CN116946396A - Continuous light supplementing device and continuous light supplementing method for designated area of lunar surface - Google Patents
Continuous light supplementing device and continuous light supplementing method for designated area of lunar surface Download PDFInfo
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Abstract
The application belongs to the field of deep space exploration, and particularly relates to a continuous light supplementing illumination device and a continuous light supplementing illumination method for a designated area of a lunar surface, comprising the following steps: a plurality of lunar satellites, wherein the lunar satellites encircle the moon on the same running orbit, and the running orbit undershot track of the lunar satellites covers a lunar surface appointed area; at least one reflecting surface for reflecting sunlight to a designated area of the lunar surface, the reflecting surface being mounted on the lunar satellite; and extra energy input is provided for the designated area of the lunar surface in a reflection light supplementing mode, so that the light supplementing illumination for the designated area without light/weak light of the lunar surface is realized, the lunar night time length is shortened, the lunar night storage risk of lunar surface working facilities and equipment is reduced, and the reliability of lunar surface scientific research activity tasks is improved.
Description
Technical Field
The application belongs to the field of deep space exploration, and particularly relates to a continuous light supplementing illumination device and a continuous light supplementing illumination method for a designated area of a lunar surface.
Background
The construction and long-term operation of the lunar research station are an important circle of manned lunar exploration tasks, but the problem of energy supply exists, such as the fact that the moon is taken as a natural satellite of the earth, due to the locking effect of tidal force, the spin period of the moon is equal to the period of the revolution of the moon around the earth, and about 27.32 earth days, so that the length of one month and night can reach 14 days, and therefore, the long-term research station on the lunar surface needs to be designed to consider the problem of how to stay cold and long month and night; if there are permanent shadow areas in some pits of the two poles of the moon due to small sun irradiation angle, scientists guess that water ice may exist in the permanent shadow areas, for example, research on the permanent shadow areas, scientific research stations at the polar areas need to consider how to face long polar night with a length exceeding hundred days during design; there is a great energy demand for many systems including life support systems and scientific research tasks at lunar research stations both during the night and during the polar night of the moon.
Disclosure of Invention
In view of the shortcomings of the prior art, the application aims to provide a continuous light supplementing illuminating device for a lunar surface designated area, which provides additional energy input for the lunar surface designated area in a reflection light supplementing mode, realizes the light supplementing illumination for the lunar surface designated area without light/weak light, shortens the lunar night time duration, reduces the lunar night storage risk of lunar surface working facilities and equipment, and improves the reliability of lunar surface scientific research activity tasks.
The purpose of the disclosure can be achieved by the following technical scheme:
a continuous light-supplementing illumination device for a designated area of a lunar surface, comprising:
a plurality of lunar satellites, wherein the lunar satellites encircle the moon on the same running orbit, and the running orbit undershot track of the lunar satellites covers a lunar surface appointed area;
at least one reflecting surface for reflecting sunlight to a designated area of the lunar surface, the reflecting surface being mounted on the lunar satellite.
In some disclosures, the orbit constraints of the lunar satellites are as follows:
wherein: t is the elapsed time; t (T) M For revolution period of moon, J 2 Is the coefficient of the second term of the lunar gravitational perturbation function; r is R M Is the radius of the moon; i is the track pitch; a is the semi-long axis of the track; e is the track eccentricity, μ is the central celestial body gravitational constant of the moon; j is the number of track periods covering the same understar track; k is the revolution period of the moon passing by covering the same sub-satellite point track.
In some disclosures, a plurality of lunar satellites are arranged at equal time intervals between them.
In some disclosures, the reflective surface primary optical axis points to an angular bisector of a vector of moon to sun and a vector angle θ of moon to satellite.
In some disclosures, a single lunar satellite is operated at a period of time around the orbit that is greater than or equal to the orbital period of the orbiting of the lunar satelliteWherein N is the number of the lunar satellites on the same running orbit.
In some disclosures, the reflective surface is one of a flat mirror, a convex mirror, or a concave mirror.
