CN111561925A - Method, device and equipment for determining in-out ground shadow area of space target - Google Patents
Method, device and equipment for determining in-out ground shadow area of space target Download PDFInfo
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Abstract
The invention relates to a method, a device and equipment for determining a region shadow area where a space target enters and exits, which are used for acquiring operation information of the space target; generating a first equivalent triangle consisting of the space target, the earth and the origin of the full-shadow cone angle and a second equivalent triangle consisting of the space target, the earth and the origin of the half-shadow cone angle according to the vector positions; calculating a first internal angle of which the vertex in the first equivalent triangle is the origin of the full-shadow cone angle, and calculating a second internal angle of which the vertex in the second equivalent triangle is the origin of the half-shadow cone angle; and determining the relation between the space target and the ground shadow area according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle and the full shadow cone angle. According to the technical scheme, the position relation between the space target and the ground shadow area is calculated on the basis of considering atmospheric refraction, so that the position relation between the space target and the ground shadow area is calculated more accurately in the process of forecasting the entrance and exit of the space target in the ground shadow area.
Description
Technical Field
The invention relates to the technical field of satellite positioning, in particular to a method, a device and equipment for determining a space target in and out of a ground shadow area.
Background
The method monitors the relation between the vector position of the space target such as the satellite and the ground shadow area, is beneficial to effectively controlling the space target by the ground and avoids the influence on the space task execution of the space target. However, the relationship between the vector position of the space target and the ground shadow area is generally pre-calculated by a traditional geometric relationship method, and the calculated position relationship has a certain error with the actual position relationship between the space target and the ground shadow area, so that the accuracy is low, and the control of the space target is adversely affected.
Disclosure of Invention
In view of the above, the present invention provides a method, an apparatus, and a device for determining an in-out ground shadow area of a space target, so as to overcome the problem that a position relationship obtained by performing pre-calculation by using a conventional geometric relationship method at present has a certain error with an actual position relationship between the space target and the ground shadow area, and the accuracy is low, thereby adversely affecting the control of the space target.
In order to achieve the purpose, the invention adopts the following technical scheme:
a method for determining an in-and-out-of-ground shadow area of a space target comprises the following steps:
acquiring operation information of a space target, wherein the operation information comprises a vector position of the space target and a deflection angle which takes the earth as an origin and consists of the space target, the earth and a sun core;
generating a first equivalent triangle consisting of the space target, the earth and the origin of the full-shadow cone angle and a second equivalent triangle consisting of the space target, the earth and the origin of the half-shadow cone angle according to the vector positions; the total shadow cone angle is an equivalent angle formed by the terrestrial solar circumscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere, and the semi-shadow cone angle is an equivalent angle formed by the terrestrial solar inscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere;
calculating a first internal angle of which the vertex in the first equivalent triangle is the origin of the full shadow cone angle, and calculating a second internal angle of which the vertex in the second equivalent triangle is the origin of the half shadow cone angle;
and determining the position relation between the space target and the ground shadow area according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle and the full shadow cone angle.
Further, the above method for determining a ground shadow area of a spatial target, where determining a positional relationship between the spatial target and the ground shadow area according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle, and the full shadow cone angle includes:
judging whether the deflection angle is less than or equal to 90 degrees;
if the deflection angle is smaller than or equal to 90 degrees, determining that the current position of the space target is a full-sunlight area;
if the deflection angle is larger than 90 degrees, further judging whether the second inner angle is larger than the half-shadow cone angle;
if the second internal angle is larger than the half-shadow cone angle, determining that the current position of the space target is a full-sunlight area;
if the second inner angle is smaller than or equal to the half-shadow cone angle, further judging whether the first inner angle is larger than the full-shadow cone angle;
if the first internal angle is larger than the full-shadow cone angle, determining that the current position of the space target is a penumbra area;
and if the first internal angle is smaller than or equal to the full-shadow cone angle, determining that the current position of the space target is a full-shadow region.
Further, in the above method for determining the entrance and exit of the space target into and out of the ground shadow region, the angle of the total shadow cone angle is the sum of the pseudo total shadow cone angle and the refraction deflection angle of the atmosphere;
the angle of the half-shadow cone angle is the difference between the pseudo-half-shadow cone angle and the refraction deflection angle of the atmosphere;
the pseudo-total shadow cone angle is an equivalent angle formed by the sunlight circumscribed in a time period and the central axis of the earth day without overlying atmospheric refraction, and the pseudo-half shadow cone angle is an equivalent angle formed by the sunlight inscribed in a time period and the central axis of the earth day without overlying atmospheric refraction.
