A controllable and deployable large-area phased array solar wing integrated antenna

Abstract

The present invention proposes a controllably deployable large-area phased array solar wing integrated antenna, which belongs to the technical field of space product structure and mechanism design, and aims to realize the real-time adjustment capability of the phased array antenna on orbit, improve the deployment flatness of the phased array antenna, reduce the locking impact, and integrate the phased array antenna with the solar wing. The integrated antenna includes a plurality of deployment plate assemblies, a high-precision damping hinge mechanism, a locking device, a timing control expander and a deployment position detection system; each deployment plate assembly is connected by a high-precision damping hinge mechanism; the timing control expander is used to control the deployment timing between each deployment plate, and is also used to press adjacent deployment plates and control the locking device to complete the locking between each deployment plate; the deployment position detection system is used to detect the positional relationship between adjacent deployment plates, and control the high-precision damping hinge mechanism according to feedback data until it reaches a predetermined position. Suitable for large-area deployment mechanisms of phased array antennas.

Description

Technical Field

[0001] The present invention belongs to the technical field of space product structure and mechanism design, and specifically relates to a controllably deployable large-area phased array solar wing integrated antenna. Background Art

[0002] For the current large-scale (20m 2 The phased array antennas of 2000 and above were studied and found that the unfolded surface accuracy was not effectively detected and closed-loop controlled. Secondly, if the traditional mechanical hinge is used for unfolding, the problem of excessive speed of the antenna end caused by spring drive cannot be overcome, which will produce a large impact. In addition, there is a lack of theoretical research on the folding, unfolding and deformation suppression of the large-area unfolding mechanism.

[0003] The traditional large-area deployment mechanism has some shortcomings, including: First, the traditional large-area deployment mechanism requires a complex mechanism to realize its compression, synchronous deployment, and locking process, and the mechanism design is complex and the precision requirements are high, resulting in a long processing cycle and the inability to control the position accuracy between the arrays; Second, the traditional flat-panel phased array antenna lacks effective on-orbit surface closed-loop monitoring means, and cannot achieve real-time and effective adjustment of the beam pointing; Third, the traditional deployment mechanism will have the problem of excessive tail speed at the end, and the locking impact is large. Summary of the invention

[0004] The purpose of the present invention is to provide a large-area phased array solar wing integrated antenna that can be controlled and deployed, so as to achieve the real-time adjustment capability of the phased array antenna in orbit, improve the deployment flatness of the phased array antenna, reduce the locking impact, etc., and at the same time integrate the phased array antenna with the solar wing.

[0005] To achieve the above object, the present invention provides the following solutions:

[0006] The present invention provides a controllably deployable large-area phased array solar wing integrated antenna, the phased array solar wing integrated antenna comprising a plurality of deployment plate components, a high-precision damping hinge mechanism, a locking device, a timing control expander and a deployment position detection system;

[0007] Each unfolding panel assembly is connected by a high-precision damping hinge mechanism;

[0008] The timing control breaker is used to control the deployment timing between each deployment plate, and is also used to press the adjacent deployment plates and control the locking device to complete the locking between each deployment plate;

[0009] The deployment position detection system is used to detect the positional relationship between adjacent deployment panels and control the high-precision damping hinge mechanism according to feedback data until it reaches a predetermined position.

[0010] Furthermore, there is a preferred embodiment, the above-mentioned unfolded plate assembly includes a carbon fiber ultra-stable rectangular frame, a phased array antenna unit, and a solar cell module;

[0011] The phased array antenna unit and the solar cell module are respectively arranged on the front and back sides of the carbon fiber ultra-stable rectangular frame.

[0012] Furthermore, in a preferred embodiment, the carbon fiber ultra-stable rectangular frame is realized by using high modulus carbon fiber.

[0013] Furthermore, there is a preferred embodiment, the high-precision damping hinge mechanism comprises a stepping motor, a reduction gearbox, a male hinge, a female hinge and a rotating shaft;

[0014] The male hinge and the female hinge are coaxially arranged and connected by a rotating shaft;

[0015] The stepper motor and the reduction gearbox are both connected to the rotating shaft and are used to control the rotation accuracy of the rotating shaft.

