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The star tracker is a high-accuracy attitude measurement device widely used in spacecraft. Its performance depends largely on the precision of the optical system parameters. Therefore, the analysis of the optical system parameter errors and a precise calibration model are crucial to the accuracy of the star tracker. Research in this field is relatively lacking a systematic and universal analysis up to now. This paper proposes in detail an approach for the synthetic error analysis of the star tracker, without the complicated theoretical derivation. This approach can determine the error propagation relationship of the star tracker, and can build intuitively and systematically an error model. The analysis results can be used as a foundation and a guide for the optical design, calibration, and compensation of the star tracker. A calibration experiment is designed and conducted. Excellent calibration results are achieved based on the calibration model. To summarize, the error analysis approach and the calibration method are proved to be adequate and precise, and could provide an important guarantee for the design, manufacture, and measurement of high-accuracy star trackers.
With the development of Earth-observing satellites and deep-space exploration satellites, requirements for attitude measurement accuracy are increasing. Thus, error analysis of the accuracy and calibration of the star tracker have become particularly important.
At present, research and analysis of the effect factors on the star tracker accuracy are being conducted. References  and  provides a general overview of the effects of the optical parameters. References  and  use a geometric method to establish a complicated error model, and obtain variations in accuracy for a certain range of optical parameters, but most of the existing analysis methods discuss the effects of factors separately and qualitatively. Up to now systemic error analysis and accurate error propagation model are inadequate.
Factors such as misalignment, aberration, instrument aging and temperature effects  could cause a departure of the star trackers from the ideal pinhole image model, and contribute to the attitude measurement error. Misalignment and aberration are time-independent, or static errors, which need to be calibrated prior to launch, and can be called ground-based calibration. By contrast, instrument aging and temperature effects are time-varying, or dynamic errors, which must be calibrated in real time, and can be called on-orbit calibration. This paper focuses only on the ground-based calibration method.
The ground-based calibration of star trackers generally includes real night sky observation and laboratory calibration. Real night sky observation can take advantage of the characteristics of the star tracker utilizing the star angular distance. This method is relatively easy to apply, whereas the model parameters interact with one another. Obtaining the global maximum is difficult, and this method is greatly influenced by the environment. Laboratory calibration could use a star simulator as the source. However, it is not easy to manufacture a high-accuracy star simulator.
Camera calibration techniques [6–10] can be choices for calibrating the star tracker considering that they are both optical imaging devices. However, there are problems for the star tracker to apply the calibration methods of the camera. First, most of these methods need to establish a complicated calibration model with scores of parameters. Good calibration results depend largely on the initial values and large amounts of calculation are needed for the optimization. Observability and convergence can be problematic. Second, the star tracker focuses more on the accuracy of the position of the image point, while the camera focuses more on the MTF or other image quality. Since the noteworthy parameters of the calibration methods of the camera and the star tracker are not exactly the same, the accuracy of general camera calibration techniques is not enough for the calibration requirement of the star tracker, which is one of the highest precision attitude measurement devices on the satellite. Moreover, majority of the camera calibration techniques have not considered the inclination of the image plane.
Last but not the least, the optical imaging principle and focus matters of the star tracker and the camera are not the same due to their functions. The camera uses a finite distance imaging mode, while the star tracker adopts an infinite distance imaging mode. General camera calibration methods are not suitable for the star tracker. Taking reference  as an example, the cubic 3-D calibration object applies to camera calibration as the camera can take a clear photograph of a finite distance object, but the star tracker is used to take pictures of infinite distance stars, so it cannot take a clear photograph of the 3-D calibration object. Even though there are a few reports about how to add another high accuracy lens to make this finite imaging calibration method apply to the star tracker, the accuracy and the position of the added lens, the accuracy of the 3-D cubic object all need to be discussed. These bring new troubles and are not easy to carry out.
Therefore, the calibration method provided in literature  or other similar camera calibration methods work better on short focal length, small view field camera. Convenient calibration methods for large FOV and high accuracy star tracker are still problems needed to be figure out. The calibration method using composite mode of high accuracy autocollimator theodolite and the features of the star tracker proposed in the manuscript is a good choice for this topic.
To summarize, the literature on the analysis and evaluation of the error sources of star trackers has not been adequate until now. This paper proposes a systematic method for weight analysis of the error source. Optical parameters that play key roles in the accuracy of the star tracker (such as the principal point deviation, focal length error, imaging plane inclination error and distortion) [1,12] are analyzed by the proposed method. From the analysis results, a calibration method is put forward. The calibration can separate the radial distortion from the image plane inclination, thus the optimization processes are simplified. The calibration result proves that the analysis of the optical systematic error and the calibration method for the high-accuracy star trackers proposed in this paper are reasonable and adequate, and can improve the accuracy of the star tracker.
