CN117228007A - Method and device for rapidly determining active off-orbit strategy of SSO orbit spacecraft - Google Patents
Method and device for rapidly determining active off-orbit strategy of SSO orbit spacecraft Download PDFInfo
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Abstract
The invention relates to the technical field of spacecraft control, in particular to a method and a device for quickly determining an active off-orbit strategy of an SSO orbit spacecraft. The method comprises the following steps: determining reentry point information of the spacecraft based on the target landing point position, aerodynamic parameters, quality characteristics and current state information of the SSO orbit spacecraft; the reentry point information comprises the height, track dip angle and geographic latitude of the reentry point; the state information comprises orbit altitude, lateral acceleration of the spacecraft, roll angle and track azimuth; determining pulse velocity impulse of off-track braking based on reentry heat flow, overload constraint, height of reentry point and track inclination; and determining the latitude amplitude angle of the off-orbit point based on the geographical latitude of the reentry point and an analysis orbit integral equation, wherein the analysis orbit integral equation is obtained by performing off-orbit feature analysis on the spacecraft after applying an off-orbit braking speed increment at any latitude amplitude angle. The method and the system can quickly determine the off-track strategy and have strong response capability.
Description
Technical Field
The invention relates to the technical field of spacecraft control, in particular to a method and a device for quickly determining an active off-orbit strategy of an SSO orbit spacecraft.
Background
The off-orbit position of the traditional SSO orbit (Sun synchronous orbit Sun-synchronous orbit) on-board spacecraft is determined before the flight mission is executed, so that off-orbit strategy calculation can be carried out in advance by adopting a ground solution mode, and the calculated strategy is injected into the spacecraft in advance. The method is suitable for scenes with relatively fixed task orbits and task drop points, off-orbit strategies can be planned in advance according to specific scenes, and spacecrafts are injected before tasks.
However, as the demand for space exploration increases, orbital maneuvers, evasions, and other unexpected events are typically encountered, requiring temporary derailment strategies to be formulated. The existing calculation method of the ground off-orbit strategy of the spacecraft is high in calculation accuracy, but is long in time consumption, and is mostly carried out in units of weeks or months, so that the requirement of quick response during unexpected off-orbit cannot be met.
Therefore, a method and a device for rapidly determining an active off-orbit strategy of an SSO orbit spacecraft are needed to solve the above technical problems.
Disclosure of Invention
The embodiment of the invention provides a method and a device for rapidly determining an active off-orbit strategy of an SSO orbit spacecraft, which can rapidly determine the off-orbit strategy and have strong response capability.
In a first aspect, an embodiment of the present invention provides a method for quickly determining an active off-orbit policy of an SSO orbit spacecraft, including:
determining reentry point information of the spacecraft based on the target landing point position, aerodynamic parameters, quality characteristics and current state information of the SSO orbit spacecraft; the reentry point information comprises the height, the track dip angle and the geographic latitude of the reentry point; the state information comprises orbit altitude, lateral acceleration of the spacecraft, roll angle and track azimuth; the aerodynamic parameters comprise aerodynamic lift and aerodynamic drag;
determining pulse velocity impulse of off-track braking based on reentry heat flow, overload constraints, and height and track inclination of the reentry point;
and determining the latitude amplitude angle of the off-orbit point based on the geographical latitude of the reentry point and an analysis orbit integral equation, wherein the analysis orbit integral equation is obtained by performing off-orbit feature analysis on the spacecraft after applying an off-orbit braking speed increment at any latitude amplitude angle.
In a second aspect, an embodiment of the present invention further provides a device for quickly determining an active off-orbit policy of an SSO orbit spacecraft, including:
the reentry point determining module is used for determining reentry point information of the spacecraft based on the target landing point position, aerodynamic parameters, quality characteristics and current state information of the SSO orbit spacecraft; the reentry point information comprises the height, the track dip angle and the geographic latitude of the reentry point; the state information comprises orbit altitude, lateral acceleration of the spacecraft, roll angle and track azimuth; the aerodynamic parameters comprise aerodynamic lift and aerodynamic drag;
the pulse speed impulse determining module is used for determining pulse speed impulse of off-track braking based on the reentry heat flow, overload constraint, the height of the reentry point and track inclination angle;
and the off-orbit point latitude amplitude angle determining module is used for determining the off-orbit point latitude amplitude angle based on the geographical latitude of the reentry point and an analysis orbit integral equation, wherein the analysis orbit integral equation is obtained by performing off-orbit feature analysis on the spacecraft after applying an off-orbit braking speed increment at any latitude amplitude angle.
