CN111891388A - Compact satellite configuration suitable for multi-band detection load - Google Patents
Compact satellite configuration suitable for multi-band detection load Download PDFInfo
- Publication number
- CN111891388A CN111891388A CN202010753142.0A CN202010753142A CN111891388A CN 111891388 A CN111891388 A CN 111891388A CN 202010753142 A CN202010753142 A CN 202010753142A CN 111891388 A CN111891388 A CN 111891388A
- Authority
- CN
- China
- Prior art keywords
- antenna
- satellite
- solar cell
- satellite body
- wing solar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001514 detection method Methods 0.000 title claims abstract description 52
- 238000004891 communication Methods 0.000 claims abstract description 44
- 230000005540 biological transmission Effects 0.000 claims abstract description 32
- 238000005259 measurement Methods 0.000 claims abstract description 12
- 230000017525 heat dissipation Effects 0.000 claims description 10
- 239000000523 sample Substances 0.000 claims description 9
- 238000005096 rolling process Methods 0.000 claims description 5
- 239000000758 substrate Substances 0.000 claims description 5
- 239000002775 capsule Substances 0.000 claims 1
- 230000010354 integration Effects 0.000 abstract description 5
- 238000013461 design Methods 0.000 description 11
- 238000003491 array Methods 0.000 description 8
- 150000001875 compounds Chemical class 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000001228 spectrum Methods 0.000 description 2
- 238000002076 thermal analysis method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Automation & Control Theory (AREA)
- Toxicology (AREA)
- Environmental Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- Biodiversity & Conservation Biology (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Photovoltaic Devices (AREA)
- Details Of Aerials (AREA)
Abstract
The invention provides a compact satellite configuration suitable for a multi-band detection load, which comprises a satellite body, a double-wing solar cell module, a relay antenna, a multi-band detection load antenna module, a communication load module, a data transmission antenna module, a measurement and control antenna and a thruster, wherein a left wing solar cell array and a right wing solar cell array in the double-wing solar cell module are respectively arranged on the left side surface and the right side surface of the satellite body; the relay antenna and the multi-band detection load antenna assembly are respectively arranged on the back and the front of the satellite body; the communication load assembly and the thruster are both arranged on the satellite body; a left data transmission antenna and a right data transmission antenna in the data transmission antenna assembly are respectively arranged on the left side surface and the right side surface of the satellite body; the measurement and control antenna is arranged on the front and/or the back of the satellite body. The invention has compact configuration, realizes good manufacturability and high integration of the satellite, and meets the on-orbit application requirement of the satellite.
Description
Technical Field
The invention relates to the technical field of overall satellite design, in particular to a compact satellite configuration suitable for a multi-band detection load.
Background
With the development of the ground remote sensing technology in the application fields of weather, environment, detection and the like, the satellite tasks and functional requirements are increased, particularly for a ground remote sensing spectrum monitoring satellite, the load of a single frequency band or type cannot meet the user requirements, the satellite is often required to carry loads of a plurality of different frequency bands, systems, types and functions, but the satellite is limited by the constraints of carrying fairing envelope, mutual compatibility among multi-frequency-band loads, large expansion, multiple movable parts, large heat flux density of a single load machine and the like, and therefore the compact configuration design of the satellite is greatly challenged. Based on the compact satellite configuration suitable for the multi-band detection load, the compact satellite configuration can provide reference for the design of the satellite configuration carrying the same type of load.
At present, many satellite configurations are available for reference at home and abroad, but most of the satellite configurations carry a single type of payload, for example, an embedded compound eye camera load satellite configuration disclosed in patent document CN104309824A includes: the compound eye camera comprises a configuration body, a compound eye camera load, a star sensor and a sun wing, wherein the configuration body is in a regular quadrilateral hexahedral configuration and comprises a bottom plate, a side plate, a top plate, a laminated plate, a conical bearing barrel and a switching ring, the top plate and the bottom plate are respectively connected to the upper end and the lower end of the side plate, the laminated plate is arranged above the bottom plate and connected with the side plate, the conical bearing barrel is arranged between the bottom plate and the laminated plate and connected with the laminated plate, and the switching ring is arranged on the other side of the laminated plate and connected with the conical bearing barrel; the solar wing is connected with the side plate; the compound eye camera load part is arranged on the inner side of the top plate and connected with the adapter ring, the star sensor is connected with the part of the compound eye camera load, which is positioned on the outer side of the top plate, but the design carries a single type of payload.
