Three-step-shaped load nested satellite configuration

Abstract

The invention provides a three-step-shaped load nested satellite configuration. The three-step-shaped load nested satellite configuration comprises a satellite configuration body, a satellite load, an antenna and a solar cell array, the front Z surface of the satellite configuration body is a ground surface, a first pair of ground steps, a second pair of ground steps and a third pair of ground steps are sequentially arranged on the ground surface, and the heights of the first pair of ground steps, the second pair of ground steps and the third pair of ground steps in the front Z direction are different; the front Z face of the first pair of ground steps, the front Z face of the second pair of ground steps and the front Z face of the third pair of ground steps are all used for installing satellite loads and / or antennas, and the solar cell arrays are located on the positive Y face and the negative Y face of the satellite configuration body. According to the invention, factors such as satellite envelope and centroid constraint, multi-load integration, multiple to-ground front ends and antennas are comprehensively considered, a three-step load nested satellite configuration is designed, the problems that a single satellite carries multiple large-size to-ground loads and the space of the antennas to the ground is insufficient are solved, and meanwhile, the envelope and centroid constraint of carrying is met.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite overall design, and specifically, to a three-step load nested satellite configuration. Background Art

[0002] With the development of earth remote sensing technologies in application fields such as meteorology, environment, and exploration, the satellite tasks and functional requirements have increased. Especially for earth remote sensing satellites, a single payload can no longer meet the user's needs, and the payload size is also getting larger and larger. Satellites often need to carry multiple large-sized payloads with different functions and types. However, due to constraints such as the space envelope of the launch vehicle fairing, large earth observation fields of view of the payloads, and a large number of earth remote sensing payloads, the requirements for the compact configuration of the satellite and the ground space design are getting higher and higher.

[0003] Currently, there are many types of satellite configurations. The satellite ground design is mainly divided into two categories: the top surface and the side surface. Constrained by the lateral envelope of the launch vehicle fairing, the top surface usually has a small area when facing the ground. Large-mass payloads are arranged on the top surface, resulting in a relatively high satellite center of mass and a harsh mechanical environment for the payload during the active section. When the side surface faces the ground, although the area is large, the payload size in the height direction is limited, and all payloads are arranged on the side surface, resulting in a serious eccentricity of the satellite's lateral center of mass and unable to meet the requirements of the launch vehicle for the center of mass. Therefore, it is necessary to design a satellite configuration with a large ground area, a low longitudinal center of mass, and a centered lateral center of mass.

[0004] After retrieving the prior art, Chinese invention patent CN109927938B, with the invention title of Geostationary Orbit Real Aperture Microwave Sounding Satellite Configuration, includes a satellite platform, a microwave sounder, a microwave sounder quasi-optical system, a locking / releasing device, solar wings, a data transmission antenna, and a light shielding mechanism; the main reflector and the sub-reflector of the microwave sounder are pressed on the satellite platform, and the main reflector and the sub-reflector are unlocked and deployed in place after the separation of the satellite and the rocket; the microwave sounder quasi-optical system is installed and embedded in the satellite platform through a micro-deformation frame; the solar wings are installed on the heat dissipation surface of the satellite platform; the data transmission antenna is installed on the top of the satellite platform through a bracket; the satellite platform and the microwave sounder are inclined, that is, there is a certain angle between the earth observation axis and the satellite Z-axis (i.e., +Z ground); after on-orbit stationing, the over-constrained connection between the microwave sounder and the satellite platform is unlocked, and the light shielding mechanism is deployed. This configuration uses the top surface as the ground-facing configuration and carries a single effective payload, and cannot be applied to carrying multiple large-sized payloads and cannot meet the requirements of the launch vehicle for the low longitudinal center of mass of the satellite. Summary of the Invention

[0005] Aiming at the defects in the prior art, the purpose of the present invention is to provide a three-step load nested satellite configuration.

[0006] The three-step load nested satellite configuration provided by the present invention includes a satellite configuration body, satellite payloads, antennas, and solar arrays;

[0007] Build a coordinate system with the satellite's centroid as the coordinate origin O, the +X axis pointing in the satellite's flight direction, the +Z axis pointing to the sub-satellite point, and the +Y axis forming a right-handed rectangular coordinate system with the +X and +Z axes.

[0008] The positive Z-plane of the satellite configuration body faces the ground. On the ground-facing surface, there are successively arranged a first pair of ground steps, a second pair of ground steps, and a third pair of ground steps. The heights of the first pair of ground steps, the second pair of ground steps, and the third pair of ground steps are different in the positive Z direction.

