Guiding control method suitable for multi-task scene

Abstract

The invention belongs to the technical field of flight control, and particularly relates to a guide control method suitable for a multi-task scene. The method comprises the following steps: step 100, acquiring a task demand, wherein the task demand comprises a plurality of flight paths; step 200, acquiring a guide control logic, wherein the guide control logic comprises a main control logic, an on-board guide sub-control logic, an on-board search sub-control logic, a manual guide sub-control logic and a command guide sub-control logic; and step 300, aircraft guidance control is carried out according to the task demand and the guidance control logic. According to the guide control method suitable for the multi-task scene, the task requirement and the task scene cross calling condition are deconstructed in a mode of combining the main control logic and the sub-control logic, so that the automatic guide function use logic is more reasonable, and the expandability is higher.

Description

Technical Field

[0001] The present application belongs to the field of flight control technology, and in particular relates to a guidance control method adapted to multi-task scenarios. Background Art

[0002] Automatic guidance is one of the main functions of the automatic flight control system. Automatic guidance includes: (1) Long-range guidance. The observation unit discovers and measures the target, sends guidance instructions, and guides the aircraft to the designated airspace or the flight phase where autonomous navigation can be performed. (2) Short-range guidance. After the long-range guidance is completed, it enters the short-range guidance phase. In this guidance phase, the conditions for discovering the target are met, and the onboard electronic equipment is used to detect, identify, intercept, and track the target, control the flight of the aircraft, and gradually meet the mission conditions. The automatic guidance function is mainly used when the aircraft needs to automatically and quickly reach a designated location from a certain location according to the mission requirements, and complete various flight missions according to mission requirements and mission scenarios.

[0003] As the performance of modern aircraft improves and the mission environment becomes more complex, relying entirely on humans to complete complex logic switching will add a huge burden to pilots. Therefore, a set of universal and easy-to-understand control logic will be able to assist pilots in completing rapid command switching, reduce the pilot's operating burden in complex environments, and improve mission accuracy.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide a guidance control method adapted to multi-task scenarios to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A guidance control method adapted to multi-task scenarios, comprising:

[0008] Step 100: Obtaining mission requirements, wherein the mission requirements include multiple flight trajectories;

[0009] Step 200, obtaining the guidance control logic, wherein the guidance control logic includes the main control logic, the onboard guidance sub-control logic, the onboard search sub-control logic, the manual guidance sub-control logic, and the command guidance sub-control logic;

[0010] Step 300: Perform aircraft guidance control according to the mission requirements and the guidance control logic.

[0011] In at least one embodiment of the present application, the flight trajectory includes:

[0012] Close-range guidance with full afterburner acceleration climbing trajectory, climbing trajectory with engine at maximum working state cruising flight, long-range guidance with acceleration climbing trajectory, evacuation trajectory, and descent trajectory.

[0013] In at least one embodiment of the present application, the main control logic includes:

[0014] Step 211, entering the boot control, determining whether it is the first time to enter the boot;

[0015] If it is the first time to enter the boot, then the boot is initialized and then the process goes to step 212;

[0016] If it is not the first time to enter the boot, directly go to step 212;

[0017] Step 212: determine whether the manual guidance instruction is valid;

[0018] If the manual guidance command is valid, the manually bound given altitude, given speed, and given heading are read, and the manual guidance control sub-mode is entered;

[0019] If the manual guidance instruction is invalid, the given altitude, given speed, and given heading sent by the mission aircraft are read, and step 213 is entered;

[0020] Step 213, determining whether the onboard guidance instruction is valid;

[0021] If the onboard guidance command is valid, the onboard guidance control sub-mode is entered;

[0022] If the onboard guidance instruction is invalid, proceed to step 214;

[0023] Step 214, determining whether the on-board search instruction is valid;

[0024] If the on-board search command is valid, the on-board search control sub-mode is entered;

[0025] If the onboard search command is invalid, the command guidance control submode will be entered.

[0026] In at least one embodiment of the present application, the onboard guidance sub-control logic includes:

[0027] Step 221, entering the onboard guidance control sub-mode, and determining whether it is the first time to enter the onboard guidance control sub-mode;

[0028] If it is the first time to enter the onboard guidance control sub-mode, the onboard guidance initialization is performed and then the mode I control is entered;

[0029] If it is not the first time to enter the onboard guidance control sub-mode, it will directly enter mode I control.

