CN105956233B - Design method is directed toward in the installation of satellite in Sun-synchronous orbit monoscopic star sensor - Google Patents
Design method is directed toward in the installation of satellite in Sun-synchronous orbit monoscopic star sensor Download PDFInfo
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- CN105956233B CN105956233B CN201610250665.7A CN201610250665A CN105956233B CN 105956233 B CN105956233 B CN 105956233B CN 201610250665 A CN201610250665 A CN 201610250665A CN 105956233 B CN105956233 B CN 105956233B
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/30—Circuit design
- G06F30/36—Circuit design at the analogue level
- G06F30/367—Design verification, e.g. using simulation, simulation program with integrated circuit emphasis [SPICE], direct methods or relaxation methods
Abstract
It is installed the invention discloses a kind of satellite in Sun-synchronous orbit monoscopic star sensor and is directed toward design method, this method propose a kind of satellite in orbit during vector model between stray light and satellite body coordinate system, the vector correlation of stray light and satellite body coordinate system during the model can analyze out satellite in orbit, by establishing stray light and satellite body coordinate system boundary curve math equation under different working conditions, it calculates star sensor under monoscopic star sensor mounting condition and is directed toward equation, and it obtains under the conditions of being differently directed as inhibition stray light star sensor Baffle design maximum sunlight, gas light shield angle.The present invention has the advantage that solving the problems, such as that the installed star sensor of sun-synchronous orbit spacecraft is to avoid stray light from installing direction, while providing theoretical foundation for monoscopic star sensor hood maximum sunlight, the design of gas light shield angle under the conditions of different installations direction.
Description
Technical field
The present invention relates to spacecraft attitude fields of measurement, and in particular to a kind of satellite in Sun-synchronous orbit haplopia field stars are sensitive
Design method is directed toward in device installation.
Background technique
Star sensor is as spacecraft attitude measurement device, using fixed star as attitude measurement reference data, with other satellites
Attitude sensor part (sun sensor, gyro, magnetometer etc.) compare have precision it is high, without drift, low in energy consumption, and export exhausted
The advantages of to posture information is the widest attitude sensor of current application.During satellite transit, star sensor is possible to
By the interference of sunlight or gas light, the image planes ambient noise of star sensor is improved, influences the accuracy of asterism extraction, very
It can be submerged in background miscellaneous light to asterism, star sensor is caused to can not work normally.Therefore, the anti-stray light of star sensor is asked
Topic is an important content of current star sensor research.
It, on the one hand can be by designing star sensor optical lens, hood knot in terms of the spuious Xanthophyll cycle of star sensor
Structure changes hood inside coating material and improves star sensor itself and resists spuious optical property, on the other hand can pass through analysis
Influence of the stray light to star sensor is avoided as far as possible with installation site of the optimization star sensor on satellite.Pacify in star sensor
Pointing method research aspect is filled, there are many research institutions to propose design method for practical application, wherein a variety of for satellite
Operating condition posture condition, the star sensor setting angle that space flight Dongfanghong company in 2010 proposes task based access control planning determine method
It can solve and give star sensor installation direction problem under quick motor-driven operating condition, but this method is by constantly adjusting star sensor
Setting angle and working condition determine suitable star sensor setting angle, and design method is sufficiently complex, while cannot calculate
It is given at star sensor hood maximum sunlight, gas light shield angle under the conditions of different installations are directed toward.
Summary of the invention
The present invention is directed at least solve one of above-mentioned technical problem.
For this purpose, an object of the present invention is to provide a kind of installations of satellite in Sun-synchronous orbit monoscopic star sensor to refer to
To design method.
