A deployment device for a spaceborne phased array antenna and its assembly and operating method

Abstract

The present invention proposes a deployment device for a satellite-borne phased array antenna and its assembly and operating method, belonging to the technical field of space product structure and mechanism design. The device solves the problem of limited deployment capability of existing deployable phased array antennas. The deployment device includes a phased array antenna deployment portion, a deployment locking mechanism, and a compression release mechanism. In the compressed state, the phased array antenna deployment portion is located below the satellite base plate. The side of the phased array antenna deployment portion is connected to the satellite's main frame via symmetrically arranged deployment locking mechanisms. Multiple compression points are provided on the phased array antenna deployment portion, each of which is connected to the satellite via a compression release mechanism. Phased array antenna sub-arrays are provided on both the phased array antenna deployment portion and the satellite base plate. The deployment locking mechanism includes a deployment arm, a deployment arm bracket, a torsion spring, and a locking hook. The two ends of the two deployment arms are rotatably connected to the two ends of the deployment arm bracket. The device is primarily used for deploying 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 in particular relates to a deployment device for a spaceborne phased array antenna and an assembly and operating method thereof. Background Art

[0002] Compared with passive phased array antennas, active phased array antennas have the advantages of flexible beam, high reliability, high power efficiency, and strong anti-interference ability. Therefore, communication satellites often use active phased array antennas as their onboard communication payloads. Each antenna unit of the active phased array antenna has an independent transmit / receive module and independent control phase and amplitude, which also results in its heavy weight. For example, the Starlink onboard antenna is expected to be about 50kg / m 2 Currently under development, satellite-borne phased array antennas often occupy several square meters and weigh hundreds of kilograms. Furthermore, active phased array antennas also have high requirements for flatness; failure to meet this requirement can significantly degrade antenna performance. For these reasons, current communication satellite networks typically utilize a flat-panel configuration, employing a single, integrated mounting surface for the phased array antennas to meet both load-bearing capacity and flatness requirements.

[0003] As the size of satellite-borne phased array antennas continues to increase, the carrier fairing can no longer meet the mounting requirements of some antennas. Therefore, deployable phased array antennas have gradually become a research hotspot. Currently, the most common deployable phased array antenna is: the phased array antenna body is arranged on a complete mounting surface of the satellite. The deployed portion of the phased array antenna is mounted at the bottom of the body via a root hinge and a clamping mechanism. After the clamping mechanism is unlocked, the deployed portion rotates around the hinge axis driven by the root hinge and unfolds. Once fully deployed, it is locked by the locking component of the root hinge.

[0004] The above-mentioned deployable phased array antenna has the following defects:

[0005] First, in the retracted state, the mounted and deployed parts of the phased array antenna face each other. At this point, the satellite has no exposed array surface, so no load testing can be performed before the antenna is deployed. If the mechanism fails and cannot be deployed, the entire phased array antenna will lose its function.

[0006] Second, when in the retracted state, the mounted and deployed phased array antennas face each other. If the distance between the arrays is small or the mechanical conditions during the launch ascent are severe, there is a risk of collision and damage.

[0007] Third, the satellite-borne active phased array antenna is heavy and has a large inertia when flipping and deploying. Therefore, the antenna deployment will cause a large disturbance to the entire satellite and require the root hinge to have a large driving force.

[0008] Fourth, the larger driving force of the root hinge further increases the requirements for the clamping force before the antenna is deployed and the strength of the driving mechanism structure. The larger driving force will also cause a larger locking impact.

[0009] 5. It is difficult to ensure that the rotation angle of the unfolded antenna array is exactly coplanar with the body-mounted array surface. The deviation of the rotation angle will cause the flatness of the antenna array surface and affect the antenna performance.

[0010] 6. The locking force arm at the root hinge position is short and the locking effect is poor. Slight angle changes in the root hinge part have an amplifying effect on the antenna array surface, which will also cause the flatness of the array surface and affect the antenna performance. Summary of the Invention

[0011] In view of this, the present invention aims to provide a deployment device for a spaceborne phased array antenna and an assembly and operating method thereof, so as to solve the problems of the deployment capability of existing deployable phased array antennas.

