CN117002747A - Method and device for monitoring performance test flight of aircraft pollution runway - Google Patents
Method and device for monitoring performance test flight of aircraft pollution runway Download PDFInfo
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- CN117002747A CN117002747A CN202310764246.5A CN202310764246A CN117002747A CN 117002747 A CN117002747 A CN 117002747A CN 202310764246 A CN202310764246 A CN 202310764246A CN 117002747 A CN117002747 A CN 117002747A
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 33
- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000011056 performance test Methods 0.000 title claims abstract description 27
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 11
- 238000007781 pre-processing Methods 0.000 claims description 9
- 230000005484 gravity Effects 0.000 claims description 8
- 239000000446 fuel Substances 0.000 claims description 7
- 238000012545 processing Methods 0.000 claims description 7
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 6
- 239000003381 stabilizer Substances 0.000 claims description 6
- 239000003638 chemical reducing agent Substances 0.000 claims description 5
- 238000012806 monitoring device Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 17
- 230000002159 abnormal effect Effects 0.000 description 3
- 238000005086 pumping Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 208000024891 symptom Diseases 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a method and a device for monitoring performance test flight of an aircraft pollution runway, which can acquire aircraft configuration information parameters, aircraft state information parameters, state information of an engine, landing gear related state information, aircraft control surface state information, aircraft overload change information and position information of the aircraft on the runway. The method can completely cover the monitoring requirement of key parameters of the performance test flight subjects of the polluted runway, display the time history curve of the conventional parameters, accurately and rapidly judge the test process, improve the efficiency of test execution, intensively monitor the key parameters of the performance test flight subjects of the polluted runway, acquire the accurate position information of the aircraft on the runway and the information of the relative positions of the aircraft and a pool, and has high monitoring efficiency.
Description
Technical Field
The invention relates to the technical field of flight tests, in particular to a method and a device for monitoring performance test flight of an aircraft pollution runway.
Background
In recent years, accidents and symptoms of accidents that pollute the runway landing and deviate from the runway are continuously happening at home and abroad. The direct cause of most landing accidents is due to water accumulation, snow water, snow or ice contaminating the runway, and the indirect cause of most landing accidents is due to runway conditions themselves or combined with adverse side wind. So how to ensure the safe operation of the aircraft under the condition of polluting the runway is one of important subjects of aviation field research. In order to acquire performance data under the condition of a polluted runway, a corresponding polluted runway performance flight test is usually required to be developed, how to accurately and rapidly judge the test process is required to be specific to test parameters which are mainly focused aiming at the characteristics of the polluted runway performance test, and special monitoring picture design is performed so as to improve the efficiency of test execution.
Currently, during civil aircraft flight test, a general monitoring picture is usually designed, and a time history curve of conventional parameters is mainly displayed.
However, the parameters of the general monitoring picture can not completely cover the monitoring requirement of key parameters of the performance test flight subjects of the pollution runway; the parameters of the universal monitoring picture are dispersed in a plurality of monitoring pictures, the monitoring pictures are required to be focused during monitoring, the monitoring efficiency is low, and the universal monitoring picture has no accurate position information of the plane on the runway and no distance information from the water pool.
Disclosure of Invention
The invention aims to provide a method and a device for monitoring performance test flight of an aircraft pollution runway, which can accurately and rapidly judge the test process and improve the efficiency of test execution.
According to one object of the invention, the invention provides a method for monitoring the performance test flight of an aircraft pollution runway, which comprises the following steps:
s1, acquiring aircraft configuration information parameters
Acquiring the real-time weight center of gravity of the aircraft, the position of a front slat of the aircraft, landing gear state information and a flight control mode;
s2, acquiring aircraft state information parameters
Acquiring the altitude, speed, pitch angle, attack angle, roll angle, heading angle and sideslip angle of an aircraft;
s3, acquiring state information of the engine
Acquiring parameters of N1 rotating speed, N2 rotating speed, throttle lever angle, exhaust temperature, fuel flow, N1 vibration and N2 vibration;
s4, acquiring landing gear related state information
Acquiring a brake temperature, a tire pressure, a wheel speed, a brake pressure and a wheel load signal;
s5, acquiring the state information of the control surface of the aircraft
Acquiring elevator deflection, aileron deflection, rudder balancing, horizontal stabilizer balancing, rudder deflection and speed reducer handle position parameters;
s6, acquiring overload change information of the airplane
Acquiring normal overload, longitudinal overload and lateral overload parameters;
s7, acquiring the position information of the aircraft on the runway
Accurate position information of the aircraft on the runway and information of the relative positions of the aircraft and the pool are obtained;
s8, data processing
And processing the aircraft configuration information parameters, the aircraft state information parameters, the state information of the engine, the landing gear related state information, the aircraft control surface state information, the aircraft overload change information and the position information of the aircraft on the runway acquired in the S1-S8 to form numerical values, curves and signal lamps for displaying the aircraft parameters.
