the satellite through a pressing and releasing mechanism (3). Phased array antenna sub-arrays (4) are provided on both the phased array antenna deployment part (1) and the satellite bottom plate (44). The deployment locking mechanism (2) includes deployment arms (15), deployment arm brackets (16), torsion springs (18), and locking hooks (19). The two ends of the two deployment arms (15) are rotatably connected to the two ends of the two deployment arm brackets (16) to form a parallelogram structure. A torsion spring (18) is provided at the connection between the deployment arm (15) and the deployment arm bracket (16). One end of the torsion spring (18) is connected to the deployment arm (15), and the other end is connected to the deployment arm bracket (16). A locking hook (19) is rotatably connected to the opposite sides of the two deployment arms (15). The side of the locking hook (19) is connected to the deployment arm (15) through a locking spring (20). One of the deployment arm brackets (16) of the deployment locking mechanism (2) is connected to the phased array antenna deployment part (1), and the other deployment arm bracket (16) is connected to the main frame (43). The pressing and releasing mechanism (3) includes a fixed seat (35), a cable (36), a fixed cover (37), and a thermal knife (38). The fixed seat (35) is provided on the satellite bottom plate (44). The fixed cover (37) is provided on the phased array antenna deployment part (1). A rope passing hole (13) is correspondingly provided on the phased array antenna deployment part (1). The cable (36) passes through the rope passing hole (13). The two ends of the cable (36) are respectively connected to the fixed seat (35) and the fixed cover (37). A thermal knife (38) is provided on the fixed cover (37), and the thermal knife (38) is in contact with the cable (36).

2. The deployment device of a spaceborne phased array antenna according to claim 1, characterized in that: The number of the phased array antenna deployment parts (1) is two. The two phased array antenna deployment parts (1) are symmetrically arranged, and the two phased array antenna deployment parts (1) realize bilateral and bidirectional deployment.

3. The deployment device of a spaceborne phased array antenna according to claim 1 or 2, characterized in that: The number of the phased array antenna deployment parts (1) is multiple. The multiple phased array antenna deployment parts (1) are arranged layer by layer in the vertical direction. Adjacent phased array antenna deployment parts (1) are connected through the deployment locking mechanism (2), and the multiple phased array antenna deployment parts (1) realize multi-layer deployment.

4. The deployment device of a spaceborne phased array antenna according to claim 3, characterized in that: The phased array antenna deployment part (1) includes a deployment cabin plate (5) and a deployment frame (6). One side of the deployment frame (6) is provided with the deployment cabin plate (5), and the other side is in contact with the satellite bottom plate (44). The phased array antenna sub-array (4) is provided on the deployment cabin plate (5). The deployment frame (6) is formed by connecting multiple carbon fiber tubes and multiple metal joints. The rope passing hole (13) is provided on the metal joint.

5. The deployment device of a spaceborne phased array antenna according to claim 3, characterized in that: A conical body (39) is provided on the fixed seat (35). One end of the rope threading hole (13) is a conical hole (14). The conical body (39) is in shape fit with the conical hole (14). The conical body (39) is a cavity structure. One end of the tension cable (36) is provided with a planar limiting structure (41), and the other end is provided with an internal hexagonal external thread structure (40). The planar limiting structure (41) is snap-fitted inside the cavity structure of the conical body (39), so that the internal hexagonal external thread structure (40) passes through the fixed cover (37) and is screwed with a nut on the outside.

6. The deployment device of a spaceborne phased array antenna according to claim 3, characterized in that: Shaft holes (22) are formed at both ends of the deployment arm (15). Shafts (27) are provided at both ends of the deployment arm bracket (16). The end of the shaft (27) is an external thread structure (30). The shaft (27) passes through the shaft hole (22). The external thread structure (30) is screwed with a special-shaped nut (17). A torsion spring fixing hole (23) is formed at the end of the deployment arm (15). A torsion spring fixing platform (28) is provided on the deployment arm bracket (16). The torsion spring (18) includes a first torsion spring fixing arm (31) and a second torsion spring fixing arm (32). The first torsion spring fixing arm (31) is inserted into the torsion spring fixing hole (23), and the second torsion spring fixing arm (32) is connected to the torsion spring fixing platform (28).

7. The deployment device of a spaceborne phased array antenna according to claim 3, characterized in that: A locking hook groove (24) is formed on the deployment arm (15). The locking hook (19) includes a rod body part and a hook (33). One end of the rod body part is the hook (33). The rod body part is located in the locking hook groove (24). Locking hook shaft holes (25) corresponding in position are formed on the rod body part and the deployment arm (15). A screw is inserted into the locking hook shaft hole (25) to realize the rotational connection between the deployment arm (15) and the locking hook (19). A pin hole (26) is formed on the side of the locking hook groove (24). A spring fixing groove (34) is formed on the rod body part. A pin (21) is inserted into the pin hole (26). One side of the locking spring (20) is sleeved outside the pin (21), and the other side is inserted into the spring fixing groove (34).

8. The unfolding device of a spaceborne phased array antenna according to claim 3, characterized in that: The materials of the fixed seat (35) and the fixed cover (37) are titanium alloy, and the tension cable (36) is a Dyneema fiber rope.

9. An assembly method of a deployment device of a spaceborne phased array antenna according to any one of claims 1-8, characterized in that: It includes the following steps: Step 1: Install the phased array antenna subarray (4) on the surface of the satellite base plate (44) to form the phased array antenna body installation part (46). Connect one end of the tension cable (36) to the fixed seat (35), and fix the fixed seat (35) on the main frame (43) by passing a screw through the through hole of the satellite base plate (44). Step 2: Install the phased array antenna subarray (4) and the fixed cover (37) on the phased array antenna deployment part (1). Pass the tension cable (36) through the rope threading hole (13) of the phased array antenna deployment part (1). Stack and install the phased array antenna deployment part (1) on the surface of the satellite base plate (44). Adjust the pressing force so that the pressing forces at each pressing point are kept consistent. Connect the tension cable (36) to the fixed cover (37). Step 3: fix the hot knife (38) on one side of the fixing cover (37), extend the hot knife (38) into the cavity of the fixing cover (37) and contact the tension cable (36), complete the connection of all the pressing points, and realize the pressing and fixing of the unfolded part (1) of the phased array antenna; Step 4: Install one deployment arm bracket (16) of the deployment locking mechanism (2) on the side of the main frame (43), pry open the locking hook (19), fold the deployment locking mechanism (2), and then fix the other deployment arm bracket (16) on the side of the phased array antenna deployment part (1).

10. A method for deploying a spaceborne phased array antenna according to any one of claims 1 to 8, characterized in that: In the launch ascending stage, the deployment device of the satellite-borne phased array antenna is in a compressed state, and the deployed part (1) of the phased array antenna is fixed on the surface of the satellite through a compression release mechanism (3); When the satellite needs to be deployed after entering orbit, the hot knife (38) is powered on to heat and fuse the tension rope (36), and the compression release mechanism (3) releases the phased array antenna deployment part (1); the phased array antenna deployment part (1) begins to deploy under the drive of the torsion spring (18) in the deployment locking mechanism (2), and during the deployment process, the two deployment arms (15) and the two deployment arm brackets (16) always maintain a parallelogram structure state, so that the phased array antenna deployment part (1) and the phased array antenna body mounting part (46) are always parallel until they are fully deployed; when the phased array antenna deployment part (1) and the phased array antenna body mounting part (46) are coplanar, the two deployment arms (15) contact each other, and the locking hooks (19) installed on the two deployment arms (15) are mutually buckled to complete the locking.

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