CN112817065B - Novel earth atmosphere light inhibition system and method - Google Patents
Novel earth atmosphere light inhibition system and method Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01W—METEOROLOGY
- G01W1/00—Meteorology
- G01W1/08—Adaptations of balloons, missiles, or aircraft for meteorological purposes; Radiosondes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/21—Interference related issues ; Issues related to cross-correlation, spoofing or other methods of denial of service
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
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Abstract
The application relates to a novel earth atmosphere light inhibition method, a system and a method, comprising the following steps: a satellite, wherein the orbit selects a morning sun synchronous orbit and keeps a posture oriented to the ground; the optical observation module is arranged on the satellite and is perpendicular to the positive Z axis of the body of the satellite; the baffle is arranged between the optical observation module and the ground plane during the operation of the satellite, wherein a satellite attitude yaw maneuver guiding law is obtained according to the operation orbit, the operation speed and the latitude of the staring required by the satellite, and an attitude maneuver rule model of the satellite is created; the satellite operates according to a gesture maneuver rule model to realize traversal observation of the latitude needing staring; wherein, the included angle between the baffle plane and the visual axis of the optical observation module is 0-10 degrees, and the ratio of the area of the baffle to the caliber area of the optical observation module is 2:1.
Description
Technical Field
The application relates to the field of aerospace star detection, in particular to a novel earth atmosphere light suppression system and method.
Background
For the field of aerospace star sky detection, the space optical observation system is adopted for detection, and the space optical observation system has the advantages of flexibility, light observation range, long running time, short data updating period, high observation precision and the like.
At present, the main means for inhibiting the earth atmosphere light by a synchronous belt optical observation satellite are as follows: firstly, extinction measures such as diaphragms, inner/outer light shields, light blocking rings and the like are utilized to inhibit stray light entering the system. For example: the earth-atmosphere light suppression means adopted by the U.S. space-based visible telescope SBV and the Canadian space-based space target observation satellite Sapphire comprise: 1) A vertical shaft tri-trans optical system is adopted; 2) Designing an aperture diaphragm and a field diaphragm; 3) The main mirror surface is subjected to smoothing treatment; 4) A special design of the shade, etc. Secondly, during the task, according to the ground earth gas light influence calculation priori data, the earth gas light influence arc section is selected to be powered off and the non-influence section is selected to be powered on for observation.
The traditional method can improve the earth-atmosphere light inhibition capability of the space observation camera to an integral degree, but has high cost and great technical difficulty, and especially has huge technical difficulty and cost for the parasitic light inhibition of the ultra-high sensitivity space camera. In addition, because the arc section influenced by the earth air light changes with seasons, the observation task of the observation satellite is complex in planning, and the satellite operation and control management workload is increased.
Therefore, it is necessary to provide a novel earth-atmosphere light suppression method and system for a synchronous belt target optical observation satellite to solve the above problems.
Disclosure of Invention
The present invention provides a geospatial light suppression system for a synchronous belt target optical observation satellite, which solves the above technical problems in the prior art. Specifically, the system of the present application includes: a satellite, wherein the orbit selects a morning sun synchronous orbit and keeps a posture oriented to the ground; the optical observation module is arranged on the satellite and is perpendicular to the main shaft of the satellite; the baffle is arranged on the optical observation module, and is arranged between the optical observation module and the ground plane during the operation of the satellite, wherein the satellite operates according to a gesture maneuver rule model so as to realize traversal observation of the latitude needing to be stared. The technical scheme of the application can realize the suppression of the earth atmosphere light only through a simple structural design, and is simple to operate and cost-saving.
The application also aims to provide a method for suppressing the earth-atmosphere light of the synchronous belt target optical observation satellite.
In order to achieve the above object, the present application provides the following technical solutions.
In a first aspect, the present application provides an earth-light suppression system for a synchronous belt target optical observation satellite, the system comprising:
a satellite, wherein the orbit selects a morning sun synchronous orbit and keeps a posture oriented to the ground;
the optical observation module is arranged on the satellite and is perpendicular to the positive Z axis of the body of the satellite; and
a baffle mounted to the optical observation module, the baffle disposed between the optical observation module and a ground plane during operation of the satellite,
obtaining a satellite attitude yaw maneuver guidance law according to the running orbit, running speed and the latitude of the staring, and creating an attitude maneuver rule model of the satellite;
the satellite operates according to a gesture maneuver rule model to realize traversal observation of the latitude needing staring;
the attitude maneuver rule model is shown in a formula (1):
wherein:
the above-mentioned maleIn the middle of
The position and the speed of the satellite are respectively, θ is the latitude of staring, and φ is the yaw maneuver guiding law of the satellite posture.