Further, the method for determining an in-out ground shadow region of a spatial target described above, where the calculating a first internal angle whose vertex is the origin of the full shadow cone angle in the first equivalent triangle, includes:
in the first equivalent triangle, calculating a first internal angle based on a sine theorem according to the first distance between the origin of the full shadow cone angle and the center of the earth, the deflection angle and the second distance between the space target and the center of the earth;
the calculating a second internal angle of which the vertex is the origin of the half-shadow cone angle in the second equivalent triangle comprises:
and in the second equivalent triangle, calculating the second internal angle based on a sine theorem according to the penumbra angle origin, the third distance of the earth center, the deflection angle and the second distance.
Further, in the method for determining an in-out ground shadow area of a spatial target described above, the calculating of the first distance includes:
determining an equivalent right-angle triangle formed by the origin of the total shadow cone angle, the center of the earth sphere, the earth sun circumscribed sunlight and the earth tangent point;
and determining a first distance between the origin of the all-shadow cone angle and the center of the earth based on a trigonometric function theorem according to the all-shadow cone angle and the radius of the earth.
Further, in the method for determining an in-out ground shadow area of a space target described above, the calculating of the third distance includes:
determining an equivalent right-angle triangle formed by the half-shadow cone angle origin, the earth center and the earth tangent point;
and determining a third distance between the origin of the half-shadow cone angle and the center of the earth sphere based on trigonometric function theorem according to the half-shadow cone angle and the radius of the earth.
The invention also provides a device for determining the in-out ground shadow area of the space target, which comprises:
the system comprises an acquisition module, a processing module and a display module, wherein the acquisition module is used for acquiring operation information of a space target, and the operation information comprises a vector position of the space target and a deflection angle which takes the earth as an origin and consists of the space target, the earth and a solar core;
the generating module is used for generating a first equivalent triangle consisting of the space target, the earth and the origin of the full shadow cone angle and generating a second equivalent triangle consisting of the space target, the earth and the origin of the half shadow cone angle according to the vector position; the total shadow cone angle is an equivalent angle formed by the terrestrial solar circumscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere, and the semi-shadow cone angle is an equivalent angle formed by the terrestrial solar inscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere;
the calculation module is used for calculating a first internal angle of which the vertex in the first equivalent triangle is the origin of the full shadow cone angle and calculating a second internal angle of which the vertex in the second equivalent triangle is the origin of the half shadow cone angle;
and the determining module is used for determining the position relation between the space target and the ground shadow area according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle and the full shadow cone angle.
Further, the determining device of the space target in-out shadow area is specifically configured to determine whether the deflection angle is less than or equal to 90 degrees;
if the deflection angle is smaller than or equal to 90 degrees, determining that the current position of the space target is a full-sunlight area;
if the deflection angle is larger than 90 degrees, further judging whether the second inner angle is larger than the half-shadow cone angle;
if the second internal angle is larger than the half-shadow cone angle, determining that the current position of the space target is a full-sunlight area;
if the second inner angle is smaller than or equal to the half-shadow cone angle, further judging whether the first inner angle is larger than the full-shadow cone angle;
if the first internal angle is larger than the full-shadow cone angle, determining that the current position of the space target is a penumbra area;
and if the first internal angle is smaller than or equal to the full-shadow cone angle, determining that the current position of the space target is a full-shadow region.
Further, the device for determining the in-out ground shadow area of the spatial target described above, the calculation module is specifically configured to calculate, in the first equivalent triangle, the first internal angle based on a sine theorem according to the first distance between the origin of the full shadow cone angle and the center of the earth, the deflection angle, and the second distance between the spatial target and the center of the earth;
the calculation module is specifically further configured to calculate the second internal angle in the second equivalent triangle according to a third distance between the origin of the half-shadow cone angle and the center of the earth sphere, the deflection angle, and the second distance based on a sine theorem.
The invention also provides a device for determining the in-and-out-of-ground shadow area of the space target, which comprises a processor and a memory, wherein the processor is connected with the memory:
the processor is used for calling and executing the program stored in the memory;
the memory is used for storing the program, and the program is at least used for executing the method for determining the access and destination shadow area of the space target in any one of the above.
