CN112193438A - Evaluation system and evaluation method for satellite orbit-in initial stage deflation disturbance - Google Patents
Evaluation system and evaluation method for satellite orbit-in initial stage deflation disturbance Download PDFInfo
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Abstract
The invention relates to an evaluation method of satellite orbit initial stage deflation disturbance, which comprises the following steps: (1) at the initial stage of satellite orbit entering, for a satellite suspected of generating the satellite body deflation disturbance, acquiring the telemetering data variable quantity of an actuating mechanism during the attitude disturbance through satellite telemetering; (2) calculating to obtain disturbance torque acting on three axes of a satellite body coordinate system during the attitude disturbance; (3) establishing a satellite deflation mechanical model based on the satellite configuration layout design and the mechanical parameters of possible deflation sites to obtain the relationship between the disturbance force and the disturbance torque of each axis of the satellite in the deflation disturbance process; (4) obtaining a criterion condition that the attitude disturbance phenomenon is satellite deflation disturbance according to the satellite flight time T, the disturbance force action duration delta T, the magnitude of the disturbance force F and the attitude disturbance phenomenon; (5) and judging the attitude disturbance phenomenon at the initial stage of satellite orbit entering through a criterion condition. The method and model of the invention provide a basis for on-orbit treatment of the deflation disturbance.
Description
Technical Field
The invention relates to a system and a method for evaluating satellite deflation disturbance.
Background
Because the satellite body and part of equipment have certain leakproofness, the satellite has the attitude disturbance caused by the deflation of the satellite body in the initial stage of orbit entering, and the safety of the satellite is endangered if the satellite is not processed in time. Therefore, the method has important significance for judging and treating the phenomenon of attitude disturbance caused by satellite deflation at the initial stage of satellite orbit entering.
In the process of satellite launching, the time from ignition takeoff to satellite-rocket separation is short, the external air pressure environment of the satellite changes rapidly, and the external surface of the satellite adopts strict thermal control coating measures due to the thermal control requirement, so that the external surface of the satellite has certain tightness, and the gas in the satellite is difficult to be completely discharged out of the satellite in a short time; and part of the in-satellite equipment also has certain tightness, and the process of finishing air release in the vacuum environment is a slow process. Therefore, in the initial stage of satellite orbit, there is an attitude disturbance phenomenon due to satellite deflation.
The satellite in-orbit working modes are basically three-axis stable modes, and in order to complete a specific payload task function, a specific attitude pointing requirement is required, and the satellite body deflation phenomenon inevitably causes attitude disturbance, so that the satellite task function can be influenced, and the satellite safety can be even endangered if the satellite is not processed in time. The actuating mechanism for controlling the satellite attitude comprises a reaction wheel, an air injection thruster, a gyro torquer and the like, and attitude disturbance caused by satellite air discharge is reflected to the state change of the actuating mechanism through an attitude control system, so that the rotating speed change of the reaction wheel, the frequent air injection of the thruster, the angle change of the gyro torquer and the like are caused. At present, no clear reference evaluation system and evaluation method exist for the deflation disturbance phenomenon and influence at the initial stage of satellite orbit entering; the evaluation system and the evaluation method of the satellite deflation disturbance need to be researched, the deflation disturbance phenomenon is judged through the telemetering change of the execution mechanism, the satellite deflation model is established, the estimation calculation of the deflation disturbance power and the evaluation on the disturbance magnitude and influence are realized, the targeted in-orbit treatment is carried out on the basis of the estimation calculation, and the influence of the deflation disturbance on the satellite pointing function and the satellite safety is avoided.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method comprises the steps of carrying out quantitative calculation and evaluation on attitude disturbance moment and disturbance force through telemetering change of a satellite executing mechanism, providing criterion conditions for carrying out deflation disturbance evaluation by adopting disturbance force, flight time and deflation duration, and providing a basis for in-orbit treatment of deflation disturbance.
