A lightweight high-thermal-stability and focal length adjustable solid surface reflector

Abstract

The application discloses a lightweight high-thermal-stability and focal length adjustable solid surface reflector, comprising a reflecting surface, an unfolding arm, a two-dimensional rotating mechanism, a first folding unfolding arm, a first one-dimensional unfolding hinge, a second folding unfolding arm, a second one-dimensional unfolding hinge and a satellite platform. The application has simple structure and good universality, can realize lightweight, high-thermal-stability, long focal length layout design and focal length adjustment of a large-aperture solid surface reflector, thereby ensuring that the antenna is no longer limited by the envelope of the satellite body, and overcoming the shortcomings of the traditional back cabinet supporting type solid surface reflector, such as heavy weight, poor thermal stability, focal length limited by the envelope of the satellite platform and unadjustable. The application is suitable for the development of high-flux satellite flexible load multi-beam antennas with high performance requirements in the future, and has wide applicability and application value.

Description

Technical Field

[0001] This invention relates to a lightweight, thermally stable, and focal-adjustable solid-surface reflector, which is particularly suitable for flexible payload multi-beam antennas that require high beam pointing accuracy, high weight, and focal length adjustment. It belongs to the field of aerospace technology. Background Technology

[0002] With the continuous development of aerospace technology, high-throughput satellites are developing rapidly, placing higher demands on multi-beam antennas, such as high thermal stability, long focal length, lightweight design, and flexibility. Existing technologies cannot meet the requirements of lightweight design, high thermal stability, and flexible focal length adjustment while maintaining a small size and high packing ratio. Therefore, there is an urgent need to develop a solid-surface reflector that is simple in structure, has a high packing ratio, high thermal stability, adjustable focal length, and is lightweight. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a lightweight, thermally stable, and focal-adjustable solid surface reflector to address the shortcomings of the prior art, for use in the field of flexible load multi-beam antennas, so as to achieve the requirements of adjustable focal length, lightweight and high thermal stability of solid surface antennas, and to have a certain structural rigidity to meet the tracking requirements of antennas.

[0004] The technical solution adopted in this invention is as follows:

[0005] A lightweight, thermally stable, and focal-adjustable solid-surface reflector includes: a reflective surface, an unfolding arm, a two-dimensional rotation mechanism, a first folding unfolding arm, a first one-dimensional unfolding hinge, a second folding unfolding arm, a second one-dimensional unfolding hinge, and a satellite platform.

[0006] The reflective surface is connected to the unfolding arm, one end of the two-dimensional rotation mechanism is connected to the unfolding arm, and the other end is connected to the first folding unfolding arm. The first folding unfolding arm is connected to the second folding unfolding arm through the first one-dimensional unfolding hinge, and the second folding unfolding arm is installed on the satellite platform through the second one-dimensional unfolding hinge.

[0007] The two-dimensional rotation mechanism is arranged near the vertex of the reflective surface to adjust the orientation of the reflective surface on the track. The first and second one-dimensional unfolding hinges remain locked after unfolding and do not participate in the adjustment of the orientation on the track.

[0008] Furthermore, it also includes a locking release device;

[0009] When folded, the reflective surface is locked to the satellite platform by four locking and releasing devices. One locking and releasing device is arranged near the two-dimensional rotating mechanism and another near the first one-dimensional unfolding hinge of the first folding and unfolding arm.

[0010] Furthermore, in the retracted state, the working surface of the reflective surface faces away from the satellite platform, and the unfolding arm, two-dimensional rotation mechanism, first folding unfolding arm, first one-dimensional unfolding hinge, second folding unfolding arm, and second one-dimensional unfolding hinge are all located below the reflective surface, forming an overlapping retracted layout.

[0011] Furthermore, the reflector adopts a backless design, with three central embedded parts that connect to three connection points on the deployable arm, ensuring that the reflector expands and contracts uniformly from the center outwards in high and low temperature environments.

[0012] Furthermore, the three central embedded parts are on a circumference. With the machining coordinate system of the reflective surface as the reference, the relationship between the projected diameter d of the circumference and the projected aperture D of the reflective surface in the XOY plane of the machining coordinate system is d=1 / 4D, so as to achieve the lightest possible weight for the unfolding arm.

