Communication method and apparatus

Abstract

Provided in the present disclosure are communication methods and apparatus. A method comprises: in response to a first signal sent by a second satellite, acquiring a first initial point ahead angle of a first satellite with respect to the second satellite and, according to the first initial point ahead angle, sending a second signal to the second satellite; according to the angle of a light beam main lobe in the second signal at a first full width at half maximum and the first initial point ahead angle, determining a first target point ahead angle; according to the first target point ahead angle, sending a third signal to the second satellite; and, in response to a fourth signal sent by the second satellite, sending to the second satellite a fifth signal carrying first communication data, the fifth signal being used for sending of a sixth signal. Thus, the present disclosure achieves point ahead orientation for a satellite having a coaxial structure of a transmitting optical axis and a receiving optical axis, corrects the first initial point ahead angle, and accurately controls the point ahead, thereby improving the applicability of the method.

Description

Communication method and device

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS

[0002] This application claims priority to the Chinese patent application filed with the State Intellectual Property Office of the People's Republic of China on November 15, 2023, with application number 202311527277.5 and application name "Communication Method and Device", all contents of which are incorporated by reference into this application. Technical Field

[0003] The present disclosure relates to the field of satellite communication technology, and in particular to a communication method and device. Background Art

[0004] In satellite communications, due to the relative motion between satellites, the transmitting satellite needs to pre-calculate the instantaneous advance aiming angle, and use the angle at which the outgoing beacon light deviates from the incident beacon light as the advance aiming angle, so that the emitted beacon light can accurately reach the receiving satellite.

[0005] In related technologies, the transmitting optical axis and the receiving optical axis on the satellite are independent of each other, and the corresponding advance aiming angles are calculated separately to perform advance aiming control. However, the above method is not applicable to satellites with antennas whose transmitting optical axis and the receiving optical axis are co-axial structures.

[0006] Summary of the Invention

[0007] The present disclosure provides a communication method and device for achieving precise control of advanced aiming of a satellite in a co-optical axis structure.

[0008] A first aspect of the present disclosure provides a communication method, applied to a first satellite, including:

[0009] In response to a first signal sent by a second satellite, a first initial advance aiming angle of the first satellite relative to the second satellite is obtained, and a second signal is sent to the second satellite based on the first initial advance aiming angle, wherein the first signal and the second signal include multiple incompletely coherent beam signals; a first target advance aiming angle is determined based on the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance aiming angle; based on the first target advance aiming angle, a third signal is sent to the second satellite so that the second satellite sends a fourth signal based on the third signal; wherein the third signal and the fourth signal include coherent beam signals; in response to the fourth signal sent by the second satellite, a fifth signal carrying first communication data is sent to the second satellite; wherein the fifth signal is used for the second satellite to send a sixth signal carrying second communication data, and the fifth signal and the sixth signal include coherent beam signals.

[0010] The above scheme calculates a first initial advance pointing angle of the first satellite relative to the second satellite based on a received first signal transmitted by the second satellite, and transmits a second signal to the second satellite based on the first initial advance pointing angle, thereby achieving advance pointing of a satellite having an antenna with a co-axial transmission and reception optical axes. Furthermore, a first target advance pointing angle is determined based on the first half-width angle of the main lobe of the beam in the second signal and the first initial advance pointing angle, thereby correcting the first initial advance pointing angle. Based on the corrected first target advance pointing angle, a third signal is transmitted to the second satellite so that the second satellite accurately receives the third signal, thereby achieving precise control of the advance pointing of the co-axial satellite. Furthermore, upon receiving a fourth signal transmitted by the second satellite, a fifth signal carrying the first communication data is transmitted to the second satellite, and upon receiving the fifth signal by the second satellite, a sixth signal carrying the second communication data is transmitted to the first satellite. This method achieves satellite communication based on the accurate establishment of a communication link between the first satellite and the second satellite having an antenna with a co-axial transmission and reception optical axes, thereby improving the applicability of the method.

[0011] A second aspect of the present disclosure provides a communication method, applied to a second satellite, including:

[0012] A first signal is sent to a first satellite so that the first satellite acquires a first initial advance aiming angle relative to the second satellite based on the first signal, and sends a second signal to the second satellite based on the first initial advance aiming angle; wherein the first signal includes multiple incompletely coherent beam signals; a second signal is received from the first satellite; wherein the second signal includes multiple incompletely coherent beam signals; a fourth signal is sent to the first satellite in response to a third signal sent by the first satellite based on the first target advance aiming angle; wherein the first target advance aiming angle is determined by the first satellite based on the first half-width at half-maximum angle of the main lobe of the beam in the second signal and the first initial advance aiming angle, and the third signal and the fourth signal include coherent beam signals; and a sixth signal is sent to the first satellite in response to a fifth signal carrying first communication data sent by the first satellite, carrying second communication data, wherein the fifth signal is sent by the first satellite in response to the fourth signal, and the fifth signal and the sixth signal include coherent beam signals.

[0013] An embodiment of the third aspect of the present disclosure proposes a communication device, which is applied to a first satellite, and includes: a processing module, used to obtain a first initial advance aiming angle of the first satellite relative to the second satellite in response to a first signal sent by a second satellite, and send a second signal to the second satellite based on the first initial advance aiming angle, wherein the first signal and the second signal include multiple incompletely coherent beam signals; a first determination module, used to determine a first target advance aiming angle based on the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance aiming angle; a first sending module, used to send a third signal to the second satellite based on the first target advance aiming angle, so that the second satellite sends a fourth signal based on the third signal; wherein the third signal and the fourth signal include coherent beam signals; a second sending module, used to send a fifth signal carrying first communication data to the second satellite in response to the fourth signal sent by the second satellite; wherein the fifth signal is used for the second satellite to send a sixth signal carrying second communication data, and the fifth signal and the sixth signal include coherent beam signals.

[0014] A fourth aspect of the present disclosure provides a communication device, which is applied to a second satellite and includes: an acquisition module for sending a first signal to a first satellite, so that the first satellite acquires a first initial advance aiming angle relative to the second satellite based on the first signal, and sends a second signal to the second satellite according to the first initial advance aiming angle; wherein the first signal includes a plurality of incompletely coherent beam signals; a first determination module for receiving the second signal sent by the first satellite; wherein the second signal includes a plurality of incompletely coherent beam signals; a sending module for sending a third signal to the first satellite in response to the third signal sent by the first satellite according to the first target advance aiming angle; The satellite sends a fourth signal; wherein, the first target advance aiming angle is sent by the first satellite according to the first target advance aiming angle, the first target advance aiming angle is determined according to the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance aiming angle, and the third signal and the fourth signal include coherent beam signals; a receiving module is used to respond to the fifth signal carrying the first communication data sent by the first satellite and send a sixth signal carrying the second communication data to the first satellite, wherein the fifth signal is sent by the first satellite in response to the fourth signal, and the fifth signal and the sixth signal include coherent beam signals.

[0015] The fifth aspect embodiment of the present disclosure proposes an electronic device, including a memory, a processor, and a computer program stored in the memory and capable of running on the processor. When the processor executes the computer program, it implements the communication method described in the first aspect embodiment of the present disclosure, or implements the communication method described in the second aspect embodiment of the present disclosure.

[0016] The sixth aspect embodiment of the present disclosure proposes a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, it implements the communication method as described in the first aspect embodiment of the present disclosure, or implements the communication method as described in the second aspect embodiment of the present disclosure.

[0017] The seventh aspect embodiment of the present disclosure proposes a computer program product. When the instruction processor in the computer program product executes, it implements the communication method described in the first aspect embodiment of the present disclosure, or implements the communication method described in the second aspect embodiment of the present disclosure.

[0018] Additional aspects and advantages of the present disclosure will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0020] FIG1 is an interactive flow chart of a first communication method provided by an embodiment of the present disclosure;

[0021] FIG2 is a schematic diagram of a first initial leading aiming angle provided by an embodiment of the present disclosure;

[0022] FIG3 is an interactive flow chart of a second communication method provided in an embodiment of the present disclosure;

[0023] FIG4 is an interactive flow chart of a third communication method provided in an embodiment of the present disclosure;

[0024] FIG5 is a schematic diagram of a vector phased array antenna provided by an embodiment of the present disclosure;

[0025] FIG6 is a schematic diagram of emitting a light beam at an advanced aiming angle according to an embodiment of the present disclosure;

[0026] FIG7 is an interactive flow chart of a fourth communication method provided in an embodiment of the present disclosure;

[0027] FIG8 is a flow chart of a first communication method provided by an embodiment of the present disclosure;

[0028] FIG9 is a schematic diagram of a flow chart of a second communication method provided in an embodiment of the present disclosure;

[0029] FIG10 is a schematic structural diagram of a communication device provided in an embodiment of the present disclosure;

[0030] FIG11 is a schematic structural diagram of another communication device provided in an embodiment of the present disclosure;

[0031] Fig. 12 is a block diagram of an electronic device for communication according to an exemplary embodiment. DETAILED DESCRIPTION

[0032] The following describes in detail embodiments of the present disclosure, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present disclosure, and should not be construed as limiting the present disclosure.

