CN114542323A - Control method and device of vectoring nozzle - Google Patents
Control method and device of vectoring nozzle Download PDFInfo
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- CN114542323A CN114542323A CN202111638016.1A CN202111638016A CN114542323A CN 114542323 A CN114542323 A CN 114542323A CN 202111638016 A CN202111638016 A CN 202111638016A CN 114542323 A CN114542323 A CN 114542323A
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- 239000007921 spray Substances 0.000 claims description 10
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- 238000012544 monitoring process Methods 0.000 claims description 6
- 230000004044 response Effects 0.000 abstract description 8
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract description 5
- 238000013461 design Methods 0.000 description 4
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
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Abstract
The application belongs to the field of vectoring nozzle control, and particularly relates to a vectoring nozzle control method and device. The method comprises the steps of S1, acquiring a maneuvering state selection signal of a user, wherein the maneuvering state comprises a conventional maneuvering state, an ultra-maneuvering state and a dynamic change-out state; step S2, determining whether the airplane can enter a specified maneuvering state according to the current state of the airplane; step S3, if the aircraft can enter a designated maneuvering state, determining a theoretical offset angle of the vectoring nozzle according to a flight attack angle corresponding to the maneuvering state, otherwise, prompting that the state fails to enter; and step S4, driving the actuating cylinder until the position of the vectoring nozzle is the same as the theoretical position as monitored by the sensor. This application can be effectively to the mobile demand of difference make judgement and response, realizes different thrust vector schemes under the different flight operating modes, realizes vector control and the meticulous cooperation of flight control surface, promotes the response speed of vectoring nozzle, promotes the turn rate of aircraft.
Description
Technical Field
The application belongs to the field of vectoring nozzle control, and particularly relates to a vectoring nozzle control method and device.
Background
A vector nozzle of a fighter engine is a key component for realizing thrust vector, and has the main functions of: in the flying process of the fighter, the thrust vector function of the engine is realized through vector deflection, and yaw or rolling acceleration is generated, so that the running distance of the fighter is shortened, and the maneuvering performance is enhanced. The vector control of the engine is closely related to the flight attitude, the control surface and the like of the airplane, and the current domestic vector control scheme design of the tail nozzle adopts an integral design: after a pilot gives a thrust vector instruction, the integrated controller evaluates whether the vector instruction can be executed or not through parameter acquisition, and drives the actuating cylinder to drive the tail nozzle to deflect through the engine control system to enter a vector thrust state after the condition that the vector thrust state is allowed to be entered is determined.
Along with the gradual improvement of the maneuverability of the fighter plane, the flying angle of attack range of the plane is gradually enlarged, and the demand for vector thrust is gradually improved. Due to the fact that the integral control scheme is not strong in pertinence to different flight angle of attack requirements, after instructions of a pilot are obtained, unified judgment logic needs to be executed, and a vector method cannot be selected autonomously, so that the response speed in the processes of judgment of a vector state, evaluation of a deflection angle and the like is relatively slow, and the requirement for the maneuvering performance of a fighter plane may not be met.
Disclosure of Invention
In order to solve the problems, the application provides a control method and a control device of a vectoring nozzle, the precise matching of engine thrust vector control and a flight control surface is realized by adopting a sectional control scheme of the vectoring nozzle, the situation that the same thrust vector control is adopted all the time in a large flight incidence angle range, a vectoring method cannot be selected autonomously, and the response speed of the vectoring nozzle is reduced is avoided.
The application provides in a first aspect a method for controlling a vectoring nozzle, comprising:
step S1, acquiring a maneuvering state selection signal of a user, wherein the maneuvering state comprises a conventional maneuvering state, a super maneuvering state and a dynamic changing state;
step S2, determining whether the airplane can enter a specified maneuvering state according to the current state of the airplane;
step S3, if the aircraft can enter a designated maneuvering state, determining a theoretical offset angle of the vectoring nozzle according to a flight attack angle corresponding to the maneuvering state, otherwise, prompting that the state fails to enter;
and step S4, driving the actuating cylinder until the position of the vectoring nozzle is the same as the theoretical position as monitored by the sensor.
Preferably, in step S1, the maneuver state selection signal is provided by a maneuver control switch, which is disposed on a console of the cockpit and is composed of three buttons, and the airplane corresponds to a normal maneuver state, a super maneuver state and a dynamic maneuver out state of the airplane.
