CN105956233A - Sun-synchronous orbital satellite single view field star sensor installation direction design method - Google Patents

Abstract

The invention discloses a method for designing the installation and pointing of a single-field star sensor in a sun-synchronous orbit satellite. The method proposes a vector model between stray light and the coordinate system of the satellite body during the satellite's in-orbit operation. The model can analyze the satellite The vector relationship between stray light and satellite body coordinate system during on-orbit operation, by establishing the mathematical equation of stray light and satellite body coordinate system boundary curve under different working conditions, solves the pointing equation of the star sensor under the installation condition of the single-field star sensor , and obtained the maximum shading angle of sunlight and earth-atmospheric light for suppressing stray light star sensor hood under different pointing conditions. The present invention has the following advantages: it solves the problem that the star sensor installed in the sun-synchronous orbit spacecraft is to avoid stray light affecting the installation pointing problem, and at the same time provides the maximum sunlight and earth-atmospheric light shading angle for the single-field star sensor shading cover under different installation pointing conditions The design provides a theoretical basis.

Description

Design method for installation and pointing of single-field star sensor in sun-synchronous orbit satellite

technical field

The invention relates to the field of spacecraft attitude measurement, in particular to a design method for installation and pointing of a single-field star sensor of a sun-synchronous orbit satellite.

Background technique

As a spacecraft attitude measurement device, star sensors use stars as attitude measurement references. Compared with other satellite attitude sensors (sun sensors, gyroscopes, magnetometers, etc.), they have high precision, no drift, low power consumption, and The advantage of outputting absolute attitude information is that it is currently the most widely used attitude sensor. During the operation of the satellite, the star sensor may be interfered by sunlight or atmospheric light, which will increase the background noise of the image plane of the star sensor, affect the accuracy of star point extraction, and even the star point will be submerged in the background stray light , causing the star sensor not to work properly. Therefore, the anti-stray light problem of the star sensor is an important content of the current star sensor research.

In terms of star sensor stray light suppression, on the one hand, the anti-stray light performance of the star sensor itself can be improved by designing the optical lens of the star sensor, the structure of the hood, or changing the coating material of the inner wall of the hood; on the other hand, through analysis and optimization The installation position of the star sensor on the satellite is to avoid the influence of stray light on the star sensor as much as possible. In terms of research on star sensor installation and pointing methods, many research institutions have proposed design methods for practical applications. Among them, in view of the satellite's various working conditions and attitude conditions, Aerospace Dongfanghong proposed a star sensor installation angle based on mission planning in 2010 The determination method can solve the installation and pointing problem of a given star sensor under agile maneuvering conditions, but this method determines the appropriate installation angle of the star sensor by continuously adjusting the installation angle of the star sensor and the working conditions, and the design method is very complicated. It is impossible to calculate and give the maximum sunlight and earth-atmospheric shading angle of the star sensor hood under different installation pointing conditions.

Contents of the invention

The present invention aims to solve at least one of the above-mentioned technical problems.

For this reason, an object of the present invention is to propose a kind of sun-synchronous orbit satellite monoscopic field star sensor installation pointing design method.