[0033] Due to relative motion between satellites, laser communication terminals on satellites must consider the lead sight angle during tracking. This angle causes slight real-time changes in the beam axis, typically achieved through a lead sight. Fine-tuning the lead sight compensates for angular differences caused by the satellite's orbital motion and beam propagation delays, and the beam is then transmitted by the optical antenna in the reverse direction of the incident light.

[0034] In related technologies, the advanced aiming system pre-calculates the instantaneous advanced aiming angle based on the ephemeris table and the relative motion speed of the satellite and ground terminals. The angle at which the outgoing beacon light deviates from the incoming beacon light is used as the advanced aiming angle, ensuring that the emitted beacon light accurately reaches the other terminal. The advanced aiming detector first detects the angular difference between the optical axis of the outgoing beacon light and the optical axis of the incoming beacon light, and transmits this information to the advanced aiming controller. This controller then controls the deflection of the advanced aiming mirror until the angle at which the optical axis of the emitted light deviates from the optical axis of the received beacon light reaches the required advanced aiming angle, completing the advanced aiming process. Using beacon light to assist in operations such as capture, tracking, and alignment requires a high-power beacon laser, increasing the payload weight and structural complexity.

[0035] At the same time, the transmitting optical axis and receiving optical axis on the satellite are independent of each other, and the corresponding advance aiming angles are calculated separately to perform advance aiming control. However, the above method is not applicable to satellites with phased array antennas using a common optical axis structure.

[0036] Therefore, to address the above problems, the present disclosure proposes a communication method and device.

[0037] The communication method and apparatus according to the embodiments of the present disclosure will be described below with reference to the accompanying drawings.

[0038] FIG1 is an interactive flow chart of a communication method provided by an embodiment of the present disclosure. As shown in FIG1 , the communication method may include the following steps:

[0039] Step 101: A second satellite sends a first signal to a first satellite.

[0040] Step 102: The first satellite obtains a first initial leading aiming angle of the first satellite relative to the second satellite in response to the first signal.

[0041] Step 103: The first satellite sends a second signal to the second satellite according to the first initial advance aiming angle.

[0042] The first signal and the second signal include a plurality of incompletely coherent beam signals.

[0043] To achieve advanced pointing of the satellite, as an example, in response to a first signal sent by a second satellite, a first initial advanced pointing angle of the first satellite relative to the second satellite may be obtained, and a second signal may be sent to the second satellite based on the first initial advanced pointing angle. The first signal and the second signal may include multiple incompletely coherent beam signals.

[0044] The first satellite may obtain a target distance between the first satellite and the second satellite based on the received first signal, and determine a first initial advance aiming angle of the first satellite relative to the second satellite according to the target distance.

[0045] As shown in FIG. 2 , assuming that the first satellite is satellite A and the second satellite is satellite B, the target distance between satellite A and satellite B is Z, where Z = c*Δt, where c represents the speed of light. The relative speed of satellite B to satellite B′ is w. The relative angle of satellite B's motion within time Δt is β*Δt, and the first initial advance aiming angle of the first satellite relative to the second satellite is w*Δt.

[0046] Step 104: The first satellite determines a first target advance aiming angle according to the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance aiming angle.

[0047] To achieve precise control of the satellite's advanced aiming, the first initial advanced aiming angle can be corrected based on the angle at half-width of the main lobe of the beam in the second signal to determine the first target advanced aiming angle. This embodiment corrects the first initial advanced aiming angle based on the angle at half-width of the main lobe of the beam in the second signal, resulting in a more accurate first target advanced aiming angle.

[0048] Step 105: The first satellite sends a third signal to the second satellite according to the first target advance aiming angle.

[0049] Step 106: The second satellite sends a fourth signal to the first satellite in response to the third signal.

[0050] The third signal and the fourth signal include coherent beam signals.

[0051] In order to accurately complete the communication link establishment between the first satellite and the second satellite including the antenna of the co-optical axis structure and perform satellite communication, as an example, the first satellite sends a third signal to the second satellite based on the first target advance aiming angle; the second satellite can accurately receive the third signal, and after receiving the third signal, the second satellite can send a fourth signal to the first satellite.

[0052] Step 107: The first satellite sends a fifth signal carrying the first communication data to the second satellite in response to the fourth signal sent by the second satellite.

[0053] Step 108: The second satellite transmits a sixth signal carrying second communication data to the first satellite in response to the fifth signal.

[0054] The fifth signal and the sixth signal include coherent beam signals.

[0055] In this embodiment, when the first satellite receives the fourth signal sent by the second satellite, it sends a fifth signal carrying the first communication data to the second satellite; and then the second satellite responds to the received fifth signal and sends a sixth signal carrying the second communication data to the first satellite.

[0056] As a possible implementation method, the first satellite can send the second signal, the third signal, and the fifth signal through a phased array antenna, and receive the first signal, the fourth signal, and the sixth signal sent by the second satellite through the phased array antenna. The second satellite can send the first signal, the fourth signal, and the sixth signal through the phased array antenna, and receive the second signal, the third signal, and the fifth signal sent by the first satellite through the phased array antenna.

[0057] As an example, the second signal, the third signal, and the fifth signal are phased array signals sent by the first satellite through the first phased array antenna, and the first signal, the fourth signal, and the sixth signal are phased array signals received by the first satellite through the first phased array antenna; the first signal, the fourth signal, and the sixth signal are phased array signals sent by the second satellite through the second phased array antenna, and the second signal, the third signal, and the fifth signal are phased array signals received by the second satellite through the second phased array antenna.

[0058] In summary, the first satellite calculates a first initial advance pointing angle of the first satellite relative to the second satellite based on the received first signal transmitted by the second satellite, and transmits a second signal to the second satellite based on the first initial advance pointing angle, thereby achieving advance pointing of the satellite including an antenna with a co-axial structure for the transmitting and receiving optical axes. Furthermore, the first target advance pointing angle is determined based on the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance pointing angle, thereby correcting the first initial advance pointing angle. Based on the corrected first target advance pointing angle, the first satellite transmits a third signal to the second satellite so that the second satellite accurately receives the third signal, thereby achieving precise control of the advance pointing of the satellite including an antenna with a co-axial structure. Furthermore, upon receiving a fourth signal transmitted by the second satellite, the first satellite transmits a fifth signal carrying the first communication data to the second satellite, and upon receiving the fifth signal, the second satellite transmits a sixth signal carrying the second communication data to the first satellite. This achieves satellite communication based on accurately completing the communication link establishment between the first satellite and the second satellite with an antenna with a co-axial structure for the transmitting and receiving optical axes, thereby improving the applicability of the method.

[0059] To clearly illustrate how the embodiment determines the first target advance aiming angle based on the first half-width angle of the main lobe of the beam in the second signal and the first initial advance aiming angle, the present disclosure proposes a second communication method. As shown in FIG3 , the communication method may include the following steps:

[0060] Step 301: A second satellite sends a first signal to a first satellite.

[0061] Step 302: The first satellite obtains a first initial leading aiming angle of the first satellite relative to the second satellite in response to the first signal.

[0062] Step 303: The first satellite sends a second signal to the second satellite according to the first initial advanced aiming angle.

[0063] The first signal and the second signal include a plurality of incompletely coherent beam signals.

[0064] It should be noted that to obtain signal light with a large divergence angle and improve advanced aiming accuracy, the second signal can be obtained by adding perturbations to multiple incoherent beam signals, with the light intensity distribution of each beam signal in the second signal being uniform. Similarly, the first signal can also be obtained by adding perturbations to multiple incoherent beam signals, with the light intensity distribution of each beam signal in the first signal being uniform.

[0065] Step 304: The first satellite obtains the angle of the first half-width of the main lobe of the light beam in the second signal.