To achieve the goals above, it is sensitive that embodiment of the invention discloses a kind of satellite in Sun-synchronous orbit haplopia field stars
Design method is directed toward in device installation, comprising the following steps: S1: setting sun-synchronous orbit parameter, satellite parametric reduction, in STK software
HPOP resistance model parameter；S2: carrying out HPOP emulation in STK software, sunlight and satellite during determining satellite in orbit
Three axial vector angle of body coordinate system；S3: definitely gas light and satellite body boundary are calculated according to earth radius, atmosphere height
Angle；S4: according to the satellite in orbit during sunlight and three axial vector angle of satellite body coordinate system, determine described in defend
Star is under no maneuvering condition, sunlight relative satellite body coordinate system boundary math equation；According to the gas light and satellite sheet
Body boundary angle determine the satellite under no maneuvering condition, gas light relative satellite body coordinate system boundary math equation；S5:
Maximum lateral swinging angle and pitch angle under satellite maneuvering condition are set, determine the satellite different motor-driven according to coordinate system spin matrix
Satellite under sunlight, gas light relative satellite body coordinate system boundary curve math equation and various working conditions under state
Body coordinate system is not by veiling glare influence area；S6: according to satellite body coordinate system under various working conditions not by the veiling glare zone of influence
Domain determines and is directed toward range math equation under monoscopic star sensor mounting condition to avoid stray light star sensor from installing；
And S7: sunlight boundary curve is put according to right side and left side pendulum gas light boundary curve determines monoscopic star sensor maximum too
Sunlight shield angle, gas light cover angular dependence, are judged to install whether section meets design requirement according to Baffle design principle；If
Meet design requirement, design terminates；If being unsatisfactory for design requirement, step S5 is executed, is reset maximum under satellite maneuvering condition
Lateral swinging angle, pitch angle, or use it can under Part load.
Design method is directed toward in satellite in Sun-synchronous orbit monoscopic star sensor according to an embodiment of the present invention installation, can be with
Effectively solving the installed star sensor of sun-synchronous orbit spacecraft is to avoid stray light (sunlight, gas light) from influencing installation to refer to
It is set to problem, while for monoscopic star sensor hood maximum sunlight, gas light shield angle under the conditions of different installations direction
Meter provides theoretical foundation.
In addition, design is directed toward in satellite in Sun-synchronous orbit monoscopic star sensor installation according to the above embodiment of the present invention
Method can also have the following additional technical features:
Further, in step sl, T when the sun-synchronous orbit parameter includes height h, southbound node place, in-orbit
Cycle of operation t；The satellite parametric reduction includes satellite mass M, satellite volume V；HPOP resistance model parameter packet in the STK software
Include atmospheric drag Cd, solar light pressure Cr, area-to mass ratio of satellite A/M and telluric magnetic force Kp, wherein the area-to mass ratio of satellite A/M defends for 1/4
The ratio of star catalogue area S and mass M.
Further, in step s 2, in the satellite body coordinate system, Z axis is directed toward the earth's core, and X-axis is satellite advance side
To Y-axis is determined by the right-hand rule；α is sunlight and X-axis angle, and β is sunlight and Y-axis angle, and γ is that sunlight and Z axis press from both sides
Angle.
Further, step S3 further comprises: setting earth radius Re, atmosphere layer height d, according to γatm=asin
((Re+ d)/h), calculate and determine gas light and satellite body boundary angle γatm。
Further, step S4 further comprises: S401: under the inorganic dynamic working condition of satellite, sunlight boundary side
Journey is determined by sunlight in step S2 and each axle clamp angle extreme value of satellite body coordinate system such as following equation:Wherein, θ1For the inclined Y-axis forward direction left margin of sunlight and Y-axis angle, θ2For too
The inclined Y-axis forward direction right margin of sunlight and Y-axis angle；S402: satellite gas light boundary under no maneuvering condition can pass through difference
Orbit altitude gas light semi-cone angle directly determines, and gas light is in the following formula of satellite body coordinate system absorbing boundary equation:Wherein, θ is gas light semi-cone angle.
Further, in step s 5, the maneuvering condition of the satellite includes left side pendulum, right side pendulum, preceding face upward and swing back.
