CN113379297A - On-orbit evaluation method under track control abnormal interruption of 490N thruster - Google Patents

On-orbit evaluation method under track control abnormal interruption of 490N thruster Download PDF

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CN113379297A
CN113379297A CN202110719347.1A CN202110719347A CN113379297A CN 113379297 A CN113379297 A CN 113379297A CN 202110719347 A CN202110719347 A CN 202110719347A CN 113379297 A CN113379297 A CN 113379297A
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李超
孙守明
王宝华
李恒年
钟文冬
叶修松
靳忠涛
杨阳
王鑫
杨元
杨彪
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China Xian Satellite Control Center
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Abstract

The invention discloses an on-orbit evaluation method under the condition of track control abnormal interruption of a 490N thruster, which specifically comprises the following steps: firstly, calculating mass second flow of an oxidant, mass second flow of a combustion agent, propellant consumption of a 10N thruster, ignition propellant consumption of a 490N thruster, satellite mass and actually-measured thrust of the thruster; then calculating the theoretical orbit number of the orbit control abnormal disturbance starting moment, the component of the thruster in a satellite body coordinate system, and the attitude control thruster average thrust between the 490N ignition abnormal disturbance starting moment and the interruption moment: then calculating the theoretical number of tracks at the moment of abnormal ignition interruption, determining the number of actually measured tracks at the moment of abnormal ignition interruption, and calibrating the 490N thruster to obtain the actually calibrated thrust; finally, the actual thrust during the period from the start of the thrust anomaly disturbance to the abort of the anomaly is evaluated 490N. The on-orbit evaluation method can effectively improve the evaluation precision of the thrust of the engine after the GEO satellite 490N orbital transfer is abnormally interrupted.

Description

On-orbit evaluation method under track control abnormal interruption of 490N thruster
Technical Field
The invention belongs to the technical field of aerospace measurement and control, and particularly relates to an on-orbit evaluation method under abnormal interruption of track control of a 490N thruster.
Background
Geosynchronous geostationary orbit satellite (GEO satellite) transfer orbit control is typically accomplished by a 490N engine orbital transfer. The GEO satellite 490N orbit transfer is usually long, and the attitude control thruster on the satellite is required to keep the ignition attitude during the orbit transfer period to ensure that the final orbit transfer target is reached. Due to various sudden reasons such as the change of the center of mass of the satellite, the installation deviation of thrust, the ablation of a jet pipe of a thruster and the like, a certain interference torque exists in the actual GEO satellite orbit control process, and in order to keep the attitude of the satellite stable, the attitude control thruster participates in the work. If the disturbance moment on the satellite continuously and rapidly increases and exceeds the normal range, the attitude instability on the satellite is caused, and the 490N orbital transfer process must be interrupted.
The 490N track transfer process generally includes the processes of 10N thruster bottoming start, 10N thruster bottoming end, 490N thruster firing, 490N thruster shutdown, etc. In the process from the start of the 490N orbital transfer attitude abnormal disturbance to the interruption of orbital transfer, the attitude control thruster participates in work for a long time, and the actual effect of the orbital control thruster is affected, so that the comprehensive thrust of orbital control and attitude control is inconsistent with the actual orbital control thrust. It would be difficult to accurately evaluate the 490N thruster with conventional thruster evaluation methods in the event of an rail-controlled abnormal interruption.
Disclosure of Invention
The invention aims to provide an on-orbit evaluation method under the condition of track control abnormal interruption of a 490N thruster, which can effectively improve the engine thrust evaluation precision of a GEO satellite 490N after the track change abnormal interruption.