The technical scheme adopted by the invention is as follows: a method for evaluating satellite orbit initial stage deflation disturbance comprises the following steps:
(1) at the initial stage of satellite orbit entering, for a satellite suspected of generating the satellite body deflation disturbance, acquiring the telemetering data variable quantity of an actuating mechanism during the attitude disturbance through satellite telemetering;
counting the jet accumulated time change condition of each thruster during the attitude disturbance period of the satellite adopting the jet thrusters for attitude control, and acquiring the jet working time [ delta t ] of each thruster during the attitude disturbance period1 Δt2 … Δtn](ii) a n is the number of attitude control thrusters configured by the satellite;
for satellites using reaction wheels for attitude control, for each reaction wheel during attitude disturbanceCounting the rotation speed variation situation to obtain the rotation speed variation [ delta w ] of each reaction wheel in the attitude disturbance period1 Δw2 … Δwm](ii) a m is the number of counteractive wheels configured for the satellite;
(2) and (3) calculating to obtain disturbance torque acting on three axes of the satellite body coordinate system during the attitude disturbance period through the telemetering data variable quantity of the actuating mechanism obtained in the step (1).
When the jet thruster is adopted to control the satellite attitude, the disturbance torque acting on three axes of the satellite body coordinate system during the attitude disturbance period is as follows:
in the formula mix，miy，mizThe moment components of the ith attitude control thruster on the X, Y and Z axes of the satellite body coordinate system are respectively theoretical moment components, delta T is attitude disturbance duration, and i is 1,2, 3.
When the reaction wheel is adopted to control the satellite attitude, the disturbance torque acting on three axes of a satellite body coordinate system during the attitude disturbance period is as follows:
in the formula
In order to counteract the nominal angular momentum of the wheel,
for nominal speed of reaction wheel, CwIs a mounting matrix for the reaction wheelsets.
The satellite body coordinate system is defined as: the origin of coordinates O is located at the center of mass of the satellite; the OX axis points to a certain characteristic axis direction of the satellite from the origin of coordinates and is parallel to the X axis of the satellite mechanical coordinate system; the OZ axis points to the other characteristic axis direction of the satellite from the origin of coordinates, is vertical to the OX axis and is parallel to the Z axis of a satellite mechanical coordinate system; the OY axis and the OX and OZ axes form a right-handed system.
Mounting matrix C of reaction wheel trainwIs defined as:
X^hm，Y^hm，Z^hmrespectively representing the angular momentum vectors h of the m-th reaction wheelmThe axis of the satellite body coordinate system X, Y, Z.
(3) And establishing a satellite deflation mechanical model based on the satellite configuration layout design and the mechanical parameters of possible deflation sites to obtain the relationship between the disturbance force and the disturbance torque of each axis of the satellite in the deflation disturbance process.
OXYZ is a satellite body coordinate system, P is any possible deflation site on the satellite surface, and the coordinate of P under the satellite body coordinate system is [ P ]x Py Pz](ii) a The reaction force generated by the satellite deflation is F, and the component of F on the three axes of the satellite body coordinate system is [ Fx Fy Fz]. The relationship between the reaction force of the bleed air to the satellite and the disturbance torque can be calculated by the following equation:
the reaction force of the deflation on the satellite is:
(4) and after the disturbance force is obtained through calculation, judging the attitude disturbance phenomenon according to the satellite flight time T, the disturbance force action time delta T and the disturbance force F.
