A type of satellite

Abstract

This application discloses a satellite, including a pentagonal prism body and a retractable and deployable solar panel disposed on the pentagonal prism body. The pentagonal prism body includes a docking plate, such that when the docking plate is installed on the arc-shaped mounting surface of the launch device, the projection envelope of the pentagonal prism body, the retracted solar panel, and the arc-shaped mounting surface on a plane perpendicular to the docking plate forms a fan-shaped ring. In this way, when the solar panel is in the retracted state and the satellite is installed on the launch device, the lateral envelope area of ​​the satellite and the arc-shaped mounting surface forms a fan-shaped ring. This fan-shaped ring occupies a portion of the mounting space around the launch device, thus enabling the launch of multiple satellites with a single rocket, thereby reducing the satellite launch cost.

Description

Technical Field

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

[0002] Currently, as satellites play an increasingly important role in meeting civilian needs and military missions, and considering both cost and benefits, users have put forward requirements for the overall design of satellites, such as diversification, multi-functionality, wide coverage, rapid mobility, low cost, and high efficiency.

[0003] In the existing technology, for Earth observation and space navigation satellites, users hope to launch them with the lowest possible configuration without affecting the satellite's normal power supply, remote control, telemetry, and other functions. However, current Earth observation and space navigation satellites, due to structural limitations, have difficulty reducing their launch costs. Therefore, it is necessary for those skilled in the art to provide a satellite that can reduce launch costs in a timely manner. Summary of the Invention

[0004] The purpose of this application is to provide a satellite that can reduce launch costs.

[0005] To achieve the above objectives, this application provides a satellite, including a pentagonal prism body and a retractable and deployable sail disposed on the pentagonal prism body. The pentagonal prism body includes a docking plate such that when the docking plate is mounted on the arc-shaped mounting surface of the launch device, the projection envelope of the pentagonal prism body, the retracted sail, and the arc-shaped mounting surface on a plane perpendicular to the docking plate forms a fan-shaped ring.

[0006] In some embodiments, the pentagonal prism body is provided with a main ground-facing surface, a set of secondary ground-facing surfaces, and a set of celestial-facing surfaces. The set of secondary ground-facing surfaces is located on both sides of the main ground-facing surface, and the set of celestial-facing surfaces and the set of secondary ground-facing surfaces are respectively arranged opposite to each other.

[0007] The main body is equipped with a ground observation payload to perform preset ground observation operations;

[0008] Each of the first communication devices is installed on the ground to enable ground communication, and a second communication device is installed on the pentagonal prism body located inside the first communication device. The second communication device and the first communication device form full space coverage.

[0009] Each of the groups of objects in the sky is equipped with a sky navigation device to enable sky navigation.

[0010] In some embodiments, the pentagonal prism body further includes a load mounting plate, a set of communication equipment mounting plates, a docking plate, a sail mounting plate, and a pair of cover plates, wherein the load mounting plate, the set of communication equipment mounting plates, the docking plate, the sail mounting plate, and the pair of cover plates form a pentagonal prism body with a closed inner cavity.

[0011] The main ground-facing component is mounted on the load mounting plate, a set of auxiliary ground-facing components are mounted on a set of communication equipment mounting plates, and a set of aerial-facing components are mounted on the docking plate and the sail mounting plate.

[0012] In some embodiments, the pentagonal prism body further includes a partition assembly disposed in the inner cavity to support the load mounting plate and the ground observation load.

[0013] In some embodiments, the partition assembly includes a plurality of partitions arranged at equal intervals, which divide the inner cavity of the pentagonal prism body into a plurality of compartments, each compartment being provided with an inclined flywheel to adjust the posture of the pentagonal prism body.

[0014] In some embodiments, the Earth observation payload is an imaging device, the first communication device and the second communication device both include a telemetry and control transmitting antenna and a telemetry and control receiving antenna, and the sky navigation device includes a navigation antenna.

[0015] In some embodiments, the cover plate is provided with a thruster for adjusting the running track of the pentagonal prism body.

[0016] In some embodiments, the end of the sail connected to the pentagonal prism body has at least two rotational degrees of freedom, allowing the sail to rotate relative to the pentagonal prism body.

