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Star point tracking method for multi-probe star sensor

A sensor and probe star technology, applied in the field of satellite control, can solve the problems of long initial capture time, large maneuvering angular velocity, inconsistent three-axis attitude measurement accuracy, etc.

Active Publication Date: 2019-12-10
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Due to the limitations of the working mechanism and structure, the use of a single star sensor on the star has the following two problems: one is that the accuracy of its three-axis attitude measurement is inconsistent; the other is that it cannot continuously output the attitude due to the interference of ambient stray light
[0009] (1) When the in-orbit product is turned on, it is affected by stray light or dynamic interference, and its initial capture time is relatively long, that is, it takes a few seconds for the product to enter the tracking mode after it is turned on;
[0010] (2) The product in orbit is affected by the installation location and satellite orbit, and it is generally affected by stray light such as the sun and the earth's atmosphere. When the sun or the earth's atmosphere is greatly affected and the image plane is not saturated, the product has a fade-out mode; After the light interference source weakens, the product needs to be recaptured successfully before returning to the normal tracking mode, which will have a certain impact on the use of the system;
[0011] (3) Most of the satellites in orbit have fast maneuvering and high maneuvering angular velocity. During the rapid maneuvering process of the satellite, the product exits the mode and needs to be re-captured after the satellite maneuver is completed to return to the normal tracking mode. The proposed dynamic and rapid response requirements

Method used

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specific Embodiment approach

[0038] like figure 1 and figure 2 Shown, the specific implementation of a kind of multi-probe star sensor star point tracking method that the present invention proposes is as follows:

[0039] (1) The relative installation array between multiple probes of the product can be obtained according to the ground-wide satellite precise measurement data, and the installation array Aij_t0 is stored as the product binding parameter;

[0040] (2) Judge the working mode of each probe of the product every cycle, whether the probe i (i=1, 2, 3, assuming that there are 3 probes in the product) is working in the tracking mode at the current moment, if so, turn to the tracking mode, otherwise , execute the next step sequentially;

[0041] (3) Determine the working mode of the probe j (j=1,2,3, and j≠i), if working in the tracking mode, then execute the next step in sequence, otherwise, if j<3, then j=j+1 , execute step (3) again; if j=3, then set the working mode of probe j as the initial ...

Embodiment 1

[0051] Example 1 (a probe of the multi-probe star sensor does not enter the tracking mode)

[0052] A kind of star point tracking method that is used for multi-probe star sensor, the step of this method comprises:

[0053] (1) The relative installation arrays of the three probes of the product can be obtained according to the ground-wide satellite precise measurement data, that is, the relative installation array A12_t0 between probe 1 and probe 2, the relative installation array A13_t0 between probe 1 and probe 3, and the relative installation array between probe 2 and probe 3 Array A23_t0, store A12_t0, A13_t0 and A23_t0 as product binding parameters;

[0054] (2) Judge the working mode of each probe of the product every cycle, whether the probe i (i=1, 2, 3, 3 probes in the product) is working in the tracking mode at the current moment, and the probe 2 has not entered the tracking mode, then execute the following one step;

[0055] (3) Determine the working mode of the pr...

Embodiment 2

[0060] Embodiment 2 (a certain probe does not output a valid attitude when the multi-probe star sensor is working normally)

[0061] A kind of star point tracking method that is used for multi-probe star sensor, the step of this method comprises:

[0062] (1) Judging the working status of all probes in tracking mode, if the current frame attitude calculation of probe 3 (i=1, 2, 3) fails, then perform step (2);

[0063] (2) Determine the working mode of the probe 1, if the probe 1 works in the tracking mode and the attitude calculation of the current frame of the probe 1 is valid, then execute the next step in sequence;

[0064] (10) Using the current frame attitude A1 of probe 1, combined with the array A13_t0 installed between probe 1 and probe 3, calculate the current frame attitude A3 of probe 3 (A3=A13_t0 T *A1);

[0065] (11) Use the attitude A3 of the probe 3 to predict the position of the star point in the field of view of the probe 3 at the current moment;

[0066] ...

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Abstract

The invention relates to a star point tracking method for a multi-probe star sensor, and belongs to the technical field of satellite control. By means of a plurality of the probes in the star sensor,an auxiliary tracking function and a continuous tracking function of the product are designed; and when a certain probe of the product is subjected to stray light on orbit or cannot output effective attitude data dynamically, the probe can be ensured to be in a tracking mode continuously and output the effective attitude data quickly.

Description

technical field [0001] The invention relates to a star point tracking method for a multi-probe star sensor, belonging to the technical field of satellite control. Background technique [0002] The star sensor is currently the attitude measurement optical sensor with the highest measurement accuracy on the satellite. It does not need a priori attitude and angular velocity information to capture and determine the attitude of the whole sky autonomously. With the advantages of high precision, no drift and high reliability, it is a key component of satellite attitude measurement. [0003] In recent years, with the continuous expansion of satellite application fields, the requirements for satellite control accuracy are getting higher and higher, and higher requirements are also put forward for attitude measurement accuracy and dynamic performance. Missions such as stereoscopic mapping satellites and high-resolution earth observation satellites have urgent requirements for attitud...

Claims

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Application Information

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IPC IPC(8): G01C21/02
CPCG01C21/025
Inventor 郑然程会艳关健张腾飞武延鹏隋杰李玉明杜建伟顾斌蒋志雄
Owner BEIJING INST OF CONTROL ENG