In order to achieve the above object, an embodiment of the present invention discloses a sun-synchronous orbit satellite single-field star sensor installation pointing design method, comprising the following steps: S1: setting sun-synchronous orbit parameters, satellite parameters, HPOP resistance model in STK software Parameters; S2: Perform HPOP simulation in STK software to determine the angle between the sun light and the three-axis vector of the satellite body coordinate system during the satellite's in-orbit operation; S3: Calculate and determine the angle between the earth's atmosphere and the satellite body's boundary according to the radius of the earth and the height of the atmosphere ; S4: According to the angle between the sunlight and the three-axis vector of the satellite body coordinate system during the satellite's in-orbit operation, determine the mathematical equation of the sunlight relative to the boundary of the satellite body coordinate system when the satellite is in a non-motorized state; The angle between the light and the satellite body boundary determines the mathematical equation of the ground, air, light, and satellite body coordinate system boundaries when the satellite is in a non-maneuvering state; S5: Set the maximum roll angle and pitch angle under the satellite maneuvering state, and determine it according to the coordinate system rotation matrix The mathematical equations of the satellite body coordinate system boundary curves of sunlight, ground, air and light relative to the satellite body coordinate system under different maneuvering states, and the area where the satellite body coordinate system is not affected by stray light under various working conditions; S6: according to various working conditions The lower satellite body coordinate system is not affected by stray light, and the mathematical equation for the installation pointing range of the star sensor to avoid the influence of stray light under the installation condition of the single-field star sensor is determined; Determine the relationship between the maximum solar shading angle of the single-field star sensor and the shading angle of the ground, air, and light by setting the boundary curve of the ground, air, and light, and judge whether the installation interval meets the design requirements according to the design principles of the shading cover; if the design requirements are met, the design ends; if not According to design requirements, execute step S5 to reset the maximum roll angle and pitch angle in the maneuvering state of the satellite, or make it available in some working conditions.

The installation and pointing design method of the single-field star sensor of the sun-synchronous orbit satellite according to the embodiment of the present invention can effectively solve the problem of the installation pointing of the star sensor installed on the sun-synchronous orbit spacecraft to avoid stray light (sunlight, earth-atmospheric light) from affecting the installation. At the same time, it provides a theoretical basis for the design of the maximum sunlight and earth-atmospheric light shading angle design of the single-field star sensor hood under different installation pointing conditions.

In addition, according to the above-mentioned embodiment of the present invention, the installation and pointing design method of the single-field star sensor of the sun-synchronous orbit satellite can also have the following additional technical features:

Further, in step S1, the sun-synchronous orbit parameters include height h, descending node local time T, on-orbit operation period t; the satellite parameters include satellite mass M, satellite volume V; HPOP resistance in the STK software Model parameters include atmospheric resistance C _d , solar light pressure C _r , satellite area-to-mass ratio A/M and geomagnetic force K _p , wherein the satellite area-to-mass ratio A/M is the ratio of 1/4 satellite surface area S to mass M .

Further, in step S2, in the coordinate system of the satellite body, the Z-axis points to the center of the earth, the X-axis is the forward direction of the satellite, and the Y-axis is determined by the right-hand rule; α is the angle between the sun and the X-axis, and β is the sun The angle between light and Y axis, γ is the angle between sunlight and Z axis.

Further, step S3 further includes: setting the radius of the earth _Re and the height of the atmosphere d, and calculating and determining the angle γ _atm between the Earth's atmosphere and the boundary of the satellite body according to γ _atm =asin((R _e +d)/h).

Further, step S4 further includes: S401: In the non-motorized working state of the satellite, the sunlight boundary equation is determined by the extreme value of the angle between the sunlight and each axis of the satellite body coordinate system in step S2 as follows: Among them, θ ₁ is the angle between the positive left boundary of the sun's Y axis and the Y axis, and θ ₂ is the angle between the positive right boundary of the sun's Y axis and the Y axis; The boundary can be directly determined by the half-cone angle of the atmosphere and light at different orbital heights. The boundary equation of the atmosphere and light in the satellite body coordinate system is as follows: Among them, θ is the semi-cone angle of the earth's atmosphere and light.

Further, in step S5, the maneuvering state of the satellite includes left swing, right swing, pitch forward and pitch backward.

Further, step S6 further includes: S601: the optimal installation pointing curve of the single-field star sensor not affected by stray light is in the YZ plane of the satellite body coordinate system; S602: the simultaneous satellite left side swings the air-optical boundary equation, The solar light boundary equation on the right side of the satellite and the plane X=0 are used to obtain the pointing boundary range of the star sensor on the Y-off-Z axis: the single-field star sensor installation pointing equation is as follows:

Among them, σ is the angle between the right pendulum boundary of sunlight and the Y axis in the YZ installation plane, and τ is the angle between the left pendulum boundary of the air and light in the YZ installation plane and the Y axis.

