A method for designing a common path on the orbital plane for multi-target observation of satellite clusters in synchronous orbit

Abstract

The present invention discloses a method for designing a common path of a synchronous orbit star cluster multi-target observation orbital plane, comprising: obtaining orbital ephemeris of n target stars of a synchronous orbit star cluster and initial orbital ephemeris of an observation satellite; establishing a common path model of an observation orbital plane of the observation satellite, and forming an objective function model formula of the common path of the observation orbital plane of the observation satellite through multiple observation quantities; establishing a preset iterative algorithm model, and traversing and solving the extreme value points of the objective function model formula; setting a threshold ε( of the preset iterative algorithm model; when the extreme value point of the objective function model formula is less than or equal to the threshold ε(, the operation is stopped, and the optimal common path of the observation orbital plane is obtained. In this embodiment, by adopting a single orbital plane control to establish an invariant common path of the observation plane, while satisfying the maximum effective observation of the observation target, the node single-satellite multi-batch orbital plane control is avoided, and the fuel consumption is greatly saved.

Description

Technical Field

[0001] The disclosed embodiments relate to the field of satellite observation technology, and in particular to a method for designing a common path for an orbital plane for multi-target observation of a star cluster in a synchronous orbit. Background Art

[0002] The geosynchronous orbit belt (GEO orbit belt for short) refers to a 360° ring belt with a width of 22077km within the range of ±15° inclination at 35785km above the earth's equator. The dynamic characteristics of the geosynchronous orbit belt itself give it good coverage stability relative to the surface, that is, the satellites on the orbit belt have the same or similar angular velocity as the earth's rotation. From the ground, the satellites on the orbit belt are stationary relative to the ground, so that the satellites arranged in the orbit belt can stare at fixed areas on the ground for a long time without interruption for 24 hours. Therefore, the geosynchronous orbit belt has become a gathering place for high-value space assets in the fields of modern navigation and communication, data relay, meteorological observation, etc. Therefore, the monitoring of in-orbit satellites is one of the important contents of in-orbit services, which can provide support for the maintenance, replenishment and operation management of satellites.

[0003] At present, the imaging of the target star in the synchronous orbit is to place the high-orbit observer above or below the synchronous orbit, so that it drifts westward (above the synchronous orbit) or eastward (below the synchronous orbit) at a certain drift rate, and use the relative motion between the observer and the geostationary orbit (GEO satellite), such as Figure 1 As shown, the high-orbit observer realizes observation and imaging of each target star when it intersects with each target star in turn.

[0004] Since the orbital plane of most target stars in the synchronous orbit belt is close to the equatorial plane, the conventional imaging path design of the target stars in the synchronous orbit belt selects the equatorial plane as the observation orbital plane. Only by controlling the orbital altitude of the observer and dynamically adjusting the drift rate of the observer, a reasonable rendezvous timing between the observer and the target stars at each longitude node is established to realize the observation of the target stars at each longitude node in the observation belt.

[0005] However, the conventional design idea of ​​the observation imaging path of the target star in the synchronous orbit essentially assumes the premise that the orbital plane of the observed target star is the equatorial plane (i≈0°, i≈is the orbital inclination), and does not use the actual orbit of the target star as the observation quantity to establish the observation orbital plane in a targeted manner. In practical engineering applications, if the conventional observation path design idea is adopted, during the observation of the target star with a large orbital inclination, due to the large normal rendezvous speed of the binary star and the short observation time, a large number of target stars will miss the effective observation opportunity, and the observation imaging efficiency is low, which cannot meet the observation task requirements.

[0006] Therefore, it is necessary to improve one or more problems existing in the above-mentioned related technical solutions.

[0007] It should be noted that this section is intended to provide background or context for the technical solutions of the present disclosure stated in the claims. The description herein is not admitted to be prior art by virtue of being included in this section. Summary of the invention

[0008] The purpose of the embodiments of the present disclosure is to provide a method for designing a common path for a multi-target observation orbital plane of a synchronous orbital belt star cluster, thereby overcoming one or more problems caused by the limitations and defects of related technologies at least to a certain extent.