[0066] As an example, the first satellite determines a target beam signal from all beam signals in the second signal and obtains the divergence angle of the target beam signal; then, based on the divergence angle, determines the angle at half maximum width of the main lobe of the beam in the second signal. It should be noted that the angle at half maximum width of the main lobe of the beam in the second signal may be positively correlated with the divergence angle of the target beam signal. The target beam signal may be any beam signal in the second signal, or may be a designated beam signal (e.g., a main lobe beam) of the second signal. This disclosure does not specifically limit this.

[0067] For example, the second signal is N, where N and M are positive integers. The divergence angle of the target beam signal in the second signal can be expressed as θ trac =2.44λ / D1, where λ represents the wavelength of the target beam signal and D1 is the diameter of the vector antenna transmitting the second signal. The angle at the first half-height width of the main lobe of the second signal and the divergence angle θ of the target beam signal trac There is a positive correlation, that is, θ trac The larger the value is, the larger the angle of the first half-height width of the main lobe of the beam in the second signal is.

[0068] It's also important to note that phased array antennas have a matrix structure and can achieve three-dimensional vector scanning in the Tip / Tilt / Piston (TTP) directions. Tip generally refers to the horizontal angle change of each antenna element in the array. Tilt generally refers to the elevation angle change of each antenna element in the array. Piston generally refers to the phase change in the beam transmission direction of each antenna element in the array. By adjusting these three directions, beam phase scanning can be achieved, changing the array's beam direction.

[0069] Step 305: The first satellite determines whether the first initial advanced aiming angle is greater than the first half-width angle.

[0070] In this embodiment, the first initial advance aiming angle is compared with the angle at the first half-width to determine whether the first initial advance aiming angle is greater than the angle at the first half-width.

[0071] In step 306, if the first satellite determines that the first initial advance aiming angle is greater than the first half-width angle, the first satellite adjusts the first initial advance aiming angle to obtain a first target advance aiming angle.

[0072] In order to achieve precise control of the satellite's advance aiming, as an example, when the first initial advance aiming angle is greater than the angle at the first half-width, the first closed-loop tracking point corresponding to the incoherent beam transmitted by the first satellite and the second closed-loop tracking point corresponding to the incoherent beam received are obtained; according to the first closed-loop tracking point and the second closed-loop tracking point, the first initial advance aiming angle is adjusted to obtain the first target advance aiming angle; wherein, the transmitting light beam emitted at the first target advance aiming angle coincides with the first closed-loop tracking point, and the receiving light beam received at the first target advance aiming angle coincides with the second closed-loop tracking point.

[0073] That is to say, when the first initial advance aiming angle is greater than the angle at the first half-width, the transmitting beam pointing angle (advance aiming angle) and the closed-loop tracking point of the receiving beam can be corrected by adjusting the Piston of the phased array antenna of the first satellite, so that the transmitting beam can realize the advanced aiming angle pointing through phase control, and the receiving beam can realize the closed-loop tracking angle of the receiving beam through phase control, which is a beam angle different from the transmitting beam pointing angle. At this time, the transmitting and receiving beam gains are respectively maximized.

[0074] As another example, when the first initial leading aiming angle is less than or equal to the angle at the first half-width, the first initial leading aiming angle is used as the first target leading aiming angle.

[0075] That is to say, when the first initial advance aiming angle is less than or equal to the angle at the first half-height width, the first initial advance aiming angle is used as the first target advance aiming angle, so that the optical power of the transmitted light beam reaching the other party is close to the optical power received by the other party.

[0076] Step 307: The first satellite sends a third signal to the second satellite according to the first target advance aiming angle.

[0077] Step 308: The second satellite sends a fourth signal to the first satellite in response to the third signal.

[0078] The third signal and the fourth signal include coherent beam signals.

[0079] Step 309: The first satellite sends a fifth signal carrying the first communication data to the second satellite in response to the fourth signal sent by the second satellite.

[0080] Step 310: The second satellite transmits a sixth signal carrying second communication data to the first satellite in response to the fifth signal.

[0081] The fifth signal and the sixth signal include coherent beam signals.

[0082] It should be noted that the implementation of steps 307 to 310 may refer to other embodiments, and the embodiments of the present disclosure do not limit this and will not be described in detail.

[0083] In summary, by obtaining the angle of the first half-width at the height of the main lobe of the light beam in the second signal; judging whether the first initial advance aiming angle is greater than the angle at the first half-width; adjusting the first initial advance aiming angle when the first initial advance aiming angle is greater than the angle at the first half-width to obtain the first target advance aiming angle, thereby, when the first initial advance aiming angle is greater than the angle at the first half-width, correcting the first initial advance aiming angle, and sending the third signal to the second satellite according to the corrected first target advance aiming angle, so that the second satellite accurately receives the third signal, thereby achieving precise control of the satellite's advance aiming, and at the same time achieving the need to use beacon light to assist in completing operations such as capture, tracking, and alignment, thereby reducing the complexity of advance aiming.

[0084] To clearly illustrate how the above embodiment sends a fifth signal carrying the first communication data to the second satellite in response to the fourth signal sent by the second satellite, the present disclosure proposes a third communication method. As shown in FIG4 , the communication method may include the following steps:

[0085] Step 401: The second satellite sends a first signal to the first satellite.

[0086] Step 402: The first satellite obtains a first initial leading aiming angle of the first satellite relative to the second satellite in response to a first signal sent by the second satellite.

[0087] Step 403: The first satellite sends a second signal to the second satellite according to the first initial advanced aiming angle.

[0088] The first signal and the second signal include a plurality of incompletely coherent beam signals.

[0089] In step 404 , the first satellite determines a first target advance aiming angle according to the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance aiming angle.

[0090] Step 405: The first satellite sends a third signal to the second satellite according to the first target advance aiming angle.

[0091] Step 406: The second satellite sends a fourth signal to the first satellite in response to the third signal.

[0092] The third signal and the fourth signal include coherent beam signals.

[0093] Step 407: The first satellite responds to the fourth signal sent by the second satellite and determines the second target leading aiming angle according to the second half-width angle of the main lobe of the light beam in the third signal and the first target leading aiming angle.

[0094] As an example, when the first target advance aiming angle is greater than the angle at the second half-width, the third closed-loop tracking point corresponding to the first satellite's transmitted coherent beam and the fourth closed-loop tracking point corresponding to the received coherent beam are obtained; according to the third closed-loop tracking point and the fourth closed-loop tracking point, the first target advance aiming angle is adjusted to obtain the second target advance aiming angle; wherein, the transmitting light beam emitted at the second target advance aiming angle coincides with the third closed-loop tracking point, and the receiving light beam received at the second target advance aiming angle coincides with the fourth closed-loop tracking point.

[0095] It should be understood that when the beams are coherently superimposed, the divergence angle θ of the signal light trac = 2.44λ / ND2, where D2 is the diameter of the vector antenna transmitting the third signal, N is the number of elements, and λ is the wavelength. After coherent multi-beam combining, the center of the far-field main lobe of the beam is the beam pointing direction. The beam is fully coherent, and the main lobe beam divergence angle decreases. Because the divergence angle of the signal light is positively correlated with the angle at half-width (FWHM) of the main lobe of the third signal, the angle at half-width (FWHM) of the main lobe of the beam decreases.

[0096] Therefore, it is possible to determine whether the first target's advanced aiming angle is greater than the second half-width angle of the main lobe of the beam in the third signal. If the first target's advanced aiming angle is greater than the second half-width angle, the first satellite's vector antenna's Piston direction phase can be changed to adjust the transmitted beam's spot within the transmitting phase monitoring camera to a calibrated closed-loop tracking point (the third closed-loop tracking point), thereby maximizing the transmitted beam's optical power. Simultaneously, the receiving section's transmitting (TR) high-speed phase shifter is controlled to adjust the received beam's spot within the receiving phase monitoring camera to a calibrated closed-loop tracking point (the fourth closed-loop tracking point), thereby maximizing the received beam's optical power. Thus, through Piston direction control, the transmitted beam emitted at the second target's advanced aiming angle coincides with the third closed-loop tracking point, and the received beam received at the second target's advanced aiming angle coincides with the fourth closed-loop tracking point, thereby improving the accuracy of advanced aiming control.

[0097] Step 408: The first satellite sends a fifth signal carrying the first communication data to the second satellite according to the second target advance aiming angle.

[0098] Step 409: The second satellite transmits a sixth signal carrying second communication data to the first satellite in response to the fifth signal.