According to the method, the device and the equipment for determining the in-out ground shadow area of the space target, disclosed by the invention, a first equivalent triangle consisting of the space target, the earth and a full shadow cone angle origin is generated by acquiring the vector position of the space target, and a second equivalent triangle consisting of the space target, the earth and a half shadow cone angle origin is generated; the total shadow cone angle is an equivalent angle formed by the terrestrial solar circumscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere, and the half shadow cone angle is an equivalent angle formed by the terrestrial solar inscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere; calculating a first internal angle of which the vertex in the first equivalent triangle is the origin of the full-shadow cone angle, and calculating a second internal angle of which the vertex in the second equivalent triangle is the origin of the half-shadow cone angle; and determining the position relation between the space target and the ground shadow region according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle and the full shadow cone angle. According to the technical scheme, the position relation between the space target and the ground shadow area is calculated on the basis of considering atmospheric refraction, so that the position relation between the space target and the ground shadow area is calculated more accurately in the process of forecasting the entrance and exit of the space target in the ground shadow area.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a flow chart provided by an embodiment of a method for determining an in-out mapping area of a space object according to the present invention;
FIG. 2 is a schematic diagram of the division of the illumination area without considering atmospheric refraction;
FIG. 3 is a schematic view of light ray deflection under the influence of the atmosphere;
FIG. 4 is a schematic diagram of off-sun tangent deflection under the influence of atmospheric air;
FIG. 5 is a schematic view of the intraday tangent deflection under the influence of the atmosphere;
FIG. 6 is a schematic diagram of the relationship of the spatial target region under the influence of the atmosphere;
FIG. 7 is a schematic structural diagram of an apparatus for determining an in-out shadow area of a space object according to an embodiment of the present invention;
fig. 8 is a schematic structural diagram of an embodiment of the apparatus for determining an in-out ground shadow area of a space object according to the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.
Fig. 1 is a flowchart of a method for determining an in-out mapping area of a space object according to an embodiment of the present invention. Referring to fig. 1, the present embodiment may include the following steps:
s101, acquiring operation information of a space target;
in this embodiment, the operation information of the space target needs to be acquired. Wherein the spatial target is typically an earth satellite. In this embodiment, the operation information includes a vector position of the space target, and a deflection angle formed by the space target, the earth, and the sun core with the earth as an origin.
S102, generating a first equivalent triangle consisting of a space target, the earth and a full-shadow cone angle origin and a second equivalent triangle consisting of the space target, the earth and a half-shadow cone angle origin according to the vector position in the operation information;
in this embodiment, a first equivalent triangle consisting of the spatial target, the earth, and the origin of the full-shadow cone angle may be generated, and a second equivalent triangle consisting of the spatial target, the earth, and the origin of the half-shadow cone angle may be generated, based on the vector positions. The total shadow cone angle is an equivalent angle formed by the terrestrial solar circumscribed sunlight and the central axis of the terrestrial sun after being refracted by the atmosphere, and the half shadow cone angle is an equivalent angle formed by the terrestrial solar inscribed sunlight and the central axis of the terrestrial sun after being refracted by the atmosphere.
Specifically, without considering the influence of atmospheric refraction on solar rays, due to the shielding of the earth on sunlight, different irradiation areas, namely a full-shadow area, a half-shadow area and a sunshine area, are formed on the back surface of the earth. FIG. 2 is a schematic diagram of the division of the irradiation region when atmospheric refraction is not taken into consideration. Referring to fig. 2, the area a is a full-sunlight area, i.e., an area irradiated by all sunlight; the area b is a full shadow area, namely an area where all the sun cannot be seen due to earth shielding; the area c is a penumbra area, i.e. an area where only part of the sun can be seen due to earth obstruction. Wherein, the ray X is the earth-sun internal tangent and the ray Y is the earth-sun external tangent.
As shown in fig. 2, when atmospheric refraction is not considered, the intersection point P of the terrestrial inner tangent and the terrestrial central axis is a pseudo-penumbra cone angle, and the embodiment records half of the pseudo-penumbra cone angle as β; when atmospheric refraction is not considered, the intersection point U of the extraterrestrial tangent and the central axis of the earth-sun is a pseudo-hologram cone angle, and the embodiment represents half of the pseudo-hologram cone angle as α.
Tangent point T of tangent line and sun in the earth and sun2The tangent point T between the earth's inner tangent line and the earth1And T1In a "composed equivalent right triangle", it can be determined that the tangent of β is T according to a trigonometric function2T1' and T1T1Length ratio. T is2T1The length of "being the sum of the radii of the earth and the sun, T1T1The length of the ' is the distance between the earth ' S centre O and the sun ' S centre S in this example 6370 km for the earth ' S radius and 6.96 × 10 for the sun ' S radius5Kilometer, distance between the earth 'S center of sphere O and the sun' S center S1.4959787 × 108Kilometers, then β may be determined to be 0.2684 points.