In a third aspect, an embodiment of the present invention further provides an electronic device, including a memory and a processor, where the memory stores a computer program, and when the processor executes the computer program, the method described in any embodiment of the present specification is implemented.
In a fourth aspect, embodiments of the present invention also provide a computer-readable storage medium having stored thereon a computer program which, when executed in a computer, causes the computer to perform a method according to any of the embodiments of the present specification.
The embodiment of the invention provides a method and a device for quickly determining an active off-orbit strategy of an SSO orbit spacecraft. In the method, after an unexpected off-orbit event occurs and the position of a target falling point is determined, the reentrant point information can be reversely deduced according to the aerodynamic parameters, the quality characteristics and the current state information of the spacecraft. After the reentry point information is determined, the pulse velocity impulse which can enable the spacecraft to reach the reentry point can be determined according to the reentry heat flow and the overload constraint. And finally, determining the latitude amplitude angle of the off-orbit point according to the geographical latitude of the reentry point and the analysis orbit integral equation. After determining the latitude amplitude angle of the off-orbit point, applying the pulse velocity impulse to the spacecraft at the latitude amplitude angle, so that the spacecraft can reach the determined reentry point and further reach the target landing point. The method can quickly determine the off-track strategy aiming at any drop point, and has strong response capability.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a method for quickly determining an active off-orbit strategy of an SSO orbit spacecraft according to an embodiment of the invention;
FIG. 2 is a hardware architecture diagram of an electronic device according to an embodiment of the present invention;
FIG. 3 is a block diagram of a device for quickly determining an active off-orbit strategy of an SSO orbit spacecraft according to an embodiment of the invention;
FIG. 4 is a schematic diagram of an off-track process according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of off-track process calculation according to an embodiment of the present invention;
FIG. 6 is a schematic diagram showing the change of the altitude and track inclination angle of a spacecraft from the ground after applying a braking velocity impulse to the spacecraft according to an embodiment of the invention;
FIG. 7 is a schematic diagram showing changes in latitude amplitude and track inclination of a spacecraft after application of a braking velocity impulse to the spacecraft according to an embodiment of the invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments, and all other embodiments obtained by those skilled in the art without making any inventive effort based on the embodiments of the present invention are within the scope of protection of the present invention.
Referring to fig. 1, an embodiment of the present invention provides a method for quickly determining an active off-orbit policy of an SSO orbit spacecraft, where the method includes:
step 100, determining reentry point information of an SSO orbit spacecraft based on a target landing point position, aerodynamic parameters, quality characteristics and current state information of the spacecraft; the reentry point information comprises the height, the track dip angle and the geographic latitude of the reentry point; the state information comprises orbit altitude, lateral acceleration of the spacecraft, roll angle and track azimuth; the aerodynamic parameters comprise aerodynamic lift and aerodynamic drag;
step 102, determining pulse velocity impulse of off-track braking based on reentry heat flow, overload constraint and height and track inclination angle of the reentry point;
and 104, determining the latitude amplitude angle of the off-orbit point based on the geographical latitude of the reentry point and an analysis orbit integral equation, wherein the analysis orbit integral equation is obtained by performing off-orbit feature analysis on the spacecraft after applying an off-orbit braking speed increment at any latitude amplitude angle.
In this embodiment, after the unexpected off-orbit event occurs and the target drop point position is determined, the reentry point information may be reversely deduced according to the aerodynamic parameters, the quality characteristics and the current state information of the spacecraft. After the reentry point information is determined, the pulse velocity impulse which can enable the spacecraft to reach the reentry point can be determined according to the reentry heat flow and the overload constraint. And finally, determining the latitude amplitude angle of the off-orbit point according to the geographical latitude of the reentry point and the analysis orbit integral equation. After determining the latitude amplitude angle of the off-orbit point, applying the pulse velocity impulse to the spacecraft at the latitude amplitude angle, so that the spacecraft can reach the determined reentry point and further reach the target landing point. The method can quickly determine the off-track strategy aiming at any drop point, and has strong response capability.
The tasks in the GNC system are software tasks.
The manner in which the individual steps shown in fig. 1 are performed is described below.
Firstly, aiming at step 100, determining reentry point information of a spacecraft based on a target landing point position, aerodynamic parameters, quality characteristics and current state information of the SSO orbit spacecraft; the reentry point information comprises the height, the track dip angle and the geographic latitude of the reentry point; the state information comprises orbit altitude, lateral acceleration of the spacecraft, roll angle and track azimuth; the aerodynamic parameters include aerodynamic lift and aerodynamic drag.
