Method for transmitting control of an aeronautical communication system

Abstract

This application provides a transmission control method for an aerospace satellite communication system. The method includes: detecting the aircraft mode of a target aircraft, wherein the aircraft mode includes an airborne mode, a general ground mode, and a ground maintenance mode; and, based on the aircraft mode, invoking the transmission status of the target aircraft, wherein the transmission status associated with the airborne mode includes a one-key no-fire switch and an emergency no-fire switch, the transmission status associated with the general ground mode includes ground voice communication and the emergency no-fire switch, and the transmission status associated with the ground maintenance mode includes a transmission status configuration change. This achieves aerospace satellite communication radio frequency transmission control that is adaptable to various environments, compatible with the needs of various airlines, and possesses scalability.

Description

Technical Field

[0001] This application relates to the field of airborne satellite communication technology, and in particular to a launch control method for an airborne satellite communication system. Background Technology

[0002] Satellite communication is a crucial communication method for civil aircraft. Different airlines have varying customization requirements for satellite communication products. For example, thanks to the Ministry of Industry and Information Technology's removal of the "3000m launch ban" policy, some airlines want to eliminate the "altitude launch ban" function, while others, considering security and scalability, wish to retain it. Given the removal of the "altitude launch ban," how to ensure security and convenience even without this function is a problem that needs to be solved. Furthermore, some airlines expect the product to be able to launch from the ground, while others prefer it to be non-launchable, and so on.

[0003] In general, different airlines have raised different requirements, and these requirements are difficult to reconcile with the existing functionalities due to reasons such as safety and convenience. For a brand-new civil aviation product, the process from research and development to obtaining certification and mass production typically takes a year or even longer and consumes significant human and material resources, while the change cycle of airlines' needs is much shorter. Therefore, a mature satellite communication product should be as compatible as possible with the needs of various airlines and reasonably consider scalability.

[0004] Therefore, given the triple demands for security, convenience, and scalability, satellite communication products urgently need a transmission control solution that can adapt to various environments and requirements. Summary of the Invention

[0005] In view of this, the present application provides a method for controlling the launch of an aerospace satellite communication system to address the technical deficiencies in the prior art.

[0006] According to a first aspect of the embodiments of this application, an airborne satellite communication system launch control method is provided, comprising:

[0007] The aircraft mode of the target aircraft is detected, wherein the aircraft mode includes air mode, ground general mode and ground maintenance mode;

[0008] According to the aircraft mode, the launch status of the target aircraft is invoked. The launch status associated with the air mode includes a one-key fire stop switch and an emergency fire stop switch. The launch status associated with the ground general mode includes ground voice communication and the emergency fire stop switch. The launch status associated with the ground maintenance mode includes launch status configuration change.

[0009] Optionally, the launch state associated with the air mode further includes a first optional state, the launch state associated with the ground general mode includes a second optional state, and the launch state associated with the ground maintenance mode further includes a third optional state.

[0010] Optionally, the aircraft mode of the detected target aircraft includes:

[0011] Based on the pose detection device installed on the target aircraft, the pose data of the target aircraft is collected;

[0012] The aircraft mode is determined based on the pose data.

[0013] Optionally, the step of collecting the pose data of the target aircraft based on the pose detection device installed on the target aircraft includes:

[0014] The pose detection device, which is based on a GPS inertial navigation system, collects pose data, which includes longitude, latitude, altitude, pitch angle, roll angle, and heading.

[0015] Optionally, the emergency deactivation switch has the highest priority and is activated by a preset mechanical switch.

[0016] Optionally, the one-button disable switch is a temporary switch, and the default value is restored after the relevant system is restarted and reset.

[0017] Optionally, when the launch status configuration changes, the launch status configuration is adjusted based on the external display device configured on the target aircraft.

[0018] Optionally, adjusting the configuration of the transmission state includes:

[0019] Based on the configuration file of the permanent configuration, the main software of the temporary configuration is built to adjust the launch state.