[0012] To achieve the above-mentioned purpose, the present invention adopts the following technical solutions: a deployment device for a satellite-borne phased array antenna, which includes a phased array antenna deployment part, a deployment locking mechanism and a compression release mechanism. In the compressed state, the phased array antenna deployment part is located below the satellite base plate, and the side of the phased array antenna deployment part is connected to the main frame of the satellite through a symmetrically arranged deployment locking mechanism. The phased array antenna deployment part is provided with a plurality of compression points, each of which is connected to the satellite through a compression release mechanism. Phased array antenna sub-arrays are provided on the phased array antenna deployment part and the satellite base plate. The opening and locking mechanism includes a deployment arm, a deployment arm bracket, a torsion spring, and a locking hook. The two ends of the two deployment arms are rotatably connected to the two ends of the deployment arm brackets to form a parallelogram structure. The connection between the deployment arm and the deployment arm bracket is provided with a torsion spring, one end of the torsion spring is connected to the deployment arm, and the other end is connected to the deployment arm bracket. The two deployment arms are rotatably connected to the locking hook on the opposite side, and the side of the locking hook is connected to the deployment arm via the locking spring. One deployment arm bracket of the deployment locking mechanism is connected to the deployed portion of the phased array antenna, and the other deployment arm bracket is connected to the main frame. The compression release mechanism includes a fixing seat, a tension rope, a fixing cover, and a hot knife. The fixing seat is provided on the satellite base plate, and the fixing cover is provided on the deployed portion of the phased array antenna. The deployed portion of the phased array antenna has corresponding rope threading holes, and the tension rope passes through the rope threading holes. The ends of the tension rope are respectively connected to the fixing seat and the fixing cover. The fixing cover is provided with a hot knife, which contacts the tension rope.

[0013] 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 can achieve bilateral and bidirectional deployment.

[0014] Furthermore, there are multiple phased array antenna deployment parts, and the multiple phased array antenna deployment parts are arranged layer by layer in the vertical direction. Adjacent phased array antenna deployment parts are connected by a deployment locking mechanism, and the multiple phased array antenna deployment parts realize multi-layer deployment.

[0015] Furthermore, the deployment part of the phased array antenna includes a deployment panel and a deployment frame. The deployment panel is provided on one side of the deployment frame, and the other side is in contact with the satellite base plate. The phased array antenna sub-array is provided on the deployment panel. The deployment frame is formed by interconnecting multiple carbon fiber tubes and multiple metal joints, and the rope threading hole is provided on the metal joint.

[0016] Furthermore, a conical body is provided on the fixing seat, one end of the rope threading hole is a conical hole, the conical body matches the shape of the conical hole, the conical body is a cavity structure, one end of the tension rope is provided with a plane limiting structure, and the other end is provided with an inner hexagonal external thread structure, the plane limiting structure is clamped inside the cavity structure of the conical body, so the inner hexagonal external thread structure passes through the rear outer side of the fixing cover and is threaded on the nut.

[0017] Furthermore, a rotating shaft hole is provided at both ends of the deployment arm, and a rotating shaft is provided at both ends of the deployment arm bracket. The end of the rotating shaft is an external thread structure, and the rotating shaft passes through the rotating shaft hole. The external thread structure is screwed to the special-shaped nut. A torsion spring fixing hole is provided at the end of the deployment arm, and a torsion spring fixing platform is provided 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.

[0018] Furthermore, a locking hook slot is provided on the deployment arm, and the locking hook includes a rod body part and a hook, one end of the rod body part is a hook, and the rod body part is located in the locking hook slot, and corresponding locking hook shaft holes are provided on the rod body part and the deployment arm, and a screw is inserted into the locking hook shaft hole to realize the rotational connection between the deployment arm and the locking hook, and a pin hole is provided on the side of the locking hook slot, and a spring fixing slot is provided on the rod body part, and a pin is inserted into the pin hole, and one side of the locking spring is sleeved on the outside of the pin, and the other side is inserted into the spring fixing slot.

[0019] Furthermore, the fixing seat and the fixing cover are made of titanium alloy, and the tension rope is a Dyneema fiber rope.

[0020] The present invention also provides a method for assembling a deployment device for a spaceborne phased array antenna, which comprises the following steps:

[0021] Step 1: Install the phased array antenna sub-array on the surface of the satellite base plate to form the phased array antenna body. Connect one end of the tension cable to the fixing base, and fix the fixing base to the main frame by screwing it through the through hole of the satellite base plate.

[0022] Step 2: Install the phased array antenna sub-arrays and the fixing cover on the phased array antenna deployment part. Pass the tensioning cable through the rope threading hole of the phased array antenna deployment part. Stack the phased array antenna deployment part and install it on the surface of the satellite base plate. Adjust the pressing force to ensure that the pressing force at each pressing point is consistent. Connect the tensioning cable to the fixing cover.

[0023] 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, completing the connection of all the pressing points to achieve the compression and fixation of the unfolded part of the phased array antenna;

[0024] Step 4: Install one deployment arm bracket of the deployment locking mechanism on the side of the main frame, open the locking hook, fold the deployment locking mechanism, and then fix the other deployment arm bracket to the side of the deployed part of the phased array antenna.

