CN116002082B - Solar sailboard sun-facing orientation system and sun-facing orientation method - Google Patents
Solar sailboard sun-facing orientation system and sun-facing orientation method Download PDFInfo
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- CN116002082B CN116002082B CN202310144321.8A CN202310144321A CN116002082B CN 116002082 B CN116002082 B CN 116002082B CN 202310144321 A CN202310144321 A CN 202310144321A CN 116002082 B CN116002082 B CN 116002082B
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- 238000000034 method Methods 0.000 title claims abstract description 24
- 230000000977 initiatory effect Effects 0.000 claims abstract description 49
- 239000002360 explosive Substances 0.000 claims abstract description 48
- 238000001514 detection method Methods 0.000 claims abstract description 29
- 238000010586 diagram Methods 0.000 description 6
- 238000000926 separation method Methods 0.000 description 4
- 238000013016 damping Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009966 trimming Methods 0.000 description 2
- FFBHFFJDDLITSX-UHFFFAOYSA-N benzyl N-[2-hydroxy-4-(3-oxomorpholin-4-yl)phenyl]carbamate Chemical compound OC1=C(NC(=O)OCC2=CC=CC=C2)C=CC(=C1)N1CCOCC1=O FFBHFFJDDLITSX-UHFFFAOYSA-N 0.000 description 1
- 238000004590 computer program Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Abstract
The invention provides a sun alignment system and a sun alignment method of a solar sailboard, which are used for unlocking the solar sailboard by detonating a initiating explosive device unlocking device so as to enable the solar sailboard to be unfolded; detecting the unfolding state information of the solar sailboard through a solar sailboard detection device; the unfolding state information is used for indicating the unfolding state of the solar sailboard and locking the solar sailboard; according to the obtained unfolding state information of the solar sailboard, the initiating explosive device unlocking device, the solar sailboard detecting device, the solar sailboard rotating device and the satellite attitude adjusting device are controlled to conduct sun orientation adjustment on the whole satellite, and therefore solar sailboard orientation can be conducted under the condition that part of the solar sailboard is unfolded or the solar sailboard is not unfolded in place.
Description
Technical Field
The invention relates to the technical field of satellites, in particular to a sun-facing orientation system and a sun-facing orientation method of a solar sailboard.
Background
The satellite-rocket separation is an important control technology in the technical field of satellites, and in the satellite-rocket separation process, a plurality of operations such as satellite separation, whole satellite power-on, solar sailboard unfolding, sun orientation and the like are needed, so that the process of completing the satellite-rocket separation by energy source is realized. In the related art, after the satellites and arrows are separated, a sun-facing orientation operation is required, so that the solar sailboard can obtain the maximum illumination to generate electric energy. In the actual rocket launching process, after the satellites and the arrows are separated, the solar sailboard needs to be unfolded firstly, and then the sun orientation operation can be carried out.
However, there are various accidents that occur because the solar panels are still deployed at present by detonating a initiating explosive device unlocking device such as an explosion bolt, and then driving the solar panels to be deployed in place and locked. For example, it is possible that after firing the initiating explosive device unlocking device, the corresponding solar array does not spread out and lock in place as intended. It may occur that only a portion of the solar panels are deployed or that the solar panels are not deployed in place and cannot be oriented for the day.
Disclosure of Invention
The invention provides a sun-facing orientation system and a sun-facing orientation method of a solar sailboard, which are used for realizing sun-facing orientation of the solar sailboard under the condition that part of the solar sailboard is unfolded or the solar sailboard is not unfolded in place.
In a first aspect, an embodiment of the present invention provides a solar array solar orientation system, including:
the initiating explosive device unlocking device is used for unlocking the solar sailboard;
the solar sailboard detection device is used for detecting the unfolding state information of the solar sailboard;
the solar sailboard rotating device is used for rotating and adjusting the direction of the solar sailboard;
the satellite attitude adjusting device is used for driving the satellite to adjust the attitude;
the control terminal is respectively connected with the initiating explosive device unlocking device, the solar sailboard detecting device, the solar sailboard rotating device and the satellite attitude adjusting device, and controls the initiating explosive device unlocking device, the solar sailboard detecting device, the solar sailboard rotating device and the satellite attitude adjusting device to perform sun alignment adjustment on the whole satellite according to the obtained unfolding state information of the solar sailboard.