[0016] Furthermore, there is a preferred embodiment, the locking device comprises a locking block, a support seat, a swing rod, a spiral spring, a rotating shaft and a locking tongue;

[0017] The locking block is coaxially arranged with the supporting seat and connected with a rotating shaft;

[0018] A volute spring and a rocker are arranged on the rotating shaft, and the rocker is connected to the rotating shaft through the volute spring;

[0019] The swing rod is used to swing through the elastic force of the spiral spring, driving the lock tongue to be installed on the locked part, and the lock tongue is blocked by the swing rod to complete the locking.

[0020] Furthermore, in a preferred embodiment, the above-mentioned phased array solar wing integrated antenna further includes an inter-board pressing device;

[0021] The inter-plate pressing device is used to ensure that the unfolded plates are pressed against each other.

[0022] Furthermore, in a preferred embodiment, the above-mentioned deployment position detection system is implemented by sensors including but not limited to proximity sensors, photoelectric switches, and laser radars.

[0023] Furthermore, in a preferred embodiment, the above-mentioned phased array solar wing integrated antenna also includes a measurement and acquisition system;

[0024] The measurement and acquisition system is used to transmit the data feedback from the deployment position detection system to the satellite platform. The satellite platform inversely calculates the dynamic characteristic data of the vibration direction, vibration amplitude and angle change relationship based on the feedback data, and controls the high-precision damping hinge mechanism to perform angle fine-tuning through the periodic law of the dynamic characteristic data.

[0025] The beneficial effects of the present invention are:

[0026] 1. The large-area deployment mechanism of the traditional phased array antenna requires a complex mechanism to achieve its function, but the mechanism design is complex and requires high precision, which will result in a long processing cycle and the inability to control the position accuracy between the arrays. The new flat-panel phased array antenna and solar wing proposed in the present invention are simple in composition, and the entire compression, deployment and locking effects can be achieved only through a high-precision damping hinge mechanism in conjunction with a timing-controlled expander.

[0027] Furthermore, the various mechanisms in the novel flat-panel phased array antenna and solar wing proposed in the present invention are simple in design, the component parts are small in size, and the precision requirements are low, which can reduce processing costs and shorten processing cycles.

[0028] 2. The traditional deployment mechanism will have a large tail speed at the end, resulting in a large locking impact. The new flat-panel phased array antenna and solar wing deployment process proposed by the present invention has a smaller impact than the traditional clamping method, which reduces the impact on the platform equipment, reduces the attitude disturbance of the satellite in orbit, and is more conducive to attitude control.

[0029] 3. The novel flat-panel phased array antenna and solar wing proposed in the present invention fully utilize the frame area, install the phased array unit on the ground, and install the solar cell module on the other side to improve the integration.

[0030] The invention is applicable to a large-area deployment mechanism of a phased array antenna. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0032] Figure 1 It is a schematic diagram of the overall composition of the phased array antenna and solar wing according to an embodiment of the present invention;

[0033] Figure 2 A schematic diagram of folding the phased array antenna and solar wing according to an embodiment of the present invention;

[0034] Figure 3 A schematic diagram of a phased array antenna and a partially unfolded solar wing panel according to an embodiment of the present invention;

[0035] Figure 4 This is a schematic diagram of the installation of the timing control breaker according to the embodiment of the present invention;

[0036] Figure 5 A schematic diagram of a locking mechanism according to an embodiment of the present invention;

[0037] Figure 6 A schematic diagram of the full deployment process of the phased array antenna and solar wings according to an embodiment of the present invention;

[0038] Figure 7 It is a schematic diagram of a deployment position detection system according to an embodiment of the present invention.

[0039] Among them, 1 represents the phased array antenna unit; 2 represents the carbon fiber ultra-stable rectangular frame; 3 represents the inter-plate clamping device; 4 represents the high-precision damping hinge mechanism; 5 represents the solar cell module; 6 represents the satellite cabin; 7 represents the timing control circuit breaker; 8 represents the locking device; 9 represents the deployment position detection system; 2-1 represents the first deployment plate; 2-2 represents the second deployment plate; 2-3 represents the third deployment plate; 2-4 represents the fourth deployment plate. DETAILED DESCRIPTION

[0040] In the following description, specific details such as specific system structures and technologies are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from obstructing the description of the present application.

[0041] The specific embodiments of the present invention are further described in detail below in conjunction with the accompanying drawings. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention.