TltdFor a set maximum flight time, Δ T, at which the phenomenon of deflation may occurmin,ΔTmax]For the possible range of set deflation duration, [ Fmin,Fmax]Disturbance of bleed air to setThe range of possible magnitudes of force. The criterion for the attitude disturbance phenomenon as satellite deflation disturbance is as follows:
T<Tltd，
and Δ Tmin<ΔT<ΔTmax，
And Fmin<F<Fmax
(5) And (4) judging the attitude disturbance phenomenon at the initial stage of satellite orbit entering through the criterion condition in the step (4), and if the criterion condition in the step (4) is met, judging that the attitude disturbance phenomenon is disturbance caused by satellite body deflation. After the attitude disturbance phenomenon is determined to be deflation disturbance, corresponding treatment measures are taken according to a satellite attitude control mode, and the method specifically comprises the following steps:
a) if the satellite adopts the jet thruster to carry out attitude control when the deflation disturbance occurs, measures for maintaining a jet control mode are adopted, the thruster is used for jetting air to counteract the influence of the deflation disturbance torque, and after the deflation disturbance phenomenon disappears, the satellite is switched to a long-term reaction wheel control mode;
b) if the satellite adopts the reaction wheel to perform attitude control when the deflation disturbance occurs, the satellite is switched to a gas injection control mode, the reaction wheel is reset to a set safe rotating speed, and after the deflation disturbance phenomenon disappears, the satellite is switched to a long-term reaction wheel control mode.
The system for evaluating the satellite orbit initial stage deflation disturbance, which is constructed according to the evaluation method, comprises the following steps:
the first module is used for acquiring the telemetering data variable quantity of an actuating mechanism during attitude disturbance for a satellite suspected of generating the satellite deflation disturbance phenomenon at the initial stage of satellite orbit entering through satellite telemetering, and calculating to obtain disturbance torque acting on three axes of a satellite body coordinate system during the attitude disturbance;
the second module is used for establishing a satellite deflation mechanical model based on the satellite configuration layout design and the mechanical parameters of possible deflation sites, and obtaining the relation between the disturbance force and the disturbance moment of each axis of the satellite in the deflation disturbance process;
the third module is used for obtaining the attitude disturbance phenomenon as a criterion condition of satellite deflation disturbance according to the satellite flight time T, the disturbance force action time length delta T, the magnitude of the disturbance force F and the attitude disturbance phenomenon; and judging the attitude disturbance phenomenon at the initial stage of satellite orbit entering through the criterion condition, wherein if the criterion condition of the step is met, the attitude disturbance phenomenon is judged to be disturbance caused by satellite body deflation.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention provides an evaluation system and an evaluation method of a satellite orbit-entering initial stage deflation disturbance phenomenon on the basis of a method which is not clear and can be referred to, and the attitude disturbance torque is quantitatively calculated and evaluated through the telemetering change of a satellite actuating mechanism;
(2) the invention establishes a satellite deflation analysis model, and provides a calculation relational expression of disturbance force and disturbance moment of a satellite in a disturbance process through satellite configuration layout and mechanical parameters of possible deflation sites;
(3) the invention provides a criterion condition for evaluating the deflation disturbance phenomenon by adopting disturbance force, flight time and deflation duration, and provides a corresponding on-orbit disposal method for the condition meeting the deflation disturbance phenomenon.
Drawings
FIG. 1 is a satellite deflation dynamics analysis model.
FIG. 2 is a flow chart of an embodiment of the method of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides an evaluation system and an evaluation method for satellite orbit-in initial stage deflation disturbance, which mainly comprise the following steps: acquiring the telemetering change condition of a satellite actuating mechanism during the attitude disturbance; calculating the attitude disturbance torque by combining the attitude control system engineering parameters; establishing a satellite deflation model, and estimating the attitude disturbance force according to the attitude disturbance force moment; comprehensively evaluating and judging the attitude disturbance phenomenon by adopting criterion conditions of disturbance force, flight time and deflation duration; and a corresponding on-orbit handling method is given to the deflation disturbance according to the attitude control mode.
As shown in fig. 2, the specific implementation process steps of the method for estimating the satellite orbit initial stage deflation disturbance are as follows:
1) and at the initial stage of satellite orbit entering, for the phenomenon suspected of generating satellite deflation disturbance, the telemetering change condition of the actuating mechanism during attitude disturbance is obtained through satellite telemetering.