The technical scheme adopted by the invention is that the on-orbit evaluation method under the condition of track control abnormal interruption of the 490N thruster is implemented according to the following steps:
step 1: calculating mass second flow of oxidant of each thruster
Figure BDA0003135961620000025
And mass second flow of the combustion agent
Figure BDA0003135961620000026
Step 2: calculating propellant consumption delta m of 10N bottom-sinking thrusterCD；
And step 3: calculating 490N thruster ignition propellant consumption delta M490；
And 4, step 4: calculating T1Time of day satellite quality
Figure BDA0003135961620000021
The quality of the satellite before orbit control;
and 5: calculating the actual measurement thrust F of each 10N thrusteriAnd 490N thruster measured thrust F490；
Step 6: will T0Number of satellite orbits at time
Figure BDA0003135961620000022
Satellite quality
Figure BDA0003135961620000023
As an initial value, the actually measured thrust F of the 10N bottoming thrusteriAnd the actual measurement thrust F of the 10N bottom-sinking thruster ignition time length delta t and 490N thrusters490490N thruster ignition time delta t before abnormal disturbance begins1fireAnd the satellite attitude parameters during ignition are used as input conditions; track dynamics equation based precise numerical method track extrapolation calculation track control abnormal disturbance starting time T1Theoretical number of orbits of
Figure BDA0003135961620000024
And 7: calculating T1～T2Working time length delta t of each attitude control thruster between momentsk，T1Ignition abnormal disturbance start time, T, of 490N2Ignition abort time at 490N; Δ tk＝tke-tks；tkeIs the cumulative operating time, t, of the thruster numbered k from the start of the 490N ignition abnormal disturbance to the end of the 490N ignitionksAccumulated working time of the thruster with the number of k at the track change starting moment;
and 8: calculating the component F of each 10N thruster in the satellite body coordinate systemix,Fiy,FizAnd component F of thrust of 490N thruster in satellite body coordinate system490x,F490y,F490z；
And step 9: calculating 490N an ignition abnormal disturbance starting time T1To 490N ignition abort time T2Average thrust of each attitude control thruster
Figure BDA0003135961620000031
Step 10: calculating T1～T2Combined thrust between moments
Figure BDA0003135961620000032
Figure BDA0003135961620000033
Step 11: starting time T of abnormal disturbance in the track control period1Number of tracks
Figure BDA0003135961620000039
Satellite quality
Figure BDA0003135961620000034
As an initial value, 490N thruster thrust F490490N ignition abnormal disturbance start time T1To 490N ignition abort time T2Duration Δ t2fireAnd satellite attitude parameters as input conditions; calculating the abnormal ignition interruption time T2Theoretical number of orbits of
Figure BDA0003135961620000035
Step 12: precisely fixing the track by using the track measuring data to determine the abnormal interruption time T2Number of actual measurement tracks
Figure BDA0003135961620000038
Carrying out 490N thruster calibration to obtain actual calibration thrust
Figure BDA0003135961620000036
Step 13: estimating 490N actual thrust F during the period from the onset of an anomalous disturbance to an anomalous shutdown of the thruster490x_real,F490y_real,F490z_real；
Figure BDA0003135961620000037
The present invention is also characterized in that,
in the step 1, a calculation formula is shown as a formula (1);
Figure BDA0003135961620000041
in the formula (1), the lower subscript i is the thruster number, poIs the oxidant tank pressure, pfIs the combustion agent tank pressure, toIs the oxidant storage tank temperature, tfIs the combustion agent storage tank temperature, omegao0iIs the theoretical value of the flow of the oxidant, omegaopoiIs the partial derivative of the oxidant flow to the oxygen tank pressure, po0Is a reference value, ω, of the oxidizer tank pressureotoiIs the partial derivative of the oxidant flow to the oxygen box temperature, to0Is a reference value, omega, of the oxidizer tank temperatureopfiIs the partial derivative of the oxidant flow to the tank pressure, pf0Is a reference value, omega, of the combustion agent tank pressureotfiIs the partial derivative of the oxidant flow to the tank temperature, tf0Is a reference value, omega, of the temperature of the combustion agent tankf0iTheoretical value of combustion agent flow, omegafpoiIs the partial derivative, omega, of the flow of the combustion agent with respect to the pressure in the oxygen tankftoiIs the partial derivative, omega, of the flow of the combustion agent with respect to the temperature of the oxygen tankfpfiIs the partial derivative of the flow of the combustion agent to the tank pressure, omegaftfiIs the partial derivative of the fuel flow to the tank temperature.
In step 2, calculating the propellant consumption amount delta m of the 10N bottoming thrusterCDAs shown in formula (2);
Figure BDA0003135961620000042
in the formula (2), T0The time is the beginning time of the bottom sinking of the 10N thruster, the time is the length of the bottom sinking of the 10N thruster, the lower foot mark j is the number of the bottom sinking thruster, and the time is the number of the bottom sinking thrusterojIs the oxidant consumption, Δ m, of the 10N bottoming thruster of number jfjIs the combustion agent consumption, Δ m, of the 10N bottoming thruster of number jocdIs the oxidant consumption of the 10N bottoming thruster, Delta mfcdIs the combustion agent consumption of the 10N bottoming thruster.
