CN115009545A - Perturbation self-adaptive correction high-precision maintaining method for satellite formation configuration objects - Google Patents
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Abstract
The invention discloses a perturbation self-adaptive correction high-precision maintaining method for satellite formation configuration targets, which comprises the following steps of: establishing a satellite formation configuration shooting divergence model based on a near-circular orbit E/I vector relative motion equation; establishing an eccentricity vector configuration target prediction model based on a satellite formation configuration forming mechanism and a shooting divergence characteristic; establishing a prediction model of the semi-major axis difference of formation configuration targets based on the divergence principle of formation configuration parameters; based on a Gaussian perturbation equation, a fuel optimal two-pulse position control scheme in a formation configuration plane is designed, and a satellite formation configuration target is adaptively corrected based on the fuel optimal two-pulse position control scheme. By adopting the control target prediction method of formation configuration ingested divergence compensation, the problem that partial parameters of a two-pulse ignition control strategy cannot be accurately controlled is solved, and the effects of low two-pulse ignition frequency and long control period are realized.
Description
Technical Field
The invention belongs to the field of satellite formation configuration, and particularly relates to a perturbation self-adaptive correction high-precision maintaining method for satellite formation configuration targets.
Background
Aiming at the formation configuration maintaining technology, spark controls the formation satellite configuration of the circular reference orbit by adopting an LQR controller, and Vaddi researches the configuration maintaining problem of the elliptical reference orbit formation satellite based on a linearized T-H equation. Since the motion between the formation satellites is nonlinear in nature, a controller designed based on a linearized kinetic equation inevitably brings about method errors. Queiroz et al propose a nonlinear adaptive controller based on a nonlinear dynamical equation, which is used for controlling and maintaining configuration of formation satellites under a nonlinear condition. The literature mostly uses the perturbation force of natural space as an interference factor, and the propellant carried by the formation satellite is used for eliminating the interference factor, so that excessive energy is consumed, and the fuel is excessively consumed. The invention researches the influence of the perturbation of the natural space on the formation of the satellite, and provides a configuration maintenance control method of the self-adaption perturbation of the target in a mode of actively utilizing the natural perturbation.
Disclosure of Invention
The invention aims to provide a perturbation self-adaptive correction high-precision maintaining method for satellite formation configuration objects, which aims to solve the problems in the prior art.
In order to achieve the aim, the invention provides a perturbation self-adaptive correction high-precision maintaining method for satellite formation configuration targets, which comprises the following steps:
establishing a satellite formation configuration shooting and dispersion model based on a near-circular orbit E/I vector relative motion equation, and analyzing a formation configuration shooting and dispersion mechanism by carrying out satellite formation configuration shooting and dispersion quantitative simulation analysis to obtain a formation configuration shooting and dispersion mechanism research result;
respectively establishing a satellite formation configuration photographic eccentricity vector and a semi-major axis difference target prediction model based on the research result of the formation configuration photographic divergence mechanism to obtain a formation configuration photographic target prediction target;
and designing a fuel optimal two-pulse position control scheme in a formation configuration plane by taking the formation configuration photographed target prediction target as an object based on a Gaussian perturbation equation, and performing self-adaptive correction on the satellite formation configuration target based on the fuel optimal two-pulse position control scheme.
Optionally, the process of establishing the satellite formation configuration shot divergence model comprises:
assuming that the relative position change amount is zero under the pulse ignition condition, constructing a common orbit control Gaussian perturbation equation;
setting a theoretically designed nominal configuration parameter and a parameter of formation at any time, and acquiring a formation configuration maintenance control target.
Optionally, the common orbit control gaussian perturbation equation is:
the formation configuration maintenance control objectives are:
in the formula (I), the compound is shown in the specification,
it is the formation configuration that maintains the maximum amount of divergence allowed relative to nominal parameters,
for the nominal configuration parameter, δ α i Is a parameter at any time of formation.