Further, step S6 further comprises: S601: the best installation that monoscopic star sensor is not influenced by veiling glare refers to
To curve in satellite body coordinate system YZ plane；S602: pendulum gas light absorbing boundary equation, satellite right side are put too on the left of simultaneous satellite
Sunlight absorbing boundary equation and plane X=0 acquire Y partially-Z axis to star sensor be directed toward bounds: monoscopic star sensor peace
Dress is directed toward equation such as following formula:
Wherein, σ is to put boundary and Y-axis angle on the right side of sunlight in YZ mounting plane,
τ is to put boundary and Y-axis angle on the left of gas light in YZ mounting plane.
Further, step S7 further comprises: S701: putting sunlight boundary curve according to right side and plane X=0 can
Sunlight and Y-axis angle σ in YZ mounting plane are acquired, maximum sun shield angle can be installed by monoscopic star sensor in YZ
It is directed toward and Y-axis angle in planeIt acquires, sun maximum shield angleS702: gas light is put according to left side
Boundary curve and plane X=0 can acquire gas light and Y-axis angle τ in YZ mounting plane, and gas light maximum shield angle can
It is directed toward in YZ mounting plane by monoscopic star sensor and Y-axis angleIt acquires, gas light maximum shield angle
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1 is that design method is directed toward in the satellite in Sun-synchronous orbit monoscopic star sensor installation of one embodiment of the invention
Flow chart；
Fig. 2 is the sunlight relative satellite body coordinate system schematic diagram of one embodiment of the invention；
Fig. 3 be 3 years of one embodiment of the invention in orbit during sunlight and satellite body coordinate system relational model
Schematic diagram；
Fig. 4 is the satellite of one embodiment of the invention without sunlight boundary curve under maneuvering condition and satellite body coordinate system
Relational graph；
Fig. 5 is the satellite of one embodiment of the invention without gas light boundary curve under maneuvering condition and satellite body coordinate system
Relational graph；
Fig. 6 be one embodiment of the invention satellite difference operating condition under sunlight, gas light boundary curve YZ plane throw
Shadow schematic diagram；
Fig. 7 be one embodiment of the invention satellite difference operating condition under sunlight, gas light boundary curve XZ plane throw
Shadow schematic diagram；
Fig. 8 is monoscopic star sensor different installations in satellite body coordinate system YZ plane of one embodiment of the invention
It is directed toward and maximum sunlight, gas light shield angle relation schematic diagram.
Specific embodiment
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Below with reference to attached
The embodiment of figure description is exemplary, and for explaining only the invention, and is not considered as limiting the invention.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
Limitation of the invention.In addition, term " first ", " second " are used for description purposes only, it is not understood to indicate or imply opposite
Importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
Referring to following description and drawings, it will be clear that these and other aspects of the embodiment of the present invention.In these descriptions
In attached drawing, some particular implementations in the embodiment of the present invention are specifically disclosed, to indicate to implement implementation of the invention
Some modes of the principle of example, but it is to be understood that the scope of embodiments of the invention is not limited.On the contrary, of the invention
Embodiment includes all changes, modification and the equivalent fallen within the scope of the spirit and intension of attached claims.
Satellite in Sun-synchronous orbit monoscopic star sensor installation according to an embodiment of the present invention is described below in conjunction with attached drawing
It is directed toward design method.
Referring to FIG. 1, design method is directed toward in a kind of satellite in Sun-synchronous orbit monoscopic star sensor installation, including following
Step:
S1: setting sun-synchronous orbit parameter, satellite parametric reduction, HPOP resistance model parameter in STK software.Of the invention
In one embodiment, T, in orbit period t when sun-synchronous orbit parameter includes height h, southbound node place.Satellite parametric reduction packet
Include satellite mass M, satellite volume V.HPOP (High precision orbit prediction) resistance mould in STK (Satellite Tool Kit) software
Shape parameter includes atmospheric drag Cd, solar light pressure Cr, area-to mass ratio of satellite A/M and telluric magnetic force Kp, wherein the area-to mass ratio of satellite A/M
For the ratio of 1/4 satellite table area S and mass M.
