CN114542323B - Control method and device for vector spray pipe - Google Patents
Control method and device for vector spray pipe Download PDFInfo
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- CN114542323B CN114542323B CN202111638016.1A CN202111638016A CN114542323B CN 114542323 B CN114542323 B CN 114542323B CN 202111638016 A CN202111638016 A CN 202111638016A CN 114542323 B CN114542323 B CN 114542323B
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 239000007921 spray Substances 0.000 title claims abstract description 21
- 238000006073 displacement reaction Methods 0.000 claims description 7
- 230000008859 change Effects 0.000 claims description 6
- 238000012544 monitoring process Methods 0.000 claims description 6
- 238000012545 processing Methods 0.000 claims description 3
- 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
- 230000004044 response Effects 0.000 abstract description 5
- 238000013461 design Methods 0.000 description 4
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- 230000001133 acceleration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
Classifications
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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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- Combustion & Propulsion (AREA)
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Abstract
The application belongs to the field of control of vector spray pipes, and particularly relates to a control method and device of a vector spray pipe. The method comprises the steps of S1, acquiring a maneuvering state selection signal of a user, wherein the maneuvering state comprises a normal maneuvering state, a super maneuvering state and a dynamic change-out state; s2, determining that the aircraft can enter a specified maneuvering state according to the current state of the aircraft; s3, if the aircraft can enter a specified 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 enters failure; and S4, driving the actuator cylinder until the sensor detects that the position of the vectoring nozzle is the same as the theoretical position. The application can effectively judge and respond to different maneuvering demands, realize different thrust vector schemes under different flight conditions, realize fine coordination of vector control and flight control surfaces, improve the response speed of the vector spray pipe and improve the turning rate of the airplane.
Description
Technical Field
The application belongs to the field of control of vector spray pipes, and particularly relates to a control method and device of a vector spray pipe.
Background
The thrust vectoring nozzle of the fighter engine is a key component for realizing thrust vector, and has the main functions of: in the flight process of the fighter, the thrust vector function of the engine is realized through vector deflection, and the yaw or rolling acceleration is generated, so that the running distance of the fighter is shortened, and the maneuvering performance is enhanced. Vector control of the engine is closely related to the flight attitude, control surface and the like of an airplane, and the design of the current domestic tail nozzle vector control scheme adopts integral design: after the pilot gives a thrust vector instruction, the comprehensive controller evaluates whether the vector instruction can be executed or not through parameter collection, and after the condition that the vector thrust state is allowed to enter is determined, the engine control system drives the actuator cylinder to drive the tail nozzle to deflect, so that the vector thrust state is entered.
With the gradual improvement of the maneuverability of the fighter plane, the attack angle range of the plane flight is gradually enlarged, and the demand for the vector thrust is also gradually increased. Because the integral control scheme has weak pertinence to different flight attack angle demands, after the pilot instruction is obtained, unified judgment logic is required to be executed, and the vector method cannot be selected autonomously, so that the response speed of the processes of judging the entering vector state, evaluating the deflection angle and the like is relatively slow, and the requirements of the maneuvering performance of the fighter aircraft may not be met.
Disclosure of Invention
In order to solve the problems, the application provides a control method and a device for a vectoring nozzle, which realize the accurate matching of the thrust vector control of an engine and a flight control surface by adopting a sectional control scheme of the vectoring nozzle, avoid that the same thrust vector control is always adopted in a large flight attack angle range, and ensure that the vectoring method cannot be selected independently, so that the response speed of the vectoring nozzle is reduced.
The first aspect of the present application provides a control method for a vectoring nozzle, 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 change-out state;
s2, determining that the aircraft can enter a specified maneuvering state according to the current state of the aircraft;
s3, if the aircraft can enter a specified 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 enters failure;
and S4, driving the actuator cylinder until the sensor detects that the position of the vectoring nozzle is the same as the theoretical position.
Preferably, in step S1, the maneuvering state selection signal is given by a maneuvering control switch, and the maneuvering control switch is disposed on an operation platform of the cockpit and is composed of three buttons, and the airplane corresponds to a normal maneuvering state, an overtravel state and a dynamic change state of the airplane.