[0025] The present invention also provides a working method of a deployment device for a spaceborne phased array antenna, which is specifically as follows:

[0026] 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;

[0027] When the satellite needs to be deployed after entering orbit, the hot knife is energized and heated to melt 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 part until it is fully deployed; when the deployed part of the phased array antenna is coplanar with the phased array antenna body part, 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.

[0028] Compared with existing technologies, the present invention offers the following advantages: It provides a deployment solution for large, heavy, and spaceborne phased array antennas. When the deployment mechanism is retracted, the array faces outward, enabling load testing in this state. Furthermore, in extreme cases where a mechanism failure prevents deployment, the phased array antenna can still maintain certain communication capabilities.

[0029] 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.

[0030] The deployment mechanism for the satellite-borne phased array antenna described in this invention utilizes a translational deployment method. Compared to a rotational deployment method, its rotational inertia is smaller, resulting in less disturbance to the entire satellite and requiring less driving force. The deployment locking mechanism is actuated by four torsion springs, avoiding the excessive driving force and stringent structural strength requirements associated with a single driving force.

[0031] The deployment locking mechanism of the satellite-borne phased array antenna deployment device described herein maintains a parallelogram shape throughout the entire process from compression to deployment, ensuring that the deployed portion of the phased array antenna remains parallel to the body-mounted portion, effectively achieving a coplanar effect after full deployment. Once fully deployed, the deployment locking mechanism achieves a three-point locking effect through the coordinated action of the locking hook and the deployment arm, providing excellent locking effectiveness.

[0032] The deployed portion of the satellite-borne phased array antenna deployment device of the present invention exhibits excellent rigidity and strength, providing excellent mechanical resistance during launch and shape-maintaining capability after on-orbit deployment. The entire process, from retraction to locking, of the satellite-borne phased array antenna deployment device of the present invention is passively driven, requiring no additional power supply and minimizing energy burden on the entire satellite.

[0033] The compression and release mechanism of the satellite-borne phased array antenna deployment device described in this invention utilizes a hot knife unlocking method, eliminating the need for explosives. This mechanism is low-cost, reusable, and facilitates ground deployment testing. It also offers low impact, requires no special ground testing environment, and minimizes impact on the satellite during in-orbit deployment. The compression and release mechanism compresses the deployed portion of the phased array antenna using a flexible tension cable. Once unlocked, this mechanism effectively prevents jamming of the unlocking mechanism components.

[0034] The satellite-borne phased array antenna deployment device described in this invention can be expanded from a single-layer deployment to a multi-layer deployment based on the required size of the phased array antenna. Each component is independent of each other, allowing for secondary design and selection based on the specific needs of the satellite, making the device highly adaptable. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The accompanying drawings, which constitute part of the present invention, are provided to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are provided to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0036] Figure 1 This is a schematic structural diagram of the deployment device of the bilaterally and bidirectionally deployable satellite-borne phased array antenna according to the present invention;

[0037] Figure 2 This is a schematic diagram of the unfolded structure of the phased array antenna according to the present invention;

[0038] Figure 3 This is a schematic diagram of the exploded structure of the deployed portion of the phased array antenna according to the present invention;

[0039] Figure 4 This is a schematic diagram of the cross-sectional structure of the rope threading hole of the unfolded portion of the phased array antenna according to the present invention;

[0040] Figure 5 This is a schematic structural diagram of the deployment and locking mechanism of the present invention;

[0041] Figure 6 This is a structural diagram of the locking hook portion of the deployment locking mechanism of the present invention;

[0042] Figure 7 Schematic diagram of the deployment arm structure of the present invention;

[0043] Figure 8 This is a schematic diagram of the deployment arm support structure of the present invention;

[0044] Figure 9 Schematic diagram of the torsion spring structure of the present invention Figure 1 ;

[0045] Figure 10 Schematic diagram of the torsion spring structure of the present invention Figure 2 ;

[0046] Figure 11 This is a schematic diagram of the locking hook structure of the present invention;

[0047] Figure 12 Schematic diagram of the installation of the deployment locking mechanism of the present invention Figure 1 ;

[0048] Figure 13 Schematic diagram of the installation of the deployment locking mechanism of the present invention Figure 2 ;

[0049] Figure 14 Schematic diagram of the installation of the unfolding locking mechanism of the present invention Figure 3 ;

[0050] Figure 15 This is a structural diagram of the compression and release mechanism of the present invention;

[0051] Figure 16 Schematic diagram of the cross-sectional structure of the compression and release mechanism of the present invention;