In step 3,. DELTA.M490The formula (3) is shown in the formula;
Figure BDA0003135961620000051
in the formula (3), T0+Δt～T1For 490N thruster operation period, T0+ Deltat is the end time of bottom sinking of the 10N thruster, T1At the time of start of ignition abnormal disturbance 490N,
Figure BDA0003135961620000052
at 490N thruster oxidant mass second flow,
Figure BDA0003135961620000053
combustion mass second flow, Δ M, for 490N thrustero490Is 490N thruster oxidant consumption, Δ Mf490Is the 490N thruster combustion consumption.
In step 5, FiAnd F490The calculation formulas of (A) and (B) are respectively shown as a formula (5) and a formula (6);
Figure BDA0003135961620000054
Figure BDA0003135961620000055
in the formula, the lower foot mark I is the number of the 10N thruster, IiIs the specific impulse of the 10N thruster, and g is the gravity acceleration; i is490Is the 490N thruster thrust specific impulse.
In step 8, Fix,Fiy,FizAnd F490x,F490y,F490zThe calculation formulas of (a) and (b) are respectively shown as a formula (8) and a formula (9);
Figure BDA0003135961620000061
Figure BDA0003135961620000062
wherein alpha isi,βi,γiThe direction cosine angle between the nozzle axis of each 10N thruster and the three axes of the satellite body X, Y, Z; alpha is alpha490,β490,γ490Is the directional cosine angle of the nozzle axis of each 490 thruster with respect to the three axes of the satellite body X, Y, Z.
In the step 9, the process is carried out,
Figure BDA0003135961620000063
the formula (2) is shown as formula (10);
Figure BDA0003135961620000064
wherein, FaxIs the component of the average thrust of the attitude control thruster on the X axis of the satellite body, FayIs the component of the average thrust of the attitude control thruster on the Y axis of the satellite body, FazIs the component of the average thrust of the attitude control thruster on the Z axis of the satellite body, delta t2fireIs 490N the ignition abnormal disturbance start time T1To 490N ignition abort time T2And the duration length, and the lower foot mark k is the serial number of the satellite attitude control thruster.
The invention has the beneficial effects that: the method has a strong guiding function on the fault diagnosis in the orbit control process of the GEO satellite 490N thruster, and has certain economic benefits on the orbit transfer and on-orbit stable operation of a spacecraft.
Drawings
FIG. 1 is a flow chart of an on-track evaluation method under abnormal interruption of track control of a 490N thruster according to the present invention.
Detailed Description
The present invention will be described in detail with reference to the following embodiments.
The invention discloses an on-orbit evaluation method under the condition of track control abnormal interruption of a 490N thruster, which is implemented according to the following steps:
step 1: calculating mass second flow of oxidant of each thruster
Figure BDA0003135961620000071
And mass second flow of the combustion agent
Figure BDA0003135961620000072
As shown in formula (1);
Figure BDA0003135961620000073
in the formula (1), the lower subscript i is the thruster number, poIs the oxidant tank pressure, pfIs the combustion agent tank pressure, toIs the oxidant storage tank temperature, tfIs the combustion agent storage tank temperature, omegao0iIs the theoretical value of the flow of the oxidant, omegaopoiIs the partial derivative of the oxidant flow to the oxygen tank pressure, po0Is a reference value, ω, of the oxidizer tank pressureotoiIs the partial derivative of the oxidant flow to the oxygen box temperature, to0Is a reference value, omega, of the oxidizer tank temperatureopfiIs the partial derivative of the oxidant flow to the tank pressure, pf0Is a reference value, omega, of the combustion agent tank pressureotfiIs the partial derivative of the oxidant flow to the tank temperature, tf0Is a reference value, omega, of the temperature of the combustion agent tankf0iTheoretical value of combustion agent flow, omegafpoiIs the partial derivative, omega, of the flow of the combustion agent with respect to the pressure in the oxygen tankftoiIs the partial derivative, omega, of the flow of the combustion agent with respect to the temperature of the oxygen tankfpfiIs the partial derivative of the flow of the combustion agent to the tank pressure, omegaftfiIs the partial derivative of the flow of the combustion agent with respect to the temperature of the fuel tank;
step 2: calculating propellant consumption delta m of 10N bottom-sinking thrusterCDAs shown in formula (2);