[0009] The present disclosure provides a method for designing a common path for a multi-target observation orbital plane of a synchronous orbit with a star cluster, comprising:

[0010] Obtain the orbital ephemeris of n target stars in the synchronous orbit constellation and the initial orbital ephemeris of the observation satellite;

[0011] Establishing a common path model of the observation orbital plane of the observation satellite, setting a plurality of observation quantities corresponding to the orbital planes of the n target stars through the orbital ephemeris of the target star, and setting the common path of the observation orbital plane of the observation satellite, so as to form an objective function model formula of the common path of the observation orbital plane of the observation satellite through the plurality of observation quantities;

[0012] Establishing a preset iterative algorithm model to traverse and solve the extreme value points of the objective function model formula;

[0013] Setting a threshold ε of the preset iterative algorithm model;

[0014] When the extreme value point of the objective function model formula is less than or equal to the threshold ε, the operation is stopped, and at this time, the observed orbital surface common path in the objective function model formula is the optimal observed orbital surface common path;

[0015] The operating orbit of the observation satellite is adjusted according to the common path of the optimal observation orbital plane, and the orbital ephemeris of the observation satellite is updated.

[0016] In one embodiment of the present disclosure, establishing the common path model of the observation orbital plane of the observation satellite includes:

[0017] Assume that the plurality of observed quantities are Let the common path of the observed orbital plane be X G (i G ,Ω G ), where i is the orbital inclination and Ω is the right ascension of the ascending node;

[0018] Establish a celestial coordinate system, select the kth observation target among the n target stars, project the observation satellite and the kth observation target in the celestial coordinate system, and set the orbital inclination and ascending node right ascension of the kth observation target to Assume that the angle between the observation satellite orbital plane and the kth observation target orbital plane is

[0019] In the celestial coordinate system, according to the spherical cosine theorem, the common path X of the observation orbital plane is established. G (i G ,Ω G ) and the angle and the kth observation target Relation (1):

[0020]

[0021] In one embodiment of the present disclosure, establishing the common path model of the observation orbital plane of the observation satellite further includes:

[0022] The common path X through the observation orbital surface G (i G ,Ω G ) and a plurality of the observed quantities X M The target stars form an angle cluster α;

[0023] The common path X of the observation satellite observation orbital plane is established according to the sum of the squares of the angle cluster α G The objective function model is (2):

[0024]

[0025] In one embodiment of the present disclosure, the step of establishing a preset iterative algorithm model and traversing to solve the extreme value points of the objective function model formula includes:

[0026] Let O(i G ,Ω G ) is equal to zero, and we get formula (3):

[0027]

[0028] Wherein, the solution of the formula (3) is the extreme point of the objective function model formula (2);

[0029] Using Newton's iteration method, the observed value X M The objective function model formula (2) is traversed and solved.

[0030] In one embodiment of the present disclosure, the step of traversing and solving the objective function model formula (2) includes:

[0031] make

[0032] Newton iteration solves equation (4) as:

[0033]

[0034] X 0 is the initial value of X, which is:

[0035] Substitute the initial value into formula (4) for iterative calculation, and the calculation formula is as follows:

[0036]

[0037] If X j+1 -X j ≤ε, then stop the iterative calculation, then X j+1 The solution is the extreme point of the objective function model formula (2).

[0038] In one embodiment of the present disclosure, the X j+1 Solution Substitute into the second-order derivative formula (6) of the objective function model:

[0039]

[0040] If equation (6) holds true, then when the common path of the observation satellite observation orbital plane is O reaches its minimum extreme point.

[0041] In one embodiment of the present disclosure, the step of establishing a common path model of the observation orbital plane of the observation satellite includes:

[0042] The weight values ​​corresponding to the n target stars in the synchronous orbit star cluster are set.

[0043] In one embodiment of the present disclosure, the method further includes:

[0044] The observation satellite observes the n target stars along the common path of the optimal observation orbital plane, and dynamically adjusts the drift rate of the observation satellite to improve the observation imaging quality of a single target star.

[0045] In one embodiment of the present disclosure, the threshold ε=10 -5 .