[0020] The aerospace satellite communication system transmission control method provided in this application detects the aircraft mode of a target aircraft, including air mode, general ground mode, and ground maintenance mode. Based on the aircraft mode, it invokes the transmission status of the target aircraft. The transmission status associated with the air mode includes a one-key no-fire switch and an emergency no-fire switch; the transmission status associated with the general ground mode includes ground voice communication and the emergency no-fire switch; and the transmission status associated with the ground maintenance mode includes transmission status configuration changes. This achieves aerospace satellite communication radio frequency transmission control that is adaptable to various environments, compatible with the needs of various airlines, and possesses scalability. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a flowchart of a transmission control method for an aerospace satellite communication system provided in one embodiment of this application;

[0023] Figure 2 This is a schematic diagram of an aircraft mode for a launch control method for an aerospace satellite communication system provided in an embodiment of this application;

[0024] Figure 3 This is a system architecture diagram of an airborne satellite communication system launch control method provided in one embodiment of this application;

[0025] Figure 4 This is a control flowchart of a transmission control method for an aerospace satellite communication system provided in one embodiment of this application;

[0026] Figure 5 This is a software schematic diagram of an airborne satellite communication system launch control method provided in an embodiment of this application. Detailed Implementation

[0027] Many specific details are set forth in the following description to provide a full understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of this application; therefore, this application is not limited to the specific embodiments disclosed below.

[0028] The terminology used in one or more embodiments of this application is for the purpose of describing particular embodiments only and is not intended to limit the scope of one or more embodiments of this application. The singular forms “a,” “the,” and “the” used in one or more embodiments of this application and in the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” used in one or more embodiments of this application refers to and includes any or all possible combinations of one or more associated listed items.

[0029] It should be understood that although the terms first, second, etc., may be used to describe various information in one or more embodiments of this application, such information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, first may also be referred to as second without departing from the scope of one or more embodiments of this application, and similarly, second may also be referred to as first.

[0030] This application provides a method for controlling the launch of an aerospace satellite communication system, which will be described in detail in the following embodiments.

[0031] Figure 1 A flowchart of a launch control method for an aerospace satellite communication system according to an embodiment of this application is shown, which specifically includes the following steps:

[0032] Step S102: Detect the aircraft mode of the target aircraft, wherein the aircraft mode includes air mode, ground general mode and ground maintenance mode;

[0033] Step S104: According to the aircraft mode, invoke the launch status of the target aircraft, wherein the launch status associated with the air mode includes a one-key launch stop switch and an emergency launch stop switch, the launch status associated with the ground general mode includes ground voice communication and the emergency launch stop switch, and the launch status associated with the ground maintenance mode includes launch status configuration change.

[0034] Among them, such as Figure 2 A schematic diagram of the aircraft modes provided for an airborne satellite communication system launch control method is shown. The aircraft modes include an airborne mode, a ground maintenance mode, and a ground general mode. The two ground-related modes are the ground maintenance mode and the ground general mode.

[0035] Based on this, each aircraft mode is associated with a corresponding launch status. Air mode corresponds to the one-button fire-stop switch and the emergency fire-stop switch; ground general mode corresponds to ground voice communication and the emergency fire-stop switch; and ground maintenance mode corresponds to launch status configuration changes. These launch status configuration changes are then involved in adjusting the launch status, such as... Figure 2 As shown, based on the change in the launch status configuration, the launch status corresponding to the air mode is adjusted to include only the one-key no-launch switch, and the one-key no-launch switch is set to a temporary configuration. The launch status corresponding to the ground maintenance mode is adjusted to include the permanently configured altitude verification switch, the ground voice communication switch, and the temporarily configured maintenance launch switch. The launch status corresponding to the ground general mode is adjusted to have no corresponding launch status.

[0036] It should be noted that temporary configurations represent the default settings that are restored after a system reset, while permanent configurations represent settings that will not be lost after a system reset. In actual use cases, these often correspond to the customized needs of airlines. Furthermore, Figure 2 The process of changing the launch status configuration depends on the actual usage scenario, and the final adjustment result is not limited in this embodiment.

[0037] Furthermore, in step S102, the process of detecting the aircraft mode of the target aircraft is specifically implemented as follows in this embodiment:

[0038] Based on the pose detection device installed on the target aircraft, the pose data of the target aircraft is collected; the aircraft mode is determined based on the pose data.