[0017] In some embodiments, one end of the sail is rotatably connected to the pentagonal prism body via a first rotary drive mechanism and a second rotary drive mechanism. One end of the sail is connected to one end of the first rotary drive mechanism, which drives the sail to rotate around a first axis. The other end of the first rotary drive mechanism is connected to the second rotary drive mechanism, which is fixed to the pentagonal prism body and drives the sail to rotate around a second axis.

[0018] In some embodiments, the central angle of the fan ring is 90°, and when the docking plate is installed on the arc-shaped mounting surface, both the pentagonal prism body and the folded sail have a safety gap of a preset size on both sides.

[0019] Compared to the aforementioned background technology, the satellite provided in this application embodiment includes a pentagonal prism body and a retractable and deployable solar panel. The solar panel is mounted on the pentagonal prism body. It can be seen that the satellite body adopts a pentagonal prism structure. Simultaneously, the pentagonal prism body includes a docking plate. When the docking plate is installed on the arc-shaped mounting surface of the launch device, the projection envelope of the pentagonal prism body, the retracted solar panel, and the arc-shaped mounting surface on a plane perpendicular to the docking plate forms a fan-shaped ring. In this way, when the solar panel is in the retracted state and the satellite is mounted on the launch device, the lateral envelope area of ​​the satellite and the arc-shaped mounting surface forms a fan-shaped ring. This fan-shaped ring occupies a portion of the mounting space around the launch device, thus meeting the conditions for launching multiple satellites with a single rocket, thereby reducing the satellite launch cost. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the satellite launch envelope angle in an embodiment of this application;

[0022] Figure 2 This is a schematic diagram of the overall structure of the satellite in the embodiments of this application;

[0023] Figure 3 for Figure 2 A structural diagram of the satellite from another angle is shown.

[0024] Figure 4 for Figure 2 The diagram shows the internal structure of the satellite.

[0025] Figure 5 for Figure 2 The diagram shows the deployment of the solar panels in the satellite.

[0026] Figure 6 for Figure 2 The diagram shows the satellite in its first Earth observation attitude.

[0027] Figure 7 for Figure 2 The diagram shows the satellite in its second Earth observation attitude.

[0028] Figure 8 for Figure 2 The diagram shows the satellite in its third Earth observation attitude.

[0029] in:

[0030] 100 - Pentagonal prism body;

[0031] 101-Load mounting plate, 102-Communication equipment mounting plate, 103-Dating plate, 104-Sail plate mounting plate, 105-Cover plate, 106-Block plate;

[0032] 110-Main ground-based antenna, 111-Ground observation payload, 120-First auxiliary ground-based antenna, 121-First ground-based telemetry and control transmitting antenna, 122-First ground-based telemetry and control receiving antenna, 123-First data transmission antenna, 130-Second auxiliary ground-based antenna, 131-Second ground-based telemetry and control transmitting antenna, 132-Second ground-based telemetry and control receiving antenna, 133-Second data transmission antenna, 140-First sky-based antenna, 141-First navigation antenna, 150-Second sky-based antenna, 151-Second navigation antenna, 161-Sky-based telemetry and control transmitting antenna, 162-Sky-based telemetry and control receiving antenna, 171-Inclined flywheel, 172-Thruster, 173-Three-axis thermocouple, 180-Sailboard, 181-First rotary drive mechanism, 182-Second rotary drive mechanism;

[0033] 200 - Sector ring, 201 - First projection envelope, 202 - Second projection envelope, 203 - Third projection envelope, 204 - Fourth projection envelope. Detailed Implementation

[0034] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0035] To enable those skilled in the art to better understand the present application, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0036] Please refer to the instruction manual appendix. Figure 1 The satellite described in this application embodiment includes a pentagonal prism body 100, on which a retractable and deployable sail 180 is provided. The sail 180 can be a solar sail 180. The function of the deployed sail 180 is to collect solar energy to power the satellite.

[0037] It can be seen that the satellite body adopts a pentagonal prism structure. At the same time, the pentagonal prism body 100 includes a docking plate 103. When the docking plate 103 is installed on the arc-shaped mounting surface of the launch device (generally a launch vehicle), the projection envelope of the pentagonal prism body 100, the retracted sail 180 and the arc-shaped mounting surface on the plane perpendicular to the docking plate 103 forms a fan ring 200.

