Variable-configuration multi-load agile maneuvering satellite configuration and echo signal acquisition method

Abstract

The application discloses a variable-structure double-side visual agile satellite configuration and echo signal collection method, relates to the field of novel satellite system design, and solves the problem of limited satellite coverage range caused by the limitation of single instantaneous field of view. The satellite configuration comprises a satellite main structure, lifting arms, an imaging reconnaissance load, a three-axis joint and two-dimensional phased array feed antennas. The satellite main structure is internally provided with an equipment cabin for controlling the imaging reconnaissance load to detect. The satellite main structure is provided with lifting arms on the left and right sides, the imaging reconnaissance load is fixed on the lifting arms on the left and right sides of the satellite main structure, and the satellite main structure is connected with the lifting arms through the three-axis joint. The satellite main structure is also provided with two two-dimensional phased array feed antennas on the left and right sides, and the two-dimensional phased array feed antennas are rotationally connected with the top of the satellite main structure. The application is applied to the field of satellite detection.

Description

Technical Field

[0001] This invention relates to the field of novel satellite system design, and more particularly to a variable configuration multi-payload agile maneuvering satellite configuration. Background Technology

[0002] Currently, most imaging reconnaissance satellites adopt a configuration where the payload is fixed to a rigid satellite platform. In this configuration, the satellite has only a single instantaneous field of view, and because the payload is fixed to the satellite platform, the satellite's field of view is limited by the payload's field of view. This means that each satellite observation can only cover a fixed area, and it cannot simultaneously observe multiple areas, thus limiting the coverage area. Due to the limitation of the instantaneous field of view, the satellite's coverage area is limited. To increase the coverage area, the satellite can only adjust its field of view through whole-satellite attitude maneuvers. However, the satellite's whole-satellite attitude maneuvering capability is limited by the satellite's large inertia and the capabilities of its actuators, resulting in limited maneuvering range and speed. To meet the increasing demand for single-orbit, multi-area imaging reconnaissance capabilities, satellites can only increase the coverage area through whole-satellite attitude maneuvers, but the maneuvering capability is also limited by the satellite's large inertia and the capabilities of its actuators. Furthermore, the relatively fixed satellite configuration restricts the expansion of satellite functions. Summary of the Invention

[0003] This invention addresses the problem of limited coverage caused by existing satellites being confined to a single instantaneous field of view. It proposes a variable-configuration, multi-payload, agile maneuvering satellite configuration, the scheme of which includes:

[0004] A variable configuration multi-payload agile maneuvering satellite configuration, the satellite configuration comprising:

[0005] Satellite main structure, lifting arm, imaging reconnaissance payload, and three-axis joint;

[0006] The satellite's main structure contains an equipment bay for controlling the imaging reconnaissance payload to perform detection.

[0007] The satellite's main structure is equipped with lifting arms on both the left and right sides. The imaging reconnaissance payload is fixed on the lifting arms on both sides of the satellite's main structure. The satellite's main structure is connected to the lifting arms via a three-axis joint.

[0008] Furthermore, a preferred embodiment is provided, wherein the imaging reconnaissance payload includes: an antenna reflector, a thin-film solar array, and a two-dimensional phased array feed antenna; the plurality of trusses are arranged in a barrel shape, the thin-film solar array is fixed on the surface of the trusses, and the antenna reflector is embedded inside the barrel shape formed by the trusses; the two-dimensional phased array feed antenna is located on both sides of the main structure of the satellite, and the two-dimensional phased array feed antenna is rotatably connected to the top of the main structure of the satellite.

[0009] Furthermore, a preferred embodiment is provided in which the height of the truss is 5m.

[0010] Furthermore, a preferred embodiment is provided in which the main structure of the satellite further includes a telescopic truss and a truss extension mechanism, the telescopic truss and the truss extension mechanism being fixedly connected.

[0011] Furthermore, a preferred embodiment is provided in which the telescopic truss has a telescopic length of 0 to 40 m.

[0012] Based on the same inventive concept, this invention also provides an echo signal acquisition method based on a variable configuration multi-payload agile maneuvering satellite configuration, the method comprising:

[0013] The satellite's main structure controls the angle and direction of the lifting arm through a three-axis joint, directing the imaging reconnaissance payload to the target area;

[0014] The imaging reconnaissance payload will collect echo signals from the target area and transmit them back to the equipment compartment inside the satellite's main structure. The processor in the equipment compartment will then process the signals to obtain image information.

