CN117009606B - Constraint-considered observation star orbit maneuver entry point selection method - Google Patents
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Abstract
The invention discloses a constraint-considered observation star orbit maneuver entry point selection method, which comprises the steps of analyzing target star information TInfo, observation star information CInfo and observation constraint parameters ObsCons, and verifying observation rationality; screening to obtain an observation point set IP (t, p, v); acquiring an inertial coordinate observation point set TP (t, p, v); according to the invention, the access point set conforming to the basic constraint is screened out through illumination constraint and observation distance constraint, then the optimal maneuvering scheme screening is carried out on the points to be selected through the observation star maneuvering capability, and finally the optimal access point selection result is given out. The method can provide the orbit maneuver entry points meeting the constraint conditions, has certain universality and can be applied to the selection of the observation entry points with different orbit heights; meanwhile, the method can be conveniently moved to an electronic detection load and a radar imaging load, and can be completed only by expanding constraint conditions and increasing calculated amount.
Description
Technical Field
The invention relates to the technical field of satellite approaching observation, in particular to an observation satellite orbit maneuver entry point selection method considering constraint.
Background
With the rapid development of aerospace technology, space has become a key field of strategic competition and game countermeasure in various countries. The geosynchronous orbit (GEO) is the focus of attention, and a large number of high-value space vehicles are deployed near the geosynchronous orbit (GEO), including strategic satellites such as communication, navigation, early warning, electronic reconnaissance, data relay, new technology experiments and the like; the space situation awareness is an important capability for guaranteeing space safety and is a hot spot which needs to be lifted and developed at present; the situation awareness planning satellite (GSSAP) can observe a high-orbit target for a long time, finely and in real time, acquire important information such as orbit, load and platform of the high-value target in time, and provide support for grasping the development capability of the space technology.
Therefore, developing new technology and new method in the orbit control field is beneficial to improving the reaction capability of the high orbit satellite countermeasure; the method is characterized in that a target is closely observed in a certain mode, a proper time range is selected, and the target enters a proper position, so that a favorable observation situation is critical.
The literature, space control technology and application, volume 48, 3 of the 6 th month of 2022, refers to various basic constraint conditions, but focuses on scheme optimization, and no further intensive study on entry point optimization is performed.
Disclosure of Invention
The invention aims to provide a constraint-considered observation star orbit maneuver entry point selection method, which realizes the optimal selection of an observation maneuver scheme and obtains an optimal observation entry point.
The aim of the invention can be achieved by the following technical scheme: a method for selecting a mobile access point of an observation star orbit taking constraints into consideration comprises the following steps:
s1, acquiring target star information TInfo, observation star information CInfo and an observation constraint parameter ObsCons, analyzing the target star information TInfo, the observation star information CInfo and the observation constraint parameter ObsCons, and verifying the observation rationality;
s2, screening and obtaining an observation point set IP (t, p, v) according to the target star information TInfo, the observation star information CInfo and the observation constraint parameter ObsCons;
s3, performing distance constraint condition DisCons screening on the observation point set IP (t, p, v) obtained by screening to obtain a distance observation point set OP (t, p, v);
s4, converting the acquired observation point set IP (t, p, v) into an earth inertial coordinate system to acquire an inertial coordinate observation point set TP (t, p, v);
further: in the step S1, a step of, in the above-mentioned step,
the target star information TInfo includes: target star orbit information T (T, p, v), target star platform maneuver information TOMInfo; and target star load information TplayLoad;
the observation star information CInfo includes: the observation star orbit information C (t, p, v), the observation star platform maneuver information COMInfo, the observation star payload information CplayLoad.
Further: the step of screening and obtaining the observation point set IP (t, p, v) in S2 includes:
s21, calculating sun position information S (T, p, v) and moon position information M (T, p, v) at the same moment according to target star orbit information T (T, p, v), and acquiring an illumination constraint condition IllCons;
s22, constructing virtual star orbit information OtmpC (ti, p, v) according to the star orbit information C (t, p, v);
s23, screening the virtual observation star orbit information OtmpC (ti, p, v) according to the target star orbit information T (T, p, v), the sun position information S (T, p, v), the moon position information M (T, p, v) and the illumination constraint condition IllCons to obtain an observation point set IP (T, p, v).