[0042] Implementation method 1, see Figures 1 to 4 This embodiment describes a controllably deployable large-area phased array solar wing integrated antenna, which is used to achieve the real-time adjustment capability of the phased array antenna in orbit, improve the deployment flatness of the phased array antenna, and reduce locking impact, while integrating the phased array antenna with the solar wing.

[0043] The phased array solar wing integrated antenna includes a plurality of deployment plate components, a high-precision damping hinge mechanism 4, a locking device 8, a timing control expander 8 and a deployment position detection system 9;

[0044] Each unfolding plate assembly is connected by a high-precision damping hinge mechanism 4;

[0045] The timing control breaker 7 is used to control the deployment timing between the deployment plates, and is also used to press the adjacent deployment plates and control the locking device 8 to complete the locking between the deployment plates;

[0046] The deployment position detection system 9 is used to detect the positional relationship between adjacent deployment panels and control the high-precision damping hinge mechanism 4 according to feedback data until it reaches a predetermined position.

[0047] In practical application, if Figures 1 to 3 As shown, the unfolding assembly uses a carbon fiber ultra-stable rectangular frame 2 as the basic frame, and the phased array antenna unit 1 and the solar cell module 5 are fixed on the carbon fiber ultra-stable rectangular frame 2. The embedded threaded parts inside the ultra-stable carbon fiber frame 2 are connected to the high-precision damping hinge mechanism 4, that is, each unfolding plate is connected through a high-precision damping hinge mechanism 4, and the plates are locked and unfolded by a timing control breaker 7. The timing control breaker 7 is installed on the opposite side of the hinge between the two folded unfolding plates. This arrangement is conducive to improving the locking stiffness of the entire assembly. The unfolding position detection system 9 is installed near the hinge of the unfolding plate. Because the existing large-surface precision detection technology cannot guarantee the measurement accuracy, the angle / distance between the plates is measured by the unfolding position detection system, and then transmitted to the measurement acquisition system to indirectly calculate the flatness of the unfolding plate. The deployment position detection system 9 is used to detect the positional relationship between adjacent deployment plates and feed back to the satellite in the satellite cabin 6. The satellite determines whether the deployment is in place based on the feedback signal. If it is in place, the deployment process is stopped. If it is not in place, the high-precision damping hinge mechanism 4 is continuously adjusted until it reaches the predetermined position and then the locking device 8 is used to complete the locking. Figure 4 As shown, the timing-controlled expander 7 is used to compress two adjacent expansion plates, and after being unlocked by the wrapping belt, the expansion sequence of the expansion plates is controlled to ensure that the expansion sequence of each expansion plate is controlled.

[0048] The deployment position detection system 9 realizes the deployment indication of the array and measures the positional relationship between the plates through sensors including but not limited to proximity sensors, photoelectric switches, laser radars and other tools.

[0049] The new flat-panel phased array antenna and solar wing proposed in this embodiment can achieve the entire compression, deployment and locking effects only through a high-precision damping hinge mechanism and a timing-controlled expander. The high-precision damping hinge mechanism is used to replace the traditional mechanical hinge to avoid the problem of excessive antenna end speed caused by spring drive, thereby generating a large impact.

[0050] Implementation method 2: This implementation method specifically describes the display panel assembly in the controllably deployable large-area phased array solar wing integrated antenna described in the above implementation method 1;

[0051] The unfolded panel assembly includes a carbon fiber ultra-stable rectangular frame 2, a phased array antenna unit 1, and a solar cell module 5;

[0052] The phased array antenna unit 1 and the solar cell module 5 are respectively arranged on the front and back surfaces of the carbon fiber ultra-stable rectangular frame 2 .

[0053] In actual application of this embodiment, the phased array antenna unit 1 and the solar cell module 5 are connected to the ultra-stable carbon fiber frame 2 through standard parts; wherein, the carbon fiber ultra-stable rectangular frame adopts high modulus carbon fiber, and the phased array antenna unit and the solar cell module are installed on the front and back sides of the carbon fiber ultra-stable rectangular frame. Since carbon fiber has strong thermal stability, it can ensure that the rectangle reduces thermal deformation in an environment of alternating high and low temperatures.

[0054] Implementation method 3: This implementation method specifically describes the high-precision damping hinge mechanism in the controllably deployable large-area phased array solar wing integrated antenna described in the above implementation method 1;

[0055] The high-precision damping hinge mechanism includes a stepping motor, a reduction gear box, a male hinge, a female hinge and a rotating shaft;

[0056] The male hinge and the female hinge are coaxially arranged and connected by a rotating shaft;

[0057] The stepper motor and the reduction gearbox are both connected to the rotating shaft and are used to control the rotation accuracy of the rotating shaft.