In a second aspect, an embodiment of the present invention provides a method for orienting solar sailboards on opposite days, including:
detonating a initiating explosive device unlocking device to unlock the solar sailboard so as to enable the solar sailboard to be unfolded;
detecting the unfolding state information of the solar sailboard through a solar sailboard detection device; the unfolding state information is used for indicating the unfolding state of the solar sailboard and locking the solar sailboard;
and controlling a initiating explosive device unlocking device, a solar sailboard detection device, a solar sailboard rotation device and a satellite attitude adjustment device to perform sun orientation adjustment on the whole satellite according to the obtained unfolding state information of the solar sailboard.
The invention provides a sun alignment system and a sun alignment method of a solar sailboard, which are used for unlocking the solar sailboard by detonating a initiating explosive device unlocking device so as to enable the solar sailboard to be unfolded; detecting the unfolding state information of the solar sailboard through a solar sailboard detection device; the unfolding state information is used for indicating the unfolding state of the solar sailboard and locking the solar sailboard; according to the obtained unfolding state information of the solar sailboard, the initiating explosive device unlocking device, the solar sailboard detecting device, the solar sailboard rotating device and the satellite attitude adjusting device are controlled to conduct sun orientation adjustment on the whole satellite, and therefore solar sailboard orientation can be conducted under the condition that part of the solar sailboard is unfolded or the solar sailboard is not unfolded in place.
It should be understood that the description in this summary is not intended to limit the critical or essential features of the embodiments of the invention, nor is it intended to limit the scope of the invention. Other features of the present invention will become apparent from the description that follows.
The above, as well as additional objectives, advantages, and features of the present application will become apparent to those skilled in the art from the following detailed description of a specific embodiment of the present application when read in conjunction with the accompanying drawings.
Drawings
The above and other features, advantages and aspects of embodiments of the present invention will become more apparent by reference to the following detailed description when taken in conjunction with the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements.
FIG. 1 illustrates a satellite ontology-based coordinate system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a solar array solar orientation system according to an embodiment of the present invention;
FIG. 3 illustrates a flow chart of a method of solar panel opposite-day orientation in accordance with an embodiment of the present invention;
FIG. 4 is a flow chart of a method of solar panel opposite-day orientation in accordance with a preferred embodiment of the present invention; and
fig. 5 shows a schematic diagram of a position vector of the sun with respect to a satellite body coordinate system in an embodiment of the invention.
In the figure: a first solar windsurfing board 210; a second solar windsurfing board 220; a first initiating explosive device unlocking device 211; a second initiating explosive device unlocking device 221; a first solar array detection device 212; a second solar array detection device 222; a first solar panel rotation device 213; a second solar panel rotation device 223; a star computer 101 (control terminal); the satellite attitude adjusting device 300.
Detailed Description
In order to enable a person skilled in the art to better understand the technical solutions in one or more embodiments of the present specification, the technical solutions in one or more embodiments of the present specification will be clearly and completely described below with reference to the drawings in one or more embodiments of the present specification, and it is obvious that the described embodiments are only some embodiments of the present specification, not all embodiments. All other embodiments, which can be made by one or more embodiments of the present disclosure without inventive faculty, are intended to be within the scope of the present disclosure.
It should be noted that, the description of the embodiment of the present invention is only for the purpose of more clearly describing the technical solution of the embodiment of the present invention, and does not constitute a limitation on the technical solution provided by the embodiment of the present invention.
Referring to fig. 1, the satellite includes: the satellite body 100, the first solar sailboard 210 and the second solar sailboard 220 connected with the satellite body 100.
Based on the coordinate system of the satellite body 100, the solar sailboards include a +y solar sailboard 210 and a-y solar sailboard 220. The +y solar windsurfing board 210 extends in the +y axis of the coordinate system and the-y solar windsurfing board 220 extends in the-y axis of the coordinate system.
Fig. 1 also shows a schematic of a +y solar array 210 and a-y solar array 220 returning to zero. Referring to fig. 1, upon returning to the null position, the normals of the +y solar windsurfing boards 210 and the-y solar windsurfing boards 220 coincide with the x-axis direction of the satellite body 100.