[0046] The technical solution provided by the embodiments of the present disclosure may have the following beneficial effects:

[0047] A method for designing a common path for multi-target observation of a synchronous orbit with a star cluster in the disclosed embodiment establishes a common path for an invariant observation surface by adopting a single orbital plane control. While satisfying the maximum effective observation of the observation targets, it avoids the orbital plane control of multiple batches of a single star at a node, thereby greatly saving fuel consumption. In addition, compared with conventional equatorial plane observation paths, it solves the problem of difficulty in screening and observing targets with large inclination angles, thereby greatly improving the effective observation coverage of targets. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] The accompanying drawings herein are incorporated into the specification and constitute a part of the specification, illustrate embodiments consistent with the present disclosure, and together with the specification are used to explain the principles of the present disclosure. Obviously, the accompanying drawings described below are only some embodiments of the present disclosure, and for ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without creative work.

[0049] Figure 1 A schematic diagram showing the sequential rendezvous observation of multiple target stars in a synchronous orbit star cluster in the prior art is shown;

[0050] Figure 2 A flow chart of a method for designing a common path for a multi-target observation orbital plane of a synchronous orbital belt star cluster in an exemplary embodiment of the present disclosure is shown;

[0051] Figure 3 A geometrical schematic diagram showing the establishment of a common path objective function model for the orbital plane of multiple target stars in a synchronous orbital star cluster in an exemplary embodiment of the present disclosure is shown;

[0052] Figure 4 A flowchart of optimizing the common path of the orbital plane of multiple target stars in a synchronous orbital zone star cluster in an exemplary embodiment of the present disclosure is shown;

[0053] Figure 5 A simulation diagram comparing the angle difference between the optimized orbit, 0 inclination, and the original orbit and the target constellation in an exemplary embodiment of the present disclosure is shown;

[0054] Figure 6 A comparison diagram of imaging effects of 0.5° / day optimized orbit, 0 inclination and original orbit traversal observation path in an exemplary embodiment of the present disclosure is shown;

[0055] Figure 7 A simulation diagram comparing the angle difference between the optimized orbit, 0 inclination, and the original orbit and the target constellation in an exemplary embodiment of the present disclosure is shown;

[0056] Figure 8 The imaging effect of 0.5° / day optimized orbit, 0 inclination and original orbit traversal screening target observation path in the exemplary embodiment of the present disclosure is shown. DETAILED DESCRIPTION

[0057] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in a variety of forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that the disclosure will be more comprehensive and complete and to fully convey the concepts of the example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0058] In addition, the accompanying drawings are only schematic illustrations of the embodiments of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the figures represent the same or similar parts, and their repeated descriptions will be omitted. Some of the block diagrams shown in the accompanying drawings are functional entities and do not necessarily correspond to physically or logically independent entities.

[0059] This example implementation provides a method for designing a common path for a multi-target observation orbital plane of a synchronous orbital star cluster, which may include:

[0060] Step S101, obtaining the orbital ephemeris of n target stars in the synchronous orbit constellation and the initial orbital ephemeris of the observation satellite.

[0061] Step S102, establishing a common path model of the observation orbital plane of the observation satellite, setting a plurality of observation quantities corresponding to the orbital planes of the n target stars through the orbital ephemeris of the target stars, and setting the common path of the observation orbital plane of the observation satellite, so as to form an objective function model formula of the common path of the observation orbital plane of the observation satellite through the plurality of the observation quantities.

[0062] Step S103, establishing a preset iterative algorithm model, and traversing to solve the extreme value points of the objective function model formula.

[0063] Step S104, setting a threshold ε of the preset iterative algorithm model.

[0064] Step S105, when the extreme value point of the objective function model formula is less than or equal to the threshold ε, the calculation is stopped. At this time, the observed orbital surface common path in the objective function model formula is the optimal observed orbital surface common path.

[0065] Step S106, adjusting the operating orbit of the observation satellite according to the common path of the optimal observation orbital plane, and updating the orbital ephemeris of the observation satellite.

[0066] Specifically, the normal control quantity of the common path of the observation satellite orbital plane is compared with the huge fuel consumption properties in the tangential and radial directions. Based on the optimal effective observation of multi-target stars, the optimal observation orbital plane target quantity of the multi-target star orbital plane of the star cluster is sought, and the design concept of establishing and optimizing the common path of the observation orbital plane once and unchanged is proposed to reduce the control times of the normal control elements of the observation satellite and solve the problem of huge fuel consumption of the observation orbital plane in engineering practice.