[0099] The fifth signal and the sixth signal include coherent beam signals.

[0100] In summary, by responding to the fourth signal sent by the second satellite, it is determined whether the advance aiming angle of the first target is greater than the angle at the second half-width of the main lobe of the beam in the third signal; when the advance aiming angle of the first target is greater than the angle at the second half-width, the third closed-loop tracking point corresponding to the coherent beam transmitted by the first satellite and the fourth closed-loop tracking point corresponding to the coherent beam received are obtained; according to the third closed-loop tracking point and the fourth closed-loop tracking point, the advance aiming angle of the first target is adjusted to obtain the advance aiming angle of the second target; wherein, the transmitting beam emitted at the advance aiming angle of the second target coincides with the third closed-loop tracking point, and the receiving beam received at the advance aiming angle of the second target coincides with the fourth closed-loop tracking point. Therefore, according to the third closed-loop tracking point and the fourth closed-loop tracking point, the advance aiming angle of the first target is adjusted to achieve the coincidence of the transmitting beam emitted at the advance aiming angle of the second target with the third closed-loop tracking point, and the receiving beam received at the advance aiming angle of the second target coincides with the fourth closed-loop tracking point, thereby improving the advance aiming control accuracy.

[0101] Based on any embodiment of the present disclosure, as shown in FIG5 , taking the vector antenna of the first satellite as an example of 4×4, the present disclosure can also implement the communication method of the embodiment of the present disclosure according to the following steps. The specific steps are as follows:

[0102] 1. According to the ephemeris and the relative motion speed of the satellite and the ground terminal, the instantaneous leading aiming angle α is calculated in advance;

[0103] 2. As shown in Figure 6, a coordinate system is established based on the positions of the laser terminal antenna of the current satellite A (first satellite) and the laser terminal receiving antenna of the satellite B (second satellite). The far-field center direction of the main lobe of the laser terminal antenna transmitting the beam of the current satellite is the beam exit direction, which is equal to half of the advanced aiming angle α.

[0104] 3. In the incomplete coherent superposition process, the divergence angle (the field of view angle of the receiving optical antenna) is obtained as: θ trac =2.44λ / D;

[0105] Where λ is the wavelength of the predetermined incoherent (or coherent) beam, D is the diameter of the vector antenna, and when D = 8 mm, θ trac =472urad;

[0106] When the optical multi-beam is not completely coherent, the Tip / Tilt item is changed so that the optical axis of the outgoing beam is pointed at half the leading aiming angle. When the angle at half-width of the main lobe of the beam is greater than or equal to the leading aiming angle, the optical power of the transmitted beam reaching the other party is close to the optical power received by the other party. When the angle at half-width of the main lobe of the beam is less than the leading aiming angle, the light spot of the receiving beam in the receiving phase monitoring camera is adjusted to the pre-calibrated closed-loop tracking point by changing the Piston direction phase. At the closed-loop tracking point, the received beam power is maximized.

[0107] 4. The far-field beams are completely coherently superimposed, and the divergence angles of the beams in the tracking and communication stages can be calculated as: θ trac =2.44λ / ND, where N=8, then θ trac =59urad;

[0108] Since the main lobe width of the outgoing beam becomes narrower when the current satellite transmits a coherent beam, the high-speed phase shifter of the transmitting part of the transmitting beam is controlled to adjust the light spot of the transmitting beam in the transmitting phase monitoring camera to the calibrated closed-loop tracking point by changing the Piston direction phase, so that the optical power of the transmitting beam is maximized. At the same time, the high-speed phase shifter of the receiving part is controlled to adjust the light spot of the receiving beam in the receiving phase monitoring camera to the calibrated closed-loop tracking point, so that the optical power of the receiving beam is maximized.

[0109] FIG7 is an interactive flow chart of a communication method provided by an embodiment of the present disclosure. As shown in FIG7 , the communication method may include the following steps:

[0110] Step 701: The second satellite acquires a second initial advance aiming angle relative to the first satellite, and sends a first signal to the first satellite according to the second initial advance aiming angle.

[0111] The first signal includes a plurality of incompletely coherent beam signals.

[0112] To achieve advanced pointing of the second satellite relative to the first satellite, as an example, a second initial advanced pointing angle of the second satellite relative to the first satellite may be determined based on the distance between the second satellite and the first satellite. Based on the second initial advanced pointing angle, a first signal is transmitted to the first satellite, the first signal including multiple incompletely coherent beam signals. The second initial advanced pointing angle may be equal to or different from the first initial advanced pointing angle.

[0113] Step 702: The first satellite obtains a first initial leading aiming angle of the first satellite relative to the second satellite in response to the first signal.

[0114] Step 703: The first satellite sends a second signal to the second satellite according to the first initial advance aiming angle.

[0115] The first signal and the second signal include a plurality of incompletely coherent beam signals.

[0116] Step 704: The second satellite determines a third target advance aiming angle according to the third half-width angle of the main lobe of the light beam in the first signal and the second initial advance aiming angle.

[0117] A third target advance aiming angle is determined according to the third half-width angle of the main lobe of the light beam in the first signal and the second initial advance aiming angle; and a fourth signal is sent to the first satellite according to the third target advance aiming angle.

[0118] In some optional implementations, the angle at the third half-width of the main lobe of the light beam in the first signal may be compared with the second initial leading aiming angle. When the second initial leading aiming angle is greater than the angle at the third half-width of the main lobe of the light beam in the first signal, the second initial leading aiming angle may be adjusted to obtain a third target leading aiming angle.

[0119] When the second initial advance aiming angle is less than or equal to the angle of the third half-height width of the main lobe of the light beam in the first signal, the second initial advance aiming angle is used as the third target advance aiming angle.

[0120] In some optional implementations, a fifth closed-loop tracking point corresponding to the incoherent beam transmitted by the second satellite and a sixth closed-loop tracking point corresponding to the incoherent beam received by the second satellite are obtained;

[0121] According to the fifth closed-loop tracking point and the sixth closed-loop tracking point, the second initial advance aiming angle is adjusted to obtain the third target advance aiming angle; wherein, the transmitting light beam emitted at the third target advance aiming angle coincides with the closed-loop tracking point corresponding to the incoherent beam emitted by the second satellite, and the receiving light beam received at the third target advance aiming angle coincides with the closed-loop tracking point corresponding to the incoherent beam received by the second satellite.

[0122] Step 705: The first satellite determines a first target advance aiming angle according to the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance aiming angle.

[0123] Step 706: The first satellite sends a third signal to the second satellite according to the first target advance aiming angle.

[0124] Step 707: The second satellite sends a fourth signal to the first satellite in response to the third signal.

[0125] The third signal and the fourth signal include coherent beam signals.

[0126] To establish a communication link between the first satellite and the second satellite, as an example, in response to the third signal sent by the first satellite, a fourth signal is sent to the first satellite according to the third target advance aiming angle.

[0127] Step 708: The first satellite sends a fifth signal carrying the first communication data to the second satellite in response to the fourth signal sent by the second satellite.

[0128] Step 709: The second satellite sends a sixth signal carrying second communication data to the first satellite in response to the fifth signal.

[0129] The fifth signal and the sixth signal include coherent beam signals.

[0130] In an embodiment of the present disclosure, after the first satellite receives the fourth signal, it sends a fifth signal carrying the first communication data to the second satellite. Thus, the second satellite can receive the fifth signal carrying the first communication data sent by the first satellite, and in response to the fifth signal carrying the first communication data sent by the first satellite, send a sixth signal carrying the second communication data to the first satellite.

[0131] It should be noted that, in order to further improve the advanced aiming control of the second satellite, before receiving the fifth signal carrying the first communication data sent by the first satellite, it is determined whether the advanced aiming angle of the third target is greater than the angle at half maximum width of the main lobe of the light beam in the fourth signal;

[0132] When the third target leading aiming angle is greater than the angle at half-height width of the main lobe of the light beam in the fourth signal, adjusting the third target leading aiming angle to obtain a fourth target leading aiming angle; otherwise, the third target leading aiming angle is used as the fourth target leading aiming angle;

[0133] A sixth signal is sent to the first satellite at a fourth target advance aiming angle.

[0134] In some optional embodiments, a transmit beam transmitted at the fourth target advance aiming angle coincides with a closed-loop tracking point of a coherent beam transmitted by the second satellite, and a receive beam received at the fourth target advance aiming angle coincides with a closed-loop tracking point of a coherent beam received by the second satellite. The second satellite transmits a sixth signal to the first satellite based on the fourth target advance aiming angle.

