CN113609708B - Mars global remote sensing orbit design method and system based on near fire drift - Google Patents
Mars global remote sensing orbit design method and system based on near fire drift Download PDFInfo
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Abstract
The invention provides a Mars global remote sensing orbit design method and system based on near fire point drift, which relate to the technical field of orbit design of deep space exploration spacecraft and comprise the following steps: step S1: determining the upper limit of the height of the near fire point, wherein the height of the near fire point at the end of the service life is larger than the atmospheric height of fire gas; step S2: calculating the track inclination angle adjusting range; step S3: calculating the change rate of the amplitude angle of the near fire point; step S4: calculating the right ascent point and the left ascent point; step S5: analyzing and calculating the semi-long axis parameters of the track by the parameters of the amplitude angle change rate and the right ascent and intersection point and the right ascent and descent change rate of the near fire point required by the remote sensing detection task. The invention can meet the requirement of low-rail-to-target imaging high-rail-to-ground communication; the emission weight of the deep space detector is saved; and the engineering task requirements of global coverage, full-range coverage detection of different track heights and detailed detection of key areas can be met.
Description
Technical Field
The invention relates to the technical field of orbit design of deep space exploration spacecraft, in particular to a Mars global remote sensing orbit design method and system based on near fire drift.
Background
The remote sensing detection of the deep space detector on the extraterrestrial planet is an important scientific task in the field of deep space detection. Compared with the earth remote sensing satellite which usually works in a near-earth circular orbit or a static orbit, the deep space detector is limited by weight limitation, a large amount of fuel is consumed when the satellite moves to a lower circular orbit, the satellite cannot move to the circular orbit with low height, and in addition, in order to cover the detection requirements of different orbit heights of a target celestial body, remote sensing detection tasks are usually carried out on a large elliptical orbit. And carrying out fire observation on the near fire points of the detectors on the task arrangement, and carrying out ground communication on the far fire points. In order to ensure enough observation arc sections and complete coverage of all regions of the world, corresponding track design is required to be carried out by combining camera imaging parameters, and constraint conditions such as the illumination angle requirement of the points below the satellite, the width of the camera and the like are met.
The invention patent with publication number of CN103198187A discloses a track design method of a deep space probe based on differential correction, which mainly comprises the following steps: calculating an initial value by a genetic algorithm or a track parameter of a deep space probe determined by a Port Chop Plots method; carrying out track numerical integration operation under an accurate dynamics model according to the control parameter as an initial value to obtain a terminal parameter value; comparing the calculated parameter value with a standard parameter to obtain a parameter deviation value, thereby obtaining a new control parameter; carrying out orbit integral operation on the dynamic model again by utilizing the new control parameters to obtain new terminal parameter value deviation; repeating the above process until the terminal parameters meet the precision requirement. The method needs to provide corresponding initial values of the orbit, and finally achieves the minimum orbit correction control quantity, minimum fuel consumption and the like through orbit dynamics iteration, and does not consider the constraint of load imaging under the condition of remote sensing detection scientific tasks.
The invention patent with publication number of CN111338367A discloses a method for determining an intermediate track by controlling eccentricity freezing common-track double pulses, which is implemented according to the following steps: step 1, determining a first orbit change middle moment front control satellite orbit; step 2, calculating the satellite position and speed when the orbit is not changed at the middle moment of the first orbit; step 3, determining a satellite orbit after time control in the middle of the second orbit change; step 4, confirming the control type, the control quantity and the control phase of the double pulse track; step 5, calculating the change of the eccentricity of the track, the change of the horizontal half long axis of the track, the actual speed increment of the first track control and the actual speed increment of the second track control respectively; step 6, calculating a satellite speed vector after the first orbit transfer middle time control; and 7, determining a double-pulse control middle arc section track. The method realizes the accurate track position in the middle of 2 track changes in track determination recursion, but cannot be applied to the initial design of the track.
The invention patent with publication number of CN102923324B discloses a low-energy planetary escape orbit design method based on invariant manifold and gravity assistance, which is suitable for low-energy deep space exploration task orbit design by utilizing dynamic balance points and belongs to the technical field of spacecraft orbit maneuver. The method is based on segment matching of near-arch point poincare mapping, and a track state set of the invariant manifold at the near-arch point is obtained by introducing the near-arch point poincare mapping; and then, according to the escape hyperbolic overspeed requirement required by realizing the inter-planetary transfer, calculating the maneuvering pulse to be applied to each branch of the constant manifold in the orbit state set by adopting a numerical iteration method, and determining the constant manifold branch and the required maneuvering pulse corresponding to the most fuel-saving escape through maneuvering pulse size comparison.
