CN113379297B - 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 PDFInfo
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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 comprises the following specific steps of: 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 actual measured tracks at the moment of abnormal ignition interruption, and calibrating the 490N thruster to obtain actual 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 abnormality is interrupted.
Description
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 orbital transfer process generally includes the processes of beginning of bottom-down of the 10N thruster, ending of bottom-down of the 10N thruster, ignition of the 490N thruster, shutdown of the 490N thruster, and the like. During the process from the track transfer attitude abnormal disturbance to the track transfer interruption of 490N, the attitude control thruster participates in the work for a long time, so that the actual effect of the track control thruster is influenced, and the comprehensive thrust of the track control and the attitude control is inconsistent with the actual track control thrust. It would be difficult to accurately evaluate the 490N thruster with conventional thruster evaluation methods under rail control abort conditions.
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 evaluation precision of the thrust of an engine after the track transfer abnormal interruption of a GEO satellite 490N.
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
And mass second flow of the combustion agent
Step 2: calculating propellant consumption delta m of 10N bottom-sinking thruster CD ；
Step (ii) of3: calculating 490N thruster ignition propellant consumption delta M 490 ；
And 4, step 4: calculating T 1 Time of day satellite quality
The quality of the satellite before orbit control;
and 5: calculating the actually measured thrust F of each 10N thruster i And 490N thruster measured thrust F 490 ；
Step 6: will T 0 Number of satellite orbits at time
Satellite quality
As an initial value, the actually measured thrust F of the 10N bottoming thruster i And the actual measurement thrust F of the 10N bottom-sinking thruster ignition time length delta t and 490N thrusters 490 490N thruster ignition time length delta t before abnormal disturbance begins 1fire And 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 T 1 Theoretical number of orbits of
And 7: calculating T 1 ～T 2 Working time length delta t of each attitude control thruster between moments k ，T 1 Ignition abnormal disturbance start time, T, of 490N 2 Ignition abort time for 490N; Δ t k ＝t ke -t ks ；t ke Is 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 ignition ks The accumulated working time of the thruster with the number of k at the track transfer starting moment;
and 8: calculating the component F of each 10N thruster in the satellite body coordinate system ix ,F iy ,F iz And component F of thrust of 490N thruster in satellite body coordinate system 490x ,F 490y ,F 490z ；
And step 9: calculating 490N an ignition abnormal disturbance starting time T 1 To 490N ignition abort time T 2 Average thrust of each attitude control thruster
Step 10: calculating T 1 ～T 2 Combined thrust between moments
Step 11: starting time T of abnormal disturbance in the track control period 1 Number of tracks
Satellite quality
As an initial value, 490N thruster thrust F 490 490N ignition abnormality disturbance start time T 1 To 490N ignition abort time T 2 Duration Δ t 2fire And satellite attitude parameters as input conditions; calculating the abnormal ignition interruption time T 2 Theoretical number of orbits of
Step 12: precisely determining the abnormal interruption time T by using the track measurement data 2 Number of actual measurement tracks
Carrying out 490N thruster calibration to obtain actual calibration thrust
Step 13: evaluation 490N thruster thrust force actual F during onset of anomalous disturbance to abort 490x_real ,F 490y_real ,F 490z_real ；
The present invention is also characterized in that,
in the step 1, a calculation formula is shown as a formula (1);
in the formula (1), the lower subscript i is the thruster number, p o Is the oxidant tank pressure, p f Is the combustion agent tank pressure, t o Is the oxidant storage tank temperature, t f Is the combustion agent storage tank temperature, omega o0i Is the theoretical value of the flow of the oxidizing agent, omega opoi Is the partial derivative of the oxidant flow to the oxygen tank pressure, p o0 Is a reference value, ω, of the oxidizer tank pressure otoi Is the partial derivative of the oxidant flow to the oxygen box temperature, t o0 Is a reference value, omega, of the oxidizer tank temperature opfi Is the partial derivative of the oxidant flow against the tank pressure, p f0 Is a reference value, omega, of the combustion-agent tank pressure otfi Is the partial derivative of the oxidant flow with respect to the tank temperature, t f0 Is a reference value, omega, of the temperature of the combustion agent tank f0i Theoretical value of flow of combustion agent, omega fpoi Is the partial derivative, omega, of the flow of the combustion agent with respect to the pressure in the oxygen tank ftoi Is the partial derivative, omega, of the flow of the combustion agent with respect to the temperature of the oxygen tank fpfi Is the partial derivative of the flow of the combustion agent with respect to the pressure in the fuel tank, omega ftfi Is the partial derivative of the flow of the combustion agent with respect to the temperature of the fuel tank.