Figure BDA0003135961620000081
in the formula (2), T0The time is the beginning time of the bottom sinking of the 10N thruster, the time is the length of the bottom sinking of the 10N thruster, the lower foot mark j is the number of the bottom sinking thruster, and the time is the number of the bottom sinking thrusterojIs the oxidant consumption, Δ m, of the 10N bottoming thruster of number jfjIs the combustion agent consumption, Δ m, of the 10N bottoming thruster of number jocdIs the oxidant consumption of the 10N bottoming thruster, Delta mfcdIs the combustion agent consumption of the 10N bottoming thruster;
and step 3: calculating 490N thruster ignition propellant consumption delta M490As shown in formula (3);
Figure BDA0003135961620000091
in the formula (3), T0+Δt～T1For 490N thruster operation period, T0+ Deltat is the end time of bottom sinking of the 10N thruster, T1At the time of start of ignition abnormal disturbance 490N,
Figure BDA0003135961620000092
at 490N thruster oxidant mass second flow,
Figure BDA0003135961620000093
at 490N thruster burner mass second flow,
Figure BDA0003135961620000094
and
Figure BDA0003135961620000095
the calculation method is the same as the step 1, delta Mo490Is 490N thruster oxidant consumption, Δ Mf490Is the 490N thruster combustion consumption.
And 4, step 4: calculating T1Time of day satellite mass MT1As shown in formula (4);
Figure BDA0003135961620000096
in the formula (4), the reaction mixture is,
Figure BDA0003135961620000097
the quality of the satellite before orbit control;
and 5: calculating the actual measurement thrust F of each 10N thrusteriAnd 490N thruster measured thrust F490Respectively represented by formula (5) and formula (6);
Figure BDA0003135961620000098
Figure BDA0003135961620000099
in the formula, the lower foot mark I is the number of the 10N thruster, IiIs the specific impulse of the 10N thruster, and g is the gravity acceleration; i is490Is 490N thruster specific impulse;
step 6: will T0Number of satellite orbits at time
Figure BDA00031359616200000910
Satellite quality
Figure BDA00031359616200000911
As an initial value, the actually measured thrust F of the 10N bottoming thrusteriAnd the actual measurement thrust F of the 10N bottom-sinking thruster ignition time length delta t and 490N thrusters490490N thruster ignition time delta t before abnormal disturbance begins1fireAnd satellite attitude parameters during ignition as input conditions. Track dynamics equation based precise numerical method track extrapolation calculation track control abnormal disturbance starting time T1Theoretical number of orbits of
Figure BDA0003135961620000101
And 7: calculating T1～T2Working time length delta t of each attitude control thruster between momentsk，T1Ignition abnormal disturbance start time, T, of 490N2Ignition abort time at 490N; as shown in formula (7);
Δtk＝tke-tks (7)；
wherein, tkeIs the cumulative operating time, t, of the thruster numbered k from the start of the 490N ignition abnormal disturbance to the end of the 490N ignitionksAccumulated working time of the thruster with the number of k at the track change starting moment;
and 8: calculating the component F of each 10N thruster in the satellite body coordinate systemix,Fiy,FizAnd component F of thrust of 490N thruster in satellite body coordinate system490x,F490y,F490zAs shown in formula (8) and formula(9) Shown;
Figure BDA0003135961620000102
Figure BDA0003135961620000103
wherein alpha isi,βi,γiThe direction cosine angle between the nozzle axis of each 10N thruster and the three axes of the satellite body X, Y, Z; alpha is alpha490,β490,γ490The direction cosine angle of the nozzle axis of each 490 thruster with the three axes of the satellite body X, Y, Z;
and step 9: calculating 490N an ignition abnormal disturbance starting time T1To 490N ignition abort time T2Average thrust of each attitude control thruster
Figure BDA0003135961620000104
As shown in formula (10);
Figure BDA0003135961620000111
wherein, FaxIs the component of the average thrust of the attitude control thruster on the X axis of the satellite body, FayIs the component of the average thrust of the attitude control thruster on the Y axis of the satellite body, FazIs the component of the average thrust of the attitude control thruster on the Z axis of the satellite body, delta t2fireIs 490N the ignition abnormal disturbance start time T1To 490N ignition abort time T2And the duration length, and the lower foot mark k is the serial number of the satellite attitude control thruster.
