CN113998095A - Control method of trainer trailing edge flap control system - Google Patents
Control method of trainer trailing edge flap control system Download PDFInfo
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- CN113998095A CN113998095A CN202111318390.3A CN202111318390A CN113998095A CN 113998095 A CN113998095 A CN 113998095A CN 202111318390 A CN202111318390 A CN 202111318390A CN 113998095 A CN113998095 A CN 113998095A
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- 230000008569 process Effects 0.000 claims abstract description 4
- 230000006872 improvement Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 231100000136 action limit Toxicity 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
- B64C13/22—Initiating means actuated automatically, e.g. responsive to gust detectors readily revertible to personal control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/042—Initiating means actuated personally operated by hand
- B64C13/0425—Initiating means actuated personally operated by hand for actuating trailing or leading edge flaps, air brakes or spoilers
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Abstract
The invention provides a control method of a trainer trailing edge flap control system, which comprises a manual control mode and an automatic control mode, wherein the control method comprises the following steps: after starting up, judging that the flap control system enters a manual control mode or an automatic control mode based on the position of a cockpit flap control knob; when the flap control system enters a manual control mode or an automatic control mode, a flap control command corresponding to a retraction state, a take-off state or a landing state of a flap is generated; during the flight process, the cockpit flap control knob is adjusted to a second setting position from a first setting position, or is adjusted to the first setting position from the second setting position, and the manual control mode and the automatic control mode of the flap control system are switched. According to the trailing edge flap control system, the automatic control mode is added on the basis of the manual control mode, and the manual control mode and the automatic control mode are flexibly switched, so that the operation load of a pilot can be reduced, and potential safety hazards caused by manual operation can be reduced.
Description
Technical Field
The invention belongs to the field of avionics, relates to an automatic control technology, and particularly relates to a control method of a trainer trailing edge flap control system.
Background
At present, the control of the wing surface of the trailing edge flap of a trainer usually adopts an open-loop control mode, and a pilot needs to operate a cockpit flap control knob switch according to the current state of the airplane and the requirement of a flight subject so as to generate a flap control command to control the switching of three states (namely a stowing state, a take-off state and a landing state) of the trailing edge flap.
Although the wing surface control of the flap of the trainer can be realized in a manual mode, a pilot needs to pay attention to the current airplane state all the time, and needs to remember relevant control conditions of different states of the flap (such as three states corresponding to the angle position of a rocker arm of a rotary actuator, the over-travel angle value of the rocker arm angle and the like), so that the pilot is greatly expended, and the flight safety hazard caused by manual operation errors is also caused.
Disclosure of Invention
The invention provides a control method of a trainer trailing edge flap control system in order to reduce the operation load of a pilot and avoid the hidden danger of flight caused by human factors.
The technical scheme for realizing the purpose of the invention is as follows: a control method of a flap control system of a training plane trailing edge comprises a manual control mode and an automatic control mode, the manual control mode and the automatic control mode are flexibly switched to generate a flap control instruction during flight, and a flap is controlled to be retracted, take-off and land, and the control method comprises the following steps:
s1, after starting up, judging whether the flap control system enters a manual control mode or an automatic control mode based on the position of a cockpit flap control knob; the control knob of the cockpit flap is positioned at a first set position when the flap control system is in a manual control mode, and the control knob of the cockpit flap is positioned at a second set position when the flap control system is in an automatic control mode;
s2, when the flap control system enters a manual control mode or an automatic control mode, generating a flap control command corresponding to the retraction state, the takeoff state or the landing state of the flap;
s3, in the flight process, the switching between the manual control mode and the automatic control mode of the flap control system comprises the following steps:
s31, changing the adjusting cabin flap control knob from a first setting position to a second setting position, and switching the trailing edge flap control system from a manual control mode to an automatic control mode;
and S32, the adjusting cabin flap control knob is changed from the second setting position to the first setting position, and the trailing edge flap control system is switched from an automatic control mode to a manual control mode.
According to the control method of the trainer trailing edge flap control system, the automatic control mode is added on the basis of the manual control mode, and the manual control mode and the automatic control mode are flexibly switched, so that the operation load of a pilot can be reduced, the potential safety hazard caused by manual operation can be reduced, and the potential safety hazard caused by only adopting one operation mode can be avoided.