As disclosed in patent document CN105501471A, the satellite configuration for loading a large deployable antenna with dual reflective surfaces is designed to meet the constraint conditions of rocket fairing envelope and correct deployment of the large deployable antenna by ensuring the relative position relationship among the feed array, the main reflective surface and the sub-reflective surface in the on-orbit flight state, but the design still carries a single type of payload. For compact satellite configurations of multi-band detection loads, no description or report of similar technologies is found, and similar data at home and abroad is not collected.
Disclosure of Invention
In view of the drawbacks of the prior art, it is an object of the present invention to provide a compact satellite configuration suitable for multi-band probe loads.
The compact satellite configuration suitable for the multi-band detection load comprises a satellite body, a double-wing solar cell module, a relay antenna, a multi-band detection load antenna module, a communication load module, a data transmission antenna module, a measurement and control antenna and a thruster, wherein the double-wing solar cell module is arranged on the satellite body;
the double-wing solar cell module, the relay antenna, the multi-band detection load antenna module, the communication load module, the data transmission antenna module, the measurement and control antenna and the thruster are all arranged on the satellite body.
Preferably, the double-wing solar cell module comprises a left wing solar cell array and a right wing solar cell array, and the left wing solar cell array and the right wing solar cell array are respectively installed on the left side surface and the right side surface of the satellite body;
the relay antenna is arranged on the back surface of the satellite body, and the multi-band detection load antenna assembly is arranged on the front surface of the satellite body;
the communication load assembly is arranged between the left side surface and the right side surface or arranged on the left side surface and/or the right side surface;
the data transmission antenna assembly comprises a left data transmission antenna and a right data transmission antenna, and the left data transmission antenna and the right data transmission antenna are symmetrically arranged on the left side surface and the right side surface of the satellite body respectively;
the measurement and control antenna is arranged on the front side and/or the back side of the satellite body;
the number of the thrusters is multiple, and the thrusters are arranged on the front surface, the back surface, the upper surface and/or the lower surface of the satellite body.
Preferably, the satellite body comprises a platform cabin, a load cabin and a thermal control cabin which are sequentially connected from bottom to top.
Preferably, the thermal control cabin adopts active heat dissipation and/or passive heat dissipation.
Preferably, the left wing solar cell array and the right wing solar cell array both comprise 5 substrates;
the left wing solar cell array and the right wing solar cell array are symmetrically arranged on two sides of the satellite body and can be switched between a folded state and an unfolded state.
Preferably, the beam of the relay antenna can dynamically cover 1/2 spherical space;
the relay antenna adopts a one-time folding and unfolding structure, and is pressed on the back of the satellite body in a transmitting state; when the relay antenna runs in the orbit, the relay antenna is unfolded and faces the opposite direction, and the unfolding angle of the unfolding arm is 90 degrees.
Preferably, the multi-band probe load antenna assembly comprises a 4-band antenna array.
Preferably, the communication payload assembly comprises a laser communication payload;
the number of the laser communication loads is six and is divided into 3 groups, and each group comprises two laser communication loads, wherein laser terminals on the two laser communication loads of each group can cover the space of a full view field, and laser terminals on a single laser communication load can cover the 1/2 spherical space formed by the view field.
Preferably, the communication load assembly further comprises a microwave communication load, the microwave communication load comprises three phased array antennas, and a combined beam of the three phased array antennas can realize full spatial coverage; the three phased array antennas are arranged along the circumferential direction of the axis direction of the left side face and the right side face of the satellite body, wherein each phased array antenna can cover 1/3 spherical space.
Preferably, the number of the thrusters is 16, wherein:
6 thrusters are respectively arranged on the upper surface and the lower surface of the satellite body, so that the rapid attitude pitching, attitude yawing and orbit control of the satellite are realized; 2 thrusters are respectively installed on the front surface and the back surface of the satellite body, so that the attitude rolling of the satellite is realized.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention comprehensively considers factors such as satellite envelope constraint, multiple expansion movable parts, multiple types of load integration, large heat consumption of products and the like and carries out optimization design, solves the problem of multi-band type load configuration design carried by a ground remote sensing spectrum monitoring satellite, is verified in practical engineering application, provides reference for the overall configuration design of the similar satellite, has compact configuration, realizes good manufacturability and high integration of the satellite, and meets the on-orbit application requirements of the satellite.