[0058] In actual application of this embodiment, the male and female hinges are coaxially installed, the rotating shaft passes through the rotating shaft hole, and the stepper motor and the reduction gearbox are installed on the rotating shaft to control the rotation accuracy of the rotating shaft.

[0059] Implementation method 4: See Figure 5 This embodiment is described. This embodiment specifically describes the locking device in the controllably deployable large-area phased array solar wing integrated antenna described in the first embodiment above.

[0060] The locking device comprises a locking block, a supporting seat, a swing rod, a spiral spring, a rotating shaft and a locking tongue;

[0061] The locking block is coaxially arranged with the supporting seat and connected with a rotating shaft;

[0062] A volute spring and a rocker are arranged on the rotating shaft, and the rocker is connected to the rotating shaft through the volute spring;

[0063] The swing rod is used to swing through the elastic force of the spiral spring, driving the lock tongue to be installed on the locked part, and the lock tongue is blocked by the swing rod to complete the locking.

[0064] In practical application, if Figure 5As shown, the locking block is installed coaxially with the support seat, a volute spring and a rocker arm are installed on the rotating shaft, the rocker arm is connected to the rotating shaft through the volute spring, the rocker arm swings due to the elastic force of the volute spring, the lock tongue is installed on the locked part, the lock tongue is blocked by the rocker arm, and the locking is completed.

[0065] Embodiment 5: This embodiment adds an inter-board pressing device 3 and a measurement and acquisition system on the basis of the controllably deployable large-area phased array solar wing integrated antenna described in the above embodiment;

[0066] The inter-plate pressing device 3 is used to ensure that the unfolded plates are pressed against each other.

[0067] The measurement and acquisition system is used to transmit the data feedback from the deployment position detection system to the satellite platform. The satellite platform inversely calculates the dynamic characteristic data of the vibration direction, vibration amplitude and angle change relationship based on the feedback data, and controls the high-precision damping hinge mechanism to perform angle fine-tuning through the periodic law of the dynamic characteristic data.

[0068] In actual application of this embodiment, the deployment position detection system 9 is used to realize the deployment indication of the array surface and measure the position relationship between the plates, and feed back to the measurement acquisition system, which is then transmitted to the satellite platform by the measurement acquisition system to judge the angular relationship of the deployment plates. Finally, the high-precision damping hinge mechanism 4 adjusts the hinge angle to ensure the flatness of the deployment array surface.

[0069] Implementation method 7: See Figure 2 , Figure 3 , Figure 6 and Figure 7 This embodiment is described. This embodiment specifically describes the deployment method of the controllably deployable large-area phased array solar wing integrated antenna described in the above embodiment.

[0070] like Figure 3 As shown, the unfolding plate comprises a phased array antenna unit 1, a carbon fiber ultra-stable rectangular frame 2, an inter-plate clamping device 3, a high-precision damping hinge mechanism 4, and a solar cell module 5. The installation relationship is that the six phased array antenna units 1 are installed on the front of the carbon fiber ultra-stable rectangular frame 2, and the solar cell module 5 is installed on the back of the carbon fiber ultra-stable rectangular frame 2. The phased array antenna unit 1 and the solar cell module 5 are connected to the carbon fiber ultra-stable rectangular frame 2 through standard parts. The pre-embedded threaded embedded parts inside the carbon fiber ultra-stable rectangular frame 2 are connected to the high-precision damping hinge mechanism 4, and each unfolding plate is connected through the high-precision damping hinge mechanism 4. The timing control breaker 7 between the plates completes the locking and unfolding timing control, as shown in FIG. Figure 2 shown.

[0071] like Figure 6As shown, a novel flat-panel phased array antenna and solar wing deployment process is shown, first the first deployment plate 2-1 is deployed, and after the first deployment plate 2-1 is fully deployed and the arrival signal is confirmed, the second deployment plate 2-2 is deployed. Repeat the above steps, and sequentially deploy the third deployment plate 2-3 and the fourth deployment plate 2-4 until they are fully deployed.