[0013] Furthermore, four connectors are provided on the edge of the reflective surface, which are connected to the reflective surface body through edge embedded parts. The edge embedded parts are distributed on the edge of the reflective surface and are located within the range of 3 / 4D to D.

[0014] Furthermore, the deployable arm is a composite laminate tube, and the reflective surface is a honeycomb sandwich structure, consisting of upper and lower carbon fiber skins and a honeycomb core. The honeycomb core is an aluminum honeycomb or a carbon fiber honeycomb. The upper and lower carbon fiber skins are designed according to quasi-isotropic layup, with layup angles of [0°, ±45°, 90°, 90°, ±45°, 0°].

[0015] Furthermore, after the reflective surface is fully deployed and its orientation is adjusted, it is locked to the first and second folding arms by the locking functions of the first and second one-dimensional deployment hinges and the power-off holding torque of the two-dimensional rotation mechanism, thus ensuring the structural rigidity and stable orientation of the reflective surface.

[0016] Furthermore, after the reflector is deployed, it is located outside the satellite's envelope. The focal length is adjusted through a first one-dimensional deployment hinge, a second one-dimensional deployment hinge, and a two-dimensional rotation mechanism. It operates in different positions and achieves forward and backward displacement adjustment along the line connecting the center of the reflector and the focal point, with an adjustment range t of not less than 300 mm. The above functions are achieved by adjusting the pitch axis angle α1→α2 of the two-dimensional rotation mechanism, the angle β1→β2 of the first one-dimensional deployment hinge, and the angle γ1→γ2 of the second one-dimensional deployment hinge.

[0017] Furthermore,

[0018] Once the antenna is unlocked, the reflector completes its deployment under the combined drive of the two-dimensional rotation mechanism, the first one-dimensional deployment hinge, and the second one-dimensional deployment hinge. The deployment strategy is either a coordinated deployment or an independent, step-by-step deployment.

[0019] Linked deployment means that three components—the two-dimensional rotation mechanism, the first one-dimensional deployment hinge, and the second one-dimensional deployment hinge—operate simultaneously.

[0020] The independent, step-by-step unfolding mechanism consists of three components: a two-dimensional rotation mechanism, a first-dimensional unfolding hinge, and a second-dimensional unfolding hinge. Only one component unfolds at a time, and the unfolding steps are as follows:

[0021] The first step involves the reflector, the unfolding arm, the two-dimensional rotation mechanism, the first folding unfolding arm, the first one-dimensional unfolding hinge, and the second folding unfolding arm unfolding counterclockwise to a certain angle under the drive of the second one-dimensional unfolding hinge. This angle ensures that the reflector and the satellite platform do not physically interfere with each other.

[0022] The second step is that the reflective surface and the unfolding arm unfold clockwise to a certain angle under the drive of the two-dimensional rotation mechanism. This angle is the final angle of the pitch axis of the two-dimensional rotation mechanism.

[0023] The third step involves the reflective surface, the unfolding arm, the two-dimensional rotation mechanism, and the first folding unfolding arm unfolding clockwise to a certain angle under the drive of the first one-dimensional unfolding hinge. This angle is the final angle of the first one-dimensional unfolding hinge.

[0024] In the fourth step, the reflective surface, the unfolding arm, the two-dimensional rotation mechanism, the first folding unfolding arm, the first one-dimensional unfolding hinge, and the second folding unfolding arm together continue to unfold counterclockwise to the final angle under the drive of the second one-dimensional unfolding hinge.

[0025] The fifth step involves fine-tuning the azimuth axis of the reflective surface and the unfolding arm together under the drive of a two-dimensional rotation mechanism, thereby unfolding them into place.

[0026] Furthermore, the power source for the first and second one-dimensional unfolding hinges can be a motor or an energy storage element such as a spring. The two-dimensional rotation mechanism is driven by a motor to ensure that they unfold at a certain speed.

[0027] Compared with the prior art, the present invention has the following advantages:

[0028] (1) After the antenna is unlocked, the reflector is first tilted and rotated to the specified angle under the drive of the two-dimensional rotation mechanism and the one-dimensional unfolding hinge. Then, the working position can be achieved by fine adjustment of the azimuth axis of the two-dimensional rotation mechanism. This design structure has a high storage ratio and can meet the long focal length requirements of large-aperture reflectors. By adjusting the rotation angle of the two-dimensional rotation mechanism, the first one-dimensional unfolding hinge, and the second one-dimensional unfolding hinge, a long focal length antenna layout of up to twice the satellite height can be achieved.