Specifically, consider that satellite is imaged over the ground, satellite orbital altitude h is arranged in suffered perturbation and resistance factor, the present embodiment
For 700km；Consider that earth observation is imaged simultaneously, T is to be illuminated by the light more complicated 10:30 when southbound node place is arranged in the present embodiment
Track；It is 3 years that t satellite period, which is arranged, in the present embodiment.
It is 20.5kg that satellite mass M, which is arranged, in the present embodiment, and satellite volume V is 324*360*400mm.
Atmospheric drag C is arranged in the present embodimentdIt is 2.2, solar light pressure CrIt is 1.0, telluric magnetic force KpIt is 3.0, according to satellite face matter
Than the ratio that A/M is 1/4 satellite table area S and mass M, area-to mass ratio of satellite A/M ≈ 0.01 can be calculated.
S2: carrying out HPOP emulation in STK software, sunlight and satellite body coordinate system during determining satellite in orbit
Three axial vector angles.In satellite body coordinate system, Z axis is directed toward the earth's core, and X-axis is satellite direction of advance, and Y-axis is true by the right-hand rule
It is fixed；α is sunlight and X-axis angle, and β is sunlight and Y-axis angle, and γ is sunlight and Z axis angle.
Specifically, as shown in Figure 2.According to step S1 parameter setting, the present embodiment obtains the in-orbit fortune of satellite by STK software
Sunlight and three axial vector angle of satellite body coordinate system between row 3 years, wherein sunlight and X axis vector angle cosine are maximum
Value αmaxIt is 0.9946, minimum value αminIt is -0.9946, therefore sunlight and X-axis angular range are 5.9620 °~174.0470 °；
Sunlight and Y-axis vector angle cosine maximum value βmaxIt is -0.0841, minimum value βminIt is -0.4537, therefore sunlight and Y
Axle clamp angular region is 94.8270 °~116.9830 °；Sunlight and Z axis are to vector angle cosine maximum value γmaxIt is 0.4376,
Minimum value γminIt is -0.9914, therefore sunlight and Y-axis angular range are 64.0470 °~172.4730 °.By each moment sun
Light vector direction is depicted in satellite body coordinate system to be come, as shown in figure 3, luminous point indicates that sunlight is sat relative to satellite body
Mark system origin comes light vector direction.
S3: setting earth radius Re, atmosphere layer height d, according to γatm=asin ((Re+ d)/h), calculate and determine gas light
With satellite body boundary angle γatm, i.e., with Z axis positive direction angle.
Specifically, since centrifugal force acts on, almost all gas is concentrated in 100 kilometers of altitude range from the ground,
Wherein 75% atmosphere is concentrated on again within the scope of ground to the troposphere of 10 kilometers of height.The present embodiment sets atmosphere layer height d
=100km, earth radius Re=6378km.According to relational expression γatm=asin ((Re+ d)/h), above-mentioned parameter is substituted into above formula meter
Calculation can obtain gas light and satellite body boundary angle (i.e. with Z axis positive direction angle) γatmIt is 66.24 °, considers semi-major axis variation,
The present embodiment is using 67 ° of (corresponding 659.44km) Redundancy Designs.
S4. according to step S2 Satellite in orbit during sunlight and three axial vector angle of satellite body coordinate system, really
Satellite is determined without sunlight relative satellite body coordinate system boundary math equation under maneuvering condition；Determine that satellite is inorganic according to step S3
Gas light relative satellite body coordinate system boundary math equation under dynamic state.
Specifically, under the inorganic dynamic working condition of satellite, sunlight absorbing boundary equation passes through sunlight in step S2 and satellite sheet
Each axle clamp angle extreme value of body coordinate system determines, is analyzed according to step S2, sunlight is in satellite body coordinate system absorbing boundary equation by two
Curve is constituted, respectively following formula, wherein z < 0.4376, θ1=94.8270 °, θ2=116.9830 °, as shown in Figure 4.