Counting the change condition of the jet accumulated time of each thruster during the attitude disturbance of a satellite adopting a jet thruster for attitude control, configuring n attitude control thrusters for the satellite, and acquiring the jet working time [ delta t ] of each thruster during the attitude disturbance1 Δt2 … Δtn]。
For a satellite for attitude control using reaction wheels, the variation of the rotation speed of each reaction wheel during attitude disturbance is counted, m reaction wheels are arranged in the satellite, and the variation [ delta w ] of the rotation speed of each reaction wheel during attitude disturbance is obtained1 Δw2 … Δwm]。
2) And calculating to obtain the disturbance torque acting on three axes of the satellite body coordinate system during the attitude disturbance period through the telemetering variation and the engineering parameters of the actuating mechanism.
When the air injection control is adopted, the disturbance torque on the three axes of the satellite is as follows:
in the formula mix，miy，mizThe moment components of the ith attitude control thruster on the X, Y and Z axes of the satellite are respectively theoretical moment components, and delta T is attitude disturbance duration. When the reaction wheel is adopted for control, the disturbance torque on the three axes of the satellite is as follows:
in the formula
In order to counteract the nominal angular momentum of the wheel,
for nominal speed of reaction wheel, CwIs a mounting matrix for the reaction wheelsets.
The satellite body coordinate system is defined as: the origin of coordinates O is located at the center of mass of the satellite; the OX axis points to a certain characteristic axis direction of the satellite from the origin of coordinates and is parallel to the X axis of the satellite mechanical coordinate system; the OZ axis points to the other characteristic axis direction of the satellite from the origin of coordinates, is vertical to the OX axis and is parallel to the Z axis of a satellite mechanical coordinate system; the OY axis and the OX and OZ axes form a right-handed system.
Mounting matrix C of reaction wheel trainwIs defined as:
X^hm，Y^hm，Z^hmrespectively representing the angular momentum vectors h of the m-th reaction wheelmThe axis of the satellite body coordinate system X, Y, Z.
3) Based on the satellite configuration layout design and the mechanical parameters of possible deflation sites, a satellite deflation mechanical model (see fig. 1) is established, and the relationship between the disturbance force and the disturbance torque of each axis of the satellite in the deflation disturbance process is obtained.
In fig. 1, let xyz be the satellite body coordinate system, P be any possible deflation site of the star catalogue, and the coordinate of P under the satellite body coordinate system is [ Px Py Pz](ii) a The reaction force generated by the satellite deflation is F, and the component of F on the three axes of the satellite body coordinate system is [ Fx Fy Fz]. The relationship between the reaction force of the bleed air to the satellite and the disturbance torque can be calculated by the following equation:
the reaction force of the deflation on the satellite is:
4) after the disturbance force is obtained through calculation, comprehensive judgment is carried out on the attitude disturbance phenomenon according to the satellite flight time T, the disturbance force action time length delta T and the disturbance force F. The satellite deflation disturbance phenomenon generally occurs at the initial stage of satellite orbit, the flight time is short, the deflation time is long, and the deflation disturbance force is small. Let TltdFor the maximum flight time at which the phenomenon of deflation is likely to occur, [ Delta T ]min,ΔTmax]For the possible range of deflation duration, [ F ]min,Fmax]To disturb the range of possible magnitudes of force for the bleed air. The criterion for the attitude disturbance phenomenon as satellite deflation disturbance is as follows:
5) and 4) judging the attitude disturbance phenomenon at the initial stage of satellite orbit entering through the criterion condition in the step 4), wherein if the condition is met, the attitude disturbance phenomenon is disturbance caused by satellite body deflation. And after the attitude disturbance phenomenon is determined to be deflation disturbance, corresponding treatment measures are taken according to the satellite attitude control mode, so that the deflation disturbance is prevented from influencing the satellite pointing function and the satellite safety.