2. The relay antenna and the data transmission antenna are adaptively provided with the unfolding mechanisms, so that the folding state of the unfolding mechanisms meets the carrying envelope, and the fields of view in the unfolding state are compatible with each other.
3. The configuration layout of the large part outside the whole satellite body adopts the design principle of symmetry, folding and mass center reduction, has a reasonable structure, and meets the in-orbit application requirement of the satellite.
4. The satellite body adopts a hexahedral structure, the Y-direction size and the Z-direction size can be partially framed according to product functions, the X-direction size can be determined according to the quantity configuration of satellite products and a thermal analysis result, and the satellite has stronger practicability.
5. The heat control cabin improves the heat dissipation capacity of the cabin section by adopting active heat dissipation and/or passive heat dissipation, and can provide a better temperature environment for a large heat consumption single machine.
6. The invention adopts a plurality of thrusters, can realize the rapid attitude pitching, yawing, rolling and orbit control of the satellite, and provides more convenience for the rapid in-orbit maneuvering and detection of the satellite.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic diagram of a front-facing satellite launching state;
FIG. 2 is a schematic diagram of a satellite in a back-facing satellite launching state;
FIG. 3 is a configuration diagram of a satellite flight state;
fig. 4 is a schematic structural diagram of the thruster on the satellite body.
The figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention provides a compact satellite configuration suitable for a multi-band detection load, which comprises a satellite body 1, a double-wing solar cell module 2, a relay antenna 3, a multi-band detection load antenna module, a communication load module, a data transmission antenna module, a measurement and control antenna and a thruster, wherein the double-wing solar cell module 2, the relay antenna 3, the multi-band detection antenna module, the communication load module, the data transmission antenna module, the measurement and control antenna and the thruster are all arranged on the satellite body 1, as shown in figures 1-2. The invention comprehensively considers the factors of satellite envelope constraint, multiple expansion movable parts, multiple types of load integration, large heat consumption of products, electromagnetic compatibility and the like and carries out optimization design, thereby realizing good manufacturability and high integration of the satellite and meeting the on-orbit application requirements of the satellite.
Specifically, as shown in fig. 1-2, the double-wing solar cell module 2 includes a left-wing solar cell array 21 and a right-wing solar cell array 22, the left-wing solar cell array 21 and the right-wing solar cell array 22 are respectively installed on the left side surface and the right side surface of the satellite body 1, and both the left-wing solar cell array 21 and the right-wing solar cell array 22 include 5 substrates; the left wing solar cell array 21 and the right wing solar cell array 22 are symmetrically arranged on two sides of the satellite body 1, and the left wing solar cell array 21 and the right wing solar cell array 22 can be switched between a folded state and an unfolded state.
Specifically, the relay antenna 3 is installed on the back of the satellite body 1, the beam of the relay antenna 3 can dynamically cover 1/2 sphere space, the relay antenna 3 adopts a one-time folding and unfolding configuration, and in a transmitting state, the relay antenna 3 is pressed on the back of the satellite body 1; when the antenna operates in the orbit, the relay antenna 3 is unfolded and faces the opposite-to-sky direction, and the unfolding angle of the unfolding arm is 90 degrees.
Specifically, the multi-band detection load antenna assembly is installed on the front face of the satellite body 1, and the multi-band detection load antenna assembly comprises an antenna array with 4 frequency bands, and in a preferred example, the multi-band detection load antenna assembly comprises a first detection load antenna 4, a second detection load antenna 5, a third detection load antenna main array 6, a third detection load antenna sub array 7, a fourth detection load antenna main array 8 and a fourth detection load antenna sub array 9.
Specifically, the communication load assembly is arranged between the left side face and the right side face or on the left side face and/or the right side face, the communication load assembly comprises laser communication loads 10 and microwave communication loads 11, the number of the laser communication loads 10 is six, the laser communication loads are divided into 3 groups, each group of two laser communication loads 10 are provided, laser terminals on each group of two laser communication loads 10 can cover the full field of view space, and laser terminals on a single laser communication load 10 can cover 1/2 spherical space formed by the field of view; the microwave communication load 11 comprises three phased array antennas, and the combined beams of the three phased array antennas can realize full airspace coverage; three phased array antennas evenly arrange along the circumference of satellite body 1 left surface, right flank axial direction, wherein, every phased array antenna adopts two face arrays to arrange and realizes the coverage to 1/3 sphere territory space.