In this embodiment, the reentry point is the point where the spacecraft enters the atmosphere. Typically, an off-orbit spacecraft will experience a pull-up Duan Heping equilibrium glide segment during flight from the reentry point to the target landing point, and the equilibrium glide segment includes a near-circular arc segment and a straight flight segment, as shown in fig. 4 and 5. Wherein, the pulling-up section, ZS-Z1 section, is mainly responsible for pulling up the descending spacecraft, so that the spacecraft gradually meets the conditions of the equilibrium gliding stage. The whole process of Z1-ZF belongs to the equilibrium gliding stage, and the equilibrium gliding condition of the spacecraft is mainly maintained by controlling the tilting angle of the spacecraft. In the process, Z1-Z2 executes near-arc steering guidance, and the flying speed direction of the aircraft at the Z2 point points to the ZF point; the Z2-ZF performs a conventional guidance based on energy-altitude, and the altitude of the ZF point can be 20km.
In step 100, the specific implementation process of the reentrant point information includes:
and A1, determining the altitude and the track dip angle of the reentry point based on the target landing point position, the pneumatic parameters, the quality characteristics and the current state information.
A2, determining a nominal total course from the reentry point to the target landing point, a nominal longitudinal course, a transverse deviation of the target landing point relative to a current orbit plane and a longitudinal flight distance of the spacecraft in the pull-up section based on the altitude and the track inclination angle of the reentry point; the current orbit plane is an orbit plane where the spacecraft flies to the reentry point;
a3, correcting the nominal longitudinal course based on the current state information, the nominal total course and the longitudinal flight distance of the spacecraft in the pull-up section to obtain a corrected nominal longitudinal course;
and step A4, determining the geographic latitude of the reentry point based on the corrected nominal longitudinal range and the geographic latitude of the target landing point.
The following details the steps:
for step A1, in SSO tracks with track height of 350km and track pitch of about 96.850 DEG, the height of the reentry point is typically taken to be 100km, and the track pitch of the reentry point is typically taken to be-1.0 deg.
For the step A2, the nominal total range from the reentry point to the target landing point, the nominal longitudinal range, the transverse deviation of the target landing point relative to the current orbit plane, and the longitudinal flight distance of the spacecraft in the pull-up section are determined based on a simplified three-degree-of-freedom reentry dynamics equation, wherein the simplified three-degree-of-freedom reentry dynamics equation is as follows:
wherein D is the aerodynamic resistance of the spacecraft and is the opposite direction of the flying speed; l is the aerodynamic lift of the spacecraft;is the acceleration of gravity; />The current real-time ground center distance of the spacecraft; />Geographic longitude for spacecraft; />The geographic latitude of the spacecraft;is the local speed of the spacecraft; />The track inclination angle of the spacecraft, namely the included angle between the flying speed and the horizontal plane; />The azimuth angle of the flight path of the spacecraft is the flying speed and the forward eastern included angle; m is the mass of the spacecraft; />Is the roll angle of the spacecraft.
Aiming at the step A3, the process of correcting the nominal longitudinal course is as follows:
determining a theoretical course of the equilibrium glide segment based on a nominal total course of the target landing point and a longitudinal flight distance of the pull-up segment;
determining a first included angle between a connecting line of the target falling point and the end point of the pull-up section and the longitudinal direction of the current track plane based on the transverse deviation of the target falling point relative to the current track plane and the flight range of the balance gliding section;
determining the transverse acceleration and the arc radius of the spacecraft in the near arc section;
based on the first included angle, the nominal longitudinal range, and the radius of the arc of the near arc segmentThe transverse deviation of the target falling point relative to the current track plane determines a second included angle between a connecting line of the target falling point and the end point of the near circular arc section and the longitudinal direction of the current track plane;
calculating an actual voyage of the balanced glide segment based on the first included angle and the second included angle;
and correcting the nominal longitudinal course based on the correction relation between the actual course of the balance gliding section and the theoretical course of the balance gliding section to obtain the corrected nominal longitudinal course.
