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Optical system design of star sensor and stray light analysis

  • Mohammad Asadnezhad1,
  • Abdollah Eslamimajd1Email author and
  • Hassan Hajghassem2
Journal of the European Optical Society-Rapid Publications201814:9

Received: 12 December 2017

Accepted: 4 March 2018

Published: 16 March 2018



Star sensor is one of the precise attitude determination sensors. It is an electro-optical system that takes an image from a set of stars and by comparing it with the star catalogue determines angle deviation of the satellite and modifies its attitude. Star sensor is composed of baffle, optical system, detector, and electronic and image processing system.


In this article, first subsystems of a star sensor is briefly described, then by determining the optical parameters, an optical system with proper quality is designed, and the tolerances are considered.


The simulation results and the optical evaluation curves indicate that the image quality is close to the diffraction limit. Next, stray lights from off-axis sources like the sun, are analyzed. For this purpose, the main parameters of baffle designing such as its dimensions and arrangement of the vanes inside it, are determined and then a cylindrical baffle with internal vanes for the star sensor is designed.


Results show that stray lights reduced 10− 11 times with the presence of baffle and its vanes.


Star sensorAttitude determinationNavigationOptical systemStray lightBaffle


Navigation is one of the most important subjects in space missions divided into position determination and attitude determination. Determining the location and angular coordinates of spacecraft according to a fixed coordinate system is called position determination and attitude determination, respectively [1, 2]. In most cases, the inertial navigation system is used for spacecraft navigation. Inertial navigation system may have some errors in the long term due to natural factors such as gravity and magnetic effects or for reasons such as gyro axis deviation and accelerometers error. These effects are numerically low, but they would be effective with a high repetition in the long term. Therefore, this cumulative error sometimes must be corrected by an auxiliary navigation system [3].

As Fig. 1 shows, there are many ways to position and attitude determination of spacecraft [2]. Star sensor is an important and high precision attitude control system [49]. It is an electro-optical system taking a picture from a set of stars (as point sources at infinity [6, 7]) in celestial sphere and comparing it with the same star pattern from reference star catalogue to calculate the angular deviation of the satellite to a specific reference [911]. Finally, this information is sent to inertial guidance and control system to attitude correction of satellite [12, 13].
Fig. 1

The ways of attitude and position determination

In this article, an optical system for a star sensor is designed and then with stray light analysis, a suitable baffle is designed for it. Thus, this article is divided into three parts. In the first part, star sensor and its subsystems are discussed. In the second part, optical design, optimization, image quality and tolerancing are explained in detail. In the third part, by analyzing stray light, a suitable baffle is designed for it.

Star sensor

As it is mentioned above, star sensor is a photographic optical system combined with image processing program to calculate the angular deviation of satellite from stationary reference object. Star sensors are divided into two generations, and their characteristics are shown in Table 1.
Table 1

Characteristics of two generations of star sensors [10, 13]


1st generation

2nd generation

Field of View


not very wide


> 20 W

< 5 W


> 20 kg

< 4 kg


20 arc sec

1 arcsec

Minimum Stars Needed to Track

1 star

Minimum 3 stars

As can be found from Table 1, second generation star sensors have better advantages. Although the star identification algorithms with sub-pixel accuracy and lost-in-space algorithms are complicated, nowadays, the second generation star sensors are used for autonomous navigation in space missions [9].

Star sensor consists of four sections that are discussed as follows (Fig. 2) [5, 13, 14].
  1. 1.


  2. 2.

    Optical System

  3. 3.


  4. 4.

    Electronic and image processing system

Fig. 2

Subsystems of a Star Sensor


Since there are not any particles in space and the distance between molecules is very long, the intensity of bright sources such as the sun, is unscattered and high. Thus, due to high intensity sources in the field of view (FOV) of star sensor, the detector is saturated in a short time, and recognition of star from the bright background is virtually impossible [5]. Therefore, to identify low magnitude stars (until mv = 7) by the detector, the intensity of out of field stray light sources, especially the sun, must be attenuated. Baffle is an opto-mechanical device that prevents coming stray light out of field into the optical system of star sensor [1517].