Preferably, the step S2 of determining whether the aircraft can enter the designated maneuver state according to the current state of the aircraft includes:
determining whether the airplane can enter a conventional maneuvering state according to the current state of the airplane, wherein the determining whether the airplane can enable a flight attack angle to intervene for 0-30 degrees according to the current state of the airplane is included;
determining whether the aircraft can enter a super-maneuvering state according to the current state of the aircraft, wherein the determining whether the aircraft can enable a flight attack angle to intervene for 30-60 degrees according to the current state of the aircraft is included;
and determining whether the aircraft can enter a dynamic change-out state according to the current state of the aircraft, wherein the step of determining whether the aircraft can enable the flight angle of attack to intervene for 60-90 degrees according to the current state of the aircraft is included.
Preferably, step S4 further includes actuating the actuator cylinder to deflect the jet nozzle via the electro-hydraulic servo valve, and the displacement sensor is disposed on the jet nozzle until the deflection angle of the jet nozzle is equal to the theoretical deflection angle.
Preferably, the control method of the vectoring nozzle further comprises:
and step S5, after the airplane enters the maneuvering state, determining whether the over-temperature and over-rotation is achieved based on the temperature sensor and the rotating speed sensor, and if the over-temperature and over-rotation is achieved, exiting the vector state.
A second aspect of the present application provides a control apparatus for a vectoring nozzle, mainly comprising:
the maneuvering state selection module is used for acquiring a maneuvering state selection signal of a user, and the maneuvering state comprises a conventional maneuvering state, a super maneuvering state and a dynamic change-out state;
the maneuvering state entering judging module is used for determining whether the airplane can enter a designated maneuvering state according to the current state of the airplane;
the vector nozzle deflection calculation module is used for determining a theoretical offset angle of the vector nozzle according to a flight attack angle corresponding to a maneuvering state if the aircraft can enter the designated maneuvering state, and otherwise, prompting that the state fails to enter;
and the vector nozzle deflection control module is used for driving the actuating cylinder until the sensor monitors that the position of the vector nozzle is the same as the theoretical position.
Preferably, in the maneuvering state selection module, the maneuvering state selection signal is given by a maneuvering control switch, the maneuvering control switch is arranged on a control console of the cockpit and consists of three buttons, and the airplane corresponds to a conventional maneuvering state, a super maneuvering state and a dynamic changing state of the airplane.
Preferably, the maneuvering state entering determination module includes:
the conventional maneuvering state entering judging unit is used for determining whether the airplane can enter a conventional maneuvering state according to the current state of the airplane, and comprises determining whether the airplane can enable a flight attack angle to intervene for 0-30 degrees according to the current state of the airplane;
the super-maneuver state entering judging unit is used for determining whether the aircraft can enter the super-maneuver state according to the current state of the aircraft, and determining whether the aircraft can enable the flight attack angle to intervene for 30-60 degrees according to the current state of the aircraft;
and the dynamic change-out state entering judging unit is used for determining whether the aircraft can enter the dynamic change-out state according to the current state of the aircraft, and comprises the step of determining whether the aircraft can enable the flight angle of attack to intervene 60-90 degrees according to the current state of the aircraft.
Preferably, the vectoring nozzle deflection control module comprises:
the motor deflection control unit is used for driving the actuating cylinder to deflect the tail spray pipe through the electro-hydraulic servo valve;
and the monitoring unit is used for monitoring the deflection angle based on the displacement sensor arranged on the spray pipe until the deflection angle of the spray pipe is the same as the theoretical deflection angle.
Preferably, the control device of the vectoring nozzle further comprises:
and the vector state exit module is used for determining whether the overtemperature and overturn is reached or not based on the temperature sensor and the rotating speed sensor after the airplane enters the maneuvering state, and exiting the vector state if the overtemperature and overturn is reached.
This application can be effectively to the mobile demand of difference make judgement and response, realizes different thrust vector schemes under the different flight operating modes, realizes vector control and the meticulous cooperation of flight control surface, promotes the response speed of vectoring nozzle, promotes the turn rate of aircraft, accelerates the aircraft nose directional to make the aircraft obtain better mobile performance.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of a method for controlling a vectoring nozzle of the present application.
FIG. 2 is a control diagram for the operation of the jet nozzle of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
In a first aspect, the present application provides a method for controlling a vectoring nozzle, as shown in fig. 1, which mainly includes:
step S1, acquiring a maneuvering state selection signal of a user, wherein the maneuvering state comprises a conventional maneuvering state, a super maneuvering state and a dynamic changing state;
step S2, determining whether the airplane can enter a specified maneuvering state according to the current state of the airplane;
step S3, if the aircraft can enter a designated maneuvering state, determining a theoretical offset angle of the vectoring nozzle according to a flight attack angle corresponding to the maneuvering state, otherwise, prompting that the state fails to enter;
and step S4, driving the actuating cylinder until the position of the vectoring nozzle is the same as the theoretical position as monitored by the sensor.