The specific calculation process is as follows:
order theThen->；
And (3) making:
the method comprises the following steps:
（1）
formula (1) is shown inThe convex problem in the interval of (2) is solved by using a line cutting method to obtain +.>Is a numerical value of (2);
based onThe actual course of the equilibrium glide segment is calculated by the following steps:
and due to；
The correction relationship between the actual course of the equilibrium glide segment and the theoretical course of the equilibrium glide segment is:
the corrected nominal longitudinal range is:
in the method, in the process of the invention,is the first included angle; />Is the second included angle; s1 is a theoretical voyage of the balance gliding section; s0 is the nominal total course of the target landing point; l1 is the longitudinal flight distance of the pull-up section; l is the aerodynamic lift of the spacecraft; h0 is the lateral deviation of the ZF point relative to the current track plane; h1 is the transverse deviation of the Z2 point relative to the current track plane; />A lateral acceleration for the near-circular arc segment; />The radius of the arc is the radius of the arc of the near arc section; />Is the roll angle of the spacecraft; v1 is the speed of the spacecraft at the Z1 point; m is the mass of the spacecraft; l2 is the longitudinal distance from point Z4 to point Z5; l3 is a slaveThe longitudinal distance from the Z1 point to the Z4 point; l0 is a nominal longitudinal range from the reentry point to the target landing point; />Is the corrected nominal longitudinal course; the ZF point is a target falling point, the ZS point is a reentry point, the Z1 point is an end point of the pull-up section and a start point of the near arc section, and the Z2 point is an end point of the near arc section and a start point of the straight flight section; the Z4 point is the intersection point of the extension line of the connecting line of the ZF point and the Z2 point and the longitudinal direction of the current track plane; the Z5 point is a longitudinal projection point of the ZF point on the current track plane; />An actual course for the equilibrium glide segment; />For the actual voyage of said equilibrium glide segment +.>And a correction coefficient between the theoretical voyage S1 of the equilibrium glide segment.
For step A4, the geographical latitude of the reentrant point is calculated by the following formula:
in the method, in the process of the invention,the geographic latitude of the target falling point is the geographic latitude of the target falling point; />Is the corrected nominal longitudinal course; />Is the earth radius; />And the geographic latitude of the reentry point.
Then, for step 102, the pulse rate impulse of the off-track brake is determined based on the re-entry heat flow, the overload constraint, and the height and track pitch of the re-entry point.
In the step, the height of the reentry point is set to be 100km, the track dip angle of the reentry point is set to be-1.0 degrees, and therefore the off-track braking pulse speed increment is calculated to be 90m/s. After calculating the speed increment, in order to satisfy the constraint of the geographical latitude of the reentry point, the latitude argument of the off-orbit point ZLG needs to be calculated.
Finally, for step 104, the calculation process of the latitude argument of the off-orbit point is:
and step B1, determining a true near point angle based on the height of the reentry point and a resolved orbit integral equation.
In the step, the analysis orbit integral equation is obtained by performing off-orbit feature analysis on the spacecraft after applying off-orbit braking speed increment at any latitude amplitude angle. According to the off-orbit feature analysis, after the off-orbit braking speed increment is applied at any latitude amplitude angle, the subsequent orbit data features of the spacecraft are shown in fig. 6 and 7, and can be seen from the figures:
in the initial stage of not applying speed impulse to the spacecraft, the spacecraft flies around a circular orbit, the heights of all points on the orbit are the same as the ground, and at the moment, the speed direction of the spacecraft is also kept parallel to the local horizontal plane, and the track dip angle is kept to be 0. When the brake speed increment is applied to the spacecraft, the circular orbit is changed into an elliptical orbit, the altitude of the spacecraft from the ground is periodically changed within a certain range, as shown in fig. 6, and meanwhile, the speed of the spacecraft relative to the local horizontal plane included angle (track dip angle) is sinusoidally changed along with the orbit phase, as shown in fig. 7. From this characteristic, an analytical orbit integration equation can be determined.
The expression of the analytical orbit integral equation is as follows:
and deforming the analysis orbit integral equation to obtain the expression of the true near point angle as follows:
f is a numerical solution in the interval [1.5 pi, 2 pi ].
And B2, determining the track phase difference between the reentry point and the off-track point based on the true near point angle.
The track phase difference between the re-entry point and the off-track point is:
and B3, taking the sum of the latitude of the reentry point and the phase difference as the latitude amplitude angle of the off-orbit point.
The expression of the latitude argument of the off-orbit point is:
in the formulas, r is the real-time ground center distance of the spacecraft; h is an orbital momentum moment;is the gravitational constant; e is the track eccentricity; f is the true near point angle of the track; />Is the track radius; h2 is the height of the reentrant point; />Is the latitude amplitude angle of the off-orbit point; />And the geographic latitude of the reentry point.
