阅读说明：本技术 波束控制方法、低轨卫星、低轨卫星系统及存储介质 (Beam control method, low orbit satellite system and storage medium ) 是由 朱棣 刘虎 陈静 寇保华 王瑞军 于 2020-04-26 设计创作，主要内容包括：本公开提供了一种波束控制方法、低轨卫星、低轨卫星系统及计算机可读存储介质,涉及卫星技术领域。其中的波束控制方法包括：低轨卫星对发射波束进行开关控制；其中,被开启的发射波束的发射方向为第一方向,高轨卫星向被开启的发射波束所覆盖用户终端发射信号的方向为第二方向,第一方向与第二方向之间的夹角大于低轨卫星与高轨卫星的最小隔离角。通过低轨卫星对发射波束的开关控制调整波束覆盖区域,能够减轻低轨卫星通信系统与高轨卫星通信系统之间的干扰。(The disclosure provides a beam control method, a low-orbit satellite system and a computer readable storage medium, and relates to the technical field of satellites. The beam control method comprises the following steps: the low-orbit satellite performs switch control on the transmitted wave beam; the transmitting direction of the opened transmitting wave beam is a first direction, the direction of the high-orbit satellite transmitting signals to the user terminal covered by the opened transmitting wave beam is a second direction, and an included angle between the first direction and the second direction is larger than the minimum isolation angle between the low-orbit satellite and the high-orbit satellite. The beam coverage area is adjusted through the on-off control of the low-orbit satellite on the transmitting beam, and the interference between a low-orbit satellite communication system and a high-orbit satellite communication system can be reduced.)

1. A method of beam steering, comprising:

the low-orbit satellite performs switch control on the transmitted wave beam; wherein the content of the first and second substances,

the transmitting direction of the opened transmitting wave beam is a first direction, the direction of the high-orbit satellite transmitting signals to the user terminal covered by the opened transmitting wave beam is a second direction, and the included angle between the first direction and the second direction is larger than the minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

2. The beam control method according to claim 1, wherein the transmission direction of the turned-off transmission beam is a third direction, the direction in which the high-earth satellite transmits signals to the user terminal corresponding to the turned-off transmission beam is a fourth direction, and an included angle between the third direction and the fourth direction is not greater than a minimum isolation angle between the low-earth satellite and the high-earth satellite.

3. The beam steering method of claim 2, wherein the low earth satellite switching-controlling a transmit beam comprises:

in the process that the low-orbit satellite moves towards the equatorial plane, beams are closed in sequence from the beam farthest from the equatorial plane until all the beams are closed; the beams are turned on in sequence starting from the beam adjacent to the turned on transmission beam and close to the equatorial plane until the beam closest to the equatorial plane is turned on.

4. The beam control method of claim 3, wherein the low earth satellite switching control of a transmit beam further comprises:

and in the process of moving the low-earth-orbit satellite away from the equatorial plane, starting the beams closest to the equatorial plane in sequence until the number of the started transmitting beams reaches a preset value.

5. The beam control method of claim 4, wherein the low earth satellite switching control of a transmit beam further comprises:

in the process that the low-orbit satellite moves away from the equatorial plane, after the number of started transmitting beams reaches a preset value, the beams are sequentially closed from the beam closest to the equatorial plane, and simultaneously, the beams are sequentially started from the beam adjacent to the started transmitting beams and far away from the equatorial plane until the started transmitting beams are symmetrical relative to a connecting line of the low-orbit satellite and the geocenter.

6. The beam control method of any one of claims 3 to 5, wherein the low earth satellite switching control of the transmit beam further comprises:

the low earth satellite turns off the beam across the equatorial plane.

7. A low earth orbit satellite configured to switch control of a transmission beam; wherein the content of the first and second substances,

the transmitting direction of the opened transmitting wave beam is a first direction, the direction of the high-orbit satellite transmitting signals to the user terminal covered by the opened transmitting wave beam is a second direction, and the included angle between the first direction and the second direction is larger than the minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

8. The low-earth-orbit satellite of claim 7, wherein the transmission direction of the switched-off transmission beam is a third direction, the transmission direction of the high-earth-orbit satellite to the user terminal corresponding to the switched-off transmission beam is a fourth direction, and an included angle between the third direction and the fourth direction is not greater than a minimum isolation angle between the low-earth-orbit satellite and the high-earth-orbit satellite.