Since satellite body coordinate system Z axis is directed toward the earth's core always, satellite can lead to without gas light boundary under maneuvering condition
Multiple orbital attitudes gas light semi-cone angle θ is crossed to directly determine, gas light in the following formula of satellite body coordinate system absorbing boundary equation,
Middle θ=67 °, as shown in Figure 5.
S5: maximum lateral swinging angle, pitch angle under setting satellite maneuvering condition determine satellite not according to coordinate system spin matrix
With (left side pendulum, preceding faced upward, swung back right side pendulum) sunlight, gas light relative satellite body coordinate system boundary curve under maneuvering condition
Satellite body coordinate system is not by veiling glare influence area under math equation and various working conditions.
Specifically, the present embodiment defines satellite forward swing are as follows: satellite around body coordinate system around Y-axis from+X to-Z axis to deflection,
Maximum deflection angle is -30 °；It is put after satellite are as follows: satellite is around body coordinate system around Y-axis from+X to+Z axis to deflection, maximum deflection angle
It is 30 °.The present embodiment defines pendulum on the left of satellite: satellite is around body coordinate system around X-axis from-Y-direction-Z axis to deflection, maximum deflection angle
It is 30 °；Right side pendulum: satellite around body coordinate system around X-axis from-Y-direction+Z axis to deflection, maximum deflection angle is 30 °.
Satellite left side 30 ° of gas light boundary curve equations of pendulum are equivalent to gas light absorbing boundary equation (3) in step S4 and revolve around X-axis
Turn -30 °, after spin matrix converts, such as following formula:
30 ° of sunlight boundary curve equations of pendulum are equivalent in step S4 sunlight absorbing boundary equation (1), (2) around X on the left of satellite
Axis rotates -30 °, need to only analyze the influence of its left border curve (1), after spin matrix converts, such as following formula:
Satellite right side 30 ° of gas light boundary curve equations of pendulum are equivalent to gas light absorbing boundary equation (3) in step S4 and revolve around X-axis
Turn 30 °, after spin matrix converts, such as following formula:
30 ° of sunlight boundary curve equations of pendulum are equivalent in step S4 sunlight absorbing boundary equation (1), (2) around X on the right side of satellite
Axis rotates 30 °, need to only analyze the influence of its right side boundary curve (2), after spin matrix converts, such as following formula:
30 ° of gas light boundary curve equations of satellite forward swing are equivalent to gas light absorbing boundary equation (3) in step S4 and revolve around Y-axis
Turn -30 °, after spin matrix converts, such as following formula:
30 ° of sunlight boundary curve equations of satellite forward swing are equivalent in step S4 sunlight absorbing boundary equation (1), (2) around Y-axis
- 30 ° of rotation, the influence area of sunlight relative satellite body coordinate system is not required to analyze in gas light coverage area.
30 ° of gas light boundary curve equations are put after satellite to be equivalent to gas light absorbing boundary equation (3) in step S4 and rotate around Y-axis
30 °, after spin matrix converts, such as following formula:
30 ° of sunlight boundary curve equations are put after satellite is equivalent in step S4 sunlight absorbing boundary equation (1), (2) around Y-axis
- 30 ° of rotation, the influence area of sunlight relative satellite body coordinate system is not required to analyze in gas light coverage area.
The extraction and change of absorbing boundary equation according to the above-mentioned part step S4 and S5 to sunlight, gas light under various operating conditions
It changes, can obtain the region that satellite body coordinate system is not interfered by sunlight, gas light under various operating conditions, boundary curve is in satellite
Ontology YZ plane projection such as Fig. 6, it is known that interference-free light influence area is total to two parts, and angular range is respectively 57.8 ° and 26 °.
It is 15 ° that star sensor field angle, which is arranged, in the present embodiment, therefore 26 ° of ranges are unsatisfactory for star sensor installation minimal condition.Boundary is bent
Line is in XZ plane projection such as Fig. 7, it is known that interference-free region is by pendulum gas light boundary curve (6), satellite right side pendulum on the left of satellite
Gas light boundary curve (8) structure is put on front side of pendulum gas light boundary curve (9) and satellite on rear side of sunlight boundary curve (5), satellite
At.