As shown in fig. 2 and 3, the embodiment of the invention provides a rapid determination device for an active off-orbit strategy of an SSO orbit spacecraft. The apparatus embodiments may be implemented by software, or may be implemented by hardware or a combination of hardware and software. In terms of hardware, as shown in fig. 2, a hardware architecture diagram of an electronic device where an SSO orbit spacecraft active off-orbit policy fast determining device provided by an embodiment of the present invention is located is shown, where the electronic device where the embodiment is located may generally include other hardware, such as a forwarding chip responsible for processing a packet, besides a processor, a memory, a network interface, and a nonvolatile memory shown in fig. 2. Taking a software implementation as an example, as shown in fig. 3, the device in a logic sense is formed by reading a corresponding computer program in a nonvolatile memory into a memory by a CPU of an electronic device where the device is located and running the computer program.
The device for quickly determining the active off-orbit strategy of the SSO orbit spacecraft provided by the embodiment comprises the following components:
a reentry point determination module 300 configured to determine reentry point information of a spacecraft based on a target landing point position, aerodynamic parameters, quality characteristics, and current state information of the SSO orbit spacecraft; the reentry point information comprises the height, the track dip angle and the geographic latitude of the reentry point; the state information comprises orbit altitude, lateral acceleration of the spacecraft, roll angle and track azimuth; the aerodynamic parameters comprise aerodynamic lift and aerodynamic drag;
a pulse rate impulse determination module 302 for determining a pulse rate impulse for off-track braking based on a reentry heat flow, an overload constraint, and a height and track pitch of the reentry point;
the off-orbit point latitude argument determining module 304 is configured to determine an off-orbit point latitude argument based on the geographical latitude of the reentry point and an analytical orbit integral equation, where the analytical orbit integral equation is obtained by performing off-orbit feature analysis on the spacecraft after applying an off-orbit braking speed increment at any one of the latitude argument.
In some embodiments, the reentry point determination module 300 is configured to perform the following operations:
determining the altitude and track inclination of the reentry point based on the target landing point position, the pneumatic parameters, the quality characteristics and the current state information;
determining a nominal total course, a nominal longitudinal course, a transverse deviation of the target landing point relative to a current orbit plane and a longitudinal flight distance of the spacecraft in the pull-up section of the spacecraft based on the height and the track inclination angle of the reentry point; the current orbit plane is an orbit plane where the spacecraft flies to the reentry point;
correcting the nominal longitudinal course based on the current state information, the nominal total course and the longitudinal flight distance of the spacecraft in the pull-up section to obtain a corrected nominal longitudinal course;
and determining the geographic latitude of the reentry point based on the corrected nominal longitudinal range and the geographic latitude of the target landing point.
In some embodiments, the reentry point determination module 300, when performing the correction of the nominal longitudinal range based on the current state information, the nominal total range, and the longitudinal flight distance of the spacecraft in the pull-up section, includes:
determining a theoretical course of the equilibrium glide segment based on a nominal total course of the target landing point and a longitudinal flight distance of the pull-up segment;
determining a first included angle between a connecting line of the target falling point and the end point of the pull-up section and the longitudinal direction of the current track plane based on the transverse deviation of the target falling point relative to the current track plane and the flight range of the balance gliding section;
determining the transverse acceleration and the arc radius of the spacecraft in the near arc section;
based on the first included angle, the nominal longitudinal range, and the radius of the arc of the near arc segmentThe transverse deviation of the target falling point relative to the current track plane determines a second included angle between a connecting line of the target falling point and the end point of the near circular arc section and the longitudinal direction of the current track plane;
calculating an actual voyage of the balanced glide segment based on the first included angle and the second included angle;
and correcting the nominal longitudinal course based on the correction relation between the actual course of the balance gliding section and the theoretical course of the balance gliding section to obtain the corrected nominal longitudinal course.