[0015] Furthermore, a preferred embodiment is also provided, wherein the method further includes acquiring side-view images via left and right vertical rails, the side-view images acquired via left and right vertical rails including:

[0016] When the left and right vertical rails are viewed from the side, the line connecting the imaging reconnaissance payloads is perpendicular to the direction of flight speed, and the imaging reconnaissance payloads of the satellite's main structure simultaneously image the areas on the left and right sides of the nadir point.

[0017] Furthermore, a preferred embodiment is also provided, wherein the method further includes acquiring images from the same side of the left and right vertical rails, the images acquired from the same side of the left and right vertical rails including:

[0018] When the left and right vertical rails are viewed from the same side, the line connecting the imaging reconnaissance payloads is perpendicular to the direction of flight speed, and the imaging reconnaissance payloads of the satellite's main structure simultaneously image the area on the same side of the nadir point.

[0019] Furthermore, a preferred embodiment is also provided, wherein the method further includes detection of moving targets on the same side along the front and rear tracks, the detection of moving targets on the same side along the front and rear tracks comprising:

[0020] When viewing from the same side along the front and rear orbits, the line connecting the imaging reconnaissance payloads is parallel to the direction of flight velocity, and the imaging reconnaissance payloads of the satellite's main structure simultaneously image the area on the same side of the nadir point.

[0021] Furthermore, a preferred embodiment is also provided, wherein the method further includes side-looking detection of uplink and downlink signals by upper and lower vertical rails, the side-looking detection of uplink and downlink signals by upper and lower vertical rails including:

[0022] When the upper and lower vertical rails are viewed from opposite sides, the line connecting the imaging reconnaissance payloads is perpendicular to the direction of flight speed. One side of the imaging reconnaissance payload rotates 180° around the truss axis to point towards the high-orbit area, while the other side of the imaging reconnaissance payload remains on the ground.

[0023] The advantages of this invention are:

[0024] This invention solves the problem that existing satellites are limited by a single instantaneous field of view, resulting in limited coverage.

[0025] This invention describes a variable-configuration, multi-payload, agile maneuvering satellite configuration. By adding lifting arms to both sides of the satellite's main structure and fixing the imaging reconnaissance payload to these arms, it enables imaging of multiple regions within the same orbital period, increasing the satellite's coverage and enhancing its single-orbit, multi-region imaging reconnaissance capabilities. A three-axis joint connection between the satellite's main structure and the lifting arms allows for attitude adjustment and field-of-view switching of the imaging reconnaissance payload, enabling the satellite to quickly and accurately adjust its field of view to adapt to the needs of different target areas. Compared to traditional satellite configurations, this flexible field-of-view adjustment capability improves the efficiency and accuracy of imaging reconnaissance. Two two-dimensional phased array feed antennas are also located on both sides of the satellite's main structure. These antennas can be used to point at different ground targets, further increasing the satellite's target coverage and observation capabilities. By adjusting the pointing angle and transmission power of the feed antennas, reconnaissance needs for different target areas can be met.

[0026] This invention discloses an echo signal acquisition method based on a variable-configuration, multi-payload, agile maneuvering satellite configuration. By using a three-axis joint to control the angle and direction of the lifting arm, the satellite can precisely orient its imaging reconnaissance payload towards the target area. This precise orientation improves imaging quality and target monitoring accuracy, giving the satellite enhanced reconnaissance and observation capabilities. The satellite's main structure transmits the signals acquired by the imaging reconnaissance payload back to the satellite through the equipment bay. This internal transmission method improves transmission efficiency while protecting data security. Compared to transmitting data to the ground for processing, internal transmission saves transmission time and bandwidth and supports real-time data requirements. Two two-dimensional phased array feed antennas are also located on both sides of the satellite's main structure. These antennas can be used to point at different ground targets, thereby further increasing the satellite's target coverage and observation capabilities. By adjusting the pointing angle and transmission power of the feed antennas, reconnaissance needs for targets in different areas can be met.