S6. it determines and is directed toward range number under monoscopic star sensor mounting condition to avoid stray light star sensor from installing
Learn equation.
Specifically, under the various working conditions of satellite, the present embodiment monoscopic star sensor not by veiling glare (sunlight,
Gas light) influence best installation direction curve in satellite body coordinate system YZ plane.Gas light boundary is put on the left of simultaneous satellite
Equation (6), on the right side of satellite pendulum sunlight absorbing boundary equation (5) and plane X=0 can acquire Y partially-Z axis is directed toward to star sensor
Bounds: (- 0.905 < z < -0.122).Therefore, equation such as following formula is directed toward in monoscopic star sensor installation:
S7. determine that monoscopic star sensor maximum sunlight shield angle, gas light cover angular dependence, according to Baffle design
Principle judges to install whether section meets design requirement；If meeting design requirement, design terminates；If being unsatisfactory for design requirement, hold
Row step S5 resets maximum lateral swinging angle, pitch angle under satellite maneuvering condition, or use it can under Part load.
Specifically, putting sunlight boundary curve (5) and plane X=0 according to right side can acquire in YZ mounting plane too
Sunlight and Y-axis angle are 64.8 °, and maximum sun shield angle can be directed toward in YZ mounting plane by monoscopic star sensor and Y
Axial angleIt acquires, sun maximum shield angle
It is similar with sunlight maximum shield angle calculating, gas light boundary curve (6) are put according to left side and plane X=0 can
Acquiring gas light and Y-axis angle in YZ mounting plane is 7 °, and gas light maximum shield angle can be existed by monoscopic star sensor
It is directed toward and Y-axis angle in YZ mounting planeIt acquires, gas light maximum shield angleAccording to above-mentioned calculating,
Relationship such as Fig. 8 of hood maximum sun shield angle and maximum gas light shield angle.
Since sun light intensity is much higher than gas light, in star sensor Baffle design, sun shield angle need to be greater than ground vapour
Light shield angle, thus Dan Xingmin installed in YZ plane be directed toward Y partially-Z axis angle should be greater than -35 °, the present embodiment Xing Min half field-of-view
Angle is 7.5 °, and design gas light shield angle is not less than 10 °, as shown in Figure 8, Y partially-Z axis angle should be less than -20 °.Specific star is sensitive
Device mounting plane, which is directed toward, to be required to combine with star sensor Baffle design.If meeting hood size and shading performance design
It is required that design terminates；If being unsatisfactory for hood size and shading performance design requirement, step S5 is executed, suitably reduction subhost
Maximum lateral swinging angle, pitch angle under dynamic state, or use it can under Part load.
In addition, its of design method is directed toward in the satellite in Sun-synchronous orbit monoscopic star sensor installation of the embodiment of the present invention
It constitute and effect be all for a person skilled in the art it is known, in order to reduce redundancy, do not repeat them here.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " example ", " specifically show
The description of example " or " some examples " etc. means specific features, structure, material or spy described in conjunction with this embodiment or example
Point is included at least one embodiment or example of the invention.In the present specification, schematic expression of the above terms are not
Centainly refer to identical embodiment or example.Moreover, particular features, structures, materials, or characteristics described can be any
One or more embodiment or examples in can be combined in any suitable manner.
Although an embodiment of the present invention has been shown and described, it will be understood by those skilled in the art that: not
A variety of change, modification, replacement and modification can be carried out to these embodiments in the case where being detached from the principle of the present invention and objective, this
The range of invention is by claim and its equivalent limits.