The star tracker is a high-accuracy attitude measurement device, which considers the stars as the measuring object. It obtains the direction vector from the celestial inertial coordinate system by detecting the different locations of the stars on the celestial sphere. After many years of astronomical observations, star positions on the celestial sphere are predictable. Stars in the celestial sphere coordinate system can be expressed in the right ascension and declination (α,δ). Based on the relationship between the rectangular coordinate system and the spherical coordinate system, the direction vector of the stars in the rectangular coordinate system is expressed as follows:
Navigation stars are selected from the star catalog to meet the imaging requirement, and their data are stored in the memory of the star tracker.
When a star tracker with attitude matrix A is in the celestial coordinate system, the ideal measurement model of the star tracker can be considered as a pinhole imaging system. Navigation star Si with direction vector vi under the celestial coordinate system can be detected through the lens, whereas the vector of its image can be expressed as wi in the star tracker coordinate system, as shown in Figure 1.
The position of the principal point of the star tracker on the image plane is (x0, y0). The position of the image point of navigation star si on the image plane is (xi, yi). The focal length of the star tracker is f. Vector wi can be expressed as follows :
The relationship between wi and vi under the ideal condition can be expressed as follows, where A is the attitude matrix of the star tracker:
When the number of navigation stars is more than two, the attitude matrix can be solved by the QUEST algorithm . In this method, the optimal attitude matrix Aq in the inertial space of the star tracker can be calculated.
The existence of errors and noise in the system are inevitable. According to the pinhole model shown in Figure 1 and Equation (2), the factors that directly affect the results of the attitude measurement of the star tracker include the extraction error of star point position, principal point error, error of focal length, direction vectors of the navigation stars, and attitude solution algorithm error. The accuracy is also related to the number of stars in the field of view (FOV). Further, the effect factors of the star tracker are classified as follows [1–5]:
Star vector measurement error concerns the accuracy of vector wi in Equation (3). Star vector measurement error includes:
Star catalog errors concern the accuracy of vector vi in Equation (3). The number of stars is very large; hence, we must select the appropriate ones for storage in the memory and meet the performance requirements of the star tracker. The different stars selected may influence the star numbers that appear in the FOV. The star catalog set-up time could also contribute small errors in the direction vectors of the stars in the celestial coordinate system. But the influence can be ignored if the star catalog can be corrected every once in a while considering proper motion of stars.
Star tracker internal algorithm error concerns the accuracy of the final attitude matrix A of the star tracker. However, algorithm errors such as star pattern recognition methods and attitude solution algorithm are irrelevant to this work. Among the errors enumerated above, those described in Section 3.1.1 exert a relatively larger effect. The error analysis in this paper focuses mainly on this error source.
In the following analysis, we use the angle measurement error (ξA) to represent the star tracker accuracy. According to the pinhole image model, ξA is expressed as follows: the change in the angle between the incident ray and the optical axis in the FOV is called the angle of real light change (ξAR), and the light calculated from the star position and focal length is called the calculated light. The change in the angle between the calculated light and the optical axis is called the angle of calculated light change (ξAC). The deviation in the ξAR and ξAC is called the ξA. The ξA represents the star tracker attitude measurement accuracy. The optical parameter errors such as the principal point error, error of focal length, inclination of the image plane and distortion influence the ξA and cause a difference betwe en the ξAR and ξAC. Therefore, analysis of the effect of the different optical parameter errors on ξA could identify the key factors that must be calibrated, which is important in improving the star tracker accuracy and can provide optimization guidelines for the star tracker design.
Figure 2 shows the sketch of complete error propagation. βri is defined as the angle between the incident ray and the optical axis. The initial value of βri is βr0, βr0 =0°. The maximum value of βri is equal to the angle of the FOV. Δβri is the ξAR, and Δβri = βri − βr0. βci is the angle between the calculated light and the optical axis. Δβci is the ξAC, and Δβci = βci − βc0. We made the following assumptions: axis e1 is along the direction of the maximum error of the principal point, and the inclination angle of the image plane in this direction is also the maximum of all directions. This can represent the worst case of error conditions. Axis e3 is the ideal optical axis of the system, and e′3 represents the actual optical axis. Δs represents the deviation of the optical axis. Δf is the deviation of the focal length. Δx represents the star point-extraction error and Δd is the distortion value. The distortion discussed in this paper concerns radial distortion only.