Referring to fig. 2, the opposite-day orientation system of the solar array of the present invention includes a first initiating explosive device unlocking device 211 and a second initiating explosive device unlocking device 221 connected to a first solar array 210 and a second solar array 220, a first solar array detecting device 212 and a second solar array detecting device 222 connected to the first solar array 210 and the second solar array 220, and a first solar array rotating device 213 and a second solar array rotating device 223 connected to the first solar array 210 and the second solar array 220. The system further comprises a control terminal 101 and a satellite attitude adjusting device 300, wherein the control terminal is a satellite computer 101 in the following embodiment.
The terms first and second and the like in the description and in the claims of embodiments of the invention, are used for distinguishing between different objects and not necessarily for describing a particular sequential order of objects. For example, the first target object and the second target object, etc., are used to distinguish between different target objects, and are not used to describe a particular order of target objects.
In embodiments of the invention, words such as "exemplary" or "such as" are used to mean serving as an example, instance, or illustration. Any embodiment or design described herein as "exemplary" or "e.g." in an embodiment should not be taken as preferred or advantageous over other embodiments or designs. Rather, the use of words such as "exemplary" or "such as" is intended to present related concepts in a concrete fashion.
Illustratively, the first initiating explosive device unlocking device 211 and the second initiating explosive device unlocking device 221 are used for unlocking the first solar sailboard 213 and the second solar sailboard 223. The first solar array detection device 212 and the second solar array detection device 222 are used for detecting whether the first solar array 210 and the second solar array 220 are unfolded and locked. The first solar panel rotation device 213 and the second solar panel rotation device 223 are used to rotate the first solar panel 210 and the second solar panel 220.
In addition, the star computer 101 is connected to the first initiating explosive device unlocking device 211 and the second initiating explosive device unlocking device 221, and is used for controlling the first initiating explosive device unlocking device 211 and the second initiating explosive device unlocking device 221 to unlock the first solar sailboard 210 and the first solar sailboard 220. The star computer 101 is further connected to the first solar panel detection device 212 and the second solar panel detection device 222, and obtains the information of the unfolding states of the first solar panel 210 and the first solar panel 220. The external star computer 101 is further connected to the first solar panel rotation device 213 and the second solar panel rotation device 223 for controlling the rotation of the first solar panel 210 and the first solar panel 220.
In addition, the satellite computer 101 is further connected to a satellite attitude adjustment device 300 for adjusting the attitude of the satellite body 100.
When at least one of the first solar sailboard 210 and the second solar sailboard 220 is unfolded and locked, the satellite computer (i.e. the control terminal) 101 drives the first solar sailboard rotating device 213 and the second solar sailboard rotating device 223 to control the first solar sailboard 210 and the second solar sailboard 220 to return to the zero position, and the satellite computer (i.e. the control terminal) 101 drives the satellite to adjust the posture through the satellite posture adjusting device 300, so as to perform-x axis direction sun-to-sun for the whole satellite; when the first solar sailboard 210 and the second solar sailboard 220 are not unfolded and locked, the satellite computer (i.e. the control terminal) 101 drives the satellite attitude adjusting device 300 to perform the sun alignment in the-z axis direction for the satellite, wherein, based on the coordinate system of the satellite body 100, when the zero position is returned, the normals of the first solar sailboard 210 and the second solar sailboard 220 located in the y axis are consistent with the x axis direction of the satellite body 100.
Based on the same inventive concept, the embodiment of the present invention further provides a method for orienting solar sailboards on opposite days by applying the above-mentioned solar sailboard on opposite days orientation system, as shown in fig. 3, where the method includes S302: detonating a initiating explosive device unlocking device to unlock the solar sailboard so as to enable the solar sailboard to be unfolded;
by way of example, the initiating explosive device unlocking device may comprise, for example:
the first initiating explosive device unlocking device 211 is respectively connected with the first solar sailboard 210 and the control terminal 101 and is used for unlocking the first solar sailboard 210; the following is realized by a star computer;
the second initiating explosive device unlocking device 221 is respectively connected with the second solar sailboard 210 and the star computer (i.e. the control terminal) 101, and is used for unlocking the second solar sailboard 220; the first solar sailboard 210 and the second solar sailboard 220 are respectively connected to two sides of the satellite body 100;
the solar sailboard detection device comprises:
the first solar sailboard detection device 211 is connected to the first solar sailboard 210 and the star computer (i.e. the control terminal) 101, respectively, and is configured to detect and lock the unfolded state of the first solar sailboard 210;
the second solar sailboard detection device 212 is connected with the second solar sailboard 220 and the star computer (i.e. the control terminal) 101 respectively, and is used for detecting and locking the unfolding state of the second solar sailboard 220;
the solar sailboard rotating device comprises:
the first solar sailboard rotating device 213 is respectively connected with the first solar sailboard and the control terminal and is used for controlling the rotation of the first solar sailboard;
the second solar panel rotation device 223 is connected to the second solar panel 220 and the star computer (i.e. the control terminal) 101, respectively, for controlling the rotation of the second solar panel 220.