In a second aspect, in view of the shortcomings of the prior art, the present application is to provide a continuous light-supplementing illumination method for a lunar surface designated area, and provide additional energy input for the lunar surface designated area by means of reflection light supplementing, so as to implement light-supplementing illumination for a lunar surface designated no-light/weak-light area, shorten the lunar night time duration, reduce the lunar night storage risk of lunar surface working facilities and equipment, and improve the reliability of lunar surface scientific research activity tasks.
The purpose of the disclosure can be achieved by the following technical scheme:
the continuous light supplementing illumination method for the designated area of the lunar surface comprises the following steps:
the method comprises the steps that a plurality of lunar satellites are located on an operation orbit of the same lunar, the operation orbit is constrained according to lunar surface appointed area position information, and the lunar surface appointed area position information comprises longitude information of a lunar surface appointed area and latitude of the lunar surface appointed area;
the plurality of the lunar satellites are arranged at equal time intervals;
the reflection surface is arranged on the lunar satellite and is used for reflecting sunlight to a lunar designated area, and the main optical axis of the reflection surface points to an angular bisector of a vector angle theta between a vector from the moon to the sun and a vector from the moon to the satellite.
In some disclosures, the orbit constraints of the lunar satellites are as follows:
wherein: t is the elapsed time; t (T) M For revolution period of moon, J 2 Is the coefficient of the second term of the lunar gravitational perturbation function; r is R M Is the radius of the moon; i is the track pitch; a is the semi-long axis of the track; e is the track eccentricity, μ is the central celestial body gravitational constant of the moon; j is the number of track periods covering the same understar track; k is the revolution period of the moon passing by covering the same sub-satellite point track.
In some disclosures, a single lunar satellite is operated at a period of time around the orbit that is greater than or equal to the orbital period of the orbiting of the lunar satelliteWherein N is the number of the lunar satellites on the same running orbit.
In some disclosures, the reflective surface is one of a flat mirror, a convex mirror, or a concave mirror.
The beneficial effects of the present disclosure are:
and extra energy input is provided for the designated area of the lunar surface in a reflection light supplementing mode, so that the light supplementing illumination for the designated area without light/weak light of the lunar surface is realized, the lunar night time length is shortened, the lunar night storage risk of lunar surface working facilities and equipment is reduced, and the reliability of lunar surface scientific research activity tasks is improved.
Drawings
In order to more clearly illustrate the embodiments of the present disclosure or the prior art, the drawings that are required for the description of the embodiments or the prior art will be briefly described, and it will be apparent to those skilled in the art that other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a schematic illustration of continuous supplemental lighting for a lunar surface designated area;
FIG. 2 is a schematic diagram of the distribution of the orbiting satellites in orbit around the moon;
FIG. 3 is a graph showing the time-dependent distance between adjacent surrounding satellites in FIG. 2;
FIG. 4 is a satellite on-the-fly time analysis of FIG. 2;
FIG. 5 is a schematic view of solar reflection from the satellite in FIG. 2;
Detailed Description
The following description of the technical solutions in the embodiments of the present disclosure will be made clearly and completely with reference to the accompanying drawings in the embodiments of the present disclosure, and it is apparent that the described embodiments are only some embodiments of the present disclosure, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments in this disclosure without inventive faculty, are intended to fall within the scope of this disclosure.
Embodiment one:
as shown in fig. 1, a continuous light-supplementing illumination device for a designated area of a lunar surface includes:
a plurality of lunar satellites, which all encircle the moon on the same running orbit, and the running orbit understar track of the lunar satellites covers the designated area of the lunar surface;
and the reflection surface is arranged on the lunar satellite and used for reflecting sunlight to a lunar designated area.
In the application, a plurality of co-orbit surrounding moon satellites with reflecting surfaces are beneficial to reflect sunlight to a designated area of the lunar surface, so as to realize continuous light supplementing illumination of a non-light/weak light area of the lunar surface and assist in supplying energy to lunar surface facilities.
In fig. 2, the number of the lunar satellites is 12, the 12 lunar satellites are located on the same running orbit and surround the moon, at this time, the orbit satellite lower point track of the lunar satellites covers the lunar surface appointed area, the same-orbit lunar satellites with reflecting surfaces reflect sunlight to the lunar surface appointed area, so as to realize continuous light supplementing illumination of the lunar surface non-light/weak light area and perform energy auxiliary supply to lunar surface facilities.