[0039] Furthermore, the process of collecting the pose data of the target aircraft based on the pose detection device installed on the target aircraft is specifically implemented in this embodiment as follows:

[0040] The pose detection device, which is based on a GPS inertial navigation system, collects pose data, which includes longitude, latitude, altitude, pitch angle, roll angle, and heading.

[0041] The system determines the position and attitude of the target aircraft based on the attitude data collected by the attitude detection equipment. In addition to longitude, latitude, altitude, pitch angle, roll angle, and heading, users can collect multi-dimensional attitude information by adding preset sensors according to their actual needs. This attitude information, together with longitude, latitude, altitude, pitch angle, roll angle, and heading, constitutes the attitude data.

[0042] Based on this, the aircraft's state after takeoff corresponds to the airborne mode. To ensure safety, the target aircraft in airborne mode cannot have its launch configuration changed to avoid accidents caused by accidental alterations. The state of the aircraft on the ground without user intervention corresponds to the ground normal mode, and correspondingly, the state of the aircraft on the ground with user intervention corresponds to the ground maintenance mode. The combined use of these three modes—airborne mode, ground normal mode, and ground maintenance mode—enables automatic and manual control of signal transmission in the aerospace satellite communication system.

[0043] Furthermore, the launch state associated with the air mode also includes a first optional state, the launch state associated with the ground general mode includes a second optional state, and the launch state associated with the ground maintenance mode also includes a third optional state.

[0044] Among them, the first optional state, the second optional state, and the third optional state are all optional states. They are new launch states established according to the different usage needs of each user. The specific launch states corresponding to the first optional state, the second optional state, and the third optional state, as well as the signal transmission control method for the target aircraft, are determined by the actual usage scenario and are not limited in this embodiment.

[0045] Furthermore, the emergency deactivation switch has the highest priority and is activated by a preset mechanical switch.

[0046] Furthermore, the one-button disable switch is a temporary switch, and the default value will be restored after the relevant system is restarted and reset.

[0047] To ensure safety in the air when the "no-fire" function is not available, a one-button no-fire switch and an emergency no-fire switch are provided in the air mode. The emergency no-fire switch has the highest priority and must be manually switched on or off using external mechanical means (i.e., a mechanical switch). The one-button no-fire switch is a temporary switch, which reverts to its default value after a system restart and reset. The default value depends on the specific needs of the airline, and this embodiment does not impose any restrictions. It is mainly used for secondary emergency operations in the air and can be implemented using a web interface.

[0048] Furthermore, when the launch status configuration is changed, the launch status configuration is adjusted based on the external display device configured on the target aircraft.

[0049] Furthermore, the process of adjusting the launch status configuration described above is implemented in this embodiment as follows:

[0050] Based on the configuration file of the permanent configuration, the main software of the temporary configuration is built to adjust the launch state.

[0051] In order to balance safety, convenience and scalability, this embodiment realizes the transmission control of the aerospace satellite communication system through the cooperation of software and hardware. In terms of hardware, it consists of "simple hardware" and "complex hardware". "Simple hardware" can be understood as mechanical switches, which are used to issue emergency signals or indicate simple states, while "complex hardware" is used to transmit protocol messages or secondary control signals between various modules of the system.

[0052] like Figure 3The system architecture diagram of an aerospace satellite communication system transmission control method is provided. The hardware components may include an external control module, an external display module, a position and attitude module, a modem manager module, a transmission control module, and a radio frequency (RF) module. The external control module consists of "simple hardware," i.e., mechanical switches. This function directly controls the transmission module and manipulates the RF module, providing the most convenient and stable means to achieve transmission prohibition. The external display module, i.e., the external display device, primarily provides an interactive interface for the user. This module can display various prompts such as the current system status, communication function status, and the status of various devices within the system, assisting user operation and status collection. The external display module may also include software functions, serving as a secondary transmission control method. Simultaneously, the external display module may also include various system configuration functions, allowing users to configure the system and change the transmission status configuration within this module.