In some alternative embodiments, determining whether the aircraft can enter the designated maneuver state based on the current state of the aircraft in step S2 includes:
determining whether the airplane can enter a conventional maneuvering state according to the current state of the airplane, wherein the determining whether the airplane can enable a flight attack angle to intervene for 0-30 degrees according to the current state of the airplane is included;
determining whether the aircraft can enter a super-maneuvering state according to the current state of the aircraft, wherein the determining whether the aircraft can enable a flight attack angle to intervene for 30-60 degrees according to the current state of the aircraft is included;
and determining whether the aircraft can enter a dynamic change-out state according to the current state of the aircraft, wherein the step of determining whether the aircraft can enable the flight angle of attack to intervene for 60-90 degrees according to the current state of the aircraft is included.
The application carries out segmentation design to the control of thrust vectoring nozzle to pilot mobility demand of not equidimension, and according to data such as aircraft flight state, engine characteristic and flight parameter record, realize logical judgement and instruct according to corresponding control law that to control annex regulation pressurized strut by digital electronic controller, realize the vector deflection of spray tube, specifically as follows:
the scheme consists of two parts, namely pilot instructions and a sectional control scheme of the vectoring nozzle.
The pilot command consists of a maneuvering control switch, a voice prompt and a signal transmission line. The maneuvering control switch is positioned on a control console of the cockpit, consists of three buttons and corresponds to three maneuvering states of the airplane: maneuver state, super maneuver state, and dynamic change-out state. When the yellow switch is turned on, the airplane is in a maneuvering state; when the green switch is turned on, the airplane is in a super-maneuvering state; when the blue switch is turned on, the aircraft is in a dynamic handoff state. If the dynamic state is quitted, the third switch is closed, and similarly, the super-maneuvering state and the maneuvering state can be quitted in sequence by closing the second switch and the first switch. When the corresponding maneuvering state can not be entered, the control console in the cockpit can prompt the pilot that the entry of a certain state fails to be entered by voice, and the pilot can be noticed.
The sectional control scheme of the vectoring nozzle is composed of three sections, and according to classification, the maneuvering state of the airplane with the flight incidence angle of 0-30 degrees is the maneuvering state of the airplane; the maneuvering state of the airplane with the flight attack angle between 30 and 60 degrees is the super maneuvering state of the airplane; the maneuvering state of the aircraft with the flight incidence angle between 60 degrees and 90 degrees is the dynamic change-out state. When the pilot gives an instruction to enter a certain motor state, the system consists of a flying pipe computer, an atmospheric data processor, a rotating speed sensor, a temperature sensor, a vector thrust controller, an electro-hydraulic servo valve, an actuating cylinder, an operating mechanism and a displacement sensor. When a pilot inputs an instruction to enter a certain maneuvering state, a signal is transmitted to the vector thrust controller of the engine control system, meanwhile, parameters such as the flight altitude, the aircraft Mach number, the flight attack angle, the flight attitude, the flight control surface and the like are transmitted to the vector thrust controller of the engine through the flight tube computer, and the vector thrust controller judges whether the corresponding maneuvering state can be entered or not according to the current aircraft state by combining the parameters of the engine state. If the vehicle can enter the corresponding maneuvering state, the vector thrust controller calculates the theoretical offset angle of the vector nozzle according to the maneuvering state requirement and the current working state of the engine, so that the actuating cylinder is driven until the position of the nozzle detected by the sensor is the same as the theoretical position. If the corresponding maneuver state can not be entered, the pilot is prompted by voice to 'enter failure in a certain state'.
In the embodiment, the vector thrust controller obtains the flight attitude and control surface parameters of the airplane from the flight pipe computer, the atmospheric data processing computer obtains the flight altitude and the Mach number, the rotating speed of the engine is calculated according to the temperature sensor and the rotating speed sensor, the judgment is carried out according to different judgment standards aiming at the maneuvering state requirement, and if the maneuvering state requirement is met, the jet pipe actuating device is driven to deflect at a corresponding angle according to a corresponding control rule.