[0030] In at least one embodiment of the present application, the on-board search sub-control logic includes:

[0031] Step 231, entering the onboard search control sub-mode, and determining whether it is the first time to enter the onboard search control sub-mode;

[0032] If it is the first time to enter the on-board search control sub-mode, the on-board search initialization is performed and then the mode I control is entered;

[0033] If it is not the first time to enter the on-board search control sub-mode, directly enter mode I control.

[0034] In at least one embodiment of the present application, the manual guidance sub-control logic includes:

[0035] Step 241, entering the manual guidance control sub-mode, and determining whether it is the first time to enter the manual guidance control sub-mode;

[0036] If it is the first time to enter the manual guidance control sub-mode, the manual guidance initialization is performed and then the mode I control is entered;

[0037] If it is not the first time to enter the manual guidance control sub-mode, it will directly enter the mode I control.

[0038] In at least one embodiment of the present application, the command and guidance sub-control logic includes:

[0039] Step 251, entering the command guidance control sub-mode, and determining whether it is the first time to enter the command guidance control sub-mode;

[0040] If it is the first time to enter the command guidance control sub-mode, the command guidance initialization is performed and then the process goes to step 252;

[0041] If it is not the first time to enter the command guidance control sub-mode, directly go to step 252;

[0042] Step 252, determine whether the mode II instruction is valid;

[0043] If the mode II instruction is valid, proceed to step 253;

[0044] If the mode II instruction is invalid, proceed to step 254;

[0045] Step 253, perform mode II command initialization, whether the mode II command initialization is successful or not, enter mode II control;

[0046] Step 254, determine whether the mode III instruction is valid;

[0047] If the mode III instruction is valid, proceed to step 255;

[0048] If the mode III command is invalid, enter mode I control;

[0049] Step 255, perform mode III command initialization. If the mode III command initialization is successful, enter mode III control. If the mode III command initialization is unsuccessful, enter mode II control.

[0050] In at least one embodiment of the present application, in step 253 and step 255, after entering mode II control, if a preset condition is met, then entering mode III control.

[0051] The invention has at least the following beneficial technical effects:

[0052] The guidance control method of the present application, which is adapted to multi-task scenarios, deconstructs the task requirements and the cross-calling of task scenarios by combining the main control logic and the sub-control logic, making the use logic of the automatic guidance function more reasonable and more scalable. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] Figure 1 This is a schematic diagram of the task requirements of an implementation method of the present application;

[0054] Figure 2 It is a main control logic schematic diagram of an implementation method of the present application;

[0055] Figure 3 It is a schematic diagram of the onboard guidance sub-control logic of an implementation mode of the present application;

[0056] Figure 4 It is a schematic diagram of the on-board search sub-control logic of one embodiment of the present application;

[0057] Figure 5 It is a schematic diagram of the control logic of the artificial guide sub-device according to one embodiment of the present application;

[0058] Figure 6 It is a schematic diagram of the command and guidance sub-control logic of an implementation mode of the present application. DETAILED DESCRIPTION

[0059] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0060] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0061] The following is combined with Figures 1 to 6 This application is described in further detail.

[0062] The present application provides a guidance control method adapted to multi-task scenarios, comprising the following steps:

[0063] Step 100: Obtain mission requirements, which include multiple flight trajectories;

[0064] Step 200, obtaining the guidance control logic, which includes the main control logic, the onboard guidance sub-control logic, the onboard search sub-control logic, the manual guidance sub-control logic, and the command guidance sub-control logic;

[0065] Step 300: Perform aircraft guidance control according to mission requirements and guidance control logic.

[0066] The guidance control method of the present application adapted to multi-task scenarios, such as Figure 1As shown, five flight trajectories are given in the mission requirements, 1-2-3-4-5-6 represents the close-range guidance full afterburner speed-up climb trajectory, 1-2'-3'-FE represents the climb trajectory of the engine's maximum working state cruise flight, 1-2'-3'-4-5-6 represents the long-range guidance speed-up climb trajectory, FE, AB, CD represent the evacuation trajectory, H1-TK, H2-TK, H3-K represent the descent trajectory. Among them, 1 represents the starting point of the climb maneuver, 2 represents the speed-up climb point, 2' represents the economic climb point, 3', 3, 4 represent the acceleration channel trajectory points, 5, 6 represent the speed-up climb point, F represents the sub-economic climb point, A, C represent the maneuvering climb point, H1, H2, H3 represent the evacuation maneuver starting point, T represents the economic evacuation point, and K represents the speed-up evacuation point.