When the satellite is separated from the rocket, the first solar array 210 and the second solar array 220 are not in an unfolded state, but in a folded and contracted state. Therefore, after the satellite is separated from the rocket, particularly after the rotation is stopped by the speed damping, the satellite computer 101 detonates the first initiating explosive device unlocking device 211 and the second initiating explosive device unlocking device 221 to unlock the first solar sailboard 210 and the second solar sailboard 220. Whereby the first solar array 210 and the second solar array 220 are spread.
S304: detecting the unfolding state information of the solar sailboard through a solar sailboard detection device; the unfolding state information is used for indicating the unfolding state of the solar sailboard and locking the solar sailboard;
illustratively, after initiating the initiating explosive device unlocking device, the star computer 101 detects the deployment status information of the corresponding solar sailboards 210-220 through the solar sailboard detection devices 212-222, wherein the deployment status information is used to indicate whether the solar sailboards 210-220 are deployed in place and locked.
S306: and controlling a initiating explosive device unlocking device, a solar sailboard detection device, a solar sailboard rotation device and a satellite attitude adjustment device to perform sun orientation adjustment on the whole satellite according to the obtained unfolding state information of the solar sailboard.
The advantageous effects of the invention are described below in a preferred embodiment:
first, the initiating explosive device unlocking device is detonated to unlock the solar sailboard.
Specifically, when the satellite is separated from the rocket, the solar sailboards 210 to 220 are not in an unfolded state, but in a folded and contracted state. Thus, after the satellite is separated from the rocket, and in particular, after the rotation is stopped by the velocity damping, the initiating explosive device unlocking devices 211 and 221 are detonated by the satellite service computer 101 to unlock the solar sailboards 210 and 220. Whereby the solar panels 210 and 220 are spread out.
And secondly, acquiring the unfolding state information of the solar sailboard.
Specifically, after the initiating explosive device unlocking device is initiated, the star computer 101 detects the unfolding status information of the corresponding solar sailboards 210 to 220 through the solar sailboard detection devices 212 to 222, wherein the unfolding status information is used for indicating whether the solar sailboards 210 to 220 are unfolded in place and locked.
And finally, performing sun alignment operation according to the obtained unfolding state information of the solar sailboard.
Referring to fig. 3, after the initiating explosive device unlocking means is initiated, the star computer 101 obtains the information of the deployment status of the +y solar sailboard 210 and the-y solar sailboard 220 through the solar sailboard detecting means 212 to 222.
With both the +y solar windsurfing board 210 and the-y solar windsurfing board 220 deployed in place and locked, the star computer 101 drives both the +y solar windsurfing board 210 and the-y solar windsurfing board 220 back to the zero position. As shown in fig. 1, when the +y solar array 210 and the-y solar array 220 return to zero, their normals coincide with the x-axis of the satellite body 100. Then, the satellite computer 101 drives the satellite to adjust the attitude through the satellite attitude adjustment device 300, thereby realizing the whole satellite-x pair-day, and thus completing the pair-day orientation.
In the event that either of the +y solar array 210 and the-y solar array 220 is deployed in place and locked, the star computer 101 drives the deployed solar array back to the zero position. Then, the satellite computer 101 drives the satellite to adjust the attitude through the satellite attitude adjustment device 300, thereby realizing the whole satellite-x pair-day, and thus completing the pair-day orientation.
When neither the +y solar array 210 nor the-y solar array 220 is deployed in place and locked, the satellite computer 101 drives the satellite attitude adjustment device 300 for-z pairs of days.
