A management method for the working mode of chemical propulsion orbit control

Abstract

The present invention discloses a management method for the working mode of chemical propulsion orbit control. Step 1: According to the orbit control data packet, enter the orbit control attitude adjustment mode at the attitude adjustment start time. Step 2: After entering the orbit control attitude adjustment mode, judge whether the attitude adjustment process is normal. If it is normal, continue the attitude adjustment process until the jet start time is reached; if it is abnormal, exit the orbit control and output the reason for exiting the orbit control. Step 3: According to the orbit control data packet, enter the orbit control jet mode at the jet start time. Step 4: After entering the orbit control jet mode, judge whether the jet process is normal. If it is normal, continue the jet process until the jet end time is reached, end the orbit control, and output the reason for exiting the orbit control as: normal end; if it is abnormal, exit the orbit control and output the reason for exiting the orbit control. The chemical propulsion orbit control is divided into two working modes: the orbit control attitude adjustment mode and the orbit control jet mode, which is convenient for clearly tracking the orbit control stage.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft orbit control, and particularly relates to a management method for the working mode of chemical propulsion orbit control. Background Art

[0002] In the existing working mode for chemical propulsion orbit control, the entire process of chemical propulsion orbit control is regarded as one mode, and it is impossible to clearly track the stages of orbit control. It is impossible to directly determine whether to end the orbit control and exit or exit abnormally after the chemical propulsion orbit control ends. The reason for the abnormal exit of the chemical propulsion orbit control cannot be directly obtained, and historical data needs to be queried for comprehensive judgment. Summary of the Invention

[0003] Aiming at the problems existing in the prior art, the present invention provides a management method for the working mode of chemical propulsion orbit control, which divides the chemical propulsion orbit control into two working modes: orbit control attitude adjustment mode and orbit control jet mode, so as to clearly track the orbit control stages.

[0004] The technical solution of the present invention is: a management method for the working mode of chemical propulsion orbit control, and the specific steps are as follows:

[0005] Step 1: According to the orbit control data packet, enter the orbit control attitude adjustment mode when reaching the attitude adjustment start time;

[0006] Step 2: After entering the orbit control attitude adjustment mode, judge whether the attitude adjustment process is normal. If it is normal, continue the attitude adjustment process until reaching the jet start time; if it is abnormal, exit the orbit control and output the reason for exiting the orbit control.

[0007] Step 3: According to the orbit control data packet, enter the orbit control jet mode when reaching the jet start time;

[0008] Step 4: After entering the orbit control jet mode, judge whether the jet process is normal. If it is normal, continue the jet process until reaching the jet end time, end the orbit control, and output the reason for exiting the orbit control as: normal end; if it is abnormal, exit the orbit control and output the reason for exiting the orbit control.

[0009] Further, the first abnormal judgment condition in Step 2: In the orbit control attitude adjustment mode, within the continuous judgment time t gk , the inertial system attitude determination mode is invalid, and set the reason for exiting the orbit control as: attitude determination invalid;

[0010] The second abnormal judgment condition in Step 2: According to the orbit control data packet, within the continuous judgment time t gk before entering the orbit control jet mode, the attitude of any axis exceeds the threshold δ gk , and set the reason for exiting the orbit control as: attitude adjustment not in place;

[0011] In Step 2, the relationship between the first and second abnormal judgment conditions is OR.

[0012] Furthermore, the first abnormal judgment condition in Step 4: In the orbit control jet mode, within the continuous judgment time t gk the inertial system attitude determination mode is invalid, and the reason for setting the exit of the orbit control is: attitude determination is invalid;

[0013] The second abnormal judgment condition in Step 4: In the orbit control jet mode, within the continuous judgment time t gk for any axis, the attitude exceeds the threshold δ gk , and the reason for setting the exit of the orbit control is: angle out of tolerance during jetting;

[0014] The third abnormal judgment condition in Step 4: In the orbit control jet mode, within the continuous judgment time t gk for any axis, the angular velocity in the orbital system exceeds the threshold ω gk and the reason for setting the exit of the orbit control is: angular velocity out of tolerance during jetting;

[0015] The relationship between the first, second, and third abnormal judgment conditions in Step 4 is OR.

[0016] Furthermore, t gk is 10 - 30 s; T1 is 10 - 60 s, and T1 is greater than t gk ; δ gk is 5° - 15°; ω gk is 0.1° / s - 0.5° / s.

[0017] The beneficial effects of the present invention are:

[0018] 1. Divide the chemical propulsion orbit control into two working modes: orbit control attitude adjustment mode and orbit control jet mode, which is convenient for clearly tracking the orbit control stage.

[0019] 2. Output the reason for exiting the orbit control without the need to trace historical data.

[0020] 3. Clearly manage the working modes of chemical propulsion orbit control and improve the reliability of satellite orbit control. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a flowchart of the management method for the working modes of chemical propulsion orbit control. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0022] The present invention will be further described below with reference to the drawings.

[0023] As Figure 1 shown, for the management method of the working modes of chemical propulsion orbit control, the specific steps are as follows:

[0024] Step 1: According to the trajectory control data packet, enter the trajectory control and attitude adjustment mode at the attitude adjustment start time.