Further, step S7 further includes: S701: The angle σ between the sunlight and the Y-axis in the YZ installation plane can be obtained according to the right pendulum sunlight boundary curve and the plane X=0, and the maximum sun shading angle can be determined by the single-field star The angle between the sensor pointing in the YZ installation plane and the Y axis Obtain the maximum shading angle of the sun S702: According to the boundary curve of the earth, atmosphere and light on the left side and the plane X=0, the angle τ between the earth, atmosphere and the Y axis in the YZ installation plane can be obtained, and the maximum shading angle of the earth, atmosphere and light can be installed in YZ by the single-field star sensor In-plane pointing angle with Y axis Obtain the maximum shading angle of the earth's air light

Additional aspects and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

Description of drawings

The above and/or additional aspects and advantages of the present invention will become apparent and comprehensible from the description of the embodiments in conjunction with the following drawings, wherein:

Fig. 1 is the flow chart of the installation and pointing design method of the sun-synchronous orbit satellite single-field star sensor installation pointing design method of an embodiment of the present invention;

Fig. 2 is a schematic diagram of sunlight relative to satellite body coordinate system according to an embodiment of the present invention;

Fig. 3 is a schematic diagram of the relationship model between sunlight and the satellite body coordinate system during the three-year on-orbit operation of an embodiment of the present invention;

Fig. 4 is a diagram of the relationship between the sunlight boundary curve and the satellite body coordinate system under the satellite no-maneuvering state according to an embodiment of the present invention;

Fig. 5 is a diagram of the relationship between the earth-air-optical boundary curve and the satellite body coordinate system under the satellite no-maneuvering state according to an embodiment of the present invention;

Fig. 6 is a schematic diagram of the YZ plane projection of the boundary curves of sunlight, earth, air and light under different working conditions of a satellite according to an embodiment of the present invention;

Fig. 7 is a schematic diagram of the XZ plane projection of the boundary curves of sunlight, earth, air and light under different working conditions of a satellite according to an embodiment of the present invention;

Fig. 8 is a schematic diagram of the relationship between the different installation orientations of the single-field star sensor in the YZ plane of the satellite body coordinate system and the maximum sunlight and terrestrial-atmospheric shading angles according to an embodiment of the present invention.

detailed description

Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary only for explaining the present invention and should not be construed as limiting the present invention.

In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", " The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner" and "outer" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and Simplified descriptions, rather than indicating or implying that the device or element referred to must have a particular orientation, be constructed and operate in a particular orientation, and thus should not be construed as limiting the invention. In addition, the terms "first" and "second" are used for descriptive purposes only, and should not be understood as indicating or implying relative importance.

In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it may be mechanically connected or electrically connected; it may be directly connected or indirectly connected through an intermediary, and it may be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

These and other aspects of embodiments of the invention will become apparent with reference to the following description and drawings. In these descriptions and drawings, some specific implementations of the embodiments of the present invention are specifically disclosed to represent some ways of implementing the principles of the embodiments of the present invention, but it should be understood that the scope of the embodiments of the present invention is not limited by this limit. On the contrary, the embodiments of the present invention include all changes, modifications and equivalents coming within the spirit and scope of the appended claims.

A method for designing the installation and pointing of a single-field star sensor for a sun-synchronous orbit satellite according to an embodiment of the present invention will be described below with reference to the accompanying drawings.

Please refer to Figure 1, a sun-synchronous orbit satellite single-field star sensor installation pointing design method, including the following steps:

S1: Set sun-synchronous orbit parameters, satellite parameters, and HPOP resistance model parameters in STK software. In an embodiment of the present invention, the sun-synchronous orbit parameters include altitude h, local time T of descending node, and on-orbit operation period t. Satellite parameters include satellite mass M and satellite volume V. The HPOP (High Precision Orbit Prediction) resistance model parameters in the STK (Satellite Tool Kit) software include atmospheric resistance C _d , solar light pressure C _r , satellite surface-to-mass ratio A/M and geomagnetic force K _p , wherein the satellite surface mass The ratio A/M is the ratio of 1/4 satellite surface area S to mass M.