Tangent point T between terrestrial and solar2The tangent point T between the earth and the earth3And T3In a "composed equivalent right triangle", it can be determined that the tangent of α is T according to a trigonometric function2T3' and T3T3Length ratio. T is2T3The length of "is the difference between the radii of the sun and the earth, T3T3The length of "is the distance between the earth 'S center of sphere O and the sun' S center of sphere S similarly α can be determined to be 0.2641 points.
Wherein, T1' is T1At S and T2Projection on the straight line, T3' is T3At S and T2The projection on the straight line.
In fact, the earth is wrapped by the atmosphere, light rays entering and exiting the atmosphere change tracks under the influence of refraction of the atmosphere, and the earth-sun inner tangent and the earth-sun outer tangent do not penetrate through the atmosphere as shown in fig. 2 and are bound to be deflected under the influence of the refraction of the atmosphere.
FIG. 3 is a schematic view of light deflection under the influence of the atmosphere, referring to FIG. 3, the incident sunlight is deflected due to atmospheric refraction; meanwhile, after the solar rays pass through the earth surface horizontally, based on the symmetry of atmospheric distribution and the principle that the light path is reversible, the rays are bent downwards in a symmetrical refraction mode to be emitted out of the atmosphere, and the emitted sunlight is deflected, so that in the whole process of entering and exiting the atmosphere, the deflection angle psi between the incident sunlight and the emitted sunlight is 2, and is 29.5 minutes through continuous integral calculation of a refraction law.
Fig. 4 is a schematic diagram of the extraterrestrial ray deflection under the influence of the atmosphere. Referring to fig. 4, in fig. 4, a light ray 1 is a path of an earth-sun external tangent line when atmospheric refraction is not considered, an intersection point with an earth-sun central axis is U, and when the light ray is incident on the earth surface, atmospheric refraction refracts an earth-sun external tangent line by a deflection angle in consideration of atmospheric refraction, the light ray 1 is refracted by an atmosphere and then becomes a light ray 2, a focus with the earth-sun central axis is U', the light ray 2 exits the atmosphere again, the light ray is deflected and turned into a light ray 3 after atmospheric refraction, and an intersection point with the earth-sun central axis is U ". After two refractions, an angle generated by intersection of the terrestrial-solar external tangent and the terrestrial-solar central axis is a total-image cone angle, U "is a total-image cone angle origin, in this embodiment, half of the total-image cone angle is denoted as α", and α ═ α + 2. In a right triangle formed by the earth center O, the earth sun-sun circumscribed sunlight, the earth tangent point C and the origin U 'of the full shadow cone angle, the origin U' of the full shadow cone angle and the first distance n of the earth center O can be calculated according to the trigonometric function theorem.
The calculation formula is as follows:
wherein r is0A second distance of the spatial target to the center of the earth's sphere.
Fig. 5 is a schematic view of the intraday tangent deflection under the influence of the atmosphere. Referring to fig. 5, under the influence of atmospheric refraction, when a terrestrial-solar internal tangent enters the atmosphere, the refraction angle is such that, after the atmospheric refraction, incident sunlight glazes onto a point C on the surface of the earth, and after the sunlight exits from the point C, the refraction angle is also such that the sunlight exits into the space according to the symmetry of the earth and the light reversibility principle, so that after two refractions, the refraction angle between the exiting light and the incident light is 2. As shown in fig. 4, if the angle is larger than β, the intersection point of the terrestrial tangent line and the central axis of the terrestrial day changes from the original point P to the point P' on the other side of the earth after one atmospheric refraction, and the intersection point of the terrestrial tangent line and the central axis of the terrestrial day changes from the original point P to the point P ″ on the other side of the earth after two atmospheric refractions. After two refractions, the angle generated by the intersection of the earth-sun internal tangent and the earth-sun central axis is the half-shadow cone angle, P "is the origin of the half-shadow cone angle, and in this embodiment, half of the half-shadow cone angle is denoted as β", and β ═ β -2. In a right triangle formed by the sunlight, the earth tangent point C, the earth center O and the origin P ' of the half-shadow cone angle in the terrestrial day, the radius and the beta ' of the earth are known, and then the length m of the third distance between the origin P ' of the half-shadow cone angle and the earth center O can be calculated according to the trigonometric function theorem. The calculation formula is as follows:
s103, calculating a first internal angle of which the vertex in the first equivalent triangle is the origin of the full-shadow cone angle, and calculating a second internal angle of which the vertex in the second equivalent triangle is the origin of the half-shadow cone angle;
FIG. 6 is a schematic diagram of the relationship of the spatial target region under the influence of the atmosphere. Referring to FIG. 6, let T be the space target and the second distance of the space target from the center O point of the earth be the vector
The deflection angle composed of the space target T, the earth sphere center O and the sun core S is theta, then the first equivalent triangle is a triangle composed of the space target T, the origin U' of the full shadow cone angle and the earth sphere center O, and the first internal angle is marked as omegau。
From the interior angle and theorem of the triangle, the angle T1 corresponding to the side U ″, O, θ - ω, can be obtainedu；
According to the sine theorem:
wherein, | TO | is a vector
If | U "O | is n, the formula can be solved:
similarly, in the second equivalent triangle, the second interior angle ω may be determined according to the sine theoremp：
S104, determining the position relation between the space target and the ground shadow region according to the deflection angle, the first inner angle, the second inner angle, the half shadow cone angle and the full shadow cone angle.