9. The low-earth satellite of claim 8, wherein the low-earth satellite is configured to:

in the process of moving towards the equatorial plane, closing the beams in sequence from the beam farthest from the equatorial plane until all the beams are closed; the beams are turned on in sequence starting from the beam adjacent to the turned on transmission beam and close to the equatorial plane until the beam closest to the equatorial plane is turned on.

10. The low-earth satellite of claim 9, wherein the low-earth satellite is further configured to:

and in the process of moving away from the equatorial plane, starting the beams from the beam closest to the equatorial plane in sequence until the number of the started transmitting beams reaches a preset value.

11. The low-earth satellite of claim 10, wherein the low-earth satellite is further configured to:

and in the process of moving away from the equatorial plane, after the number of the started transmitting beams reaches a preset value, sequentially closing the beams from the beam closest to the equatorial plane, and simultaneously sequentially starting the beams from the beam adjacent to the started transmitting beams and far away from the equatorial plane until the started transmitting beams are symmetrical relative to a connecting line of the low-orbit satellite and the geocenter.

12. The low-earth satellite of any one of claims 9-11, wherein the low-earth satellite is further configured to: the beam across the equatorial plane is turned off.

13. A low earth orbit satellite system comprising a plurality of low earth orbit satellites according to any one of claims 7 to 12.

14. The low earth orbit satellite system of claim 13, wherein the beams turned on by the plurality of low earth orbit satellites continuously cover the user terminals on the ground.

15. A low earth orbit satellite comprising:

a memory; and

a processor coupled to the memory, the processor configured to perform the beam steering method of any of claims 1-6 based on instructions stored in the memory.

16. A computer readable storage medium, wherein the computer readable storage medium stores computer instructions which, when executed by a processor, implement the beam steering method of any of claims 1 to 6.

Technical Field

The present disclosure relates to the field of satellite technologies, and in particular, to a beam control method, a low-earth orbit satellite system, and a computer-readable storage medium.

Background

In recent years, low-earth orbit satellite communication systems have become a new growth point in the field of satellite communications. A low earth orbit satellite communication system generally comprises a constellation consisting of a plurality of communication satellites with orbit heights of 300 to 1500 kilometers, and system equipment such as a matched ground system. The user access terminal transmits wireless signals, the wireless signals are received by a receiving antenna of the low-orbit communication satellite and forwarded to the ground system, and the ground system is accessed to the ground network. Meanwhile, the low earth orbit communication satellite transmits the signal returned by the ground system downwards to the user terminal through the satellite transmitting antenna, and the whole communication process is completed.

Another type of satellite communication system, in addition to low-orbit satellite communication systems, is the high-orbit communication system. High earth orbit communication system satellites are located in geosynchronous orbits, approximately 36000 kilometers in height, above the equator. The communication process of the high orbit satellite communication system is similar to that of the low orbit satellite communication system.

Since both communication system users are located on the ground and the satellite itself has a height difference in the air, there will be a situation where two satellite system user terminals transmit signals and a satellite transmit signal, which cause interference to the satellite and the user terminal of the other satellite system. For example, when a low-earth satellite is operating to a space near the equator, if the low-earth satellite system terminal, the low-earth satellite, and the high-earth satellite are approximately located on the same connection line, the uplink signal transmitted by the low-earth satellite system terminal is received by the high-earth satellite at the same time, and if the two systems use the same frequency band, interference may be caused to the high-earth satellite system. On the contrary, at this time, the high-orbit satellite transmission signal and the low-orbit satellite transmission signal also interfere with two types of terminals on the ground, and the communication quality is affected.

According to the international telecommunications union rules, low earth orbit satellite communication systems are allowed to use the same frequency band as high earth orbit satellite communication systems under certain conditions in consideration of scarcity of space frequency resources, but on the premise that the low earth orbit satellite systems must not interfere with the high earth orbit satellite systems using the same frequency band.

Disclosure of Invention

One technical problem that the present disclosure addresses is how to mitigate interference between a low-earth orbit satellite communication system and a high-earth orbit satellite communication system.