Further, in S1, according to the weight center of the zero oil of the aircraft, the total weight and the center of gravity of the aircraft are calculated by pumping the bus oil quantity information of the aircraft.
Further, in S1, the position of the wing slat, the landing gear state information and the flight control mode are obtained through drawing the bus parameters of the aircraft, and are displayed in the form of numerical values and signal lamps.
Further, in S2, the altitude, speed, pitch angle, attack angle, roll angle, heading angle and sideslip angle of the aircraft are obtained by drawing the bus parameters of the aircraft, and are displayed in the form of numerical and time history curves.
Further, in S3, parameters of N1 rotation speed, N2 rotation speed, throttle lever angle, exhaust temperature, fuel flow, N1 vibration and N2 vibration are obtained by drawing the bus parameters of the aircraft, and are shown in a numerical value and time history curve.
Further, in S4, the brake temperature, the tire pressure, the wheel speed, the brake pressure and the wheel load signal are obtained through drawing the bus parameters or the additional parameters of the aircraft, and are displayed in a numerical value, a time history curve or a signal lamp.
Further, in S5, the elevator offset, aileron offset, rudder trim, horizontal stabilizer trim, rudder offset, and speed reducer handle position are obtained by extracting aircraft bus parameters, and are represented in a numerical and time history curve.
Further, in S6, the normal overload, the longitudinal overload, and the lateral overload are obtained by extracting the aircraft bus parameters, and are represented by numerical and time history curves.
Further, in S7, accurate position information of the aircraft on the runway and information of relative positions of the aircraft and the pool are obtained by calibrating latitude and longitude information of the pool and latitude information of the runway and combining real-time latitude and longitude information of the aircraft, and are displayed in terms of numerical values and relative position information.
According to another object of the present invention, there is provided an aircraft pollution runway performance test flight monitoring device comprising:
the data acquisition unit is used for acquiring data of aircraft configuration information parameters, aircraft state information parameters, state information of an engine, landing gear related state information, aircraft control surface state information, aircraft overload change information and aircraft runway position information;
the data preprocessing unit is connected with the data acquisition unit and is used for processing the data acquired by the data acquisition unit to form a numerical value, a curve and a signal lamp for displaying aircraft parameters;
and the display unit is connected with the data preprocessing unit and used for displaying parameter values, curves and signal lamps.
The technical scheme of the invention can acquire the aircraft configuration information parameter, the aircraft state information parameter, the state information of the engine, the landing gear related state information, the aircraft control surface state information, the aircraft overload change information and the position information of the aircraft on the runway. The method can completely cover the monitoring requirement of key parameters of the performance test flight subjects of the polluted runway, display the time history curve of the conventional parameters, accurately and rapidly judge the test process, improve the efficiency of test execution, intensively monitor the key parameters of the performance test flight subjects of the polluted runway, acquire the accurate position information of the aircraft on the runway and the distance information from a water pool, and has high monitoring efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of an embodiment of the present invention;
in the figure: 1. a data acquisition unit; 2. a data preprocessing unit; 3. and a display unit.
Detailed Description
The technical solutions of the present invention will be clearly and completely described in connection with the embodiments, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more of the described features. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise. Furthermore, the terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Example 1
A method for monitoring performance test flight of an aircraft pollution runway comprises the following steps:
s1, aircraft configuration information parameters:
1) According to the zero-oil weight center of the aircraft, the total weight and the center of gravity of the aircraft are calculated by extracting the bus oil quantity information of the aircraft, if the aircraft is additionally provided with a center of gravity allocation system, the related parameters of the center of gravity allocation system can be directly extracted and displayed in the form of numerical values and package charts, and the purpose of the method is to monitor and confirm whether the weight center of gravity of the aircraft meets the test requirements;
2) The position of the aircraft wing slat, the state information of the landing gear and the flight control mode are mainly obtained through drawing the bus parameters of the aircraft and are displayed in the forms of numerical values, signal lamps, position information and the like, and the purpose of the method is to monitor and confirm that the states of the wing slat landing gear and the flight control mode of the aircraft meet test requirements.