[0072] Expand position detection system 9 Figure 7 The installation shown is used to detect the positional relationship between adjacent unfolded panels. The feedback data can be sampled in time to understand the angular change relationship between the panels, and then the dynamic characteristic data such as vibration direction, vibration amplitude, and angular change relationship can be inversely calculated. According to the periodic law of the dynamic characteristics, the angle between the panels can be fine-tuned through the high-precision damping hinge mechanism 4, so that the phased array antenna can point more accurately.

[0073] In summary, the novel flat-panel phased array antenna and solar wing proposed in the above implementation mode can achieve the entire compression, deployment and locking effects only through a high-precision damping hinge mechanism in conjunction with a timing-controlled expander. The high-precision damping hinge mechanism is used to replace the traditional mechanical hinge to avoid the problem of excessive antenna end speed caused by spring drive, thereby causing a large impact.

[0074] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of described features, integers, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or groups thereof.

[0075] It should also be understood that the terms used in this application specification are only for the purpose of describing specific embodiments and are not intended to limit the present application. As used in this application specification and the appended claims, the singular forms "a", "an" and "the" are intended to include plural forms unless the context clearly indicates otherwise.

[0076] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0077] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0078] The above description is only the implementation mode of the present invention and is not limited to the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent substitution, improvement, etc. made within the spirit and principle of the present invention shall be included in the scope of the claims of the present invention.

Claims

1. A controllably deployable large-area phased array solar wing integrated antenna, characterized in that: It includes multiple deployment plate assemblies, high-precision damping hinge mechanisms, locking devices, time-controlled breakers and deployment position detection systems; Each unfolding panel assembly is connected by a high-precision damping hinge mechanism; The timing control breaker is used to control the deployment timing between each deployment plate, and is also used to press the adjacent deployment plates and control the locking device to complete the locking between each deployment plate; The deployment position detection system is used to detect the positional relationship between adjacent deployment panels and control the high-precision damping hinge mechanism according to feedback data until it reaches a predetermined position.

2. The controllably deployable large-area phased array solar wing integrated antenna according to claim 1, characterized in that: The unfolded panel assembly includes a carbon fiber ultra-stable rectangular frame, a phased array antenna unit, and a solar cell module; The phased array antenna unit and the solar cell module are respectively arranged on the front and back sides of the carbon fiber ultra-stable rectangular frame.

3. The controllably deployable large-area phased array solar wing integrated antenna according to claim 2, characterized in that: The carbon fiber ultra-stable rectangular frame is made of high modulus carbon fiber.

4. The controllably deployable large-area phased array solar wing integrated antenna according to claim 1, characterized in that: The high-precision damping hinge mechanism includes a stepping motor, a reduction gear box, a male hinge, a female hinge and a rotating shaft; The male hinge and the female hinge are coaxially arranged and connected by a rotating shaft; The stepper motor and the reduction gearbox are both connected to the rotating shaft and are used to control the rotation accuracy of the rotating shaft.

5. The controllably deployable large-area phased array solar wing integrated antenna according to claim 1, characterized in that: The locking device comprises a locking block, a supporting seat, a swing rod, a spiral spring, a rotating shaft and a locking tongue; The locking block is coaxially arranged with the supporting seat and connected with a rotating shaft; A volute spring and a rocker are arranged on the rotating shaft, and the rocker is connected to the rotating shaft through the volute spring; The swing rod is used to swing through the elastic force of the spiral spring, driving the lock tongue to be installed on the locked part, and the lock tongue is blocked by the swing rod to complete the locking.

6. The controllably deployable large-area phased array solar wing integrated antenna according to claim 1, characterized in that: Also included is an inter-plate clamping device; The inter-plate pressing device is used to ensure that the unfolded plates are pressed against each other.

7. The controllably deployable large-area phased array solar wing integrated antenna according to claim 1, characterized in that: The deployment position detection system is implemented through sensors including but not limited to proximity sensors, photoelectric switches, and laser radars.

8. The controllably deployable large-area phased array solar wing integrated antenna according to claim 1, characterized in that: It also includes a measurement acquisition system; The measurement and acquisition system is used to transmit the data feedback from the deployment position detection system to the satellite platform. The satellite platform inversely calculates the dynamic characteristic data of the vibration direction, vibration amplitude and angle change relationship based on the feedback data, and controls the high-precision damping hinge mechanism to perform angle fine-tuning through the periodic law of the dynamic characteristic data.

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