In the prior document Yang Weilian, in the research of the frozen orbit of a Mars satellite (see spacecraft engineering, 5 months in 2011, volume 20, 3 rd phase and page numbers 20-24), the frozen orbit characteristic of the Mars satellite is correspondingly researched on the basis of researching the frozen orbit characteristic of the lunar satellite. The difference of the frozen orbits of the earth, the moon and the Mars is compared, the minimum order number required by calculation under the orbit freezing condition and the Mars orbit eccentricity characteristic are given through simulation, and the conclusion that the amplitude angle of the near-place of the Mars frozen orbit is opposite to the earth is provided. The research indicates design thought and calculation constraint conditions for Mars orbit design, but in the field of deep space remote sensing detection, the orbit needs to meet the task conditions of global coverage, point revisit under the satellite and the like, and the frozen orbit is suitable for the requirements of relay communication tasks and cannot meet the requirements of remote sensing detection.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a Mars global remote sensing track design method and system based on near fire drift.
According to the Mars global remote sensing track design method and system based on near fire point drift, the scheme is as follows:
in a first aspect, a spark global remote sensing orbit design method based on near fire drift is provided, the method comprising:
step S1: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images fire, and enabling the height of the near fire point at the end of the service life to be larger than the atmospheric height of fire gas according to the descending rate of the track height in the service life;
step S2: calculating the track inclination angle adjusting range according to the field angle of view of the detector camera;
step S3: calculating to obtain the change rate of the amplitude angle of the near fire point according to the remote sensing task period;
step S4: calculating to obtain the right ascent point and the left ascent point variation rate according to the target solar altitude constraint of the imaging period and the remote sensing detection task period;
step S5: analyzing and calculating the semi-long axis parameters of the track by the parameters of the amplitude angle change rate and the right ascent and intersection point and the right ascent and descent change rate of the near fire point required by the remote sensing detection task.
Preferably, determining the near fire height in the step S1 includes: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images the fire; according to the track height descending rate in the service life period, the height of a near fire point in the service life end period is larger than the height of a fire atmosphere:
wherein h is p The height is the initial track near the fire point;
h cmax a working height constraint for the load camera;
is the height descending rate of the near fire point;
t is the working life of the Mars detector;
h atmo is the atmospheric height of Mars.
Preferably, the determining the track inclination angle in step S2 includes:
the method meets the requirements of Mars global area coverage detection, the track inclination angle is required to be about 90 degrees, and meanwhile, the inclination angle deviation range is calculated according to the field angle of view of a detector camera:
wherein v is the field angle of the camera; i is the track inclination.
Preferably, the determining the change rate of the amplitude angle of the near fire point in the step S3 includes:
according to the remote sensing detection task period, the near fire point drift amount is larger than 180 degrees in the task period, so that coverage of different latitude areas of the Mars is realized, and the calculation steps are as follows:
wherein,indicating the change rate of the amplitude angle of the near fire point; t is the service life of the remote sensing detection task of the detector.
Preferably, determining the rate of change of the right ascertainment point in the step S4 includes:
according to the target solar altitude constraint of the imaging period and the remote sensing detection task period, the precession direction of the constrained track surface is consistent with the revolution direction of the Mars, and the solar altitude of the position of the satellite lower point corresponding to the near fire point in the task period is greater than the load imaging condition constraint, and the calculation step comprises the following steps:
wherein,the right ascent point and the right ascent point are represented by the right ascent point and the right ascent point;
η 1 、η 2 solar altitude angles of the positions of the points under the satellite corresponding to the near fire points at the initial stage and the final stage of the task respectively;
t is the service life of the remote sensing detection task of the detector;
the average angular velocity of the mars revolution.
Preferably, the determining the track semi-major axis parameter in step S5 includes:
the semi-long axis parameter is analyzed and calculated by the parameter of the change rate of the amplitude angle of the near fire point and the change rate of the right ascent and intersection point required by a remote sensing detection task, and the calculation step comprises the following steps:
wherein,the right ascent point and the right ascent point are represented by the right ascent point and the right ascent point;
indicating the change rate of the amplitude angle of the near fire point;
representing the rate of change of the angle of the point of closest approach;
a 0 semi-major axis parameters for the solution of demand;
μ represents the parameter of the gravity field of the Mars center;
J 2 representing the perturbation term of the Mars gravitational field;
R e is a semi-long axis of a Mars sphere;
i 0 is a track inclination angle parameter;
e 0 is the track eccentricity.