[0038] It should be noted that the outline of the fan ring 200 includes the first projection envelope 201 of the arc-shaped mounting surface on the plane perpendicular to the docking plate 103, the second projection envelope 202 of the folded sail 180 on the plane perpendicular to the docking plate 103, the third projection envelope 203 of the side of the pentagonal prism body 100 away from the sail 180 on the plane perpendicular to the docking plate 103, and the fourth projection envelope 204 of the side of the satellite away from the arc-shaped mounting surface on the plane perpendicular to the docking plate 103.

[0039] In this way, when the solar panel 180 is in the retracted state, and the satellite is installed on the launch device, the lateral envelope area of ​​the satellite and the arc-shaped mounting surface forms a fan ring 200. The fan ring 200 occupies a part of the mounting space around the launch device, which can meet the conditions for launching multiple satellites with one rocket, thereby reducing the launch cost of the satellite.

[0040] In some embodiments, the central angle of the fan ring is 90°, and when the docking plate 103 is installed on the arc-shaped mounting surface, both the pentagonal prism body 100 and the folded sail 180 have a safety gap of a preset size on both sides. The preset size is preferably 100 mm.

[0041] In other words, after the satellite is installed on the launch pad, it occupies a 90° sector of the 360° space surrounding the launch pad, with a 100mm safety gap reserved on both sides of the satellite. This allows for the launch of four satellites in one launch, thereby reducing the launch cost to one-quarter of that of the entire launch vehicle.

[0042] In this embodiment, the satellite is a dual-purpose Earth observation and space navigation satellite. Current users desire to achieve wide-area Earth observation with minimal cost configuration, without affecting the satellite's normal power supply, remote control, telemetry, and other functions. However, current Earth observation and space navigation satellites often only operate in one attitude, leading to some impact on Earth communication and space navigation after attitude adjustments. Therefore, it is necessary for those skilled in the art to provide a satellite capable of providing Earth communication and space navigation in multiple Earth observation attitudes.

[0043] Please refer to the instruction manual appendix. Figure 2 Included with instruction manual Figure 3The satellite provided in this application embodiment has a pentagonal prism body 100 with a main ground-monitoring device 110, a set of secondary ground-monitoring devices, and a set of celestial-monitoring devices. The set of secondary ground-monitoring devices is located on both sides of the main ground-monitoring device 110, and the set of celestial-monitoring devices and the set of secondary ground-monitoring devices are respectively arranged opposite to each other. The main ground-monitoring device 110 is equipped with a ground observation payload 111, which is used to perform preset operations on the ground. Each of the secondary ground-monitoring devices is equipped with a first communication device for ground communication. A second communication device is installed on the pentagonal prism body 100 located inside the set of celestial-monitoring devices, and the second communication device and the first communication device on the set of secondary ground-monitoring devices form full space coverage. Each of the celestial-monitoring devices is equipped with a celestial navigation device to achieve celestial navigation.

[0044] It should be noted that satellites are the optimal transmission medium for high-utilization international trunk lines. The principle of satellite communication is to launch a satellite into a geostationary orbit 36,000 km above the equator. The satellite's transponders receive signals transmitted from ground stations, amplify and convert the signals before relaying them to other ground stations, thus completing the transmission between them. Satellite communication systems have advantages such as wide bandwidth, large communication capacity, low bit error rate, high communication quality, and wide coverage.

[0045] In this embodiment, the communication satellite is mainly used for long-distance transmission of telephone, telex, and television services. For example, the Earth observation payload 111 can be an imaging device, such as a remote sensing camera. When the Earth observation payload 111 is a remote sensing camera, the satellite can transmit satellite images or satellite remote sensing images, also called satellite images. Remote sensing means sensing from a distance. Satellite remote sensing involves using satellites in space to detect the reflection and emission of electromagnetic waves by objects on the Earth's surface, thereby extracting information about these objects, identifying them at a distance, and converting and recognizing this electromagnetic wave information to obtain the image, which is the satellite image. Of course, depending on actual needs, the Earth observation payload 111 can also be other detection devices, and this embodiment does not impose specific limitations on this.

[0046] It is understood that the satellite configured according to the embodiments of this application can realize ground communication and space navigation in the main ground observation attitude 110, as well as ground communication and space navigation in the respective ground observation attitudes of a group of secondary ground observation satellites.