[0029] (2) Under the premise of high storage ratio, the present invention realizes large-angle rotation and unfolding. By adjusting the rotation angle of the two-dimensional rotation mechanism, the first one-dimensional unfolding hinge and the second one-dimensional unfolding hinge, the antenna focal length can be changed, thereby realizing the requirement of variable focal length of flexible load multi-beam antenna.

[0030] (3) The back-frame-less reflector proposed in this invention can greatly reduce the weight of the reflector, reducing the weight by about 40% compared to the back-frame reflector. The central connection method realizes the uniform deformation of the reflector in high and low temperature environments, avoiding the constraint of the back frame on the reflector surface of the back-frame reflector, thereby ensuring that the pointing angle of the antenna beam formed by the reflector does not change, thus achieving high thermal stability.

[0031] (4) The two-dimensional rotation mechanism of the present invention is arranged near the vertex of the reflecting surface, closer to the center of the reflecting surface.

[0032] Used for on-orbit pointing adjustment, this has the advantage of improving the sensitivity of reflector displacement adjustment, enabling high-precision adjustment of reflector with minute displacements;

[0033] (5) This invention has a simple structure, good adaptability, and a simple deployment process. On-orbit deployment can be achieved simply by rotating the pitch axis of a two-dimensional rotation mechanism and a one-dimensional deployment hinge. The trajectory is simple, the reliability is high, and the difficulty of ground testing and verification is low. These features are particularly important in the aerospace field, where stability and reliability are the most important requirements. Therefore, it is not necessarily better for the structure to be more complex or the function to be more advanced. Rather, achieving the best performance with the simplest and most reliable structure is the preferred requirement in the aerospace field. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of the folded state according to the present invention;

[0035] Figure 2 This is a schematic diagram of an intermediate unfolded state according to the present invention;

[0036] Figure 3 This is a schematic diagram of the second intermediate state of the present invention;

[0037] Figure 4 This is a schematic diagram of the three intermediate states of the present invention.

[0038] Figure 5 This is a schematic diagram of the unfolded position according to the present invention;

[0039] Figure 6 This is a schematic diagram of the reflective surface structure;

[0040] Figure 7 This is a schematic diagram showing the dimensions in the unfolded state;

[0041] Figure 8This is a schematic diagram showing the trajectory circles corresponding to changes in focal length and different angles in the unfolded state. Detailed Implementation

[0042] like Figure 1 As shown, the present invention proposes a lightweight, thermally stable, and focal-adjustable solid surface reflector, comprising: a reflective surface 1, an unfolding arm 2, a two-dimensional rotation mechanism 3, a first folding unfolding arm 4, a first one-dimensional unfolding hinge 5, a second folding unfolding arm 6, a second one-dimensional unfolding hinge 7, and a satellite platform 9.

[0043] The reflective surface 1 is connected to the unfolding arm 2. One end of the two-dimensional rotation mechanism 3 is connected to the unfolding arm 2, and the other end is connected to the first folding unfolding arm 4. The first folding unfolding arm 4 is connected to the second folding unfolding arm 6 through the first one-dimensional unfolding hinge 5. The second folding unfolding arm 6 is installed on the satellite platform 9 through the second one-dimensional unfolding hinge 7.

[0044] The two-dimensional rotation mechanism 3 is arranged near the vertex of the reflective surface 1 and is used to adjust the on-track orientation of the reflective surface 1. The first one-dimensional unfolding hinge 5 and the second one-dimensional unfolding hinge 7 remain locked after unfolding into place and do not participate in the on-track orientation adjustment.

[0045] The reflector of the present invention also includes a locking and releasing device 8;

[0046] When folded, the reflective surface 1 is locked to the satellite platform 9 by four locking and releasing devices 8. A locking and releasing device 8 is arranged at the position of the first folding and unfolding arm 4 near the two-dimensional rotating mechanism 3 and at the position of the first one-dimensional unfolding hinge 5.

[0047] In the retracted state, the working surface of the reflective surface 1 faces away from the satellite platform 9. The unfolding arm 2, the two-dimensional rotation mechanism 3, the first folding unfolding arm 4, the first one-dimensional unfolding hinge 5, the second folding unfolding arm 6, and the second one-dimensional unfolding hinge 7 are all located below the reflective surface 1, forming an overlapping retracted layout.