In this embodiment, it may be determined whether the deflection angle is less than or equal to 90 degrees, and if the deflection angle is less than or equal to 90 degrees, it is determined that the current position of the spatial target is the full sunlight area; if the deflection angle is larger than 90 degrees, whether the second inner angle is larger than the half-shadow cone angle is further judged. If the second internal angle is larger than the half-shadow cone angle, determining that the current position of the space target is a full-sunlight area; if the second internal angle is smaller than or equal to the half-shadow cone angle, further judging whether the first internal angle is larger than the full-shadow cone angle, if the first internal angle is larger than the full-shadow cone angle, determining that the current position of the space target is a half-shadow area, and if the first internal angle is smaller than or equal to the full-shadow cone angle, determining that the current position of the space target is a full-shadow area.
In particular, it may be based on θ, α ", β", ωuAnd ωpThe size of (d) determines the position of the spatial target. For example:
if theta is less than or equal to pi/2, the space target is on the right side relative to the earth, and at the moment, the space target is always in the full-sunlight area;
if theta is greater than pi/2, the space target is on the left side relative to the earth, and at the moment, whether the target is in the penumbra area needs to be further judged:
if, theta>Pi/2, and, omegap>β', the space object is outside the penumbra area, and the object is fully illuminated by the sun;
if, theta>Pi/2, and, omegapβ', the spatial target may be in the penumbra region or the diatumbra region;
after further determination, if ω isu>α', the object is within the penumbra;
after further determination, if ω isuα', the target is within the full shadow region.
In the embodiment, a comparative analysis method is adopted for algorithm verification, namely, the time of the target entering and exiting the shadow area is forecasted and compared with the time of the target entering and exiting the shadow area actually observed under the conditions of not considering atmospheric refraction and considering atmospheric refraction influence.
The data is divided into three major parts, wherein firstly, the influence of direct air is not considered, the latest ephemeris data is utilized to theoretically calculate the time point of the space target relative to the in-and-out shadow area of the observation station, and secondly, the scheme of the embodiment is adopted to theoretically calculate the time point of the space target relative to the in-and-out shadow area of the observation station; thirdly, the system actually tracks the time point of the photoelectric video data target in and out of the ground shadow area obtained by the target, and the specific point is shown in table 1.
TABLE 1 Observation System target in and out of the ground shadow area time point
Description of the symbols:
U-P: representing the time point when the target crosses the terrain area and the semi-terrain area;
P-L: representing points in time when the target crosses the full-sun and half-terrestrial shaded areas;
the method comprises the following steps: calculating the time point when the target enters and exits the ground shadow area by adopting the scheme of the embodiment;
secondly, the step of: calculating the time points of the target entering and exiting the ground shadow region by using an ephemeris theory without considering the influence of atmospheric refraction;
③: the influence of atmospheric refraction is not considered, and the difference value between the time point when the target enters and exits the ground shadow area and the actual observation data is calculated by using an ephemeris theory;
fourthly, the method comprises the following steps: the difference value between the time point when the target enters and exits the ground shadow area and the actual observation data is calculated by adopting the scheme of the embodiment.
By analyzing the table 1, it can be known that, in the satellite observation transit prediction calculation, the difference value between the theoretical calculation target and the actual observation data is about 20 seconds without considering atmospheric refraction, and the error is large, and the difference value between the time point when the target enters and exits the ground shadow area and the actual observation data is calculated within 1 second by adopting the scheme of the embodiment, so that the position relation between the space target and the ground shadow area is calculated more accurately.