[0027] This invention is applied to the field of satellite exploration. Attached Figure Description

[0028] Figure 1This is a schematic diagram of a variable configuration multi-payload agile maneuvering satellite configuration as described in Embodiment 1, wherein 1 is the main structure of the satellite, 2 is the antenna reflector, 3 is the lifting arm, 4 is the two-dimensional phased array feed antenna, 5 is the equipment bay, 6 is the three-axis joint, 7 is the thin-film solar array, 8 is the telescopic truss, and 9 is the truss extension mechanism.

[0029] Figure 2 This is a schematic diagram of the variable configuration dual-side-looking microwave imaging reconnaissance satellite configuration as described in Embodiment 2.

[0030] Figure 3 This is a side view diagram of the left and right vertical rails as described in Embodiment Seven;

[0031] Figure 4 This is a schematic diagram of the left and right vertical rails viewed from the same side as described in Embodiment 8;

[0032] Figure 5 This is a schematic diagram of the front and rear rails viewed from the same side as described in Embodiment Nine;

[0033] Figure 6 This is a side view schematic diagram of the upper and lower vertical rails as described in Embodiment 10. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0035] Implementation Method 1, see [link] Figure 1 This embodiment describes a variable configuration multi-payload agile maneuvering satellite configuration, which includes:

[0036] Satellite main structure 1, lifting arm 3, imaging reconnaissance payload and three-axis joint 6;

[0037] The satellite's main structure 1 contains an equipment compartment 5, which is used to control the imaging reconnaissance payload for detection.

[0038] The satellite main structure 1 is provided with lifting arms 3 on the left and right sides. The imaging reconnaissance payload is fixed on the lifting arms 3 on both sides of the satellite main structure 1. The satellite main structure 1 is connected to the lifting arms 3 through a three-axis joint 6.

[0039] In this embodiment, the satellite main structure 1 is connected to the lifting arm 3 via a three-axis joint 6. This connection method provides high structural rigidity and stability. This is crucial for imaging reconnaissance satellites, as they need to maintain a stable attitude during operation to obtain clear images. The three-axis joint 6 connection effectively constrains the movement between the satellite main structure 1 and the lifting arm 3, ensuring the stability and accuracy of the imaging reconnaissance payload.

[0040] Most modern satellites have a central rigid body layout. This implementation omits the central rigid body and adds lifting arms 3 to the left and right sides of the satellite's main structure 1, fixing the imaging reconnaissance payload to the lifting arms 3. This enables imaging of multiple areas within the same orbital period. This configuration increases the satellite's coverage area and enhances its single-orbit, multi-area imaging reconnaissance capability. A three-axis joint 6 connects the satellite's main structure 1 and the lifting arms 3, allowing for attitude adjustment and field-of-view switching of the imaging reconnaissance payload. This allows the satellite to quickly and accurately adjust its field of view to adapt to the needs of different target areas. Compared to traditional satellite layouts, this flexible field-of-view adjustment capability improves the efficiency and accuracy of imaging reconnaissance. Two two-dimensional phased array feed antennas 4 are also located on both sides of the satellite's main structure 1. These antennas can be used to point at different ground targets, further increasing the satellite's target coverage and observation capabilities. By adjusting the pointing angle and transmission power of the feed antennas, imaging reconnaissance of targets in different areas can be achieved.

[0041] The satellite configuration described in this embodiment enhances the imaging capabilities, flexibility, and coverage of imaging reconnaissance satellites. Through multi-region imaging, flexible adjustment of the field of view, and increased comprehensive target coverage, this scheme aims to overcome the limitations of traditional layout methods, meet the needs of more complex missions, and improve the application value and performance of the satellite.

[0042] Implementation Method 2: This implementation method further defines the variable configuration multi-payload agile maneuvering satellite configuration described in Implementation Method 1. The imaging reconnaissance payload includes: an antenna reflector 2, a thin-film solar array 7, and a two-dimensional phased array feed antenna 4. Several trusses are arranged in a barrel shape, the thin-film solar array 7 is fixed on the surface of the trusses, and the antenna reflector 2 is embedded inside the barrel shape formed by the trusses. The two-dimensional phased array feed antenna 4 is located on both sides of the satellite main structure 1, and the two-dimensional phased array feed antenna 4 is rotatably connected to the top of the satellite main structure 1.