[0048] like Figure 6 As shown, the reflector 1 of the focal length adjustable fixed surface reflector of the present invention adopts a back frameless design. The middle part is designed with 3 embedded parts, which are connected to 3 connection points on a part of the unfolding arm 2. This design eliminates the traditional reflector back frame design and reduces weight by about 40%.

[0049] Since there is no back basket, the center position of the reflector 1 and its connection with the unfolding arm 2 can ensure that the reflector 1 expands and contracts uniformly from the center to the surrounding area in high and low temperature environments. This avoids the rigid constraint of the back basket on the thermal deformation of the reflector, thus achieving uniform deformation. Uniform deformation minimizes the change in the shape distribution of the reflector 1, thereby ensuring that the antenna beam angle formed by the reflector 1 does not change, thus achieving high thermal stability in high and low temperature environments.

[0050] To ensure that the reflector 1 meets the mechanical conditions, namely the fundamental frequencies X≥30Hz, Y≥30Hz, and Z≥60Hz in the three directions, and the three embedded parts are on a circle, with the processing coordinate system of the reflector 1 as the reference, the optimal relationship between the projected diameter d of the circle and the projected aperture D of the reflector 1 in the XOY plane of the processing coordinate system is d=1 / 4D, so as to achieve the lightest weight of the unfolding arm 2.

[0051] Four connectors are provided on the edge of the reflective surface 1, which are connected to the body of the reflective surface 1 through embedded parts. These embedded parts are distributed on the edge of the reflective surface 1 and are located within the range of 3 / 4D to D.

[0052] The deployable arm 2 is a composite laminate tube, and the carbon fiber layup angle is designed with zero axial expansion. The layup angle is common knowledge. The reflective surface 1 is a honeycomb sandwich structure, consisting of two layers of carbon fiber skin and a honeycomb core (which can be aluminum honeycomb or carbon fiber honeycomb). The two layers of carbon fiber skin are designed with quasi-isotropic layup, and the layup angle is common knowledge. One layup example is provided [0°, ±45°, 90°, 90°, ±45°, 0°].

[0053] In this invention, the two-dimensional rotation mechanism 3 is arranged near the vertex of the reflective surface 1 to adjust the on-track orientation of the reflective surface 1. The first one-dimensional unfolding hinge 5 and the second one-dimensional unfolding hinge 7 remain locked after unfolding and do not participate in the on-track orientation adjustment. The advantage of this is that the two-dimensional rotation mechanism 3 is closer to the center of the reflective surface 1, and the displacement adjustment sensitivity of the reflective surface 1 is high.

[0054] For example, such as Figure 7 As shown, the minimum rotation angle of the pitch axis of the two-dimensional rotation mechanism 3 is θ, and the displacement from the center of the two-dimensional rotation mechanism 3 to the center of the reflective surface is L1. Similarly, if the first one-dimensional unfolding hinge 5 is used for pointing adjustment, the minimum rotation angle of the first one-dimensional unfolding hinge 5 is θ degrees, and the displacement from the center of the first one-dimensional unfolding hinge 5 to the center of the reflective surface is L2. Since L2>L1, then L2×θ>L1×θ. Under the same minimum rotation angle, the layout of the present invention can provide higher accuracy of reflective surface displacement adjustment.

[0055] In this invention, after the reflective surface 1 is unfolded into position and the orientation is adjusted, it is locked onto the first folding unfolding arm 4 and the second folding unfolding arm 6 by the locking function of the first one-dimensional unfolding hinge 5 and the second one-dimensional unfolding hinge 7 and the power-off holding torque of the two-dimensional rotation mechanism 3, so as to ensure the structural rigidity and stable orientation of the reflective surface 1.

[0056] In this invention, after the reflector 1 is deployed, it is located outside the envelope of the satellite body 9. The focal length is adjusted via a first one-dimensional deployment hinge 5, a second one-dimensional deployment hinge 7, and a two-dimensional rotation mechanism 3. Working in different positions, it allows for forward and backward displacement adjustment along the line connecting the center and focal point of the reflector 1, with an adjustment range t of not less than 300 mm. This function is achieved by adjusting the pitch axis angle α1→α2 of the two-dimensional rotation mechanism 3, the angle β1→β2 of the first one-dimensional deployment hinge 5, and the angle γ1→γ2 of the second one-dimensional deployment hinge 7. The rotation angles of each part can be easily calculated using the pitch axis trajectory circle of the two-dimensional rotation mechanism 3 and the trajectory circle of the second one-dimensional deployment hinge 7. Figure 8 As shown.