Further: the distance constraint condition DisCons screening in the S3 comprises observation distance screening and safety distance screening.
Further: the distance observation point set OP (t, p, v) in S3 includes a same-plane observation point set XOP (t, p, v) and an out-of-plane observation point set YOP (t, p, v).
Further: the step of obtaining the inertial coordinate observation point set TP (t, p, v) in S4 includes:
s41, establishing a conversion matrix Q from a target star orbit information coordinate system to an earth inertia coordinate system;
s42, converting the distance observation point set OP (t, p, v) into an inertial coordinate observation point set TP (t, p, v) point under an earth inertial coordinate system through a conversion matrix Q.
Further: also comprises the steps of
S5, screening the inertial coordinate observation point set TP (t, p, v) through observation satellite observation maneuver constraint to obtain an optimal maneuver entry point OB (t, p, v).
The invention has the beneficial effects that:
1. the invention provides a track maneuvering access point selection method considering various constraints, which screens out access point sets conforming to basic constraints through illumination constraints and observation distance constraints, screens out optimized maneuvering schemes for points to be selected through observability maneuvering capability, and finally gives out optimal access point options; meanwhile, the method can be conveniently moved to an electronic detection load and a radar imaging load, and can be completed only by expanding constraint conditions and increasing calculated amount.
2. The invention provides a constraint-considered mobile access point selection method for an observation star orbit, which comprehensively considers the constraint of illumination conditions and the constraint of distance and the mobile capability of an observation star for mobile access point selection, can acquire a more ideal approach observation mobile scheme for the observation star, selects an optimal mobile access point OB (t, p, v), improves the quality of approach observation of the observation star, and can acquire a more ideal observation effect.
3. The invention can form different observation point sets according to the requirements of the observation tasks of the circumvolve and the glancing flight of the observation star, can meet the various requirements of the observation tasks of the observation star, and has wide application range.
4. The method combines multi-step screening optimization and star observation maneuverability, carries out constraint optimization on the task scheme to be executed, and the selected optimal scheme has higher accuracy, better observation effect, stronger stability, lower fuel consumption in a specified time, and better use value.
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FIG. 1 is a flow chart of a method for selecting a mobile entry point of an observed star orbit taking constraints into consideration.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar symbols indicate like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are exemplary only for explaining the present invention and are not to be construed as limiting the present invention.
As shown in fig. 1, the invention discloses a method for selecting a orbit maneuver entry point of an observation star considering constraint, which comprises the following steps:
s1, acquiring target star information (TInfo), observed star information (CInfo) and observed constraint parameters (ObsCons), analyzing the target star information (TInfo), the observed star information (CInfo) and the observed constraint parameters (ObsCons), and verifying the observation rationality;
s2, screening and obtaining an observation point set IP (t, p, v) according to target star information (TInfo), observation star information (CInfo) and observation constraint parameters (ObsCons);
s3, performing distance constraint condition DisCons screening on the observation point set IP (t, p, v) obtained by screening to obtain a distance observation point set OP (t, p, v);
s4, converting the acquired observation point set IP (t, p, v) into an earth inertial coordinate system to acquire an inertial coordinate observation point set TP (t, p, v).
The target star may be a geosynchronous orbit (GEO) that is in an important strategic location in space on which a high value core space satellite system is operating, and thus is particularly important for the observation of geosynchronous orbit (GEO) targets.
The observation satellite can be a situation awareness satellite (GSSAP), the situation awareness satellite (GSSAP) can realize the approaching observation of the geosynchronous orbit (GEO) through short-distance glancing or winding flying, the method is an important means for carrying out satellite situation awareness in the current space, the situation awareness satellite (GSSAP) approaches the geosynchronous orbit (GEO) to carry out observation, and a plurality of conditions such as proper illumination angle, observation distance and the like are required to be met.
First, target star information (TInfo) and observed star information (CInfo) are acquired, the target star information (TInfo) including: target star orbit information T (T, p, v), target star platform maneuver information (tomimfo); and target star load information (TplayLoad); the observation star information (CInfo) includes: the satellite orbit information C (t, p, v), the satellite platform maneuver information (COMInfo), the satellite payload information (CplayLoad).