The method for determining the entrance and exit of the space target into and out of the ground shadow area of the embodiment acquires the operation information of the space target; generating a first equivalent triangle consisting of the space target, the earth and the origin of the full-shadow cone angle and a second equivalent triangle consisting of the space target, the earth and the origin of the half-shadow cone angle according to the vector positions; calculating a first internal angle of which the vertex in the first equivalent triangle is the origin of the full-shadow cone angle, and calculating a second internal angle of which the vertex in the second equivalent triangle is the origin of the half-shadow cone angle; and determining the relation between the space target and the ground shadow area according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle and the full shadow cone angle. According to the technical scheme, the position relation between the space target and the ground shadow area is calculated on the basis of considering atmospheric refraction, so that the position relation between the space target and the ground shadow area is calculated more accurately in the process of forecasting the entrance and exit of the space target in the ground shadow area.
The invention also provides a device for determining the in-out ground shadow area of the space target, which is used for realizing the embodiment of the method.
Fig. 7 is a schematic structural diagram of an apparatus for determining an in-out area of a space object according to an embodiment of the present invention, referring to fig. 7, the apparatus for determining an in-out area of a space object according to the embodiment includes:
the acquisition module 11 is configured to acquire operation information of the space target, where the operation information includes a vector position of the space target and a deflection angle formed by the space target, the earth, and a sun core, and using the earth as an origin;
the generating module 12 is used for generating a first equivalent triangle consisting of the space target, the earth and the origin of the full shadow cone angle and generating a second equivalent triangle consisting of the space target, the earth and the origin of the half shadow cone angle according to the vector position; the total shadow cone angle is an equivalent angle formed by the terrestrial solar circumscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere, and the half shadow cone angle is an equivalent angle formed by the terrestrial solar inscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere;
the calculation module 13 is configured to calculate a first internal angle of which a vertex in the first equivalent triangle is a full shadow cone angle origin, and calculate a second internal angle of which a vertex in the second equivalent triangle is a half shadow cone angle origin;
and the determining module 14 is configured to determine a position relationship between the space target and the ground shadow region according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle and the full shadow cone angle.
Further, the determining module of this embodiment is specifically configured to determine whether the deflection angle is less than or equal to 90 degrees; if the deflection angle is smaller than or equal to 90 degrees, determining the current position of the space target to be a full-sunlight area; if the deflection angle is larger than 90 degrees, further judging whether the second internal angle is larger than the half-shadow cone angle; if the second internal angle is larger than the half-shadow cone angle, determining that the current position of the space target is a full-sunlight area; if the second inner angle is smaller than or equal to the half-shadow cone angle, further judging whether the first inner angle is larger than the full-shadow cone angle; if the first internal angle is larger than the full-shadow cone angle, determining the current position of the space target as a penumbra area; and if the first internal angle is smaller than or equal to the full-shadow cone angle, determining the current position of the space target as a full-shadow area.
Furthermore, the angle of the total shadow cone angle is the sum of the pseudo total shadow cone angle and the atmospheric refraction deflection angle;
the angle of the half-shadow cone angle is the difference between the pseudo-half-shadow cone angle and the refraction deflection angle of the atmosphere;
the pseudo-ghost cone angle is an equivalent angle formed by the sunlight circumscribed in a day and the central axis of the earth day when atmospheric refraction is not superposed, and the pseudo-ghost cone angle is an equivalent angle formed by the sunlight inscribed in a day and the central axis of the earth day when atmospheric refraction is not superposed.
Further, the device for determining the in-out ground shadow area of the spatial target of this embodiment, the calculating module 13, is specifically configured to calculate, in the first equivalent triangle, a first internal angle based on the sine theorem according to the first distance between the origin of the cone angle of the full shadow and the center of the earth, the deflection angle, and the second distance between the spatial target and the center of the earth; and in the second equivalent triangle, calculating a second internal angle based on the sine theorem according to the origin of the half-shadow cone angle, the third distance of the earth center of sphere, the deflection angle and the second distance.
Further, the device for determining the entrance and exit of the space target into and out of the earth shadow area, the calculation module 13, is specifically further configured to determine an equivalent right triangle formed by the origin of the full shadow cone angle, the center of the earth sphere, the sunday circumscribed sunlight and the earth tangent point;
and determining a first distance between the origin of the all-shadow cone angle and the center of the earth sphere based on the trigonometric function theorem according to the all-shadow cone angle and the radius of the earth.
Further, the device for determining the entrance and exit of the space target into and out of the earth shadow area, the calculation module 13, is specifically further configured to determine an equivalent right triangle formed by the half shadow cone angle origin, the earth center and the earth tangent point;
and determining a third distance between the origin of the half-shadow cone angle and the center of the earth sphere based on the trigonometric function theorem according to the half-shadow cone angle and the radius of the earth.