New generation of star sensors are improved in terms of light weight, small size, low power consumption and intelligent systems [7, 8]. For this purpose, using active pixel sensor (APS) instead of charge coupled device (CCD) detectors is more useful. APS compared to CCD has more advantages such as higher dynamic range, lower power consumption, smaller size and higher radiation tolerance [9, 18]. Therefore, they become more interesting to be utilized in space explorations and many attitude sensors applications and space imaging navigation [1720]. Accordingly, APS detector that its spectral response is shown in Fig. 3, is used in this article. It is obvious from this figure that this detector has higher responses to the wavelength from 0.55 to 0.85 μm. The detector spectral response is desirable for different spectral classes of stars, and its maximum is approximately 0.6 μm. Table 2 shows the characteristics of the APS detector [21].
Fig. 3

Spectral response of selective APS detector [21]

Table 2

Characteristics of selective APS detector




1024 × 1024

Pixel Pitch


Spectral Range

0.4-1 μm

Quantum Efficiency


Dynamic Range


Optical system and image processing

As mentioned in section Star sensor, a star sensor consists of an optical system with a detector and an image processing program running in an on-board computer of microsatellite. The optical system takes images from stars as point sources in any region of celestial sphere in its FOV (Fig. 4) [8, 9]. Since stars are fixed in cosmos relative to inertial space [7], then they are the best candidates for attitude determination.
Fig. 4

Star sensor (principal planes H &H`) makes the image of a star location somewhere in celestial sphere

The taken image from the optical system is compared with a precise star catalogue saved in on-board computer of satellite. Then, the centroid position of each star in the FOV is calculated by centroid algorithm. Eq. (1) and (2) show the position of star in X and Y direction, respectively [11, 22].
$$ {X}_c=\frac{\sum {x}_i\Phi \left({x}_i,{y}_i\right)}{\sum \Phi \left({x}_i,{y}_i\right)} $$
$$ {Y}_c=\frac{\sum {y}_i\Phi \left({x}_i,{y}_i\right)}{\sum \Phi \left({x}_i,{y}_i\right)} $$

Where (x i , y i ) is the position of ith pixel and Ф is the intensity of imaged star on ith pixel. It is obvious from these equations that the star sensor optical system must be designed near diffraction limit. The position of star image on a pixel must be calculated less than one pixel surface accuracy to achieve arc second order accuracy. Thus, imaging a star on one pixel, as agreed criterion in normal optics, is not satisfactory. To achieve sub-pixel accuracy, the image of a star must be distributed on a set of pixels by defocussing in the first step [6, 9, 13]. Next, a program must be written to calculate the position of star on the detector pixels. For this purpose, the interpolation algorithms are generally used [9, 11, 22].

For precise attitude determination, the location of star in celestial sphere (Fig. 4) should be imaged on the detector without any position and angular deviation. For this purpose, aberrations affecting position of object like distortion and lateral color must be reduced or eliminated.


Optical design

Primary parameter of focal length, FOV, F# and spectral range are essential to design optical systems [23, 24]. The following relation can be made between detector dimensions, FOV, and focal length in the imaging system:
$$ \mathit{\tan}\frac{FOV_x}{2}=\frac{X}{2f}\kern1.75em ,\kern2.25em \mathit{\tan}\frac{FOV_y}{2}=\frac{Y}{2f} $$

Where FOV x and FOV y are the field of view of the system in horizontal and vertical direction according to the detector, respectively; X and Y are the width and length of the detector, respectively, and f is the focal length of the optical system.

As it is obvious in Eq. (3), there must be a tradeoff between focal length and FOV. Increasing each one will decrease the other.

The F# is one of the most important parameters of any optical system controlling the energy entering the detector through entrance aperture of the optical system. Since F# controls magnitude range of stars in the FOV, it plays an important role in star sensor. With a constant value of focal length, high amount of F# decreases aperture size, limiting the stellar magnitude. The low amount for F# increases the entrance aperture size, leading to catch low-bright stars but increases the weight and length of the optical system. In this situation, high order aberrations appear, resulting in a more complicated optical system [23, 24].