According to an aspect of the embodiments of the present disclosure, there is provided a beam control method, including: the low-orbit satellite performs switch control on the transmitted wave beam; the transmitting direction of the opened transmitting wave beam is a first direction, the direction of the high-orbit satellite transmitting signals to the user terminal covered by the opened transmitting wave beam is a second direction, and an included angle between the first direction and the second direction is larger than the minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

In some embodiments, the transmission direction of the switched-off transmission beam is a third direction, the direction of the high-orbit satellite transmitting signals to the user terminal corresponding to the switched-off transmission beam is a fourth direction, and an included angle between the third direction and the fourth direction is not greater than a minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

In some embodiments, the low earth orbit satellite switching control of the transmit beam comprises: in the process that the low-orbit satellite moves towards the equatorial plane, beams are closed in sequence from the beam farthest from the equatorial plane until all the beams are closed; the beams are turned on in sequence starting from the beam adjacent to the turned on transmission beam and close to the equatorial plane until the beam closest to the equatorial plane is turned on.

In some embodiments, the switching control of the transmit beam by the low earth orbit satellite further comprises: and in the process of moving the low-earth-orbit satellite away from the equatorial plane, starting the beams closest to the equatorial plane in sequence until the number of the started transmitting beams reaches a preset value.

In some embodiments, the switching control of the transmit beam by the low earth orbit satellite further comprises: and in the process of moving the low-orbit satellite away from the equatorial plane, after the number of the started transmitting beams reaches a preset value, sequentially closing the beams from the beam closest to the equatorial plane, and simultaneously sequentially starting the beams from the beam adjacent to the started transmitting beams and far away from the equatorial plane until the started transmitting beams are symmetrical relative to a connecting line of the low-orbit satellite and the geocenter.

In some embodiments, the switching control of the transmit beam by the low earth orbit satellite further comprises: the low earth satellite turns off the beam across the equatorial plane.

According to yet another aspect of an embodiment of the present disclosure, there is provided a low earth orbit satellite configured to switch control of a transmission beam; the transmitting direction of the opened transmitting wave beam is a first direction, the direction of the high-orbit satellite transmitting signals to the user terminal covered by the opened transmitting wave beam is a second direction, and an included angle between the first direction and the second direction is larger than the minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

In some embodiments, the transmission direction of the switched-off transmission beam is a third direction, the direction of the high-orbit satellite transmitting signals to the user terminal corresponding to the switched-off transmission beam is a fourth direction, and an included angle between the third direction and the fourth direction is not greater than a minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

In some embodiments, the low earth orbit satellite is configured to: in the process of moving towards the equatorial plane, closing the beams in sequence from the beam farthest from the equatorial plane until all the beams are closed; the beams are turned on in sequence starting from the beam adjacent to the turned on transmission beam and close to the equatorial plane until the beam closest to the equatorial plane is turned on.

In some embodiments, the low earth orbit satellite is further configured to: and in the process of moving away from the equatorial plane, starting the beams from the beam closest to the equatorial plane in sequence until the number of the started transmitting beams reaches a preset value.

In some embodiments, the low earth orbit satellite is further configured to: and in the process of moving away from the equatorial plane, after the number of the started transmitting beams reaches a preset value, the beams are sequentially closed from the beam closest to the equatorial plane, and simultaneously, the beams are sequentially started from the beam adjacent to the started transmitting beams and far away from the equatorial plane until the started transmitting beams are symmetrical relative to a connecting line of the low-earth-orbit satellite and the geocenter.

In some embodiments, the low earth orbit satellite is further configured to: the beam across the equatorial plane is turned off.

According to another aspect of the embodiments of the present disclosure, there is provided a low-earth satellite system including a plurality of the aforementioned low-earth satellites.

In some embodiments, a plurality of low earth orbit satellites are turned on beams that continuously cover user terminals on the ground.

According to yet another aspect of an embodiment of the present disclosure, there is provided a low earth orbit satellite including: a memory; and a processor coupled to the memory, the processor configured to perform the aforementioned beam steering method based on instructions stored in the memory.

According to yet another aspect of the embodiments of the present disclosure, there is provided a computer-readable storage medium, wherein the computer-readable storage medium stores computer instructions, which when executed by a processor, implement the aforementioned beam steering method.

