A small GEO communication satellite configuration

Abstract

The application provides a small GEO communication satellite configuration, which comprises a satellite main body structure, a solar cell array, an antenna unit and a satellite-rocket separation mechanism; the satellite main body structure comprises a structural assembly, the structural assembly is assembled into a trapezoidal hexahedral box type satellite body, in a three-dimensional coordinate system OXYZ with the geometric center of the structural assembly as an origin O, side plates are arranged along X, Y and Z directions respectively, the side plates comprise a +Z side plate, a -Z side plate, a +Y side plate, a -Y side plate, a +X side plate, a -X side plate and an OX side plate, wherein the +Z side plate, the -Z side plate, the +Y side plate, the -Y side plate, the +X side plate and the -X side plate are connected into the trapezoidal hexahedral box type satellite body, the OX side plate is installed between the +X side plate and the -X side plate and abuts against the -Z side plate, and the OX side plate is located at the middle line of the +X side plate, the -X side plate and the -Z side plate. The application removes the traditional force bearing cylinder design, increases the flexibility of the internal space of the satellite, and improves the space utilization efficiency.

Description

Technical Field

[0001] This application relates to the field of spacecraft structure technology, and in particular to a configuration of a small GEO communication satellite. Background Technology

[0002] Satellite configuration design is a crucial part of overall satellite design. Its fundamental task is to determine the satellite's main load-bearing structure, module composition, dimensions, and launch vehicle interfaces under various constraints, and to complete the layout design of various satellite equipment. A suitable satellite configuration design can better adapt to payload requirements, offering advantages such as reducing satellite envelope size, decreasing satellite weight, improving satellite space utilization, and enhancing launch vehicle space utilization.

[0003] Traditional GEO (Geostationary Orbit) satellites often employ a cuboid structure with a central load-bearing cylinder. This configuration is technologically mature, has high mechanical strength, and the cylindrical space of the load-bearing cylinder can accommodate fuel tanks for chemical propulsion. Examples include the LS-1300 satellite platform from Loral Corporation in the United States, the SpaceBus4000 platform from TAS Corporation in Europe, the Eurostar3000 platform from ADS Corporation in Europe, and the DFH-4 satellite platform from China.

[0004] However, with the rapid growth in global demand for GEO (Geostationary Orbit) communication satellites, low-cost and high-efficiency satellite design has become crucial. In this context, miniaturization, lightweighting, and "multiple satellites on a single rocket" launch methods will be more advantageous for GEO satellites. The traditional rectangular configuration with a central support tube is no longer suitable for miniaturization and lightweighting due to its structural complexity. The rectangular configuration also has relatively low space utilization within the cylindrical rocket fairing, and with the increasing use of electric propulsion with higher specific impulse, the propulsion tank is significantly reduced in size, leaving the internal space of the cylindrical support tube unused and difficult to utilize for other square-shaped equipment on board.

[0005] To reduce the envelope size of GEO satellites, decrease the overall weight of GEO satellites, improve the internal space utilization efficiency of GEO satellites, and improve the space utilization efficiency of rocket fairings, the satellite configuration must be optimized accordingly. Summary of the Invention

[0006] To achieve the above objectives, this application proposes a small GEO communication satellite configuration, including: a satellite main structure, a solar cell array, an antenna unit, and a satellite-launcher separation mechanism; the satellite main structure includes structural components, which are assembled into a trapezoidal hexahedral box-type satellite, and the solar cell array, satellite-launcher separation mechanism, and antenna unit are respectively mounted on the structural components.

[0007] Specifically, in the three-dimensional coordinate system OXYZ with the geometric center of the structural component as the origin O, side plates are set along the X, Y, and Z directions respectively.

[0008] Specifically, the side plates include: +Z side plate, -Z side plate, +Y side plate, -Y side plate, +X side plate, -X side plate and OX side plate. Among them, the +Z side plate, -Z side plate, +Y side plate, -Y side plate, +X side plate and -X side plate are connected to form a trapezoidal hexahedral box-type star. The OX side plate is installed between the +X side plate and the -X side plate and abuts against the -Z side plate. The OX side plate is located at the center line of the +X side plate, -X side plate and -Z side plate.