In order to ensure the coverage effect of the ring-moon satellite on the lunar surface appointed area, the ring-moon satellite is covered on the lunar surface appointed area, and in order to reduce fuel consumption caused by later-stage orbit adjustment, the ring-moon satellite is designed to be a lunar repetition orbit in the same orbit, and orbit is controlled by utilizing the precession effect of orbit ascending intersection points, so that the satellite-satellite orbit of each period can keep consistent with lunar revolution.
First, according to longitude information of the lunar surface designated area and latitude of the lunar surface designated area, such as longitude and latitude of the lunar surface designated areaThe coverage requirement, the inclination angle i of the working orbit around the moon is selected, and can also be determined according to specific requirements, such as frozen orbit, polar orbit and the like. And then, the right ascent point and the left ascent point are adjusted according to the actual working condition, for example, the track surface of the secondary light supplementing target is in the vicinity of each light supplementing target. After the orbit inclination angle i and the ascending intersection point right ascent angle omega are determined, the near moon point amplitude angle omega is determined according to the working state requirement, the near moon point amplitude angle omega is adjusted to ensure that the satellite is positioned above the target point when passing through the near moon point, and a better light supplementing effect can be obtained by closer over-jacking height. Near moon altitude h p Given by the design index of the optical component, the near moon height h p And the distance moon height h a The relationship with the track semi-major axis a and the eccentricity e is as follows:
wherein: r is R M The moon radius was taken as 1737.10km.
The longitude that the moon turns over after a period of time is given by:
wherein: t is the elapsed time; t (T) M Is a moon revolution period. Precession about the lunar orbit elevation intersection is given by:
wherein: j (J) 2 Is the coefficient of the second term of the lunar gravitational perturbation function; to offset the influence of the two above terms after the orbit period and the revolution period of the moon, the above two equations are combined to obtain the following equation of the repetition orbit of the moon:
wherein: mu is the gravitational constant of the central celestial body of the moon; j is the number of track periods covering the same understar track; k is the revolution period of the moon passing by covering the same sub-satellite point track. In the above, only the track semi-long axis a and the eccentricity e are unknown, and both are only equal to the distance moon height h a The unknown quantity is related to the distance and the moon height h can be obtained by using a numerical method a 。
Meanwhile, due to the existence of solar-earth three-body gravitational perturbation and high-order moon non-spherical gravitational perturbation, the orbit of the lunar satellite slowly floats away from the nominal orbit obtained in the previous step, and in order to maintain the lunar satellite on the lunar orbit, an on-board electric propulsion engine can be used for orbit maintenance, which is already well-developed, such as Hangzhong, li Shining, kang Xiaolu and the like, the Hall electric propulsion space is applied to the current situation and future expectation [ J ]. Propulsion technology, 2023,44 (06): 38-51.DOI:10.13675/j.cnki.tjjs.2209006 ] [4]; yuan Chunzhu, zhang Jiang, fu Danying, et al ultra-low orbit satellite technology development and hope [ J ]. Spacecraft engineering, 2021,30 (06): 89-99.[5].