During the optical design process, our trend is to make an optical system with FOV as wide as possible because more stars in the FOV lead to easier achievement of star pattern and better attitude determination. However, as mentioned before, it decreases the focal length, which causes other problems. In such situations, the star catalogue and star identification algorithm become more important. The spectral range is determined by detector spectral range and spectral class of stars.

According to the conceptual design, the parameters in Table 3 are calculated for optical system.
Table 3

Principal parameters needed to design the optical system



Focal Length

60 mm



Minimum Stellar Magnitude


Field of View

14 degrees

Spectral Class


As mentioned in section Optical system and image processing, the optical system must satisfy the following cases:
  1. a)

    According to spectral response of detector and star spectral class, chromatic aberration must be corrected.

  2. b)

    Image magnification must be identical in full FOV.

  3. c)

    Optical system must be light weight and compact [8]. The numbers of optical components must be minimized to facilitate processing and assembly.


Stray light analysis and baffle design

During navigation by star sensor, the image quality may be unexpectedly reduced by stray light sources. Stray light is the unwanted light reaching the detector and reducing the image quality. These incoherent and discrete lights do not follow the normal optical path of the imaging system [2530]. Stray light in an optical system may lead to restrictions on detector dynamic range, artificial effects (ghost) in the image, and blurring as well as reducing image contrast, signal to noise ratio, resolution, and desirable FOV [2528].

Using baffle is one of the ways to control and reduce stray light. As mentioned in section Baffle, baffle is a highly important part of star sensor. It is an opto-mechanical device installed at the entrance aperture of the star sensor to protect the optical system against the external stray light sources such as sun, earth, moon and other celestial bodies [16, 17, 27, 31]. The satellite is also a source of stray light by reflecting the light from the intense sources. All these sources are able to saturate the detector and reduce the probability of finding low stellar magnitudes. To avoid this problem, in this work, a suitable baffle is designed for the designed optical system.

Result and discussion

Optimization of optical design

Considering the conditions in section Optical Design, three candidates for start point are found: the frontal aperture optical system, the telecentric [8] type of optical systems and very simple symmetric Double Gauss system. All these types can control the distortion easily. Optical design of Double Gauss system is easier relative to other types. In addition, its opto-mechanics is easier. Its tolerances are looser, and fabrication limits are less than them, especially relative to telecentric system. Therefore, Gaussian optical system as a start point was chosen in this work (Fig. 5).
Fig. 5

The Double Gauss system

As can be seen from Fig. 5 the second lens and the third lens, as well as the fourth lens and the fifth lens are laminated in the initial structure. It is necessary to separate the second lens from the third lens and the fourth lens from the fifth lens to prevent degumming in space environment. Thus, the structure of the optical system needs to be optimized. Furthermore, the small volume and mass of star sensor can be reached by minimizing the radial and axial dimensions of the lenses. By considering optical parameters in Table 3, Double Gauss system is designed and optimized by ZEMAX optical design software.

With considering the characteristics of the optical system and the requirements to determine centroid position in image processing, monochromatic aberrations should be controlled. It is obvious from the spherical aberration coefficient formulas that the higher the refractive index of lens material at the same focal power, the smaller the spherical aberration of the lens. Moreover, high refractive index optical glass has less requirement of the lens’ thickness. So, the structure of the optical system will be compact, and the miniaturization of the optical system is obtained. On the other hand, astigmatism and field curvature should be controlled to ensure that the star spot size is the same over the FOV. Since the aim of this work is to have a wide FOV, the distortion aberration is high and reducing it is too important. Distortion is the displacement of the image from the paraxial position and is different from other aberrations. So it causes displacement of the star image, especially at the end of the FOV, and changes the center of the star. Therefore the distortion in the star sensor should be controlled.