[0009] The positive Z-planes of the first pair of ground steps, the second pair of ground steps, and the third pair of ground steps are all used to install satellite payloads and / or antennas. The solar arrays are arranged on both sides of the positive and negative Y-planes of the satellite configuration body.

[0010] Preferably, the second pair of ground steps is a plate-like structure, and an installation position is formed between the negative Z-plane of the second pair of ground steps and the positive Z-plane of the first pair of ground steps.

[0011] Preferably, the negative Z-plane of the second pair of ground steps and the positive Z-plane of the first pair of ground steps are supported and connected by strengthening frames on both sides.

[0012] Preferably, the satellite payload includes a microwave payload, and the microwave payload is embedded between the positive Z-plane of the first pair of ground steps and the negative Z-plane of the second pair of ground steps.

[0013] Preferably, there are two wings of the solar arrays, and the two wings of the solar arrays are symmetrically arranged on the positive and negative Y-planes of the satellite configuration body and wrap the microwave payload in space.

[0014] Preferably, the antenna includes a radar antenna, and the radar antenna has two mounting surfaces, and the two mounting surfaces are respectively used for double-sided fixed mounting with the positive Z-plane of the second pair of ground steps and the vertical X-axis plane of the third pair of ground steps.

[0015] Preferably, when the satellite is in the active launch stage, the two mounting surfaces of the radar antenna are respectively double-sided fixed-mounted with the second pair of ground steps and the third pair of ground steps.

[0016] After the separation of the satellite and the rocket, one of the mounting surfaces of the radar antenna is unlocked, and the radar antenna is only fixed-mounted with the second pair of ground steps or the third pair of ground steps through one mounting surface.

[0017] Preferably, the antenna includes a data transmission antenna and a telemetry and command antenna, and both the data transmission antenna and the telemetry and command antenna are installed on the positive Z-plane of the third pair of ground steps.

[0018] Preferably, it further includes a star sensor and a sun sensor. The star sensor is installed in the inner layer board of the satellite configuration body and points to the sky through the side plate opening of the inner layer board.

[0019] The sun sensor is installed at the four corners of the satellite configuration body.

[0020] Preferably, two sun sensors are respectively installed on both sides of the vertical X-axis plane of the first pair of ground steps, and two sun sensors are respectively installed on both sides of the positive Z-plane of the third pair of ground steps.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. The present invention comprehensively considers factors such as satellite envelope and centroid constraint, multi-payload integration, multi-ground front ends and antennas, etc., and designs a three-step load nested satellite configuration, which solves the problem of insufficient ground space for a single satellite carrying multiple large-size ground-facing payloads and antennas, and at the same time meets the envelope and centroid constraints of the launch vehicle, and has been verified in actual engineering, providing a reference for the overall configuration design of similar satellites.

[0023] 2. In the present invention, the three ground steps are nested with each other, and can be adaptively adjusted according to the size of the carried payload. Moreover, a strengthening frame is designed between the steps, increasing the stiffness and strength of the satellite body, and having strong practicability and expansibility.

[0024] 3. In the present invention, two installation surfaces are respectively provided for the three ground steps, supporting the double-sided installation of the large-mass payloads carried, and supporting the unlocking of one of the installation surfaces of the payload after the separation of the satellite and the rocket, reducing the influence of overconstraint on the on-orbit thermal deformation. The installation method is reasonable and meets the on-orbit requirements of the satellite.

[0025] 4. In the present invention, the solar array on the outer side of the satellite configuration body adopts the principle of symmetric layout, reducing the influence of the solar array in the stowed and deployed states on the satellite centroid, and meeting the requirements of the satellite control system. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] By reading the following detailed description of the non-limiting embodiments with reference to the accompanying drawings, other features, objects and advantages of the present invention will become more apparent:

[0027] Figure 1 It is the overall structural schematic diagram of the present invention in the stowed state;

[0028] Figure 2 It is the overall structural schematic diagram of the present invention in the deployed state.

[0029] As shown in the figure:

[0030] Satellite configuration body 1, star sensor 7

[0031] Microwave payload 2, Sun sensor 8

[0032] Radar antenna 3, First pair of ground steps 9

[0033] Solar array 4, Second pair of ground steps 10

[0034] Data transmission antenna 5, Third pair of ground steps 11

[0035] TT&C antenna 6 Specific implementation manner

[0036] The present invention will be described in detail below in conjunction with specific embodiments. 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, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0037] The present invention discloses a three-step load nested satellite configuration, which comprehensively considers factors such as satellite envelope and centroid constraints, multi-load integration, multi-ground front ends and antennas, etc., designs a three-step load nested satellite configuration, solves the problem of insufficient ground space for a single satellite carrying multiple large-size ground-facing loads and antennas, and at the same time meets the envelope and centroid constraints of the launch vehicle.