[0067] The guidance control method of the present application adapted to multi-task scenarios, such as Figure 2 As shown, the main control logic includes:

[0068] Step 211, entering the boot control, determining whether it is the first time to enter the boot;

[0069] If it is the first time to enter the boot, then the boot is initialized and then the process goes to step 212;

[0070] If it is not the first time to enter the boot, directly go to step 212;

[0071] Step 212: determine whether the manual guidance instruction is valid;

[0072] If the manual guidance command is valid, the manually bound given altitude, given speed, and given heading are read, and the manual guidance control sub-mode is entered;

[0073] If the manual guidance instruction is invalid, the given altitude, given speed, and given heading sent by the mission aircraft are read, and step 213 is entered;

[0074] Step 213, determining whether the onboard guidance instruction is valid;

[0075] If the onboard guidance command is valid, the onboard guidance control sub-mode is entered;

[0076] If the onboard guidance instruction is invalid, proceed to step 214;

[0077] Step 214, determining whether the on-board search instruction is valid;

[0078] If the on-board search command is valid, the on-board search control sub-mode is entered;

[0079] If the onboard search command is invalid, the command guidance control submode will be entered.

[0080] like Figure 3As shown, in this embodiment, the onboard guidance sub-control logic includes:

[0081] Step 221, entering the onboard guidance control sub-mode, and determining whether it is the first time to enter the onboard guidance control sub-mode;

[0082] If it is the first time to enter the onboard guidance control sub-mode, the onboard guidance initialization is performed and then the mode I control is entered;

[0083] If it is not the first time to enter the onboard guidance control sub-mode, it will directly enter mode I control.

[0084] like Figure 4 As shown, in this embodiment, the on-board search sub-control logic includes:

[0085] Step 231, entering the onboard search control sub-mode, and determining whether it is the first time to enter the onboard search control sub-mode;

[0086] If it is the first time to enter the on-board search control sub-mode, the on-board search initialization is performed and then the mode I control is entered;

[0087] If it is not the first time to enter the on-board search control sub-mode, directly enter mode I control.

[0088] like Figure 5 As shown, in this embodiment, the manual guidance sub-control logic includes:

[0089] Step 241, entering the manual guidance control sub-mode, and determining whether it is the first time to enter the manual guidance control sub-mode;

[0090] If it is the first time to enter the manual guidance control sub-mode, the manual guidance initialization is performed and then the mode I control is entered;

[0091] If it is not the first time to enter the manual guidance control sub-mode, it will directly enter the mode I control.

[0092] like Figure 6 As shown, in this embodiment, the command and guidance sub-control logic includes:

[0093] Step 251, entering the command guidance control sub-mode, and determining whether it is the first time to enter the command guidance control sub-mode;

[0094] If it is the first time to enter the command guidance control sub-mode, the command guidance initialization is performed and then the process goes to step 252;

[0095] If it is not the first time to enter the command guidance control sub-mode, directly go to step 252;

[0096] Step 252, determine whether the mode II instruction is valid;

[0097] If the mode II instruction is valid, proceed to step 253;

[0098] If the mode II instruction is invalid, proceed to step 254;

[0099] Step 253, perform mode II command initialization, whether the mode II command initialization is successful or not, enter mode II control;

[0100] Step 254, determine whether the mode III instruction is valid;

[0101] If the mode III instruction is valid, proceed to step 255;

[0102] If the mode III command is invalid, enter mode I control;

[0103] Step 255, perform mode III command initialization. If the mode III command initialization is successful, enter mode III control. If the mode III command initialization is unsuccessful, enter mode II control.

[0104] Among them, in step 253 and step 255, after entering mode II control, if the preset conditions are met, entering mode III control.

[0105] The guidance control method of the present application, which is adapted to multi-task scenarios, selects to enter the corresponding sub-control logic according to the main control logic, and enters different modal controls when the conditions are met, thereby controlling the aircraft to fly quickly to the specified position according to the selected flight trajectory and guidance method.

[0106] The guidance control method of this application, which is adapted to multi-task scenarios, unifies the mission requirements and mission scenarios by combining the main control logic and the sub-control logic. This control logic is proposed for the first time in China, filling a domestic gap. It greatly simplifies the problem of cross-calling between mission requirements and mission scenarios, and uses a common logic architecture to improve the rationality of system switching, which is in line with the pilot's usage habits; at the same time, it retains a logical interface for new mission scenarios and mission requirements that may appear in the future, ensuring scalability. The control logic is highly versatile and easy to promote, suitable for subsequent automatic guidance function design, and has great application value.