[0135] In summary, by obtaining a second initial advance pointing angle of the second satellite relative to the first satellite and sending a first signal to the first satellite based on the second initial advance pointing angle; determining a third target advance pointing angle based on the third half-width angle of the main lobe of the light beam in the first signal and the second initial advance pointing angle in response to the second signal sent by the first satellite; sending a fourth signal to the first satellite based on the third target advance pointing angle in response to the third signal sent by the first satellite; and sending a sixth signal carrying second communication data to the first satellite in response to the fifth signal carrying first communication data sent by the first satellite. Thus, the second satellite sends the first signal to the first satellite using the second initial advance pointing angle. The first satellite can calculate the first initial advance pointing angle of the first satellite relative to the second satellite based on the received first signal transmitted by the second satellite and transmit the second signal to the second satellite based on the first initial advance pointing angle, thereby achieving advance pointing of the satellite including the antenna having a co-optical axis structure. Furthermore, the first target advance pointing angle is determined based on the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance pointing angle, thereby correcting the first initial advance pointing angle. Based on the corrected first target advance pointing angle, A third signal is sent to the second satellite so that the second satellite accurately receives the third signal, thereby realizing precise control of the advance aiming of the satellite including the antenna with a co-optical axis structure. Furthermore, the second satellite can accurately send the fourth signal to the first satellite according to the advance aiming angle of the third target. When the first satellite receives the fourth signal sent by the second satellite, the first satellite sends the fifth signal carrying the first communication data to the second satellite, and when the second satellite receives the fifth signal, the first satellite sends the sixth signal carrying the second communication data to the first satellite. This realizes satellite communication on the basis of accurately completing the communication link establishment between the first satellite and the second satellite including the antenna with the transmitting optical axis and the receiving optical axis as the co-optical axis structure, thereby improving the applicability of the method.

[0136] In the embodiment of the present application, the communication method performed by the first satellite is shown in FIG8 , and includes the following steps:

[0137] Step 801: In response to a first signal sent by a second satellite, obtain a first initial advance aiming angle of the first satellite relative to the second satellite, and send a second signal to the second satellite based on the first initial advance aiming angle, wherein the first signal and the second signal include a plurality of incompletely coherent beam signals.

[0138] Step 802: determining a first target advance aiming angle according to the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance aiming angle;

[0139] Step 803: Send a third signal to the second satellite based on the first target advance aiming angle, so that the second satellite sends a fourth signal based on the third signal; wherein the third signal and the fourth signal include coherent beam signals;

[0140] Step 804: In response to the fourth signal sent by the second satellite, a fifth signal carrying the first communication data is sent to the second satellite; wherein the fifth signal is used for the second satellite to send a sixth signal carrying the second communication data, and the fifth signal and the sixth signal include coherent beam signals.

[0141] In some optional implementations, determining the first target advance aiming angle according to the angle at the first half-width of the main lobe of the light beam in the second signal and the first initial advance aiming angle includes:

[0142] determining whether the first initial advance aiming angle is greater than the first half-width angle;

[0143] If the first initial advance aiming angle is greater than the first angle at half-width, the first initial advance aiming angle is adjusted to obtain the first target advance aiming angle.

[0144] In some optional implementations, adjusting the first initial leading aiming angle to obtain the first target leading aiming angle includes:

[0145] Acquire a first closed-loop tracking point corresponding to the incoherent beam transmitted by the first satellite and a second closed-loop tracking point corresponding to the incoherent beam received by the first satellite;

[0146] According to the first closed-loop tracking point and the second closed-loop tracking point, the first initial advance aiming angle is adjusted to obtain the first target advance aiming angle; wherein, the transmitted light beam emitted at the first target advance aiming angle coincides with the first closed-loop tracking point, and the received light beam received at the first target advance aiming angle coincides with the second closed-loop tracking point.

[0147] In some optional implementations, the first angle at half-width is obtained by:

[0148] determining a target beam signal from each beam signal in the second signal;

[0149] The angle at the first half-width is determined according to the divergence angle of the target beam signal.

[0150] In some optional implementations, the method further comprises:

[0151] If the first initial advance aiming angle is less than or equal to the first angle at half-width, the first initial advance aiming angle is used as the first target advance aiming angle.

[0152] In some optional implementations, before sending the second signal to the second satellite according to the first initial advance aiming angle, the method further includes:

[0153] Perturbations are added to a plurality of incoherent beam signals respectively to obtain the second signal, wherein the light intensity distribution of each beam signal in the second signal is uniform.

[0154] In some optional implementations, sending a fifth signal carrying the first communication data to the second satellite includes:

[0155] determining a second target leading aiming angle according to an angle at a second half-width of a main lobe of the light beam in the third signal and the first target leading aiming angle;

[0156] The fifth signal is sent to the second satellite according to the second target advance aiming angle.

[0157] In some optional implementations, determining the second target leading aiming angle according to the angle at the second half-width of the main lobe of the light beam in the third signal and the first target leading aiming angle includes:

[0158] determining whether the first target advance aiming angle is greater than the second half-width angle;

[0159] If the first target advance aiming angle is greater than the second half-width angle, obtaining a third closed-loop tracking point corresponding to the first satellite's transmitted coherent beam and a fourth closed-loop tracking point corresponding to the first satellite's received coherent beam;

[0160] According to the third closed-loop tracking point and the fourth closed-loop tracking point, the first target advance aiming angle is adjusted to obtain the second target advance aiming angle; wherein, the transmitted light beam emitted at the second target advance aiming angle coincides with the third closed-loop tracking point, and the received light beam received at the second target advance aiming angle coincides with the fourth closed-loop tracking point.

[0161] In some optional implementations, obtaining a first initial leading aiming angle of the first satellite relative to the second satellite includes:

[0162] The first initial advance aiming angle is determined based on a target distance between the first satellite and the second satellite.

[0163] In some optional embodiments, the second signal, the third signal, and the fifth signal are phased array signals sent by the first satellite through a phased array antenna; the first signal, the fourth signal, and the sixth signal are phased array signals received by the first satellite through the phased array antenna.

[0164] In the embodiment of the present application, the communication method performed by the second satellite is shown in FIG9 , and includes the following steps:

[0165] Step 901: Send a first signal to a first satellite so that the first satellite obtains a first initial advance aiming angle relative to the second satellite based on the first signal, and sends a second signal to the second satellite based on the first initial advance aiming angle; wherein the first signal includes multiple incompletely coherent beam signals.

[0166] Step 902: Receive a second signal sent by the first satellite; wherein the second signal includes a plurality of incompletely coherent beam signals.

[0167] Step 903: In response to the third signal sent by the first satellite based on the first target advance aiming angle, a fourth signal is sent to the first satellite; wherein the first target advance aiming angle is determined by the first satellite based on the first half-width angle of the main lobe of the light beam in the second signal and the first initial advance aiming angle, and the third signal and the fourth signal include coherent beam signals.

[0168] Step 904: In response to a fifth signal carrying first communication data sent by the first satellite, a sixth signal carrying second communication data is sent to the first satellite, wherein the fifth signal is sent by the first satellite in response to the fourth signal, and the fifth signal and the sixth signal include coherent beam signals.

[0169] In some optional implementations, sending the first signal to the first satellite includes:

[0170] A first signal is transmitted to the first satellite based on a second initial advance aiming angle of the second satellite relative to the first satellite.

[0171] In some optional implementations, after receiving the second signal sent by the first satellite, the method further includes:

[0172] determining a third target advance aiming angle according to an angle at a third half-width of the main lobe of the light beam in the first signal and the second initial advance aiming angle;

[0173] Sending a fourth signal to the first satellite includes:

[0174] The fourth signal is sent to the first satellite according to the third target advance aiming angle.

[0175] In some optional implementations, determining a third target advance aiming angle according to an angle at a third half-width of a main lobe of the light beam in the first signal and the second initial advance aiming angle includes:

[0176] determining whether the second initial advance aiming angle is greater than the third half-width angle;

[0177] If the second initial leading aiming angle is greater than the third half-width angle, the second initial leading aiming angle is adjusted to obtain the third target leading aiming angle; or

[0178] If the second initial advance aiming angle is less than or equal to the third half-width angle, the second initial advance aiming angle is used as the third target advance aiming angle.