The data transmission antenna assembly comprises a left data transmission antenna 12 and a right data transmission antenna 13, and the left data transmission antenna 12 and the right data transmission antenna 13 are respectively and symmetrically arranged on the left side surface and the right side surface of the satellite body 1; the measurement and control antenna is arranged on the front and/or the back of the satellite body 1.
Specifically, the number of the thrusters is plural, and the plurality of thrusters are installed on the front, back, upper and/or lower surfaces of the satellite body 1. In a preferred example, the number of the thrusters is 16, wherein: 6 thrusters are respectively arranged on the upper surface and the lower surface of the satellite body 1, so that the rapid attitude pitching, attitude yawing and orbit control of the satellite are realized; 2 thrusters are respectively arranged on the front surface and the back surface of the satellite body 1, so that the attitude rolling of the satellite is realized.
Specifically, as shown in fig. 1-2, the satellite body 1 includes a platform cabin 101, a load cabin 102, and a thermal control cabin 103, which are connected in sequence from bottom to top, where the thermal control cabin 103 employs active heat dissipation and/or passive heat dissipation.
Example (b):
as shown in fig. 1-2, the left-wing solar cell array 21 and the right-wing solar cell array 22 are respectively folded and installed on the + -Y side of the satellite, the relay antenna 3 is folded and installed on the-Z side of the satellite, the 4 frequency band detection load antennas are highly integrated on the ground (+ Z) of the satellite, the communication load assembly has 9 load heads, and is arranged in the XOZ plane of the satellite, the left data transmission antenna 12 and the right data transmission antenna 13 are symmetrically installed on the + -Y side of the satellite, and the measurement and control antennas are respectively arranged 3 pairs on the + -Z side of the satellite. As shown in FIG. 4, 16 thrusters are arranged on the +/-X and +/-Z side surfaces of the satellite, and the configuration layout of the large part outside the whole satellite body adopts the design principle of symmetry, folding and center of mass reduction.
The satellite configuration of the present invention, the launching state is shown in fig. 1 and fig. 2, and the flight state is shown in fig. 3.
The satellite body 1 is of a hexahedral structure, the dimension is Y multiplied by Z multiplied by X, 2000 mm multiplied by 4500 mm, the Y and Z dimensions can be partially framed according to the functions of the products, and the X dimension can be determined according to the quantity configuration of the satellite products and the thermal analysis result.
The satellite body 1 is sequentially provided with a platform cabin 101, a load cabin 102 and a thermal control cabin 103 along the X direction. The heat control cabin 103 adopts active heat dissipation or passive heat dissipation, and the temperature level of the cabin section of the heat control cabin 103 is lower, so that a better temperature environment can be provided for a large heat consumption single machine.
The left-wing solar cell array 21 and the right-wing solar cell array 22 in the double-wing solar cell module 2 are both composed of 5 substrates, and the size of each substrate is 1800 × 3800 mm. The left wing solar cell array 21 and the right wing solar cell array 22 are respectively folded on the +/-Y side surfaces of the star body and respectively unfolded towards the +/-Y side.
The relay antenna 3 has two-dimensional maneuvering of azimuth and elevation, and the antenna beam can dynamically cover 1/2 sphere space by driving the relay antenna 3 by a driving mechanism. The relay antenna 3 adopts a one-time folding and unfolding structure, is pressed on the satellite-Z side through 4 pressing points in a transmitting state, faces the opposite-to-sky direction after being unfolded, the unfolding angle of the unfolding arm is 90 degrees, and the relay antenna 3 realizes the tracking of the relay satellite through a two-dimensional driving mechanism after being unfolded in place on the orbit.
The multi-band detection load antenna assembly comprises antenna arrays with 4 frequency bands, wherein the antenna arrays with 4 frequency bands are not limited to specific frequency bands, and the antenna arrays with 4 frequency bands are named as a first detection load antenna 4, a second detection load antenna 5, a third detection load antenna (1 third detection load antenna main array 6, 6 third detection load antenna sub-arrays 7) and a fourth detection load antenna (1 fourth detection load antenna main array 8, 6 fourth detection load antenna sub-arrays 9). The first detection load antenna 4 is large in size and light in weight, and the first frequency band antenna array is arranged on the + X side of the satellite, close to the ground, in combination with the layout space requirements of antennas in other frequency bands; the second detection load antenna 5 is large in size and weight and is arranged on the ground-X side of the satellite, so that the layout space is fully utilized, the height of the mass center of the satellite is reduced, and the mechanical environment of the satellite and other single machines is improved; the third detection load antenna main array 6, the third detection load antenna sub array 7, the fourth detection load antenna main array 8 and the fourth detection load antenna sub array 9 are all distributed by 1 pair of main arrays and 6 pairs of sub arrays according to the requirement of a two-dimensional orthogonal base line, the satellite locally widens to 2600mm and 2100mm on the ground, and the requirement of the longest base line of two frequency bands is met respectively.