The method comprises the following specific steps:
a) if the satellite adopts air injection to perform attitude control when the deflation disturbance occurs, measures for maintaining an air injection control mode are adopted, a thruster is used for injecting air to counteract the influence of the deflation disturbance torque, and after the deflation disturbance phenomenon disappears, the satellite is switched to a long-term reaction wheel control mode;
b) if the satellite adopts the reaction wheel to perform attitude control when the deflation disturbance occurs, the satellite is switched to a gas injection control mode by the opportunity selection, the reaction wheel is reset to a safe rotating speed, and the satellite is switched to a long-term reaction wheel control mode after the deflation disturbance phenomenon disappears.
The evaluation system of the satellite orbit initial stage deflation disturbance constructed according to the evaluation method of the satellite orbit initial stage deflation disturbance comprises the following steps:
the first module is used for acquiring the telemetering data variable quantity of an actuating mechanism during attitude disturbance for a satellite suspected of generating the satellite deflation disturbance phenomenon at the initial stage of satellite orbit entering through satellite telemetering, and calculating to obtain disturbance torque acting on three axes of a satellite body coordinate system during the attitude disturbance;
the second module is used for establishing a satellite deflation mechanical model based on the satellite configuration layout design and the mechanical parameters of possible deflation sites, and obtaining the relation between the disturbance force and the disturbance moment of each axis of the satellite in the deflation disturbance process;
the third module is used for obtaining the attitude disturbance phenomenon as a criterion condition of satellite deflation disturbance according to the satellite flight time T, the disturbance force action time length delta T, the magnitude of the disturbance force F and the attitude disturbance phenomenon; and judging the attitude disturbance phenomenon at the initial stage of satellite orbit entering through the criterion condition, wherein if the criterion condition of the step is met, the attitude disturbance phenomenon is judged to be disturbance caused by satellite body deflation.
Example (b):
1) taking the attitude disturbance phenomenon of a certain time at the initial stage of orbit entering of a certain satellite as an example, the satellite is provided with 4 reaction wheels, and the reaction wheels are adopted to carry out attitude control during the attitude disturbance. During the period of acquiring the attitude disturbance duration delta T9913 s through satellite remote measurement, the rotating speed variation of each reaction wheel is [ delta w [)1 Δw2 Δw3 Δw4]＝[-823rpm -493rpm 2195rpm -881rpm]。
2) Nominal angular momentum of each reaction wheel based on engineering parameters
Nominal speed of each reaction wheel
Mounting matrix C of reaction wheel trainwComprises the following steps:
therefore, the disturbance torques acting on the three axes of the satellite during the attitude disturbance are calculated as:
3) according to the configuration layout design and the general assembly implementation condition of the satellite, the position of the star catalogue, where the deflation is most likely to occur, comprises a pipeline leading-out point at the mounting position of the thruster, a cable outgoing port of a part of the star catalogue and the like, and the coordinate of a possible action point P of the deflation equivalent disturbance force under a centroid coordinate system is about [ Px Py Pz]＝[0.879m 0.605m 0.453m]The component of the reaction force F generated by the deflation on the satellite on the three axes of the satellite body coordinate system is [ Fx Fy Fz]：
The reaction force of the deflation on the satellite is:
4) according to flight data of a plurality of satellites, the time period of attitude disturbance of the satellites is from the satellite-rocket separation time (T0) to about T0+5h, the magnitude of the rear attitude disturbance is gradually reduced to be free of influence, the flight time before the satellite-rocket separation is 3.5h and a certain margin are considered, and the maximum flight time of possible deflation phenomenon is about Tltd10 h; on the other hand, the measured deflation disturbance durations are all larger than 1h and smaller than Tltd10h, i.e. [ Delta T ]min,ΔTmax]＝[1h 10h](ii) a The magnitude of the air-discharge disturbance force is between 0.1mN and 10mN, namely Fmin,Fmax]＝[0.1mN 10mN]. In the embodiment, the flight time T of the satellite with the attitude disturbance phenomenon is about 5.5h, meanwhile, the attitude disturbance phenomenon of the satellite is judged according to the disturbance force action time delta T obtained in the steps 2) and 3) and the calculated disturbance force F, and the satellite is judged according to the judgmentThe flight time T, the deflation duration delta T and the disturbance force F all meet the criteria of deflation disturbance, namely:
T<Tltd，
and Δ Tmin<ΔT<ΔTmax，
And Fmin<F<Fmax
Therefore, the attitude disturbance phenomenon occurring in the satellite is the attitude disturbance generated by satellite star deflation.