[0025] Step 2: After entering the trajectory control and attitude adjustment mode, judge whether the attitude adjustment process is normal. If it is normal, continue the attitude adjustment process until the jet start time is reached; if it is abnormal, exit the trajectory control and output the reason for exiting the trajectory control.

[0026] Furthermore: The first abnormal judgment condition in Step 2: In the trajectory control and attitude adjustment mode, within the continuous judgment time t gk the inertial system attitude determination mode is invalid, and set the reason for exiting the trajectory control as: attitude determination invalid;

[0027] Furthermore: The second abnormal judgment condition in Step 2: According to the trajectory control data packet, within the continuous judgment time t gk before entering the trajectory control jet mode T1, the attitude of any axis exceeds the threshold δ gk with respect to the target attitude, and set the reason for exiting the trajectory control as: attitude adjustment not in place;

[0028] The relationship between the first and second abnormal conditions in Step 2 is OR.

[0029] Step 3: According to the trajectory control data packet, enter the trajectory control jet mode at the jet start time.

[0030] Step 4: After entering the trajectory control jet mode, judge whether the jet process is normal. If it is normal, continue the jet process until the jet end time is reached, end the trajectory control, and output the reason for exiting the trajectory control as: normal end; if it is abnormal, exit the trajectory control and output the reason for exiting the trajectory control.

[0031] Furthermore: The first abnormal judgment condition in Step 4: In the trajectory control jet mode, within the continuous judgment time t gk the inertial system attitude determination mode is invalid, and set the reason for exiting the trajectory control as: attitude determination invalid;

[0032] Furthermore: The second abnormal judgment condition in Step 4: In the trajectory control jet mode, within the continuous judgment time t gk the attitude of any axis exceeds the threshold δ gk with respect to the target attitude, and set the reason for exiting the trajectory control as: angle out of tolerance during jet;

[0033] Furthermore: The third abnormal judgment condition in Step 4: In the trajectory control jet mode, within the continuous judgment time t gk the angular velocity of any axis in the orbital system exceeds the threshold ω gk and set the reason for exiting the trajectory control as: angular velocity out of tolerance during jet;

[0034] The relationship between the first, second, and third abnormal conditions in Step 4 is OR.

[0035] Above: tgk Any value within 10 - 30 s can be selected as needed; T1 can be any value within 10 - 60 s as needed, and T1 > t gk ; δ gk Any value within 5° - 15° can be selected as needed; ω gk Any value within 0.1° / s - 0.5° / s can be selected as needed.

[0036] Example 1

[0037] A certain type of satellite was used to test this method: In the standby mode, a trajectory control data packet was sent (parameters: jet start time: 10:32:47, December 17, 2021, attitude adjustment duration: 600 s, jet duration: 50 s, trajectory control mode: ascending trajectory control, attitude adjustment target quaternion q1: 0, attitude adjustment target quaternion q2: 0, attitude adjustment target quaternion q3: 0, attitude adjustment target quaternion q4: 1).

[0038] The parameter selection for this type of satellite is as follows: t gk : 20 s; T1: 60 s; δ gk : 10°; ω gk : 0.3° / s.

[0039] The satellite switched from the attitude control working mode from the standby mode to the trajectory control attitude adjustment mode at 10:22:47, December 17, 2021. The attitude determination mode was star sensor attitude determination. The attitude adjustment was completed at 10:24:10, December 17, 2021. It switched from the trajectory control attitude adjustment mode to the trajectory control jet mode at 10:32:47, December 17, 2021. The attitude determination mode was gyro integration attitude determination. The control mode was phase plane control. The jet ended at 10:32:58, December 17, 2021. The working mode switched from the trajectory control jet mode to the standby mode. The reason for exiting the trajectory control was: normal end.

[0040] Example 2

[0041] A certain type of satellite was used to test this method: In the standby mode, a trajectory control data packet was sent (parameters: jet start time: 08:42:12, December 18, 2021, attitude adjustment duration: 600 s, jet duration: 67 s, trajectory control mode: ascending trajectory control, attitude adjustment target quaternion q1: 0, attitude adjustment target quaternion q2: 0, attitude adjustment target quaternion q3: 0, attitude adjustment target quaternion q4: 1).

[0042] The parameter selection for this type of satellite is as follows: t gk : 20 s; T1: 60 s; δ gk : 10°; ω gk : 0.3° / s.

[0043] The satellite switched from the standby mode to the orbit control and attitude adjustment mode at 08:32:12 on December 18, 2021. At 08:34:10, the single-unit status was set, and the attitude determination mode was set to unable to determine the attitude. At 08:34:30, the working mode switched from the orbit control and attitude adjustment mode to the standby mode. The reason for exiting the orbit control was: attitude determination was invalid.

[0044] Example 3

[0045] A certain type of satellite was used to test this method: In the standby mode, an orbit control data packet was sent (parameters: jet start time: 15:21:40 on December 19, 2021, attitude adjustment duration: 120 s, jet duration: 55 s, orbit control mode: descending orbit control, attitude adjustment target quaternion q1: 0, attitude adjustment target quaternion q2: 0, attitude adjustment target quaternion q3: 0, attitude adjustment target quaternion q4: 1).