[0052] 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 ;

[0053] 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 ;

[0054] 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 ;

[0055] 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 ;

[0056] Figure 21 This is a schematic diagram of the stacking structure of a satellite-borne phased array antenna deployment device according to the present invention applied to a large-size and heavy-weight flat-panel satellite;

[0057] Figure 22 Schematic diagram of the deployment process of the deployment device of a spaceborne phased array antenna according to the present invention when in use Figure 1 ;

[0058] Figure 23 Schematic diagram of the deployment process of the deployment device of a spaceborne phased array antenna according to the present invention when in use Figure 2 ;

[0059] Figure 24 This is a schematic diagram of a deployment device for a spaceborne phased array antenna according to the present invention in a deployed state;

[0060] Figure 25 This is a schematic diagram of the locking hook fastening process of the present invention;

[0061] Figure 26 This is a schematic diagram of the locking effect of the deployment locking mechanism of the present invention;

[0062] Figure 27 This is a schematic structural diagram of the deployment device for the unilaterally and unidirectionally deployable satellite-borne phased array antenna of the present invention;

[0063] Figure 28 Schematic diagram of the deployment process of the deployment device of the unilaterally unidirectionally deployable satellite-borne phased array antenna according to the present invention;

[0064] Figure 29 This is a schematic diagram of the completion of the deployment of the deployment device of the unilaterally unidirectionally deployable satellite-borne phased array antenna described in the present invention.

[0065] In the picture:

[0066] 1-Phase array antenna deployment part, 2-Deployment locking mechanism, 3-Compression release mechanism, 4-Phase array antenna sub-array, 5-Deployment cabin, 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-Deployment mechanism mounting hole, 13-Rope hole, 14-Conical hole, 15-Deployment arm, 16-Deployment arm bracket, 17-Special nut, 18-Torsion spring, 19-Locking hook, 20-Locking spring, 21-Pin, 22-Horseshaft hole, 23-Torsion spring fixing hole, 2 4-locking hook slot, 25-locking hook shaft hole, 26-pin hole, 27-shaft, 28-torsion spring fixing platform, 29-mounting countersunk hole, 30-external thread structure, 31-first torsion spring fixing arm, 32-second torsion spring fixing arm, 33-hook, 34-spring fixing slot, 35-fixing seat, 36-tension rope, 37-fixing cover, 38-hot knife, 39-conical body, 40-hexagonal external thread structure, 41-plane limiting structure, 42-satellite top plate, 43-main frame, 44-satellite bottom plate, 45-stacked column, 46-phased array antenna body mounting part. DETAILED DESCRIPTION

[0067] The following will clearly and completely explain the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. It should be noted that the embodiments of the present invention and the features therein can be combined with each other without conflict, and the embodiments described are only part of the embodiments of the present invention, not all of the embodiments.

[0068] See also Figure 1-29The present embodiment describes a deployment device for a satellite-borne phased array antenna, which includes a phased array antenna deployment portion 1, a deployment locking mechanism 2, and a compression release mechanism 3. In the compressed state, the phased array antenna deployment portion 1 is located below the satellite base plate 44. The side of the phased array antenna deployment portion 1 is connected to the main frame 43 of the satellite through a symmetrically arranged deployment locking mechanism 2. The phased array antenna deployment portion 1 is provided with a plurality of compression points, each of which is connected to the satellite through a compression release mechanism 3. The phased array antenna deployment portion 1 and the satellite base plate 44 are both provided with phased array antenna sub-arrays 4, which are mounted on the surface of the satellite base plate 44 to form a phased array antenna body mounting portion 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. The connection between the deployment arm 15 and the deployment arm bracket 16 is provided with a torsion spring 18. 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. The two deployment arms 15 are rotatably connected to the opposite side with a locking hook 19. 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 compression release mechanism 3 includes a fixing seat 35, a tension rope 36, a fixing cover 37 and The hot knife 38, the fixing seat 35 is arranged on the satellite base plate 44, the fixing cover 37 is arranged on the phased array antenna deployment part 1, and a rope hole 13 is correspondingly opened on the phased array antenna deployment part 1. The tension rope 36 passes through the rope hole 13, and the two ends of the tension rope 36 are respectively connected to the fixing seat 35 and the fixing cover 37. The fixing cover 37 is provided with a hot knife 38, and the hot knife 38 is in contact with the tension rope 36. The hot knife 38 is electrically heated to melt the tension rope 36, thereby achieving a release effect.