In a second aspect, there is provided a spark global remote sensing orbit system based on near fire drift, the system comprising:
module M1: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images fire, and enabling the height of the near fire point at the end of the service life to be larger than the atmospheric height of fire gas according to the descending rate of the track height in the service life;
module M2: calculating the track inclination angle adjusting range according to the field angle of view of the detector camera;
module M3: calculating to obtain the change rate of the amplitude angle of the near fire point according to the remote sensing task period;
module M4: calculating to obtain the right ascent point and the left ascent point variation rate according to the target solar altitude constraint of the imaging period and the remote sensing detection task period;
module M5: analyzing and calculating the semi-long axis parameters of the track by the parameters of the amplitude angle change rate and the right ascent and intersection point and the right ascent and descent change rate of the near fire point required by the remote sensing detection task.
Preferably, determining the near fire height in the module M1 includes: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images the fire; according to the track height descending rate in the service life period, the height of a near fire point in the service life end period is larger than the height of a fire atmosphere:
wherein h is p The height is the initial track near the fire point;
h cmax a working height constraint for the load camera;
is the height descending rate of the near fire point;
t is the working life of the Mars detector;
h atmo is the Mars atmosphereHeight of the steel plate.
Preferably, the determining the track inclination angle in the module M2 includes:
the method meets the requirements of Mars global area coverage detection, the track inclination angle is required to be about 90 degrees, and meanwhile, the inclination angle deviation range is calculated according to the field angle of view of a detector camera:
wherein v is the field angle of the camera; i is the track inclination.
Preferably, determining the rate of change of the amplitude angle of the near fire point in the module M3 includes:
according to the remote sensing detection task period, the near fire point drift amount is larger than 180 degrees in the task period, so that coverage of different latitude areas of the Mars is realized, and the calculation steps are as follows:
wherein,indicating the change rate of the amplitude angle of the near fire point; t is the service life of the remote sensing detection task of the detector.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention meets the requirement of low-orbit imaging high-orbit ground communication on the target at the same time by using the remote sensing detection of the large elliptical orbit;
2. the large elliptic orbit of the invention consumes less fuel and saves the emission weight of the deep space detector;
3. the invention meets the engineering task requirements of global coverage, full-range coverage detection of different track heights and detailed detection of key areas.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a flow chart of steps of a method for designing a Mars ellipse remote sensing track based on near fire point drift.
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 present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
The embodiment of the invention provides a Mars global remote sensing orbit design method based on near fire drift, which specifically comprises the following steps of:
step S1: determining the upper limit of the height of the near fire point according to the maximum height requirement of the load when the load images the fire, and enabling the height of the near fire point at the end of the service life to be still larger than the atmospheric height of the fire gas according to the descending rate of the track height in the service life;
wherein h is p The height is the initial track near the fire point; h is a cmax A working height constraint for the load camera;is the height descending rate of the near fire point; t is the working life of the Mars detector; h is a atmo Is the atmospheric height of Mars.
Step S2: determining an orbit inclination angle range, meeting the requirement of Mars global area coverage detection, wherein the orbit inclination angle is required to be about 90 degrees, and simultaneously calculating an inclination angle deviation range according to the field angle of a detector camera:
wherein v is the field angle of the camera; i is the track inclination.
Step S3: determining the change rate of the amplitude angle of the near fire point, calculating the semi-long axis of the track, calculating according to the remote sensing detection task period, wherein the drift amount of the near fire point is larger than 180 degrees in the task period, and realizing the coverage of the different latitude areas of the Mars, wherein the calculating steps are as follows:
wherein,indicating the change rate of the amplitude angle of the near fire point; t is the service life of the remote sensing detection task of the detector.
Step S4: determining the right ascent point and the left ascent point, wherein the right ascent point and the left ascent point are used for track semi-major axis calculation, the right ascent point and the left ascent point are calculated according to the target solar altitude constraint of an imaging period and a remote sensing detection task period, the precession direction of a constraint track surface is consistent with the revolving direction of a Mars, and the solar altitude of a position of a satellite lower point corresponding to a near fire point in the task period is larger than the load imaging condition constraint, and the calculation step comprises the following steps:
wherein,the right ascent point and the right ascent point are represented by the right ascent point and the right ascent point; η (eta) 1 、η 2 Solar altitude angles of the positions of the points under the satellite corresponding to the near fire points at the initial stage and the final stage of the task respectively; t is the service life of the remote sensing detection task of the detector; />The average angular velocity of the mars revolution.