Double Gauss system is a symmetric, light weight and compact optical system. This system is able to reduce or eliminate symmetric aberrations such as spherical, astigmatism and distortion. Optimization process was performed for peak wavelengths of the selective APS detector (Fig. 3), being harmonized with the star spectral class. After optimization process, a quasi-symmetric optical system (Fig. 6) was designed.
Fig. 6

Optical system after optimization process

The designed optical system is composed of six lenses. The first, second, fifth and sixth lenses are positive lenses, and the third and fourth lenses are negative lenses. This structure has a small volume and can reduce stray light.

Optical evaluation curves show that the distortion (Fig. 7) and lateral color (Fig. 8) are enough low. Distortion is less than 0.03% at full FOV. The optimization program by destroying the symmetry of optical system decreased the field curvature and chromatic axial color aberrations. Accordingly, as Fig. 7 obviously shows, the field curvature is less than 0.05 mm that is satisfying.
Fig. 7

Field curvature and Distortion of optimized system

Fig. 8

Laterl color curve

Spot diagram (Fig. 9) shows that maximum root mean square (RMS) of spot radius for full FOV is less than 2 μm. As this figure shows, beams are gathering in a geometric diameter of 11–12 μm at full FOV.
Fig. 9

Spot diagram

The geometric radius is distributed on almost 45% of the whole surface of each pixel. It is an advantage in fabrication process since fabrication errors increase the radius spot. Therefore, looser tolerances are needed, which reduce the cost and complexity of optical system.

This optical system has six lenses (twelve surfaces that all of them are spherical), and its overall length is 93.49 mm. It includes fewer types of lenses and has wide FOV, than the congeneric optical systems, and its structure is simple. Therefore, the optical system is minimized in volume and mass, and its manufacturing process is easier. Besides, fully separated optical structure is designed to prevent gluing surface from degumming in space orbit, and it meets the requirements of design and practical engineering for small star sensor.

Tolerancing of optical system

Tolerance analysis is one of the most important steps in optical design. By tolerance analysis, the maximum and minimum fabrication error limits and the manufacturability of optical system are determined. Table 4 shows the tolerances for the designed optical system. These are normal optical tolerances, which are achievable for most manufacturers.
Table 4

Tolerances of designed optical system



Radius of Curvature

R/1000 mm


0.1 mm

Decenter X

0.05 mm

Decenter Y

0.05 mm

Tilt X

0.0167 degree = 1 arc minute

Tilt Y

0.0167 degree = 1 arc minute

Tolerance analysis is performed by the ZEMAX software with two methods including sensitivity analysis and Monte Carlo analysis. In these analyzes the adjustment parameter (compensator) and the performance criteria are the back focus and RMS spot radius respectively. Table 5 shows results of tolerancing by sensitivity analysis method. As can be seen, nominal RMS spot radius is equal to 1.5 μm. While estimated RMS spot radius is about 8.3 μm.
Table 5

Estimated performance changes based upon Root-Sum-Square method

Nominal RMS Spot Radius (mm)


Estimated change (mm)


Estimated RMS Spot Radius (mm)


Tolerancing by Monte Carlo analysis method shows that 90% of tolerances have RMS spot radius of approximately 8.1 μm (Table 6). Furthermore, 80% of tolerances lead to RMS spot radius of 7.7 μm that is satisfying by considering the selective detector with 15 μm pixel pitch and easy manufacture process.
Table 6

Deviation of nominal criteria by tolerances in Table 4


Criteria (RMS spot radius in mm)
















Results shown in Table 7 indicate that the mean deviation of nominal criterion is 6 μm. The nominal criterion is a spot with an RMS radius of 1.5 μm.
Table 7

statistics for deviation from nominal criterion (RMS Spot Radius in mm)









Std Dev


The analysis of these two methods of tolerancing shows that the system has a good tolerance.

Principle of baffle design

The parameters and characteristics that must be considered in baffle design are [16, 17, 29, 32]:

a- Dimensions: Dimensions of baffle are strongly affected by entrance pupil diameter of optical system, FOV and exclusion angle of the sun.

b- Vanes arrangement: Location, size and shape of vanes should be designed to meet the following conditions:

b-1- The vanes should be designed so that none of the optical elements could directly see the places illuminated by intense stray light sources.

b-2- The stray light has the maximum reflections inside the baffle and between the vanes before reaching the optical elements.

c- The surface of the baffle must be coated by a black absorbing material.