[0053] In addition, the position and attitude module, i.e., the attitude detection device, mainly provides the system with information such as the aircraft's position and attitude. The position and attitude module can be composed of a GPS inertial navigation system, providing attitude data including longitude, latitude, altitude, pitch angle, roll angle, and heading. The position and attitude module should be sensitive enough to collect position and attitude information and transmit it to the system at a high frequency. The modem manager module mainly provides modulation and demodulation, network management, and user configuration functions. It connects to the external control module via simple signals to ensure the independence, stability, and security of the external control module. It connects to the external display module and transmission control module via Ethernet or other means to receive or transmit status information. The system includes information on the state and prohibition of transmission, etc.; the transmission control module mainly provides the decision-making function for radio frequency transmission, with the following four main decision bases: first, based on the information provided by the position and attitude module and the configuration of the modem manager module, a transmission decision is made; second, based on its own sensors, which can also be integrated into the attitude detection device, environmental factors are perceived and used as the basis for the transmission decision; third, a decision is made based on the prohibition of transmission information transmitted by the external control module; and fourth, a decision is made based on the control information transmitted by the external display and control module. The radio frequency module mainly realizes the conversion from intermediate frequency to radio frequency, converting the intermediate frequency signal carrying information into a radio frequency signal suitable for transmission and transmitting it to the outside.

[0054] It should be noted that the hardware component also includes computing devices, whose components include, but are not limited to, memory and processors. The processor and memory are connected via a bus, and the database is used to store data.

[0055] The computing device also includes access devices that enable the computing device to communicate via one or more networks. Examples of such networks include a Public Switched Telephone Network (PSTN), a Local Area Network (LAN), a Wide Area Network (WAN), a Personal Area Network (PAN), or a combination of communication networks such as the Internet. Access devices may include one or more of any type of wired or wireless network interface (e.g., a Network Interface Card (NIC)), such as an IEEE 802.11 Wireless Local Area Network (WLAN) interface, a Wi-MAX interface, an Ethernet interface, a Universal Serial Bus (USB) interface, a cellular network interface, a Bluetooth interface, a Near Field Communication (NFC) interface, and so on.

[0056] In one embodiment of this application, other components of the computing device not described above may also be interconnected, for example, via a bus. The computing device can be any type of stationary or mobile computing device, including mobile computers or mobile computing devices (e.g., tablet computers, personal digital assistants, laptop computers, notebook computers, netbooks, etc.), mobile phones (e.g., smartphones), wearable computing devices (e.g., smartwatches, smart glasses, etc.) or other types of mobile devices, or stationary computing devices such as desktop computers or PCs. The computing device can also be a mobile or stationary server.

[0057] The processor executes computer-executable instructions for each step of the aerospace satellite communication system launch control method. One embodiment of this application also provides a computer-readable storage medium storing computer instructions that, when executed by a processor, are used to perform each step of the aerospace satellite communication system launch control method. Another embodiment of this application provides a chip storing a computer program that, when executed by the chip, implements the steps of the aerospace satellite communication system launch control method.

[0058] The computer instructions include computer program code, which may be in the form of source code, object code, executable file, or some intermediate form. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording media, USB flash drive, portable hard drive, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signals, telecommunication signals, and software distribution media, etc. It should be noted that the content included in the computer-readable medium may be appropriately added to or subtracted according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media may not include electrical carrier signals and telecommunication signals.

[0059] It should be noted that the components in the hardware embodiments should be understood as functional modules necessary to implement each step of the program flow or method, and these functional modules are not actual functional divisions or separations. A device claim defined by such a set of functional modules should be understood as a functional module architecture that primarily implements the solution through the computer program described in the specification, and not as a physical device that primarily implements the solution through hardware.

[0060] Specific implementation examples, such as Figure 4 The control flowchart of a transmission control method for an aviation satellite communication system shows that by detecting the wheel load, it is determined whether the target aircraft is on the ground. If not, it is determined that the aircraft is in air mode. For the target aircraft, it is checked whether altitude verification is enabled. If not, the aircraft is immediately prohibited from transmitting and will wait for subsequent external environment verification to pass before transmitting. If altitude verification is enabled and passes, it is determined that the target aircraft is not in a low-altitude area where signal transmission is at risk. In this case, the aircraft is immediately prohibited from transmitting and will wait for subsequent external environment verification to pass before transmitting. If the altitude verification fails, the aircraft is in a low-altitude area and transmission is prohibited.