Preferably, in step S2, determining whether the aircraft can enter the specified maneuver state according to the current aircraft state includes:
determining whether the aircraft can enter a conventional maneuvering state according to the current state of the aircraft, including determining whether the aircraft can make a flight attack angle intervening by 0-30 degrees according to the current state of the aircraft;
determining whether the aircraft can enter an overrun state according to the current state of the aircraft, including determining whether the aircraft can make a flight attack angle intervening by 30-60 degrees according to the current state of the aircraft;
determining whether the aircraft can enter a dynamic change-out state according to the current state of the aircraft comprises determining whether the aircraft can make a flight attack angle intervening by 60-90 degrees according to the current state of the aircraft.
Preferably, step S4 further comprises deflecting the nozzle by actuating the actuator cylinder via the electrohydraulic servo valve, the displacement sensor being arranged on the nozzle until the deflection angle of the nozzle is identical to the theoretical deflection angle.
Preferably, the control method of the vectoring nozzle further comprises the following steps:
and S5, after the aircraft enters a maneuvering state, determining whether the overtemperature overturns are achieved based on the temperature sensor and the rotating speed sensor, and if the overtemperature overturns are achieved, exiting the vector state.
The second aspect of the present application provides a control device for a vectoring nozzle, mainly comprising:
the mobile state selection module is used for acquiring mobile state selection signals of a user, wherein the mobile state comprises a conventional mobile state, a super mobile state and a dynamic change-out state;
the maneuvering state entering judging module is used for determining that the aircraft can enter a specified maneuvering state according to the current state of the aircraft;
the vector jet pipe deflection calculation module is used for determining a theoretical deflection angle of the vector jet pipe according to a flight attack angle corresponding to a maneuvering state if the aircraft can enter the designated maneuvering state, otherwise, prompting that the state enters failure;
and the vectoring nozzle deflection control module is used for driving the actuator cylinder until the sensor detects that the position of the vectoring 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 an operation platform of the cockpit, and consists of three buttons, and the airplane corresponds to a normal maneuvering state, an overtravel state and a dynamic change-out state of the airplane.
Preferably, the maneuver state entry determination module includes:
the conventional maneuver state entering judging unit is used for determining whether the aircraft can enter the conventional maneuver state according to the current state of the aircraft, and comprises the steps of determining whether the aircraft can enable the angle of attack of the flight to be inserted by 0-30 degrees according to the current state of the aircraft;
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 comprises the step of determining whether the aircraft can make the flying attack angle intervene by 30-60 degrees according to the current state of the aircraft;
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 angle of attack of the flight to be inserted by 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 nozzle through the electrohydraulic servo valve;
and the monitoring unit is used for monitoring the deflection angle based on a 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 overrun is achieved based on the temperature sensor and the rotating speed sensor after the aircraft enters the maneuvering state, and exiting the vector state if the overtemperature overrun is achieved.
The application can effectively judge and respond to different maneuvering demands, realize different thrust vector schemes under different flight conditions, realize the fine matching of vector control and flight control surfaces, improve the response speed of the vector spray pipe, improve the turning rate of the aircraft and accelerate the heading of the aircraft, thereby enabling the aircraft to obtain better maneuvering performance.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of the control method of the vectoring nozzle of the present application.
FIG. 2 is a diagram of a tail nozzle control according to the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail 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 application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, based on the embodiments of the application, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The first aspect of the present application provides a control method for a vectoring nozzle, as shown in fig. 1, mainly including:
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 change-out state;
s2, determining that the aircraft can enter a specified maneuvering state according to the current state of the aircraft;
s3, if the aircraft can enter a specified 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 enters failure;
and S4, driving the actuator cylinder until the sensor detects that the position of the vectoring nozzle is the same as the theoretical position.
In some alternative embodiments, in step S2, determining whether the aircraft can enter the specified maneuver state based on the current aircraft state includes:
determining whether the aircraft can enter a conventional maneuvering state according to the current state of the aircraft, including determining whether the aircraft can make a flight attack angle intervening by 0-30 degrees according to the current state of the aircraft;
determining whether the aircraft can enter an overrun state according to the current state of the aircraft, including determining whether the aircraft can make a flight attack angle intervening by 30-60 degrees according to the current state of the aircraft;
determining whether the aircraft can enter a dynamic change-out state according to the current state of the aircraft comprises determining whether the aircraft can make a flight attack angle intervening by 60-90 degrees according to the current state of the aircraft.