[0069] like Figure 27-Figure 29 As shown, this embodiment can be a deployment device structure for a single-sided, unidirectionally deployable satellite-borne phased array antenna. A phased array antenna deployment portion 1 is disposed above the phased array antenna body portion 46, covering the entire phased array antenna body portion 46. Deployment locking mechanisms 2 are symmetrically disposed on either side of the phased array antenna deployment portion 1. When unlocked, the deployment locking mechanisms 2 drive the phased array antenna deployment portion 1 to deploy in a single, unidirectional manner. This approach improves the utilization rate of the phased array antenna deployment portion 1, allowing for the deployment of more phased array antenna sub-arrays 4. Furthermore, this approach only requires two deployment locking mechanisms 2 to achieve deployment, resulting in a more lightweight design.

[0070] like Figure 1As shown, in this embodiment, the two phased array antenna deployment sections 1 are symmetrically arranged, enabling bilateral and bidirectional deployment. Both phased array antenna deployment sections 1 are positioned above the phased array antenna mounting section 46, collectively covering the mounting section 46. Deployment locking mechanisms 2 are symmetrically positioned on either side of each phased array antenna deployment section 1. When unlocked, the deployment locking mechanisms 2 cause the two phased array antenna deployment sections 1 to deploy in both directions. This bilateral and bidirectional deployment method minimizes disturbance to the satellite, reduces the satellite's attitude and orbit control requirements, and improves device reliability.

[0071] Building on the above-mentioned embodiment, this embodiment comprises multiple phased array antenna deployment sections 1, each arranged vertically layer by layer. Adjacent phased array antenna deployment sections 1 are connected by a deployment locking mechanism 2, enabling multi-layer deployment. This approach expands a single-layer deployment scheme into a multi-layer one. Adding one or more layers of phased array antenna deployment sections 1 on top of an existing single-layer deployment section 1 achieves a multi-layer deployment effect, further enhancing the deployment capability of the phased array antenna. Satellites can select a specific deployment scheme based on their specific satellite specifications.

[0072] This embodiment takes the deployment device of the satellite-borne phased array antenna in which the phased array antenna deployment part 1 is deployed in both directions along both sides as an example. Figure 2 and Figure 3 As shown, the phased array antenna deployment part 1 includes a deployment panel 5 and a deployment frame 6. The deployment panel 5 is set on one side of the deployment frame 6, and the other side is in contact with the satellite base plate 44. The phased array antenna sub-array 4 is set on the deployment panel 5. The deployment frame 6 is formed by interconnecting multiple carbon fiber tubes and multiple 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.

[0073] like Figure 3 As shown, the deployment portion 1 of the phased array antenna is installed by nesting the carbon fiber tube and metal connector together and securing them with structural adhesive. The deployment panel 5 is then fixed to the surface of the deployment frame 6 using screws. Finally, the phased array antenna sub-arrays 4 are mounted and fixed to the surface of the deployment panel 5. The deployment portion 1 has a deployment mechanism mounting hole 12 on its side for securing the deployment locking mechanism 2.

[0074] like Figure 4As shown, each metal joint of the phased array antenna deployment part 1 is provided with a rope hole 13, which passes through the metal joint and the deployment cabin 5, and the tension rope 36 can pass through the rope hole 13. One end of the rope hole 13 is a tapered hole 14. Figure 15 and 16 As shown, the fixing seat 35 is provided with a conical body 39, which mates with the conical hole 14 in shape. The conical body 39 is a hollow structure. The tension cable 36 is provided with a planar retaining structure 41 at one end and a hexagonal external thread structure 40 at the other end. The planar retaining structure 41 is engaged within the hollow structure of the conical body 39. The hexagonal external thread structure 40 passes through the rear outer side of the fixing cover 37 and is threaded with a nut. The planar retaining structure 41 and the hexagonal external thread structure 40 are respectively used to tighten and secure the upper and lower sides of the release mechanism 3.

[0075] like Figure 5 and Figure 6 As shown, 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. The opposite side of the two deployment arms 15 is rotatably connected with a locking hook 19. 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.

[0076] like Figure 7 and Figure 8 As shown, a shaft hole 22 is provided at both ends of the deployment arm 15, and a shaft 27 is 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, and the external thread structure 30 is screwed to the special-shaped nut 17. A torsion spring fixing hole 23 is provided at the end of the deployment arm 15, and a torsion spring fixing platform 28 is provided on the deployment arm bracket 16.

[0077] like Figure 9 and Figure 10 As 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 shapes depending on the angle of the torsion spring fixing arm. When the locking mechanism 2 is deployed and assembled, different torsion springs 18 are selected based on the requirements after deployment.