The present disclosure enables adjustment of the beam coverage area of a low earth orbit satellite through on-off control of a transmission beam by the low earth orbit satellite, thereby mitigating interference between a low earth orbit satellite communication system and a high earth orbit satellite communication system.

Other features of the present disclosure and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.

Drawings

In order to more clearly illustrate the embodiments of the present disclosure or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and for those skilled in the art, other drawings can be obtained according to the drawings without inventive exercise.

Fig. 1 shows a schematic view of the minimum isolation angle.

Figure 2 shows a schematic diagram of turning off a low earth orbit satellite that does not meet the minimum isolation angle requirement.

Figure 3 shows a schematic diagram of a low earth orbit satellite transmit beam.

Fig. 4 shows a beam steering process when a low earth orbit satellite is flying from north to south.

Figure 5 illustrates a schematic structural diagram of a low earth orbit satellite according to some embodiments of the present disclosure.

Detailed Description

The technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure, and it is obvious that the described embodiments are only a part of the embodiments of the present disclosure, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the disclosure, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.

In order to meet the requirement of the international telecommunication union rules on interference avoidance of the high-orbit communication system, interference avoidance measures are required to be taken, so that an included angle formed by a connection line between a user terminal and a low-orbit satellite and an included angle formed by the connection line between the user terminal and the high-orbit satellite is smaller than the requirement of a minimum isolation angle determined by the radiation characteristics of the high-orbit satellite and low-orbit satellite communication systems (hereinafter, the requirement of the minimum isolation angle is simply met), and the interference of the low-orbit satellite system on the high-orbit communication satellite system is reduced. A schematic diagram of the minimum isolation angle is shown in fig. 1.

The inventors have studied interference avoidance measures. On one hand, the frequency interference between the two systems can be avoided by closing the low-orbit satellite with the connection line between the terminal and the low-orbit satellite with the connection line between the terminal and the high-orbit satellite having the included angle smaller than the minimum isolation angle. Figure 2 shows a schematic diagram of turning off a low earth orbit satellite that does not meet the minimum isolation angle requirement. This measure makes it necessary to shut down each orbital satellite when it is moving on the equator, which results in failure to achieve service coverage in a zonal area centered on the equator. On the other hand, when the satellite runs to the vicinity of the equator, the ground coverage area can be moved towards the equator by gradually inclining the satellites on the north and south sides, so that the complete coverage can be still maintained under the condition that one satellite above the equator is closed. Although the global service coverage can be realized by the measure, the low-orbit satellite has a short operation period, the satellite needs to be tilted and overturned twice when operating for one circle, and tens of thousands of times of tilting are performed in the service life period, so that the requirement on the strength of the satellite structure mechanism is high, and particularly when the rotational inertia of the solar sailboard is large, the metal fatigue of the sailboard supporting mechanism can be caused.

In view of this, the inventor provides a beam control method, which can not only realize continuous coverage of beams and services on the ground, but also reduce the complexity of satellite space motion and reduce the failure rate of the satellite.

Some embodiments of the disclosed beam steering method are described first.

In some embodiments, the low earth orbit satellite switches the transmit beam. The transmitting direction of the opened transmitting wave beam is a first direction, the direction of the high-orbit satellite transmitting signals to the user terminal covered by the opened transmitting wave beam is a second direction, and an included angle between the first direction and the second direction is larger than the minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

In some embodiments, the transmission direction of the switched-off transmission beam is a third direction, the direction of the high-orbit satellite transmitting signals to the user terminal corresponding to the switched-off transmission beam is a fourth direction, and an included angle between the third direction and the fourth direction is not greater than a minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

In the above embodiments, the low earth orbit satellite is provided with a signal transmitting device such as an antenna, which can transmit several communication beams to the ground. In the case where the low-earth satellite is not located near the equator (referred to as the general case for short), only the partial beams on both sides with the satellite subsatellite point as the center are turned on, and the total number of the transmission beams that can be formed by the signal transmission device may be more than twice the number of the beams that are turned on in the general state.

In some embodiments, the low earth orbit satellite switching control of the transmit beam comprises: in the process that the low-orbit satellite moves towards the equatorial plane, beams are closed in sequence from the beam farthest from the equatorial plane until all the beams are closed; the beams are turned on in sequence starting from the beam adjacent to the turned on transmission beam and close to the equatorial plane until the beam closest to the equatorial plane is turned on.