[0067] In the celestial coordinate system, Figure 3 As shown in the figure, the correlation between the orbit angle between the observation satellite and the target satellite and the rendezvous velocity is used to invent and design the objective function model of the common path of the multi-orbital plane of the observation satellite. Through the least squares principle, the observation quantities of the multi-target orbital plane of the star cluster are iteratively solved, and the square sum of the angle target is minimized to meet the condition ε, and the optimal observation orbital plane target quantity of the common path objective function of the multi-orbital plane is found, and the problem of solving the common path control strategy of the observation orbital plane is solved.

[0068] like Figure 2 , 4 As shown, first, get the initial star cluster set Including the observation satellite and the orbit ephemeris of n target stars in the synchronous orbit belt constellation or two rows of roots; then, the threshold of the preset iterative algorithm model is set to ε, and the preset iterative algorithm can be a Newton iterative algorithm, but there is no specific restriction; then, the public path solution model is started, and the traversal optimization is performed to solve the objective function O(i G ,Ω G ) minimum value; when the extreme value of the objective function model is less than or equal to the threshold ε, the operation is stopped, and finally, the final X of the iteration is obtained. j It is to find the optimal common path of the observation satellite orbit plane. j In order to observe the orbital plane of the star cluster, the orbital plane is adjusted once to establish a common path for the unchanged observation orbital plane, so as to avoid the node single star multi-batch orbital plane control while meeting the maximum effective observation of the target star, greatly saving fuel consumption. In addition, compared with the conventional equatorial plane observation path, this embodiment solves the problem of difficulty in observing and screening target stars with large inclination angles, and greatly improves the effective observation coverage of the target.

[0069] In this implementation, by adopting a single orbital plane control and establishing a common path for an unchanging observation surface, while satisfying the maximum effective observation of the observation target, the node single-satellite multi-batch orbital plane control is avoided, thereby greatly saving fuel consumption. In addition, compared with the conventional equatorial plane observation path, the problem of difficulty in observing and screening targets with large inclination angles is solved, thereby greatly improving the effective observation coverage of the target.

[0070] Optionally, in step S102, in establishing the common path model of the observation orbital plane of the observation satellite, the following further comprises: step S1021, assuming that the plurality of observation quantities are Let the common path of the observed orbital plane be X G (i G ,Ω G ), where i is the orbital inclination, Ω is the right ascension of the ascending node; Step S1022, establish a celestial coordinate system, select the kth observation target among the n target stars, project the observation satellite and the kth observation target in the celestial coordinate system, and set the orbital inclination and the right ascension of the ascending node of the kth observation target to Assume that the angle between the observation satellite orbital plane and the kth observation target orbital plane is Step S1023, in the celestial coordinate system, according to the spherical cosine theorem, establish the common path X of the observation orbital plane G (i G ,Ω G ) and the angle and the kth observation target Relation (1):

[0071] Specifically, arbitrarily select the kth observation target star in the observation star cluster, and project the orbits of the observation satellite and the target star on the celestial sphere, such as Figure 3 As shown, Corresponding to the kth target star orbit inclination and ascending node right ascension, is the angle between the observation satellite orbital plane and the kth target satellite orbital plane in the celestial coordinate system, in the spherical triangle angle ΔABC: ∠ABC=π-i G .

[0072] In the celestial coordinate system, according to the spherical cosine theorem, the angle between the common path of the observation orbital plane and the orbital plane of the kth target star is established. Relationship with orbital elements (1):

[0073]

[0074] According to the angle between the common path of the observation satellite orbital plane and the target star The correlation between the binary star angle and the rendezvous velocity is such that when the objective function (1) is satisfied and the normal distance of the observation satellite is satisfied, the effective observation time for the kth observation target is the longest.

[0075] Optionally, in step S102, in establishing the observation orbital plane common path model of the observation satellite, the following further comprises: step S1024, through the observation orbital plane common path X G (i G ,Ω G ) and a plurality of the observed quantities X MThe target stars form an angle cluster α; step S1025, establishing the common path X of the observation satellite observation orbit plane according to the sum of the squares of the angle cluster α G The objective function model is (2):

[0076]

[0077] Specifically, the common path X of the observation orbital plane is adopted G (i G ,Ω G ) and observed star cluster X M Based on the idea of ​​the square sum of the target angles α, the objective function model of the common path orbital plane observed by multiple observations is established (2):

[0078]

[0079] In formula (2), is the orbital inclination and right ascension of the ascending node of the target satellite. According to the engineering characteristics that the normal direction of the orbital plane of the synchronous orbit satellite remains basically unchanged or changes slightly, the observation period is relatively short for the observation satellite, and the observation sample is taken as Fixed observations.