The application designs the control of the vectoring nozzle in sections according to the pilot mobility demands of different degrees, realizes logic judgment by a digital electronic controller according to the data such as the flight state, the engine characteristic, the flight parameter record and the like of the airplane, and guides the operation of the accessory to adjust the actuator cylinder according to the corresponding control law, thereby realizing the vectoring deflection of the nozzle, and comprises the following specific steps:
the scheme consists of 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 the console of the cockpit and consists of three buttons corresponding to three maneuvering states of the airplane: motorized state, super motorized state, dynamic change out state. When the yellow switch is turned on, the aircraft is in a maneuvering state; when the green switch is turned on, the aircraft is in an over-maneuvering state; when the blue switch is turned on, the aircraft is in a dynamic change-out state. If the dynamic change state is exited, the third switch is closed, and similarly, the second switch and the first switch can be sequentially exited from the super-maneuvering state and the maneuvering state. When the corresponding maneuvering state cannot be entered, a console in the cockpit of the pilot can be used for prompting a certain state to enter failure in a voice mode, so that the pilot is attracted.
The sectional control scheme of the vectoring nozzle consists of three sections, and according to classification, the maneuvering state that the flight attack angle of the airplane is 0-30 degrees is the maneuvering state of the airplane; the maneuvering state of the aircraft with the flight attack angle between 30 and 60 degrees is the super maneuvering state of the aircraft; the maneuvering state of the aircraft with the flight attack angle between 60 degrees and 90 degrees is a dynamic change state. When the pilot gives an instruction for entering a certain maneuvering state, the aircraft is composed of a flight tube computer, an atmosphere data processor, a rotating speed sensor, a temperature sensor, a vector thrust controller, an electrohydraulic servo valve, an actuator cylinder, an operating mechanism and a displacement sensor. When the 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 flight altitude, aircraft Mach number, flight attack angle, flight attitude and flight control surface are transmitted to the vector thrust controller of the engine through the flight tube computer, and the vector thrust controller makes a judgment on whether the corresponding maneuvering state can be entered according to the current aircraft state by combining with the engine state parameters. If the corresponding maneuvering state can be entered, the vector thrust controller calculates a theoretical offset angle of the vector spray pipe according to the maneuvering state requirement and the current working state of the engine, so as to drive the actuator cylinder until the sensor detects that the position of the spray pipe is the same as the theoretical position. If the corresponding maneuver state cannot be entered, the pilot is prompted with a voice of "certain state entered failure".
In the embodiment, the vector thrust controller obtains the flight attitude and control surface parameters of the aircraft from the flight tube computer, the air data processing computer obtains the flight altitude and Mach number, the rotating speed of the engine is calculated according to the temperature sensor and the rotating speed sensor, the motor state requirement is judged according to different judging standards, and if the requirement of entering the motor state is met, the nozzle actuating device is driven to deflect at a corresponding angle according to a corresponding control rule.
The operational steps of a design method for a control scheme for a vectoring nozzle are described by taking a supermaneuver condition as an example. The pilot turns on the red thrust vectoring switch in the cockpit, and at this time, the vectoring function of the nozzle is turned on, and the green switch in the maneuvering control switch is turned on. The pilot's super maneuver requirement instruction is transmitted into the vector controller, and meanwhile, the pilot's super maneuver requirement instruction is judged according to the flight attitude, the control surface parameter, the altitude Mach number and the engine state at the moment, if the requirement of entering the super maneuver state is not met, the pilot's super maneuver state is broadcasted through voice, if the pilot's super maneuver state can be entered, the theoretical deflection angle of the vector spray pipe is calculated according to the control law of the super maneuver state, as shown in fig. 2, the actuator cylinder is driven by the electrohydraulic servo valve to deflect the tail spray pipe, and the displacement sensor is 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 method of the vectoring nozzle further comprises:
and S5, after the aircraft enters a maneuvering state, determining whether the overtemperature overturns are achieved based on the temperature sensor and the rotating speed sensor, and if the overtemperature overturns are achieved, exiting the vector state.