Step S5: determining semi-long axis parameters, analyzing and calculating the track semi-long axis parameters by using the near fire point amplitude angle change rate and the rising intersection point right ascent and trafficking change rate parameters required by a remote sensing detection task, and calculating the track semi-long axis parameters:
wherein,the right ascent point and the right ascent point are represented by the right ascent point and the right ascent point; />Indicating the change rate of the amplitude angle of the near fire point; />Representing the rate of change of the angle of the point of closest approach; a, a 0 Semi-major axis parameters for the solution of demand; μ represents the parameter of the gravity field of the Mars center; j (J) 2 Representing the perturbation term of the Mars gravitational field; r is R e Is a semi-long axis of a Mars sphere; i.e 0 Is a track inclination angle parameter; e, e 0 Is the track eccentricity.
The invention also provides a Mars global remote sensing track system based on near fire drift, which specifically comprises:
module M1: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images fire, and enabling the height of the near fire point at the end of the service life to be larger than the atmospheric height of fire gas according to the descending rate of the track height in the service life;
module M2: calculating the track inclination angle adjusting range according to the field angle of view of the detector camera;
module M3: calculating to obtain the change rate of the amplitude angle of the near fire point according to the remote sensing task period;
module M4: calculating to obtain the right ascent point and the left ascent point variation rate according to the target solar altitude constraint of the imaging period and the remote sensing detection task period;
module M5: analyzing and calculating the semi-long axis parameters of the track by the parameters of the amplitude angle change rate and the right ascent and intersection point and the right ascent and descent change rate of the near fire point required by the remote sensing detection task.
Determining the height of a near fire point in a module M1, and determining the upper limit of the height of the near fire point according to the maximum height requirement when the load images fire; according to the track height descending rate in the service life period, the height of a near fire point in the service life end period is larger than the height of a fire atmosphere:
wherein h is p The height is the initial track near the fire point; h is a cmax A working height constraint for the load camera;is the height descending rate of the near fire point; t is the working life of the Mars detector; h is a atmo Is the atmospheric height of Mars.
Determining an orbit inclination angle in a module M2, meeting the requirement of Mars global area coverage detection, wherein the orbit inclination angle is required to be about 90 degrees, and simultaneously calculating an inclination angle deviation range according to the field angle of a camera of the detector:
wherein v is the field angle of the camera; i is the track inclination.
Determining the amplitude angle change rate of the near fire point in a module M3, calculating according to the remote sensing detection task period, wherein the drift amount of the near fire point in the task period is larger than 180 degrees, and realizing the coverage of different latitude areas of the Mars, wherein the calculating steps are as follows:
wherein,indicating the change rate of the amplitude angle of the near fire point; t is the service life of the remote sensing detection task of the detector.
The embodiment of the invention provides a Mars global remote sensing orbit design method and system based on near fire drift, which are based on the overall input of a Mars detector orbit, comprise the working life, regression period and the constraint on the illumination angle of the lower point of a Mars imager, consider the influence of a Mars J2 perturbation item, utilize the characteristic of large elliptic orbit arch line precession, obtain the near fire amplitude angle change rate and the ascending intersection point right-angle change rate according to task constraint, further obtain the orbit semi-major axis analysis result, and enable the detector to finish the coverage of Mars global remote sensing detection in the life cycle.
Those skilled in the art will appreciate that the invention provides a system and its individual devices, modules, units, etc. that can be implemented entirely by logic programming of method steps, in addition to being implemented as pure computer readable program code, in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers, etc. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units for realizing various functions included in the system can also be regarded as structures in the hardware component; means, modules, and units for implementing the various functions may also be considered as either software modules for implementing the methods or structures within hardware components.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (6)
1. A Mars global remote sensing orbit design method based on near fire drift is characterized by comprising the following steps:
step S1: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images fire, and enabling the height of the near fire point at the end of the service life to be larger than the atmospheric height of fire gas according to the descending rate of the track height in the service life;
step S2: calculating the track inclination angle adjusting range according to the field angle of view of the detector camera;
step S3: calculating to obtain the change rate of the amplitude angle of the near fire point according to the remote sensing task period;
step S4: calculating to obtain the right ascent point and the left ascent point variation rate according to the target solar altitude constraint of the imaging period and the remote sensing detection task period;
step S5: analyzing and calculating semi-long axis parameters of the track by using parameters of the amplitude angle change rate and the right ascent and intersection point and the right ascent and descent change rate of the near fire point required by a remote sensing detection task;
the determining the height of the near fire point in the step S1 includes: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images the fire; according to the track height descending rate in the service life period, the height of a near fire point in the service life end period is larger than the height of a fire atmosphere:
wherein,the height is the initial track near the fire point;
a working height constraint for the load camera;
is the height descending rate of the near fire point;
the service life of the spark detector is prolonged;
is the atmospheric height of Mars;
the track inclination determination in step S2 includes:
the method meets the requirements of Mars global area coverage detection, the track inclination angle is required to be about 90 degrees, and meanwhile, the inclination angle deviation range is calculated according to the field angle of view of a detector camera:
wherein,the field angle of the view of the camera; />Is the track inclination angle.