Optionally, the process of separately establishing the satellite formation configuration photographic eccentricity vector and the semimajor axis difference target prediction model comprises:
given a threshold δ E for the E vector maintenance control requirement in the formation plane max When the formation configuration real-time state δ e satisfies the following formula
||δe-δe nom ||≥δe max
Starting a formation configuration maintaining control operation, and keeping the formation configuration parameters in a use range; and taking the symmetric value of the E vector divergence threshold relative to the nominal value as a target, and calculating the maintenance control target.
Optionally, the calculation method of the maintenance control target is as follows:
in the formula, δ e man In order to maintain the control target(s),
the maximum allowable divergence amount is maintained and controlled by the amplitude and the angle of the relative eccentricity E vector and is calculated as
In the formula,. DELTA.u M The amplitude and angle difference of the latitude of the main satellite in the control process is maintained for two pulses.
Optionally, the process of establishing a prediction model of the semi-major axis difference of the formation configuration target includes:
in the two-pulse maintaining control process, a constant offset is caused along the track direction;
between two times of maintaining control, the constant offset along the track is diffused at an approximately stable speed;
calculating a semi-long axis active bias target to enable the semi-long axis active bias target delta a man The constant offset after ignition is restrained, and the semi-major axis active bias target is kept within the target in the application range.
Optionally, the method for calculating the semi-major axis active bias target includes:
where Δ t is the control period, δ u tot Is the variation of relative latitude amplitude angle between formation stars in the time interval (delta t-pi/n) between the second pulse of the period and the first pulse of the next periodChemical quantity is expressed as
δu tot ＝δu T -δu-δu δv -δu δa -δu J2 -δu D -δu env
In the formula, delta u is the relative latitude argument between formation stars before the first pulse; delta u δv Is expressed as δ v t1 At u M2 ～u M1 The delta u change caused in the interval is expressed as
δu δa Denotes that delta a is at u before the first pulse M2 ～u M1 The delta u change caused in the interval is expressed as
δu D Represents the delta u variation caused by the atmospheric resistance in a single maintenance control period, and is expressed as
δu T Is the expected inter-satellite relative latitude argument, δ u, at the end of a single maintenance control cycle env Is the relative latitude argument change due to the ambient force perturbation excluding the J2 perturbation and the atmospheric resistance perturbation; instinct and nominal target delta u nom The concept of symmetry, approximately
Finally, δ a can be obtained man
Optionally, the process of designing a fuel-optimal two-pulse position control scheme in the formation configuration plane comprises:
the fuel-optimal two-pulse maintenance control scheme is represented as:
the invention has the technical effects that:
the invention provides a configuration target prediction method of formation uptake divergence based on the symmetrical arrangement thought of a configuration retention control target, adopts a perturbation quantity active full compensation control method to realize the formation retention control effect of the optimal long period of fuel, solves the problem that partial parameters of a two-pulse ignition control strategy can not be accurately controlled by adopting the control target prediction method of formation uptake divergence compensation, and realizes the effects of low two-pulse ignition frequency and long control period.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the application and, together with the description, serve to explain the application and are not intended to limit the application. In the drawings:
fig. 1 is a flowchart of a perturbation adaptive correction high-precision maintaining method for satellite formation configuration objects in an embodiment of the invention.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that the steps illustrated in the flowcharts of the figures may be performed in a computer system such as a set of computer-executable instructions and that, although a logical order is illustrated in the flowcharts, in some cases, the steps illustrated or described may be performed in an order different than presented herein.
Example one
As shown in fig. 1, the present embodiment provides a perturbation adaptive correction high-precision maintaining method for satellite formation configuration objects, including:
step one, establishing a shooting and diverging model of satellite formation configuration according to a near-circular orbit E/I vector relative motion equation;
assuming that the relative position change amount is zero under the condition of pulse ignition, the common orbit control Gaussian perturbation equation can be obtained as
Formation configuration maintenance is to eliminate the divergence caused by spatial disturbance to the configuration, so that formation configuration parameters always meet certain application requirements. Assuming a theoretical design with nominal configuration parameters of
The parameter at any time of formation is delta alpha i Then the formation configuration maintenance control objective can be described as
In the formula (I), the compound is shown in the specification,
it is the formation configuration that maintains the maximum amount of divergence allowed relative to the nominal parameters.