[0009] The above technical solution not only eliminates the traditional load-bearing cylinder design, increasing the flexibility of the satellite's internal space and improving the space utilization efficiency of the satellite platform; but also differs from the existing trapezoidal hexahedral box structure in that it sets up OX side plates, which not only separate functional spaces, but also replace the load-bearing frame in supporting the side plate structure.

[0010] Specifically, the side panels are aluminum honeycomb sandwich panels.

[0011] Specifically, the solar array includes: ±Y solar wing deployment panels, ±Y solar wing root hinges, ±Y solar wing inter-panel hinges, and ±Y solar wing clamping and release devices. The ±Y solar wing root hinges are connected to the +Y side panel and the -Y side panel, respectively. The ±Y solar wing root hinges are connected to the ±Y solar wing deployment panels, respectively. The ±Y solar wing clamping and release devices are installed on the ±Y solar wing deployment panels. Each ±Y solar wing deployment panel contains at least two solar wing panels, which are connected to each other via the ±Y solar wing inter-panel hinges.

[0012] Specifically, the antenna units include: a phased array antenna, a telemetry and control antenna, a beacon antenna, a V antenna, and a QV-fed antenna; the phased array antenna, the telemetry and control antenna, and the beacon antenna are mounted on the +Z side panel facing the ground; the QV-fed antenna is mounted on the -Z side panel; and the V antenna is mounted on the +X side panel.

[0013] Specifically, the star-rocket separation mechanism is located on the -X side plate.

[0014] Specifically, the QV-fed antenna and the V-antenna are pointed in the +Z direction after the satellite enters orbit.

[0015] It also includes a phased array antenna, which is mounted on the +Z side panel.

[0016] Compared with the prior art, the advantages of this application are:

[0017] 1. The traditional load-bearing cylinder design has been eliminated, increasing the flexibility of the satellite's internal space, improving the space utilization efficiency of the satellite platform, and adapting to electric propulsion systems.

[0018] 2. Compared to the conventional cuboid configuration, the trapezoidal configuration has two asymmetrical sides. When arranging a planar phased array antenna on the large trapezoidal side, it has more antenna area, which can achieve more antenna gain, lower satellite envelope size, and lower satellite weight.

[0019] 3. It can launch two satellites with one rocket. For cylindrical rocket fairings, it significantly improves the utilization efficiency of launch vehicles and reduces the launch cost of a single satellite. Attached Figure Description

[0020] The accompanying drawings are included to provide a further understanding of the embodiments and are incorporated in and constitute a part of this specification. The drawings illustrate embodiments and, together with the description, serve to explain the principles of this application. Other embodiments and many anticipated advantages of these embodiments will be readily recognized as they become better understood through reference to the following detailed description. Elements in the drawings are not necessarily to scale. The same reference numerals refer to corresponding similar parts.

[0021] Figure 1 This is a schematic diagram of the overall structure of a small GEO communication satellite configuration according to an embodiment of this application;

[0022] Figure 2 This is a structural schematic diagram of a structural component of a small GEO communication satellite configuration according to an embodiment of this application.

[0023] The meanings of the numbers in the diagram are as follows: 1. Structural component; 1a, +X side plate; 1b, -X side plate; 1c, -Y side plate; 1d, +Y side plate; 1e, OX side plate; 1f, -Z side plate; 1g, +Z side plate; 2. Solar cell array; 3. Phased array antenna; 4. QV-fed antenna; 5. Satellite-rocket separation mechanism; 6. V antenna; 7. Beacon antenna; 8. Telemetry and control antenna. Detailed Implementation

[0024] In the following detailed description, reference is made to the accompanying drawings, which form part of the detailed description and illustrate illustrative specific embodiments in which the present application may be practiced. In this regard, directional terms such as “top,” “bottom,” “left,” “right,” “up,” “down,” etc., are used with reference to the orientation of the described figures. Because components of the embodiments can be positioned in several different orientations, directional terms are used for illustrative purposes and are by no means limiting. It should be understood that other embodiments may be utilized or logical changes may be made without departing from the scope of the present application. Therefore, the following detailed description should not be taken in a limiting sense, and the scope of the present application is defined by the appended claims.