In one implementation of the first aspect, the main axis of the satellite remains pointed toward the earth center.
In one implementation of the first aspect, the optical observation module includes an observation camera, and the baffle is fixedly or rotatably coupled to a lens of the observation camera.
In one embodiment of the first aspect, an angle between a normal to the baffle plane and a viewing axis of the optical observation module is between 0 ° and 10 °.
In one embodiment of the first aspect, the baffle plane and the optical viewing module viewing axis are parallel.
In one embodiment of the first aspect, the shape of the baffle is selected from rectangular, circular, trapezoidal or irregular, the material of the baffle is selected from titanium alloy, and SB-3 black paint is sprayed on the surface.
In one embodiment of the first aspect, a ratio of an area of the baffle to an aperture area of the optical observation module is 2:1.
in one embodiment of the first aspect, the latitude of the desired gaze ranges between 0 ° -30 °.
In a second aspect of the present application, the present application provides a method for suppressing earth-light of a synchronous belt target optical observation satellite, the method comprising:
(1) Installing a baffle on an optical observation module of a satellite, wherein the baffle is used for reducing the influence of earth-gas light from the earth on the optical observation module;
(2) Setting the satellite orbit to select a morning sun synchronous orbit, and keeping the attitude to be oriented to the ground; and
(3) According to the running orbit, running speed and latitude of the staring, creating a gesture maneuver rule model of the satellite to realize traversal observation of the latitude of the staring, wherein the gesture maneuver rule model is shown in a formula (1):
wherein:
in the above formula
The position and the speed of the satellite are respectively, θ is the latitude of staring, and φ is the yaw maneuver guiding law of the satellite posture.
In one embodiment of the second aspect, the satellite is used to traverse satellites in geostationary orbits (The geostationary orbit, GEO) ranging from 0 ° -30 ° in latitude of gaze.
Compared with the prior art, the device has the beneficial effects that (1) the device can realize a good inhibiting effect on the ground gas light only through a simple structural design, is simple to operate and saves cost; (2) The on-off time is not required to be calculated according to the influence of the earth gas light, so that the satellite operation control management workload caused by the influence of the earth gas light is greatly reduced; (3) The method and the device can adjust the satellite running orbit according to the required staring latitude, so that almost the whole orbit of the satellite can execute the synchronous belt observation task, and the staring traversing observation efficiency of the satellite synchronous belt is improved.
Drawings
The present application may be better understood by describing embodiments thereof in conjunction with the accompanying drawings, in which:
FIG. 1 is a schematic view of satellite operation according to one embodiment of the present application;
fig. 2 is a schematic structural view of a satellite optical observation module mounted with a baffle according to an embodiment of the present application.
Detailed Description
The present application relates to an earth-atmosphere suppression system of a synchronous belt target optical observation satellite, and an earth-atmosphere suppression method of a synchronous belt target optical observation satellite.
As used herein, the terms "module," "system" and the like are intended to include a computer-related entity, either hardware, firmware, a combination of hardware and software, or software in execution. For example, a module may be, but is not limited to: a process running on a processor, an object, an executable, a thread of execution, a program, and/or a computer. By way of example, both an application running on a computing device and the computing device can be a module. One or more modules may be located in one process and/or thread of execution.
The terms "comprises," "comprising," "including," and their derivatives do not exclude the presence of any other component, step or procedure, and are not related to whether or not such other component, step or procedure is disclosed in the present application. For the avoidance of any doubt, all use of the terms "comprising," "including," or "having" herein, unless expressly stated otherwise, may include any additional additive, adjuvant, or compound. Rather, the term "consisting essentially of … …" excludes any other component, step or process from the scope of any of the terms recited below, except as necessary for operability. The term "consisting of … …" does not include any components, steps or processes not specifically described or listed. The term "or" refers to the listed individual members or any combination thereof unless explicitly stated otherwise.
Definition of terms
As used herein, the term "earth's atmosphere" refers to various types of radiation released by the earth-atmosphere system into the space.