The single laser communication load 10 can cover 1/2 sphere space formed by a view field, 6 laser communication loads 10 are configured on the satellite, 3 groups of the laser communication loads correspond to 3 other satellites in a formation respectively, and 2 laser terminals in each group can cover the full view field space. The layout of the laser terminal is mainly restricted and influenced by extra-cabin components such as a detection antenna, a solar array and the like. And selecting the edges of the bottom plate of the satellite platform cabin and the top of the load cabin as laser communication load mounting surfaces to avoid relevant components interfering in the field of view envelope.
The microwave communication load 11 comprises 3 sets of phased array antennas, combined beams can cover a full airspace, and the 3 phased array antennas are uniformly distributed around a Y axis of a satellite in the circumferential direction of the satellite, namely the satellite is positively arranged on the ground (+ Z), and the satellite is obliquely arranged on the sky (-Z) to avoid extra-cabin components such as a detection antenna, a solar array and the like. Every phased array antenna adopts two face battles to arrange, and every phased array antenna can compromise the space of two faces of satellite body 1 promptly, realizes the cover to 1/3 ball domain space. The scanning range of each wavefront beam is satellite reference pitch > +/-60 degrees and azimuth > +/-45 degrees.
The data transmission antenna has 2 pairs, namely a left data transmission antenna 12 and a right data transmission antenna 13 which are folded and symmetrically arranged on the +/-Y side surface of the star body through a pressing and unfolding mechanism respectively, and unfolded around the X axis of the star body to point to the ground (+ Z). In order to realize a large-angle rotation range and avoid the beam range of the detection antenna, the height of the projection of the mounting surface of the data transmission antenna to the ground is 300 mm.
As shown in fig. 4, the thrusters have 16 thrusters, wherein 6 thrusters are provided on ± X surfaces respectively, so as to realize rapid attitude pitching, attitude yawing and orbit control of the satellite, and 2 thrusters are provided on ± Z surfaces respectively, so as to realize rapid attitude rolling of the satellite.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A compact satellite configuration suitable for multi-band detection loads is characterized by comprising a satellite body (1), a double-wing solar cell module (2), a relay antenna (3), a multi-band detection load antenna module, a communication load module, a data transmission antenna module, a measurement and control antenna and a thruster, wherein the double-wing solar cell module is arranged on the satellite body;
the double-wing solar cell module (2), the relay antenna (3), the multi-band detection load antenna module, the communication load module, the data transmission antenna module, the measurement and control antenna and the thruster are all installed on the satellite body (1).
2. The compact satellite configuration applicable to multi-band detection loads according to claim 1, wherein the double-wing solar cell module (2) comprises a left-wing solar cell array (21) and a right-wing solar cell array (22), and the left-wing solar cell array (21) and the right-wing solar cell array (22) are respectively installed on the left side surface and the right side surface of the satellite body (1);
the relay antenna (3) is arranged on the back surface of the satellite body (1), and the multi-band detection load antenna assembly is arranged on the front surface of the satellite body (1);
the communication load assembly is arranged between the left side surface and the right side surface or arranged on the left side surface and/or the right side surface;
the data transmission antenna assembly comprises a left data transmission antenna (12) and a right data transmission antenna (13), and the left data transmission antenna (12) and the right data transmission antenna (13) are respectively and symmetrically arranged on the left side surface and the right side surface of the satellite body (1);
the measurement and control antenna is arranged on the front side and/or the back side of the satellite body (1);
the number of the thrusters is multiple, and the thrusters are arranged on the front surface, the back surface, the upper surface and/or the lower surface of the satellite body (1).
3. The compact satellite configuration for multiband probe loads according to claim 1, characterized in that the satellite body (1) comprises a platform compartment (101), a load compartment (102), a thermal control compartment (103) connected in sequence from bottom to top.
4. The compact satellite configuration for multiband probe loads according to claim 3, characterized in that said thermal controlled capsule (103) employs active and/or passive heat dissipation.