[0047] Specifically, when the main ground observation payload 110 is observing the ground, the ground observation payload 111 is directly facing the ground (directly facing the ground). A group of secondary ground observation payloads' first communication devices jointly complete the ground communication work. The second communication device and the group of secondary ground observation payloads' first communication devices form full space coverage. A group of celestial navigation devices jointly complete the celestial navigation work. When the first secondary ground observation payload 120 in the group of secondary ground observation payloads is observing the ground, the ground observation payload 111 is facing downward to the left (downward to the left). The first communication device on the first secondary ground observation payload 120 completes the ground communication work. The second communication device, the first communication device on the second secondary ground observation payload 130 in the group of secondary ground observation payloads, and the first... The first communication device on the ground 120 forms full space coverage, and the sky navigation device on the sky surface opposite the first ground 120 completes the sky navigation work; when the second ground 130 in the group of ground 120 is observing the ground, the ground observation payload 111 observes the ground to the lower right (lower right ground observation), the first communication device on the second ground 130 completes the ground communication work, and the second communication device, the first communication device on the first ground 120 and the first communication device on the second ground 130 in the group of ground 120 form full space coverage, and the sky navigation device on the sky surface opposite the second ground 130 completes the sky navigation work.

[0048] in, Figure 2 and Figure 3 The X-axis represents the satellite's direction of travel, the Y-axis represents the normal direction of the first satellite relative to the ground at 120 degrees, and the Z-axis represents the normal direction of the second satellite relative to the ground at 130 degrees.

[0049] In this way, according to different observation targets and directions, the embodiments of this application set three attitudes, that is, the three attitudes can be adjusted by the roll of the satellite, so that the Earth observation payload 111 on the satellite has the ability to observe directly below, to the lower left and to the lower right, and realize Earth communication and space navigation under multiple Earth observation attitudes.

[0050] It should be noted that the above-mentioned "directly facing the ground," "lower left facing the ground," and "lower right facing the ground" are set with reference to the satellite's direction of travel. Among them, "lower left facing the ground" and "lower right facing the ground" refer to the lower left and lower right of the satellite's direction of travel, respectively.

[0051] In some embodiments, the pentagonal prism body 100 further includes a load mounting plate 101, a set of communication equipment mounting plates 102, a sail mounting plate 104, and a pair of cover plates 105, wherein the load mounting plate 101, the set of communication equipment mounting plates 102, the docking plate 103, the sail mounting plate 104, and the pair of cover plates 105 form a pentagonal prism configuration with a closed inner cavity.

[0052] The main ground-facing device 110 is mounted on the load mounting plate 101, a set of auxiliary ground-facing devices (the first auxiliary ground-facing device 120 and the second auxiliary ground-facing device 130) are respectively mounted on a set of communication equipment mounting plates 102, and a set of roof-facing devices (the first roof-facing device 140 and the second roof-facing device 150) are respectively mounted on the sailboard mounting plate 104 and the docking plate 103.

[0053] Understandably, the satellite's pentagonal prism body 100 structure adopts a pentagonal prism box-plate configuration, formed by cutting off one edge of a cuboid (hexahedron), resulting in a pentagonal prism with a large 45° inclined plane (i.e., the main face to the ground 110). Besides the two end faces facing the opposite direction of flight, the five sides of the pentagonal prism have different functions:

[0054] a) Load mounting surface (also known as the main ground surface 110, located on the load mounting plate 101): Figure 1 The inclined plane shown is on which the Earth observation load 111 is installed. When the normal of the plane is directly facing the Earth's center, the Earth observation load 111 is directly observing the Earth.

[0055] b) First ground-facing device 120 (located on a communication equipment mounting plate 102): A narrow surface on one side of the main ground-facing device 110. After the satellite rolls 45° around its flight axis, the payload observes downwards and to the left. The normal of this surface is directly facing the ground. A first communication device (including a first ground-facing telemetry and control transmitting antenna 121, a first ground-facing telemetry and control receiving antenna 122, and a first data transmission antenna 123) is installed on it to realize ground communication in this attitude.

[0056] c) Second ground-to-surface 130 (located on another communication equipment mounting plate 102): The narrow surface on the other side of the main ground-to-surface 110. After the satellite rolls -45° around its flight axis, the payload observes downwards and to the right. The normal of this surface is directly facing the ground. Another set of first communication equipment (including the second ground-to-surface telemetry and control transmitting antenna 131, the second ground-to-surface telemetry and control receiving antenna 132, and the second data transmission antenna 133) is installed on it to realize ground communication in this attitude.