Step two, establishing an eccentricity ratio vector configuration target prediction model based on a satellite formation configuration forming mechanism and a shooting divergence characteristic;
in the formation configuration E vector plane (delta E plane), under the influence of J2 items of main perturbation force, relative eccentricity vectors (E vectors) in the formation plane are circular motion with approximately constant amplitude and only phase change.
Given a threshold δ E for the E vector maintenance control requirement in the formation plane max When the formation configuration real-time state δ e satisfies the following formula
||δe-δe nom ||≥δe max
The formation configuration maintaining control operation needs to be started, and the formation configuration parameters are kept within the use range. Taking the symmetric value of the divergence threshold value of the E vector relative to the nominal value as a target, namely calculating a maintenance control target delta E man Is composed of
In the formula (I), the compound is shown in the specification,
the maximum allowable divergence is maintained and controlled by the amplitude and the angle of the relative eccentricity E vector, and can be calculated as
In the formula,. DELTA.u M The amplitude and angle difference of the latitude of the main satellite in the control process is maintained for two pulses.
Step three, establishing a prediction model of the semi-major axis difference of the formation configuration target according to the divergence principle that the formation configuration parameters are influenced by J2 perturbation force and atmospheric resistance;
in the two-pulse maintenance control process, in order to eliminate the divergence amount of the relative eccentricity vector (E vector) in the formation plane, a constant offset is caused in the track direction. Between the two maintenance controls, the constant offset along the track diverges at an approximately steady rate, subject to the semi-major axis maintenance control residual and the J2 perturbation. Semi-major axis active bias target delta a man If the suppression of the post-ignition constant offset amount can be achieved,and the target of the method in the application range can be ensured, and the task application requirement can be met.
According to the application requirement of active bias of the semimajor axis and the principle of long-term drift along the flight path caused by formation of the semimajor axis, the delta a can be obtained man Is composed of
Where Δ t is the control period, δ u tot Is the variation of relative latitude amplitude angle between formation stars in the time interval (delta t-pi/n) between the second pulse of the period and the first pulse of the next period, and can be expressed as
In the formula, delta u is the relative latitude argument between formation stars before the first pulse; delta u δv Is expressed as δ v t1 At u M2 ～u M1 The delta u change caused in the interval can be expressed as
δu δa Denotes that delta a is at u before the first pulse M2 ～u M1 The delta u change caused in the interval can be expressed as
δu D Represents the delta u variation caused by atmospheric resistance in a single maintenance control period, and can be expressed as
δu T Is the expected inter-satellite relative latitude argument, δ u, at the end of a single maintenance control cycle env Is the amount of relative latitude amplitude change caused by environmental force perturbations in addition to the J2 perturbation and the atmospheric resistance perturbation. Instinct and nominal target delta u nom The concept of symmetry can be approximated as
Finally, δ a can be obtained man
Designing an optimal two-pulse position control method for the fuel in the formation configuration plane based on a Gaussian perturbation equation;
the optimal two-pulse maintenance control method for the fuel in the formation configuration plane can be expressed as
The above description is only for the preferred embodiment of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A perturbation self-adaptive correction high-precision maintaining method for satellite formation configuration targets is characterized by comprising the following steps:
establishing a satellite formation configuration shooting and dispersion model based on a near-circular orbit E/I vector relative motion equation, and analyzing a formation configuration shooting and dispersion mechanism by carrying out satellite formation configuration shooting and dispersion quantitative simulation analysis to obtain a formation configuration shooting and dispersion mechanism research result;
respectively establishing a satellite formation configuration photographic eccentricity vector and a semi-major axis difference target prediction model based on the research result of the formation configuration photographic divergence mechanism to obtain a formation configuration photographic target prediction target;
and designing a fuel optimal two-pulse position control scheme in a formation configuration plane by taking the formation configuration photographed target prediction target as an object based on a Gaussian perturbation equation, and performing self-adaptive correction on the satellite formation configuration target based on the fuel optimal two-pulse position control scheme.