And in the process of moving towards the equatorial plane, according to the requirement of the minimum isolation angle, closing the beams which are farthest away from the equatorial plane and do not meet the requirement of the isolation angle in sequence, and simultaneously opening the beams which are adjacent to the opened beams and are closest to the equatorial plane. The above steps are repeated until all the beams close to one side of the equatorial plane are turned on. At this point, the beam located on the turned-on and farthest from the equatorial plane meets the minimum isolation angle requirement.

In some embodiments, the switching control of the transmit beam by the low earth orbit satellite further comprises: the low earth satellite turns off the beam across the equatorial plane.

During the continued movement towards the equatorial plane, the closing of the beams not meeting the minimum isolation angle requirement is continued, while the closing of the beams beyond the equatorial plane is gradually carried out. This is repeated until all beams are turned off. In this case, the satellites moving toward the equatorial plane in the same orbital plane are just the next most distant satellites from the equatorial plane, and thus continuous coverage of the ground by the beams can be ensured.

In some embodiments, the switching control of the transmit beam by the low earth orbit satellite further comprises: and in the process of moving the low-earth-orbit satellite away from the equatorial plane, starting the beams closest to the equatorial plane in sequence until the number of the started transmitting beams reaches a preset value.

In some embodiments, the switching control of the transmit beam by the low earth orbit satellite further comprises: and in the process of moving the low-orbit satellite away from the equatorial plane, after the number of the started transmitting beams reaches a preset value, sequentially closing the beams from the beam closest to the equatorial plane, and simultaneously sequentially starting the beams from the beam adjacent to the started transmitting beams and far away from the equatorial plane until the started transmitting beams are symmetrical relative to a connecting line of the low-orbit satellite and the geocenter.

After the satellite crosses the equatorial plane, the control process of the beam switch moving to the equatorial plane is reversed. For example, the corresponding beams are turned on gradually first, and after the number of beams to be turned on reaches half of the total number of beams, the beam closest to the equatorial plane is turned off gradually, and the beam closest to the turned-on beam and farthest from the equatorial plane is turned on at the same time until the general state is restored.

The embodiment adds the openable emission beam of the low-orbit satellite, and can adjust the beam coverage area of the low-orbit satellite through the on-off control of the low-orbit satellite on the emission beam, so that the emission beam which is always kept open in the whole process that the low-orbit satellite crosses the equatorial plane meets the requirement of the minimum isolation angle, thereby reducing the interference between the low-orbit satellite communication system and the high-orbit satellite communication system. Meanwhile, the low-orbit satellites are covered redundantly, so that the requirement of a low-orbit satellite system for ground continuous coverage is met.

Some specific application examples of the beam steering method of the present disclosure are described below.

In these application examples, the low-orbit satellite runs along the near-polar orbit, and the signal transmitting device can form 32 beam coverage areas on the ground at most. Figure 3 shows a schematic diagram of a low earth orbit satellite transmit beam. The low earth orbit satellite can simultaneously turn on 16 beams, which are numbered 1-32 respectively from the farthest position in the flight direction of the satellite to the farthest position behind the flight direction. In the general case, beams 9-24 are turned on.

Fig. 4 shows a beam steering process when a low earth orbit satellite is flying from north to south. It will be understood by those skilled in the art that the beam steering method of a low earth orbit satellite may be changed accordingly when the satellite is flown from north to south.

The low-orbit satellite is at a certain starting position in the northern hemisphere, and in the coverage area of No. 24 wave beams (note: 8 wave beams in the north and south with the subsatellite point as the center are opening wave beams, and No. 24 is the most northern opening wave beam), the terminal, the low-orbit satellite and the high-orbit satellite meet the requirement of a minimum isolation angle.

The satellite continues to fly southward along the orbit, and based on the satellite orbit characteristics and the transmit beam characteristics, satellite position 1 can be uniquely calculated, and in the south of this position, satellite number 24 beam will not meet the isolation angle requirement. When the satellite is moving to this position, its beam number 24 is turned off, and beam number 8 is turned on at the same time. By analogy, satellite positions 2-8 can be calculated respectively, corresponding to turning off beams 23-17, and turning on beams 7-1, respectively.