[0057] Working principle:

[0058] like Figure 2 , 3 Figures 4 and 5 show schematic diagrams of the antenna deployment process. Figure 5 This is a schematic diagram of the antenna in its fully deployed position. After the antenna is unlocked, the reflector 1 unfolds under the combined drive of the two-dimensional rotation mechanism 3, the first one-dimensional unfolding hinge 5, and the second one-dimensional unfolding hinge 7. The unfolding strategy can be either a coordinated unfolding or an independent, step-by-step unfolding. The rotation angles of each rotating part must be carefully calculated to avoid physical interference between the reflector 1 and the satellite platform 9 during unfolding. The power source for the first one-dimensional unfolding hinge 5 and the second one-dimensional unfolding hinge 7 can be a motor or an energy storage element such as a spring. The two-dimensional rotation mechanism 3 is driven by a motor to ensure that they unfold at a certain speed.

[0059] The independent, step-by-step unfolding mechanism consists of three components: the two-dimensional rotation mechanism 3, the first one-dimensional unfolding hinge 5, and the second one-dimensional unfolding hinge 7. Only one component unfolds at a time, and the unfolding steps are as follows:

[0060] In the first step, the reflector 1, the unfolding arm 2, the two-dimensional rotation mechanism 3, the first folding unfolding arm 4, the first one-dimensional unfolding hinge 5, and the second folding unfolding arm 6 together unfold counterclockwise to a certain angle under the drive of the second one-dimensional unfolding hinge 7. This angle ensures that the reflector 1 and the satellite platform 9 do not physically interfere with each other.

[0061] In the second step, the reflector 1 and the unfolding arm 2 unfold clockwise to a certain angle under the drive of the two-dimensional rotation mechanism 3. This angle is the final angle of the pitch axis of the two-dimensional rotation mechanism 3.

[0062] The third step involves the reflective surface 1, the unfolding arm 2, the two-dimensional rotation mechanism 3, and the first folding unfolding arm 4 unfolding clockwise to a certain angle under the drive of the first one-dimensional unfolding hinge 5. This angle is the final angle of the first one-dimensional unfolding hinge 5.

[0063] In the fourth step, the reflective surface 1, the unfolding arm 2, the two-dimensional rotation mechanism 3, the first folding unfolding arm 4, the first one-dimensional unfolding hinge 5, and the second folding unfolding arm 6 together continue to unfold counterclockwise to the final angle under the drive of the second one-dimensional unfolding hinge 7.

[0064] In the fifth step, the reflective surface 1 and the unfolding arm 2 are together finely adjusted in azimuth under the drive of the two-dimensional rotation mechanism 3, thus unfolding into place.

[0065] The linkage deployment means that the three components, namely the two-dimensional rotation mechanism 3, the first one-dimensional deployment hinge 5, and the second one-dimensional deployment hinge 7, move simultaneously. The principle is similar to the step-by-step deployment process. The deployment angle and speed of each part must be calculated to avoid physical interference during the deployment process.

[0066] The following are embodiments of the present invention.

[0067] The reflective surface 1 adopts a backless design, with three embedded parts in the middle section, which connect to three connection points on a part of the folding and unfolding arm 3. The three embedded parts are on a circle. Taking the machining coordinate system of the reflective surface 1 as the reference, the optimal relationship between the projected diameter d of the circle and the projected aperture D of the reflective surface 1 in the XOY plane of the machining coordinate system should be d=1 / 4D, so as to achieve the lightest weight and best thermal stability of the folding and unfolding arm 3. The folding and unfolding arm 3 is a composite material laminated tube, and the carbon fiber layup angle is designed with zero axial expansion. The reflective surface 1 is a honeycomb sandwich structure, consisting of upper and lower carbon fiber skins and a honeycomb core. It can be an aluminum honeycomb or a carbon fiber honeycomb. The upper and lower carbon fiber skins are designed with quasi-isotropic layup.