In some embodiments, the calculating process of correcting the nominal longitudinal course based on the current state information, the nominal total course and the longitudinal flight distance of the spacecraft in the pull-up section to obtain the corrected nominal longitudinal course is as follows:
order theThen->；
And (3) making:
the method comprises the following steps:
（1）
formula (1) is shown inThe convex problem in the interval of (2) is solved by using a line cutting method to obtain +.>Is a numerical value of (2);
based onThe actual course of the equilibrium glide segment is calculated by the following steps:
and because:；
the correction relationship between the actual course of the equilibrium glide segment and the theoretical course of the equilibrium glide segment is:
the corrected nominal longitudinal range is:
in the method, in the process of the invention,is the first included angle; />Is the second included angle; s1 is a theoretical voyage of the balance gliding section; s0 is the nominal total course of the target landing point; l1 is the longitudinal flight distance of the pull-up section; l is the aerodynamic lift of the spacecraft; h0 is the lateral deviation of the ZF point relative to the current track plane; h1 is the transverse deviation of the Z2 point relative to the current track plane; />A lateral acceleration for the near-circular arc segment; />The radius of the arc is the radius of the arc of the near arc section; />Is the roll angle of the spacecraft; v1 is the speed of the spacecraft at the Z1 point; m is the mass of the spacecraft; l2 is the longitudinal distance from point Z4 to point Z5; l3 is the longitudinal distance from point Z1 to point Z4; l0 is a nominal longitudinal range from the reentry point to the target landing point; />Is the corrected nominal longitudinal course; the ZF point is a target falling point, the ZS point is a reentry point, the Z1 point is an end point of the pull-up section and a start point of the near arc section, and the Z2 point is an end point of the near arc section and a start point of the straight flight section; the Z4 point is the intersection point of the extension line of the connecting line of the ZF point and the Z2 point and the longitudinal direction of the current track plane; the Z5 point is a longitudinal projection point of the ZF point on the current track plane; />An actual course for the equilibrium glide segment; />For the actual voyage of said equilibrium glide segment +.>And a correction coefficient between the theoretical voyage S1 of the equilibrium glide segment.
In some embodiments, the geographic latitude of the reentry point is calculated by the following formula:
in the method, in the process of the invention,the geographic latitude of the target falling point is the geographic latitude of the target falling point; />Is the corrected nominal longitudinal course; />Is the earth radius; />And the geographic latitude of the reentry point.
In some embodiments, the off-track latitude argument determination module 304 is configured to:
determining a true near point angle based on the reentrant point height and an analytical orbit integral equation;
determining an orbital phase difference of the reentry point and the off-track point based on the true near point angle;
and taking the sum of the latitude of the reentry point and the phase difference as the latitude argument of the off-orbit point.
In some embodiments, the calculation process for determining the latitude argument of the off-orbit point based on the geographical latitude of the reentry point and the analysis orbit integral equation is as follows:
the expression of the analytical orbit integral equation is as follows:
and deforming the analysis orbit integral equation to obtain the expression of the true near point angle as follows:
f is a numerical solution in the interval of [1.5 pi, 2 pi ];
the track phase difference between the re-entry point and the off-track point is:
the expression of the latitude argument of the off-orbit point is:
in the formulas, r is the real-time ground center distance of the spacecraft; h is an orbital momentum moment;is the gravitational constant; e is the track eccentricity; f is the true near point angle of the track; />Is the track radius; h2 is the height of the reentrant point; />Is the latitude amplitude angle of the off-orbit point; />And the geographic latitude of the reentry point.
It can be understood that the structure illustrated in the embodiment of the present invention does not constitute a specific limitation on a device for quickly determining the active off-track strategy of an SSO orbit spacecraft. In other embodiments of the present invention, a rapid determination device for an SSO orbit spacecraft active off-orbit strategy may include more or fewer components than shown, or certain components may be combined, certain components may be split, or different component arrangements. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.
The content of information interaction and execution process between the modules in the device is based on the same conception as the embodiment of the method of the present invention, and specific content can be referred to the description in the embodiment of the method of the present invention, which is not repeated here.
The embodiment of the invention also provides electronic equipment, which comprises a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method for quickly determining the active off-track strategy of the SSO orbit spacecraft in any embodiment of the invention is realized.
The embodiment of the invention also provides a computer readable storage medium, and the computer readable storage medium is stored with a computer program, when the computer program is executed by a processor, the processor is caused to execute the method for quickly determining the active off-track strategy of the SSO orbit spacecraft in any embodiment of the invention.
Specifically, a system or apparatus provided with a storage medium on which a software program code realizing the functions of any of the above embodiments is stored, and a computer (or CPU or MPU) of the system or apparatus may be caused to read out and execute the program code stored in the storage medium.
In this case, the program code itself read from the storage medium may realize the functions of any of the above-described embodiments, and thus the program code and the storage medium storing the program code form part of the present invention.
Examples of the storage medium for providing the program code include a floppy disk, a hard disk, a magneto-optical disk, an optical disk (e.g., CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), a magnetic tape, a nonvolatile memory card, and a ROM. Alternatively, the program code may be downloaded from a server computer by a communication network.