The feasibility of the observation star to the near observation of the target star can be judged by analyzing the orbit information and the observation constraint parameters, and the observation rationality is verified.
According to the target star orbit information T (T, p, v) and the observed star orbit information C (T, p, v), screening and obtaining an observation point set IP (T, p, v), wherein the process is as follows:
calculating sun position information S (T, p, v) and moon position information M (T, p, v) at the same moment according to target star orbit information T (T, p, v), and acquiring illumination constraint conditions (IllCons); solar light and moon light constraint conditions can be obtained through solar position information S (t, p, v) and moon position information M (t, p, v), and if an observation star has better observation and imaging capabilities on a target star, the relative positions of the two stars need to meet good imaging illumination angles of solar light and moon light.
The geometrical relationship of the target star, the observation star and the sun is described by the phase angle of the sunlight, the included angle between the connection line of the observation star and the sun and the connection line of the observation star and the target star is the phase angle, and the brightness information of the target star is greatly changed under the condition of different phase angles. The solar phase angle of the observation star when approaching to the target star is generally kept between 40 degrees and 160 degrees, and the target is located in the forward-looking observation area of the observation star at the moment, so that the influence of solar stray light on imaging can be effectively avoided, and the restriction of moon light is also realized.
Virtual observation star orbit information OtmpC (ti, p, v) is constructed according to the observation star orbit information, the virtual observation star orbit information OtmpC (ti, p, v) is based on normal observation star orbit information, according to the mobile capability of an observation star, the operation orbit of the observation star approaching a target star is simulated first, and the virtual observation star orbit information OtmpC (ti, p, v) can simulate various approaching observation conditions so as to be convenient for selecting an optimal observation point.
And screening the virtual observation star orbit information OtmpC (ti, p, v) according to the target star orbit information T (T, p, v), the sun position information S (T, p, v), the moon position information M (T, p, v) and the illumination constraint condition (IllCons) to obtain an observation point set IP (T, p, v).
The observation point set IP (t, p, v) acquired at this time is IP (t, p, v) acquired under the condition that the illumination constraint such as the solar phase angle constraint and the moon light phase angle constraint is satisfied.
Besides meeting the above illumination constraint (IllCons), the observation of the target star by the observation star can also be further screened to enable the observation star and the target star to meet the distance constraint, which requires further distance constraint (DisCons) screening of the observation point set IP (t, p, v).
And (3) screening the observation point set IP (t, p, v) obtained by screening under a distance constraint condition (DisCons) to obtain a distance observation point set OP (t, p, v).
Distance constraint (DisCons) screening mainly includes observation distance screening and safety distance screening.
The observation distance constraint means that an imaging camera for observing the satellites has the maximum observation distance, and the distance between two satellites cannot exceed the maximum observation distance in the short-distance observation process.
The safe distance constraint means that the distance between the observation star and the target star cannot be too close, and the observation star needs to be always located outside the safe distance of the target star.
After the distance constraint condition (DisCons) is filtered, a distance observation point set OP (t, p, v) can be obtained, and the distance observation point set OP (t, p, v) meets the illumination constraint condition (IllCons) and the distance constraint condition (DisCons), so that the distance observation point set OP (t, p, v) can be further divided into a same-plane observation point set XOP (t, p, v) and an out-of-plane observation point set YOP (t, p, v).
The observation points included in the same-plane observation point set XOP (t, p, v) are suitable for the circumvolve flight of the observation star, and the observation points included in the different-plane observation point set YOP (t, p, v) are suitable for the glancing flight of the observation star; the general round-the-fly is suitable for coplanar targets, the glancing-the-fly is suitable for different-surface targets, the running inclination angle of two stars is smaller than 0.05 degrees when the two stars meet in a coplanar mode, and the running inclination angle is larger than or equal to 0.05 degrees when the two stars meet in a different-surface mode.
The track of the observation star on the target star around the object is generally elliptical, the process of continuous around imaging reconnaissance is realized, the observation star sweeps the target star, the track of the observation star is generally 30-50 km below the target star, and the imaging reconnaissance on the target is realized by utilizing track drift.