Further, the cabin flap control knob comprises a front cabin control knob and a rear cabin control knob, and the front cabin control knob is provided with a front cabin automatic state, a front cabin retracting state, a front cabin takeoff state and a front cabin landing state; the rear cabin control knob is provided with a rear cabin front cabin effective state, a rear cabin retracting state, a rear cabin takeoff state and a rear cabin landing state;
when the front cabin control knob is in a front cabin automatic state and the rear cabin control knob is in a rear cabin front cabin effective state, the cabin flap control knob is located at a second set position; when the front cabin control knob and the rear cabin control knob are in other states, the cockpit flap control knob is located at the first set position.
Further, when the flap control system is in the manual control mode:
the flap control system generates a flap control instruction based on the position of the front cabin control knob in the first set position and the state position of the rear cabin control knob; the flap control instruction outputs a control signal after being operated by a control algorithm, and the flap control system controls the flap to carry out retraction, take-off or landing operation according to the control signal.
Further, when the flap control system is in the automatic control mode:
the flap control system judges whether the automatic control mode is effective or not through a back flap instruction interpretation method based on the indicated airspeed, the undercarriage state parameter, the engine state parameter and the hydraulic system state parameter, and generates a flap control instruction if the automatic control mode is effective;
the flap control instruction outputs a control signal after being operated by a control algorithm, and the flap control system controls the flap to carry out retraction, take-off or landing operation according to the control signal.
Specifically, the method for determining whether the automatic control mode is valid includes:
based on the engine state parameter and the hydraulic system state parameter, if the rotating speed of the high-pressure rotor of the engine is greater than 65% or the working state of the engine is normal and the pressure of the hydraulic system is low, the automatic control mode is judged to be valid, otherwise, the automatic control mode is judged to be invalid.
Further, in step S1, before determining that the flap control system enters the manual control mode or the automatic control mode, the over-travel state needs to be determined:
if the overtravel signal is invalid, judging and entering a manual control mode or an automatic control mode of the flap control system;
if the overtravel signal is effective, a wing surface overrun signal is output to the flap control system, and the flap control system outputs a warning signal.
Compared with the prior art, the invention has the beneficial effects that:
according to the control method of the trainer trailing edge flap control system, the automatic control mode is added on the basis of the manual control mode, and the manual control mode and the automatic control mode are flexibly switched, so that the operation load of a pilot can be reduced, the potential safety hazard caused by manual operation can be reduced, and the potential safety hazard caused by only adopting one operation mode can be avoided.
2. Because there are front deck control knob and rear deck control knob in the passenger cabin flap control knob, and have 4 states respectively on front deck control knob and the rear deck control knob, both combine a total 16 kinds of forms, through the front deck automatic status with the rear deck of rear deck control knob the front deck valid state combination formation second settlement position, set up as first settlement position in other 15. During flight operation, if an automatic control mode is adopted, only one operation is needed; the manual control mode is the same as the existing knob operation method, so that the switching operation between the automatic control mode and the manual control mode is greatly simplified, and the problem of misoperation can be avoided.
3. According to the invention, when the flap control system enters the automatic control mode, the automatic control mode is judged to be effective firstly, and the flap control system can enter the automatic control mode only when the automatic control mode is effective, and the flap control system interprets the indicated airspeed, the landing gear state parameter, the engine state parameter and the hydraulic system state parameter to form a flap control instruction, so that the flight safety can be further ensured.
Drawings
In order to more clearly illustrate the technical solution of the embodiment of the present invention, the drawings used in the description of the embodiment will be briefly introduced below. It should be apparent that the drawings in the following description are only for illustrating the embodiments of the present invention or technical solutions in the prior art more clearly, and that other drawings can be obtained by those skilled in the art without any inventive work.
FIG. 1 is a block diagram of a trailing edge flap control system of a trainer in an embodiment;
FIG. 2 is a flowchart of a control method of a trailing edge flap control system of a trainer in an embodiment;
the device comprises an electromechanical management computer 1, a rear flap flow combination valve 2, a rotary actuator 3, a trailing edge flap wing surface actuator 4, a left rocker arm angle sensor 5, a right rocker arm angle sensor 5, a cabin flap control knob 6 and an overtravel switch 7.
Detailed Description
The invention will be further described with reference to specific embodiments, and the advantages and features of the invention will become apparent as the description proceeds. These examples are illustrative only and do not limit the scope of the present invention in any way. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention, and that such changes and modifications may be made without departing from the spirit and scope of the invention.