Further, it should be apparent that the functions of any of the above-described embodiments may be implemented not only by executing the program code read out by the computer, but also by causing an operating system or the like operating on the computer to perform part or all of the actual operations based on the instructions of the program code.
Further, it is understood that the program code read out by the storage medium is written into a memory provided in an expansion board inserted into a computer or into a memory provided in an expansion module connected to the computer, and then a CPU or the like mounted on the expansion board or the expansion module is caused to perform part and all of actual operations based on instructions of the program code, thereby realizing the functions of any of the above embodiments.
It is noted that relational terms such as first and second, and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one …" does not exclude the presence of additional identical elements in a process, method, article or apparatus that comprises the element.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. The method for quickly determining the active off-orbit strategy of the SSO orbit spacecraft is characterized by comprising the following steps of:
determining reentry point information of the spacecraft based on the target landing point position, aerodynamic parameters, quality characteristics and current state information of the SSO orbit spacecraft; the reentry point information comprises the height, the track dip angle and the geographic latitude of the reentry point; the state information comprises orbit altitude, lateral acceleration of the spacecraft, roll angle and track azimuth; the aerodynamic parameters comprise aerodynamic lift and aerodynamic drag;
determining pulse velocity impulse of off-track braking based on reentry heat flow, overload constraints, and height and track inclination of the reentry point;
and determining the latitude amplitude angle of the off-orbit point based on the geographical latitude of the reentry point and an analysis orbit integral equation, wherein the analysis orbit integral equation is obtained by performing off-orbit feature analysis on the spacecraft after applying an off-orbit braking speed increment at any latitude amplitude angle.
2. The method of claim 1, wherein the flying of the spacecraft from the reentry point to the target landing point comprises pulling up a Duan Heping equilibrium glide segment; the determining the reentry point information of the spacecraft based on the target landing point position, the aerodynamic parameters, the quality characteristics and the current state information of the SSO orbit spacecraft comprises the following steps:
determining the height and track inclination angle of the reentry point based on the target landing point position, the pneumatic parameters, the quality characteristics and the current state information;
determining a nominal total course, a nominal longitudinal course, a transverse deviation of the target landing point relative to a current orbit plane and a longitudinal flight distance of the spacecraft in the pull-up section of the spacecraft based on the height and the track inclination angle of the reentry point; the current orbit plane is an orbit plane where the spacecraft flies to the reentry point;
correcting the nominal longitudinal course based on the current state information, the nominal total course and the longitudinal flight distance of the spacecraft in the pull-up section to obtain a corrected nominal longitudinal course;
and determining the geographic latitude of the reentry point based on the corrected nominal longitudinal range and the geographic latitude of the target landing point.
3. The method of claim 2, wherein the equilibrium glide segment comprises a near circular arc segment and a straight flight segment; the correcting the nominal longitudinal course based on the current state information, the nominal total course and the longitudinal flight distance of the spacecraft in the pull-up section to obtain a corrected nominal longitudinal course comprises the following steps:
determining a theoretical course of the equilibrium glide segment based on a nominal total course of the target landing point and a longitudinal flight distance of the pull-up segment;
determining a first included angle between a connecting line of the target falling point and the end point of the pull-up section and the longitudinal direction of the current track plane based on the transverse deviation of the target falling point relative to the current track plane and the flight range of the balance gliding section;
determining the transverse acceleration and the arc radius of the spacecraft in the near arc section;
based on the first included angle, the nominal longitudinal range, and the radius of the arc of the near arc segmentThe transverse deviation of the target falling point relative to the current track plane determines a second included angle between a connecting line of the target falling point and the end point of the near circular arc section and the longitudinal direction of the current track plane;
calculating an actual voyage of the balanced glide segment based on the first included angle and the second included angle;
and correcting the nominal longitudinal course based on the correction relation between the actual course of the balance gliding section and the theoretical course of the balance gliding section to obtain the corrected nominal longitudinal course.