Illustratively, in this embodiment, for a lunar designated area of lunar north located at 90 ° north latitude and 0 ° east longitude, the selected lunar orbit parameters are shown in table 1. First, since the lunar designated area is located at the north pole of the moon, the orbiting satellite is set as an polar orbit satellite, and the orbit inclination angle thereof is selected to be 89.5 °; then, considering that the secondary light supplementing target area is located at 85 degrees of north latitude and 95 degrees of west longitude, and adjusting and setting the right ascent intersection point and the right ascent longitude to 299 degrees in order to ensure that the track surface is near each light supplementing target; in order to ensure that the satellite is positioned above the target area at the moment of passing the near moon, adjusting and setting the amplitude angle of the near moon to be 130 degrees; and according to the design index of the optical component, the height of the near moon is 10km, and the height of the far moon is 100km through the simultaneous moon repeated orbit equation, the orbit semi-long axis and the eccentricity equation. The working orbit parameters of the winding month are as follows:
table 1 working orbit parameters around the month
In order to ensure continuous and even coverage of the lunar satellite formation on the designated position of the lunar surface, the lunar satellite formation is designed into an equal-time-interval formation, namely, the interval time of all satellites in the formation passing through the same satellite point is the sameT is the orbit period, and N is the number of formation satellites. Assume that the average point angle of one satellite in the initial state is M 0 The closest point angle M of the satellite adjacent to it can be solved according to the kepler equation:
the method can sequentially obtain the closest point angles of all satellites in the formation in the initial state, and formation orbit information is obtained. The consideration load will be used to make reflective light-filling for the lunar surface designated area, so the queue-ready mission time needs to be analyzed. During the satellite task execution period, the connection line between the satellite and the sun and the connection line between the satellite and the lunar surface designated area are required to be free of shielding, in order to ensure that the lunar surface designated area can be continuously reflected and supplemented with light by surrounding lunar satellite formation, verification calculation is required to be carried out on the working time length of each cycle of a single satellite, and if the working time length exceeds the orbit periodThe track is determined to meet the requirements.
As shown in fig. 3 and 4, in the present embodiment, the distance between two adjacent satellites is periodically changed due to the small eccentricity, the distance between two adjacent satellites is not greatly changed, the minimum distance is 907km, and the maximum distance is 957km. Referring to fig. 5, illustratively, the orbit period is calculated to be about 7067s, and the actual satellite can operate for about 740s per period, exceeding 1/12 of the orbit period (589 s), based on the operating orbit parameters around the month provided in table 1, so the designed satellite fleet orbit can meet the continuous reflection light filling requirement.
In the application, the reflecting surface can use reflecting surfaces with different forms such as a plane mirror, a convex mirror or a concave mirror and the like so as to meet different illumination supplementing requirements.
Of course, in the present application, the reflecting surface refers to a reflecting surface in different forms such as a plane mirror, a convex mirror or a concave mirror in the working state of the reflecting surface; for example, in some states, such as when the satellite is transmitting, the reflecting surface can be folded, and when the satellite is working, the reflecting surface in different forms such as a plane mirror, a convex mirror or a concave mirror is unfolded, and the research is directed at the reflecting surface, such as solar sail [1];
illustratively, in this embodiment, a plane mirror is used, and the illumination power P received by the plane mirror at the incident position m The method comprises the following steps:
P m ＝S m cos(α m )P 0
wherein: s is S m Is the area of plane mirror alpha m For the included angle between the incident parallel light and the main optical axis of the plane mirror, P 0 The solar illumination power is the solar illumination power on the unit area of the circular moon orbit. Let the surface reflectivity of the plane mirror be R m Because the moon is in a vacuum environment, the influence of medium scattering is avoided, the main optical axis of the plane mirror points to the angular bisector of the vector angle theta between the vector from the moon to the sun and the vector from the moon to the satellite, the reflected light can be approximately considered to vertically irradiate to the lunar surface, and the total amount of illumination power P received at the designated position of the lunar surface is as follows:
P＝S m cos(α m )sin(β m )P 0 R m
wherein: beta m The included angle between the emergent parallel light and the lunar surface can be obtained by the space positions of the designated areas of the lunar satellite and the lunar surface. In the above calculation, α m And beta m Can be obtained by track calculation, at P 0 With a known constant value, the minimum value of the lunar surface received illumination power P is only equal to R m The reflectivity of the mirrors used can be designed accordingly.
Illustratively, in this embodiment, P will be 0 Approximately the ground solar illumination power 1380W/m 2 According to the orbit information about the moon in Table 1 and the designated area of the lunar surface of the moon located at 90 degrees in North latitude and 0 degree in east longitude, the working period alpha is obtained by extrapolation of the orbit m Varying from about 28 to 83, beta m The minimum value of the reflection light-supplementing power requirement of the designated area of the lunar surface is not lower than 50000W, the maximum value is not lower than 250000W, and the carrying capacity limits the plane mirror area to 300m 2 R is calculated by m The plane mirror can be designed according to the index without being lower than 0.86.