Angle βci is obtained as:
The ξA is calculated based on the above analysis:
When the actual optical axis is along the positive direction of the ideal optical axis, Δs is defined as positive. When the inclination angle θ is in the clockwise direction, it is defined as positive. Another ξA form is expressed as follows:
We define ξP as the position measurement error of the incident light ray. ξA and ξP describe the measurement error in different views, however, they can be transformed from one form to the other. ξA is more concerned with the accuracy of the star tracker, whereas ξP is more suitable for using in the calibration.
We adopt two methods to discuss the error effects. First, we use the Monte Carlo (MC) stochastic modeling method. In this method, it is assumed that the errors after calibration, such as noise, inclination angle, focal length and principal point errors are random errors. These errors are considered to coincide with the normal distribution. In addition, the number of stars that can be captured in the sky is more than 6,000. Therefore, it is reasonable to consider the incident angle in the FOV as uniformly distributed. Based on the two statistical assumptions, we can combine the geometry and MC random models, and develop the complete error effect analysis. Second, we use the maximum error method to prove the simulation result of the MC method. This method can easily identify the error distribution of the different incident angles. Analysis of the position of the maximum error can also provide information for further study. The object analyzed in this paper is a star tracker of 7″ accuracy and the FOV is 17°. The focal length of the system is approximately 49.74 mm. The star tracker adopts the APS CMOS image sensor with 1,024 × 1,024 pixels, and the size of each pixel is 0.015 mm.
The MC method  used the statistical rule of random numbers for the calculation and simulation. The following subjects analyze the single factor and the combination of factors using the MC method. Using a 1,000,000 times simulation, the statistical results are obtained. The simulation is conducted with an 8.5° incident angle.
Then, combination error analysis using the MC stochastic simulation is conducted. The ξA satisfies the distribution rule: μ = −0.0225, σ = 4.4218″. The accuracy is in the range of μ−3σ~μ+3σ = −13.2881~13.2430″. Considering that at least 4 stars can be captured in the normal working state, the simulation boresight accuracy can be calculated as: . Thus, the allocation of permissible errors of the star tracker with a 7″ accuracy is obtained.
Table 1 and Figure 3 show that, for the analyzed system, error of star point extraction, error of principal point, error of focal length, error of inclination of the image plane and distortion are respectively distributed in the range of 0.1 pixels, 4.5 pixels, 0.6 pixels, 0.075° and twenty thousandth, they bring the ξA to the same level. Considering their combined effects can ensure the accuracy of the star tracker.
We conduct a simulation using Maximum Error Method to compare with the method in Section 3.3.1 based on the error propagation model in Section 3.2 and the system parameters of the star tracker, as well as the range of the star point extraction error, the principal point error, focal length error, inclination of the image plane and distortion. The incident angle βri is in the range of 0–8.5° and the focal length is approximately 49.74 mm. Under the simulation conditions, the effect of the error of star point extraction on the star tracker accuracy, along with the incident angle is shown in Figure 4.
Under the simulation conditions, the effect of the error of the principal point on the star tracker accuracy, along with the incident angle is shown in Figure 5.
Under the simulation conditions, the effect of the error of focal length on the star tracker accuracy, along with the incident angle is shown in Figure 6.
Under the simulation conditions, the effect of the error of inclination image plane on the star tracker accuracy, along with the incident angle is shown in Figure 7.
Under the simulation conditions, the effect of the error due to distortion on the star tracker accuracy, along with the incident angle is shown in Figure 8.
The simulation results show that the error effects obtained by the maximum error method agree with the results obtained by the MC simulation method. We can also find that inclination of the image plane and the distortion are two key factors that need to be calibrated. The calibration method will be elaborated in the next section.
Optical systematic error analysis method proposed in this paper can perform analysis on the sensitivity of factors (such as the error of star position extraction error, position error of principal point, error of focal length, inclination of the image plane and the distortion) that may influence the accuracy of the star tracker.
The above analysis of the system error can be applied in the following areas: (1) reference for the calibration target, i.e., if the five indicators are simultaneously satisfied, the calibration results could meet the requirements; (2) analysis for the highest accuracy of the system; and (3) determining the major factors that emphasized the calibration experiment.
