A ground control system for multi-mode switching of aircraft throughout its life cycle

Abstract

The ground control system for multi-mode switching of a full-life cycle aircraft disclosed in the present invention includes a proximal part and a distal part, wherein the proximal part is close to one end of the full-life cycle aircraft, and the distal part is far away from one end of the full-life cycle aircraft; the proximal part is used to switch the working mode of the ground control system according to the received control command, wherein the working mode of the ground control system corresponds to the multi-mode of the aircraft; the distal part is used to receive the control command for presetting the aircraft operation and send the control command to the proximal part. It is possible to realize automatic and real-time supervision of the changing trend of control system degradation.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft multi-mode switching, and in particular relates to a ground control system for aircraft multi-mode switching throughout its entire life cycle. Background Art

[0002] Aircraft are special products that are stored for a long time and used once for launch. The test control during their use involves multiple modes. How to effectively divide the multiple modes and effectively switch between them has always been a major problem that has troubled the development, production and use departments. Due to the complex structure, high price, small batch, and immature accelerated life research methods of aircraft, it is difficult to give a scientific and practical mode control strategy to achieve optimal health management during development and production. Due to the lack of actual storage environment data and actual aircraft test data support, the current internationally common method is to use long-term power-on and continuous single-mode test control, which usually reduces the service life of the aircraft.

[0003] The multi-mode (multiple working modes) of aircraft development is mainly based on meeting the mission requirements of the aircraft equipment system, at the expense of part of the performance of the aircraft system platform, to achieve the development goals of low loss and cost in multi-mode management, but the reduced performance does not affect the normal operation of the entire aircraft system. This is because as a development aircraft system, each design mode state does not need to be used for a long time, and is generally on standby. When the aircraft system needs to enter a certain mode or simulation state, the multi-mode autonomous system will be able to quickly start from the low-loss mode to the normal working mode to ensure the normal operation of the aircraft system. However, in the process of the multi-mode autonomous system being able to quickly start from the low-loss mode to the normal working mode, there will be a trend of degradation, and a supervision platform for the aircraft multi-mode switching system is urgently needed. Summary of the invention

[0004] The present invention overcomes one of the deficiencies of the prior art and provides a ground control system for multi-mode switching of aircraft throughout its life cycle, which can realize automatic and real-time supervision of the changing trend of control system degradation.

[0005] According to one aspect of the present disclosure, a ground control system for multi-mode switching of a full-life cycle aircraft is provided, the system comprising a proximal portion and a distal portion, the proximal portion being close to one end of the full-life cycle aircraft, and the distal portion being far away from one end of the full-life cycle aircraft;

[0006] a proximal portion, for switching the operating mode of the ground control system according to the received control command, 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 control instructions for preset aircraft operations and send the control instructions to the near-end part.

[0008] In a possible implementation, the remote part is further used to send the received control instruction for preset aircraft operation to the TC end of the aircraft.

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

[0010] Wherein, the fire control box is used to realize the basic test requirements of the aircraft;

[0011] The small power supply is used to provide working 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 supply 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 a possible implementation, the remote part includes an emergency processing device and a remote interactive computer;

[0017] Wherein, the emergency processing device is used to process redundant data of the aircraft in an emergency situation;

[0018] The remote interactive computer is used to receive control instructions for preset aircraft operations.

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

[0020] In a possible implementation, when the working mode of the ground control system is the emergency launch mode, the fire control box and the small power supply of the proximal part are in working state, and the remote interactive computer of the distal part is in working state.

[0021] In one possible implementation, when the working mode of the ground control system is the core mechanism hot backup component mode, the measurement and control processing unit and the power supply system of the proximal part are in working state, and the remote interactive computer of the distal part is in working state.

[0022] In one possible implementation, when the operating mode of the ground control system is the full hot backup mode of the aircraft, the measurement and control processing unit, the power supply system, the measurement and control system and the processor of the proximal part are in working state, and the remote interactive computer, emergency processing device and AC power of the remote part are in working state.