Figure 10 shows an example of no vane baffle that its angle relative to the sun axis is θ.
Fig. 10

No vane cylindrical optical baffle with angle ϴ relative to sun

According to Fig. 10, if the aperture diameter of the baffle is D, then:
$$ \mathit{\tan}\varTheta =\frac{D}{S_m} $$
As Fig. 10 shows, to prevent the entrance of sunlight to the optical system directly, the optical baffle length must be always larger than S m . In other words, we should have:
$$ L>{S}_m\to \kern0.5em L>\frac{D}{\mathit{\tan}\varTheta } $$
As Fig. 10 shows, for a no-vane optical baffle with a diameter equal to that of the optical system, the amount of stray light entered to the optical system is obtained from the following formula [17]:
$$ {E}_c=\frac{\rho {E}_i\sin \theta }{\pi }\ {\int}_0^{S_m}\frac{\left(L-S\right)\left(4{S}^2-{S}^2{\mathit{\tan}}^2\theta \right)}{{\left({\left(L-S\right)}^2+{a}^2\right)}^2} ds $$

Where E i is the solar irradiance normal to the line of sight, θ is the angle of the sun with respect to the optical axis, S is the distance of baffle that is illuminated, ρ is a diffuse reflectivity of the inner wall of the baffle, L is the baffle length, and a is its radius. According to the above explanation and Fig. 10, if the baffle is longer, the stray lights become further weakened.

Vanes designing

The vanes are structures in the baffle preventing scattering from walls. In an optimal state, baffle and vanes must be designed so that with a minimum size and number of vanes, maximum possible efficiency can be obtained. In this step, ray tracing is used to determine the position and height of the vanes. The height of the first vane should be determined according to entrance aperture diameter, FOV of the optical system and baffle length. Line AB in Fig. 11 is the part of baffle wall, which could be seen by the upper edge of the lens. The position and height of the second vane is determined by the cross of AB and FOV line of the system. The position and height of other vanes are calculated by this method.
Fig. 11

Vanes arrangement in baffle with ray tracing

According to Fig. 11, the position and height of vanes can be determined using Eqs. (7–9):
$$ {x}_{n+1}=\left({y}_0-{y}_{n+1}\right)\frac{L}{y_0-a} $$
$$ {y}_{n+1}=r-\frac{r+a}{1+{z}_n} $$
$$ {z}_n=2a{\left[\mathrm{r}-{y}_0+{x}_n\frac{y_0-a}{L}\frac{y_0+r}{y_0+{y}_n}\right]}^{-1} $$

Where x n and (r-y n ) are position and height of the nth vane, respectively; a is the semi diameter of the lens; r is the semi diameter of the baffle, and L is the baffle length.

Designed baffle for the optical system

The baffle designed for the optical system is a tube with two baffles combined with each other (Fig. 12). The front baffle is a shield against direct sunlight. The rear one rejects or attenuates the remaining stray light reflected into optical system from the front baffle walls.
Fig. 12

The designed baffle for optical system

In Fig. 12, α is the half FOV, β is the maximum angle between the sun and optical axis which is 30°, D 1 is entrance aperture diameter, which is 35.676 mm. For the baffle design, a safety margin of 1.5° for vanes was added to the half of FOV to reduce the edge scattering. According to the geometrical relation in Fig. 12, for front baffle length (X 2 ), rear baffle length (X 1 ) and final length of the baffle (L), we have:
$$ {X}_1=\frac{D_1}{\mathit{\tan}\beta -\mathit{\tan}\alpha } $$
$$ {X}_2=\frac{\mathit{\tan}\beta +\mathit{\tan}\alpha }{{\left(\mathit{\tan}\beta -\mathit{\tan}\alpha \right)}^2}{D}_1 $$
$$ L={X}_1+{X}_2=\frac{2\mathit{\tan}\beta }{{\left(\mathit{\tan}\beta -\mathit{\tan}\alpha \right)}^2}{D}_1 $$

The above equation shows that the baffle length (L) depends on FOV, exclusion angle of the sun and entrance aperture diameter.