[0038] Before describing in conjunction with specific embodiments, the coordinate systems involved are described as follows:

[0039] Satellite body coordinate system: The origin O of the coordinate system is the centroid of the satellite, the +X axis points to the satellite flight direction, the +Z axis points to the sub-satellite point, and the +Y axis forms a right-handed rectangular coordinate system with the +X axis and the +Z axis;

[0040] Such as Figure 1As shown in the figure, the three-step load nested satellite configuration involved in the present invention includes: a satellite configuration body 1, a microwave payload 2, a radar antenna 3, a solar array 4, a data transmission antenna 5, a TT&C antenna 6, an attitude control sensor, etc. The main body of the satellite configuration body 1 is a hexahedron, with the positive Z-plane facing the ground, adopting a three-step configuration; the microwave payload 2 is arranged on the first ground-facing step 9 and embedded behind the second ground-facing step 10. The radar antenna 3 is arranged on the second ground-facing step 10 and fixedly installed on both sides of the second ground-facing step 10 and the third ground-facing step 11. The data transmission antenna 5 and the TT&C antenna 6 are arranged on the third ground-facing step 11, making full use of the space facing the ground to achieve earth observation and signal reception; the solar array 4 is arranged on both sides of the positive and negative Y-planes of the satellite configuration body 1, and is in a retracted state during the launch active section and in a deployed state after the separation of the satellite and the rocket; the attitude control sensors mainly include a star sensor 7 and a sun sensor 8. The star sensor 7 is arranged on the inner layer board of the cabin, pointing to the sky-facing surface through an opening on the side board, and the sun sensor 8 is arranged at the four corners of the satellite configuration body 1 to achieve the function of capturing the sun when any of the six faces of the satellite faces the sun.

[0041] In the satellite configuration of the present invention, the launch state is as Figure 1 shown, and the flight state is as Figure 2 shown.

[0042] Specifically, the main body of the satellite configuration body is a hexahedron, with the positive Z-plane facing the ground, adopting a three-step configuration;

[0043] The microwave payload 2 is arranged on the first ground-facing step 9 and embedded behind the second ground-facing step 10. The transverse size of the microwave payload 2 is 1300mm×760mm, and the thickness is 550mm. The thickness of the first ground-facing step 9 embedded in the second ground-facing step 10 is determined according to the size of the microwave payload 2, and the specific embedded thickness is 580mm, and the embedded depth is 520mm;

[0044] The microwave payload 2 has a scanning observation field of view requirement of swinging 180° left and right with respect to the ground;

[0045] Between the first ground-facing step 9 and the second ground-facing step 10 of the satellite configuration body 1, it is supported by a strengthening frame, and the material of the strengthening frame is selected as carbon fiber;

[0046] The radar antenna 3 is arranged on the second ground-facing step 10 and fixedly installed on both sides of the second ground-facing step 10 and the third ground-facing step 11. The transverse size of the radar antenna 3 is 1300mm×760mm, and the thickness is 650mm. The second ground-facing step 10 is determined to be 490mm according to the size of the radar antenna 3;

[0047] The radar antenna 3 has two mounting surfaces. The X-direction mounting surface has 10 waist-shaped through holes, and the Z-direction mounting surface has 48 circular through holes, which are fixedly mounted on the second pair of ground steps 10 and the third pair of ground steps 11 in a double-sided manner. The design of the waist-shaped through holes facilitates the process adjustment during double-sided installation. The two mounting surfaces of the active section of the launch are both fixed, and the 10 fastening screws on the X-direction mounting surface are unlocked after the separation of the satellite and the rocket.

[0048] There are two sets of the data transmission antenna 5 and the TT&C antenna 6 respectively. The data transmission antenna 5 and the TT&C antenna 6 both have a requirement for a ground observation field of view with a 60° half-cone angle, and are reasonably arranged on the third pair of ground steps 11 to ensure that the antenna fields of view do not block each other.

[0049] The solar array 4 is arranged on both sides of the positive and negative Y planes of the satellite configuration body 1. It is in a retracted state during the active section of the launch and in an unfolded state after the separation of the satellite and the rocket.

[0050] The solar array 4 has a total of two wings. Each wing of the solar array 4 has four substrates, and the size of a single substrate is 1500 mm × 1350 mm. The two wings of the solar array 4 are symmetrically arranged on both sides of the positive and negative Y planes of the satellite configuration body 1, wrapping the microwave payload 2 in space.

[0051] The attitude control sensors mainly include a star sensor 7 and a sun sensor 8. The star sensor 7 is arranged on the inner layer board of the configuration body, and points to the sky surface through an opening in the side board. The sun sensor 8 is arranged at the four corners of the satellite configuration body 1 to achieve the function of capturing the sun when the satellite faces the sun on all six sides.