5) Through evaluation and judgment, the attitude disturbance phenomenon at the initial stage of satellite orbit entering is disturbance caused by satellite deflation, and when the deflation disturbance occurs, the satellite adopts a reaction wheel to perform attitude control, and then treatment measures are adopted as follows: and the satellite is switched to a jet control mode by the selection of the satellite, the influence of the deflation disturbance torque is counteracted by using jet of the thruster, the reaction wheel is reset to a safe rotating speed, and the satellite is switched to a long-term reaction wheel control mode after the deflation disturbance phenomenon disappears.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A method for evaluating satellite orbit initial stage deflation disturbance is characterized by comprising the following steps:
(1) at the initial stage of satellite orbit entering, for a satellite suspected of generating the satellite body deflation disturbance, acquiring the telemetering data variable quantity of an actuating mechanism during the attitude disturbance through satellite telemetering;
(2) calculating to obtain disturbance torque acting on three axes of a satellite body coordinate system during attitude disturbance through the telemetering data variable quantity of the actuating mechanism obtained in the step (1);
(3) establishing a satellite deflation mechanical model based on the satellite configuration layout design and the mechanical parameters of possible deflation sites to obtain the relationship between the disturbance force and the disturbance torque of each axis of the satellite in the deflation disturbance process;
(4) after the disturbance force is obtained through calculation, according to the satellite flight time T, the disturbance force action time delta T, the magnitude of the disturbance force F and the attitude disturbance phenomenon, the attitude disturbance phenomenon is obtained and is used as a criterion condition of satellite deflation disturbance;
(5) judging the attitude disturbance phenomenon at the initial stage of satellite orbit entering through the criterion condition in the step (4), and if the criterion condition in the step (4) is met, judging the attitude disturbance phenomenon as disturbance caused by satellite body deflation; and after the attitude disturbance phenomenon is determined to be deflation disturbance, corresponding treatment measures are taken according to a satellite attitude control mode.
2. The method for evaluating satellite orbit initial stage deflation disturbance according to claim 1, wherein in the step (1), for the satellite adopting the jet thruster for attitude control: counting the jet accumulated time change condition of each jet thruster in the attitude disturbance period, and acquiring the jet working time [ delta t ] of each jet thruster in the attitude disturbance period1 Δt2 … Δtn](ii) a And n is the number of attitude control thrusters configured by the satellite.
3. The method for estimating disturbance of initial satellite deflation during orbiting as claimed in claim 2, wherein in step (1), for the satellite adopting reaction wheels for attitude control: counting the rotation speed change condition of each reaction wheel during the attitude disturbance period to obtain the rotation speed change [ delta w ] of each reaction wheel during the attitude disturbance period1 Δw2 … Δwm](ii) a m is the number of reaction wheels of the satellite configuration.
4. The method for estimating disturbance of initial satellite orbit deflation as claimed in claim 3, wherein the satellite body coordinate system OXYZ is defined as: the origin of coordinates O is located at the center of mass of the satellite; the OX axis points to any characteristic axis direction of the satellite from the origin of coordinates and is parallel to the X axis of the satellite mechanical coordinate system; the OZ axis points to the other characteristic axis direction of the satellite from the origin of coordinates, is vertical to the OX axis and is parallel to the Z axis of a satellite mechanical coordinate system; the OY axis and the OX and OZ axes form a right-handed system.