In the description of the present embodiments, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
In this embodiment, as shown in fig. 1, the trainer trailing edge flap control system includes an electromechanical management computer 1, a trailing edge flow combination valve 2, a rotary actuator 3, a trailing edge flap airfoil actuator 4, a left rocker arm angle sensor 5, a right rocker arm angle sensor 5, and a cockpit flap control knob 6, where the electromechanical management computer 1 is used as a core of the whole trailing edge flap control system, and by acquiring a front/rear cockpit knob signal, an over-travel switch signal, and a left/right rocker arm angle signal, and processing the acquired signals, and outputting a control signal after operation to drive the trailing edge flow combination valve 2, the pressure of a trailing edge flap pipeline is changed, so as to realize the switching of three states of retracting, taking-off, and landing of the trailing edge flap airfoil.
The electromechanical management computer 1 is used for collecting and processing input signals of analog quantity and discrete quantity, selecting corresponding control parameters according to a set control state, and outputting corresponding control signals to drive the rear flap flow combination valve 2 after operation. The rear flap flow combination valve 2 is used for adjusting the opening of an electro-hydraulic valve and changing the hydraulic pressure of the current rear flap pipeline, so that the rotary actuator 3 is driven to act. The rotary actuator 3 is connected with the trailing edge flap surface actuator 4, so as to drive the trailing edge flap surface actuator 4 to act. The trailing edge flap surface actuator 4 directly drives the trailing edge flap surface to act, so that the state switching of the trailing edge flap surface is realized.
The cabin flap control knob 6 is used as a switch on one hand, and on the other hand, through the change of different state positions of a front cabin control knob and a rear cabin control knob of the cabin flap control knob, the cabin flap control knob 6 comprises a front cabin control knob and a rear cabin control knob, and the front cabin control knob is provided with a front cabin automatic state, a front cabin retracting state, a front cabin takeoff state and a front cabin landing state; the rear cabin control knob is provided with a rear cabin front cabin effective state, a rear cabin retracting state, a rear cabin takeoff state and a rear cabin landing state; the front cabin control knob and the rear cabin control knob of the cabin flap control knob 6 are adjusted to be in different state positions, so that the flap control system can enter an automatic control mode or a manual control mode, when the manual control mode is entered, corresponding trailing edge flap control instructions (including flap retraction instructions, flap takeoff instructions and flap landing instructions) are generated through the improvement of the state positions of the front cabin control knob and the rear cabin control knob, and the retraction, takeoff and landing are switched.
According to the trailing edge flap control system of the specific embodiment, the automatic control mode is added on the basis of the manual control mode, and the manual control mode and the automatic control mode are flexibly switched, so that the operation load of a pilot can be reduced, the potential safety hazard caused by manual operation can be reduced, and meanwhile, the potential safety hazard caused by only adopting one operation mode can be avoided.
The trainer trailing edge flap control system is also provided with an overtravel switch 7, the overtravel switch 7 is used for preventing the trailing edge flap surface actuator 4 from exceeding the action limit and damaging the mechanical structure of the trailing edge flap system, and the overtravel switch 7 generates an overtravel signal and inputs the overtravel signal into the electromechanical management computer 1 for judgment.
The specific embodiment designs a control method of a trainer trailing edge flap control system, as shown in fig. 2, the flap control system comprises a manual control mode and an automatic control mode, the manual control mode and the automatic control mode are flexibly switched to generate a flap control instruction during flight, and the flap is controlled to be retracted, take-off and landing.
Specifically, the control method comprises the following steps:
s1, after starting up, judging whether the flap control system enters a manual control mode or an automatic control mode based on the position of a cockpit flap control knob;
the control knob of the cockpit flap is positioned at a first set position when the flap control system is in a manual control mode, and the control knob of the cockpit flap is positioned at a second set position when the flap control system is in an automatic control mode;
specifically, 16 combinations can be formed by adjusting the states of a front cabin control knob and a rear cabin control knob, wherein when the front cabin control knob is in a front cabin automatic state and the rear cabin control knob is in a rear cabin front cabin effective state, a cabin flap control knob is in a second set position, and at the moment, a flap control system enters an automatic control mode; when the front cabin control knob and the rear cabin control knob are located in other states and combined, the cockpit flap control knob is located at a first set position, the flap control system is still in a manual control mode, and the control flap is retracted, takes off and lands through the pilot operating the front cabin control knob and the rear cabin control knob.
And S2, when the flap control system enters the manual control mode or the automatic control mode, generating a flap control command corresponding to the retraction state, the take-off state or the landing state of the flap.