2. The perturbation self-adaptive correction high-precision keeping method for the satellite formation configuration targets as claimed in claim 1, wherein the process of establishing the satellite formation configuration shot divergence model comprises the following steps:
assuming that the relative position change amount is zero under the pulse ignition condition, constructing a common orbit control Gaussian perturbation equation;
setting the nominal configuration parameters of theoretical design and the parameters of formation at any time, and acquiring the formation configuration maintenance control target.
3. The perturbation self-adaptive correction high-precision keeping method for the satellite formation configuration targets according to claim 2, wherein the common orbit control Gaussian perturbation equation is as follows:
the formation configuration maintenance control objectives are:
in the formula (I), the compound is shown in the specification,
it is the formation configuration that maintains the maximum amount of divergence allowed relative to nominal parameters,
for the nominal configuration parameter, δ α i Is a parameter at any time of formation.
4. The perturbation self-adaptive correction high-precision keeping method for the satellite formation configuration targets according to claim 1, wherein the process of respectively establishing the satellite formation configuration photographic eccentricity vector and the semimajor axis difference target prediction model comprises the following steps:
given a threshold δ E for the E vector maintenance control requirement in the formation plane max When the formation configuration real-time state δ e satisfies the following formula
||δe-δe nom ||≥δe max
Starting a formation configuration maintaining control operation, and keeping the formation configuration parameters in a use range; and taking a symmetrical value of the E vector divergence threshold relative to the nominal value as a target, and calculating a maintenance control target.
5. The perturbation self-adaptive correction high-precision keeping method for the satellite formation configuration targets according to claim 4, wherein the calculation method for maintaining the control targets is as follows:
in the formula, δ e man In order to maintain the control target(s),
the maximum allowable divergence amount is maintained and controlled by the amplitude and the angle of the relative eccentricity E vector and is calculated as
In the formula,. DELTA.u M The amplitude and angle difference of the latitude of the main satellite in the control process is maintained for two pulses.
6. The perturbation self-adaptive correction high-precision keeping method for the satellite formation configuration targets as claimed in claim 1, wherein the process of establishing the prediction model of the semi-major axis difference of the formation configuration targets comprises the following steps:
in the two-pulse maintaining control process, a constant offset is caused along the track direction;
between two times of maintaining control, the constant offset along the track is diverged at an approximately stable speed;
calculating a semi-long axis active bias target to enable the semi-long axis active bias target delta a man The constant offset after ignition is restrained, and the semi-major axis active bias target is kept within the target in the application range.
7. The perturbation self-adaptive correction high-precision maintaining method for the satellite formation configuration targets according to claim 6, wherein the calculation method for the semi-major axis active bias targets is as follows:
where Δ t is the control period, δ u tot Is the variation of relative latitude amplitude angle between formation stars in the time interval (delta t-pi/n) between the second pulse of the period and the first pulse of the next period, and is expressed as
In the formula, delta u is the relative latitude argument between formation satellites before the first pulse; delta u δv Is expressed as δ v t1 At u M2 ～u M1 The amount of delta u change caused in the interval is expressed as
δu δa Denotes that delta a is at u before the first pulse M2 ～u M1 The amount of delta u change caused in the interval is expressed as
δu D Represents the delta u variation caused by the atmospheric resistance in a single maintenance control period, and is expressed as
δu T Is the expected inter-satellite relative latitude argument, δ u, at the end of a single maintenance control cycle env Is the relative latitude argument change due to the ambient force perturbation excluding the J2 perturbation and the atmospheric resistance perturbation; instinct and nominal target delta u nom The concept of symmetry, approximately
Finally, δ a can be obtained man
8. The perturbation adaptive correction high precision preservation method for satellite formation configuration targets according to claim 1, wherein the process of designing a fuel optimal two-pulse position control scheme in the formation configuration plane comprises:
the fuel-optimal two-pulse maintenance control scheme is represented as:
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Application publication date: 20220906 |