[0057] d) Solar panel mounting surface (also known as the first pair of sky panels 140, located on the solar panel mounting plate 104): opposite to the first pair of ground planes 120, on which a solar panel 180 is mounted and a first navigation antenna 141 is installed to realize the reception of satellite navigation signals in the sky direction when the first pair of ground planes 120 is facing the ground.

[0058] e) Satellite-rocket docking surface (also known as the second pair of sky surfaces 150, located on the docking plate 103): opposite to the second pair of ground surfaces 130, it is the docking surface between the satellite and the launch vehicle, and a second navigation antenna 151 is installed thereto enable the satellite to receive navigation signals in the sky direction when the second pair of ground surfaces 130 is facing the ground.

[0059] In addition, the satellite has attitude and orbit control units such as star sensors and propulsion devices installed on its two end faces (on the two cover plates 105 respectively) in the direction of flight. For example, a thruster 172 is set on the rear cover plate 105, which is used to adjust the satellite's orbit.

[0060] Meanwhile, on the two end faces mentioned above, a second communication device (including a sky telemetry and control transmitting antenna 161 and a sky telemetry and control receiving antenna 162) is installed. Its direction is opposite to that of the main ground 110, forming full space coverage with the two auxiliary ground telemetry and control antennas to ensure uninterrupted telemetry and remote control signals.

[0061] In other words, the Earth observation payload 111 is installed on the inclined surface of a pentagonal prism. The inclined surface serves as the primary ground observation point 110, the narrow faces on both sides of the inclined surface serve as two secondary ground observation points, and the opposite sides of the two secondary ground observation points serve as two celestial observation points. That is, the five outer faces of the pentagonal prism serve as three ground observation points and two celestial observation points. A set of ground observation and control antennas and data transmission antennas are installed on each of the two secondary ground observation points, and a set of celestial observation and control antennas is installed at the diagonal corner of the inclined surface (the angle between the two celestial observation points), forming all-sky coverage with ground observation as the primary focus. At the same time, a set of navigation antennas is installed on each of the two celestial observation points, forming all-sky coverage.

[0062] In some embodiments, in order to achieve full-space solar capture, a three-axis solar sensor 173 is installed on the spacecraft docking surface and the second ground-to-ground 130.

[0063] In some embodiments, the pentagonal prism body 100 further includes a partition assembly disposed in the inner cavity to support the load mounting plate 101 and the ground observation load 111.

[0064] Preferably, the partition assembly inside the pentagonal prism body 100 structure bears the longitudinal load. In this way, the load is transmitted from the docking plate 103 through the partition assembly to the load mounting plate 101, where it bears the overload of the main load, achieving the shortest force transmission path and ensuring the support stability of the ground observation load 111.

[0065] In some embodiments, the partition assembly includes a plurality of partitions 106 arranged at equal intervals (e.g., three partitions 106). The partitions 106 divide the inner cavity of the pentagonal prism body 100 into a plurality of compartments, and each compartment is provided with an inclined flywheel 171 to adjust the posture of the pentagonal prism body 100.

[0066] Please refer to the instruction manual appendix as well. Figure 4The three partitions 106 divide the internal space of the pentagonal prism configuration into four compartments, each housing a platform unit and a payload unit. Four inclined flywheels 171 are respectively installed on the bottom plates of the four compartments. This fully utilizes the bottom plate, cover plate 105, and partitions 106 as mounting plates for the units, effectively utilizing the internal space and avoiding the existence of useless space in narrow corners and central cavities.

[0067] This approach, compared to existing technologies that employ costly propulsion and control systems, resulting in larger satellite sizes and higher launch and separation costs, achieves a lower cost. Furthermore, the satellite provided in this application meets the low-cost requirement, and its Earth-to-ground communication and space-to-air navigation remain unaffected after attitude adjustments.

[0068] In some embodiments, the end of the sail 180 connected to the pentagonal prism body 100 has at least two rotational degrees of freedom, allowing the sail 180 to rotate relative to the pentagonal prism body 100.

[0069] Understandably, after the satellite enters orbit and separates from the launch vehicle, the solar panels deploy 180 degrees to conduct Earth observation work.