With regard to the apparatus in the above-described embodiment, the specific manner in which each module performs the operation has been described in detail in the embodiment related to the method, and will not be elaborated here.
The invention also provides a set of equipment for determining the in-and-out-of-ground shadow area of the space target, which is used for realizing the embodiment of the method. Fig. 8 is a schematic structural diagram of an apparatus for determining an in-out area of a space object according to an embodiment of the present invention, referring to fig. 8, the apparatus for determining an in-out area of a space object according to the embodiment includes a processor 21 and a memory 22, the processor 21 is connected to the memory 22:
the processor 21 is configured to call and execute a program stored in the memory 22;
a memory 22 for storing the program, the program at least being used for executing the method for determining the in-and-out-of-ground shadow area of the space target described in the above embodiment.
It is understood that the same or similar parts in the above embodiments may be mutually referred to, and the same or similar parts in other embodiments may be referred to for the content which is not described in detail in some embodiments.
It should be noted that the terms "first," "second," and the like in the description of the present invention are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Further, in the description of the present invention, the meaning of "a plurality" means at least two unless otherwise specified.
Any process or method descriptions in flow charts or otherwise described herein may be understood as representing modules, segments, or portions of code which include one or more executable instructions for implementing specific logical functions or steps of the process, and alternate implementations are included within the scope of the preferred embodiment of the present invention in which functions may be executed out of order from that shown or discussed, including substantially concurrently or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art of the present invention.
It should be understood that portions of the present invention may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, the various steps or methods may be implemented in software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, any one or combination of the following techniques, which are known in the art, may be used: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application specific integrated circuit having an appropriate combinational logic gate circuit, a Programmable Gate Array (PGA), a Field Programmable Gate Array (FPGA), or the like.
It will be understood by those skilled in the art that all or part of the steps carried by the method for implementing the above embodiments may be implemented by hardware related to instructions of a program, which may be stored in a computer readable storage medium, and when the program is executed, the program includes one or a combination of the steps of the method embodiments.
In addition, functional units in the embodiments of the present invention may be integrated into one processing module, or each unit may exist alone physically, or two or more units are integrated into one module. The integrated module can be realized in a hardware mode, and can also be realized in a software functional module mode. The integrated module, if implemented in the form of a software functional module and sold or used as a stand-alone product, may also be stored in a computer readable storage medium.
The storage medium mentioned above may be a read-only memory, a magnetic or optical disk, etc.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. A method for determining an in-out mapping area for a space object, comprising:
acquiring operation information of a space target, wherein the operation information comprises a vector position of the space target and a deflection angle which takes the earth as an origin and consists of the space target, the earth and a sun core;
generating a first equivalent triangle consisting of the space target, the earth and the origin of the full-shadow cone angle and a second equivalent triangle consisting of the space target, the earth and the origin of the half-shadow cone angle according to the vector positions; the total shadow cone angle is an equivalent angle formed by the terrestrial solar circumscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere, and the semi-shadow cone angle is an equivalent angle formed by the terrestrial solar inscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere;
calculating a first internal angle of which the vertex in the first equivalent triangle is the origin of the full shadow cone angle, and calculating a second internal angle of which the vertex in the second equivalent triangle is the origin of the half shadow cone angle;
and determining the position relation between the space target and the ground shadow area according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle and the full shadow cone angle.
2. The method for determining the in-and-out-of-ground-shadow region of the spatial target according to claim 1, wherein the determining the position relationship between the spatial target and the ground-shadow region according to the deflection angle, the first internal angle, the second internal angle, the half-shadow cone angle and the full-shadow cone angle comprises:
judging whether the deflection angle is less than or equal to 90 degrees;
if the deflection angle is smaller than or equal to 90 degrees, determining that the current position of the space target is a full-sunlight area;
if the deflection angle is larger than 90 degrees, further judging whether the second inner angle is larger than the half-shadow cone angle;
if the second internal angle is larger than the half-shadow cone angle, determining that the current position of the space target is a full-sunlight area;
if the second inner angle is smaller than or equal to the half-shadow cone angle, further judging whether the first inner angle is larger than the full-shadow cone angle;
if the first internal angle is larger than the full-shadow cone angle, determining that the current position of the space target is a penumbra area;
and if the first internal angle is smaller than or equal to the full-shadow cone angle, determining that the current position of the space target is a full-shadow region.
3. The method of claim 1, wherein the angle of the global cone angle is the sum of a pseudo-global cone angle and an atmospheric refraction deflection angle;
the angle of the half-shadow cone angle is the difference between the pseudo-half-shadow cone angle and the refraction deflection angle of the atmosphere;
the pseudo-total shadow cone angle is an equivalent angle formed by the sunlight circumscribed in a time period and the central axis of the earth day without overlying atmospheric refraction, and the pseudo-half shadow cone angle is an equivalent angle formed by the sunlight inscribed in a time period and the central axis of the earth day without overlying atmospheric refraction.