[0179] In some optional implementations, adjusting the second initial leading aiming angle to obtain the third target leading aiming angle includes:

[0180] Acquire a fifth closed-loop tracking point corresponding to the incoherent beam transmitted by the second satellite and a sixth closed-loop tracking point corresponding to the incoherent beam received by the second satellite;

[0181] According to the fifth closed-loop tracking point and the sixth closed-loop tracking point, the second initial advance aiming angle is adjusted to obtain the third target advance aiming angle; wherein, the transmitting light beam emitted at the third target advance aiming angle coincides with the closed-loop tracking point corresponding to the incoherent beam emitted by the second satellite, and the receiving light beam received at the third target advance aiming angle coincides with the closed-loop tracking point corresponding to the incoherent beam received by the second satellite.

[0182] In some optional implementations, sending a sixth signal carrying second communication data to the first satellite includes:

[0183] determining a fourth target leading aiming angle according to an angle at a fourth half-width of a main lobe of the light beam in the fourth signal and the third target leading aiming angle;

[0184] The sixth signal is sent to the first satellite according to the fourth target advance aiming angle.

[0185] In some optional implementations, determining a fourth target advance aiming angle according to an angle at a fourth half-width of a main lobe of the light beam in the fourth signal and the third target advance aiming angle includes:

[0186] determining whether the third target advance aiming angle is greater than the fourth half-width angle;

[0187] If the third target advance aiming angle is greater than the fourth half-width angle, obtaining a seventh closed-loop tracking point corresponding to the second satellite's transmitted coherent beam and an eighth closed-loop tracking point corresponding to the second satellite's received coherent beam;

[0188] According to the seventh closed-loop tracking point and the eighth closed-loop tracking point, the third target advance aiming angle is adjusted to obtain the fourth target advance aiming angle; wherein, the transmitted light beam emitted at the fourth target advance aiming angle coincides with the seventh closed-loop tracking point, and the received light beam received at the fourth target advance aiming angle coincides with the eighth closed-loop tracking point.

[0189] The specific implementation of the embodiments of FIG8 to FIG9 can refer to the implementation of the above-mentioned interaction method, which will not be described in detail here.

[0190] As shown in FIG10 , based on the same inventive concept as the communication method shown in FIG8 , an embodiment of the present application provides a first communication device 1000 , which is applied to a first satellite and includes:

[0191] The processing module 1001 is configured to obtain, in response to a first signal sent by a second satellite, a first initial advance aiming angle of the first satellite relative to the second satellite, and send a second signal to the second satellite based on the first initial advance aiming angle, wherein the first signal and the second signal include a plurality of incompletely coherent beam signals;

[0192] A first determining module 1002 is configured to determine a first target leading aiming angle according to an angle at a first half-width of a main lobe of the light beam in the second signal and the first initial leading aiming angle;

[0193] a first sending module 1003, configured to send a third signal to the second satellite according to the first target advance aiming angle, so that the second satellite sends a fourth signal based on the third signal; wherein the third signal and the fourth signal include coherent beam signals;

[0194] The second sending module 1004 is used to send a fifth signal carrying the first communication data to the second satellite in response to the fourth signal sent by the second satellite; wherein the fifth signal is used for the second satellite to send a sixth signal carrying the second communication data, and the fifth signal and the sixth signal include coherent beam signals.

[0195] As a possible implementation of the embodiment of the present disclosure, the first determining module 1002 is specifically configured to:

[0196] determining whether the first initial advance aiming angle is greater than the first half-width angle;

[0197] If the first initial advance aiming angle is greater than the first angle at half-width, the first initial advance aiming angle is adjusted to obtain the first target advance aiming angle.

[0198] As a possible implementation of the embodiment of the present disclosure, the first determining module 1002 is specifically configured to:

[0199] Acquire a first closed-loop tracking point corresponding to the incoherent beam transmitted by the first satellite and a second closed-loop tracking point corresponding to the incoherent beam received by the first satellite;

[0200] According to the first closed-loop tracking point and the second closed-loop tracking point, the first initial advance aiming angle is adjusted to obtain the first target advance aiming angle; wherein, the transmitted light beam emitted at the first target advance aiming angle coincides with the first closed-loop tracking point, and the received light beam received at the first target advance aiming angle coincides with the second closed-loop tracking point.

[0201] As a possible implementation of the embodiment of the present disclosure, the first determining module 1002 is further configured to:

[0202] determining a target beam signal from each beam signal in the second signal;

[0203] The angle at the first half-width is determined according to the divergence angle of the target beam signal.

[0204] As a possible implementation of the embodiment of the present disclosure, the first determining module 1002 is further configured to:

[0205] If the first initial advance aiming angle is less than or equal to the first angle at half-width, the first initial advance aiming angle is used as the first target advance aiming angle.

[0206] As a possible implementation of the embodiment of the present disclosure, a disturbance module 1005 is further included, which is configured to:

[0207] Perturbations are added to a plurality of incoherent beam signals respectively to obtain the second signal, wherein the light intensity distribution of each beam signal in the second signal is uniform.

[0208] As a possible implementation of the embodiment of the present disclosure, the second sending module 1004 is specifically configured to:

[0209] determining a second target leading aiming angle according to an angle at a second half-width of a main lobe of the light beam in the third signal and the first target leading aiming angle;

[0210] The fifth signal is sent to the second satellite according to the second target advance aiming angle.

[0211] As a possible implementation of the embodiment of the present disclosure, the second sending module 1004 is specifically configured to:

[0212] determining whether the first target advance aiming angle is greater than the second half-width angle;

[0213] If the first target advance aiming angle is greater than the second half-width angle, obtaining a third closed-loop tracking point corresponding to the first satellite's transmitted coherent beam and a fourth closed-loop tracking point corresponding to the first satellite's received coherent beam;

[0214] According to the third closed-loop tracking point and the fourth closed-loop tracking point, the first target advance aiming angle is adjusted to obtain the second target advance aiming angle; wherein, the transmitted light beam emitted at the second target advance aiming angle coincides with the third closed-loop tracking point, and the received light beam received at the second target advance aiming angle coincides with the fourth closed-loop tracking point.

[0215] As a possible implementation of the embodiment of the present disclosure, the processing module 1001 is specifically configured to:

[0216] The first initial advance aiming angle is determined based on a target distance between the first satellite and the second satellite.

[0217] As a possible implementation of an embodiment of the present disclosure, the second signal, the third signal, and the fifth signal are phased array signals sent by the first satellite through a phased array antenna, and the first signal, the fourth signal, and the sixth signal are phased array signals received by the first satellite through the phased array antenna.

[0218] In order to implement the embodiment of FIG. 7 , another communication device is proposed in an embodiment of the present disclosure.

[0219] As shown in FIG11 , based on the same inventive concept as the communication method shown in FIG9 , an embodiment of the present application provides a first communication device 1100 applied to a second satellite, the device comprising:

[0220] An acquisition module 1101 is configured to send a first signal to a first satellite, so that the first satellite acquires a first initial advance aiming angle relative to a second satellite based on the first signal, and send a second signal to the second satellite based on the first initial advance aiming angle; wherein the first signal includes a plurality of incompletely coherent beam signals;

[0221] A second determining module 1102 is configured to receive a second signal sent by the first satellite; wherein the second signal includes a plurality of incompletely coherent beam signals;

[0222] a transmitting module 1103 configured to transmit a fourth signal to the first satellite in response to a third signal transmitted by the first satellite according to a first target advance aiming angle; wherein the first target advance aiming angle is transmitted by the first satellite according to the first target advance aiming angle, the first target advance aiming angle is determined based on a first half-width angle of a main lobe of a beam in the second signal and the first initial advance aiming angle, and the third signal and the fourth signal include coherent beam signals;

[0223] The receiving module 1104 is configured to send a sixth signal carrying second communication data to the first satellite in response to a fifth signal carrying first communication data sent by the first satellite, wherein the fifth signal is sent by the first satellite in response to the fourth signal, and the fifth signal and the sixth signal include coherent beam signals.

[0224] In some optional implementations, the acquisition module 1101 is specifically configured to:

[0225] A first signal is transmitted to the first satellite based on a second initial advance aiming angle of the second satellite relative to the first satellite.

[0226] In some optional implementations, the second determining module 1102 is further configured to:

[0227] After receiving the second signal sent by the first satellite, determining a third target advance aiming angle according to the angle at a third half-width of the main lobe of the light beam in the first signal and the second initial advance aiming angle;

[0228] The sending module 1103 is specifically configured to:

[0229] The fourth signal is sent to the first satellite according to the third target advance aiming angle.