The second aspect of the present application provides a control device for a vectoring nozzle corresponding to the above method, mainly comprising:
the mobile state selection module is used for acquiring mobile state selection signals of a user, wherein the mobile state comprises a conventional mobile state, a super mobile state and a dynamic change-out state;
the maneuvering state entering judging module is used for determining that the aircraft can enter a specified maneuvering state according to the current state of the aircraft;
the vector jet pipe deflection calculation module is used for determining a theoretical deflection angle of the vector jet pipe according to a flight attack angle corresponding to a maneuvering state if the aircraft can enter the designated maneuvering state, otherwise, prompting that the state enters failure;
and the vectoring nozzle deflection control module is used for driving the actuator cylinder until the sensor detects that the position of the vectoring nozzle is the same as the theoretical position.
In some alternative embodiments, the maneuvering state selection module provides the maneuvering state selection signal by a maneuvering control switch, wherein the maneuvering control switch is arranged on an operation platform of the cockpit and consists of three buttons, and the airplane corresponds to a normal maneuvering state, an overtravel state and a dynamic change-out state of the airplane.
In some alternative embodiments, the maneuver state entry determination module includes:
the conventional maneuver state entering judging unit is used for determining whether the aircraft can enter the conventional maneuver state according to the current state of the aircraft, and comprises the steps of determining whether the aircraft can enable the angle of attack of the flight to be inserted by 0-30 degrees according to the current state of the aircraft;
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 comprises the step of determining whether the aircraft can make the flying attack angle intervene by 30-60 degrees according to the current state of the aircraft;
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 angle of attack of the flight to be inserted by 60-90 degrees according to the current state of the aircraft.
In some alternative embodiments, the vectoring nozzle deflection control module comprises:
the motor deflection control unit is used for driving the actuating cylinder to deflect the tail nozzle through the electrohydraulic servo valve;
and the monitoring unit is used for monitoring the deflection angle based on a 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 overrun is achieved based on the temperature sensor and the rotating speed sensor after the aircraft enters the maneuvering state, and exiting the vector state if the overtemperature overrun is achieved.
The application can effectively judge and respond to different maneuvering demands, realize different thrust vector schemes under different flight conditions, realize the fine matching of vector control and flight control surfaces, improve the response speed of the vector spray pipe, improve the turning rate of the aircraft and accelerate the heading of the aircraft, thereby enabling the aircraft to obtain better maneuvering performance.
While the application has been described in detail in the foregoing general description and with reference to specific embodiments thereof, it will be apparent to one skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the application and are intended to be within the scope of the application as claimed.
Claims (8)
1. A method of controlling a vectoring nozzle comprising:
step S1, acquiring a maneuvering state selection signal of a user, wherein the maneuvering states comprise a conventional maneuvering state, an ultra maneuvering state and a dynamic change-out state, and the maneuvering state of the aircraft with the flight attack angle of 0-30 degrees is the conventional maneuvering state of the aircraft; the maneuvering state of the aircraft with the flight attack angle between 30-60 degrees is the super maneuvering state of the aircraft; the maneuvering state of the aircraft with the flight attack angle between 60 degrees and 90 degrees is a dynamic change state;
s2, determining whether the aircraft can enter a specified maneuvering state according to the current state of the aircraft, wherein a maneuvering state selection signal is transmitted to a vector thrust controller of an engine control system, meanwhile, the vector thrust controller obtains the flight attitude and control surface parameters of the aircraft from a flight tube computer, obtains the flight altitude and Mach number from an atmosphere data processing computer, calculates the rotating speed of the engine according to a temperature sensor and a rotating speed sensor, and further judges whether the aircraft can enter the specified maneuvering state;
s3, if the aircraft can enter a specified maneuvering state, determining a theoretical offset angle of the vectoring nozzle according to a flight attack angle corresponding to the specified maneuvering state, otherwise, prompting that the state enters failure;
s4, driving the actuator cylinder until the sensor monitors that the position of the vectoring nozzle is the same as the theoretical position;
in step S2, determining that the aircraft can enter the specified maneuver state based on the current aircraft state includes: determining whether the aircraft can enter a conventional maneuvering state according to the current state of the aircraft, including determining whether the aircraft can make a flight attack angle intervening 0-30 degrees according to the current state of the aircraft; determining whether the aircraft can enter a super-maneuver state according to the current state of the aircraft, including determining whether the aircraft can make a flight attack angle intervening by 30-60 degrees according to the current state of the aircraft; determining whether the aircraft can enter a dynamic change-out state according to the current state of the aircraft comprises determining whether the aircraft can make a flight attack angle intervening 60-90 degrees according to the current state of the aircraft.