2. The method for designing global remote sensing orbits of sparks based on near fire drift of claim 1, wherein determining the near fire amplitude angle change rate in step S3 includes:
according to the remote sensing detection task period, the near fire point drift amount is larger than 180 degrees in the task period, so that coverage of different latitude areas of the Mars is realized, and the calculation steps are as follows:
wherein,indicating the change rate of the amplitude angle of the near fire point; />The service life of the task is detected for the remote sensing of the detector.
3. The method for designing global remote sensing orbits of Mars based on near fire drift of claim 1, wherein determining the rate of change of the intersection right ascertainment in step S4 comprises:
according to the target solar altitude constraint of the imaging period and the remote sensing detection task period, the precession direction of the constrained track surface is consistent with the revolution direction of the Mars, and the solar altitude of the position of the satellite lower point corresponding to the near fire point in the task period is greater than the load imaging condition constraint, and the calculation step comprises the following steps:
wherein,the right ascent point and the right ascent point are represented by the right ascent point and the right ascent point;
solar altitude angles of the positions of the points under the satellite corresponding to the near fire points at the initial stage and the final stage of the task respectively;
the service life of the task is detected for the remote sensing of the detector;
the average angular velocity of the mars revolution.
4. The method for designing a global remote sensing orbit of a Mars based on near fire drift according to claim 1, wherein determining the semi-major axis parameters of the orbit in step S5 comprises:
the semi-long axis parameter is analyzed and calculated by the parameter of the change rate of the amplitude angle of the near fire point and the change rate of the right ascent and intersection point required by a remote sensing detection task, and the calculation step comprises the following steps:
wherein,the right ascent point and the right ascent point are represented by the right ascent point and the right ascent point;
indicating the change rate of the amplitude angle of the near fire point;
representing the rate of change of the angle of the point of closest approach;
semi-major axis parameters for the solution of demand;
representing the parameters of a gravity field of a Mars center;
representing the perturbation term of the Mars gravitational field;
is a semi-long axis of a Mars sphere;
is a track inclination angle parameter;
for the railEccentricity of the track.
5. A spark global remote sensing track system based on near fire drift, comprising:
module M1: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images fire, and enabling the height of the near fire point at the end of the service life to be larger than the atmospheric height of fire gas according to the descending rate of the track height in the service life;
module M2: calculating the track inclination angle adjusting range according to the field angle of view of the detector camera;
module M3: calculating to obtain the change rate of the amplitude angle of the near fire point according to the remote sensing task period;
module M4: calculating to obtain the right ascent point and the left ascent point variation rate according to the target solar altitude constraint of the imaging period and the remote sensing detection task period;
module M5: analyzing and calculating semi-long axis parameters of the track by using parameters of the amplitude angle change rate and the right ascent and intersection point and the right ascent and descent change rate of the near fire point required by a remote sensing detection task;
determining the near fire height in the module M1 comprises: determining the upper limit of the height of a near fire point according to the maximum height requirement of the load when the load images the fire; according to the track height descending rate in the service life period, the height of a near fire point in the service life end period is larger than the height of a fire atmosphere:
wherein,the height is the initial track near the fire point;
a working height constraint for the load camera;
is the height of the near fire point is reducedA rate;
the service life of the spark detector is prolonged;
is the atmospheric height of Mars;
the track inclination determination in the module M2 includes:
the method meets the requirements of Mars global area coverage detection, the track inclination angle is required to be about 90 degrees, and meanwhile, the inclination angle deviation range is calculated according to the field angle of view of a detector camera:
wherein,the field angle of the view of the camera; />Is the track inclination angle.
6. The near fire drift based Mars global remote sensing orbital system of claim 5, wherein determining the near fire argument rate of change in the module M3 comprises:
according to the remote sensing detection task period, the near fire point drift amount is larger than 180 degrees in the task period, so that coverage of different latitude areas of the Mars is realized, and the calculation steps are as follows:
wherein,indicating the change rate of the amplitude angle of the near fire point; />The service life of the task is detected for the remote sensing of the detector.
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