[0023] In a possible implementation, the response capability of the emergency launch mode has the highest priority, and the response capability of the aircraft's full hot backup mode has the lowest priority.

[0024] In a possible implementation, the priority of the response capability of the emergency launch mode is the highest, and the priority of the response capability of all hot standby modes of the aircraft is the lowest, including:

[0025] The emergency launch mode jumps to the core mechanism hot backup component mode or the entire aircraft hot backup mode;

[0026] The core mechanism hot backup component mode jumps to the entire aircraft hot backup mode.

[0027] The ground control system for multi-mode switching of a full-life cycle aircraft disclosed in the present invention includes a proximal part and a distal part, wherein the proximal part is close to one end of the full-life cycle aircraft, and the distal part is far away from one end of the full-life cycle aircraft; the proximal part is used to switch the working mode of the ground control system according to the received control command, wherein the working mode of the ground control system corresponds to the multi-mode of the aircraft; the distal part is used to receive the control command for presetting the aircraft operation and send the control command to the proximal part. It is possible to realize automatic and real-time supervision of the changing trend of control system degradation. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0029] Figure 1 A principle block diagram showing the working mode of the flying ground control system according to an embodiment of the present disclosure is shown;

[0030] Figure 2 A principle block diagram showing that the working mode of the ground control system according to an embodiment of the present disclosure is an emergency launch mode;

[0031] Figure 3A principle block diagram showing a working mode of a ground control system according to an embodiment of the present disclosure as a core mechanism hot backup component mode;

[0032] Figure 4 A principle block diagram showing that the working mode of the ground control system according to an embodiment of the present disclosure is a full hot backup mode; DETAILED DESCRIPTION

[0033] The following will describe the implementation methods of the present invention in detail with reference to the accompanying drawings and embodiments, so that the implementation process of how the present invention applies 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 technical solutions formed are all within the protection scope of the present invention.

[0034] In addition, the steps shown in the flowchart of the accompanying drawings can be executed in a computer such as a set of computer executable instructions. Also, although a logical sequence is shown in the flowchart, in some cases, the steps shown or described can be performed in a sequence different from that here.

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

[0036] Depend on Figure 2-4 As shown, the ground control system includes two parts, a proximal part and a distal part. The proximal part is close to one end of the full life cycle aircraft and is used to switch the working mode of the ground control system according to the received control command, wherein the working mode of the ground control system corresponds to the multi-mode of the aircraft. The distal part is far away from one end of the full life cycle aircraft. It is used to receive the control command for preset aircraft operation and send the control command to the proximal part, for example, to the measurement and control processing unit of the proximal part; at the same time, the distal part is also used to send the received control command for preset aircraft operation to the TC end of the aircraft.

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

[0038] The fire control box is used to achieve the basic test requirements of the aircraft. The small power supply is used to provide working power to the fire control box. As highly real-time embedded measurement and control equipment, the fire control box and the small power supply have fast wake-up or fast response, meet the basic function measurement and control requirements of the aircraft, and realize the ground test control function of the emergency launch mode.

[0039] The measurement and control processing unit is used for multi-threaded online scheduling of the ground control system; the power supply system is used to provide power to the ground control system, for example, the power supply system provides power supply voltage to the measurement and control processing unit, the command and control system, the processor, etc. Among them, the measurement and control processing unit adds complex ground control system operation functions compared to the fire control box, and supports the ability of multi-threaded online scheduling. Compared with the small power supply in the emergency launch mode, the power supply system can achieve high-power, variable-frequency, and high-voltage power output, and support the test and control requirements of the hot backup component mode of the core mechanism of the aircraft.

[0040] The command and control system is used to assist the ground control system in making control decisions, and can ensure the robustness and stability of non-aircraft test control work. The processor is used to improve the processing of system data obtained before the aircraft takes off. The emergency processing device is used to process the redundant data of the aircraft in an emergency. The ground control system's command and control system, processor, emergency processing device, and mains power supply can ensure the redundant fault tolerance and robustness of the ground control system and are used in full hot backup mode.

[0041] The remote interactive computer is used to receive control instructions for preset aircraft operations, such as the interactive information platform of the human in the loop, receive the preset instructions from the superior, and intervene in the test control process as needed. The remote interactive computer can transmit the control instructions for preset aircraft operations to the measurement and control processing unit of the proximal part and the TC end of the aircraft, thereby controlling the proximal part of the ground control system and the aircraft to switch to the corresponding working mode.

[0042] In addition to the hardware circuits for energy management, the ground control system also includes core processors, processor peripheral circuits, memory, communication interfaces, signal conditioning circuits, analog-to-digital conversion circuits and other multi-mode hardware aircraft system analog circuit designs, which will not be introduced in detail here.

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

[0044] The multi-mode of the aircraft includes emergency launch mode, core mechanism hot backup component mode and rocket-ground full hot backup mode. The TC end of the aircraft receives the top-level command (control command) sent by the remote interactive computer of the remote part of the ground control system, and controls the start-up of the aircraft to the emergency launch mode or the core mechanism hot backup component mode or the full hot backup mode of the aircraft according to the top-level command, until the aircraft working mode jumps to the flight state, and the aircraft is launched under the premise that all parameters of the aircraft are safe.

[0045] Figure 1 A principle block diagram of the working mode of an aircraft ground control system according to an embodiment of the present disclosure is shown.

[0046] like Figure 1 As shown, the working modes of the ground control system may include an emergency launch mode, a core mechanism hot backup component mode, and an aircraft full hot backup mode. Among them, the response capability of the emergency launch mode has the highest priority, and the response capability of the aircraft full hot backup mode has the lowest priority. That is, the emergency launch mode can be jumped to the core mechanism hot backup component mode or the aircraft full hot backup mode; the core mechanism hot backup component mode can be jumped to the aircraft full hot backup mode.

[0047] For example, the ground control system can receive preset aircraft operation control instructions through a remote interactive computer, and according to the preset aircraft operation control instructions, it can control the proximal part of the ground control system to realize the aircraft ground system starts working in the emergency launch mode, or realizes the aircraft ground system starts working in the core mechanism hot backup component mode, or realizes the aircraft ground system starts working in the aircraft full hot backup mode, or realizes the aircraft ground system jumps from the emergency launch mode to the core mechanism hot backup mode, or realizes the aircraft ground system jumps from the emergency launch mode to the aircraft full hot backup mode, or realizes the aircraft ground system jumps from the core mechanism hot backup mode to the core mechanism hot backup mode; finally, the mode of taking off the aircraft is directly started from the converted emergency launch mode, core mechanism hot backup mode, and aircraft core mechanism hot backup mode.

[0048] Figure 2-4 A principle block diagram showing the working modes of a ground control system according to an embodiment of the present disclosure, namely, an emergency launch mode, a core mechanism hot backup component mode, and a full hot backup mode. Figure 2-4 The gray part in the diagram is the dormant module, and the white part is the working module.

[0049] Depend on Figure 2 It can be seen that when the working mode of the ground control system is the emergency launch mode, the fire control box and the small power supply of the proximal part are in working state, and the remote interactive computer of the distal part is in working state. Among them, the interactive computer of the distal part sends out the control instruction of the preset aircraft operation, and controls the working mode of the proximal part of the aircraft ground system and the aircraft on-board system to start the emergency launch mode.

[0050] Depend on Figure 3It can be seen that when the working mode of the ground control system is the core mechanism hot backup component mode (this mode has the ability to dynamically monitor thermal response), the measurement and control processing unit of the proximal part and the power supply system are in working state, and the remote interactive computer of the distal part is in working state. Among them, the control instructions for presetting the operation of the aircraft are issued through the remote interactive computer, and the working modes of the proximal end of the aircraft ground system and the aircraft onboard system are started as the core mechanism hot backup component mode. The core mechanism hot backup component mode requires a more comprehensive test, and the embedded response control equipment (fire control box and small power supply) needs to be turned off, and the measurement and control processing unit as the center of the ground control system is enabled to handle complex business.

[0051] Depend on Figure 4 It can be seen that when the working mode of the ground control system is the aircraft full hot standby mode (with full power hot standby capability), the measurement and control processing unit, the power supply system, the measurement and control system and the processor of the proximal part are in working state, and the remote interactive computer, the emergency processing device and the mains power of the remote part are in working state. Among them, the control instructions for preset aircraft operation are issued through the remote interactive computer to control the working mode of the proximal part of the aircraft ground system and the aircraft onboard system to start in full hot standby mode. It can process redundant fault-tolerant information to ensure the robustness and stability of non-aircraft test control work.

[0052] The ground control system for multi-mode switching of a full-life cycle aircraft disclosed in the present invention includes a proximal part and a distal part, wherein the proximal part is close to one end of the full-life cycle aircraft, and the distal part is far away from one end of the full-life cycle aircraft; the proximal part is used to switch the working mode of the ground control system according to the received control command, wherein the working mode of the ground control system corresponds to the multi-mode of the aircraft; the distal part is used to receive the control command for presetting the aircraft operation and send the control command to the proximal part. It is possible to realize automatic and real-time supervision of the changing trend of control system degradation.

[0053] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be included in the protection scope of the present application.

Claims

1. A ground control system for multi-mode switching of aircraft throughout its life cycle, characterized in that: The system comprises a proximal portion and a distal portion, wherein the proximal portion is close to one end of the full life cycle aircraft, and the distal portion is far from one end of the full life cycle aircraft; a proximal portion, for switching the operating mode of the ground control system according to the received control command, the operating mode of the ground control system corresponding to the multi-mode of the aircraft; The remote part is used to receive control instructions for preset aircraft operations and send the control instructions to the near-end part; The proximal part includes a fire control box, a small power supply, a measurement and control processing unit, a power supply system, a command and control system and a processor; Wherein, the fire control box is used to realize the basic test requirements of the aircraft; The small power supply is used to provide working 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 supply 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; The remote part includes an emergency processing device and a remote interactive computer; Wherein, the emergency processing device is used to process redundant data of the aircraft in an emergency situation; The remote interactive computer is used to receive control instructions for preset aircraft operations; The working modes of the ground control system include emergency launch mode, core mechanism hot backup component mode and aircraft full hot backup mode; When the working mode of the ground control system is the emergency launch mode, the fire control box and the small power supply of the proximal part are in working state, and the remote interactive computer of the distal part is in working state.

2. The ground control system according to claim 1, characterized in that: The remote part is also used to send the received control instructions for preset aircraft operations to the TC end of the aircraft.

3. The ground control system according to claim 1, characterized in that: When the working mode of the ground control system is the core mechanism hot backup component mode, the measurement and control processing unit and the power supply system of the proximal part are in working state, and the remote interactive computer of the distal part is in working state.

4. The ground control system according to claim 1, characterized in that: When the working mode of the ground control system is the full hot backup mode of the aircraft, the measurement and control processing unit, the power supply system, the measurement and control system and the processor of the proximal part are in working state, and the remote interactive computer, emergency processing device and AC power of the distal part are in working state.

5. The ground control system according to claim 1, characterized in that: The priority of the response capability of the emergency launch mode is the highest, and the priority of the response capability of the full hot backup mode of the aircraft is the lowest.

6. The ground control system according to claim 5, characterized in that: The priority of the response capability of the emergency launch mode is the highest, and the priority of the response capability of all hot backup modes of the aircraft is the lowest, including: The emergency launch mode jumps to the core mechanism hot backup component mode or the entire aircraft hot backup mode; The core mechanism hot backup component mode jumps to the entire aircraft hot backup mode.

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