[0070] Please refer to the instruction manual appendix as well. Figure 5 One end of the sail 180 is rotatably connected to the pentagonal prism body 100 via a first rotary drive mechanism 181 (also called a connecting frame drive mechanism) and a second rotary drive mechanism 182 (also called a root drive mechanism). One end of the sail 180 is connected to one end of the first rotary drive mechanism 181, which drives the sail 180 to rotate around a first axis. The other end of the first rotary drive mechanism 181 is connected to the second rotary drive mechanism 182, which is fixed to the pentagonal prism body 100 and drives the sail 180 to rotate around a second axis.

[0071] Specifically, the sail 180 is driven by a root drive mechanism and a connecting frame drive mechanism to achieve directional rotation at any angle. The root drive mechanism drives the sail 180 to rotate around the N-axis, and the connecting frame drive mechanism drives the sail 180 to rotate around the M-axis. The spatial position of the sail 180 is expressed by two coordinates (m, n), where m represents the rotation angle of the connecting frame drive mechanism and n represents the rotation angle of the root drive mechanism. Figure 5 The spatial position of the sailboard 180 shown is (0, 0).

[0072] In summary, the satellite provided in this application embodiment can define three attitudes based on different observation targets and directions, and achieve these three attitudes through satellite roll attitude adjustment. The details are as follows:

[0073] Please refer to the instruction manual appendix as well. Figure 6The satellite's main ground-monitoring antenna (110) faces the ground, with its payload directly observing the Earth. Two sets of telemetry, tracking, and command (TT&C) antennas and data transmission antennas on the first and second ground-monitoring antennas (120 and 130) work together to complete ground communication. The space-based TT&C transmitting antenna (161) and space-based TT&C receiving antenna (162) provide full space coverage. Two navigation antennas on the satellite-rocket docking surface and the solar panel mounting surface work together to complete space-based navigation and communication. Figure 6 The configuration shown is of the solar panel at position 180 (-45, 0). The solar panel rotates in real time according to the sun's position.

[0074] Please refer to the instruction manual appendix as well. Figure 7 The satellite rolls 45°, positioning the first ground-monitoring antenna 120 directly facing the ground, while the payload observes the ground from the lower left. The telemetry and control antennas and data transmission antennas on the first ground-monitoring antenna 120 complete ground communication. The space-to-ground telemetry and control transmitting antenna 161, the space-to-ground telemetry and control receiving antenna 162, and the second ground-monitoring antenna 130 together form full-space coverage. The navigation antenna on the solar panel mounting surface completes space-to-air navigation and communication. Figure 7 The secondary configuration shown is of the 180 (90, 0) position of the solar panel. The 180 solar panel rotates in real time according to the sun's position.

[0075] Please refer to the instruction manual appendix as well. Figure 8 The satellite rolls -45°, aligning the second ground-monitoring antenna (130) directly with the ground, while the payload performs ground observation from the lower right. The telemetry, tracking, and command (TT&C) antennas and data transmission antennas on the second ground-monitoring antenna (130) complete ground communication. The space-to-ground TT&C transmitting antenna (161), space-to-ground TT&C receiving antenna (162), and the TT&C antennas on the first ground-monitoring antenna (120) form full space coverage. The navigation antennas on the satellite-rocket docking surface complete space-to-ground navigation and communication. Figure 8 The secondary configuration shown is of the 180 (0, 0) position of the solar panel. The 180 solar panel rotates in real time according to the sun's position.

[0076] Using the satellite provided in the embodiments of this application can bring the following beneficial effects:

[0077] Firstly, the satellite's pentagonal prism body 100 structural configuration adopts a pentagonal prism box-plate structure. Based on the rectangular box-plate configuration with a large volume ratio, one edge is cut off to become a pentagonal prism configuration, avoiding the existence of useless space in narrow corners and central cavities, and further increasing the effective utilization rate of the satellite's internal space.

[0078] Secondly, the satellites are small in size, with a pentagonal prism structure, resulting in lower development costs. The satellite envelope size is designed for a four-satellite launch with a wall-mounted central support cylinder. The satellite's envelope space is a quarter-sector of the launch vehicle's space, meaning the launch vehicle only needs to bear one-quarter of the launch costs, significantly reducing launch costs.

[0079] Third, the satellite adopts a three-plane configuration with three ground-facing and two-plane-facing orientations, effectively enabling ground-to-ground communication and space-to-space navigation in three ground-to-ground observation attitudes.