Specifically, considering the satellite's ground imaging, perturbation and resistance factors, this embodiment sets the satellite orbit height h to 700km; at the same time considering the earth observation imaging, when this embodiment sets the descending node, T is the place where the illumination is more complicated 10:30 orbit; the present embodiment sets the satellite operation period t as 3 years.

In this embodiment, the mass M of the satellite is set to 20.5 kg, and the volume V of the satellite is set to 324*360*400 mm.

In this embodiment, the atmospheric resistance C _d is set to 2.2, the solar light pressure C _r is 1.0, and the geomagnetic force K _p is 3.0. According to the satellite surface-to-mass ratio A/M is 1/4 the ratio of the satellite surface area S to the mass M, the calculation can be obtained Satellite surface-to-mass ratio A/M≈0.01.

S2: Perform HPOP simulation in STK software to determine the angle between the sunlight and the three-axis vector of the satellite body coordinate system during the satellite's in-orbit operation. In the coordinate system of the satellite body, the Z axis points to the center of the earth, the X axis is the forward direction of the satellite, and the Y axis is determined by the right-hand rule; α is the angle between the sunlight and the X axis, β is the angle between the sunlight and the Y axis, and γ is the sun The angle between the light and the Z axis.

Specifically, as shown in FIG. 2 . According to the parameter setting in step S1, this embodiment uses the STK software to obtain the angle between the sun light and the three-axis vector of the satellite body coordinate system during the three-year operation of the satellite in orbit, wherein the maximum cosine α _max of the angle between the sun light and the X-axis vector is 0.9946, the minimum value α _min is -0.9946, so the angle between sunlight and the X-axis ranges from 5.9620° to 174.0470°; the maximum value of the cosine β _max of the angle between sunlight and the Y-axis vector is -0.0841, and the minimum value β _min is - 0.4537, so the angle between sunlight and Y-axis ranges from 94.8270° to 116.9830°; the maximum cosine γ _max of the angle between sunlight and the Z-axis vector is 0.4376, and the minimum γ _min is -0.9914, so the angle between sunlight and the Y-axis The angle range is 64.0470°～172.4730°. The direction of the sunlight vector at each moment is described in the satellite body coordinate system, as shown in Figure 3, the light point represents the direction of the incoming light vector of sunlight relative to the origin of the satellite body coordinate system.

S3: Set the radius of the earth _Re , the height of the atmosphere d, and calculate and determine the angle γ _atm between the earth's air light and the boundary of the satellite body according to γ _atm =asin((R _e +d)/h), that is, the angle with the positive direction of the Z axis .

Specifically, due to the gravitational effect of the earth, almost all the gas is concentrated within a height of 100 kilometers from the ground, and 75% of the atmosphere is concentrated in the troposphere from the ground to a height of 10 kilometers. In this embodiment, it is set that the altitude of the atmosphere is d=100km, and the radius of the earth _Re =6378km. According to the relationship γ _atm =asin((R _e +d)/h), substituting the above parameters into the above formula to calculate the angle between the Earth's air and light and the satellite body boundary (that is, the angle with the positive direction of the Z axis) γ _atm is 66.24 °, considering the change of the semi-major axis, this embodiment adopts a redundant design of 67° (corresponding to 659.44km).

S4. According to the angle between the sunlight and the three-axis vector of the satellite body coordinate system during the satellite's in-orbit operation in step S2, determine the mathematical equation of sunlight relative to the boundary of the satellite body coordinate system under the satellite no-maneuvering state; determine the ground under the satellite no-maneuvering state according to step S3. Mathematical equation of air-optic relative to satellite body coordinate system boundary.

Specifically, when the satellite is in the non-maneuvering state, the boundary equation of sunlight is determined by the extreme value of the angle between the sunlight and each axis of the satellite body coordinate system in step S2. According to the analysis of step S2, the boundary equation of sunlight in the satellite body coordinate system is composed of two The curves are composed of the following formulas, where z<0.4376, θ ₁ =94.8270°, θ ₂ =116.9830°, as shown in Figure 4 .