The operating steps of a design method of a control scheme of a vectoring nozzle are described by taking a super-maneuvering state as an example. The pilot turns on the red thrust vector switch in the cockpit, at this time the vector function of the nozzle is turned on, and the green switch in the maneuvering control switch is turned on. The pilot's demand instruction for exceeding maneuver is transmitted into the vector controller, and is judged according to the flight attitude, control surface parameters, row height Mach number and engine state at the same time, if the demand for entering the exceeding maneuver state is not met, the ' exceeding maneuver state entering failure ' is broadcasted in a cockpit voice, if the exceeding maneuver state can be entered, the theoretical deflection angle of the vector nozzle is calculated according to the control rule of the exceeding maneuver state, as shown in fig. 2, the actuator cylinder is driven by the electro-hydraulic servo valve to deflect the tail nozzle, and the displacement sensor is arranged on the nozzle until the deflection angle of the nozzle is the same as the theoretical deflection angle.
In some alternative embodiments, the vectoring nozzle control method further comprises:
and step S5, after the airplane enters the maneuvering state, determining whether the over-temperature and over-rotation is achieved based on the temperature sensor and the rotating speed sensor, and if the over-temperature and over-rotation is achieved, exiting the vector state.
In a second aspect, the present application provides a control apparatus for a vectoring nozzle corresponding to the above method, which mainly includes:
the maneuvering state selection module is used for acquiring a maneuvering state selection signal of a user, and the maneuvering state comprises a conventional maneuvering state, a super maneuvering state and a dynamic change-out state;
the maneuvering state entering judging module is used for determining whether the airplane can enter a designated maneuvering state according to the current state of the airplane;
the vector nozzle deflection calculation module is used for determining a theoretical offset angle of the vector nozzle according to a flight attack angle corresponding to a maneuvering state if the aircraft can enter the designated maneuvering state, and otherwise, prompting that the state fails to enter;
and the vector nozzle deflection control module is used for driving the actuating cylinder until the sensor monitors that the position of the vector nozzle is the same as the theoretical position.
In some optional embodiments, in the maneuvering state selection module, the maneuvering state selection signal is given by a maneuvering control switch, which is arranged on a control console of the cockpit and consists of three buttons, and the airplane corresponds to a normal maneuvering state, a super maneuvering state and a dynamic transition state of the airplane.
In some optional embodiments, the maneuver state entry determination module includes:
the conventional maneuvering state entering judging unit is used for determining whether the airplane can enter a conventional maneuvering state according to the current state of the airplane, and comprises determining whether the airplane can enable a flight attack angle to intervene for 0-30 degrees according to the current state of the airplane;
the super-maneuver state entering judging unit is used for determining whether the aircraft can enter the super-maneuver state according to the current state of the aircraft, and determining whether the aircraft can enable the flight attack angle to intervene for 30-60 degrees according to the current state of the aircraft;
and the dynamic change-out state entering judging unit is used for determining whether the aircraft can enter the dynamic change-out state according to the current state of the aircraft, and comprises the step of determining whether the aircraft can enable the flight angle of attack to intervene 60-90 degrees according to the current state of the aircraft.
In some alternative embodiments, the vectoring nozzle deflection control module includes:
the motor deflection control unit is used for driving the actuating cylinder to deflect the tail spray pipe through the electro-hydraulic servo valve;
and the monitoring unit is used for monitoring the deflection angle based on the displacement sensor arranged on the spray pipe until the deflection angle of the spray pipe is the same as the theoretical deflection angle.
In some alternative embodiments, the control device of the vectoring nozzle further comprises:
and the vector state exit module is used for determining whether the overtemperature and overturn is reached or not based on the temperature sensor and the rotating speed sensor after the airplane enters the maneuvering state, and exiting the vector state if the overtemperature and overturn is reached.
This application can be effectively to the mobile demand of difference make judgement and response, realizes different thrust vector schemes under the different flight operating modes, realizes vector control and the meticulous cooperation of flight control surface, promotes the response speed of vectoring nozzle, promotes the turn rate of aircraft, accelerates the aircraft nose directional to make the aircraft obtain better mobile performance.
Although the present application has been described in detail with respect to specific embodiments and general description, it will be apparent to those skilled in the art that some modifications or improvements may be made based on the present application. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.
Claims (10)
1. A method of controlling a vectoring nozzle comprising:
step S1, acquiring a maneuvering state selection signal of a user, wherein the maneuvering state comprises a conventional maneuvering state, a super maneuvering state and a dynamic changing state;
step S2, determining whether the airplane can enter a designated maneuvering state according to the current state of the airplane;
step S3, if the aircraft can enter a designated maneuvering state, determining a theoretical offset angle of the vectoring nozzle according to a flight attack angle corresponding to the maneuvering state, otherwise, prompting that the state fails to enter;
and step S4, driving the actuating cylinder until the position of the vectoring nozzle is the same as the theoretical position as monitored by the sensor.