[0080] In addition, in order to find the common path X of the observation orbital plane that is closest to the set of observations of the orbital planes of all n target stars in the star cluster, G (i G ,Ω G ), the objective function model (2) can be solved. When the function reaches the minimum value, the orbital angle between the observation satellite and all target stars is optimized, the imaging time between the observation satellite and all stars in the target star cluster is the longest, and the maximum number of effective imaging targets is achieved.

[0081] Optionally, in step S103, a preset iterative algorithm model is established, and the process of traversing and solving the extreme value points of the objective function model formula also includes step S1031, setting O(i G ,Ω G ) is equal to zero, and we get formula (3): The solution of formula (3) is the extreme point of the objective function model formula (2); Step S1032, using the Newton iteration method, through the observation quantity X M The objective function model formula (2) is traversed and solved.

[0082] Specifically, to find the objective function O(i G ,Ω G ), let O(i G ,Ω G ) is equal to zero, and we get equation (3). The solution of equation (3) is the extreme point of the objective function (2). (3) Using the Newton iteration method, taking all the observed target star path elements of the star cluster as the observed quantities, the objective function model is traversed and solved.

[0083] Optionally, the step of traversing and solving the objective function model formula (2) includes: step S10321, let Newton iteration solves equation (4) as: X 0 is the initial value of X, which is: Step S10322, substitute the initial value into formula (4) for iterative calculation, the calculation formula is as follows:

[0084] Step S10322, if X j+1 -X j ≤ε, then stop the iterative calculation, then X j+1 The solution is the extreme point of the objective function model formula (2).

[0085] Specifically, iterate equation (5) until X j+1 -X j ≤ε, the iterative calculation is stopped. In one example, ε=10 -5 , but no specific restrictions are made; to obtain X j+1 Solution This is the extreme point of the objective function (2).

[0086] Optionally, the X j+1 Solution Substitute into the second-order derivative formula (6) of the objective function model: If equation (6) holds true, then when the common path of the observation satellite observation orbital plane is O reaches its minimum extreme point.

[0087] Specifically, X j+1 Solution i * and Ω * Check if The second-order derivative of the objective function model (6) is established, which proves that the common path of the observation orbital plane is O reaches its minimum value when .

[0088] At this time, the solution It is based on maximizing the number of observed target stars, taking into account the orbital control fuel consumption, and through an initial inclination control, forming a target orbital plane control target in which the target star cluster observation space orbital plane points to an unchanging common path.

[0089] Optionally, before the step S102 of establishing the observation orbital plane common path model of the observation satellite, the step S1011 includes setting weight values ​​corresponding to the n target stars in the synchronous orbital star cluster. Specifically, the weight value can be set as needed, and there is no limitation here. The setting of the weight value can increase the observation time of important target stars in the synchronous orbital star cluster.

[0090] Optionally, the method further includes step S107, wherein the observation satellite observes the n target stars along a common path of the optimal observation orbital plane, and dynamically adjusts the drift rate of the observation satellite to improve the observation imaging quality of a single target star.

[0091] Specifically, The star cluster observes the common path of the orbital plane, and based on the visibility of each target star in the star cluster, dynamically adjusts the drift rate of the observation satellite to achieve optimal imaging observation of a single target at a longitude node.

[0092] The engineering application effects are as follows:

[0093] Select the target constellation in the range of 50°E to 120°E in the synchronous orbit. Observe the original orbit of the satellite: 6 elements of the J2000 inertial system orbit, as shown in Table 1:

[0094] Table 1 The number of orbital elements of the original J2000 inertial system of the observed satellite

[0095] date Semi-major axis of orbit Eccentricity Orbital inclination Ascending node right ascension Argument of perigee Mean anomaly 20180416061000 42216045 0.00024 4.169 70.19 27.05 276.485911

[0096] Target constellation spatial position: Date: 00:00:00, October 24, 2018, in the format of TLE.