For application (1) above, because of the limitations in the calibration method, the effect factors cannot be separated from one another. Thus, determining whether the five indicators are all satisfied is difficult. Therefore, the proposed method is used primarily in the determination and demonstration of the design indicators. For application (3), some of the restrictions in certain error range can easily meet, such as the principal point position error, whereas satisfying the others are more difficult. These error factors need to be calibrated elaborately, such as the inclination angle of the image plane and the distortion. Therefore, emphasis on the calibration method is related to the system parameters. The calibration method and the processes are designed according to the characteristics of the system, so that the ξA or ξP of the star tracker is within the design range.
The calibration object of this paper is a star tracker with 7″ accuracy. Based on the result of the above analysis, optical parameters of the system are calibrated. The laboratory calibration of the star tracker can be performed using a three-axis turntable and a collimator or an autocollimator theodolite. In essence, their operating principle is the same. However, because the collimator does not have a self-collimation function, which could introduce trouble to the calibration of the principal point, we adopt the autocollimator theodolite.
The autocollimator theodolite we employ in the experiment is the Leica 6100A. Figure 9(a) shows its external view. It has a small size, high accuracy 0.5″ and simple operation. We can use its auto-collimation eyepiece to determine whether the crosslines coincide, as shown in Figure 9(b). Other experiment devices consist of the optical table and auxiliary fixtures. It is worth noting that the aperture of the autocollimator should be comparable or larger than the aperture of the star tracker in order to avoid vignetting.
According to the analysis in Section 3, the calibration objective should be focused on the inclination of the image plane and the distortion. The basic block diagram of the calibration process is shown in Figure 10.
For better representation of the location and the relationship, we create the coordinate systems as in Figure 11. Axes XC YC in coordinate system CSC represent the movement directions of the outgoing light rays of the theodolite in the two orthogonal axes, respectively. ZC, XC and YC comply with the right-hand rule. Coordinate system CSN represents the normalized coordinate of the focal plane. The positive directions of XC YC are consistent with the directions of the increase in the image pixel value. The coordinate origin is the same as the optical system principal point. The distance between CSN and the pinhole is normalized to one. Coordinate system CSOXY has the same direction as that of CSN, and the only difference is that the distance between CSOXY and the pinhole is equal to the focal length f. CSOUV represents the actual coordinate system of the image plane. The positive directions of u, v are consistent with the directions of the increase in the image pixel value. The coordinate origin is at the zero pixel of the image plane, and the optical system principal point can be expressed as (u0, v0). The distance between CSOUV and the pinhole is f. The axes of CSO′U′V′ and CSOUV have the same direction, with the coordinate origin O′ is the same as the principal point. Ideally, CSO′U′V′ coincides with CSOXY. Angle α is the longitude value of the outgoing light ray of theodolite in coordinate system CSC, whereas δ is the latitude value. Angle is the angle between the axis XC and axis XN. Thus, the coordinates of the ideal pinhole imaging model are established as shown in Figure 11. The relationship of the parameters are presented in Equations (9)–(11).
Angle α is positive along the positive direction of XC, whereas it is negative along the negative direction of XC. Angle δ is positive along the positive direction of YC, whereas it is negative along the negative direction of YC. When the angle from XN to XC is counterclockwise, angle is considered as positive. The ideal pinhole imaging model cannot be achieved in practical application. There are position errors of principal point, focal length error, inclination of image plane and distortion to cause the CSO′U′V′ departure from CSOXY as shown in Figure 12, and the equations above are invalid. It is necessary to estimate the parameters by calibration.
First, we adjust the theodolite to ensure that its outgoing light travels only along the longitude direction. The latitude value does not change during this process. Imaging conducted at every 0.5° can yield a series of measured values that determines the external parameters.
Then, according to the 17° FOV of the star tracker, we adjust the theodolite so that its light travels along the two orthogonal directions as shown in Figure 13 while conducting imaging at every 0.5°. If any of the two directions satisfies the requirement of the first step, two steps can be combined to determine the internal parameter of the star tracker. Because the outgoing rays of the theodolite are crosslines, the images on the image plane appear similar to that shown in Figure 13(b). It is worth mentioning that the star tracker is supposed to be settled on the same optical table with the auto-collimation theodolite to avoid relative vibration. Considering that our experiment is conducted at the State Key Laboratory of Precision Measurement Technology and Instruments, the floor of the laboratory has been treated with vibration isolation. So the relative vibration could be reduced and ignored in the calibration form in Figure 13(a), and it is easier to adjust the relative position of the theodolite and the star tracker with the tripod.