In step 2, calculating the propellant consumption delta m of the 10N bottoming thruster CD As shown in formula (2);
in the formula (2), T 0 The time is the bottom sinking starting time of the 10N thruster, delta t is the bottom sinking time length of the 10N thruster, a lower foot mark j is the number of the bottom sinking thruster, and delta m oj Is the oxidant consumption, Δ m, of the 10N bottoming thruster of number j fj Is the combustion agent consumption, Δ m, of the 10N bottoming thruster of number j ocd Is the oxidant consumption of the 10N bottoming thruster, delta m fcd Is the combustion agent consumption of the 10N bottoming thruster.
In step 3,. DELTA.M 490 The formula (3) is shown in the formula;
in the formula (3), T 0 +Δt～T 1 For 490N thruster operation period, T 0 + delta T is the bottom sinking finish time of the 10N thruster, T 1 At the start time of the ignition abnormality disturbance for 490N,
at 490N thruster oxidant mass second flow,
combustion mass second flow, Δ M, for 490N thruster o490 Is 490N thruster oxidant consumption, Δ M f490 Is 490N thruster combustion agent consumption.
In step 5, F i And F 490 The calculation formulas of (a) and (b) are respectively shown in formula (5) and formula (6);
in the formula, the lower subscript I is the number of the 10N thruster, I i Is a thrust of 10NSpecific impulse of the device, g is gravity acceleration; i is 490 Is the 490N thruster thrust specific impulse.
In step 8, F ix ,F iy ,F iz And F 490x ,F 490y ,F 490z The calculation formulas of (a) and (b) are respectively shown as a formula (8) and a formula (9);
wherein alpha is i ,β i ,γ i The direction cosine angles between the axis of the spray pipe of each 10N thruster and the three axes X, Y and Z of the satellite body are included; alpha (alpha) ("alpha") 490 ,β 490 ,γ 490 Is the direction cosine angle between the jet pipe axis of each 490 thruster and the three axes X, Y and Z of the satellite body.
In the step 9, the process is carried out,
the formula (2) is shown as formula (10);
wherein, F ax Is the component of the average thrust of the attitude control thruster on the X axis of the satellite body, F ay Is the component of the average thrust of the attitude control thruster on the Y axis of the satellite body, F az Is the component of the average thrust of the attitude control thruster on the Z axis of the satellite body, delta t 2fire Is 490N the ignition abnormal disturbance start time T 1 To 490N ignition abort time T 2 And the duration length, and the lower foot mark k is the serial number of the satellite attitude control thruster.
The beneficial effects of the invention are: 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 the on-orbit stable operation of a spacecraft.
Drawings
FIG. 1 is a flow chart of an on-track evaluation method under track control abnormal interruption of a 490N thruster according to the 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 the oxidant of each thruster
And mass second flow of the combustion agent
As shown in formula (1);
in the formula (1), the lower subscript i is the thruster number, p o Is the oxidant tank pressure, p f Is the combustion agent tank pressure, t o Is the oxidant storage tank temperature, t f Is the combustion agent storage tank temperature, omega o0i Is the theoretical value of the flow of the oxidant, omega opoi Is the partial derivative of the oxidant flow to the oxygen tank pressure, p o0 Is a reference value, ω, of the oxidizer tank pressure otoi Is the partial derivative of the oxidant flow to the oxygen box temperature, t o0 Is a reference value, ω, of the temperature of the oxidizer tank opfi Is the partial derivative of the oxidant flow against the tank pressure, p f0 Is a reference value, omega, of the combustion agent tank pressure otfi Is the partial derivative of the oxidant flow with respect to the tank temperature, t f0 Is a reference value, omega, of the temperature of the combustion agent tank f0i Theoretical value of flow of combustion agent, omega fpoi Is the partial derivative, omega, of the flow of the combustion agent with respect to the pressure in the oxygen tank ftoi Is the partial derivative, omega, of the flow of the combustion agent with respect to the temperature of the oxygen tank fpfi Is the partial derivation of the flow of the combustion agent against the pressure in the fuel tankNumber, omega ftfi Is the partial derivative of the flow of the combustion agent with respect to the temperature of the fuel tank;
and 2, step: calculating propellant consumption delta m of 10N bottoming thruster CD As shown in formula (2);
in formula (2), T 0 The time is the bottom sinking starting time of the 10N thruster, delta t is the bottom sinking time length of the 10N thruster, a lower foot mark j is the number of the bottom sinking thruster, and delta m oj Is the oxidant consumption, Δ m, of the 10N bottoming thruster of number j fj Is the combustion agent consumption, Δ m, of the 10N bottoming thruster of number j ocd Is the oxidant consumption of the 10N bottoming thruster, delta m fcd Is the combustion agent consumption of the 10N bottoming thruster;
and 3, step 3: calculating 490N thruster ignition propellant consumption delta M 490 As shown in formula (3);
in formula (3), T 0 +Δt～T 1 For 490N thruster operation period, T 0 + Deltat is the end time of bottom sinking of the 10N thruster, T 1 At the start time of the ignition abnormality disturbance for 490N,
at 490N thruster oxidant mass second flow,
at 490N thruster burner mass second flow,
and
the calculation method is the same as the step 1, delta M o490 Is 490N thruster oxidant consumption, Δ M f490 Is the 490N thruster combustion consumption.