5. The compact satellite configuration for multiband probe loads according to claim 2, wherein the left-wing solar cell array (21), the right-wing solar cell array (22) both comprise 5 substrates;
the left wing solar cell array (21) and the right wing solar cell array (22) are symmetrically arranged on two sides of the satellite body (1), and the left wing solar cell array (21) and the right wing solar cell array (22) can be switched between a folded state and an unfolded state.
6. The compact satellite configuration for multiband probe loads according to claim 1, characterized in that the beam of said relay antenna (3) is capable of dynamically covering 1/2 spherical space;
the relay antenna (3) adopts a one-time folding and unfolding structure, and in a transmitting state, the relay antenna (3) is pressed on the back of the satellite body (1); when the relay antenna operates in an orbit, the relay antenna (3) faces the opposite direction after being unfolded, and the unfolding angle of the unfolding arm is 90 degrees.
7. The compact satellite configuration for multiband detection loads of claim 1, wherein said multiband detection load antenna assembly comprises a 4-band antenna array.
8. The compact satellite configuration for multi-band probe loads according to claim 1, wherein said communication payload package comprises a laser communication payload (10);
the number of the laser communication loads (10) is six and is divided into 3 groups, each group comprises two laser communication loads (10), laser terminals on each group of the two laser communication loads (10) can cover the space of a full view field, and laser terminals on a single laser communication load (10) can cover the 1/2 spherical space formed by the view field.
9. The compact satellite configuration for multiband probe payloads of claim 8, wherein the communication payload assembly further comprises a microwave communication payload (11), the microwave communication payload (11) comprising three phased array antennas, the combined beam of the three phased array antennas enabling full airspace coverage; the three phased array antennas are arranged along the circumferential direction of the axial direction of the left side face and the right side face of the satellite body (1), wherein each phased array antenna can cover 1/3 spherical space.
10. The compact satellite configuration for multi-band probe loads according to claim 1, wherein the number of thrusters is 16, wherein:
6 thrusters are respectively arranged on the upper surface and the lower surface of the satellite body (1) to realize rapid attitude pitching, attitude yawing and orbit control of the satellite; 2 thrusters are respectively arranged on the front surface and the back surface of the satellite body (1) to realize the attitude rolling of the satellite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010753142.0A CN111891388B (en) | 2020-07-30 | 2020-07-30 | Compact satellite configuration suitable for multi-band detection load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010753142.0A CN111891388B (en) | 2020-07-30 | 2020-07-30 | Compact satellite configuration suitable for multi-band detection load |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111891388A true CN111891388A (en) | 2020-11-06 |
| CN111891388B CN111891388B (en) | 2021-08-27 |
Family
ID=73182799
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010753142.0A Active CN111891388B (en) | 2020-07-30 | 2020-07-30 | Compact satellite configuration suitable for multi-band detection load |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111891388B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148228A (en) * | 2021-03-16 | 2021-07-23 | 上海卫星工程研究所 | Passive positioning system suitable for micro-nano satellite |
| CN113212798A (en) * | 2021-04-28 | 2021-08-06 | 中国科学院高能物理研究所 | Design method of load thermal control system for all-day monitoring high-energy telescope |
| CN113277121A (en) * | 2021-06-08 | 2021-08-20 | 中国空间技术研究院 | Constellation deployment-oriented minisatellite configuration and modular assembly method |
| CN113665843A (en) * | 2021-08-30 | 2021-11-19 | 上海卫星工程研究所 | Surround configuration for deep space exploration |
| CN114506474A (en) * | 2022-01-14 | 2022-05-17 | 上海卫星工程研究所 | Satellite layout based on joint detection of multiple types of remote sensing instruments |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105501471A (en) * | 2015-12-16 | 2016-04-20 | 上海卫星工程研究所 | Configuration of satellite loaded with large deployable antenna with double reflecting surfaces |
| CN106477072A (en) * | 2016-11-09 | 2017-03-08 | 上海卫星工程研究所 | Many types of load application satellite configuration |