S2, aircraft state information parameters: the altitude, speed (ground speed, airspeed), pitch angle, attack angle, roll angle, course angle and sideslip angle are mainly obtained through drawing the bus parameters of the aircraft and are displayed in the form of numerical value and time course curve, and the purpose of the method is to monitor and confirm whether the state of the aircraft is normal or not, and to confirm whether the speed of the aircraft entering a pool meets the test requirement or not at the same time, whether yaw exists or not in the process of sliding the aircraft, and the like.
S3, state information of an engine: n1 rotation speed, N2 rotation speed, throttle lever angle, exhaust temperature, fuel flow, N1 vibration and N2 vibration are mainly obtained through drawing aircraft bus parameters and displayed in a numerical value and time history curve, and the purpose of the device is to monitor whether an engine is abnormal after the aircraft enters a pool;
s4, landing gear related state information: the brake temperature, tire pressure, wheel speed, brake pressure and wheel load signals are mainly obtained through pumping aircraft bus parameters or additional parameters and are displayed in a numerical value, time history curve or signal lamp, and the purpose of the brake temperature, tire pressure, wheel speed, brake pressure and wheel load signals is to monitor the working states of the brake and the tires and confirm whether abnormal conditions exist when the brake and the tires pass through a water tank;
s5, aircraft control surface state information: the elevator deflection, aileron deflection, rudder balancing, horizontal stabilizer balancing, rudder deflection and speed reducer handle positions are mainly obtained through drawing aircraft bus parameters and displayed in a numerical value and time history curve, and the purpose of the elevator deflection, aileron deflection, rudder balancing, horizontal stabilizer balancing, rudder deflection and speed reducer handle positions is to monitor the movement condition of aircraft control surfaces and confirm whether abnormal conditions exist when the aircraft control surfaces pass through a water pool;
s6, aircraft overload change information: the normal overload, the longitudinal overload and the lateral overload are mainly obtained through drawing the bus parameters or the additional parameters of the aircraft, are shown by numerical value and time history curves, and aim to monitor the change condition of acceleration of the aircraft when the aircraft passes through a pool;
s7, position information of the aircraft on the runway: accurate position information of the aircraft on the runway and information of the relative positions of the aircraft and the water pool are obtained by calibrating the longitude and latitude information of the water pool and the longitude and latitude information of the runway and combining the real-time longitude and latitude information of the aircraft, and the information is displayed in numerical value and relative position information, so that the position of the aircraft running on the runway is monitored.
As shown in fig. 1, the aircraft pollution runway performance test flight monitoring device comprises a data acquisition unit 1, a data preprocessing unit 2 and a display unit 3, wherein the data acquisition unit 1 is connected with the data preprocessing unit 2, and the data preprocessing unit 2 is connected with the display unit 3.
The data acquisition unit 1 is used for acquiring data of aircraft configuration information parameters, aircraft state information parameters, state information of an engine, landing gear related state information, aircraft control surface state information, aircraft overload change information and position information of an aircraft on a runway, the data preprocessing unit 2 is used for processing the data acquired by the data acquisition unit to form values, curves and signal lamps for displaying the aircraft parameters, and the display unit 3 is used for displaying the parameter values, the curves and the signal lamps.
The invention relates to a method for monitoring performance test flight of an aircraft pollution runway, which is a method for intensively displaying key parameters of the performance test flight subjects of the pollution runway, and can acquire aircraft configuration information parameters, aircraft state information parameters, state information of an engine, landing gear related state information, aircraft control surface state information, aircraft overload change information and position information of the aircraft on the runway. The invention can completely cover the monitoring requirement of key parameters of the performance test flight subjects of the polluted runway, display the time course curve of the conventional parameters, accurately and quickly judge the test process, improve the efficiency of test execution, intensively monitor the key parameters of the performance test flight subjects of the polluted runway, acquire the accurate position information of the plane on the runway and the distance information from a water pool, and has high monitoring efficiency.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (10)
1. The method for monitoring the performance test flight of the aircraft pollution runway is characterized by comprising the following steps of:
s1, acquiring aircraft configuration information parameters
Acquiring the real-time weight center of gravity of the aircraft, the position of a front slat of the aircraft, landing gear state information and a flight control mode;
s2, acquiring aircraft state information parameters
Acquiring the altitude, speed, pitch angle, attack angle, roll angle, heading angle and sideslip angle of an aircraft;
s3, acquiring state information of the engine
Acquiring parameters of N1 rotating speed, N2 rotating speed, throttle lever angle, exhaust temperature, fuel flow, N1 vibration and N2 vibration;
s4, acquiring landing gear related state information
Acquiring a brake temperature, a tire pressure, a wheel speed, a brake pressure and a wheel load signal;
s5, acquiring the state information of the control surface of the aircraft
Acquiring elevator deflection, aileron deflection, rudder balancing, horizontal stabilizer balancing, rudder deflection and speed reducer handle position parameters;
s6, acquiring overload change information of the airplane
Acquiring normal overload, longitudinal overload and lateral overload parameters;
s7, acquiring the position information of the aircraft on the runway
Accurate position information of the aircraft on the runway and information of the relative positions of the aircraft and the pool are obtained;
s8, data processing
And processing the aircraft configuration information parameters, the aircraft state information parameters, the state information of the engine, the landing gear related state information, the aircraft control surface state information, the aircraft overload change information and the position information of the aircraft on the runway acquired in the S1-S8 to form numerical values, curves and signal lamps for displaying the aircraft parameters.