[0107] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A guidance control method adapted to multi-task scenarios, characterized in that: include: Step 100: Obtaining mission requirements, wherein the mission requirements include multiple flight trajectories; Step 200, obtaining the guidance control logic, wherein the guidance control logic includes the main control logic, the onboard guidance sub-control logic, the onboard search sub-control logic, the manual guidance sub-control logic, and the command guidance sub-control logic; Step 300: Perform aircraft guidance control according to the mission requirements and the guidance control logic.

2. The guidance control method adapted to multi-task scenarios according to claim 1, characterized in that: The flight trajectory includes: Close-range guidance with full afterburner acceleration climbing trajectory, climbing trajectory with engine at maximum working state cruising flight, long-range guidance with acceleration climbing trajectory, evacuation trajectory, and descent trajectory.

3. The guidance control method adapted to multi-task scenarios according to claim 2, characterized in that: The main control logic includes: Step 211, entering the boot control, determining whether it is the first time to enter the boot; If it is the first time to enter the boot, then the boot is initialized and then the process goes to step 212; If it is not the first time to enter the boot, directly go to step 212; Step 212: determine whether the manual guidance instruction is valid; If the manual guidance command is valid, the manually bound given altitude, given speed, and given heading are read, and the manual guidance control sub-mode is entered; If the manual guidance instruction is invalid, the given altitude, given speed, and given heading sent by the mission aircraft are read, and step 213 is entered; Step 213, determining whether the onboard guidance instruction is valid; If the onboard guidance command is valid, the onboard guidance control sub-mode is entered; If the onboard guidance instruction is invalid, proceed to step 214; Step 214, determining whether the on-board search instruction is valid; If the on-board search command is valid, the on-board search control sub-mode is entered; If the onboard search command is invalid, the command guidance control submode will be entered.

4. The guidance control method adapted to multi-task scenarios according to claim 3 is characterized in that: The onboard guidance sub-control logic includes: Step 221, entering the onboard guidance control sub-mode, and determining whether it is the first time to enter the onboard guidance control sub-mode; If it is the first time to enter the onboard guidance control sub-mode, the onboard guidance initialization is performed and then the mode I control is entered; If it is not the first time to enter the onboard guidance control sub-mode, it will directly enter mode I control.

5. The guidance control method adapted to multi-task scenarios according to claim 4, characterized in that: The on-board search sub-control logic includes: Step 231, entering the onboard search control sub-mode, and determining whether it is the first time to enter the onboard search control sub-mode; If it is the first time to enter the on-board search control sub-mode, the on-board search initialization is performed and then the mode I control is entered; If it is not the first time to enter the on-board search control sub-mode, directly enter mode I control.

6. The guidance control method adapted to multi-task scenarios according to claim 5, characterized in that: The artificial guidance sub-control logic includes: Step 241, entering the manual guidance control sub-mode, and determining whether it is the first time to enter the manual guidance control sub-mode; If it is the first time to enter the manual guidance control sub-mode, the manual guidance initialization is performed and then the mode I control is entered; If it is not the first time to enter the manual guidance control sub-mode, it will directly enter the mode I control.

7. The guidance control method adapted to multi-task scenarios according to claim 6, characterized in that: The command and guidance sub-control logic includes: Step 251, entering the command guidance control sub-mode, and determining whether it is the first time to enter the command guidance control sub-mode; If it is the first time to enter the command guidance control sub-mode, the command guidance initialization is performed and then the process goes to step 252; If it is not the first time to enter the command guidance control sub-mode, directly go to step 252; Step 252, determine whether the mode II instruction is valid; If the mode II instruction is valid, proceed to step 253; If the mode II instruction is invalid, proceed to step 254; Step 253, perform mode II command initialization, whether the mode II command initialization is successful or not, enter mode II control; Step 254, determine whether the mode III instruction is valid; If the mode III instruction is valid, proceed to step 255; If the mode III command is invalid, enter mode I control; Step 255, perform mode III command initialization. If the mode III command initialization is successful, enter mode III control. If the mode III command initialization is unsuccessful, enter mode II control.

8. The guidance control method adapted to multi-task scenarios according to claim 7, characterized in that: In step 253 and step 255, after entering mode II control, if the preset conditions are met, then entering mode III control.

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