[0046] The parameter selection for this type of satellite is as follows: t gk : 20 s; T1: 60 s; δ gk : 10°; ω gk : 0.3° / s.

[0047] The satellite switched from the attitude control working mode from the standby mode to the orbit control and attitude adjustment mode at 15:19:40 on December 19, 2021. The attitude determination mode was dual-star sensor attitude determination, and the control mode was wheel control PID1 + magnetic non-control. At 15:21, the deviation attitude angle was [6.12° 7.27° 39.34°]. The working mode switched from the orbit control and attitude adjustment mode to the standby mode. The reason for exiting the orbit control was: attitude adjustment was not in place.

[0048] Example 4

[0049] A certain type of satellite was used to test this method: In the standby mode, an orbit control data packet was sent (parameters: jet start time: 16:36:38 on December 20, 2021, attitude adjustment duration: 600 s, jet duration: 81 s, orbit control mode: ascending orbit control, attitude adjustment target quaternion q1: 0, attitude adjustment target quaternion q2: 0, attitude adjustment target quaternion q3: 0, attitude adjustment target quaternion q4: 1).

[0050] The parameter selection for this type of satellite is as follows: t gk : 20 s; T1: 60 s; δ gk : 10°; ω gk : 0.3° / s.

[0051] The satellite switched from the attitude control standby mode to the orbit control attitude adjustment mode at 16:26:38 on December 20, 2021. The attitude determination mode is dual-star sensor attitude determination, and the control mode is wheel control PID1 + magnetic non-control. At 16:36:38, the attitude control working mode switched from the orbit control attitude adjustment mode to the orbit control jet mode. Subsequently, through setting, the output torques of reaction wheel 1 and reaction wheel 2 were set to a fixed value of 0.05 Nm, and the inertial system angular velocity was [0.12° / s, 0.11° / s, 0.35° / s]. At 16:36:58, the attitude control working mode switched from the orbit control jet mode to the standby mode. The reason for exiting the orbit control was that the angular velocity exceeded the tolerance during jetting.

[0052] In summary, in the embodiment of this patent, the chemical propulsion orbit control is divided into two working modes: the orbit control attitude adjustment mode and the orbit control jet mode, which is convenient for clearly tracking the orbit control stage. The reason for exiting the orbit control is output, and there is no need to trace historical data. It can clearly manage the working mode of chemical propulsion orbit control and improve the orbit control reliability of the satellite.

[0053] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. A management method for the working mode of chemical propulsion orbit control, characterized in that: The specific steps are as follows: Step 1: Enter the attitude control and adjustment mode according to the trajectory control data packet at the attitude adjustment start time; Step 2: After entering the attitude control and adjustment mode, judge whether the attitude adjustment process is normal. If it is normal, continue the attitude adjustment process until the jet start time; if it is abnormal, exit the trajectory control and output the reason for exiting the trajectory control; Abnormal judgment condition 1 in step 2: In the orbit control attitude adjustment mode, continuously judge that the inertial system attitude determination mode is invalid within the time t gk and set the reason for exiting the orbit control as: attitude determination is invalid; Abnormal judgment condition 2 in step 2: According to the orbit control data packet, continuously judge the time t within T1 before entering the orbit control jet mode, and if the attitude of any axis exceeds the threshold δ with respect to the target attitude gk , set the reason for exiting orbit control as: attitude adjustment not in place; gk ​ In Step 2, the relationship between the first abnormal judgment condition and the second abnormal judgment condition is OR; Step 3: Enter the trajectory control jet mode according to the trajectory control data packet at the jet start time; Step 4: After entering the trajectory control jet mode, judge whether the jet process is normal. If it is normal, continue the jet process until the jet end time, end the trajectory control, and output the reason for exiting the trajectory control as: normal end; if it is abnormal, exit the trajectory control and output the reason for exiting the trajectory control.

2. The management method for a working mode of chemical propulsion orbit control according to claim 1, wherein: Step 4, abnormal judgment condition 1: In the orbit control jet mode, during the continuous judgment time t gk the inertial system attitude determination mode is invalid, and the reason for exiting the orbit control is set as: attitude determination is invalid; Judgment condition 2 for step 4 anomaly: In the orbit control jet mode, continuously judge the time t gk Within, the attitude of any axis exceeds the threshold δ from the target attitude gk , set the reason for exiting the orbit control as: angle out of tolerance during jetting; The third abnormal judgment condition for Step 4: In the orbit control jet mode, continuously judge the time t gk Within, the angular velocity of any axis orbit system exceeds the threshold ω gk Set the reason for exiting the orbit control as: the angular velocity exceeds the tolerance during jetting; In Step 4, the relationship between the first abnormal judgment condition, the second abnormal judgment condition, and the third abnormal judgment condition is OR.

3. The management method for a working mode of chemical propulsion orbit control according to claim 2, characterized in that: t gk is 10 - 30 s; T1 is 10 - 60 s, and T1 is greater than t gk ; δ gk is 5° - 15°; ω gk is 0.1° / s - 0.5° / s.

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