When the flap control system is in a manual control mode, the flap control system generates a flap control command based on the position of a front cabin control knob and the state position of a rear cabin control knob in a first set position; the flap control instruction outputs a control signal after being operated by a control algorithm, and the flap control system controls the flap to carry out retraction, take-off or landing operation according to the control signal. Specifically, a pilot adjusts the position of a front cabin control knob and the state position of a rear cabin control knob, the electromechanical management computer 1 generates a flap control instruction according to the state of the knobs, the flap control instruction is calculated by a set control algorithm and then outputs a control signal, and switching of a trailing edge flap surface retracting state, a take-off state and a landing state is achieved.
Wherein, when the flap control system is in an automatic control mode (namely, a pilot adjusts the front cabin control knob to a front cabin automatic state, and adjusts the rear cabin control knob to a rear cabin front cabin effective state): the flap control system judges whether the automatic control mode is effective or not through a back flap instruction interpretation method based on the indicated airspeed, the undercarriage state parameter, the engine state parameter and the hydraulic system state parameter, and generates a flap control instruction if the automatic control mode is effective; the flap control instruction outputs a control signal after being operated by a control algorithm, and the flap control system controls the flap to carry out retraction, take-off or landing operation according to the control signal. For example: if the airplane state is in the ground state and the indicated airspeed is less than 120Km/h, the flap takeoff control instruction is effective; if the airplane state is in the air state and the undercarriage is in the retraction state, the flap retraction control instruction is effective; if the aircraft is in an air state, the indicated airspeed is within the range of (380, 450) Km/h, and the average value of the left/right rocker arm angles is greater than 46 degrees, the flap takeoff control instruction is effective; if the aircraft is in an air state and the indicated airspeed is not less than 450Km/h, the flap retraction control instruction is effective; and if the aircraft is in an air state, the landing gear frame is not in a retracted state after the landing gear is in the retracted state, the indicated airspeed is not more than 350Km/h, and the state lasts for 3s, the flap landing control command is effective.
S3, in the flight process, the switching between the manual control mode and the automatic control mode of the flap control system comprises the following steps:
s31, changing the adjusting cabin flap control knob from a first setting position to a second setting position, and switching the trailing edge flap control system from a manual control mode to an automatic control mode;
when the flap control system enters the automatic control mode from the manual control mode, the electromechanical management computer 1 firstly sets the flap control instruction at the previous moment to be invalid, and then forms a new flap control instruction according to the instruction interpretation method of the automatic control mode.
Meanwhile, when the trailing edge flap control system enters the automatic control mode, whether the automatic control mode is effective or not needs to be judged firstly, and the judgment method comprises the following steps: based on the engine state parameter and the hydraulic system state parameter, if the rotating speed of the high-pressure rotor of the engine is greater than 65% or the working state of the engine is normal and the pressure of the hydraulic system is low, the automatic control mode is judged to be valid, otherwise, the automatic control mode is judged to be invalid.
S32, the adjusting cockpit flap control knob is changed from the second setting position to the first setting position, the trailing edge flap control system is switched from the automatic control mode to the manual control mode, and the manual control mode forms a flap control command which is the same as that in the step S2, and the details are not repeated again.
According to the control method of the trainer trailing edge flap control system, the automatic control mode is added on the basis of the manual control mode, and the manual control mode and the automatic control mode are flexibly switched, so that the operation load of a pilot can be reduced, the potential safety hazard caused by manual operation can be reduced, and the potential safety hazard caused by only adopting one operation mode can be avoided.
Since the trailing edge flap actuator 4 may have an overrun problem, on the basis of the above control method, as shown in fig. 2, before the flap control system is determined to enter the manual control mode or the automatic control mode in step S1, the overstroke state needs to be determined:
if the overtravel signal is invalid, judging and entering a manual control mode or an automatic control mode of the flap control system; if the overtravel signal is effective, the over-limit accident of the trailing edge flap actuator 4 is indicated, a flap surface over-limit signal is output to the flap control system, and a warning signal is output by the flap control system.