The image obtained by the star tracker is shown in Figure 14. An appropriate image processing method should be adopted to obtain the precise center position of the crossline which represents the outgoing ray of the theodolite. For the pixels in the first area, we regard the pixels in the same row as a group, and determine their gray value center of gravity (i.e., weighted average). For the pixels in the second area, we consider pixels in the same column as a group, and also determine their gray value center. The centers of gravity are marked with a circle as shown in Figure 15. Finally, we use the least square method to fit the two straight lines. The point of intersection of the two lines is considered as the center of the crossline. This work provides a basis for further algorithm. Since the light intensity of the theodolite could be adjusted by a knob, obtaining image before experiment and observing whether the image is saturation is also important.
The series of point coordinate values obtained in Section 4.2.2 can be used to solve angle between the XC-axis of coordinate system CSC and the XN-axis of CSN. Symbol n represents the number of sampling points:
Linear fitting can also be adopted to solve the value of besides Equation (12).
The positions of the series of specific points are obtained according to the above discussion and preparation. The characteristics of these points include the following: the test points are distributed in two orthogonal directions and the test points in the same direction are almost centrosymmetrical. Taking advantage of relationship between the symmetric points, we build a calibration model, shown in Figure 16. In the actual calibration process, we try to make one of α, δ equal to zero for simplicity of the calculation. In reality, no restriction is imposed on the theodolite longitude and latitude angle, and the two orthogonal directions formed by the test points do not necessarily coincide with any of the defined coordinates. For the general situation, we name the two orthogonal directions distributed with the test points as L1 and L2. βi is the synthesis angle of the theodolite longitude and latitude. When there are distortion and inclination of the image plane in the system, the imaging model is shown in Figure 16. βi+ and βi− respectively represent the incident angles of the two centrosymmetric points in the same test direction. PIi+ and PIi− are the ideal image point positions corresponding to the incident light rays when no distortion and inclination of image plane occurs. PDi+ and PDi− are the positions of the image points when distortion is present but with no inclination of the image plane. PTi+ and PTi− are the positions of the image points with the presence of image plane inclination but with no distortion. PRi+ and PRi− are the positions of the image points when both distortion and inclination of the image plane are present.
The longitude and latitude values (αi, δi) corresponding to the incident rays and the coordinate positions (uRi, vRi) on the image plane can be used to solve the principal point position (u0, v0), focal length f, distortion coefficients α1, α2, α3, α4, α5 and the inclination angle corresponding to the test direction. Finally, the calibration model for the entire image plane is obtained. This method is elaborated as follows:
Equation (18) is suitable for the symmetric points. When |OPRi| + Δi > |OPIi|, θi is defined positive; when |OPRi| + Δi < |OPIi|, θi is defined negative.
So far, the principal point, the focal length, the radial distortion coefficients and the inclination angle of image plane in one direction are obtained. The principal point, focal length, and radial distortion coefficients are suitable for the entire plane. Inclination angle in the other measurement direction can be obtained in the same manner.
The inclination angle in the two measurement directions is not sufficient. The ultimate goal of calibration experiment is to obtain an ideal image position of incident rays from any direction in the FOV. Based on the parameters obtained above, there are many methods to solve this problem. We adopt a coordinate transformation method, and establish a coordinate transformation framework for incident rays. Therefore, we make the following analysis.
We can obtain the position of point PIi+ as (xIi+, yIi+, 0) in the coordinate system CSOXY by considering the longitude and latitude of the incident ray, external parameter , focal length f and Equations (9)–(11). Then, the straight line OCPIi+ can be expressed as:
Considering the angle PIi+OPTi+ = |θi| and the positive or negative of the angle value, the position of point PTi+ in coordinate system CSOXY can be solved though the following equations:
Thus, the position of point PTi+ is obtained (xTi+, yTi+, kTi+). The position of point PTi− can also be obtained in the same way. So far, the positions of the multiple sets of points as PTi+ and PTi− in both the two measurement direction in CSOXY can be obtained. Therefore, the plane equation of actual image plane with inclination O′U′V′ in coordinate system CSOXY can be expressed as p(O′U′V′).
The transformation matrix from coordinate system CSOXY to coordinate system CSO′U′V′ can be obtained at the same time:
R1 and R2 are the coordinate system transformation matrices.
Thus, the whole parameter estimation model of the optical system of the star tracker is completed.