According to Eqs. (79), position and height of vanes in the baffle were calculated (Table 8). Results show that six vanes in the baffle are enough to prevent the bright sources stray light in space.
Table 8

Position and height of vanes in the baffle

Vane number

Position (mm)

Vane number

Position (mm)































The metal chosen for baffle should be low in weight, strong, inexpensive and provide the strength necessary for the survival of launch. 6061 and 7075 aluminum alloys are the most applicable and most widely used metals in aerospace industries and are best choices for baffle manufacturing purposes which their strength are comparable to steel [3234]. Therefore, the 6061 aluminum alloy is used in this work. Because it is cheaper and more available than 7075 alloy.

To evaluate stray light performance in the optical system, particularly in the visible spectrum, the best method is to measure the point source transmittance (PST) at the detector location. PST is equal to the ratio of stray light irradiance in the desired location to light irradiance at different angles relative to the optical axis at the entrance aperture of the optical system [16, 27, 32]. In the following, to evaluate the effect of baffle and vanes on controlling and reducing stray light, after modeling the baffle in TracePro software, PST values are calculated. In this step to complete the simulations, the inner surface of the baffle and vanes are coated by a typical black coating with a 90% absorption coefficient which is available to all manufacturers. Figure 13 shows the corresponding PST curves.
Fig. 13

Log PST as a function of source angle

The above curve shows PST in a condition that baffle has no vanes and the below curve shows PST in a condition that baffle has optomecanical vanes. As these curves shows, using baffle and vanes caused the stray light to dramatically decrease. Figure 13 indicates that PST values of the two modes decrease with the increase of source angle. Furthermore, the vanes caused the PST to be approximately 10 to 15 times less than the condition of baffle without vanes. On the other hand, existence of baffle with vanes leads to reduce the value of PST to 10− 11 in off-axis angles. It has better performance of stray light suppression.


In this study, an optical system based on Double Gauss was designed for the star sensor. The purpose of the design was to calculate a simple and lightweight optical system meeting all of the parameters of the optical system. For this purpose, the APS detector, that is suitable for space applications, was used. The optical system is made up of six spherical lenses, all of which are available in Schott, and its structure is simple. The focal length of the optical system is 60 mm, its field of view is 14°, and its overall length is 93.49 mm. The results of simulation with ZEMAX software show that the designed optical system has high image quality. RMS size of the spot is less than 4 μm, and its distortion in the full FOV is less than 0.03%. Moreover, the results of tolerancing show that the system retains its optical quality by considering normal tolerances.

In the following, with stray light analysis, a simple, light weight and short optical baffle with 6 inner vanes to control and reduce stray lights due to bright sources in space, especially the sun, is designed in TracePro software. Finally, to evaluate the baffles and vanes, PST in different modes were calculated and simulated at the detector location. The results of the simulation show that using vanes in the baffle has improved the performance of the system against stray lights. Furthermore, the PST curve shows that its value has been reduced to 11− 10 times at off-axis angles, indicating a proper baffle performance against stray lights.



Active pixel sensor


Charge coupled device


Field of view


Point source transmission


Root mean square



‘Not applicable’.

Availability of data and materials

‘Not applicable’.

Authors’ contributions

MA carried out the initial studies, designed of optical system and baffle and drafted the manuscript. AE participated in the design of the study and performed the statistical analysis. HH conceived of the study, and participated in its design and coordination and helped to draft the manuscript. All authors read and approved the final manuscript.

Competing interests

‘The authors declare that they have no competing interests’.

Publisher’s Note

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Open AccessThis article is distributed under the terms of the Creative Commons Attribution 4.0 International License (, which permits unrestricted use, distribution, and reproduction in any medium, provided you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license, and indicate if changes were made.

Authors’ Affiliations

Department of Electrical and Electronic Engineering, Maleke-ashtar University of Technology, Tehran, Iran
Department of New Sciences & Technologies, University of Tehran, Tehran, Iran


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