$\left\{\begin{array}{c}{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; z</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}\\ \mathrm{<span\; class="notranslate">\; the\; y</span>}<span\; class="notranslate">\; =</span>{\mathrm{<span\; class="notranslate">\; sin\&theta;</span>}}_{\mathrm{<span\; class="notranslate">\; 1</span>}}\end{array}\right.<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; )</span>$

$\left\{\begin{array}{c}{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; z</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}\\ \mathrm{<span\; class="notranslate">\; the\; y</span>}<span\; class="notranslate">\; =</span>{\mathrm{<span\; class="notranslate">\; sin\&theta;</span>}}_{\mathrm{<span\; class="notranslate">\; 2</span>}}\end{array}\right.<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 2</span>}<span\; class="notranslate">\; )</span>$

Since the Z-axis of the satellite body coordinate system always points to the center of the earth, the boundary of the Earth’s atmosphere and light can be directly determined by the half-cone angle θ of the Earth’s atmosphere and light at different orbital heights when the satellite is not maneuvering. The boundary equation of the Earth’s atmosphere and light in the satellite’s body coordinate system is as follows: Where θ = 67°, as shown in Figure 5.

$\left\{\begin{array}{c}{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; z</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}\\ \mathrm{<span\; class="notranslate">\; z</span>}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; c</span>}\mathrm{<span\; class="notranslate">\; o</span>}\mathrm{<span\; class="notranslate">\; the\; s</span>}\mathrm{<span\; class="notranslate">\; \&theta;</span>}\end{array}\right.<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 3</span>}<span\; class="notranslate">\; )</span>$

S5: Set the maximum roll angle and pitch angle in the satellite maneuvering state, and determine the relative satellite light, earth, atmosphere, and light in different maneuvering states (left swing, right swing, forward tilt, and backward tilt) according to the coordinate system rotation matrix The mathematical equation of the boundary curve of the body coordinate system, and the area where the satellite body coordinate system is not affected by stray light under various working conditions.

Specifically, this embodiment defines the forward swing of the satellite as: the satellite deflects from +X to the -Z axis around the Y axis around the body coordinate system, and the maximum deflection angle is -30°; the back swing of the satellite is: the satellite around the body coordinate system around the Y axis The shaft deflects from +X to +Z, and the maximum deflection angle is 30°. This embodiment defines the left side swing of the satellite: the satellite rotates around the body coordinate system around the X axis from -Y to the -Z axis, and the maximum deflection angle is 30°; the right side swing: the satellite around the body coordinate system around the X axis from the -Y direction +Z axis deflection, the maximum deflection angle is 30°.

The equation of the earth-air-optical boundary curve equation for the left side of the satellite swinging 30° is equivalent to the equation (3) of the earth-air-optical boundary in step S4, which rotates -30° around the X axis. After the transformation of the rotation matrix, it is as follows:

The solar boundary curve equation of the satellite swinging 30° on the left side is equivalent to the solar boundary equations (1) and (2) in step S4 rotating -30° around the X axis, and only need to analyze the influence of the left boundary curve (1), After the rotation matrix transformation, the following formula:

The equation of the earth-air-optical boundary curve equation for the right side of the satellite swinging 30° is equivalent to the equation (3) of the earth-air-optical boundary in step S4 rotated 30° around the X axis, and after transformation by the rotation matrix, it is as follows:

The solar boundary curve equation of the right side of the satellite swinging 30° is equivalent to the sunlight boundary equations (1) and (2) rotating 30° around the X axis in step S4, and only need to analyze the influence of the right boundary curve (2). After the rotation matrix is transformed, the formula is as follows:

The equation of the satellite's forward swing of 30°, the Earth's air-optical boundary curve is equivalent to the equation (3) of the Earth's air-optical boundary in step S4, which is rotated by -30° around the Y axis, and after transformation by the rotation matrix, it is as follows:

The solar boundary curve equation of the satellite's forward swing of 30° is equivalent to the solar boundary equations (1) and (2) in step S4 rotating -30° around the Y axis. range, no analysis is required.