2. The control method of the vectoring nozzle according to claim 1, wherein in step S1, the maneuver state selection signal is given by a maneuver control switch arranged on the console of the cockpit, consisting of three buttons, corresponding to the normal maneuver state, the supermaneuver state and the dynamic change-out state of the aircraft, respectively.
3. The method of vectoring nozzle control according to claim 1 wherein step S4 further comprises deflecting the nozzle by actuating the actuator cylinder via an electrohydraulic servo valve, the displacement sensor being arranged on the nozzle until the deflection angle of the nozzle is the same as the theoretical deflection angle.
4. The method for controlling a vectoring nozzle of claim 1, further comprising:
and S5, after the aircraft enters a specified maneuvering state, determining whether the overtemperature overrun is achieved based on the temperature sensor and the rotating speed sensor, and if the overtemperature overrun is achieved, exiting the vector state.
5. A control device for a vectoring nozzle, comprising:
the system comprises a maneuvering state selection module, a control module and a control module, wherein the maneuvering state selection module is used for acquiring maneuvering state selection signals of a user, and the maneuvering states comprise a conventional maneuvering state, an overrun maneuvering state and a dynamic change-out state, wherein the maneuvering state of the aircraft with the flight attack angle of 0-30 degrees is the conventional maneuvering state of the aircraft; the maneuvering state of the aircraft with the flight attack angle between 30-60 degrees is the super maneuvering state of the aircraft; the maneuvering state of the aircraft with the flight attack angle between 60 degrees and 90 degrees is a dynamic change state;
the system comprises a maneuvering state entering judging module, a speed sensor and a speed sensor, wherein the maneuvering state entering judging module is used for determining that the aircraft can enter a specified maneuvering state according to the current state of the aircraft, a maneuvering state selecting signal is transmitted to a vector thrust controller of an engine control system, meanwhile, the vector thrust controller obtains the flight attitude and control surface parameters of the aircraft from a flight tube computer, obtains the flight altitude and Mach number from an atmosphere data processing computer, calculates the rotating speed of the engine according to the temperature sensor and the rotating speed sensor, and further judges whether the aircraft can enter the specified maneuvering state;
the vector jet pipe deflection calculation module is used for determining a theoretical deflection angle of the vector jet pipe according to a flight attack angle corresponding to a designated maneuvering state if the aircraft can enter the designated maneuvering state, otherwise, prompting that the state enters failure;
the vectoring nozzle deflection control module is used for driving the actuator cylinder until the sensor monitors that the position of the vectoring nozzle is the same as the theoretical position;
wherein the maneuver state entry determination module comprises:
the conventional maneuver state entering judging unit is used for determining whether the aircraft can enter the conventional maneuver state according to the current state of the aircraft, and comprises the steps of determining whether the aircraft can enable the flight attack angle to be inserted by 0-30 degrees according to the current state of the aircraft;
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 make the flying attack angle intervene by 30-60 degrees according to the current state of the aircraft;
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 flying attack angle to be inserted by 60-90 degrees according to the current state of the aircraft.
6. The control device of the vectoring nozzle of claim 5, wherein in the manoeuvring state selection module the manoeuvring state selection signal is given by a manoeuvring control switch arranged on the cockpit console, consisting of three buttons, corresponding to the normal manoeuvring state, the overmanoeuvring state and the dynamic change-out state of the aircraft respectively.
7. The vectoring nozzle control apparatus of claim 5, wherein the vectoring nozzle deflection control module comprises:
the motor deflection control unit is used for driving the actuating cylinder to deflect the tail nozzle through the electrohydraulic servo valve;
and the monitoring unit is used for monitoring the deflection angle based on a displacement sensor arranged on the spray pipe until the deflection angle of the spray pipe is the same as the theoretical deflection angle.
8. The vectoring nozzle control apparatus of claim 5, wherein the vectoring nozzle control apparatus further comprises:
and the vector state exit module is used for determining whether the overtemperature overrun is achieved based on the temperature sensor and the rotating speed sensor after the aircraft enters the appointed maneuvering state, and exiting the vector state if the overtemperature overrun is achieved.
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