| CN109018432A (en) * | 2018-06-19 | 2018-12-18 | 上海卫星工程研究所 | The high-precision comprehensive remote sensing satellite of multi-load synergistic observation is laid out |
| US20190039754A1 (en) * | 2017-08-04 | 2019-02-07 | Rocket Lab Usa, Inc. | Satellite deployer door release mechanism |
| CN109850185A (en) * | 2019-02-19 | 2019-06-07 | 上海卫星工程研究所 | Load the satellite structure of deployable antenna and more optical cameras |
| CN109927937A (en) * | 2019-02-20 | 2019-06-25 | 上海卫星工程研究所 | Separate type Solar and Heliospheric Observatory configuration |
-
2020
- 2020-07-30 CN CN202010753142.0A patent/CN111891388B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105501471A (en) * | 2015-12-16 | 2016-04-20 | 上海卫星工程研究所 | Configuration of satellite loaded with large deployable antenna with double reflecting surfaces |
| CN106477072A (en) * | 2016-11-09 | 2017-03-08 | 上海卫星工程研究所 | Many types of load application satellite configuration |
| US20190039754A1 (en) * | 2017-08-04 | 2019-02-07 | Rocket Lab Usa, Inc. | Satellite deployer door release mechanism |
| CN109018432A (en) * | 2018-06-19 | 2018-12-18 | 上海卫星工程研究所 | The high-precision comprehensive remote sensing satellite of multi-load synergistic observation is laid out |
| CN109850185A (en) * | 2019-02-19 | 2019-06-07 | 上海卫星工程研究所 | Load the satellite structure of deployable antenna and more optical cameras |
| CN109927937A (en) * | 2019-02-20 | 2019-06-25 | 上海卫星工程研究所 | Separate type Solar and Heliospheric Observatory configuration |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148228A (en) * | 2021-03-16 | 2021-07-23 | 上海卫星工程研究所 | Passive positioning system suitable for micro-nano satellite |
| CN113212798A (en) * | 2021-04-28 | 2021-08-06 | 中国科学院高能物理研究所 | Design method of load thermal control system for all-day monitoring high-energy telescope |
| CN113277121A (en) * | 2021-06-08 | 2021-08-20 | 中国空间技术研究院 | Constellation deployment-oriented minisatellite configuration and modular assembly method |
| CN113665843A (en) * | 2021-08-30 | 2021-11-19 | 上海卫星工程研究所 | Surround configuration for deep space exploration |
| CN114506474A (en) * | 2022-01-14 | 2022-05-17 | 上海卫星工程研究所 | Satellite layout based on joint detection of multiple types of remote sensing instruments |
| CN114506474B (en) * | 2022-01-14 | 2023-08-18 | 上海卫星工程研究所 | Satellite layout based on multi-type remote sensing instrument joint detection |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111891388B (en) | 2021-08-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111891388B (en) | Compact satellite configuration suitable for multi-band detection load | |
| Gao et al. | Advanced antennas for small satellites | |
| CN101164251B (en) | Deployable phased array antenna for satellite communications | |
| US5386953A (en) | Spacecraft designs for satellite communication system | |
| US9966658B2 (en) | Antennas for small satellites | |
| EP0888967B1 (en) | Spacecraft platforms | |
| JP6419180B2 (en) | Parallel dual launch mechanism | |
| CN106848558B (en) | Solar sailboard conformal antenna of spacecraft | |
| US5833175A (en) | Spacecraft with large east-west dimensions | |
| Akan et al. | Antennas for space applications: A review | |
| JP5414181B2 (en) | Spacecraft adapter with embedded resources and method of forming the same | |
| Fikes et al. | The Caltech space solar power project: Design, progress, and future direction | |
| CN219017902U (en) | Satellite-borne radar antenna and satellite | |
| US20230192325A1 (en) | Dispenserless multi-satellite launch configuration with simple adapter interface | |
| CN114506474B (en) | Satellite layout based on multi-type remote sensing instrument joint detection | |
| US11912440B2 (en) | Partially flexible solar array structure | |
| Pearson et al. | Thin film antenna development and optimization | |
| CN112298607A (en) | Modularized satellite platform for realizing high agility maneuvering capability | |
| You et al. | Design Case of Typical Spacecraft Antenna System | |
| CN116632508A (en) | Satellite configuration and switching method of multi-band planar phased array antenna | |
| CN116845531A (en) | Satellite configuration and switching method of dual-band planar phased array antenna | |
| US20230049753A1 (en) | Retractable z-fold flexible blanket solar array | |
| CN115158699A (en) | Satellite structure for double-satellite parallel launching and satellite carrier rocket | |
| US20230369737A1 (en) | Antenna reflector spacecraft temperature regulation during orbit raising | |
| US20230062667A1 (en) | Multi-satellite deployable dispenser |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |