A ground control system for full life cycle aircraft multimodal switching

Abstract

The ground control system for full life cycle aircraft multimodal switching of the present disclosure comprises two parts of near end and far end, the near end part is close to one end of the full life cycle aircraft, and the far end part is away from one end of the full life cycle aircraft; the near end part is used for switching the working mode of the ground control system according to the received control instruction, wherein the working mode of the ground control system corresponds to the multimode of the aircraft; the far end part is used for receiving the control instruction of preset aircraft working and sending the control instruction to the near end part. The supervision of the change trend of the automatic and real-time control system deterioration can be realized.

Description

Technical Field

[0001] This invention belongs to the field of aircraft multimodal switching technology, and specifically relates to a ground control system for aircraft multimodal switching throughout its entire life cycle. Background Technology

[0002] Aircraft are special products designed for long-term storage and single-launch use. Their testing and control during operation involves multiple modes. Effectively classifying these modes and seamlessly switching between them has long been a major challenge for research, development, production, and user departments. Due to their complex structure, high cost, and small production runs, and the immaturity of accelerated lifespan research methods, it is difficult to develop scientific and practical mode control strategies to achieve optimal health management during research and production. Lacking supporting data from actual storage environments and real-world aircraft testing, the current internationally accepted approach is to use continuous power-on, single-mode testing and control, which typically reduces the aircraft's lifespan.

[0003] Multimodal (multiple operating modes) aircraft development primarily aims to meet the mission requirements of the aircraft's equipment systems, sacrificing some performance of the aircraft system platform to achieve the development goals of low loss and cost in multimodal management. However, the reduced performance does not affect the normal operation of the entire aircraft system because, as an aircraft system under development, each design mode is not required for long-term use and is generally kept on standby. When the aircraft system needs to enter a certain mode or simulation state, the multimodal autonomous system can quickly start from the low-loss mode and enter the normal operating mode, ensuring the normal operation of the aircraft system. However, during the process of the multimodal autonomous system quickly starting from the low-loss mode and entering the normal operating mode, a degradation trend may occur, necessitating a monitoring platform for the aircraft's multimodal switching system. Summary of the Invention

[0004] This invention overcomes one of the shortcomings of the prior art and provides a ground control system for multi-mode switching of aircraft throughout its entire life cycle, which can realize automated, real-time monitoring of the degradation trend of the control system.

[0005] According to one aspect of this disclosure, a ground control system for multi-mode switching of an aircraft throughout its entire life cycle is proposed. The system includes a near end and a far end, the near end being close to one end of the aircraft throughout its life cycle, and the far end being far from one end of the aircraft throughout its life cycle.

[0006] The near-end portion is used to switch the operating mode of the ground control system according to the received control commands, wherein the operating mode of the ground control system corresponds to the multi-mode of the aircraft;

[0007] The remote part is used to receive preset control commands for the operation of the aircraft and send the control commands to the near part.

[0008] In one possible implementation, the remote portion is also used to send the received preset control commands for aircraft operation to the TC terminal of the aircraft.

[0009] In one possible implementation, the near-end portion includes a fire control box, a small power supply, a measurement and control processing unit, a power system, a command and control system, and a processor;

[0010] The fire control box is used to meet the basic testing requirements of the aircraft.

[0011] The small power supply is used to provide operating power to the fire control box;

[0012] The measurement and control processing unit is used for multi-threaded online scheduling of the ground control system;

[0013] The power system is used to provide power to the ground control system;

[0014] The command and control system is used to assist the ground control system in making control decisions;

[0015] The processor is used to improve the processing of system data acquired before the aircraft takes off.

[0016] In one possible implementation, the remote portion includes an emergency response device and a remote interactive computer;

[0017] The emergency processing device is used to process redundant data of the aircraft in emergency situations.

[0018] The remote interactive computer is used to receive preset control commands for the operation of the aircraft.

[0019] In one possible implementation, the operating modes of the ground control system include emergency launch mode, core mechanism hot backup component mode, and full spacecraft hot backup mode.

[0020] In one possible implementation, when the ground control system is in emergency launch mode, the fire control box and small power supply of the near-end section are in operation, and the remote interactive computer of the far-end section is in operation.

[0021] In one possible implementation, when the ground control system operates in the core mechanism hot backup component mode, the measurement and control processing unit and the power system of the near-end part are in operation, and the remote interactive computer of the far-end part is in operation.

[0022] In one possible implementation, when the ground control system operates in the full hot backup mode of the aircraft, the telemetry and control processing unit, the power system, the telemetry and control system and the processor of the near-end part are in working condition, and the remote interactive computer, the emergency response device and the mains power of the far-end part are in working condition.

[0023] In one possible implementation, the emergency launch mode has the highest priority in terms of responsiveness, while the full hot standby mode of the aircraft has the lowest priority in terms of responsiveness.

[0024] In one possible implementation, the emergency launch mode has the highest priority in terms of response capability, and the full hot standby mode of the aircraft has the lowest priority in terms of response capability, including:

[0025] The emergency launch mode will switch to the hot backup component mode of the core mechanism or the hot backup mode of the entire aircraft.

[0026] The core mechanism hot backup component mode is switched to the full hot backup mode of the aircraft.

[0027] This disclosure discloses a ground control system for multi-modal switching of an aircraft throughout its entire lifecycle, comprising a near-end and a far-end. The near-end is close to one end of the aircraft throughout its lifecycle, and the far-end is far from one end. The near-end is used to switch the operating mode of the ground control system according to received control commands, wherein the operating mode of the ground control system corresponds to the multi-modal characteristics of the aircraft. The far-end is used to receive preset control commands for aircraft operation and send the control commands to the near-end. This enables automated, real-time monitoring of the degradation trends of the control system. Attached Figure Description

[0028] The accompanying drawings are used to provide a further understanding of the technical solutions of this application or the prior art, and constitute a part of the specification. The drawings illustrating embodiments of this application, together with the embodiments of this application, are used to explain the technical solutions of this application, but do not constitute a limitation on the technical solutions of this application.

[0029] Figure 1 A schematic block diagram illustrating the operating mode of a flight ground control system according to an embodiment of the present disclosure is shown.

[0030] Figure 2 A schematic block diagram of the ground control system according to an embodiment of the present disclosure, operating in emergency launch mode, is shown.

[0031] Figure 3A schematic block diagram is shown of the principle of the ground control system according to an embodiment of the present disclosure, with the operating mode being the core mechanism hot backup component mode;

[0032] Figure 4 A schematic diagram of the ground control system according to an embodiment of the present disclosure is shown, with the operating mode being a full hot backup mode. Detailed Implementation

[0033] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings and examples, so that the process of how the present invention uses technical means to solve technical problems and achieve corresponding technical effects can be fully understood and implemented accordingly. The various features in the examples and embodiments of this application can be combined with each other without conflict, and the resulting technical solutions are all within the protection scope of the present invention.

[0034] Furthermore, the steps illustrated in the flowcharts of the accompanying drawings can be executed in a computer, such as a set of computer-executable instructions. Also, although a logical order is shown in the flowcharts, in some cases the steps shown or described may be performed in a different order than that presented here.

[0035] Figure 2-4 Principle block diagrams of different operating modes of a ground control system for multi-mode switching of an aircraft throughout its entire life cycle, according to an embodiment of the present disclosure, are shown.

[0036] Depend on Figure 2-4 As shown, the ground control system comprises a near-end and a far-end. The near-end is located closer to one end of the aircraft throughout its lifecycle and is used to switch the operating mode of the ground control system according to received control commands. The operating mode of the ground control system corresponds to the multi-modal operation of the aircraft. The far-end is located further away from the aircraft throughout its lifecycle. It is used to receive preset control commands for aircraft operation and send these commands to the near-end, for example, to the telemetry, tracking, and command (TT&C) processing unit within the near-end. Simultaneously, the far-end also sends the received preset control commands for aircraft operation to the TC (Traffic Control Unit) of the aircraft.

[0037] In one example, by Figure 2-4 As shown, the near-end portion of the ground control system may include a fire control box, a small power supply, a measurement and control processing unit, a power system, a command and control system, and a processor; the far-end portion includes an emergency response device and a remote interactive computer.

[0038] The fire control box is used to meet the basic testing requirements of the aircraft. The small power supply provides operating power to the fire control box. As highly real-time embedded measurement and control devices, the fire control box and the small power supply have the ability to quickly wake up or respond, meet the basic functional measurement and control requirements of the aircraft, and realize the ground test control function in emergency launch mode.

[0039] The telemetry, control and processing unit (TT&C unit) is used for multi-threaded online scheduling of the ground control system; the power supply system provides power to the ground control system, for example, supplying power voltage to the TT&C unit, command and control system, processor, etc. The TT&C unit adds complex ground control system operation functions compared to the fire control box, supporting multi-threaded online scheduling capabilities. Compared to the small power supply in emergency launch mode, the power supply system can achieve high-power, variable-frequency, high-voltage power output, supporting the testing and control requirements of the aircraft's core mechanism hot backup components.

[0040] The command and control system assists the ground control system in making control decisions, ensuring the robustness and stability of non-aircraft test control operations. The processor enhances the processing of pre-flight system data acquired by the aircraft. The emergency processing unit handles redundant aircraft data in emergency situations. These components—command and control system, processor, emergency processing unit, and mains power—ensure the ground control system's redundancy, fault tolerance, and robustness, allowing it to operate in full hot-standby mode.

[0041] The remote interactive computer is used to receive pre-set control commands for aircraft operation, such as those from a human-in-the-loop interactive information platform. It receives pre-set commands from higher authorities and intervenes in the test control process as needed. Through the remote interactive computer, pre-set control commands for aircraft operation can be transmitted to the telemetry and control processing unit (TT&C) at the near end and the aircraft's control center (TC), thereby controlling the near end of the ground control system and the aircraft to switch to the corresponding operating mode.

[0042] In addition to the hardware circuitry for energy management, the ground control system also includes analog circuit designs for the development of multiple hardware aircraft systems, such as a core processor, processor peripheral circuitry, memory, communication interface, signal conditioning circuitry, and analog-to-digital conversion circuitry. These will not be discussed in detail here.

[0043] In one example, the operating mode of the ground control system corresponds to the multimodal operation of the aircraft.

[0044] The aircraft's multi-mode operation includes emergency launch mode, core mechanism hot backup component mode, and rocket-ground full hot backup mode. The aircraft's TC terminal receives top-level commands (control commands) from the remote interactive computer of the ground control system. Based on the top-level commands, the aircraft is controlled to start in emergency launch mode, core mechanism hot backup component mode, or full hot backup mode until the aircraft's operating mode switches to flight mode, and the aircraft is launched under the premise that all parameters of the aircraft are safe.

[0045] Figure 1 A schematic block diagram illustrating the operating mode of a flight ground control system according to an embodiment of the present disclosure is shown.

[0046] like Figure 1 As shown, the ground control system's operating modes can include emergency launch mode, core mechanism hot backup component mode, and full spacecraft hot backup mode. Among these, the emergency launch mode has the highest priority for response capability, while the full spacecraft hot backup mode has the lowest priority. This means it can switch between the emergency launch mode and the core mechanism hot backup component mode, or vice versa.

[0047] For example, the ground control system can receive preset control commands for the aircraft's operation via a remote interactive computer. Based on these commands, it can control the near-end portion of the ground control system to initiate the aircraft's ground system into emergency launch mode, core mechanism hot backup component mode, full hot backup mode, or switch from emergency launch mode to core mechanism hot backup mode, or switch from emergency launch mode to full hot backup mode, or switch from core mechanism hot backup mode to core mechanism hot backup mode. Finally, the transition from emergency launch mode, core mechanism hot backup mode, or core mechanism hot backup mode directly initiates the aircraft's takeoff mode.

[0048] Figure 2-4 A schematic diagram of the operating modes of a ground control system according to an embodiment of the present disclosure is shown, namely emergency launch mode, core mechanism hot backup component mode, and full hot backup mode. Figure 2-4 The gray area represents the hibernation module, and the white area represents the working module.

[0049] Depend on Figure 2 It is known that when the ground control system is in emergency launch mode, the fire control box and small power supply in the near-end section are operational, and the remote interactive computer in the far-end section is also operational. Specifically, the remote interactive computer issues preset control commands for the aircraft's operation, controlling the near-end of the aircraft's ground system and the onboard system to activate the emergency launch mode.

[0050] Depend on Figure 3It is known that when the ground control system operates in the core mechanism hot backup component mode (this mode has dynamic monitoring and thermal response capabilities), the near-end measurement and control processing unit and the power system are operational, as is the remote interactive computer in the far-end section. Specifically, by issuing preset control commands for the aircraft's operation through the remote interactive computer, the operating mode of the near-end of the aircraft's ground system and the onboard system is activated to the core mechanism hot backup component mode. The core mechanism hot backup component mode requires comprehensive testing, necessitating the shutdown of embedded response control devices (fire control box and small power supply) and the activation of the measurement and control processing unit, which serves as the central hub of the ground control system, to handle complex operations.

[0051] Depend on Figure 4 It is known that when the ground control system operates in the full hot backup mode (possessing full-power hot standby capability), the near-end measurement and control processing unit, the power system, the measurement and control system, and the processor are operational, while the remote interactive computer, emergency response device, and mains power are operational in the far-end. Specifically, by issuing preset control commands for the aircraft's operation through the remote interactive computer, the operating mode of the near-end of the ground system and the onboard system is activated to full hot backup mode. This allows for the processing of redundant fault-tolerant information, ensuring the robustness and stability of non-aircraft test control operations.

[0052] This disclosure discloses a ground control system for multi-modal switching of an aircraft throughout its entire lifecycle, comprising a near-end and a far-end. The near-end is close to one end of the aircraft throughout its lifecycle, and the far-end is far from one end. The near-end is used to switch the operating mode of the ground control system according to received control commands, wherein the operating mode of the ground control system corresponds to the multi-modal characteristics of the aircraft. The far-end is used to receive preset control commands for aircraft operation and send the control commands to the near-end. This enables automated, real-time monitoring of the degradation trends of the control system.

[0053] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application, and should all be included within the protection scope of this application.

Claims

1. A ground control system for multi-mode switching of an aircraft throughout its entire life cycle, characterized in that, The system includes a proximal portion and a distal portion, the proximal portion being close to one end of the aircraft throughout its life cycle, and the distal portion being far from one end of the aircraft throughout its life cycle. The near-end portion is used to switch the operating mode of the ground control system according to the received control commands, and the operating mode of the ground control system corresponds to the multi-mode of the aircraft. The remote unit is used to receive preset control commands for the operation of the aircraft and to transmit the control commands. Send to the near end portion; The operating modes of the ground control system include emergency launch mode, core mechanism hot backup component mode, and full spacecraft hot backup mode. When the ground control system is in emergency launch mode, the fire control box and small power supply of the near end are in working state, and the remote interactive computer of the far end is in working state. When the ground control system operates in the core mechanism hot backup component mode, the measurement and control processing unit and power system of the near-end part are in working state, and the remote interactive computer of the far-end part is in working state. When the ground control system operates in the full hot backup mode of the aircraft, the telemetry and control processing unit, the power system, the command and control system and the processor of the near-end part are in working condition, and the remote interactive computer, the emergency response device and the mains power of the far-end part are in working condition.

2. The ground control system according to claim 1, characterized in that, The remote unit is also used to send the received preset control commands for the aircraft's operation to the TC terminal of the aircraft.

3. The ground control system according to claim 1, characterized in that, The near-end portion includes a fire control box, a small power supply, a measurement and control processing unit, a power system, a command and control system, and a processor; The fire control box is used to meet the basic testing requirements of the aircraft. The small power supply is used to provide operating power to the fire control box; The measurement and control processing unit is used for multi-threaded online scheduling of the ground control system; The power system is used to provide power to the ground control system; The command and control system is used to assist the ground control system in making control decisions; The processor is used to improve the processing of system data acquired before the aircraft takes off.

4. The ground control system according to claim 3, characterized in that, The remote component includes an emergency response device and a remote interactive computer; The emergency processing device is used to process redundant data of the aircraft in emergency situations. The remote interactive computer is used to receive preset control commands for the operation of the aircraft.

5. The ground control system according to claim 4, characterized in that, The emergency launch mode has the highest priority in response capability, while the full hot backup mode of the aircraft has the lowest priority in response capability.

6. The ground control system according to claim 5, characterized in that, The emergency launch mode has the highest priority in response capability, while the full hot backup mode of the aircraft has the lowest priority in response capability, including: The emergency launch mode will switch to the hot backup component mode of the core mechanism or the hot backup mode of the entire aircraft. The core mechanism hot backup component mode is switched to the full hot backup mode of the aircraft.

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