And 4, step 4: calculating T 1 Time of day satellite mass M T1 As shown in formula (4);
in the formula (4), the reaction mixture is,
the quality of the satellite before orbit control;
and 5: calculating the actual measurement thrust F of each 10N thruster i And 490N thruster measured thrust F 490 Respectively represented by formula (5) and formula (6);
in the formula, the lower subscript I is the number of the 10N thruster, I i Is the specific impulse of the 10N thruster, g is the gravity acceleration; i is 490 Is 490N thruster specific impulse;
step 6: will T 0 Number of satellite orbits at time
Satellite quality
As an initial value, the actually measured thrust F of the 10N bottoming thruster i And the actual measurement thrust F of the 10N bottoming thruster ignition time length delta t and 490N thruster 490 490N thruster ignition time delta t before abnormal disturbance begins 1fire And satellite attitude parameters during ignition as input conditions. Track dynamics equation-based precise numerical method track extrapolation calculation track control abnormal disturbance starting time T 1 Theoretical number of orbits of
And 7: calculating T 1 ～T 2 The working time length delta t of each attitude control thruster between moments k ，T 1 Ignition abnormal disturbance start time, T, of 490N 2 Ignition abort time for 490N; as shown in formula (7);
Δt k ＝t ke -t ks (7)；
wherein, t ke The cumulative working time t of the thruster numbered k from the ignition abnormal disturbance start at 490N to the ignition end at 490N ks Accumulated working time of the thruster with the number of k at the track change starting moment;
and 8: calculating component F of each 10N thruster in a satellite body coordinate system ix ,F iy ,F iz And component F of thrust of 490N thruster in satellite body coordinate system 490x ,F 490y ,F 490z As shown in formulas (8) and (9);
wherein alpha is i ,β i ,γ i The direction cosine angles between the axis of the spray pipe of each 10N thruster and the three axes X, Y and Z of the satellite body are included; alpha (alpha) ("alpha") 490 ,β 490 ,γ 490 The cosine angles of the jet pipe axis of each 490 thruster and the three axes X, Y and Z of the satellite body are formed;
and step 9: calculating 490N an ignition abnormal disturbance starting time T 1 To 490N ignition abort time T 2 Mean thrust of each attitude control thruster
As shown in formula (10);
wherein, F ax Is the component of the average thrust of the attitude control thruster on the X axis of the satellite body, F ay Is the component of the average thrust of the attitude control thruster on the Y axis of the satellite body, F az Is the component of the average thrust of the attitude control thruster on the Z axis of the satellite body, delta t 2fire Is 490N the ignition abnormality disturbance start time T 1 To 490N ignition abort time T 2 And the duration length, and the lower foot mark k is the serial number of the satellite attitude control thruster.