The Earth-Air-Optical Boundary Curve Equation of the 30° Backward Swing of the Satellite is Equivalent to the Earth-Air-Optic Boundary Equation (3) rotated 30° around the Y-axis in Step S4, and after transformation by the rotation matrix, it is as follows:

The solar boundary curve equation of the satellite backswing 30° is equivalent to the solar boundary equations (1) and (2) in step S4 rotated by -30° around the Y axis. range, no analysis is required.

According to the extraction and transformation of the boundary equations of sunlight and earth-atmospheric light under various working conditions according to the above-mentioned parts of steps S4 and S5, it can be concluded that the satellite body coordinate system is not interfered by sunlight and earth-atmospheric light under various working conditions The area where the boundary curve is projected on the YZ plane of the satellite body is shown in Figure 6. It can be seen that the area not affected by interfering light consists of two parts, and the included angle ranges are 57.8° and 26° respectively. In this embodiment, the field of view angle of the star sensor is set to 15°, so the range of 26° does not meet the minimum installation condition of the star sensor. The projection of the boundary curve on the XZ plane is shown in Figure 7. It can be seen that the undisturbed area consists of the Earth's air-optical boundary curve (6) on the left side of the satellite, the sunlight boundary curve (5) on the right side of the satellite, and the air-optical boundary curve on the rear side of the satellite. (9) and the front side of the satellite swing the air-optical boundary curve (8) to form.

S6. Determine the mathematical equation for the installation pointing range of the star sensor to avoid stray light under the installation condition of the single-field star sensor.

Specifically, under various operating conditions of the satellite, the best installation pointing curve of the single-field star sensor in this embodiment that is not affected by stray light (sunlight, earth-atmospheric light) is within the YZ plane of the satellite body coordinate system. Simultaneously combining the left side of the satellite with the air-optical boundary equation (6), the satellite's right side with the solar light boundary equation (5) and the plane X=0, it can be obtained that the star sensor points to the boundary range in the Y-Z axis: (- 0.905<z<-0.122). Therefore, the installation pointing equation of the monoscopic star sensor is as follows:

$\left\{\begin{array}{c}{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; z</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}\\ \mathrm{<span\; class="notranslate">\; x</span>}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 0</span>}\\ <span\; class="notranslate">\; -</span>\mathrm{<span\; class="notranslate">\; 0.905</span>}<span\; class="notranslate">\; <</span>\mathrm{<span\; class="notranslate">\; z</span>}<span\; class="notranslate">\; <</span><span\; class="notranslate">\; -</span>\mathrm{<span\; class="notranslate">\; 0.122</span>}<span\; class="notranslate">\; ,</span>\mathrm{<span\; class="notranslate">\; the\; y</span>}<span\; class="notranslate">\; ></span>\mathrm{<span\; class="notranslate">\; 0</span>}\end{array}\right.<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 10</span>}<span\; class="notranslate">\; )</span>$

S7. Determine the relationship between the maximum sunlight shading angle of the single-field star sensor and the ground-atmospheric light shading angle, and judge whether the installation interval meets the design requirements according to the design principles of the shading cover; if the design requirements are met, the design ends; if the design requirements are not met, execute Step S5, reset the maximum roll angle and pitch angle in the maneuvering state of the satellite, or make it available in some working conditions.

Specifically, according to the right pendulum sunlight boundary curve (5) and the plane X=0, it can be obtained that the angle between the sunlight and the Y axis in the YZ installation plane is 64.8°, and the maximum sun shading angle can be determined by the single-field star sensor Angle between pointing and Y axis in YZ installation plane Obtain the maximum shading angle of the sun

Similar to the calculation of the maximum shading angle of sunlight, according to the boundary curve (6) on the left and the plane X=0, it can be obtained that the angle between the air light and the Y axis in the YZ installation plane is 7°, and the ground air light is the largest The shading angle can be pointed by the monoscopic star sensor in the YZ installation plane and the angle between the Y axis Obtain the maximum shading angle of the earth's air light According to the above calculation, the relationship between the maximum solar shading angle of the shading cover and the maximum air-light shading angle is shown in Figure 8.