4. The method for determining an in-and-out-of-space object mapping region according to claim 1, wherein said calculating a first internal angle with a vertex of the origin of the full-shadow cone angle in the first equivalent triangle comprises:
in the first equivalent triangle, calculating a first internal angle based on a sine theorem according to the first distance between the origin of the full shadow cone angle and the center of the earth, the deflection angle and the second distance between the space target and the center of the earth;
the calculating a second internal angle of which the vertex is the origin of the half-shadow cone angle in the second equivalent triangle comprises:
and in the second equivalent triangle, calculating the second internal angle based on a sine theorem according to the penumbra angle origin, the third distance of the earth center, the deflection angle and the second distance.
5. The method of claim 4, wherein the calculating of the first distance comprises:
determining an equivalent right-angle triangle formed by the origin of the total shadow cone angle, the center of the earth sphere, the earth sun circumscribed sunlight and the earth tangent point;
and determining a first distance between the origin of the all-shadow cone angle and the center of the earth based on a trigonometric function theorem according to the all-shadow cone angle and the radius of the earth.
6. The method of claim 4, wherein the third distance is calculated by:
determining an equivalent right-angle triangle formed by the half-shadow cone angle origin, the earth center and the earth tangent point;
and determining a third distance between the origin of the half-shadow cone angle and the center of the earth sphere based on trigonometric function theorem according to the half-shadow cone angle and the radius of the earth.
7. An apparatus for determining an in-out-of-ground shadowed area of a spatial object, comprising:
the system comprises an acquisition module, a processing module and a display module, wherein the acquisition module is used for acquiring operation information of a space target, and the operation information comprises a vector position of the space target and a deflection angle which takes the earth as an origin and consists of the space target, the earth and a solar core;
the generating module is used for generating a first equivalent triangle consisting of the space target, the earth and the origin of the full shadow cone angle and generating a second equivalent triangle consisting of the space target, the earth and the origin of the half shadow cone angle according to the vector position; the total shadow cone angle is an equivalent angle formed by the terrestrial solar circumscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere, and the semi-shadow cone angle is an equivalent angle formed by the terrestrial solar inscribed sunlight and the central axis of the terrestrial solar after being refracted by the atmosphere;
the calculation module is used for calculating a first internal angle of which the vertex in the first equivalent triangle is the origin of the full shadow cone angle and calculating a second internal angle of which the vertex in the second equivalent triangle is the origin of the half shadow cone angle;
and the determining module is used for determining the position relation between the space target and the ground shadow area according to the deflection angle, the first internal angle, the second internal angle, the half shadow cone angle and the full shadow cone angle.
8. The apparatus according to claim 7, wherein the determining module is specifically configured to determine whether the deflection angle is smaller than or equal to 90 degrees;
if the deflection angle is smaller than or equal to 90 degrees, determining that the current position of the space target is a full-sunlight area;
if the deflection angle is larger than 90 degrees, further judging whether the second inner angle is larger than the half-shadow cone angle;
if the second internal angle is larger than the half-shadow cone angle, determining that the current position of the space target is a full-sunlight area;
if the second inner angle is smaller than or equal to the half-shadow cone angle, further judging whether the first inner angle is larger than the full-shadow cone angle;
if the first internal angle is larger than the full-shadow cone angle, determining that the current position of the space target is a penumbra area;
and if the first internal angle is smaller than or equal to the full-shadow cone angle, determining that the current position of the space target is a full-shadow region.
9. The apparatus for determining an in-out-of-ground shadow of a spatial target according to claim 7, wherein the computing module is specifically configured to compute the first interior angle based on a sine theorem in the first equivalent triangle according to the first distance between the origin of the full shadow cone angle and the center of the earth, the deflection angle, and the second distance between the spatial target and the center of the earth;
the calculation module is specifically further configured to calculate the second internal angle in the second equivalent triangle according to a third distance between the origin of the half-shadow cone angle and the center of the earth sphere, the deflection angle, and the second distance based on a sine theorem.
10. A device for determining the in-out-of-ground shadow area of a spatial object, comprising a processor and a memory, the processor being coupled to the memory:
the processor is used for calling and executing the program stored in the memory;
the memory for storing the program for performing at least the method of determining in and out of a shadowed area of a spatial object as claimed in any one of claims 1 to 6.
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