5. The method for evaluating satellite early-stage deflation disturbance in orbit according to claim 4, wherein in step (2), when the attitude of the satellite is controlled by the jet thruster, the disturbance torques acting on three axes of the coordinate system of the satellite body during the attitude disturbance are:
in the formula mix，miy，mizThe moment components of the ith attitude control thruster on the X, Y, Z axis of the satellite body coordinate system are respectively, Δ T is the attitude disturbance duration, and i is 1,2, 3.
6. The method according to claim 5, wherein in the step (2), when the reaction wheel is used to control the attitude of the satellite, the disturbance torques applied to three axes of the coordinate system of the satellite body during the attitude disturbance are:
in the formula
In order to counteract the nominal angular momentum of the wheel,
for nominal speed of reaction wheel, CwA mounting matrix for the reaction wheelset;
mounting matrix C of reaction wheel trainwIs defined as:
X^hm，Y^hm，Z^hmrespectively representing the angular momentum vectors h of the m-th reaction wheelmThe axis of the satellite body coordinate system X, Y, Z.
7. The method for evaluating disturbance of initial satellite orbit deflation as claimed in claim 6, wherein in step (3), the mechanical model of satellite deflation is as follows:
the relationship between the reaction force of the bleed air to the satellite and the disturbance torque is calculated by the following equation:
the reaction force of the deflation on the satellite is:
p is any possible deflation site on the surface of the satellite, and the coordinate of P in the coordinate system of the satellite body is [ P ]x Py Pz](ii) a The reaction force generated by the satellite deflation is F, and the component of F on the three axes of the satellite body coordinate system is [ Fx Fy Fz]。
8. The method for evaluating satellite orbit initial stage deflation disturbance according to claim 7, wherein in the step (4), the criterion condition that the attitude disturbance phenomenon is satellite deflation disturbance is:
T<Tltd，
and Δ Tmin<ΔT<ΔTmax，
And Fmin<F<Fmax,
TltdFor a set maximum flight time, Δ T, at which the phenomenon of deflation may occurmin,ΔTmax]For the possible range of set deflation duration, [ Fmin,Fmax]The range of possible magnitudes of the disturbance force for the set bleed air.
9. The method for evaluating disturbance of initial satellite orbit deflation as claimed in claim 8, wherein in step (5), the treatment is specifically as follows:
if the satellite adopts the jet thruster to carry out attitude control when the deflation disturbance occurs, measures for maintaining a jet control mode are adopted, the thruster is used for jetting air to counteract the influence of the deflation disturbance torque, and after the deflation disturbance phenomenon disappears, the satellite is switched to a long-term reaction wheel control mode;
if the satellite adopts the reaction wheel to perform attitude control when the deflation disturbance occurs, the satellite is switched to a gas injection control mode, the reaction wheel is reset to a set safe rotating speed, and after the deflation disturbance phenomenon disappears, the satellite is switched to a long-term reaction wheel control mode.
10. The system for evaluating disturbance of initial satellite orbit deflation constructed according to the evaluation method of any of claims 1 to 9, comprising:
the first module is used for acquiring the telemetering data variable quantity of an actuating mechanism during attitude disturbance for a satellite suspected of generating the satellite deflation disturbance phenomenon at the initial stage of satellite orbit entering through satellite telemetering, and calculating to obtain disturbance torque acting on three axes of a satellite body coordinate system during the attitude disturbance;
the second module is used for establishing a satellite deflation mechanical model based on the satellite configuration layout design and the mechanical parameters of possible deflation sites, and obtaining the relation between the disturbance force and the disturbance moment of each axis of the satellite in the deflation disturbance process;
the third module is used for obtaining the attitude disturbance phenomenon as a criterion condition of satellite deflation disturbance according to the satellite flight time T, the disturbance force action time length delta T, the magnitude of the disturbance force F and the attitude disturbance phenomenon; and judging the attitude disturbance phenomenon at the initial stage of satellite orbit entering through the criterion condition, and if the criterion condition of the step is met, judging the attitude disturbance phenomenon to be disturbance caused by satellite body deflation.
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