[0043] This embodiment employs a truss-enclosed barrel-shaped structural design, which effectively reduces the weight and volume of the imaging reconnaissance payload. The truss structure itself possesses excellent strength and rigidity, while providing a stable support frame, ensuring the payload remains stable and safe during satellite operation. The use of the thin-film solar array 7 further reduces weight and space occupation, improving the satellite's load capacity and the payload's imaging capabilities. While the thin-film solar array 7 is fixed to the truss surface, the antenna reflector 2 is embedded within the barrel-shaped structure formed by the truss. This integrated design achieves multifunctionality. The antenna reflector 2 reflects signals transmitted and received by the feed cabin, while the thin-film solar array 7 provides energy to the satellite, supporting the normal operation of the payload and satellite system. By integrating these two functions into the imaging reconnaissance payload, the system resource utilization efficiency can be maximized. By installing a two-dimensional phased array feed antenna 4 on top of the satellite's main structure 1 and rotating it to the top of the satellite's main structure 1, the angle of the feed antenna can be adjusted. This allows for changing the satellite's field of view, flexibly adapting to different imaging needs. Adjusting the angle enables in-depth observation and detail capture of specific areas. Therefore, this connection scheme provides flexibility in adjusting the imaging angle.

[0044] This implementation reduces the weight and size of the imaging reconnaissance payload to ensure overall satellite weight control and improved effective carrying capacity. A lighter payload provides the satellite with more allocable payload space, allowing it to carry more critical equipment and functions to meet diverse mission requirements. By integrating the antenna reflector 2 and the thin-film solar array 7 into the imaging reconnaissance payload, this design aims for comprehensive resource utilization. The antenna reflector 2 not only provides communication and data transmission functions but also serves as an imaging reconnaissance unit. The thin-film solar array 7 provides energy support for the satellite, enabling it to operate and perform missions independently. This comprehensive resource utilization design contributes to improving the satellite's autonomy and sustainability.

[0045] Implementation Method 3: This implementation method further defines the variable configuration multi-payload agile maneuvering satellite configuration described in Implementation Method 2, wherein the truss height is 5m.

[0046] Implementation Method 4: This implementation method further defines the variable configuration multi-payload agile maneuvering satellite configuration described in Implementation Method 1. The main satellite structure 1 further includes a telescopic truss 8 and a truss extension mechanism, which are fixedly connected.

[0047] This embodiment is described in conjunction with Embodiment 2. The main satellite structure 1 bears the mechanical load of the satellite during the launch phase and provides an installation interface for the payload and other individual equipment. A telescopic pod-shaped truss and a corresponding extension mechanism are installed at the center of the main structure. After the satellite enters orbit, the extension mechanism drives the truss to unfold and supports the adjustment of the truss length during on-orbit operation.

[0048] Equipment compartment 5 houses the individual equipment necessary for the payload to operate, including attitude control, power supply, thermal control, measurement and control data transmission, and data processing.

[0049] The lifting arm 3 connects the satellite main structure 1 and the payload antenna. After entering orbit, the lifting arm 3 unfolds, allowing the feed antenna and reflector to reach the designated position. A three-degree-of-freedom joint is installed at the base of the lifting arm 3 and a high-torque motor is configured to drive the payload to complete the transformation in any direction.

[0050] The two-dimensional phased array feed antenna can transmit and receive microwave signals, which are then reflected by the antenna reflector 2 to perform tasks such as imaging and reconnaissance. Thin-film solar cells are attached to the antenna truss of the reflector, realizing an integrated antenna power supply design, which can further reduce the overall satellite weight and improve the overall satellite deployment-reception ratio.

[0051] In this embodiment, the telescopic truss and truss extension mechanism allow the satellite's main structure 1 to be in a compact state before launch, thereby reducing the satellite's volume and space requirements within the fairing. This design allows the satellite's deployment process to be delayed until after it reaches orbit, improving the satellite's adaptability and deployment flexibility. The telescopic truss provides excellent structural support; the satellite's main structure 1 decreases in height as the deployment length increases. The truss's telescopic nature is designed to meet the requirements for dual-load antenna distance (i.e., baseline length) for interferometric imaging, moving target detection, and other applications. This design improves the satellite's stability and structural vibration resistance, reducing potential risks caused by vibration and gyroscopic effects. Through fixed connections, the telescopic truss and extension mechanism can be stably fixed in predetermined positions, ensuring the satellite's structural integrity and reliability under various operating conditions.