Claims (7)
1. design method is directed toward in a kind of satellite in Sun-synchronous orbit monoscopic star sensor installation, which is characterized in that including following
Step:
S1: setting sun-synchronous orbit parameter, satellite parametric reduction, High precision orbit prediction HPOP resistance model parameter in STK software；
S2: carrying out HPOP emulation in STK software, sunlight and three axis of satellite body coordinate system during determining satellite in orbit
Vector angle, wherein in the satellite body coordinate system, Z axis is directed toward the earth's core, and X-axis is satellite direction of advance, and Y-axis is determined by the right hand
It then determines, α is sunlight and X-axis angle, and β is sunlight and Y-axis angle, and γ is sunlight and Z axis angle；
S3: definitely gas light and satellite body boundary angle are calculated according to earth radius, atmosphere height；
S4: according to the satellite in orbit during sunlight and three axial vector angle of satellite body coordinate system, determine described in defend
Star is under no maneuvering condition, sunlight relative satellite body coordinate system boundary math equation；According to the gas light and satellite sheet
Body boundary angle determine the satellite under no maneuvering condition, gas light relative satellite body coordinate system boundary math equation；
S5: maximum lateral swinging angle and pitch angle under setting satellite maneuvering condition determine that the satellite exists according to coordinate system spin matrix
Sunlight, gas light relative satellite body coordinate system boundary curve math equation and various operating condition items under different maneuvering conditions
Satellite body coordinate system is not by veiling glare influence area under part；
S6: according to satellite body coordinate system under various working conditions not by veiling glare influence area, determine that monoscopic star sensor is pacified
Range math equation is directed toward to avoid stray light star sensor from installing under the conditions of dress, wherein the star sensor installation refers to
Include: to range math equation
In formula, σ is to put boundary and Y-axis angle on the right side of sunlight in YZ mounting plane, and τ is the gas light in YZ mounting plane
Put boundary and Y-axis angle in left side；And
S7: sunlight boundary curve is put according to right side and left side pendulum gas light boundary curve determines monoscopic star sensor maximum too
Sunlight shield angle, gas light cover angular dependence, are judged to install whether section meets design requirement according to Baffle design principle；If
Meet design requirement, design terminates；If being unsatisfactory for design requirement, step S5 is executed, is reset maximum under satellite maneuvering condition
Lateral swinging angle, pitch angle, or use it can under Part load.
2. design method is directed toward in satellite in Sun-synchronous orbit monoscopic star sensor installation according to claim 1, special
Sign is, in step sl, T, in orbit period t when the sun-synchronous orbit parameter includes height h, southbound node place；
The satellite parametric reduction includes satellite mass M, satellite volume V；
HPOP resistance model parameter includes atmospheric drag C in the STK softwared, solar light pressure Cr, area-to mass ratio of satellite A/M and earth magnetism
Power Kp, wherein the area-to mass ratio of satellite A/M is the ratio of 1/4 satellite table area S and mass M.
3. design method is directed toward in satellite in Sun-synchronous orbit monoscopic star sensor installation according to claim 2, special
Sign is that step S3 further comprises:
Earth radius R is sete, atmosphere layer height d, according to γatm=asin ((Re+ d)/h), calculate and determine gas light and satellite sheet
Body boundary angle γatm。
4. design method, step are directed toward in satellite in Sun-synchronous orbit monoscopic star sensor installation according to claim 3
S4 further comprises: S401: under the inorganic dynamic working condition of satellite, sunlight absorbing boundary equation by sunlight in step S2 with
Each axle clamp angle extreme value of satellite body coordinate system such as following equation determines:
Wherein, θ1For the inclined Y-axis forward direction left margin of sunlight and Y-axis angle, θ2It is pressed from both sides for the inclined Y-axis forward direction right margin of sunlight and Y-axis
Angle；
S402: gas light boundary can be directly true by multiple orbital attitudes gas light semi-cone angle under no maneuvering condition for the satellite
Fixed, gas light is in the following formula of satellite body coordinate system absorbing boundary equation:
Wherein, θ is gas light semi-cone angle.
5. design method is directed toward in satellite in Sun-synchronous orbit monoscopic star sensor installation according to claim 4, special
Sign is, in step s 5, the maneuvering condition of the satellite includes left side pendulum, right side pendulum, preceding face upward and swing back.