Since the intensity of sunlight is much higher than that of the earth's atmosphere, in the design of the star sensor hood, the sun's shading angle must be greater than the earth's atmosphere's shading angle, so the installation of a single star sensor in the YZ plane points to the Y-axis angle should be greater than - 35°, the half-field angle of the star sensor in this embodiment is 7.5°, and the designed air-light shielding angle is not less than 10°. It can be seen from Figure 8 that the Y-axis angle should be less than -20°. The specific orientation of the star sensor installation plane needs to be combined with the design requirements of the star sensor hood. If the design requirements for the size of the hood and the shading performance are met, the design ends; if the design requirements for the size and shading performance of the hood are not met, go to step S5, and appropriately reduce the maximum roll angle and pitch angle in the maneuvering state of the satellite, or make it partially available under working conditions.

In addition, other components and functions of the sun-synchronous orbit satellite single-field star sensor installation and pointing design method of the embodiment of the present invention are known to those skilled in the art, and will not be repeated in order to reduce redundancy.

In the description of this specification, descriptions referring to the terms "one embodiment", "some embodiments", "example", "specific examples", or "some examples" mean that specific features described in connection with the embodiment or example , structure, material or characteristic is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

Although the embodiments of the present invention have been shown and described, those skilled in the art can understand that various changes, modifications, substitutions and modifications can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the invention is defined by the claims and their equivalents.

Claims (8)

1. a satellite in Sun-synchronous orbit monoscopic star sensor is installed and is pointed to method for designing, it is characterised in that include following Step:

S1: HPOP resistance model parameter in sun-synchronous orbit parameter, satellite parametric reduction, STK software is set；

S2: carry out HPOP emulation in STK software, determines satellite period sunlight in orbit and satellite body coordinate system three axle Vector angle；

S3: the base area radius of a ball, atmosphere high computational determine gas light and satellite body border angle；

S4: according to described satellite period sunlight and satellite body coordinate system three axial vector angle in orbit, determine described in defend Star under without maneuvering condition, sunlight relative satellite body coordinate system border math equation；According to described gas light with satellite originally Body border angle determine described satellite under without maneuvering condition, gas light relative satellite body coordinate system border math equation；

S5: maximum lateral swinging angle and the angle of pitch under satellite maneuvering condition are set, determine that described satellite exists according to coordinate system spin matrix Sunlight, gas light relative satellite body coordinate system boundary curve math equation under different maneuvering conditions, and various operating mode bar Under part, satellite body coordinate system is not by veiling glare influence area；

S6: according to satellite body coordinate system under various working conditions not by veiling glare influence area, determines that monoscopic star sensor is pacified For avoiding stray light star sensor to install sensing scope math equation under the conditions of dress；And

S7: determine monoscopic star sensor maximum too according to right side pendulum sunlight boundary curve and left side pendulum gas light boundary curve Sunlight shield angle, gas light shield angle relation, judge to install whether interval meets design requirement according to Baffle design principle；If Meeting design requirement, design terminates；If being unsatisfactory for designing requirement, performing step S5, resetting under satellite maneuvering condition maximum Lateral swinging angle, the angle of pitch, or make it available under Part load.

Satellite in Sun-synchronous orbit monoscopic star sensor the most according to claim 1 is installed and is pointed to method for designing, and it is special Levying and be, in step sl, described sun-synchronous orbit parameter includes T, in orbit cycle t local time the in of height h, southbound node；

Described satellite parametric reduction includes satellite mass M, satellite volume V；

In described STK software, HPOP resistance model parameter includes atmospheric drag C_d, solar light pressure C_r, area-to mass ratio of satellite A/M and earth magnetism Power K_p, wherein, described area-to mass ratio of satellite A/M is the ratio of 1/4 satellite table area S and mass M.