[0080] Fourth, attitude control is achieved through four inclined flywheels 171, avoiding the need for a high-cost propulsion system. The attitude control system achieves low cost by using only the flywheels for rolling and attitude adjustment.

[0081] Fifth, by employing one solar panel 180 and a two-axis drive mechanism to control the solar panel 180's orientation to the sun, the utilization efficiency of the solar panel 180 is improved, the area of ​​the solar panel 180 is minimized, and the development cost of the solar panel 180 is reduced. At the same time, one solar panel 180 only requires one set of two-axis drive mechanisms, reducing the number of drive mechanisms and lowering their cost.

[0082] It should be noted that in this specification, relational terms such as first and second are used only to distinguish one entity from several other entities, and do not necessarily require or imply any such actual relationship or order between these entities.

[0083] The satellite provided in this application has been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are merely for the purpose of helping to understand the solution and core ideas of this application. It should be noted that those skilled in the art can make various improvements and modifications to this application without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of this application.

Claims

1. A satellite, characterized in that, It includes a pentagonal prism body and a retractable and deployable sail disposed on the pentagonal prism body. The pentagonal prism body includes a docking plate such that when the docking plate is installed on the arc-shaped mounting surface of the launching device, the projection envelope of the pentagonal prism body, the retracted sail, and the arc-shaped mounting surface on a plane perpendicular to the docking plate forms a fan-shaped ring. The pentagonal prism body has a main ground plane, a set of secondary ground planes and a set of celestial planes. The set of secondary ground planes is located on both sides of the main ground plane, and the set of celestial planes and the set of secondary ground planes are respectively arranged opposite to each other. The main ground is equipped with a ground observation payload to perform preset ground operations; Each of the aforementioned sub-surfaces is equipped with a first communication device to enable ground communication. A second communication device is installed on the pentagonal prism body, located inside the aforementioned celestial surface. The second communication device and the first communication device form full space coverage. Each of the aforementioned celestial surfaces is equipped with celestial navigation devices to enable celestial navigation.

2. The satellite as described in claim 1, characterized in that, The pentagonal prism body also includes a load mounting plate, a set of communication equipment mounting plates, a sailboard mounting plate, and a pair of cover plates. The load mounting plate, the set of communication equipment mounting plates, the docking plate, the sailboard mounting plate, and the pair of cover plates form the pentagonal prism body with a closed inner cavity. The main ground plane is mounted on the load mounting plate, a set of auxiliary ground planes are respectively mounted on a set of communication equipment mounting plates, and a set of aerial planes are respectively mounted on the docking plate and the sail mounting plate.

3. The satellite as described in claim 2, characterized in that, The pentagonal prism body also includes a partition assembly disposed in the inner cavity to support the load mounting plate and the Earth observation load.

4. The satellite as described in claim 3, characterized in that, The partition assembly includes several partitions arranged at equal intervals. The partitions divide the inner cavity of the pentagonal prism into several compartments. Each compartment is equipped with an inclined flywheel to adjust the posture of the pentagonal prism.

5. The satellite as described in claim 1, characterized in that, The Earth observation payload is an imaging device, the first communication device and the second communication device both include a telemetry and control transmitting antenna and a telemetry and control receiving antenna, and the space navigation device includes a navigation antenna.

6. The satellite as described in claim 2, characterized in that, The cover plate is equipped with a thruster, which is used to adjust the running track of the pentagonal prism body.

7. The satellite as described in any one of claims 1-6, characterized in that, The end of the sail connected to the pentagonal prism body has at least two rotational degrees of freedom, allowing the sail to rotate relative to the pentagonal prism body.

8. The satellite as described in claim 7, characterized in that, One end of the sail is rotatably connected to the pentagonal prism body via a first rotation drive mechanism and a second rotation drive mechanism. One end of the sail is connected to one end of the first rotation drive mechanism, which drives the sail to rotate around a first axis. The other end of the first rotation drive mechanism is connected to the second rotation drive mechanism, which is fixed to the pentagonal prism body. The second rotation drive mechanism drives the sail to rotate around a second axis.

9. The satellite as described in any one of claims 1-6, characterized in that, The central angle of the fan ring is 90°, and when the docking plate is installed on the arc-shaped mounting surface, both the pentagonal prism body and the folded sail have a safety gap of a preset size on both sides.

Images