[0230] In some optional implementation manners, the second determining module 1102 is specifically configured to:

[0231] determining whether the second initial advance aiming angle is greater than the third half-width angle;

[0232] If the second initial leading aiming angle is greater than the third half-width angle, the second initial leading aiming angle is adjusted to obtain the third target leading aiming angle; or

[0233] If the second initial advance aiming angle is less than or equal to the third half-width angle, the second initial advance aiming angle is used as the third target advance aiming angle.

[0234] In some optional implementation manners, the second determining module 1102 is specifically configured to:

[0235] Acquire a fifth closed-loop tracking point corresponding to the incoherent beam transmitted by the second satellite and a sixth closed-loop tracking point corresponding to the incoherent beam received by the second satellite;

[0236] According to the fifth closed-loop tracking point and the sixth closed-loop tracking point, the second initial advance aiming angle is adjusted to obtain the third target advance aiming angle; wherein, the transmitting light beam emitted at the third target advance aiming angle coincides with the closed-loop tracking point corresponding to the incoherent beam emitted by the second satellite, and the receiving light beam received at the third target advance aiming angle coincides with the closed-loop tracking point corresponding to the incoherent beam received by the second satellite.

[0237] In some optional implementations, the receiving module 1104 is specifically configured to:

[0238] determining a fourth target leading aiming angle according to an angle at a fourth half-width of a main lobe of the light beam in the fourth signal and the third target leading aiming angle;

[0239] The sixth signal is sent to the first satellite according to the fourth target advance aiming angle.

[0240] In some optional implementations, the receiving module 1104 is specifically configured to:

[0241] determining whether the third target advance aiming angle is greater than the fourth half-width angle;

[0242] If the third target advance aiming angle is greater than the fourth half-width angle, obtaining a seventh closed-loop tracking point corresponding to the second satellite's transmitted coherent beam and an eighth closed-loop tracking point corresponding to the second satellite's received coherent beam;

[0243] According to the seventh closed-loop tracking point and the eighth closed-loop tracking point, the third target advance aiming angle is adjusted to obtain the fourth target advance aiming angle; wherein, the transmitted light beam emitted at the fourth target advance aiming angle coincides with the seventh closed-loop tracking point, and the received light beam received at the fourth target advance aiming angle coincides with the eighth closed-loop tracking point.

[0244] It should be noted that the above explanation of the communication method embodiment is also applicable to the communication device of this embodiment and will not be repeated here.

[0245] In order to implement the above embodiments, the present application further proposes an electronic device, as shown in FIG12 . FIG12 is a block diagram of an electronic device for communication according to an exemplary embodiment.

[0246] As shown in FIG12 , the electronic device 1200 includes:

[0247] The memory 1010 and the processor 1020, and the bus 1030 connecting different components (including the memory 1010 and the processor 1020), the memory 1010 stores a computer program, and when the processor 1020 executes the computer program, the communication method described in the embodiment of the present disclosure is implemented.

[0248] Bus 1030 represents one or more of several types of bus structures, including a memory bus or memory controller, a peripheral bus, an accelerated graphics port, a processor, or a local bus using any of a variety of bus architectures. Examples of these architectures include, but are not limited to, an Industry Standard Architecture (ISA) bus, a Micro Channel Architecture (MAC) bus, an Enhanced ISA bus, a Video Electronics Standards Association (VESA) local bus, and a Peripheral Component Interconnect (PCI) bus.

[0249] The electronic device 1200 typically includes a variety of electronic device-readable media. These media can be any available media that can be accessed by the electronic device 1200, including volatile and non-volatile media, removable and non-removable media.

[0250] The memory 1010 may also include computer system readable media in the form of volatile memory, such as random access memory (RAM) 1040 and / or cache memory 1050. The electronic device 1200 may further include other removable / non-removable, volatile / non-volatile computer system storage media. By way of example only, the storage system 1060 may be used to read and write non-removable, non-volatile magnetic media (not shown in FIG. 12 , commonly referred to as a “hard drive”). Although not shown in FIG. 12 , a disk drive for reading and writing to a removable non-volatile disk (such as a “floppy disk”) and an optical disk drive for reading and writing to a removable non-volatile optical disk (such as a CD-ROM, DVD-ROM or other optical media) may be provided. In these cases, each drive may be connected to the bus 1030 via one or more data media interfaces. The memory 1010 may include at least one program product having a set (e.g., at least one) of program modules that are configured to perform the functions of the various embodiments of the present disclosure.

[0251] A program / utility 1080 having a set (at least one) of program modules 1070 may be stored, for example, in memory 1010. Such program modules 1070 include, but are not limited to, an operating system, one or more application programs, other program modules, and program data, each of which, or some combination thereof, may include an implementation of a network environment. Program modules 1070 generally implement the functions and / or methods of the embodiments described herein.

[0252] The electronic device 1200 can also communicate with one or more external devices 1090 (e.g., a keyboard, a pointing device, a display 1091, etc.), one or more devices that enable a user to interact with the electronic device 1200, and / or any device that enables the electronic device 1200 to communicate with one or more other computing devices (e.g., a network card, a modem, etc.). Such communication can occur via an input / output (I / O) interface 1092. Furthermore, the electronic device 1200 can communicate with one or more networks (e.g., a local area network (LAN), a wide area network (WAN), and / or a public network such as the Internet) via a network adapter 1093. As shown in FIG. 12 , the network adapter 1093 communicates with other modules of the electronic device 1200 via the bus 1030. It should be understood that, although not shown in FIG. 12 , other hardware and / or software modules can be used in conjunction with the electronic device 1200, including but not limited to microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems.

[0253] The processor 1020 executes various functional applications and data processing by running programs stored in the memory 1010 .

[0254] It should be noted that the implementation process and technical principles of the electronic device of this embodiment can be found in the aforementioned explanation of the communication method of the embodiment of the present disclosure, and will not be repeated here.

[0255] In order to implement the above embodiments, the present application further proposes a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the communication method described in the above embodiments is implemented.

[0256] In order to implement the above embodiments, the present disclosure further provides a computer program product. When an instruction processor in the computer program product executes, the communication method described in the above embodiments is executed.

[0257] In the description of this specification, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include at least one of such features. In the description of this application, "plurality" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0258] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials, or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0259] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A communication method, characterized in that: Applied to the first satellite, including: In response to a first signal sent by a second satellite, acquiring a first initial advance aiming angle of the first satellite relative to the second satellite, and sending a second signal to the second satellite according to the first initial advance aiming angle, wherein the first signal and the second signal include a plurality of incompletely coherent beam signals; Determine a first target advance aiming angle according to an angle at a first half-width of a main lobe of the light beam in the second signal and the first initial advance aiming angle; Sending a third signal to the second satellite according to the first target advance aiming angle, so that the second satellite sends a fourth signal based on the third signal; wherein the third signal and the fourth signal include coherent beam signals; In response to the fourth signal sent by the second satellite, a fifth signal carrying the first communication data is sent to the second satellite; wherein the fifth signal is used for the second satellite to send a sixth signal carrying the second communication data, and the fifth signal and the sixth signal include coherent beam signals.

2. The method according to claim 1, characterized in that Determining a first target advance aiming angle according to an angle at a first half-width of a main lobe of a light beam in the second signal and the first initial advance aiming angle comprises: Determining whether the first initial advance aiming angle is greater than the first half-width angle; If the first initial advance aiming angle is greater than the first half-width angle, the first initial advance aiming angle is adjusted to obtain the first target advance aiming angle.

3. The method according to claim 2, characterized in that Adjusting the first initial leading aiming angle to obtain the first target leading aiming angle includes: Acquire a first closed-loop tracking point corresponding to the incoherent beam transmitted by the first satellite and a second closed-loop tracking point corresponding to the incoherent beam received by the first satellite; According to the first closed-loop tracking point and the second closed-loop tracking point, the first initial advance aiming angle is adjusted to obtain the first target advance aiming angle; wherein, the transmitting light beam emitted at the first target advance aiming angle coincides with the first closed-loop tracking point, and the receiving light beam received at the first target advance aiming angle coincides with the second closed-loop tracking point.

4. The method according to claim 2, characterized in that: The first half-width angle is obtained by: Determining a target beam signal from each beam signal in the second signal; The angle at the first half-width is determined according to the divergence angle of the target beam signal.