At this point, the satellite beam # 1 should be located exactly at the equator. After this, the beams 7 to 1 will gradually not meet the minimum isolation angle requirement, requiring to be switched off in sequence. At the same time, the beam coverage area beyond the equator is considered to be covered by low earth satellites on the south side of the equator, and is also turned off successively.

It should be noted that in this process, the adjacent satellite located in the same orbital plane and north side also starts the beam control operation, and the redundant coverage area between the two satellites can ensure continuous coverage.

After all the transmitted beams of the satellite are turned off, they fly along the orbit beyond the equatorial plane. After crossing the equatorial plane, the beam is gradually turned on according to the isolation angle requirement, contrary to the closing strategy of the north side of the equator, until the general condition is recovered, and the beams 9-24 are turned on.

According to yet another aspect of an embodiment of the present disclosure, there is provided a low earth orbit satellite configured to switch control of a transmission beam; the transmitting direction of the opened transmitting wave beam is a first direction, the direction of the high-orbit satellite transmitting signals to the user terminal covered by the opened transmitting wave beam is a second direction, and an included angle between the first direction and the second direction is larger than the minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

In some embodiments, the transmission direction of the switched-off transmission beam is a third direction, the direction of the high-orbit satellite transmitting signals to the user terminal corresponding to the switched-off transmission beam is a fourth direction, and an included angle between the third direction and the fourth direction is not greater than a minimum isolation angle between the low-orbit satellite and the high-orbit satellite.

In some embodiments, the low earth orbit satellite is configured to: in the process of moving towards the equatorial plane, closing the beams in sequence from the beam farthest from the equatorial plane until all the beams are closed; the beams are turned on in sequence starting from the beam adjacent to the turned on transmission beam and close to the equatorial plane until the beam closest to the equatorial plane is turned on.

In some embodiments, the low earth orbit satellite is further configured to: and in the process of moving away from the equatorial plane, starting the beams from the beam closest to the equatorial plane in sequence until the number of the started transmitting beams reaches a preset value.

In some embodiments, the low earth orbit satellite is further configured to: and in the process of moving away from the equatorial plane, after the number of the started transmitting beams reaches a preset value, the beams are sequentially closed from the beam closest to the equatorial plane, and simultaneously, the beams are sequentially started from the beam adjacent to the started transmitting beams and far away from the equatorial plane until the started transmitting beams are symmetrical relative to a connecting line of the low-earth-orbit satellite and the geocenter.

In some embodiments, the low earth orbit satellite is further configured to: the beam across the equatorial plane is turned off.

According to another aspect of the embodiments of the present disclosure, there is provided a low-earth satellite system including a plurality of the aforementioned low-earth satellites.

In some embodiments, a plurality of low earth orbit satellites are turned on beams that continuously cover user terminals on the ground.

Some embodiments of the disclosed low earth orbit satellites are described below in conjunction with fig. 5.

Figure 5 illustrates a schematic structural diagram of a low earth orbit satellite according to some embodiments of the present disclosure. As shown in fig. 5, the beam steering apparatus 50 of this embodiment includes: a memory 510 and a processor 520 coupled to the memory 510, the processor 520 being configured to perform the beam steering method of any of the foregoing embodiments based on instructions stored in the memory 510.

Memory 510 may include, for example, system memory, fixed non-volatile storage media, and the like. The system memory stores, for example, an operating system, an application program, a Boot Loader (Boot Loader), and other programs.

The beam steering apparatus 50 may further include an input-output interface 530, a network interface 540, a storage interface 550, and the like. These interfaces 530, 540, 550 and the connections between the memory 510 and the processor 520 may be, for example, via a bus 560. The input/output interface 530 provides a connection interface for input/output devices such as a display, a mouse, a keyboard, and a touch screen. The network interface 540 provides a connection interface for various networking devices. The storage interface 550 provides a connection interface for external storage devices such as an SD card and a usb disk.

The present disclosure also includes a computer readable storage medium having stored thereon computer instructions which, when executed by a processor, implement the beam steering method of any of the foregoing embodiments.

The present disclosure is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the disclosure. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.

These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.

These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.

The above description is only exemplary of the present disclosure and is not intended to limit the present disclosure, so that any modification, equivalent replacement, or improvement made within the spirit and principle of the present disclosure should be included in the scope of the present disclosure.