Optionally, the side of the satellite body 100 facing the-x axis direction is provided with a sun sensor 102. The satellite computer 101 drives a satellite to adjust the posture through the satellite posture adjusting device 300, so as to realize the whole satellite-x operation on the sun, and the method comprises the following steps:
the satellite computer 101 acquires the position information of the sun relative to the satellite body 100 from the sun sensor 102;
the satellite computer 101 determines an included angle between a position vector of the sun relative to a coordinate system of the satellite body 100 and a satellite body 100-x axis according to the position information of the sun relative to the satellite body 100; referring specifically to fig. 5, the S point represents a position point of the sun with respect to the coordinate system of the satellite body 100, which is determined by the satellite computer 101 according to the position information of the sun acquired from the sun sensor 102.So that the position vector Vs of the sun relative to the satellite body 100 coordinate system can be determined according to the coordinate information of the S point 0 (as shown by the dashed lines in fig. 5). Thus, the star computer 101 can determine the position vector Vs 0 An included angle between the satellite body 100 coordinate system and the-x axis; and
the satellite computer 101 drives the satellite to adjust the posture through the satellite posture adjusting device 300, so that the sun is relative to the position vector Vs of the satellite body 100 coordinate system 0 Consistent with the x-axis of the satellite body 100 coordinate system.
Thus, through the above operation, the satellite computer 101 can realize the whole-x-to-day operation of the satellite using the sun sensor 102 provided to the satellite body 100. Therefore, after the whole star-x pair-day operation, the solar sailboards 210-220 can be pair-day, and the power generation efficiency of the solar sailboards 210-220 is improved.
More specifically, in the whole-satellite-x-to-day operation, the satellite computer 101 can acquire the position of the sun relative to the coordinate system of the satellite body 100 in real time and calculate the corresponding position vector Vs 0 . Then, the position vector Vs is calculated in real time 0 The projection in the x-y plane is at an angle alpha to the-x axis 1 Position vector Vs 0 The projection in the x-z plane is at an angle alpha to the-x axis 2 . And according to the included angle alpha 1 And an included angle alpha 2 Calculate C 1 ＝cosα 1 C 2 ＝cosα 2
Thereby the star computer 101 further calculates the overall daily eigenvalue L 1 ：
Thus, the star computer 101 calculates the daily feature value L in real time during the daily adjustment process 1 When the sun is relative to the characteristic value L 1 Above a predetermined threshold (e.g., some value close to the value 2), then it is determined that the-x-axis daily operation is complete. In this way, accurate sun-to-sun operation can be achieved using the sun sensor 102 provided to the satellite body 100.
Further alternatively, the solar panels 210 to 220 are further provided with solar sensors 213 to 223 on the side facing the satellite body-x axis direction. Thus, after the whole star-x pair-day operation is completed, the star computer 101 rotates the +y solar sailboard 210 through the solar sailboard rotating device 213 and/or rotates the-y solar sailboard 220 through the solar sailboard rotating device 223 according to the position information about the sun measured by the solar sensors 213 and/or 223, and performs pair-day fine adjustment on the +y solar sailboard 210 and/or the-y solar sailboard 220.
Specifically, after the star computer 101 completes the-x pair day operation of the whole star, the position information of the sun with respect to the +y solar sailboard 210 is further received from the sun sensor 213 and the position information of the sun with respect to the-y solar sailboard 220 is received from the sun sensor 223.
For example, the star computer 101 determines the position vector Vs in the coordinate system of the sun relative to the +y solar array 210 from the information received from the sun sensor 213 1 . Wherein the coordinate system of the +y solar sailboard 210 is parallel to the coordinate system of the satellite body 110 when it is zeroed. So that the-x axis of the coordinate system of the +y solar array 210 coincides with the direction of the normal to the +y solar array 210.
Thus, in the process of fine adjustment of the sun of the +y solar sailboard 210, the star computer 101 can obtain the position of the sun relative to the coordinate system of the +y solar sailboard in real time, and calculate the corresponding position vector Vs 1 . Then, the position vector Vs is calculated in real time 1 The projection in the x-z plane of the coordinate system of the +y solar sailboard forms an angle beta with the-x axis 1 . And according to the included angle beta 1 Calculating a sun-to-sun characteristic value L of the +y solar sailboard 2 ：
L 2 ＝|cosβ 1 I (equation 2)
Thus, the star computer 101 calculates the sun-to-sun characteristic value L in real time in the sun-to-sun fine adjustment process of the +y solar sailboard 2 When the sun is relative to the characteristic value L 2 Above a predetermined threshold (e.g., a value close to the value 1), then it is determined that the solar panel pair trimming is complete.