[0052] In this embodiment, the size and weight of the satellite's main structure 1 can be minimized by employing a telescopic truss and truss extension mechanism. This helps to improve the satellite's payload capacity, enabling it to carry more scientific instruments, communication equipment, and imaging reconnaissance payloads, and providing enhanced data collection and transmission capabilities. The satellite's main structure 1 can remain compact during launch and then deploy after entering orbit. This design provides greater flexibility and adaptability, allowing the satellite to be compatible with different launch platforms and payload adapters. Through fixed connections, the telescopic truss and truss extension mechanism ensure the stability and reliability of the satellite's main structure 1. This connection method provides robust structural support, ensuring that the satellite's main structure 1 remains intact and stable during launch and in orbit to withstand various environmental and workload conditions.

[0053] This implementation integrates telescopic trusses and truss extension mechanisms to optimize the satellite's weight and volume, improve its launch adaptability, and provide reliable structural support to ensure the satellite remains stable and safe during all phases of deployment and operation.

[0054] Implementation Method 5: This implementation method further defines the variable configuration multi-load agile maneuvering satellite configuration described in Implementation Method 1, wherein the telescopic truss has a telescopic length of 0 to 40 m.

[0055] Implementation Method Six: An echo signal acquisition method based on a variable-configuration, two-sided-looking, agile maneuvering satellite configuration, as described in this implementation method, includes:

[0056] The satellite main structure 1 controls the angle and direction of the lifting arm 3 through the three-axis joint 6, directing the imaging reconnaissance payload to the target area;

[0057] The imaging reconnaissance payload will transmit the echo signals from the target area back to the equipment compartment 5 inside the main structure 1 of the satellite. The processor in the equipment compartment will then process the signals to obtain image information.

[0058] This embodiment uses a three-axis joint 6 to control the angle and direction of the lifting arm 3, allowing the satellite to precisely orient the imaging reconnaissance payload towards the target area. This precise orientation improves imaging quality and target monitoring accuracy, giving the satellite enhanced reconnaissance and observation capabilities. The satellite's main structure 1 transmits the echo signal data acquired by the imaging reconnaissance payload back to the satellite via the equipment compartment 5. This internal transmission method improves transmission efficiency while protecting data security. Compared to transmitting data to the ground for processing, internal transmission saves transmission time and bandwidth, and supports real-time data requirements.

[0059] This embodiment enhances the satellite's reconnaissance and observation capabilities by controlling the lifting arm 3 and the directional imaging reconnaissance payload using a three-axis joint 6. This enhanced capability allows for the monitoring and collection of various information about the Earth's surface, including geological changes, resource utilization, and environmental monitoring, supporting applications in scientific research, resource management, and environmental protection. By transmitting the echo signals acquired by the imaging reconnaissance payload to the equipment compartment 5 inside the satellite's main structure 1, efficient data transmission and processing can be achieved. This method reduces data transmission time and bandwidth requirements, increases data processing speed, and supports real-time monitoring and application needs.

[0060] Implementation Method Seven: Participation Figure 3This embodiment further defines the echo signal acquisition method based on a variable configuration multi-payload agile maneuvering satellite configuration described in Embodiment Six. The method further includes side-view image acquisition via left and right vertical rails, wherein the side-view image acquisition via left and right vertical rails includes:

[0061] When the left and right vertical rails are viewed from the side, the imaging reconnaissance payload line is perpendicular to the flight speed direction, and the imaging reconnaissance payload of the satellite main structure 1 simultaneously images the left and right sides of the nadir point.

[0062] This implementation acquires images via side-looking observation using left and right vertical rails, allowing the imaging reconnaissance payload to simultaneously image the areas on both the left and right sides below the satellite. This dual-side-looking acquisition method expands the reconnaissance range and provides a wider range of ground target information. Compared to imaging only on one side (left or right) of the nadir point, side-looking observation via left and right vertical rails can obtain a more comprehensive picture, including the side of the target, the surrounding environment, etc., increasing the accuracy of target identification and analysis.