[0061] When the target aircraft is determined to be on the ground, a status assessment is performed. If it is not under maintenance, it indicates that it is in normal ground mode. The system checks whether ground voice communication is possible. If so, it waits for external input to transmit; otherwise, it prohibits transmission. If the status is under maintenance, it indicates that it is in ground maintenance mode. The system checks whether personnel are currently performing maintenance actions. If not, it prohibits transmission; otherwise, it waits for external input to transmit.

[0062] It should be noted that the aforementioned external inputs are implemented using a manual mechanical switch. This enables functions such as emergency firing prohibition. The "wheel load" signal is implemented using a simple hardware CPLD signal to indicate whether the aircraft is on the ground or in the air. External environment verification utilizes hardware sensing, such as external sensors, combined with hardware judgment, such as logic circuits. Environmental verification includes the judgments of various sensors on external hazards. The altitude firing prohibition verification, according to industry standards, uses the ARINC429 channel to transmit GPS inertial navigation data, which is then parsed and verified by software.

[0063] The execution process of the above embodiments depends on the software component, such as... Figure 5 A software schematic diagram of an aerospace satellite communication system transmission control method is provided. The software includes multiple software main bodies, namely the aforementioned main software, which is a temporary configuration. This temporary configuration is generated by combining configuration files of permanent configuration. Specifically, the software main bodies are the general parts, while the configuration files are customized versions for each airline. That is, each airline or aircraft type corresponds to a version of the configuration file, and the software main bodies and configuration files have a one-to-many relationship.

[0064] Therefore, when facing the needs of different airlines, only the configuration file needs to be changed and maintained, and the main software and hardware do not need to be changed. In other words, the main software and hardware are common parts, which reduces maintenance costs.

[0065] The foregoing has described specific embodiments of this application. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims may be performed in a different order than that shown in the embodiments and may still achieve the desired results. Furthermore, the processes depicted in the drawings do not necessarily require the specific or sequential order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0066] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, as some steps may be performed in other orders or simultaneously according to this application. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to this application.

[0067] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0068] The preferred embodiments disclosed above are merely illustrative of this application. The optional embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this application. These embodiments are selected and specifically described in this application to better explain the principles and practical applications of this application, thereby enabling those skilled in the art to better understand and utilize this application. This application is limited only by the claims and their full scope and equivalents.

Claims

1. A method for controlling the launch of an airborne satellite communication system, characterized in that, include: The aircraft mode of the target aircraft is detected, wherein the aircraft mode includes air mode, ground general mode and ground maintenance mode; According to the aircraft mode, the launch status of the target aircraft is invoked. The launch status associated with the air mode includes a one-key fire stop switch and an emergency fire stop switch. The launch status associated with the ground general mode includes ground voice communication and the emergency fire stop switch. The launch status associated with the ground maintenance mode includes launch status configuration change.

2. The method according to claim 1, characterized in that, The launch state associated with the air mode also includes a first optional state, the launch state associated with the ground general mode includes a second optional state, and the launch state associated with the ground maintenance mode also includes a third optional state.

3. The method according to claim 1, characterized in that, The aircraft mode of the detected target aircraft includes: Based on the pose detection device installed on the target aircraft, the pose data of the target aircraft is collected; The aircraft mode is determined based on the pose data.

4. The method according to claim 3, characterized in that, The method of collecting pose data of the target aircraft based on the pose detection device installed on the target aircraft includes: The pose detection device, which is based on a GPS inertial navigation system, collects pose data, which includes longitude, latitude, altitude, pitch angle, roll angle, and heading.

5. The method according to claim 1, characterized in that, The emergency deactivation switch has the highest priority and is activated by a preset mechanical switch.

6. The method according to claim 1, characterized in that, The one-button disable switch is a temporary switch, and the default value will be restored after the relevant system is restarted and reset.

7. The method according to claim 1, characterized in that, When the launch status configuration is changed, the launch status configuration is adjusted based on the external display device configured on the target aircraft.

8. The method according to claim 7, characterized in that, The configuration for adjusting the transmission state includes: Based on the configuration file of the permanent configuration, the main software of the temporary configuration is built to adjust the launch state.

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