As used herein, the term "solar synchronous orbit" refers to the orbit plane of a satellite and the sun always remain in a relatively fixed orientation, with the inclination of the orbit (the angle between the orbit plane and the equatorial plane) approaching 90 degrees, and the satellite will pass near the poles, thus also known as the near-polar solar synchronous satellite orbit.
As used herein, the term "geostationary orbit" refers to a perfectly circular geosynchronous orbit of a satellite or satellite perpendicular to the earth's equator. The geostationary orbit belongs to one type of geosynchronous orbit.
First, a coordinate system is set as shown in fig. 1:
A.J2000 inertial coordinate System
The origin of the coordinate system is the earth centroid. The x-axis points to the spring point at time 1, 12:00:00 of 2000 and the z-axis is along the earth rotation axis at that time, and the y-axis is orthogonal to the right hand of the x-axis and the z-axis.
B. Satellite body coordinate system
The origin of the coordinate system is the satellite centroid. The z '(principal axis) is directed from the center of mass of the satellite to the earth center and the y' axis (the optic viewing axis of the optical viewing module) to the right-front direction of the satellite's body, the x' axis being orthogonal to the right hand of the y ', z' axis. The satellite star coordinate system is fully coincident with the orbital coordinate system while the satellite maintains a strict earth-directed attitude with the camera axis pointing toward the earth center.
The application provides a method for suppressing earth atmosphere light of a synchronous belt target optical observation satellite, which comprises the following steps:
(1) Installing a baffle on an optical observation module of a satellite, wherein the baffle is used for reducing the influence of earth-gas light from the earth on the optical observation module;
(2) Setting the satellite orbit to select a morning sun synchronous orbit, and keeping the attitude to be oriented to the ground; and
(3) According to the running orbit, running speed and latitude of the staring, creating a gesture maneuver rule model of the satellite to realize traversal observation of the latitude of the staring, wherein the gesture maneuver rule model is shown in a formula (1):
wherein:
in the above formula
The position and the speed of the satellite are respectively, θ is the latitude of staring, and φ is the yaw maneuver guiding law of the satellite posture.
Fig. 2 is a schematic structural view of a satellite optical observation module 100 with a baffle 200 installed according to an embodiment of the present application, and as shown in fig. 2, a baffle 200 is designed and installed for the optical observation module 100 in a ground design development stage of the optical observation module 100, for reducing an influence of earth-gas light from the earth on the optical observation module.
In one embodiment, the angle between the plane of the baffle 200 and the viewing axis of the optical viewing module 100 is between 150 ° and 180 °. In a specific embodiment, the plane of baffle 200 is parallel to the viewing axis of optical viewing module 100.
In one embodiment, the optical viewing module 100 includes a viewing camera, and the baffle 200 is fixedly or rotatably coupled to the lens 110 of the viewing camera by a bracket 300.
In one embodiment, the shape of the baffle 200 is selected from rectangular, circular, trapezoidal, or any shape that can function to block the light of the earth.
In one embodiment, to minimize the effect of earth's light from the earth on the optical observation module 100 without adding satellite weight by using an oversized baffle 200, the ratio of the baffle area to the optical observation module aperture area is 2:1.
in the satellite installation integration stage, the optical observation module 100 is installed on the satellite shown in fig. 1 and is perpendicular to the main axis z ' of the satellite, that is, the visual axis of the optical observation module 100 is parallel to the y ' axis of the satellite, and the baffle 200 is perpendicular to the z ' axis of the satellite.
During satellite operation, the satellite orbit selects the morning and evening sun synchronous orbit, the attitude remains oriented to ground, and a baffle 200 is disposed between the optical observation module 100 and ground level. In some embodiments, the major axis of the satellite is oriented toward the earth center and the baffle 200 is parallel to the ground plane.
The device can achieve a good suppression effect on the earth atmosphere light only through a simple structural design, is simple to operate and saves cost. The satellite attitude keeps the earth orientation (the main shaft always points to the earth center), so that the baffle is always blocked between the ground plane and the optical observation module, the influence of earth gas light on the optical observation module is reduced, the on-off time is not required to be calculated according to the earth gas light influence, and the satellite operation control management workload caused by the earth gas light influence is greatly reduced.