5. The method according to claim 2, characterized in that: The method further comprises: If the first initial advance aiming angle is less than or equal to the first angle at half-width, the first initial advance aiming angle is used as the first target advance aiming angle.

6. The method according to claim 1, characterized in that Before sending a second signal to the second satellite according to the first initial advanced aiming angle, the method further includes: Perturbations are added to a plurality of incoherent beam signals respectively to obtain the second signal, wherein the light intensity distribution of each beam signal in the second signal is uniform.

7. The method according to claim 1, characterized in that Sending a fifth signal carrying the first communication data to the second satellite includes: Determine a second target advance aiming angle according to an angle at a second half-width of a main lobe of the light beam in the third signal and the first target advance aiming angle; The fifth signal is sent to the second satellite according to the second target advance aiming angle.

8. The method according to claim 7, characterized in that Determining a second target advance aiming angle according to an angle at a second half-width of a main lobe of a light beam in the third signal and the first target advance aiming angle comprises: Determining whether the first target advance aiming angle is greater than the second half-width angle; If the first target advance aiming angle is greater than the second half-width angle, obtaining a third closed-loop tracking point corresponding to the first satellite transmitting coherent beam and a fourth closed-loop tracking point corresponding to the receiving coherent beam; According to the third closed-loop tracking point and the fourth closed-loop tracking point, the first target advance aiming angle is adjusted to obtain the second target advance aiming angle; wherein the transmitting light beam emitted at the second target advance aiming angle coincides with the third closed-loop tracking point, and the receiving light beam received at the second target advance aiming angle coincides with the fourth closed-loop tracking point.

9. The method according to claim 1, characterized in that: Acquiring a first initial advance aiming angle of the first satellite relative to the second satellite, comprising: The first initial advance aiming angle is determined based on a target distance between the first satellite and the second satellite.

10. The method according to any one of claims 1 to 9, characterized in that The second signal, the third signal, and the fifth signal are phased array signals sent by the first satellite through a phased array antenna; the first signal, the fourth signal, and the sixth signal are phased array signals received by the first satellite through the phased array antenna.

11. A communication method, characterized in that: Applicable to the second satellite, including: Sending a first signal to a first satellite so that the first satellite acquires a first initial advance aiming angle relative to the second satellite based on the first signal, and sending a second signal to the second satellite according to the first initial advance aiming angle; wherein the first signal includes a plurality of incompletely coherent beam signals; receiving a second signal sent by the first satellite; wherein the second signal includes a plurality of incompletely coherent beam signals; In response to a third signal sent by the first satellite according to a first target advance aiming angle, a fourth signal is sent to the first satellite; wherein the first target advance aiming angle is determined by the first satellite according to a first half-width angle of a main lobe of a beam in the second signal and the first initial advance aiming angle, and the third signal and the fourth signal include coherent beam signals; In response to a fifth signal carrying first communication data sent by the first satellite, a sixth signal carrying second communication data is sent to the first satellite, wherein the fifth signal is sent by the first satellite in response to the fourth signal, and the fifth signal and the sixth signal include coherent beam signals.

12. The method according to claim 11, characterized in that Sending a first signal to a first satellite includes: A first signal is sent to a first satellite based on a second initial advance aiming angle of the second satellite relative to the first satellite.

13. The method according to claim 12, characterized in that After receiving the second signal sent by the first satellite, the method further includes: Determine a third target advance aiming angle according to the angle of the third half-width at half-height of the main lobe of the light beam in the first signal and the second initial advance aiming angle; The method further comprises: sending a fourth signal to the first satellite, comprising: The fourth signal is sent to the first satellite according to the third target advance aiming angle.

14. The method according to claim 13, characterized in that Determining a third target advance aiming angle according to the third half-width angle of the main lobe of the light beam in the first signal and the second initial advance aiming angle comprises: Determining whether the second initial advance aiming angle is greater than the third half-width angle; If the second initial advance aiming angle is greater than the third half-width angle, the second initial advance aiming angle is adjusted to obtain the third target advance aiming angle; or If the second initial advance aiming angle is less than or equal to the third half-width angle, the second initial advance aiming angle is used as the third target advance aiming angle.

15. The method according to claim 14, characterized in that The second initial leading aiming angle is adjusted to obtain the third target leading aiming angle, comprising: Acquire a fifth closed-loop tracking point corresponding to the incoherent beam transmitted by the second satellite and a sixth closed-loop tracking point corresponding to the incoherent beam received by the second satellite; According to the fifth closed-loop tracking point and the sixth closed-loop tracking point, the second initial advance aiming angle is adjusted to obtain the third target advance aiming angle; wherein the transmitting light beam emitted at the third target advance aiming angle coincides with the closed-loop tracking point corresponding to the incoherent beam emitted by the second satellite, and the receiving light beam received at the third target advance aiming angle coincides with the closed-loop tracking point corresponding to the incoherent beam received by the second satellite.

16. The method according to claim 11, characterized in that Sending a sixth signal carrying second communication data to the first satellite includes: Determine a fourth target advance aiming angle according to the fourth half-width angle of the main lobe of the light beam in the fourth signal and the third target advance aiming angle; The sixth signal is sent to the first satellite according to the fourth target advance aiming angle.

17. The method according to claim 16, characterized in that Determining a fourth target advance aiming angle according to an angle at a fourth half-width of a main lobe of the light beam in the fourth signal and the third target advance aiming angle comprises: Determining whether the third target leading aiming angle is greater than the fourth half-width angle; If the leading aiming angle of the third target is greater than the angle at the fourth half-width, acquiring a seventh closed-loop tracking point corresponding to the transmitting coherent beam of the second satellite and an eighth closed-loop tracking point corresponding to the receiving coherent beam; According to the seventh closed-loop tracking point and the eighth closed-loop tracking point, the third target leading aiming angle is adjusted to obtain the fourth aiming point. wherein, the emission light beam emitted at the fourth target advance aiming angle coincides with the seventh closed-loop tracking point, and the reception light beam received at the fourth target advance aiming angle coincides with the eighth closed-loop tracking point.

18. A communication device, characterized in that: Applied to the first satellite, including: a processing module, configured to obtain, in response to a first signal sent by a second satellite, a first initial advance aiming angle of the first satellite relative to the second satellite, and send a second signal to the second satellite according to the first initial advance aiming angle, wherein the first signal and the second signal include a plurality of incompletely coherent beam signals; A first determination module, configured to determine a first target advance aiming angle according to an angle at a first half-width at half-height of a main lobe of a light beam in the second signal and the first initial advance aiming angle; a first sending module, configured to send a third signal to the second satellite according to the first target advance aiming angle, so that the second satellite sends a fourth signal based on the third signal; wherein the third signal and the fourth signal include coherent beam signals; The second sending module is used to send a fifth signal carrying the first communication data to the second satellite in response to the fourth signal sent by the second satellite; wherein the fifth signal is used for the second satellite to send a sixth signal carrying the second communication data, and the fifth signal and the sixth signal include coherent beam signals.

19. A communication device, characterized in that: Applicable to the second satellite, including: an acquisition module, configured to send a first signal to a first satellite, so that the first satellite acquires a first initial advance aiming angle relative to the second satellite based on the first signal, and sends a second signal to the second satellite according to the first initial advance aiming angle; wherein the first signal includes a plurality of incompletely coherent beam signals; A second determination module is configured to receive a second signal sent by the first satellite; wherein the second signal includes a plurality of incompletely coherent beam signals; a sending module, configured to send a fourth signal to the first satellite in response to a third signal sent by the first satellite according to a first target advance aiming angle; wherein the first target advance aiming angle is sent by the first satellite according to the first target advance aiming angle, the first target advance aiming angle is determined according to a first half-width angle of a main lobe of a light beam in the second signal and the first initial advance aiming angle, and the third signal and the fourth signal include coherent beam signals; A receiving module is used to send a sixth signal carrying second communication data to the first satellite in response to a fifth signal carrying first communication data sent by the first satellite, wherein the fifth signal is sent by the first satellite in response to the fourth signal, and the fifth signal and the sixth signal include coherent beam signals.

20. An electronic device, characterized in that: The invention comprises a memory, a processor and a computer program stored in the memory and capable of running on the processor, wherein when the processor executes the computer program, the communication method according to any one of claims 1 to 10 is implemented, or the communication method according to any one of claims 11 to 17 is implemented.

21. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the computer program implements the communication method according to any one of claims 1 to 10, or the computer program implements the communication method according to any one of claims 11 to 17.

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