4. A method according to claim 3, wherein the correcting the nominal longitudinal course based on the current state information, the nominal total course and the longitudinal flight distance of the spacecraft in the pull-up section comprises the following calculation steps:
order theThen->；
And (3) making:
the method comprises the following steps:
（1）
formula (1) is shown inThe convex problem in the interval of (2) is solved by using a line cutting method to obtain +.>Is a numerical value of (2);
based onThe actual course of the equilibrium glide segment is calculated by the following steps:
and because:；
the correction relationship between the actual course of the equilibrium glide segment and the theoretical course of the equilibrium glide segment is:
the corrected nominal longitudinal range is:
in the method, in the process of the invention,is the first included angle; />Is the second included angle; s1 is a theoretical voyage of the balance gliding section; s0 is the nominal total course of the target landing point; l1 is the longitudinal flight distance of the pull-up section; l is the aerodynamic lift of the spacecraft; h0 is the lateral deviation of the ZF point relative to the current track plane; h1 is the transverse deviation of the Z2 point relative to the current track plane; />A lateral acceleration for the near-circular arc segment; />The radius of the arc is the radius of the arc of the near arc section; />Is the roll angle of the spacecraft; v1 is the speed of the spacecraft at the Z1 point; m is the mass of the spacecraft; l2 is the longitudinal distance from point Z4 to point Z5; l3 is the longitudinal distance from point Z1 to point Z4; l0 is a nominal longitudinal range from the reentry point to the target landing point; />Is the corrected nominal longitudinal course; the ZF point is a target falling point, the ZS point is a reentry point, the Z1 point is an end point of the pull-up section and a start point of the near arc section, and the Z2 point is an end point of the near arc section and a start point of the straight flight section; the Z4 point is the intersection point of the extension line of the connecting line of the ZF point and the Z2 point and the longitudinal direction of the current track plane; the Z5 point is a longitudinal projection point of the ZF point on the current track plane; />An actual course for the equilibrium glide segment; />For said balancing glideActual voyage of segment->And a correction coefficient between the theoretical voyage S1 of the equilibrium glide segment.
5. The method of claim 2, wherein the geographic latitude of the reentry point is calculated by the formula:
in the method, in the process of the invention,the geographic latitude of the target falling point is the geographic latitude of the target falling point; />Is the corrected nominal longitudinal course; />Is the earth radius;and the geographic latitude of the reentry point.
6. The method of claim 1, wherein the determining the latitude argument of the off-track point based on the geographical latitude of the reentry point and the analytical orbit integral equation comprises:
determining a true near point angle based on the reentrant point height and an analytical orbit integral equation;
determining an orbital phase difference of the reentry point and the off-track point based on the true near point angle;
and taking the sum of the latitude of the reentry point and the phase difference as the latitude argument of the off-orbit point.
7. The method of claim 6, wherein the calculating process for determining the latitude argument of the off-orbit point based on the geographical latitude of the reentry point and the analytical orbit integral equation is as follows:
the expression of the analytical orbit integral equation is as follows:
and deforming the analysis orbit integral equation to obtain the expression of the true near point angle as follows:
f is a numerical solution in the interval of [1.5 pi, 2 pi ];
the track phase difference between the re-entry point and the off-track point is:
the expression of the latitude argument of the off-orbit point is:
in the formulas, r is the real-time ground center distance of the spacecraft; h is an orbital momentum moment;is the gravitational constant; e is the track eccentricity; f is the true near point angle of the track; />Is the track radius; h2 is the height of the reentrant point; />Is the latitude amplitude angle of the off-orbit point; />And the geographic latitude of the reentry point.
8. A rapid determination device for an active off-orbit strategy of an SSO orbit spacecraft, comprising:
the reentry point determining module is used for determining reentry point information of the spacecraft based on the target landing point position, aerodynamic parameters, quality characteristics and current state information of the SSO orbit spacecraft; the reentry point information comprises the height, the track dip angle and the geographic latitude of the reentry point; the state information comprises orbit altitude, lateral acceleration of the spacecraft, roll angle and track azimuth; the aerodynamic parameters comprise aerodynamic lift and aerodynamic drag;
the pulse speed impulse determining module is used for determining pulse speed impulse of off-track braking based on the reentry heat flow, overload constraint, the height of the reentry point and track inclination angle;
and the off-orbit point latitude amplitude angle determining module is used for determining the off-orbit point latitude amplitude angle based on the geographical latitude of the reentry point and an analysis orbit integral equation, wherein the analysis orbit integral equation is obtained by performing off-orbit feature analysis on the spacecraft after applying an off-orbit braking speed increment at any latitude amplitude angle.
9. A computing device comprising a memory and a processor, the memory having stored therein a computer program, the processor implementing the method of any of claims 1-7 when the computer program is executed.
10. A computer readable storage medium having stored thereon a computer program which, when executed in a computer, causes the computer to perform the method of any of claims 1-7.
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