Step 10: calculating T1～T2Combined thrust between moments
Figure BDA0003135961620000112
As shown in formula (11);
Figure BDA0003135961620000113
step 11: starting time T of abnormal disturbance in the track control period1Number of tracks
Figure BDA0003135961620000116
Satellite quality
Figure BDA0003135961620000114
As an initial value, 490N thruster thrust F490490N ignition abnormal disturbance start time T1To 490N ignition abort time T2Duration Δ t2fireAnd satellite attitude parameters as input conditions; calculating the abnormal ignition interruption time T based on the method of the step 62Theoretical number of orbits of
Figure BDA0003135961620000115
Step 12: precisely fixing the track by using the track measuring data to determine the abnormal interruption time T2The number of the actually measured track sigmaT2_realAnd carrying out 490N thruster calibration to obtain actual calibration thrust
Figure BDA0003135961620000121
(490N thruster calibration method is the general method in the trade, and the literature "Chang' e I" satellite orbit accuse calibration method research and realization "has also the relevant method description).
Step 13: estimating 490N actual thrust F during the period from the onset of an anomalous disturbance to an anomalous shutdown of the thruster490x_real,F490y_real,F490z_realAs shown in formula (12);
Figure BDA0003135961620000122
examples
In a specific application example, an adopted east four-platform satellite launches an orbit in 2020, the orbit-entering mass of the satellite is 5399.5kg, 1 490N thruster and 14 10N thrusters are installed on the satellite, wherein 8 10N thrusters are installed in the X-axis direction, 4 10N thrusters are installed in the Y-axis direction, and 2 10N thrusters and 1 490N thruster are installed in the Z-axis direction. The 10N thrusters in the Z-axis direction are rail-controlled bottom-sinking thrusters, and can also be used as attitude-control thrusters to participate in work after bottom sinking is finished, the 490N thrusters are rail-controlled thrusters, and the X, Y10N thrusters in the axial direction are used as attitude-control thrusters to participate in work.
As shown in fig. 1, the specific steps are as follows:
step 1: calculating the mass second flow of the oxidant of the 490N thruster and the 14 10N thrusters
Figure BDA0003135961620000131
Mass second flow of combustion agent
Figure BDA0003135961620000132
Figure BDA0003135961620000133
Wherein, the lower subscript i is the thruster number, poIs the oxidant tank pressure, pfIs the combustion agent tank pressure, toIs the oxidant storage tank temperature, tfIs the combustion agent storage tank temperature, omegao0iIs the theoretical value of the flow of the oxidant, omegaopoiIs the partial derivative of the oxidant flow to the oxygen tank pressure, po0Is a reference value, ω, of the oxidizer tank pressureotoiIs the partial derivative of the oxidant flow to the oxygen box temperature, to0Is a reference value, omega, of the oxidizer tank temperatureopfiIs the partial derivative of the oxidant flow to the tank pressure, pf0Is a reference value, omega, of the combustion agent tank pressureotfiIs the partial derivative of the oxidant flow to the tank temperature, tf0Is a reference value, omega, of the temperature of the combustion agent tankf0iTheoretical value of combustion agent flow, omegafpoiIs the partial derivative, omega, of the flow of the combustion agent with respect to the pressure in the oxygen tankftoiIs the partial derivative, omega, of the flow of the combustion agent with respect to the temperature of the oxygen tankfpfiIs the partial derivative of the flow of the combustion agent to the tank pressure, omegaftfiIs the temperature of the combustion agent flow to the fuel tankPartial derivatives of (a).
Step 2: calculating propellant consumption delta m of 4 10N bottom-sinking thrustersCD；
Figure BDA0003135961620000134
Figure BDA0003135961620000135
ΔmCD＝Δmocd+Δmfcd＝ΣΔmoj+ΣΔmfj
Wherein, T0The time is the bottom sinking starting time of the 10N thruster, the bottom sinking time of the 10N thruster is 232 seconds, the lower foot mark j is the number of the bottom sinking thruster, and the number is delta mojIs the oxidant consumption, Δ m, of the 10N bottoming thruster of number ifjIs the combustion agent consumption, Δ m, of the 10N bottoming thruster of number jocdIs the oxidant consumption of the 10N bottoming thruster, Delta mfcdIs the combustion agent consumption of the 10N bottoming thruster.