[0097] 1. Census Observation

[0098] The observed star cluster is 60 survey targets to be observed within an orbital inclination of 7°. Substitute the observed satellite and the star cluster TLE into equation (4) respectively, and exhaustively traverse the extreme value solution. Solve the target initial inclination orbit control optimization target quantity control quantity: O(i: 0.992608, Ω: 71.25188).

[0099] (1) Comparison between the optimal common path and the equatorial common path

[0100] Compare and analyze the angle differences between the optimized observation common path, the equatorial plane common path, and the initial orbit common path and the target orbits of the star cluster. Figure 5 shown.

[0101] (2) Imaging effect of multi-target observation of star cluster

[0102] The observation satellite drift rate is set to 0.5° / day. The input conditions are the same. The imaging distance of 150km meets the imaging conditions. The optimized observation common path, equatorial common path, and initial orbit common path are used respectively. The observation imaging effect simulation is as follows: Figure 6 As shown in Table 2, the observation effect statistics are as follows:

[0103] Table 2 Target observation statistics for optimized orbit, 0 inclination and original orbit observation paths

[0104]

[0105] 2. Screening and Observation of Key Targets

[0106] The observation constellation is 20 key observation targets in the range of 50° to 120° east longitude, among which there are more simulations of large-angle targets. The solution outputs the target initial inclination orbit control optimization target quantity control quantity: O(i:3.832337,Ω:63.134861).

[0107] (1) Public Path Comparison Simulation

[0108] Compare and analyze the angle differences between the optimized observation common path, equatorial plane common path, initial orbit common path and the target orbits of the star cluster. Figure 7 shown.

[0109] (2) Observation imaging effect

[0110] The observation drift rate is set to 0.5° / day. The input conditions are the same. The imaging distance of 150km meets the imaging conditions. The optimized observation common path, equatorial plane common path, and initial orbit common path are used respectively. The observation imaging effect simulation is as follows: Figure 8 As shown in Table 3, the observed effect statistics are as follows:

[0111] Table 3 Target observation statistics for optimized orbit, 0 inclination and original orbit observation paths

[0112]

[0113] 3. Effect Evaluation

[0114] (1) Star cluster survey effect

[0115] Under the same observation time conditions, the observation effect of the fitted optimized common path is the best during the 60-target observation survey, followed by the 0-inclination common path, and the original observation satellite orbit common path is the worst. The optimized common path is relatively close to the 0-inclination common path.

[0116] (2) Star cluster screening effect

[0117] Under the same observation time conditions, for the observations of 20 key screening targets, the optimized common path had the best observation effect, followed by the original observation satellite orbit common path, and the 0 inclination public path was the worst. The optimized common path was close to the 0 original observation satellite orbit public path, indicating that the optimized public observation path has the best imaging effect.

[0118] (3) Fuel consumption assessment

[0119] Fuel consumption analysis and evaluation were conducted for target survey observation, key screening target imaging effect and orbital plane establishment. When observing 60 targets, under the condition of the maximum observation effect of the number of observed targets in the constellation, the number of observations on the optimized common path orbit was the largest, and the orbit control saved 23.8% of fuel compared with the 0° inclination observation path; when observing and imaging key screening targets, the optimized orbit control saved 86% of fuel compared with the 0° inclination observation path.

[0120] When the initial orbit of the observation satellite remains unchanged and the observation effect is slightly different from the optimized observation path, the initial orbit is selected as the public observation path in consideration of fuel saving.

[0121] In the present disclosure, by adopting a single orbital plane control and establishing a common path for an invariant observation surface, while satisfying the maximum effective observation of the observation target, the node single-satellite multi-batch orbital plane control is avoided, and it has been applied in engineering practice, greatly saving fuel consumption; in addition, compared with the conventional equatorial plane observation path, it solves the problem of difficulty in screening and observing large-angle targets, and greatly improves the effective observation coverage of the target.

[0122] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0123] Those skilled in the art will readily appreciate other embodiments of the present disclosure after considering the specification and practicing the invention disclosed herein. This application is intended to cover any modification, use or adaptation of the present disclosure, which follows the general principles of the present disclosure and includes common knowledge or customary techniques in the art that are not disclosed in the present disclosure. The specification and examples are intended to be exemplary only, and the true scope and spirit of the present disclosure are indicated by the appended claims.