For any point on the image plane of the incident ray, we can determine its position in CSO′U′V′ as (uRi+−u0, vRi+−v0, 0). The position of point PTi+ can be calculated by considering the distortion as (uTi+−u0, vTi+−v0, 0). According to the coordinate system transformation matrix, the position of point PTi+ in CSOXY can be calculated as:
The equation for straight line OCPTi+ can be obtained. Further, by solving the position of the point of intersection of straight line OCPTi+ and plane OXY, the point of intersection GIi+ is the ideal position of point PRi+. Thus, the ideal image position of the incident ray can be obtained. This solution is particularly important for the star pattern recognition and attitude solution of the star tracker.
In the calibration process described in Section 22.214.171.124, the principal point position is obtained and considered as its true position. In reality however, due to lens installation, accuracy in manufacture as well as the limitations in the eyepiece alignment when using the theodolite, a deviation error of the optical axis is inevitable. That is to say, there may be an error β0 between the optical axis obtained in Section 126.96.36.199 and the true optical axis of the lens. Maximum value of β0 is approximately 40″ in this calibration system, consisting of 30″ installation error of the lens and 10″ eyepiece alignment error. In this situation, the optical axis error will cause the deviation error of principal point, the focal length and inclination angle. The specific effect analysis is described as follows:
As shown in Figure 20(b), assuming the deviation error of the optical axis is 40″ as analyzed above, the position error of principal point is about f·tan(40″) (equal to 0.64 pixels); the error of inclination angle is approximately 0.01°. The errors due to the focal length and the distortion are merged and the residual error of the distortion after calibration is within 0.1 pixels. Because the light ray is brighter than a real star in practical use, the signal to noise ratio is higher and the extraction error of the light ray position can reach approximately 0.05 pixels. We can use the MC error analysis method described in Section 3.3.1 to determine the ξA and ξP.
The ξA meets distribution rule: μ = 0.0034, σ = 2.1192″. The ξP meets distribution rule: μ= 0.0007, σ = 0.0338 pixels. We adopt ξP as the basis of the calibration target. That means the calibration residual error should in the range of μ+3σ distribution of ξP.
The calibration experiment is conducted in the laboratory. From the above analysis, we can know the longitude angle αi and latitude angle δi of the incident ray of the theodolite. We also can obtain the position of point as PRi+ or PRi− by the image processing mentioned in Section 4.2.3. Then we do the same procedure as Section 188.8.131.52, and calculate the position of point GIi+. The position of point PIi+ can be also obtained through Equations (9)–(11). Comparing the two positions, the calibration model is proved to be effective and adequate if the error between the two positions is less than the ξP for points on the image plane at any incident light angle. In the experiment, we conduct two orthogonal direction measurements to get the parameters and the calibration model. Then we conducted measurements in another two independent and orthogonal directions that have an angle of 45° or 135° with the 1st measurement direction L1 to prove the analysis and calibration model in this paper.
Calibration result is summarized in Table 3:
After calibration, we can obtain the calibrated image point position of the incident light in different directions. The estimations of f can be conducted again to show the effect of the calibration (Figure 24) compared to the initial values in Figure 22. We can see from Figure 24 that the values of focal length do not change with the incident angles any more. They are in a range of 1 pixels (standard deviation ≈0.23 pixels). This can also demonstrate that the residual errors are improved after calibration. The position error between points GIi+ and PIi+ is shown in Figure 25.
We can see from Figure 25 that the position errors in the entire FOV are within the ξP and in accordance with analysis in Section 4.3.1. The results demonstrate that the point position errors can be kept within the ξP after calibration. Based on MC analysis, the accuracy of this calibration method can reach 7″, which related to the focal length and the FOV of the system. The accuracy of the star tracker is supposed to be better than 4.5″ after calibration, compared with the worse accuracy of more than 10″ if no calibration is conducted.
A synthetic error analysis approach for the star tracker has been proposed in detail in this paper. This approach can provide the error propagation relationship of the star tracker. Based on the analysis results, a calibration experiment is designed and conducted. Excellent calibration results are achieved. The calibration experiment can not only guarantee the accuracy to meet the design requirement, but can even improve the accuracy of the star tracker to a higher level. To summarize, the error analysis approach and the calibration method are proved to be adequate and precise, and are very important for the design, manufacture, and measurement of high-accuracy star trackers.
This work is partially supported by a grant from the National High Technology Research and Development Program of China (863 Program) (No. 2012AA121503). The laboratory calibration is performed in the State Key Laboratory of Precision Measurement Technology and Instruments at Tsinghua University. Both of them are gratefully acknowledged.