[0063] In this embodiment, the side-view image acquisition by the left and right vertical rails enables the imaging reconnaissance payload to simultaneously obtain data from multiple target areas, which helps to expand the coverage of the satellite within a single orbital period.

[0064] Implementation Method Eight: This implementation method further defines the echo signal acquisition method based on a variable configuration multi-payload agile maneuvering satellite configuration described in Implementation Method Six. The method further includes side-view acquisition images from both left and right vertical rails, which include:

[0065] When the left and right vertical rails are viewed from the same side, the line connecting the imaging reconnaissance payloads is perpendicular to the direction of flight speed, and the imaging reconnaissance payloads of the satellite's main structure simultaneously image the area on the same side of the nadir point.

[0066] This embodiment uses the left and right vertical rails to view from the same side, forming an interference baseline between the two loads in the direction perpendicular to the flight speed, thereby achieving interferometric measurement and obtaining information such as regional ground elevation changes.

[0067] Implementation Method Nine: This implementation method further defines the echo signal acquisition method based on a variable configuration multi-payload agile maneuvering satellite configuration described in Implementation Method Six. The method further includes forward and backward track-side same-side look-moving target detection, which includes:

[0068] When viewing from the same side along the front and rear orbits, the imaging reconnaissance payloads are parallel to the direction of flight velocity, and the imaging reconnaissance payloads of the satellite main structure 1 simultaneously image the area on the same side of the nadir point.

[0069] This implementation method enables the detection and monitoring of dynamic targets on the ground and in the air by looking at the same side along the front and rear tracks.

[0070] Implementation Method 10: This implementation method further defines the image acquisition method based on a variable configuration multi-payload agile maneuvering satellite configuration described in Implementation Method 6. The method further includes side-looking detection of uplink and downlink signals from the upper and lower vertical orbits. The detection of uplink and downlink signals includes:

[0071] When the upper and lower vertical rails are viewed from opposite sides, the line connecting the imaging reconnaissance payloads is perpendicular to the direction of flight speed. One side of the imaging reconnaissance payload rotates 180° around the truss axis to point towards the high-orbit area, while the other side of the imaging reconnaissance payload remains on the ground.

[0072] This implementation, through side-looking observation via vertical rails, can detect signals in both the downlink to Earth and the uplink to high-orbit satellites, and can also simultaneously transmit jamming signals to interfere with each other's communications. One side of the imaging reconnaissance payload rotates 180° around the truss axis to point towards the high-orbit region, while the other side remains ground-oriented. This enhances the satellite's ability to simultaneously detect uplink and downlink communications.

[0073] Implementation Method Eleven: This implementation method provides a specific embodiment of the variable configuration multi-payload agile maneuvering satellite configuration described in Implementation Method One, and also serves to explain Implementation Methods Two to Five. Specifically:

[0074] In this embodiment, the dual-side-looking microwave imaging reconnaissance payload is symmetrically arranged on the entire satellite. The two payloads have the same mass and inertia characteristics. Therefore, when the payloads rotate along any rotation axis at equal and opposite angular velocities, the entire satellite can maintain zero momentum, thereby breaking free from the limitation of the traditional flywheel on the angular momentum envelope of the entire satellite and improving the satellite's variable structure maneuverability.

[0075] Let antenna reflector 2 be a homogeneous disk with a diameter of 22m and a mass of 200kg. The distance between the axis of rotation and the principal axis of inertia in the plane of the disk is 20m. Then the moment of inertia of the reflector is...

[0076]

[0077] When the motor's maximum output torque is 500 Nm, the maximum angular acceleration β of the reflecting surface is... m =T m / J=0.333° / s 2 Under the condition of maintaining maximum angular acceleration and deceleration during attitude maneuvers, the duration t of the attitude maneuver and the angular displacement θ satisfy the following condition:

[0078]

[0079] Therefore, the shortest maneuver time is

[0080]

[0081] The maximum angular velocity during the maneuver is

[0082]

[0083] The corresponding maximum angular momentum on one side is

[0084]

[0085] From equations (3), (4), and (5), the maneuver time at a maneuver angle of 45° is 23.25s, the maximum angular velocity is 3.87° / s, and the maximum angular momentum is 5813Nms; the maneuver time at a maneuver angle of 90° is 32.88s, the maximum angular velocity is 5.47° / s, and the maximum angular momentum is 8221Nms. It has maneuverability comparable to or better than mainstream agile maneuvering satellites, enabling phased array radar to scan ground targets.