Claims

1. A method for designing a common path for multi-target observation of a constellation in a synchronous orbit. It is characterized in that include: Obtain the orbital ephemeris of n target stars in the synchronous orbit constellation and the initial orbital ephemeris of the observation satellite; Establishing a common path model of the observation orbital plane of the observation satellite, setting a plurality of observation quantities corresponding to the orbital planes of the n target stars through the orbital ephemeris of the target star, and setting the common path of the observation orbital plane of the observation satellite, so as to form an objective function model formula of the common path of the observation orbital plane of the observation satellite through the plurality of observation quantities; Establishing a preset iterative algorithm model to traverse and solve the extreme value points of the objective function model formula; Setting a threshold ε of the preset iterative algorithm model; When the extreme value point of the objective function model formula is less than or equal to the threshold ε, the operation is stopped, and at this time, the observed orbital surface common path in the objective function model formula is the optimal observed orbital surface common path; Adjusting the operating orbit of the observation satellite according to the common path of the optimal observation orbit plane, and updating the orbit ephemeris of the observation satellite; Establishing the common path model of the observation orbital plane of the observation satellite comprises: Assume that the plurality of observed quantities are Let the common path of the observed orbital plane be X G (i G ,Ω G ), where i is the orbital inclination and Ω is the right ascension of the ascending node; Establish a celestial coordinate system, select the kth observation target among the n target stars, project the observation satellite and the kth observation target in the celestial coordinate system, and set the orbital inclination and ascending node right ascension of the kth observation target to Assume that the angle between the observation satellite orbital plane and the kth observation target orbital plane is In the celestial coordinate system, according to the spherical cosine theorem, the common path X of the observation orbital plane is established. G (i G ,Ω G ) and the angle and the kth observation target Relation (1): Establishing the common path model of the observation orbital plane of the observation satellite also includes: The common path X through the observation orbital surface G (i G ,Ω G ) and a plurality of the observed quantities X M The target stars form an angle cluster α; The common path X of the observation satellite observation orbital plane is established according to the sum of the squares of the angle cluster α G The objective function model is (2):

2. According to the method for designing a common path for a multi-target observation orbital plane of a synchronous orbital belt star cluster according to claim 1, It is characterized in that The step of establishing a preset iterative algorithm model and traversing to solve the extreme value points of the objective function model formula includes: Let O(i G ,Ω G ) is equal to zero, and we get formula (3): Wherein, the solution of the formula (3) is the extreme point of the objective function model formula (2); Using Newton's iteration method, the observed value X M The objective function model formula (2) is traversed and solved.

3. According to the method for designing a common path for a multi-target observation orbital plane of a synchronous orbital belt constellation according to claim 1, It is characterized in that The steps of traversing and solving the objective function model formula (2) include: make Newton iteration solves equation (4) as: X 0 is the initial value of X, which is: Substitute the initial value into formula (4) for iterative calculation, and the calculation formula is as follows: If X j+1 -X j ≤ε, then stop the iterative calculation, then X j+1 The solution is the extreme point of the objective function model formula (2).

4. According to the method for designing a common path for a multi-target observation orbital plane of a synchronous orbital star cluster as described in claim 3, It is characterized in that The X j+1 Solution Substitute into the second-order derivative formula (6) of the objective function model: If equation (6) holds true, then when the common path of the observation satellite observation orbital plane is O reaches its minimum extreme point.

5. According to the method for designing a common path for a multi-target observation orbital plane of a synchronous orbital belt star cluster according to claim 1, It is characterized in that The step of establishing a common path model of the observation orbital plane of the observation satellite comprises: The weight values ​​corresponding to the n target stars in the synchronous orbit star cluster are set.

6. According to the method for designing a common path for a multi-target observation orbital plane of a synchronous orbital belt star cluster as described in claim 1, It is characterized in that The method further includes: The observation satellite observes the n target stars along the common path of the optimal observation orbital plane, and dynamically adjusts the drift rate of the observation satellite to improve the observation imaging quality of a single target star.

7. According to the method for designing a common path for a multi-target observation orbital plane of a synchronous orbital belt star cluster according to claim 1, It is characterized in that The threshold ε=10 -5 .

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