[0025] like Figure 1 and Figure 2As shown, a small GEO communication satellite configuration includes: a satellite main structure, a solar cell array 2, an antenna unit, and a satellite-rocket separation mechanism 5; the satellite main structure includes a structural component 1, which is assembled into a trapezoidal hexahedral box-type satellite, and the solar cell array 2, the satellite-rocket separation mechanism 5, and the antenna unit are respectively mounted on the structural component 1.

[0026] In the three-dimensional coordinate system OXYZ with the geometric center of structural component 1 as the origin O, side plates are set along the X, Y and Z directions respectively.

[0027] The side plates include: +Z side plate 1g, -Z side plate 1f, +Y side plate 1d, -Y side plate 1c, +X side plate 1a, -X side plate 1b and OX side plate 1e. Among them, +Z side plate 1g, -Z side plate 1f, +Y side plate 1d, -Y side plate 1c, +X side plate 1a and -X side plate 1b are connected to form a trapezoidal hexahedral box-type star. OX side plate 1e is installed between +X side plate 1a and -X side plate 1b and abuts against -Z side plate 1f. OX side plate 1e is located at the center line of +X side plate 1a, -X side plate 1b and -Z side plate 1f.

[0028] The solar array 2 includes: ±Y solar wing deployment panels, ±Y solar wing root hinges, ±Y solar wing inter-panel hinges, and ±Y solar wing clamping and release devices. The ±Y solar wing root hinges are connected to the +Y side panel 1d and the -Y side panel 1c, respectively. The ±Y solar wing root hinges are connected to the ±Y solar wing deployment panels, respectively. The ±Y solar wing clamping and release devices are installed on the ±Y solar wing deployment panels. Each ±Y solar wing deployment panel contains at least two solar wing panels, which are connected to each other by the ±Y solar wing inter-panel hinges.

[0029] The antenna unit includes: phased array antenna 3, telemetry and control antenna 8, beacon antenna 7, V antenna 6 and QV-fed antenna 4; phased array antenna 3, telemetry and control antenna 8 and beacon antenna 7 are mounted on the +Z side plate 1g facing the ground; QV-fed antenna 4 is mounted on the -Z side plate 1f; V antenna 6 is mounted on the +X side plate 1a.

[0030] The star-rocket separation mechanism 5 is located on the -X side plate 1b.

[0031] QV-fed antenna 4 and V-antenna 6 are pointed in the +Z direction after the satellite enters orbit.

[0032] It also includes a phased array antenna 3, which is mounted on the +Z side plate 1g.

[0033] In one specific embodiment, the satellite mechanical coordinate system is defined as follows: the origin O is located within the mechanical separation surface between the satellite separation mechanism 5 and the launch vehicle, and coincides with the geometric center of gravity of the satellite's side.

[0034] OZ axis (satellite yaw axis): parallel to the separation surface between the satellite and the launch vehicle, passing through the origin O, with the positive direction pointing towards the Earth after the satellite enters orbit;

[0035] OX axis (satellite's rolling axis): perpendicular to the separation surface between the satellite and the launch vehicle, passing through the origin O, with its positive direction pointing in the direction of the launch vehicle's flight, and pointing in the direction of the satellite's flight after entering orbit;

[0036] OY axis (satellite pitch axis): forms a right-handed rectangular coordinate system with OZ and OX axes;

[0037] The OXYZ coordinate system is a rectangular coordinate system, fixed to the celestial body. The OX axis is also the vertically upward direction when the satellite is vertically positioned on the ground, and its axis passes through the Earth's center. When the satellite is in orbit, under theoretical attitude conditions, the OX axis lies within the satellite's orbital plane, with its positive direction pointing in the satellite's direction of travel. The positive direction of the OZ axis points to the Earth's center, and the OY axis is aligned with the normal direction of the orbital plane.

[0038] Based on the constructed OXYZ coordinate system, the satellite configuration is designed as a trapezoidal hexahedral box structure, providing installation and support for other subsystems to form a complete spacecraft. To accommodate all satellite equipment, maximize the mission payload's impact on ground layout space, and fully utilize the launch envelope space, the satellite body is designed as a trapezoidal box structure, composed of seven aluminum honeycomb sandwich panels in ±Z, ±Y, ±X, and OX directions.