[0068] When the projected aperture D of reflector 1 is 2100mm and the optimal value of d is 525mm, the reflector skin layer ply is [0°, ±45°, 90°, 90°, ±45°, 0°], the aluminum honeycomb height is 15mm, and the weight of reflector 1 and part of the folding and unfolding arm 2 (with the two-dimensional rotation mechanism as the boundary) is 13kg, while the weight of a traditional basket-type reflector of the same aperture is 22kg. Under a temperature difference of 100℃, the antenna beam pointing angle formed by the surface of reflector 1 changes by ≤0.01°, compared to 0.05° for a traditional basket-type reflector of the same aperture.

[0069] This invention features a simple structure and good versatility, enabling lightweight, high thermal stability, and long focal length layout designs for large-aperture solid-surface reflectors with adjustable focal lengths. This ensures the antenna is no longer limited by the satellite's envelope, overcoming the shortcomings of traditional back-frame supported solid-surface reflectors, such as heavy weight, poor thermal stability, and fixed focal lengths limited by the satellite platform's envelope. This invention is well-suited to the development of high-throughput, flexible payload multi-beam antennas for future high-performance satellites, and has broad applicability and application value.

[0070] The parts of this invention not described in detail are common knowledge to those skilled in the art.

Claims

1. A lightweight, thermally stable, and focal-adjustable solid-surface reflector, characterized in that... include: The reflective surface (1), the unfolding arm (2), the two-dimensional rotation mechanism (3), the first folding unfolding arm (4), the first one-dimensional unfolding hinge (5), the second folding unfolding arm (6), the second one-dimensional unfolding hinge (7), and the satellite platform (9); The reflective surface (1) is connected to the unfolding arm (2), one end of the two-dimensional rotation mechanism (3) is connected to the unfolding arm (2), and the other end is connected to the first folding unfolding arm (4). The first folding unfolding arm (4) is connected to the second folding unfolding arm (6) through the first one-dimensional unfolding hinge (5). The second folding unfolding arm (6) is installed on the satellite platform (9) through the second one-dimensional unfolding hinge (7). The two-dimensional rotation mechanism (3) is arranged near the vertex of the reflective surface (1) to adjust the on-track orientation of the reflective surface (1), while the first one-dimensional unfolding hinge (5) and the second one-dimensional unfolding hinge (7) remain locked after unfolding and do not participate in the on-track orientation adjustment. The reflective surface (1) adopts a backless design, and the central part is designed with three central embedded parts, which are connected to three connection points on the unfolding arm (2) to ensure that the reflective surface (1) expands and contracts evenly from the center to the surrounding area in high and low temperature environments. The three central embedded parts are on a circle. Taking the machining coordinate system of the reflective surface (1) as the reference, the relationship between the projected diameter d of the circle and the projected aperture D of the reflective surface (1) in the XOY plane of the machining coordinate system is d=1 / 4D, so as to achieve the lightest weight of the unfolding arm (2).

2. The lightweight, thermally stable, and focal-adjustable solid-surface reflector according to claim 1, characterized in that: It also includes a locking release device (8); When folded, the reflective surface (1) is locked to the satellite platform (9) by four locking and releasing devices (8). The first folding and unfolding arm (4) is equipped with a locking and releasing device (8) near the two-dimensional rotating mechanism (3) and near the first one-dimensional unfolding hinge (5).

3. A lightweight, thermally stable, and focal-adjustable solid-surface reflector according to claim 2, characterized in that: When in the retracted state, the working surface of the reflective surface (1) faces away from the satellite platform (9), and the unfolding arm (2), the two-dimensional rotation mechanism (3), the first folding unfolding arm (4), the first one-dimensional unfolding hinge (5), the second folding unfolding arm (6), and the second one-dimensional unfolding hinge (7) are all located below the reflective surface (1), forming an overlapping retracted layout.

4. A lightweight, thermally stable, and focal-adjustable solid-surface reflector according to claim 1, characterized in that: Four connectors are provided on the edge of the reflective surface (1), which are connected to the body of the reflective surface (1) through edge embedded parts. The edge embedded parts are distributed on the edge of the reflective surface (1) and are located in the range of 3 / 4D~D.