[0052] Specifically, the attitude control sensors include one star sensor 7 and four sun sensors 8. The star sensor 7 has a sky observation field of view with a 30° half-cone angle, and is arranged on the inner layer board of the configuration body, and points to the sky surface through an opening in the side board. The sun sensor 8 has a square cone field of view of 45° in each of the three quadrants, and is arranged at the four corners of the satellite configuration body 1 to ensure that the 3 / 4 spherical space field of view corresponding to the quadrant where a single sun sensor 8 is located is visible. The four sun sensors 8 jointly achieve the function of capturing the sun when the satellite faces the sun on all six sides.

[0053] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0054] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A three-step payload nested satellite configuration, characterized in that: It comprises a satellite configuration body (1), a satellite payload, an antenna and a solar cell array (4); Construct a coordinate system with the satellite's center of mass as the coordinate origin O, the +X axis pointing to the satellite's flight direction, the +Z axis pointing to the sub-satellite point, and the +Y axis, +X axis, and +Z axis forming a right-handed rectangular coordinate system; The positive Z-plane of the satellite configuration body (1) is facing the ground, and a first pair of ground steps (9), a second pair of ground steps (10) and a third pair of ground steps (11) are sequentially arranged on the facing ground, and the first pair of ground steps (9), the second pair of ground steps (10) and the third pair of ground steps (11) have different heights in the positive Z direction; The positive Z surface of the first pair of ground steps (9), the positive Z surface of the second pair of ground steps (10) and the positive Z surface of the third pair of ground steps (11) are all used to install satellite payloads and / or antennas, and the solar cell array (4) is arranged on both sides of the positive and negative Y surfaces of the satellite configuration body (1).

2. The three-step payload nested satellite configuration according to claim 1 is characterized in that: The second pair of ground steps (10) is a plate-shaped structure, and a mounting position is formed between the negative Z surface of the second pair of ground steps (10) and the positive Z surface of the first pair of ground steps (9).

3. The three-step payload nested satellite configuration according to claim 2 is characterized in that: The negative Z-surface of the second pair of ground steps (10) and the positive Z-surface of the first pair of ground steps (9) are supported and connected by reinforcement frames on both sides.

4. The three-step payload nested satellite configuration according to claim 2 is characterized in that: The satellite payload comprises a microwave payload (2), and the microwave payload (2) is embedded between the positive Z-plane of the first pair of ground steps (9) and the negative Z-plane of the second pair of ground steps (10).

5. The three-step payload nested satellite configuration according to claim 4 is characterized in that: The solar cell array (4) has two wings in total. The two-wing solar cell arrays (4) are symmetrically arranged on the positive and negative Y planes of the satellite configuration body (1) and wrap around the microwave load (2) in space.

6. The three-step payload nested satellite configuration according to claim 1 is characterized in that: The antenna comprises a radar antenna (3), wherein the radar antenna (3) has two mounting surfaces, and the two mounting surfaces are respectively used for double-sided fixed mounting on the positive Z-plane of the second pair of ground steps (10) and the perpendicular X-axis plane of the third pair of ground steps (11).

7. The three-step payload nested satellite configuration according to claim 6 is characterized in that: When the satellite is in the active transmission phase, the two mounting surfaces of the radar antenna (3) are fixedly mounted on the second pair of ground steps (10) and the third pair of ground steps (11) on both sides; After the satellite and rocket are separated, one of the mounting surfaces of the radar antenna (3) is unlocked, and the radar antenna (3) is fixedly mounted on the second pair of ground steps (10) or the third pair of ground steps (11) only through the one mounting surface.

8. The three-step payload nested satellite configuration according to claim 1, characterized in that: The antenna comprises a data transmission antenna (5) and a measurement and control antenna (6), and the data transmission antenna (5) and the measurement and control antenna (6) are both installed on the positive Z plane of the third pair of ground steps (11).

9. The three-step payload nested satellite configuration according to claim 1, characterized in that: It also includes a star sensor (7) and a sun sensor (8), wherein the star sensor (7) is installed in the inner plate of the satellite configuration body (1) and points to the sky through the side plate opening of the inner plate; The sun sensors (8) are installed at the four corners of the satellite configuration body (1).

10. The three-step payload nested satellite configuration according to claim 9, characterized in that: Two solar sensors (8) are respectively installed on both sides of the vertical X-axis surface of the first pair of ground steps (9), and two solar sensors (8) are respectively installed on both sides of the positive Z-plane of the third pair of ground steps (11).

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