The control method of the trainer trailing edge flap control system in the embodiment adopts a closed-loop control mode, enters a manual control mode or an automatic control mode through the judgment conditions set in the electromechanical management computer 1, and then generates a corresponding flap control instruction, so that the state switching of the flap surface is realized, the operation load of a pilot is reduced, and the reliability of the trailing edge flap system is improved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (6)
1. A control method of a flap control system at the trailing edge of a trainer is characterized in that the flap control system comprises a manual control mode and an automatic control mode, the manual control mode and the automatic control mode are flexibly switched to generate a flap control instruction during flight, and the flap is controlled to be retracted, take-off and land, and the control method comprises the following steps:
s1, after starting up, judging whether the flap control system enters a manual control mode or an automatic control mode based on the position of a cockpit flap control knob; the control knob of the cockpit flap is positioned at a first set position when the flap control system is in a manual control mode, and the control knob of the cockpit flap is positioned at a second set position when the flap control system is in an automatic control mode;
s2, when the flap control system enters a manual control mode or an automatic control mode, generating a flap control command corresponding to the retraction state, the takeoff state or the landing state of the flap;
s3, in the flight process, the switching between the manual control mode and the automatic control mode of the flap control system comprises the following steps:
s31, changing the adjusting cabin flap control knob from a first setting position to a second setting position, and switching the trailing edge flap control system from a manual control mode to an automatic control mode;
and S32, the adjusting cabin flap control knob is changed from the second setting position to the first setting position, and the trailing edge flap control system is switched from an automatic control mode to a manual control mode.
2. The control method according to claim 1, characterized in that: the cabin flap control knob comprises a front cabin control knob and a rear cabin control knob, and the front cabin control knob is provided with a front cabin automatic state, a front cabin retracting state, a front cabin takeoff state and a front cabin landing state; the rear cabin control knob is provided with a rear cabin front cabin effective state, a rear cabin retracting state, a rear cabin takeoff state and a rear cabin landing state;
when the front cabin control knob is in a front cabin automatic state and the rear cabin control knob is in a rear cabin front cabin effective state, the cabin flap control knob is located at a second set position; when the front cabin control knob and the rear cabin control knob are in other states, the cockpit flap control knob is located at the first set position.
3. The control method according to claim 2, characterized in that: when the flap control system is in a manual control mode:
the flap control system generates a flap control instruction based on the position of the front cabin control knob in the first set position and the state position of the rear cabin control knob; the flap control instruction outputs a control signal after being operated by a control algorithm, and the flap control system controls the flap to carry out retraction, take-off or landing operation according to the control signal.
4. The control method according to claim 2, characterized in that: when the flap control system is in an automatic control mode:
the flap control system judges whether the automatic control mode is effective or not through a back flap instruction interpretation method based on the indicated airspeed, the undercarriage state parameter, the engine state parameter and the hydraulic system state parameter, and generates a flap control instruction if the automatic control mode is effective;
the flap control instruction outputs a control signal after being operated by a control algorithm, and the flap control system controls the flap to carry out retraction, take-off or landing operation according to the control signal.
5. The control method according to claim 4, characterized in that: the method for judging whether the automatic control mode is effective is as follows: based on the engine state parameter and the hydraulic system state parameter, if the rotating speed of the high-pressure rotor of the engine is greater than 65% or the working state of the engine is normal and the pressure of the hydraulic system is low, the automatic control mode is judged to be valid, otherwise, the automatic control mode is judged to be invalid.
6. The control method according to claim 1, characterized in that: in step S1, before determining that the flap control system enters the manual control mode or the automatic control mode, the overstroke state needs to be determined:
if the overtravel signal is invalid, the flap control system enters a manual control mode or an automatic control mode to control the flap to retract, take off or land;
if the overtravel signal is effective, a wing surface overrun signal is output to the flap control system, and the flap control system outputs a warning signal.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111318390.3A CN113998095B (en) | 2021-11-08 | 2021-11-08 | Control method of trailing edge flap control system of trainer |
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| CN202111318390.3A CN113998095B (en) | 2021-11-08 | 2021-11-08 | Control method of trailing edge flap control system of trainer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115783247A (en) * | 2022-11-11 | 2023-03-14 | 中国航空工业集团公司西安飞行自动控制研究所 | Active control method for improving longitudinal riding quality |
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| CN110949659A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Trailing edge flap control method |
| CN111071432A (en) * | 2019-12-06 | 2020-04-28 | 江西洪都航空工业集团有限责任公司 | Flap retraction control circuit for flight training plane |
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2021
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| CN115783247A (en) * | 2022-11-11 | 2023-03-14 | 中国航空工业集团公司西安飞行自动控制研究所 | Active control method for improving longitudinal riding quality |
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| CN113998095B (en) | 2024-07-02 |
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