[0086] In practice, the payload carried by the satellite is not limited to bilateral microwave imaging reconnaissance payloads. In addition, the payloads carrying communication, optical remote sensing and other payloads, and the number of payloads is greater than 2, should also be included in the scope of protection of this invention.

[0087] The technical solutions provided by the present invention have been described in further detail above with reference to the accompanying drawings in order to highlight their advantages and benefits, and are not intended to limit the present invention. Any modifications, combinations, improvements and equivalent substitutions of the present invention based on the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for echo signal acquisition based on a variable-configuration multi- payload agile maneuvering satellite configuration, characterized in that, The satellite configuration comprises: a satellite main structure, a lifting arm, an imaging reconnaissance load and a three-axis joint; the satellite main structure is internally provided with an equipment cabin for controlling the imaging reconnaissance load to detect; the satellite main structure is provided with the lifting arm on the left and right sides, the imaging reconnaissance load is fixed on the lifting arm on the left and right sides of the satellite main structure, and the satellite main structure is connected with the lifting arm through the three-axis joint; the imaging reconnaissance load comprises: an antenna reflector, a thin film solar wing and a two-dimensional phased array feed antenna; a plurality of trusses form a barrel shape, the truss surface is fixed with the thin film solar wing, and the antenna reflector is embedded in the barrel shape formed by the truss; the two-dimensional phased array feed antenna is arranged on the left and right sides of the satellite main structure, and the two-dimensional phased array feed antenna is rotationally connected with the top of the satellite main structure; the height of the truss is 5 m; the satellite main structure further comprises a telescopic truss and a truss extension mechanism, and the telescopic truss and the truss extension mechanism are fixedly connected; the telescopic length of the telescopic truss is 0-40 m; the telescopic truss is used for changing the distance of the imaging reconnaissance load; the method comprises: the satellite main structure controls the angle and direction of the lifting arm through the three-axis joint, and directs the imaging reconnaissance load to a target area; the imaging reconnaissance load transmits the echo signal collected from the target area back to the equipment cabin in the satellite main structure, and a processor in the equipment cabin acquires image information.

2. The echo signal acquisition method based on the variable-configuration multi-load agile maneuvering satellite configuration according to claim 1, further comprising left-right vertical orbit opposite side view image acquisition, wherein the left-right vertical orbit opposite side view image acquisition comprises: when the left-right vertical orbit opposite side view condition occurs, the imaging reconnaissance load line is perpendicular to the flight speed direction, and the imaging reconnaissance load of the satellite main structure simultaneously images the left and right sides of the subsatellite point.

3. The echo signal acquisition method based on the variable-configuration multi-load agile maneuvering satellite configuration according to claim 1, further comprising left-right vertical orbit same side view image acquisition, wherein the left-right vertical orbit same side view image acquisition comprises: when the left-right vertical orbit same side view condition occurs, the imaging reconnaissance load line is perpendicular to the flight speed direction, and the imaging reconnaissance load of the satellite main structure simultaneously images the same side of the subsatellite point.

4. The echo signal acquisition method based on the variable-configuration multi-load agile maneuvering satellite configuration according to claim 1, further comprising forward-backward along orbit same side view moving target detection, wherein the forward-backward along orbit same side view moving target detection comprises: when the forward-backward along orbit same side view condition occurs, the imaging reconnaissance load line is parallel to the flight speed direction, and the imaging reconnaissance load of the satellite main structure simultaneously images the same side of the subsatellite point.

5. The echo signal acquisition method based on the variable-configuration multi-load agile maneuvering satellite configuration according to claim 1, further comprising up-down vertical orbit opposite side view detection of uplink and downlink signals, wherein the up-down vertical orbit opposite side view detection of uplink and downlink signals comprises: when the up-down vertical orbit opposite side view condition occurs, the imaging reconnaissance load line is perpendicular to the flight speed direction, one side of the imaging reconnaissance load is rotated by 180° around the truss shaft to point to the high orbit area, and the other side of the imaging reconnaissance load remains to point to the ground.

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