And step 3: calculating 490N thruster ignition propellant consumption delta M490；
Figure BDA0003135961620000141
Figure BDA0003135961620000142
ΔM490＝ΔMo490+ΔMf490
Wherein, T0+Δt～T1For 490N thruster operation period, T0+ Deltat is the end time of bottom sinking of the 10N thruster, T1At the time of start of ignition abnormal disturbance 490N,
Figure BDA0003135961620000143
at 490N thruster oxidant mass second flow,
Figure BDA0003135961620000144
at 490N thruster burner mass second flow,
Figure BDA00031359616200001413
and
Figure BDA0003135961620000145
the calculation method is the same as the step 1, delta Mo490Is 490N thruster oxidant consumption, Δ Mf490Is the 490N thruster combustion consumption.
And 4, step 4: calculating T1Time of day satellite quality
Figure BDA0003135961620000146
Figure BDA0003135961620000147
Wherein,
Figure BDA0003135961620000148
the quality of the satellite before orbit control.
And 5: calculating the thrust F of 14 10N thrustersiAnd 490N thruster thrust magnitude F490；
Figure BDA0003135961620000149
Figure BDA00031359616200001410
Wherein, the lower foot mark I is the number of the 10N thruster, IiIs the specific impulse of the 10N thruster, and g is the gravity acceleration; i is490Is the 490N thruster thrust specific impulse.
Step 6: will T0Number of satellite orbits at time
Figure BDA00031359616200001411
Satellite quality
Figure BDA00031359616200001412
As an initial value, the actually measured thrust F of the 10N bottoming thrusteriAnd the actual measurement thrust F of the 10N bottom-sinking thruster ignition time length delta t and 490N thrusters490490N thruster ignition time delta t before abnormal disturbance begins1fireAnd satellite attitude parameters during ignition as input conditions. Track dynamics equation based precise numerical method track extrapolation calculation track control abnormal disturbance starting time T1Theoretical number of orbits of
Figure BDA0003135961620000151
And 7: calculating T1～T2Working time length delta t of each attitude control thruster between momentsk，T1Ignition abnormal disturbance start time, T, of 490N2The ignition abort time is 490N.
Δtk＝tke-tks
Wherein t iskeIs the cumulative operating time, t, of the thruster numbered k from the start of the 490N ignition abnormal disturbance to the end of the 490N ignitionksAnd the accumulated working time of the thruster with the number k at the track change starting moment.
And 8: calculating a component F of 14 10N thrusters in a satellite body coordinate systemix,Fiy,FizAnd component F of thrust of 490N thruster in satellite body coordinate system490x,F490y,F490z；
Figure BDA0003135961620000152
{F490x＝F490·cos(α490)
{F490y＝F490·cos(β490)
{F490z＝F490·cos(γ490)
Wherein alpha isi,βi,γiThe cosine angle of the direction of the jet pipe axis of each thruster and the three axes of the satellite body X, Y, Z; alpha is alpha490,β490,γ490Is 490 the direction cosine angle of the thrust tube axis of the thruster to the three axes of the satellite body X, Y, Z.
And step 9: calculating 490N an ignition abnormal disturbance starting time T1To 490N ignition abort time T2Average thrust of each attitude control thruster
Figure BDA0003135961620000153
Figure BDA0003135961620000161
Wherein FaxIs the component of the average thrust of the attitude control thruster on the X axis of the satellite body, FayIs the component of the average thrust of the attitude control thruster on the Y axis of the satellite body, FazIs the component of the average thrust of the attitude control thruster on the Z axis of the satellite body, delta t2fireIs 490N the ignition abnormal disturbance start time T1To 490N ignition abort time T2Duration length, lower footmark k is satellite 14 station 10N thruster number.