As shown in fig. 5, for controlling the desired attitude pointing of the satellite so that the solar light utilization is maximized; to maximize the utilization of solar illumination, the mirror principal optical axis should be directed to the bisector of the angle θ of the vector from moon to sun and the vector from moon to satellite, and the mirror pointing vector can be obtained by:
wherein:to obtain the position of the sun in the lunar inertial coordinate system at a given moment by looking up the DE405 ephemeris +.>The position of the reflector carried by the lunar satellite under the lunar inertial coordinate system is>The lunar surface is assigned the position of the region under the lunar inertial coordinate system. After the expected attitude of the satellite under the lunar inertial system is obtained, the satellite can be directly used after being converted into an orbit coordinate system.
Aiming at the problem that the satellite loaded with the reflecting surface may have an attitude on the orbit, the prior art can overcome the problems, such as document [2] [3];
the application can be realized by utilizing the prior art to realize that the reflecting surface reaches a specified orbit along with the surrounding satellite, and simultaneously the reflecting surface is unfolded, so that the surrounding satellite can maintain a specified posture.
Illustratively, in the present embodiment, according to the lunar orbit information of table 1, the reflection light filling is performed for the lunar surface designated area of the lunar north pole located at 90 ° north latitude and 0 ° east longitude, given time 2023, 6, 27, 06:03:00 The method comprises the steps that (at the moment, the lunar satellite just passes through the upper portion of a designated area), under the VVLH coordinate system of the lunar satellite, the unit pointing vector of the lunar satellite to the sun is (0.931935,0.362002, -0.021239), the unit pointing vector of the lunar satellite to the designated area of the lunar surface is (-0.017375,0.090755,0.995722), the expected unit pointing vector of the main optical axis of the reflector carried by the lunar satellite is (0.648147,0.320868,0.690615), and the expected attitude pointing of the lunar satellite can be obtained by combining the installation information of the reflector.
Embodiment two:
the continuous light supplementing illumination method for the designated area of the lunar surface comprises the following steps:
the plurality of lunar satellites are positioned on an operation orbit of the same lunar, the operation orbit is constrained according to position information of a lunar surface designated area, and the position information of the lunar surface designated area comprises longitude information of the lunar surface designated area and latitude of the lunar surface designated area;
the plurality of the lunar satellites are arranged at equal time intervals;
the reflection surface is arranged on the lunar satellite and is used for reflecting sunlight to a lunar designated area, and the main optical axis of the reflection surface points to an angular bisector of a vector angle theta between a vector from the moon to the sun and a vector from the moon to the satellite.
In actual use, sunlight is reflected to a lunar surface appointed area by using a plurality of co-orbit lunar satellites with reflecting surfaces so as to realize light supplementing illumination of a lunar surface non-light/weak light area, and energy auxiliary supply is carried out on lunar surface facilities, wherein the orbit of the lunar satellite is acquired according to longitude information of the lunar surface appointed area and latitude information of the lunar surface appointed area, so that the lunar satellite can run on the orbit to pass through the lunar surface appointed area; the plurality of the lunar satellites are arranged at equal time intervals, so that the designated positions can be supplemented by the plurality of the lunar satellites in a periodical and continuous manner; and the main optical axis of the reflecting surface is directed to an angular bisector of an included angle theta between a vector from the moon to the sun and a vector from the moon to the satellite, so that the solar illumination utilization rate is maximized.
Reference is made to embodiment one for other information.
[1] The on-orbit key technology of solar sails is verified in China for the first time [ J ]. Automation Expandable 2020,37 (01): 4.
[2] Zhang Xiuyun, zong Qun, zhu Wanwan, etc. flexible spacecraft attitude maneuver trajectory design and tracking control [ J ]. Astronautics report, 2019,40 (11): 1332-1340.
[3] Chen Yicheng the solar sail spacecraft levitation orbit maintenance and Flexible attitude control study [ D ] university of Nanj aviation aerospace, 2020.DOI:10.27239/d.cnki.gnhhu.2020.000194.