Likewise, during the fine tuning of the solar array 220,the star computer 101 can obtain the position of the sun relative to the coordinate system of the-y solar sailboard in real time and calculate the corresponding position vector Vs 2 . Then, the position vector Vs is calculated in real time 2 The projection in the x-z plane of the coordinate system of the-y solar panel is at an angle beta to the-x axis 2 . And according to the included angle beta 2 Calculating a sun-to-sun characteristic value L of the-y solar sailboard 3 ：
L 3 ＝|cosβ 2 I (equation 3)
Thus, the star computer 101 calculates the sun-to-sun characteristic value L in real time in the sun-to-sun fine adjustment process of the-y solar sailboard 3 When the sun is relative to the characteristic value L 3 Above a predetermined threshold (e.g., a value close to the value 1), then it is determined that the solar panel pair-wise trimming is complete.
Thus, according to the technical solution of the present embodiment, the satellite computer 101 first preliminarily realizes the sun-to-sun operation of the solar sailboard by using the whole satellite sun-to-sun operation of the satellite body 100. Then, the star computer 101 further performs the sun-setting fine adjustment operation on the solar sailboard, so that the sun-setting operation on the solar sailboard can be more accurately realized, and the efficiency of the solar sailboard is further improved.
The embodiment provides a sun-facing orientation method of a solar sailboard, which is used for unlocking the solar sailboard by detonating a initiating explosive device unlocking device so as to enable the solar sailboard to be unfolded; detecting the unfolding state information of the solar sailboard through a solar sailboard detection device; the unfolding state information is used for indicating the unfolding state of the solar sailboard and locking the solar sailboard; according to the obtained unfolding state information of the solar sailboard, the initiating explosive device unlocking device, the solar sailboard detecting device, the solar sailboard rotating device and the satellite attitude adjusting device are controlled to conduct sun orientation adjustment on the whole satellite, and therefore solar sailboard orientation can be conducted under the condition that part of the solar sailboard is unfolded or the solar sailboard is not unfolded in place.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present invention. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The above description is only illustrative of the preferred embodiments of the present invention and of the principles of the technology employed. It will be appreciated by persons skilled in the art that the scope of the invention referred to in the present invention is not limited to the specific combinations of the technical features described above, but also covers other technical features formed by any combination of the technical features described above or their equivalents without departing from the inventive concept. Such as the above-mentioned features and the technical features disclosed in the present invention (but not limited to) having similar functions are replaced with each other.
Claims (10)
1. A solar array solar orientation system, comprising:
the initiating explosive device unlocking device is used for unlocking the solar sailboard;
the solar sailboard detection device is used for detecting the unfolding state information of the solar sailboard;
the solar sailboard rotating device is used for rotating and adjusting the direction of the solar sailboard;
the satellite attitude adjusting device is used for driving the satellite to adjust the attitude;
the control terminal is respectively connected with the initiating explosive device unlocking device, the solar sailboard detecting device, the solar sailboard rotating device and the satellite attitude adjusting device, and controls the initiating explosive device unlocking device, the solar sailboard detecting device, the solar sailboard rotating device and the satellite attitude adjusting device to conduct sun alignment adjustment on the whole satellite according to the obtained unfolding state information of the solar sailboard, wherein the sun alignment adjustment is conducted on the whole satellite by the control terminal
Further comprises: the first sun sensor, the second sun sensor and the third sun sensor, the solar panel includes: a first solar panel and a second solar panel, and wherein
The control terminal is further configured to perform the following operations:
acquiring first position information of the sun relative to a satellite body from a first sun sensor, and determining a first position vector of the sun relative to a coordinate system of the satellite body according to the acquired first position information;
calculating a first included angle between the projection of the first position vector in the x-y plane of the coordinate system of the satellite body and the-x axis, and a second included angle between the projection of the first position vector in the x-z plane of the coordinate system of the satellite body and the-x axis;
according to the first included angle and the second included angle, a first pair of daily characteristic values of the satellite body are calculated, and the calculation formula is as follows:
；
wherein,，/>representing said first angle,/->，/>Representing the second included angle;
determining that the sun-to-sun operation of the satellite body is completed under the condition that the first sun-to-sun characteristic value is larger than a first preset threshold value;
acquiring second position information of the sun relative to the first solar sailboard from a second sun sensor, and determining a second position vector of the sun relative to a coordinate system of the first solar sailboard according to the acquired second position information;
calculating a third included angle between the projection of the second position vector in the x-z plane of the coordinate system of the first solar sailboard and the-x axis;
according to the third included angle, calculating a second pair of daily characteristic values of the first solar sailboard, wherein the calculation formula is as follows:
；
wherein,representing the third included angle;
determining that the sun-to-sun operation of the first solar sailboard is completed under the condition that the second sun-to-sun characteristic value is larger than a second preset threshold value;
acquiring third position information of the sun relative to the second solar sailboard from a third sun sensor, and determining a third position vector of the sun relative to a coordinate system of the second solar sailboard according to the acquired third position information;
calculating a fourth included angle between the projection of the third position vector in the x-z plane of the coordinate system of the second solar sailboard and the-x axis;
according to the fourth included angle, a third pair of daily characteristic values of the second solar sailboard are calculated, and the calculation formula is as follows:
；
wherein,representing the fourth included angle; and
and determining that the sun-facing operation of the second solar panel is completed under the condition that the third sun-facing characteristic value is larger than the second preset threshold value.