[0039] The satellite configuration in the above embodiments takes into account the requirement of launching two satellites with one rocket. By adopting the above satellite configuration, the satellites are mainly distributed in the cylindrical section inside the fairing. This design can be adapted to a 4200mm fairing, in which the fairing can utilize a space diameter of 3850mm. According to the preliminary analysis of three-dimensional simulation assembly, it can meet the static envelope requirements inside the fairing.

[0040] It is obvious that those skilled in the art can make various modifications and alterations to the embodiments of this application without departing from the spirit and scope of this application. In this way, this application also aims to cover such modifications and alterations if they fall within the scope of the claims and their equivalents. The word "comprising" does not exclude the presence of other elements or steps not listed in the claims. The simple fact that certain measures are described in mutually different dependent claims does not indicate that a combination of these measures cannot be used for profit. Any reference numerals in the claims should not be considered limiting in scope.

Claims

1. A small GEO communication satellite configuration, characterized in that, The configuration is adapted to a cylindrical rocket fairing for launching two satellites simultaneously. The configuration includes: a main satellite structure, a solar array, antenna units, and a satellite-rocket separation mechanism. The main satellite structure includes structural components assembled into a trapezoidal hexahedral box-type satellite. The solar array, satellite-rocket separation mechanism, and antenna units are respectively mounted on the structural components. In a three-dimensional coordinate system OXYZ with the geometric center of the structural components as the origin O, side plates are respectively arranged along the X, Y, and Z directions. The side plates include: a +Z side plate, a -Z side plate, a +Y side plate, and a -... The satellite comprises a Y-side plate, a +X-side plate, a -X-side plate, and an OX-side plate, wherein the +Z-side plate, -Z-side plate, +Y-side plate, -Y-side plate, +X-side plate, and -X-side plate are connected to form the trapezoidal hexahedral box-type satellite. The OX-side plate is installed between the +X-side plate and the -X-side plate and abuts against the -Z-side plate, and the OX-side plate is located at the centerline of the +X-side plate, -X-side plate, and -Z-side plate. The satellite-rocket separation mechanism is located on the -X-side plate. The antenna unit includes a phased array antenna, which is installed on the +Z-side plate relative to the ground. The satellite mechanical coordinate system includes: Origin O: Located within the mechanical separation surface between the satellite and the launch vehicle, coinciding with the geometric center of gravity of the satellite's side; and The OX axis is perpendicular to the separation surface between the satellite and the launch vehicle, passes through the origin O of the coordinate system, and points in the positive direction of the launch vehicle's flight direction. After entering orbit, it points in the direction of the satellite's flight direction. The OX axis is also the vertical upward direction when the satellite is vertically parked on the ground, and its axis passes through the Earth's center. When the satellite is in orbit, the OX axis is located in the orbital plane of the satellite, and its positive direction points in the direction of the satellite's forward movement.

2. The configuration of a small GEO communication satellite according to claim 1, characterized in that, The side panel is an aluminum honeycomb sandwich panel.

3. The configuration of a small GEO communication satellite according to claim 2, characterized in that, The solar array includes: ±Y solar array deployment panels, ±Y solar array root hinges, ±Y solar array inter-panel hinges, and ±Y solar array clamping and release devices. The ±Y solar array root hinges are connected to the +Y side panel and the -Y side panel, respectively. The ±Y solar array root hinges are connected to the ±Y solar array deployment panels, respectively. The ±Y solar array clamping and release devices are installed on the ±Y solar array deployment panels. Each ±Y solar array deployment panel contains at least two solar array panels, which are connected to each other via the ±Y solar array inter-panel hinges.

4. The configuration of a small GEO communication satellite according to claim 2, characterized in that, The antenna unit further includes: a telemetry and control antenna, a beacon antenna, a V antenna, and a QV-fed antenna; the telemetry and control antenna and the beacon antenna are mounted on the +Z side plate facing the ground; the QV-fed antenna is mounted on the -Z side plate; and the V antenna is mounted on the +X side plate.

5. A small GEO communication satellite configuration according to claim 4, characterized in that, The QV-fed antenna and the V-antenna are pointed in the +Z direction after the satellite enters orbit.

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