2. The method for controlling a vectoring nozzle as claimed in claim 1, wherein in step S1, said maneuver state selection signal is provided by a maneuver switch, said maneuver switch being provided on a console of a cockpit and consisting of three buttons, the aircraft corresponding to a normal maneuver state, a super maneuver state and a dynamic maneuver state of the aircraft.
3. The method of controlling a vectoring nozzle as claimed in claim 1 wherein the step S2 of determining whether the aircraft can enter the designated maneuver state based on the current aircraft state comprises:
determining whether the airplane can enter a conventional maneuvering state according to the current state of the airplane, wherein the determining whether the airplane can enable a flight attack angle to intervene for 0-30 degrees according to the current state of the airplane is included;
determining whether the aircraft can enter a super-maneuvering state according to the current state of the aircraft, wherein the determining whether the aircraft can enable a flight attack angle to intervene for 30-60 degrees according to the current state of the aircraft is included;
and determining whether the aircraft can enter a dynamic change-out state according to the current state of the aircraft, wherein the step of determining whether the aircraft can enable the flight angle of attack to intervene for 60-90 degrees according to the current state of the aircraft is included.
4. The method of claim 1, wherein step S4 further comprises deflecting the jet nozzle by actuating the actuator cylinder via the electro-hydraulic servo valve, and the displacement sensor is disposed on the nozzle until the nozzle deflection angle is the same as the theoretical deflection angle.
5. The method of controlling a vector nozzle of claim 1, further comprising:
and step S5, after the airplane enters the maneuvering state, determining whether the over-temperature and over-rotation is achieved based on the temperature sensor and the rotating speed sensor, and if the over-temperature and over-rotation is achieved, exiting the vector state.
6. A control apparatus for a vectoring nozzle, comprising:
the maneuvering state selection module is used for acquiring a maneuvering state selection signal of a user, and the maneuvering state comprises a conventional maneuvering state, a super maneuvering state and a dynamic change-out state;
the maneuvering state entering judging module is used for determining whether the airplane can enter a designated maneuvering state according to the current state of the airplane;
the vector nozzle deflection calculation module is used for determining a theoretical offset angle of the vector nozzle according to a flight attack angle corresponding to a maneuvering state if the aircraft can enter the designated maneuvering state, and otherwise, prompting that the state fails to enter;
and the vector nozzle deflection control module is used for driving the actuating cylinder until the sensor monitors that the position of the vector nozzle is the same as the theoretical position.
7. The control device for the thrust vectoring nozzle according to claim 6, wherein in said maneuver state selection module, said maneuver state selection signal is provided by a maneuver control switch, said maneuver control switch is disposed on a console of a cockpit and comprises three buttons, and the aircraft corresponds to a normal maneuver state, a super maneuver state and a dynamic maneuver out state of the aircraft.
8. The control device for a vectoring nozzle as claimed in claim 6 wherein said maneuver state entry determination module comprises:
the conventional maneuvering state entering judging unit is used for determining whether the airplane can enter a conventional maneuvering state according to the current state of the airplane, and comprises determining whether the airplane can enable a flight attack angle to intervene for 0-30 degrees according to the current state of the airplane;
the super-maneuver state entering judging unit is used for determining whether the aircraft can enter the super-maneuver state according to the current state of the aircraft, and determining whether the aircraft can enable the flight attack angle to intervene for 30-60 degrees according to the current state of the aircraft;
and the dynamic change-out state entering judging unit is used for determining whether the aircraft can enter the dynamic change-out state according to the current state of the aircraft, and comprises the step of determining whether the aircraft can enable the flight angle of attack to intervene 60-90 degrees according to the current state of the aircraft.
9. The vector nozzle control apparatus of claim 6, wherein the vector nozzle deflection control module comprises:
the motor deflection control unit is used for driving the actuating cylinder to deflect the tail spray pipe through the electro-hydraulic servo valve;
and the monitoring unit is used for monitoring the deflection angle based on the displacement sensor arranged on the spray pipe until the deflection angle of the spray pipe is the same as the theoretical deflection angle.
10. The control device for a vector nozzle of claim 6, wherein the control device for a vector nozzle further comprises:
and the vector state exit module is used for determining whether the overtemperature and overturn is reached or not based on the temperature sensor and the rotating speed sensor after the airplane enters the maneuvering state, and exiting the vector state if the overtemperature and overturn is reached.
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| CN202111638016.1A CN114542323B (en) | 2021-12-29 | 2021-12-29 | Control method and device for vector spray pipe |
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| CN202111638016.1A CN114542323B (en) | 2021-12-29 | 2021-12-29 | Control method and device for vector spray pipe |
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