For the acquired distance observation point set IP (T, p, v) is established according to a coordinate system of the target star orbit information T (T, p, v), the distance observation point set IP (T, p, v) is converted into a universal earth inertial coordinate system for convenient operation and dynamic display, and the conversion can be performed through a conversion matrix Q from the target star orbit information coordinate system to the earth inertial coordinate system; the distance observation point set OP (t, p, v) is converted into an inertial coordinate observation point set TP (t, p, v) in the earth inertial coordinate system by the conversion matrix Q.
The obtained inertial coordinate observation point set TP (t, p, v) is an observation point set meeting illumination conditions and distance constraints, and various approaching observation schemes and multiple mechanical entry points can be formed according to the observation point set.
In practical application, the maneuvering capability of the observation star needs to be further considered, the inertial coordinate observation point set TP (t, p, v) is optimized, an optimal maneuvering entering scheme is formed, and the optimal maneuvering entering point OB (t, p, v) is selected.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
It is to be understood that the terms "center," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counter-clockwise," "axial," "radial," "circumferential," and the like are directional or positional relationships as indicated based on the drawings, merely to facilitate describing the invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be configured and operated in a particular orientation, and therefore should not be construed as limiting the invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
Claims (2)
1. The method for selecting the orbit maneuver entry point of the observation star considering the constraint is characterized by comprising the following steps:
s1, acquiring target star information TInfo, observation star information CInfo and an observation constraint parameter ObsCons, analyzing the target star information TInfo, the observation star information CInfo and the observation constraint parameter ObsCons, and verifying the observation rationality;
s2, screening and obtaining an observation point set IP (t, p, v) according to the target star information TInfo, the observation star information CInfo and the observation constraint parameter ObsCons;
s3, performing distance constraint condition DisCons screening on the observation point set IP (t, p, v) obtained by screening to obtain a distance observation point set OP (t, p, v);
s4, converting the acquired observation point set OP (t, p, v) into an earth inertial coordinate system to acquire an inertial coordinate observation point set TP (t, p, v);
s5, screening an inertial coordinate observation point set TP (t, p, v) through observation satellite observation maneuver constraint to obtain an optimal maneuver entry point OB (t, p, v);
in the step S1, a step of, in the above-mentioned step,
the target star information TInfo includes: target star orbit information T (T, p, v), target star platform maneuver information TOMInfo; and target star load information TplayLoad;
the observation star information CInfo includes: the observation star orbit information C (t, p, v), the observation star platform maneuver information COMInfo and the observation star load information CplayLoad;
the step of screening and obtaining the observation point set IP (t, p, v) in S2 includes:
s21, calculating sun position information S (T, p, v) and moon position information M (T, p, v) at the same moment according to target star orbit information T (T, p, v), and acquiring an illumination constraint condition IllCons;
s22, constructing virtual star orbit information OtmpC (ti, p, v) according to the star orbit information C (t, p, v);
s23, screening the virtual observation star orbit information OtmpC (ti, p, v) according to the target star orbit information T (T, p, v), the sun position information S (T, p, v), the moon position information M (T, p, v) and the illumination constraint condition IllCons to obtain an observation point set IP (T, p, v) meeting the illumination condition;
the distance observation point set OP (t, p, v) in S3 includes a same-plane observation point set XOP (t, p, v) and a different-plane observation point set YOP (t, p, v);
the observation points included in the same-plane observation point set XOP (t, p, v) are suitable for observing satellite around flight, and the observation points included in the different-plane observation point set YOP (t, p, v) are suitable for observing satellite glancing flight;
the step of obtaining the inertial coordinate observation point set TP (t, p, v) in S4 includes:
s41, establishing a conversion matrix Q from a target star orbit information coordinate system to an earth inertia coordinate system;
s42, converting the distance observation point set OP (t, p, v) into an inertial coordinate observation point set TP (t, p, v) point under an earth inertial coordinate system through a conversion matrix Q.
2. A method of selecting a constraint-considered orbital maneuver entry point for an observed star as defined in claim 1 wherein: the distance constraint condition DisCons screening in the S3 comprises observation distance screening and safety distance screening.
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| 一种载人小行星探测目标星初选方法;赵建文;李人杰;王晓慧;韩潮;夏人伟;;载人航天(06);75-80 * |
| 敏捷凝视卫星密集点目标聚类与最优观测规划;耿远卓;郭延宁;李传江;马广富;李文博;;控制与决策(03);104-112 * |
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