2. The orientation system of claim 1 wherein the initiating explosive device unlocking device comprises:
the first initiating explosive device unlocking device is respectively connected with the first solar sailboard and the control terminal and is used for unlocking the first solar sailboard;
the second initiating explosive device unlocking device is respectively connected with the second solar sailboard and the control terminal and is used for unlocking the second solar sailboard; the first solar sailboard and the second solar sailboard are respectively connected to two sides of the satellite body.
3. The orientation system of claim 2 wherein the solar array detection device comprises:
the first solar sailboard detection device is respectively connected with the first solar sailboard and the control terminal and is used for detecting the unfolding state of the first solar sailboard and locking the unfolding state;
and the second solar sailboard detection device is connected with the second solar sailboard and the control terminal respectively and is used for detecting the unfolding state of the second solar sailboard and locking the unfolding state.
4. A directional system according to claim 2 or 3, wherein the solar array rotation means comprises:
the first solar sailboard rotating device is respectively connected with the first solar sailboard and the control terminal and is used for controlling the rotation of the first solar sailboard;
and the second solar sailboard rotating device is respectively connected with the second solar sailboard and the control terminal and is used for controlling the rotation of the second solar sailboard.
5. A directional system according to claim 2 or 3, wherein when at least one of the first solar panel and the second solar panel is unfolded and locked, the control terminal drives the first solar panel rotating device and the second solar panel rotating device to control the first solar panel and the second solar panel to return to zero positions, and the control terminal drives the satellite to adjust the attitude by the satellite attitude adjusting device, so as to perform-x axis direction sun alignment on the whole satellite; when the first solar sailboard and the second solar sailboard are not unfolded in place and locked, the control terminal drives the satellite attitude adjusting device to perform-x axis direction sun alignment on the satellite; and when the zero position is returned, the normal line of the first solar sailboard and the normal line of the second solar sailboard positioned on the y axis are consistent with the direction of the x axis of the satellite body based on the coordinate system of the satellite body.