Step 10: calculating T 1 ～T 2 Combined thrust between moments
As shown in formula (11);
step 11: starting time T of abnormal disturbance in the track control period 1 Number of tracks
Satellite quality
As an initial value, 490N thruster thrust F 490 490N ignition abnormal disturbance start time T 1 To 490N ignition abort time T 2 Duration Δ t 2fire And satellite attitude parameters as input conditions; calculating the abnormal ignition interruption time T based on the method of the step 6 2 Theoretical number of orbits of
Step 12: precisely fixing the track by using the track measuring data to determine the abnormal interruption time T 2 Number of actual measurement tracksσ T2_real And carrying out 490N thruster calibration to obtain actual calibration thrust
(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 thruster 490x_real ,F 490y_real ,F 490z_real As shown in formula (12);
examples
In a specific application example, an adopted east four-platform satellite launches an orbit in 2020, the mass of the satellite in the orbit 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 2N 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 10N thrusters in the X-axis direction and the Y-axis 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
Mass second flow of combustion agent
Wherein the content of the first and second substances,the lower subscript i is the thruster number, p o Is the oxidant tank pressure, p f Is the combustion agent tank pressure, t o Is the oxidant storage tank temperature, t f Is the combustion agent storage tank temperature, omega o0i Is the theoretical value of the flow of the oxidizing agent, omega opoi Is the partial derivative of the oxidant flow to the oxygen tank pressure, p o0 Is a reference value, ω, of the oxidizer tank pressure otoi Is the partial derivative of the oxidant flow to the oxygen box temperature, t o0 Is a reference value, ω, of the temperature of the oxidizer tank opfi Is the partial derivative of the oxidant flow to the tank pressure, p f0 Is a reference value, omega, of the combustion-agent tank pressure otfi Is the partial derivative of the oxidant flow to the tank temperature, t f0 Is a reference value, omega, of the temperature of the combustion agent tank f0i Theoretical value of combustion agent flow, omega fpoi Is the partial derivative of the flow of the combustion agent with respect to the pressure in the oxygen tank, omega ftoi Is the partial derivative, omega, of the flow of the combustion agent with respect to the temperature of the oxygen tank fpfi Is the partial derivative of the flow of the combustion agent with respect to the pressure in the fuel tank, omega ftfi Is the partial derivative of the fuel flow to the tank temperature.
Step 2: calculating propellant consumption delta m of 4 10N bottom-sinking thrusters CD ；
Δm CD ＝Δm ocd +Δm fcd ＝ΣΔm oj +ΣΔm fj
Wherein, T 0 The time is the beginning time of the bottom sinking of the 10N thruster, the time of the bottom sinking of the 10N thruster is 232 seconds, a lower foot mark j is the number of the bottom sinking thruster, and the number is delta m oj Is the oxidant consumption, Δ m, of the 10N bottoming thruster of number i fj Is the combustion agent consumption, Δ m, of the 10N bottoming thruster of number j ocd Is the oxidant consumption of the 10N bottoming thruster, delta m fcd Is the combustion agent consumption of the 10N bottoming thrusterAmount of the compound (A).
And 3, step 3: calculating 490N thruster ignition propellant consumption delta M 490 ；
ΔM 490 ＝ΔM o490 +ΔM f490
Wherein, T 0 +Δt～T 1 For 490N thruster operation period, T 0 + delta T is the bottom sinking finish time of the 10N thruster, T 1 At the time of start of ignition abnormal disturbance 490N,
at 490N thruster oxidant mass second flow,
at 490N thruster burner mass second flow,
and
the calculation method is the same as the step 1, delta M o490 Is 490N thruster oxidant consumption, Δ M f490 Is the 490N thruster combustion consumption.
And 4, step 4: calculating T 1 Time of day satellite quality
Wherein the content of the first and second substances,
the quality of the satellite before orbit control.
And 5: calculating the thrust F of 14 10N thrusters i And 490N thruster thrust magnitude F 490 ；
Wherein, the lower foot mark I is the number of the 10N thruster, I i Is the specific impulse of the 10N thruster, and g is the gravity acceleration; i is 490 Is the 490N thruster thrust specific impulse.
And 6: will T 0 Number of satellite orbits at time
Satellite quality
As an initial value, the actually measured thrust F of the 10N bottoming thruster i And the actual measurement thrust F of the 10N bottom-sinking thruster ignition time length delta t and 490N thrusters 490 490N thruster ignition time delta t before abnormal disturbance begins 1fire And satellite attitude parameters during ignition as input conditions. Track dynamics equation based precise numerical method track extrapolation calculation track control abnormal disturbance starting time T 1 Theoretical number of orbits of
And 7: calculating T 1 ～T 2 Working time length delta t of each attitude control thruster between moments k ，T 1 Ignition abnormal disturbance start time, T, of 490N 2 The ignition abort time is 490N.
Δt k ＝t ke -t ks
Wherein t is ke Is 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 ignition ks And the accumulated working time of the thruster with the number k at the track change starting moment.