In the description of the present specification, the descriptions of the terms "one embodiment," "example," "specific example," and the like, 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 present disclosure. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing has shown and described the basic principles, principal features, and advantages of the present disclosure. It will be understood by those skilled in the art that the present disclosure is not limited to the embodiments described above, which have been described in the foregoing and description merely illustrates the principles of the disclosure, and that various changes and modifications may be made therein without departing from the spirit and scope of the disclosure, which is defined in the appended claims.
Claims (10)
1. Continuous light filling lighting device to moon face appointed region, its characterized in that includes:
a plurality of lunar satellites, wherein the lunar satellites encircle the moon on the same running orbit, and the running orbit undershot track of the lunar satellites covers a lunar surface appointed area;
at least one reflecting surface for reflecting sunlight to a designated area of the lunar surface, the reflecting surface being mounted on the lunar satellite.
2. The continuous light-supplementing illuminating device for a designated area of a lunar surface according to claim 1, wherein the orbit constraint of the lunar satellite is as follows:
wherein: t is the elapsed time; t (T) M For revolution period of moon, J 2 Is the coefficient of the second term of the lunar gravitational perturbation function; r is R M Is the radius of the moon; i is the track pitch; a is the semi-long axis of the track; e is the track eccentricity, μ is the central celestial body gravitational constant of the moon; j is the number of track periods covering the same understar track; k is the revolution period of the moon passing by covering the same sub-satellite point track.
3. The continuous light-supplementing illuminating device for a designated area of a lunar surface according to claim 1, wherein a plurality of the lunar satellites are arranged at equal time intervals.
4. The continuous light-supplementing illuminating device for a lunar surface designated area according to claim 1, wherein the main optical axis of the reflecting surface points to an angular bisector of a vector of moon to sun and a vector angle θ of moon to satellite.
5. The continuous-light-supplementing illuminating device for a lunar surface designated area according to claim 1, wherein the period of operation of a single lunar satellite around the orbit is longer than or equal to the orbit period of the lunar satellite's orbitWherein N is the number of the lunar satellites on the same running orbit.
6. The continuous light-supplementing illuminating device for a lunar surface of claim 1, wherein the reflecting surface is one of a plane mirror, a convex mirror or a concave mirror.
7. The continuous light supplementing illumination method for the designated area of the lunar surface is characterized by comprising the following steps:
the method comprises the steps that a plurality of lunar satellites are located on an operation orbit of the same lunar, the operation orbit is constrained according to lunar surface appointed area position information, and the lunar surface appointed area position information comprises longitude information of a lunar surface appointed area and latitude of the lunar surface appointed area;
the plurality of the lunar satellites are arranged at equal time intervals;
the reflection surface is arranged on the lunar satellite and is used for reflecting sunlight to a lunar designated area, and the main optical axis of the reflection surface points to an angular bisector of a vector angle theta between a vector from the moon to the sun and a vector from the moon to the satellite.
8. The method of claim 7, wherein the orbit constraints of the lunar satellites are as follows:
wherein: t is the elapsed time; t (T) M For revolution period of moon, J 2 Is the coefficient of the second term of the lunar gravitational perturbation function; r is R M Is the radius of the moon; i is the track pitch; a is the semi-long axis of the track; e is the track eccentricity, μ is the central celestial body gravitational constant of the moon; j is the number of track periods covering the same understar track; k is the revolution period of the moon passing by covering the same sub-satellite point track.
9. The method of claim 7, wherein a single lunar satellite is operated for a period of time greater than or equal to the orbital period of the orbital orbit of the lunar satelliteWherein N is the number of the lunar satellites on the same running orbit.
10. The method of claim 7, wherein the reflective surface is one of a flat mirror, a convex mirror, or a concave mirror.
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| CN202311165883.7A CN116946396A (en) | 2023-09-11 | 2023-09-11 | Continuous light supplementing device and continuous light supplementing method for designated area of lunar surface |
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| CN202311165883.7A CN116946396A (en) | 2023-09-11 | 2023-09-11 | Continuous light supplementing device and continuous light supplementing method for designated area of lunar surface |
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