Step 10: calculating T1～T2Combined thrust between moments
Figure BDA0003135961620000162
Figure BDA0003135961620000163
Step 11: starting time T of abnormal disturbance in the track control period1Number of tracks
Figure BDA0003135961620000164
Satellite quality
Figure BDA0003135961620000165
As an initial value, 49Thrust F of 0N thruster490490N ignition abnormal disturbance start time T1To 490N ignition abort time T2Duration Δ t2fireAnd satellite attitude parameters as input conditions. Calculating the abnormal ignition interruption time T based on the method of the step 62Theoretical number of orbits of
Figure BDA0003135961620000166
Step 12: precisely fixing the track by using the track measuring data to determine the abnormal interruption time T2Number of actual measurement tracks
Figure BDA0003135961620000168
Carrying out 490N thruster calibration to obtain actual calibration thrust
Figure BDA0003135961620000167
Step 13: estimating 490N actual thrust F during the period from the onset of an anomalous disturbance to an anomalous shutdown of the thruster490x_real,F490y_real,F490z_real。
Figure BDA0003135961620000171
The invention discusses an on-orbit evaluation method under the condition of track control abnormal interruption of a 490N thruster, which can effectively improve the engine thrust evaluation precision of a GEO satellite 490N after the track change abnormal interruption.

Claims (7)

1. An on-orbit evaluation method under track control abnormal interruption of a 490N thruster is characterized by comprising the following steps of:
step 1: calculating mass second flow of oxidant of each thruster
Figure FDA0003135961610000011
And mass second flow of the combustion agent
Figure FDA0003135961610000012
Step 2: calculating propellant consumption delta m of 10N bottom-sinking thrusterCD；
And step 3: calculating 490N thruster ignition propellant consumption delta M490；
And 4, step 4: calculating T1Time of day satellite quality
Figure FDA0003135961610000013
Figure FDA0003135961610000014
Figure FDA0003135961610000015
The quality of the satellite before orbit control;
and 5: calculating the actual measurement thrust F of each 10N thrusteriAnd 490N thruster measured thrust F490；
Step 6: will T0Number of satellite orbits at time
Figure FDA0003135961610000016
Satellite quality
Figure FDA0003135961610000017
As an initial value, the actually measured thrust F of the 10N bottoming thrusteriAnd the actual measurement thrust F of the 10N bottom-sinking thruster ignition time length delta t and 490N thrusters490490N thruster ignition time delta t before abnormal disturbance begins1fireAnd the satellite attitude parameters during ignition are used as input conditions; track dynamics equation based precise numerical method track extrapolation calculation track control abnormal disturbance starting time T1Theoretical number of orbits of
Figure FDA0003135961610000018
And 7: calculating T1～T2Working time length delta t of each attitude control thruster between momentsk，T1Ignition abnormal disturbance start time for 490N，T2Ignition abort time at 490N; Δ tk＝tke-tks；tkeIs the cumulative operating time, t, of the thruster numbered k from the start of the 490N ignition abnormal disturbance to the end of the 490N ignitionksAccumulated working time of the thruster with the number of k at the track change starting moment;
and 8: calculating the component F of each 10N thruster in the satellite body coordinate systemix,Fiy,FizAnd component F of thrust of 490N thruster in satellite body coordinate system490x,F490y,F490z；
And step 9: calculating 490N an ignition abnormal disturbance starting time T1To 490N ignition abort time T2Average thrust of each attitude control thruster
Figure FDA0003135961610000021
Step 10: calculating T1～T2Combined thrust between moments
Figure FDA0003135961610000022
Figure FDA0003135961610000023
Step 11: starting time T of abnormal disturbance in the track control period1Number of tracks
Figure FDA0003135961610000024
Satellite quality
Figure FDA0003135961610000025
As an initial value, 490N thruster thrust F490490N ignition abnormal disturbance start time T1To 490N ignition abort time T2Duration Δ t2fireAnd satellite attitude parameters as input conditions; calculating the abnormal ignition interruption time T2Theoretical number of orbits of
Figure FDA0003135961610000026
Step 12: precisely fixing the track by using the track measuring data to determine the abnormal interruption time T2Number of actual measurement tracks
Figure FDA0003135961610000027
Carrying out 490N thruster calibration to obtain actual calibration thrust
Figure FDA0003135961610000028
Step 13: estimating 490N actual thrust F during the period from the onset of an anomalous disturbance to an anomalous shutdown of the thruster490x_real,F490y_real,F490z_real；
Figure FDA0003135961610000029
2. The on-orbit evaluation method under the abnormal interruption of the track control of the 490N thruster, according to claim 1, wherein in the step 1, the calculation formula is shown as formula (1);
Figure FDA0003135961610000031
in the formula (1), the lower subscript i is the thruster number, poIs the oxidant tank pressure, pfIs the combustion agent tank pressure, toIs the oxidant storage tank temperature, tfIs the combustion agent storage tank temperature, omegao0iIs the theoretical value of the flow of the oxidant, omegaopoiIs the partial derivative of the oxidant flow to the oxygen tank pressure, po0Is a reference value, ω, of the oxidizer tank pressureotoiIs the partial derivative of the oxidant flow to the oxygen box temperature, to0Is a reference value, omega, of the oxidizer tank temperatureopfiIs the partial derivative of the oxidant flow to the tank pressure,pf0is a reference value, omega, of the combustion agent tank pressureotfiIs the partial derivative of the oxidant flow to the tank temperature, tf0Is a reference value, omega, of the temperature of the combustion agent tankf0iTheoretical value of combustion agent flow, omegafpoiIs the partial derivative, omega, of the flow of the combustion agent with respect to the pressure in the oxygen tankftoiIs the partial derivative, omega, of the flow of the combustion agent with respect to the temperature of the oxygen tankfpfiIs the partial derivative of the flow of the combustion agent to the tank pressure, omegaftfiIs the partial derivative of the fuel flow to the tank temperature.