During the execution of a mission, as shown in fig. 1, satellites are required to orbit (The geostationary orbit, GEO) on earth with latitudes ranging between 0 ° -30 °. The satellite operates according to a gesture maneuver rule model to realize traversal observation of the latitude needing to be stared, and the gesture maneuver rule model is shown in a formula (1):
wherein:
in the above formula
The position and the speed of the satellite are respectively, θ is the latitude of staring, and φ is the yaw maneuver guiding law of the satellite posture.
The attitude maneuver rule model can adjust the satellite running orbit according to the required staring latitude, so that almost the whole orbit of the satellite can execute the synchronous belt observation task, and the staring traversing observation efficiency of the satellite synchronous belt is improved. Compared with the prior art, the satellite only changes the angle of the main shaft (z ') and does not change the x ' and y ' axes, so that the data volume and the calculated amount of the attitude maneuver rule model are greatly reduced, the satellite operation and control management workload is reduced, and the cost is reduced.
The embodiments are described above in order to facilitate the understanding and application of the present application by those of ordinary skill in the art. It will be apparent to those skilled in the art that various modifications can be made to these embodiments and that the general principles described herein may be applied to other embodiments without the use of inventive faculty. Accordingly, the present application is not limited to the embodiments herein, and those skilled in the art, based on the present disclosure, may make improvements and modifications without departing from the scope and spirit of the present application.
Claims (5)
1. A novel earth-boring light suppression system, the system comprising:
a satellite, wherein the orbit selects a morning sun synchronous orbit and keeps a posture oriented to the ground;
the optical observation module is arranged on the satellite and is perpendicular to the positive Z axis of the body of the satellite; and
a baffle mounted to the optical observation module, the baffle disposed between the optical observation module and a ground plane during operation of the satellite,
obtaining a satellite attitude yaw maneuver guidance law according to the running orbit, running speed and the latitude of the staring, and creating an attitude maneuver rule model of the satellite;
the satellite operates according to a gesture maneuver rule model to realize traversal observation of the latitude needing staring;
wherein, the included angle between the baffle plane and the visual axis of the optical observation module is 0-10 degrees, and the ratio of the area of the baffle to the caliber area of the optical observation module is 2:1, a step of;
the main shaft of the satellite keeps pointing to the earth center;
the attitude maneuver rule model is shown in a formula (1):
wherein:
in the above formula
The position and the speed of the satellite are respectively, θ is the latitude of staring, and φ is the yaw maneuver guiding law of the satellite posture;
wherein the optical viewing module comprises a viewing camera, the baffle is fixedly or rotatably coupled to a lens of the viewing camera, and wherein the baffle plane and the optical viewing module viewing axis are parallel.
2. The system of claim 1, wherein the shape of the baffle is selected from rectangular, circular, trapezoidal, or irregular, the material of the baffle is selected from titanium alloy, and SB-3 black paint is sprayed on the surface.
3. The system of claim 1, wherein the latitude of the desired gaze ranges from 0 ° to ±30°.
4. A method of earth-gas-light suppression using the system of any one of claims 1-3, the method comprising:
(1) Installing a baffle on an optical observation module of a satellite, wherein the baffle is used for reducing the influence of earth-gas light from the earth on the optical observation module;
(2) Setting the satellite orbit to select a morning sun synchronous orbit, and keeping the attitude to be oriented to the ground; and
(3) And creating a gesture maneuver rule model of the satellite according to the running orbit, the running speed and the latitude needing to be stared so as to realize traversal observation of the latitude needing to be stared.
5. The method of claim 4, wherein the satellite is used to traverse satellites in geostationary orbits ranging from 0 ° to ±30° in latitude.
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| CN201810584344.XA CN109001762B (en) | 2018-06-08 | 2018-06-08 | Ground gas light inhibition method and system for synchronous belt target optical observation satellite |
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| CN111368455B (en) * | 2020-03-18 | 2023-11-28 | 中国人民解放军战略支援部队航天工程大学 | Design method of solar follow-up GEO target optical observation orbit |
| CN111366986B (en) * | 2020-03-24 | 2022-08-26 | 中国科学院微小卫星创新研究院 | Space debris observation system and method |
| CN115688385B (en) * | 2022-10-11 | 2023-04-07 | 中国人民解放军63921部队 | Method for constructing observation model of star sensor of single observation platform |
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