[0078] like Figure 11 and Figure 12 As shown, a locking hook slot 24 is provided on the deployment arm 15, and the locking hook 19 includes a rod body portion and a hook 33, one end of the rod body portion is a hook 33, and the rod body portion is located in the locking hook slot 24, and a locking hook shaft hole 25 corresponding to the position is provided on the rod body portion and the deployment arm 15, and 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, and a pin hole 26 is provided on the side of the locking hook slot 24, and a spring fixing slot 34 is provided on the rod body portion, and a pin 21 is inserted into the pin hole 26, and one side of the locking spring 20 is sleeved on the outside of the pin 21, and the other side is inserted into the spring fixing slot 34.

[0079] In the above embodiment, the material of the fixing seat 35 and the fixing cover 37 is preferably titanium alloy to improve its strength. The tension rope 36 is preferably Dyneema fiber rope, which has excellent tensile strength. The tensile strength of a single rope can reach the kilonewton level. Several compression points can bear the overload generated by the deployment device of the satellite-borne phased array antenna in the launch ascent phase.

[0080] This embodiment is a method for installing the unfolded locking mechanism 2, which specifically includes the following steps:

[0081] Step 1: If Figure 12 As shown, the pin 21 is glued and screwed into the pin hole 26 to complete the fixation; the rod part of the locking hook 19 is inserted into the locking hook groove 24, and the screw is used to pass through the locking hook shaft hole 25 of the deployment arm 15 and the rod part in sequence to complete the fixation of the locking hook 19; one side of the locking spring 20 is placed on the outside of the pin 21, and the other side is inserted into the spring fixing groove 34.

[0082] Step 2: If Figure 13 As 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, and then the shaft hole 22 is sleeved on the shaft 27 of the deployment arm bracket 16, and the second torsion spring fixing arm 32 of the torsion spring 18 is fixed to the surface of the torsion spring fixing platform 28, and then the special-shaped nut 17 is screwed onto the external thread structure 30 to complete the fixation.

[0083] 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 locking mechanism 2 is as shown in FIG. Figure 14 As shown, the deployment locking mechanism 2 is in the deployed state.

[0084] This embodiment provides a method for assembling a deployment device for a spaceborne phased array antenna, which includes the following steps:

[0085] The satellite top plate 42, main frame 43, satellite bottom plate 44, stacking columns 45, and other major satellite equipment are installed 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.

[0086] Step 1: If Figure 17 As shown, the phased array antenna sub-array 4 is mounted on the surface of the satellite base plate 44, forming the phased array antenna body 46. One end of the tension cable 36 is connected to the fixing base 35. The tension cable 36 is passed through the cone 39 of the fixing base 35, so that the planar limiting structure 41 is engaged with the cavity structure of the cone 39. The fixing base 35 is directly fixed to the main frame 43 by screws passing through the through holes of the satellite base plate 44. Specifically, the fixing strength of the fixing base 35 to the satellite is ensured.

[0087] Step 2: If Figure 18 As shown, the phased array antenna sub-array 4 and the fixing cover 37 are mounted 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, and the tapered holes 14 of each metal joint are engaged with the tapered body 39 of each fixing seat 35. The phased array antenna deployment part 1 is stacked and mounted on the surface of the satellite base plate 44, and the deployment frame 6 is in direct contact with the satellite base plate 44. Figure 19 As shown, after the tension rope 36 is passed through, the internal hexagonal external thread structure 40 of the tension rope 36 is led out and tightened with a nut. The tension rope 36 is connected to the fixed cover 37 by tightening the internal hexagonal external thread structure 40 and the nut. The tightening torque of the nut can control the clamping force of the tension rope 36, and the clamping force is adjusted to keep the clamping force of each clamping point consistent, and then glue is applied to seal the nut and the internal hexagonal external thread structure 40 on the surface of the fixed cover 37.

[0088] Step 3: Fix the hot knife 38 on one side of the fixed cover 37. Insert the hot knife 38 into the cavity of the fixed cover 37 and contact the tension cable 36. Repeat the above steps to complete the connection of all the pressing points, thus achieving the pressing and fixing of the phased array antenna deployment part 1.

[0089] Step 4: If Figure 20 As shown, the deployment arm bracket 16 is provided with a mounting countersunk hole 29. A countersunk screw is passed through the mounting countersunk hole 29 and connected to the deployment mechanism mounting hole 12. One deployment arm bracket 16 of the deployment locking mechanism 2 is mounted on the side of the main frame 43. The locking hook 19 is opened, the deployment locking mechanism 2 is folded, and then the other deployment arm bracket 16 is fixed to the side of the phased array antenna deployment part 1. Repeat the above steps to complete the installation of all deployment locking mechanisms 2, thereby completing all assembly work of the deployment device of the spaceborne phased array antenna. The effect after assembly is as follows Figure 1 or Figure 27 shown.

[0090] After the assembly is completed, the flat-panel satellites can be stacked by stacking columns 45 to form a multi-satellite stack. Figure 21 As shown, the combination is launched in the form of multiple satellite stacks, thereby improving the utilization of the carrying space. Figure 21 The figure shows a multi-satellite stacked state, which is also a normal installation state, that is, the satellite base plate 44 is located below the main frame 43, the satellite top plate 42 is located above the main frame 43, and the phased array antenna unfolded part 1 is set below the satellite base plate 44. When working, the phased array antenna sub-array 4 is facing the ground. The drawings of the remaining assembly structures have been flipped to clearly show the structure.

[0091] This embodiment is a working method of a deployment device for a spaceborne phased array antenna, specifically as follows:

[0092] During the launch ascent phase, the deployment device of the satellite-borne phased array antenna is in a compressed state. The deployment part 1 of the phased array antenna is fixed on the satellite surface through the compression release mechanism 3. The tension rope 36 tightens the fixing seat 35 and the fixing cover 37 to achieve the longitudinal fixation of the deployment part 1 of the phased array antenna on the satellite surface; the conical holes 14 of each metal joint are engaged with the conical body 39 of each fixing seat 35 to achieve the transverse fixation of the deployment part 1 of the phased array antenna on the satellite surface; the tensile strength of a single wire can reach the kilonewton level, and several compression points can bear the overload generated by the deployment device of the satellite-borne phased array antenna in the launch ascent phase.

[0093] When the satellite needs to be deployed after entering orbit, the hot knife 38 is powered on to heat and melt the tension rope 36, and the compression release mechanism 3 releases the phased array antenna deployment part 1; since the longitudinal fixation is achieved by flexible ropes and the lateral fixation is achieved by a conical structure, there will be no jamming problem during the release process.

[0094] like Figure 22 and Figure 23 As shown, after the phased array antenna deployment portion 1 is released, the phased array antenna deployment portion 1 begins 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, the two deployment arms 15 and the two deployment arm brackets 16 always maintain a parallelogram structure during the entire deployment process, so that the phased array antenna deployment portion 1 is always parallel to the phased array antenna body portion 46 until it is fully deployed.

[0095] like Figure 24 As shown, when the phased array antenna deployment portion 1 is deployed to be coplanar with the phased array antenna body portion 46, the two deployment arms 15 contact each other. On the basis of achieving position limiting to prevent excessive deployment, the two-point symmetrical contact further ensures the flatness of the phased array antenna deployment portion 1 and the phased array antenna body portion 46. At the same time, the locking hooks 19 installed on the two deployment arms 15 engage with each other to complete the locking. The locking process is as follows Figure 25 As shown. Figure 26 As shown, the locking hook 19 engages and locks, and the mutual contact of the deployment arm 15 cooperates to achieve a three-point locking effect of the device after deployment, which can prevent the phased array antenna deployment part 1 and the phased array antenna body part 46 from relative displacement when the flat-panel satellite is maneuvering.

[0096] The specific embodiments of the present invention disclosed above are intended only to help illustrate the present invention. The specific embodiments do not describe all details in detail, nor do they limit the invention to the specific embodiments described. Numerous modifications and variations are possible based on the contents of this specification. These embodiments are selected and described in detail in this specification to better explain the principles and practical applications of the present invention, thereby enabling those skilled in the art to better understand and utilize the present invention.

Claims

1. A deployment device for a spaceborne phased array antenna, characterized by: It comprises a phased array antenna deployment part (1), a deployment locking mechanism (2) and a compression release mechanism (3). When working, the phased array antenna sub-array (4) is facing the ground. In the compression 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 the symmetrically arranged deployment locking mechanism (2). The phased array antenna deployment part (1) is provided with a plurality of compression points, each of which is connected to the satellite through the compression release mechanism (3). The phased array antenna deployment part (1) and the satellite bottom plate (44) are both provided with a phased array antenna sub-array (4), the deployment locking mechanism (2) comprises 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, the connection between the deployment arm (15) and the deployment arm bracket (16) is provided with a torsion spring (18), one end of the torsion spring (18) is connected to the deployment arm (15) ) is connected to the expansion arm bracket (16), and the other end is connected to the expansion arm bracket (16). The two expansion arms (15) are rotatably connected to the opposite side with a locking hook (19). The side of the locking hook (19) is connected to the expansion arm (15) through a locking spring (20). One of the expansion arm brackets (16) of the expansion locking mechanism (2) is connected to the phased array antenna expansion part (1), and the other expansion arm bracket (16) is connected to the main frame (43). The compression release mechanism (3) includes a fixing seat (35), a tension rope (36), a fixing The invention relates to a phased array antenna system comprising a cover (37) and a hot knife (38), wherein the fixing seat (35) is arranged on the satellite bottom plate (44), the fixing cover (37) is arranged on the phased array antenna deployment part (1), a rope threading hole (13) is correspondingly opened on the phased array antenna deployment part (1), the tension rope (36) passes through the rope threading hole (13), the two ends of the tension rope (36) are respectively connected to the fixing seat (35) and the fixing cover (37), the fixing cover (37) is provided with a hot knife (38), and the hot knife (38) contacts the tension rope (36).

2. The deployment device for 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) achieve bilateral and bidirectional deployment.

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

4. The deployment device for a spaceborne phased array antenna according to claim 3, characterized in that: The phased array antenna deployment part (1) comprises a deployment panel (5) and a deployment frame (6); the deployment panel (5) is provided on one side of the deployment frame (6), and the other side is in contact with a satellite base plate (44); a phased array antenna sub-array (4) is provided on the deployment panel (5); the deployment frame (6) is formed by interconnecting a plurality of carbon fiber tubes and a plurality of metal joints; and the rope threading hole (13) is provided on the metal joint.

5. The deployment device for a spaceborne phased array antenna according to claim 3, characterized in that: A conical body (39) is provided on the fixing seat (35), one end of the rope threading hole (13) is a conical hole (14), the conical body (39) matches the conical hole (14) in shape, the conical body (39) is a cavity structure, one end of the tension rope (36) is provided with a plane limiting structure (41), and the other end is provided with an inner hexagonal external thread structure (40), the plane limiting structure (41) is clamped inside the cavity structure of the conical body (39), so the inner hexagonal external thread structure (40) passes through the fixing cover (37) and is screwed to the nut on the outside.

6. The deployment device for a spaceborne phased array antenna according to claim 3, characterized in that: The two ends of the unfolding arm (15) are provided with a rotating shaft hole (22), and the two ends of the unfolding arm bracket (16) are provided with a rotating shaft (27). The end of the rotating shaft (27) is an external thread structure (30), and the rotating shaft (27) passes through the rotating shaft hole (22). The external thread structure (30) is screwed with the special-shaped nut (17). The end of the unfolding arm (15) is provided with a torsion spring fixing hole (23), and the unfolding arm bracket (16) is provided with a torsion spring fixing platform (28). 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 for a spaceborne phased array antenna according to claim 3, characterized in that: The unfolding arm (15) is provided with a locking hook groove (24), and the locking hook (19) comprises a rod body part and a hook (33), one end of the rod body part is a hook (33), and the rod body part is located in the locking hook groove (24), and the rod body part and the unfolding arm (15) are provided with locking hook shaft holes (25) corresponding to the positions, and a screw is inserted into the locking hook shaft hole (25) to realize the rotation connection between the unfolding arm (15) and the locking hook (19), and a pin hole (26) is provided on the side of the locking hook groove (24), and a spring fixing groove (34) is provided on the rod body part, and a pin (21) is inserted into the pin hole (26), and one side of the locking spring (20) is sleeved on the outside of the pin (21), and the other side is inserted into the spring fixing groove (34).

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

9. A method for assembling a deployment device for a spaceborne phased array antenna according to any one of claims 1 to 8, characterized in that: It includes the following steps: Step 1: Install the phased array antenna sub-array (4) on the surface of the satellite base plate (44) to form the phased array antenna body (46), connect one end of the tension cable (36) to the fixing seat (35), and fix the fixing seat (35) to the main frame (43) by screwing through the through hole of the satellite base plate (44); Step 2: Install the phased array antenna sub-array (4) and the fixed cover (37) on the phased array antenna expansion part (1), pass the tension rope (36) through the rope threading hole (13) of the phased array antenna expansion part (1), and stack the phased array antenna expansion part (1) on the surface of the satellite base plate (44). Adjust the pressing force so that the pressing force of each pressing point remains consistent, and connect the tension rope (36) to the fixed cover (37); 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 rope (36), complete the connection of all the pressing points, and realize the pressing and fixing of the phased array antenna expansion part (1); Step 4: Install one deployment arm bracket (16) of the deployment locking mechanism (2) on the side of the main frame (43), 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: During the launch ascending phase, the deployment device of the satellite-borne phased array antenna is in a compressed state, and the deployed portion (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 the tension rope (36) to melt, 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). 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 part (46) are always parallel until they are fully deployed; when the phased array antenna deployment part (1) and the phased array antenna body 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 buckled together to complete the locking.

Images