3. The on-orbit assessment method under abnormal interruption of track control of 490N thruster, according to claim 2, wherein in the step 2, the propellant consumption Δ m of 10N bottom thruster is calculatedCDAs shown in formula (2);
Figure FDA0003135961610000041
in the formula (2), T0The time is the beginning time of the bottom sinking of the 10N thruster, the time is the length of the bottom sinking of the 10N thruster, the lower foot mark j is the number of the bottom sinking thruster, and the time is the number of the bottom sinking thrusterojIs the oxidant consumption, Δ m, of the 10N bottoming thruster of number jfjIs the combustion agent consumption, Δ m, of the 10N bottoming thruster of number jocdIs the oxidant consumption of the 10N bottoming thruster, Delta mfcdIs the combustion agent consumption of the 10N bottoming thruster.
4. The on-orbit assessment method under abnormal interruption of track control of 490N thruster, as claimed in claim 3, wherein in said step 3, Δ M490The formula (3) is shown in the formula;
Figure FDA0003135961610000042
in the formula (3), T0+Δt～T1For 490N thruster operation period, T0+ Deltat is the end time of bottom sinking of the 10N thruster, T1At the time of start of ignition abnormal disturbance 490N,
Figure FDA0003135961610000043
at 490N thruster oxidant mass second flow,
Figure FDA0003135961610000044
combustion mass second flow, Δ M, for 490N thrustero490Is 490N thruster oxidant consumption, Δ Mf490Is the 490N thruster combustion consumption.
5. The on-orbit assessment method under abnormal interruption of track control of 490N thruster, as claimed in claim 4, wherein in said step 5, FiAnd F490The calculation formulas of (A) and (B) are respectively shown as a formula (5) and a formula (6);
Figure FDA0003135961610000051
Figure FDA0003135961610000052
in the formula, the lower foot mark I is the number of the 10N thruster, IiIs the specific impulse of the 10N thruster, and g is the gravity acceleration; i is490Is the 490N thruster thrust specific impulse.
6. The on-orbit assessment method under abnormal interruption of track control of 490N thruster, as claimed in claim 5, wherein in said step 8, Fix,Fiy,FizAnd F490x,F490y,F490zThe calculation formulas of (a) and (b) are respectively shown as a formula (8) and a formula (9);
Figure FDA0003135961610000053
Figure FDA0003135961610000054
wherein alpha isi,βi,γiThe direction cosine angle between the nozzle axis of each 10N thruster and the three axes of the satellite body X, Y, Z; alpha is alpha490,β490,γ490Is the directional cosine angle of the nozzle axis of each 490 thruster with respect to the three axes of the satellite body X, Y, Z.
7. The on-orbit evaluation method under abnormal interruption of track control of the 490N thruster, according to claim 6, wherein in the step 9,
Figure FDA0003135961610000055
the formula (2) is shown as formula (10);
Figure FDA0003135961610000061
wherein, FaxIs the component of the average thrust of the attitude control thruster on the X axis of the satellite body, FayIs the component of the average thrust of the attitude control thruster on the Y axis of the satellite body, FazIs the component of the average thrust of the attitude control thruster on the Z axis of the satellite body, delta t2fireIs 490N the ignition abnormal disturbance start time T1To 490N ignition abort time T2And the duration length, and the lower foot mark k is the serial number of the satellite attitude control thruster.
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