6. design method is directed toward in satellite in Sun-synchronous orbit monoscopic star sensor installation according to claim 5, special
Sign is that step S6 further comprises:
S601: the best installation that monoscopic star sensor is not influenced by veiling glare is directed toward curve in satellite body coordinate system YZ plane
It is interior；
S602: pendulum gas light absorbing boundary equation, satellite right side pendulum sunlight absorbing boundary equation and plane X=0 are asked on the left of simultaneous satellite
It obtains-Z axis inclined in Y and is directed toward bounds to star sensor.
7. design method is directed toward in satellite in Sun-synchronous orbit monoscopic star sensor installation according to claim 6, special
Sign is that step S7 further comprises:
S701: sunlight and Y-axis in YZ mounting plane can be acquired by putting sunlight boundary curve and plane X=0 according to right side
To angle σ, maximum sun shield angle can be directed toward in YZ mounting plane and Y-axis angle by monoscopic star sensorIt acquires, too
Positive maximum shield angle
S702: gas light and Y-axis in YZ mounting plane can be acquired by putting gas light boundary curve and plane X=0 according to left side
To angle τ, gas light maximum shield angle can be directed toward in YZ mounting plane and Y-axis angle by monoscopic star sensorIt asks
, gas light maximum shield angle
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| CN107487460B (en) * | 2017-06-30 | 2020-07-14 | 上海卫星工程研究所 | Remote sensing satellite configuration method suitable for multiple descending intersection points |
| CN108225306B (en) * | 2017-12-28 | 2020-07-31 | 长光卫星技术有限公司 | Star sensor installation layout method based on remote sensing satellite staring attitude |
| CN107993281B (en) * | 2018-01-09 | 2021-03-05 | 北京航空航天大学 | Method for simulating optical characteristics of space target visible light |
| CN108681617B (en) * | 2018-03-29 | 2022-07-29 | 北京空间飞行器总体设计部 | Optimization design method for layout of spacecraft multi-star sensor |
| CN108680171A (en) * | 2018-05-24 | 2018-10-19 | 清华大学 | Acquisition methods and system are directed toward in a kind of installation of Direct to the sun satellite star sensor |
| CN109063259B (en) * | 2018-07-02 | 2023-03-31 | 上海卫星工程研究所 | Method for designing load sun shield of geostationary orbit large-caliber optical imaging satellite |
| CN109159922B (en) * | 2018-09-29 | 2020-06-16 | 上海微小卫星工程中心 | Use method of low-inclination satellite star sensor |
| CN109302256B (en) * | 2018-12-05 | 2020-03-24 | 上海航天控制技术研究所 | Star sensor time synchronization signal timing method and logic circuit |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101487699A (en) * | 2009-03-06 | 2009-07-22 | 清华大学 | High-precision APS solar sensor and its implementing method |
| CN103616028A (en) * | 2013-11-29 | 2014-03-05 | 哈尔滨工程大学 | Star light refraction satellite autonomous navigation method based on single star sensor |
| CN104406607A (en) * | 2014-11-21 | 2015-03-11 | 北京航空航天大学 | Multi-visual field composite optical sensor calibration device and method |
| CN105371870A (en) * | 2015-11-27 | 2016-03-02 | 北京空间飞行器总体设计部 | Star map data based method for measurement of in-orbit precision of star sensor |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101487699A (en) * | 2009-03-06 | 2009-07-22 | 清华大学 | High-precision APS solar sensor and its implementing method |
| CN103616028A (en) * | 2013-11-29 | 2014-03-05 | 哈尔滨工程大学 | Star light refraction satellite autonomous navigation method based on single star sensor |
| CN104406607A (en) * | 2014-11-21 | 2015-03-11 | 北京航空航天大学 | Multi-visual field composite optical sensor calibration device and method |
| CN105371870A (en) * | 2015-11-27 | 2016-03-02 | 北京空间飞行器总体设计部 | Star map data based method for measurement of in-orbit precision of star sensor |
Non-Patent Citations (1)
| Title |
|---|
| 多视场星敏感器结构布局优化;王真 等;《红外与激光工程》;20111231(第12期);第2469-2473页 |
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