6. A method of solar panel orientation for sun, comprising:
detonating a initiating explosive device unlocking device to unlock the solar sailboard so as to enable the solar sailboard to be unfolded;
detecting unfolding state information of the solar sailboard through a solar sailboard detection device, wherein the unfolding state information is used for indicating the unfolding state of the solar sailboard and locking the unfolding state;
according to the obtained unfolding state information of the solar sailboard, controlling the initiating explosive device unlocking device, the solar sailboard detecting device, the solar sailboard rotating device and the satellite attitude adjusting device to adjust the sun orientation of the whole satellite, wherein the sun orientation adjusting device comprises a solar energy sailboard detecting device, a solar energy sailboard rotating device, a satellite attitude adjusting device and a solar energy sailboard, wherein the solar energy sailboard rotating device is arranged on the satellite
Further comprises:
acquiring first position information of the sun relative to a satellite body from a first sun sensor, and determining a first position vector of the sun relative to a coordinate system of the satellite body according to the acquired first position information;
calculating a first included angle between the projection of the first position vector in the x-y plane of the coordinate system of the satellite body and the-x axis, and a second included angle between the projection of the first position vector in the x-z plane of the coordinate system of the satellite body and the-x axis;
according to the first included angle and the second included angle, a first pair of daily characteristic values of the satellite body are calculated, and the calculation formula is as follows:
；
wherein,，/>representing said first angle,/->，/>Representing the second included angle;
determining that the sun-to-sun operation of the satellite body is completed if the first sun-to-sun characteristic value is greater than a first predetermined threshold value, and wherein
The solar sailboard comprises: a first solar panel and a second solar panel, wherein
Acquiring second position information of the sun relative to the first solar sailboard from a second sun sensor, and determining a second position vector of the sun relative to a coordinate system of the first solar sailboard according to the acquired second position information;
calculating a third included angle between the projection of the second position vector in the x-z plane of the coordinate system of the first solar sailboard and the-x axis;
according to the third included angle, calculating a second pair of daily characteristic values of the first solar sailboard, wherein the calculation formula is as follows:
；
wherein,representing the third included angle;
determining that the sun-to-sun operation of the first solar sailboard is completed under the condition that the second sun-to-sun characteristic value is larger than a second preset threshold value;
acquiring third position information of the sun relative to the second solar sailboard from a third sun sensor, and determining a third position vector of the sun relative to a coordinate system of the second solar sailboard according to the acquired third position information;
calculating a fourth included angle between the projection of the third position vector in the x-z plane of the coordinate system of the second solar sailboard and the-x axis;
according to the fourth included angle, a third pair of daily characteristic values of the second solar sailboard are calculated, and the calculation formula is as follows:
；
wherein,representing the fourth included angle; and
and determining that the sun-facing operation of the second solar panel is completed under the condition that the third sun-facing characteristic value is larger than the second preset threshold value.
7. The orientation method according to claim 6, wherein the initiating explosive device unlocking means comprises:
the first initiating explosive device unlocking device is respectively connected with the first solar sailboard and the control terminal and is used for unlocking the first solar sailboard;
the second initiating explosive device unlocking device is respectively connected with the second solar sailboard and the control terminal and is used for unlocking the second solar sailboard; the first solar sailboard and the second solar sailboard are respectively connected to two sides of the satellite body;
the solar sailboard detection device comprises:
the first solar sailboard detection device is respectively connected with the first solar sailboard and the control terminal and is used for detecting the unfolding state of the first solar sailboard and locking the unfolding state;
the second solar sailboard detection device is connected with the second solar sailboard and the control terminal respectively and is used for detecting the unfolding state of the second solar sailboard and locking the unfolding state;
the solar sailboard rotating device comprises:
the first solar sailboard rotating device is respectively connected with the first solar sailboard and the control terminal and is used for controlling the rotation of the first solar sailboard;
and the second solar sailboard rotating device is respectively connected with the second solar sailboard and the control terminal and is used for controlling the rotation of the second solar sailboard.
8. The orientation method according to claim 7, wherein after the first initiating explosive device and the second initiating explosive device are detonated, the control terminal obtains the unfolding state information of the first solar sailboard and the second solar sailboard through the first solar sailboard detection device and the second solar sailboard detection device;
when the first solar sailboard and the second solar sailboard are unfolded in place and locked, the control terminal drives the first solar sailboard rotating device and the second solar sailboard rotating device to control the first solar sailboard and the second solar sailboard to return to zero positions, and the control terminal drives the satellite to adjust the gesture through the satellite gesture adjusting device to perform-x axis direction sun alignment on the whole satellite, wherein the normals of the first solar sailboard and the second solar sailboard positioned on the y axis are consistent with the x axis direction of the satellite body when the satellite returns to the zero position based on the coordinate system of the satellite body.
9. The orientation method according to claim 7, wherein the control terminal drives the unfolded solar sailboard to return to a zero position in a case where any one of the first solar sailboard and the second solar sailboard is unfolded and locked, and the control terminal drives the satellite to adjust the attitude by the satellite attitude adjusting device, so as to perform-x axis direction sun alignment on the whole satellite, wherein, based on a coordinate system of the satellite body, when returning to the zero position, normals of the first solar sailboard and the second solar sailboard located on the y axis are consistent with the x axis direction of the satellite body.
10. The method of claim 7, wherein the control terminal drives the satellite attitude adjustment device to perform-x-axis direction sun alignment for the entire satellite when neither the first solar array nor the second solar array is deployed in place and locked.
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