And 8: calculating component F of 14 10N thrusters in a satellite body coordinate system ix ,F iy ,F iz And component F of thrust of 490N thruster in satellite body coordinate system 490x ,F 490y ,F 490z ；
{F 490x ＝F 490 ·cos(α 490 )
{F 490y ＝F 490 ·cos(β 490 )
{F 490z ＝F 490 ·cos(γ 490 )
Wherein alpha is i ,β i ,γ i The cosine angles of the jet pipe axes of each thruster and the three axes of the satellite body X, Y and Z are included; alpha is alpha 490 ,β 490 ,γ 490 Is the cosine angle between the jet pipe axis of the 490 thruster and the three axes of the satellite body X, Y and Z.
And step 9: calculating 490N an ignition abnormal disturbance starting time T 1 To 490N ignition abort time T 2 Average thrust of each attitude control thruster
Wherein F ax Is the component of the average thrust of the attitude control thruster on the X axis of the satellite body, F ay Is the component of the average thrust of the attitude control thruster on the Y axis of the satellite body, F az Is the component of the average thrust of the attitude control thruster on the Z axis of the satellite body, delta t 2fire Is 490N ignition abnormal disturbance starting time T 1 To 490N ignition abort time T 2 Duration length, lower footmark k is satellite 14 station 10N thruster number.
Step 10: calculating T 1 ～T 2 Combined thrust between moments
Step 11: starting time T of abnormal disturbance in the track control period 1 Number of tracks
Satellite quality
As an initial value, 490N thruster thrust F 490 490N ignition abnormal disturbance start time T 1 To 490N ignition abort time T 2 Duration Δ t 2fire And satellite attitude parameters as input conditions. Calculating the abnormal ignition interruption time T based on the method of the step 6 2 Theoretical number of orbits of
Step 12: precisely fixing the track by using the track measuring data to determine the abnormal interruption time T 2 Number of actual measurement tracks
Carrying out 490N thruster calibration to obtain actual calibration thrust
Step 13: estimating 490N actual thrust F during the period from the onset of an anomalous disturbance to an anomalous shutdown of the thruster 490x_real ,F 490y_real ,F 490z_real 。
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 after the 490N orbital transfer abnormal interruption of a GEO satellite 490N.
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 the mass second flow of the oxidant of the 10N bottoming thruster, the 10N attitude control thruster and the 490N thruster
And mass second flow of the combustion agent
Step 2: calculating propellant consumption delta m of 10N bottoming thruster CD ；
And step 3: calculating 490N thruster ignition propellant consumption delta M 490 ；
And 4, step 4: calculating T 1 Time of day satellite quality
The quality of the satellite before orbit control;
and 5: calculating the actually measured thrust F of the 10N bottoming thruster and the 10N attitude control thruster i And 490N thruster measured thrust F 490 ；
And 6: will T 0 Number of satellite orbits at time
Satellite quality
As an initial value, the actually measured thrust F of the 10N bottoming thruster i And the actual measurement thrust F of the 10N bottoming thruster ignition time length delta t and 490N thruster 490 490N thruster ignition time length delta t before abnormal disturbance begins 1firre And 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 T 1 Theoretical number of orbits of
And 7: calculating T 1 ～T 2 Working time length delta t of 10N attitude control thruster between moments k ，T 1 Ignition abnormal disturbance start time, T, of 490N thruster 2 An 490N thruster fire abort time; Δ t k ＝t ke -t ks ；t ke The cumulative working time t of the 10N attitude control thruster with the number of k from the ignition abnormal disturbance start of the 490N thruster to the ignition end of the 490N thruster ks The accumulated working time of the 10N attitude control thrusters with the number of k at the track transfer starting moment is shown;
and 8: calculating the component F of each 10N bottom-sinking thruster and 10N attitude control thruster in the satellite body coordinate system ix ,F iy ,F iz And component F of thrust of 490N thruster in satellite body coordinate system 490x ,F 490y ,F 490z ；
And step 9: calculating 490N thruster ignition abnormal disturbance starting moment T 1 To 490N thruster ignition abort time T 2 Mean thrust of 10N attitude control thrusters
Step 10: calculating T 1 ～T 2 Combined thrust between moments
Step 11: starting time T of abnormal disturbance in the track control period 1 Number of tracks
Satellite quality
As an initial value, 490N thruster thrust F 490 490N thruster abnormal ignition disturbance starting time T 1 Moment T of abnormal ignition interruption of 490N thruster 2 Duration Δ t 2fire And satellite attitude parameters as input conditions; calculating the abnormal ignition interruption time T 2 Theoretical number of orbits of