5. A lightweight, thermally stable, and focal-adjustable solid-surface reflector according to claim 1, characterized in that: The unfolding arm (2) is a composite material laminate tube, and the reflective surface (1) is a honeycomb sandwich structure, consisting of two layers of carbon fiber skin and a honeycomb core. The honeycomb core is an aluminum honeycomb or a carbon fiber honeycomb. The two layers of carbon fiber skin are designed according to quasi-isotropic layup, with layup angles of [0°, ±45°, 90°, 90°, ±45°, 0°].

6. A lightweight, thermally stable, and focal-adjustable solid-surface reflector according to claim 1, characterized in that: After the reflective surface (1) is unfolded and the orientation adjustment is completed, it is locked onto the first folding unfolding arm (4) and the second folding unfolding arm (6) by the locking function of the first one-dimensional unfolding hinge (5) and the second one-dimensional unfolding hinge (7) and the power-off holding torque of the two-dimensional rotation mechanism (3), so as to ensure the structural rigidity and stable orientation of the reflective surface (1).

7. A lightweight, thermally stable, and focal-adjustable solid-surface reflector according to claim 1, characterized in that: After the reflector (1) is unfolded, it is located outside the envelope of the satellite platform (9). The focal length is adjusted by the first one-dimensional unfolding hinge (5), the second one-dimensional unfolding hinge (7) and the two-dimensional rotation mechanism (3). It works in different working positions and realizes the front and rear displacement adjustment along the line connecting the center and the focal point of the reflector (1), with an adjustment range t of not less than 300mm. The focal length is adjusted by adjusting the pitch axis angle α1→α2 of the two-dimensional rotation mechanism (3), the angle β1→β2 of the first one-dimensional unfolding hinge (5) and the angle γ1→γ2 of the second one-dimensional unfolding hinge (7).

8. A lightweight, thermally stable, and focal-adjustable solid-surface reflector according to any one of claims 1-7, characterized in that: After the antenna is unlocked, the reflector (1) completes the unfolding action under the joint drive of the two-dimensional rotation mechanism (3), the first one-dimensional unfolding hinge (5), and the second one-dimensional unfolding hinge (7). The unfolding strategy is either linkage unfolding or independent step-by-step unfolding. The linkage unfolding means that the three components, namely the two-dimensional rotation mechanism (3), the first one-dimensional unfolding hinge (5), and the second one-dimensional unfolding hinge (7), move simultaneously. The three components—two-dimensional rotation mechanism (3), first one-dimensional unfolding hinge (5), and second one-dimensional unfolding hinge (7)—are unfolded in separate steps, with only one component unfolding at a time. The unfolding steps are as follows: In the first step, the reflective surface (1), the unfolding arm (2), the two-dimensional rotation mechanism (3), the first folding unfolding arm (4), the first one-dimensional unfolding hinge (5), and the second folding unfolding arm (6) unfold counterclockwise to a certain angle under the drive of the second one-dimensional unfolding hinge (7). This angle ensures that the reflective surface (1) and the satellite platform (9) do not physically interfere with each other. In the second step, the reflective surface (1) and the unfolding arm (2) unfold clockwise to a certain angle under the drive of the two-dimensional rotation mechanism (3). This angle is the final angle of the pitch axis of the two-dimensional rotation mechanism (3). In the third step, the reflective surface (1), the unfolding arm (2), the two-dimensional rotation mechanism (3), and the first folding unfolding arm (4) unfold clockwise to a certain angle under the drive of the first one-dimensional unfolding hinge (5). This angle is the final angle of the first one-dimensional unfolding hinge (5). In the fourth step, the reflective surface (1), the unfolding arm (2), the two-dimensional rotation mechanism (3), the first folding unfolding arm (4), the first one-dimensional unfolding hinge (5), and the second folding unfolding arm (6) together continue to unfold counterclockwise to the final angle under the drive of the second one-dimensional unfolding hinge (7). In the fifth step, the reflective surface (1) and the unfolding arm (2) are together finely adjusted in azimuth under the drive of the two-dimensional rotation mechanism (3) to unfold into place.

9. A lightweight, thermally stable, and focal-adjustable solid-surface reflector according to claim 8, characterized in that: The power source for the first one-dimensional unfolding hinge (5) and the second one-dimensional unfolding hinge (7) is a motor or a spring, and the two-dimensional rotating mechanism (3) is driven by a motor.

Images