Satellite in Sun-synchronous orbit monoscopic star sensor the most according to claim 2 is installed and is pointed to method for designing, and it is special Levying and be, in step s 2, in described satellite body coordinate system, Z axis points to the earth's core, and X-axis is satellite direction of advance, and Y-axis is by the right side Hand rule determines；α is sunlight and X-axis angle, and β is sunlight and Y-axis angle, and γ is sunlight and Z axis angle.

Satellite in Sun-synchronous orbit monoscopic star sensor the most according to claim 3 is installed and is pointed to method for designing, and it is special Levying and be, step S3 farther includes:

It is configured to radius of a ball R_e, atmosphere height d, according to γ_atm=asin ((R_e+ d)/h), calculate and determine that gas light is with satellite originally Body border angle γ_atm。

Satellite in Sun-synchronous orbit monoscopic star sensor the most according to claim 4 is installed and is pointed to method for designing, step S4 farther includes: S401: under the inorganic dynamic duty of described satellite, sunlight absorbing boundary equation by sunlight in step S2 with Satellite body coordinate system each axle clamp angle extreme value such as following equation determines:

$\left\{\begin{array}{c}{x}^2+y^2+z^2=1\\ y={\mathrm{sin\&theta;}}_1\end{array}\right.$

$\left\{\begin{array}{c}{x}^2+y^2+z^2=1\\ y={\mathrm{sin\&theta;}}_2\end{array}\right.;$

Wherein, θ₁For sunlight inclined Y-axis forward left margin and Y-axis angle, θ₂Press from both sides with Y-axis for sunlight inclined Y-axis forward right margin Angle；

S402: described satellite without gas light border under maneuvering condition can by multiple orbital attitudes gas light semi-cone angle the most true Fixed, gas light is in satellite body coordinate system absorbing boundary equation equation below:

$\left\{\begin{array}{c}{x}^2+y^2+z^2=1\\ z=cos\mathrm{\&theta;}\end{array}\right.$

Wherein, θ is gas light semi-cone angle.

Satellite in Sun-synchronous orbit monoscopic star sensor the most according to claim 5 is installed and is pointed to method for designing, and it is special Levying and be, in step s 5, the maneuvering condition of described satellite includes left side pendulum, right side pendulum, front face upward and swing back.

Satellite in Sun-synchronous orbit monoscopic star sensor the most according to claim 6 is installed and is pointed to method for designing, and it is special Levying and be, step S6 farther includes:

The optimal installation that S601: monoscopic star sensor is not affected by veiling glare points to curve in satellite body coordinate system YZ plane In；

S602: put pendulum sunlight absorbing boundary equation and plane X=0 on the right side of gas light absorbing boundary equation, satellite on the left of simultaneous satellite and ask Obtain-Z-axis direction star sensor inclined at Y and point to bounds: monoscopic star sensor is installed and pointed to equation such as following formula:

$\left\{\begin{array}{c}{x}^2+y^2+z^2=1\\ x=0\\ -sin\mathrm{\&sigma;}<z<-\sin \mathrm{\&tau;},y>0\end{array}\right.$

Wherein, σ is to put border and Y-axis angle in YZ mounting plane on the right side of sunlight, and τ is gas light in YZ mounting plane Pendulum border, left side and Y-axis angle.

Satellite in Sun-synchronous orbit monoscopic star sensor the most according to claim 7 is installed and is pointed to method for designing, and it is special Levying and be, step S7 farther includes:

S701: sunlight and Y-axis in YZ mounting plane can be tried to achieve according to right side pendulum sunlight boundary curve and plane X=0 To angle σ, maximum sun shield angle can be pointed to and Y-axis angle by monoscopic star sensor in YZ mounting planeTry to achieve, too The maximum shield angle of sun

S702: gas light and Y-axis in YZ mounting plane can be tried to achieve according to left side pendulum gas light boundary curve and plane X=0 To angle τ, gas light maximum shield angle can be pointed to and Y-axis angle by monoscopic star sensor in YZ mounting planeTry to achieve, Gas light maximum shield angle