Step 12: precisely fixing the track by using the track measuring data to determine the abnormal interruption time T 2 Number of actual measurement tracks
Carrying out 490N thruster calibration to obtain actual calibration thrust
Step 13: estimating 490N actual thrust F during the period from the onset of an anomalous disturbance to an anomalous shutdown of the thruster 490x_real ,F 490y_real ,F 490z_real ；
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);
in the formula (1), the lower foot mark i is the number of the 10N bottoming thruster, the 10N attitude control thruster and the 490N thruster, and p o Is the oxidant tank pressure, p f Is the combustion agent tank pressure, t o Is the oxidant storage tank temperature, t f Is the combustion agent storage tank temperature, omega o0i Is the theoretical value of the flow of the oxidant, omega opoi Is the partial derivative of the oxidant flow to the oxygen tank pressure, p o0 Is a reference value, ω, of the oxidizer tank pressure otoi Is the partial derivative of the oxidant flow to the oxygen box temperature, t o0 Is a reference value, ω, of the temperature of the oxidizer tank opfi Is the partial derivative of the oxidant flow to the tank pressure, p f0 Is a reference value, omega, of the combustion agent tank pressure otfi Is the partial derivative of the oxidant flow with respect to the tank temperature, t f0 Is a reference value, omega, of the temperature of the combustion-agent tank f0i Theoretical value of flow of combustion agent, omega fpoi Is the partial derivative, omega, of the flow of the combustion agent with respect to the pressure in the oxygen tank ftoi Is the partial derivative of the flow of the combustion agent with respect to the temperature of the oxygen box, omega fpfi Is the partial derivative of the flow of the combustion agent with respect to the pressure in the fuel tank, omega ftfi Is 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 calculated CD As shown in formula (2);
Δm CD ＝Δm ocd +Δm fcd ＝∑Δm oj +∑Δm fj
in formula (2), T 0 The bottom sinking starting time of the 10N thruster is set, delta t is the bottom sinking time length of the 10N thruster, a lower foot mark j is the number of the bottom sinking thruster, and delta mo j Is the oxidant consumption, Δ m, of the 10N bottoming thruster of number j fj Is the combustion agent consumption, Δ mo, of the 10N bottoming thruster of number j cd Is the oxidant consumption of the 10N bottoming thruster, delta m fcd Is the combustion agent consumption of the 10N bottoming thruster.
4. The on-track assessment method under abnormal interruption of track control of 490N thruster, as claimed in claim 3, wherein, in said step 3, Δ M 490 The formula (3) is shown in the formula;
ΔN 490 ＝ΔN o490 +ΔM f490
in the formula (3), T 0 +Δt～T 1 For 490N thruster operation period, T 0 + Deltat is the bottom sinking ending time of the 10N bottom sinking thruster, T 1 At the 490N thruster firing anomalous perturbation start time,
at 490N thruster oxidant mass second flow,
combustion mass second flow, Δ M, for 490N thruster o490 Is 490N thruster oxidant consumption, Δ M f490 Is the 490N thruster combustion consumption.
5. The on-track assessment method under abnormal interruption of track control of 490N thruster, as claimed in claim 4, wherein in said step 5, F i And F 490 The calculation formulas of (a) and (b) are respectively shown in formula (5) and formula (6);
in the formula, the lower foot mark I is the serial number of the 10N bottoming thruster and the 10N attitude control thruster, and I i Is a 10N bottoming thruster and a 10N attitude control thruster, and g is gravity acceleration; (ii) a I.C. A 490 Is 490N thruster 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, F ix ,F iy ,F iz And F 490x ,F 490y ,F 490z The calculation formulas of (a) and (b) are respectively shown in formula (8) and formula (9);
wherein alpha is i ,β i ,γ i For each 10N bottomThe axis of a spray pipe of the thruster forms a cosine angle with the directions of the three axes X, Y and Z of the satellite body; alpha is alpha 490 ,β 490 ,γ 490 The cosine angle between the axis of the jet pipe of each 490N thruster and the three axes X, Y and Z of the satellite body is provided.
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,
the formula (2) is shown as formula (10);
wherein, F ax Is the component of the average thrust of the 10N attitude control thruster on the X axis of the satellite body, F ay Is the component of the average thrust of the 10N attitude control thruster on the Y axis of the satellite body, F az Is the component of the average thrust of the 10N attitude control thruster on the Z axis of the satellite body, delta t 2fire Is ignition abnormal disturbance starting time T of 490N thruster 1 To 490N thruster ignition abort time T 2 Duration length, lower footmark k is satellite 10N attitude control thruster number.
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