2. The method for monitoring performance test flight of an aircraft pollution runway according to claim 1, wherein in S1, the total weight and the center of gravity of the aircraft are calculated by extracting the information of the total fuel quantity of the aircraft according to the weight center of the zero fuel of the aircraft.
3. The method for monitoring performance test flight of an aircraft pollution runway according to claim 1, wherein in S1, the positions of the front slats of the aircraft, the state information of the landing gear and the flight control mode are obtained by extracting bus parameters of the aircraft and are displayed in the form of numerical values and signal lamps.
4. The method for monitoring performance test flight of an aircraft pollution runway according to claim 1, wherein in S2, the altitude, speed, pitch angle, attack angle, roll angle, heading angle and sideslip angle of the aircraft are obtained by extracting bus parameters of the aircraft and are displayed in the form of numerical and time history curves.
5. The method for monitoring performance test flight of an aircraft pollution runway according to claim 1, wherein in S3, N1 rotation speed, N2 rotation speed, throttle lever angle, exhaust temperature, fuel flow, N1 vibration and N2 vibration parameters are obtained by drawing aircraft bus parameters and are displayed in a numerical and time history curve.
6. The method for monitoring performance test flight of an aircraft pollution runway according to claim 1, wherein in S4, the brake temperature, the tire pressure, the wheel speed, the brake pressure and the wheel load signal are obtained through drawing the bus parameters or the additional parameters of the aircraft and are displayed in a numerical value, a time history curve or a signal lamp.
7. The method for pilot flight monitoring of aircraft pollution runway performance according to claim 1, wherein in S5, elevator deflection, aileron deflection, rudder balancing, horizontal stabilizer balancing, rudder deflection and speed bump handle positions are obtained by extracting aircraft bus parameters and presented in a numerical and time history curve.
8. The method for pilot flight monitoring of aircraft pollution runway performance according to claim 1, wherein in S6, the normal overload, the longitudinal overload and the lateral overload are obtained by extracting aircraft bus parameters and are represented in a numerical and time history curve.
9. The method for monitoring performance test flight of an aircraft pollution runway according to claim 1, wherein in S7, accurate position information of the aircraft on the runway and information of relative positions of the aircraft and the water pool are obtained by calibrating longitude and latitude information of the water pool and longitude and latitude information of the runway and combining real-time longitude and latitude information calculation of the aircraft, and are displayed in numerical values and relative position information.
10. An aircraft pollution runway performance test flight monitoring device, comprising:
the data acquisition unit is used for acquiring data of aircraft configuration information parameters, aircraft state information parameters, state information of an engine, landing gear related state information, aircraft control surface state information, aircraft overload change information and aircraft runway position information;
the data preprocessing unit is connected with the data acquisition unit and is used for processing the data acquired by the data acquisition unit to form a numerical value, a curve and a signal lamp for displaying aircraft parameters;
and the display unit is connected with the data preprocessing unit and used for displaying parameter values, curves and signal lamps.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310764246.5A CN117002747A (en) | 2023-06-26 | 2023-06-26 | Method and device for monitoring performance test flight of aircraft pollution runway |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310764246.5A CN117002747A (en) | 2023-06-26 | 2023-06-26 | Method and device for monitoring performance test flight of aircraft pollution runway |
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| Publication Number | Publication Date |
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| CN117002747A true CN117002747A (en) | 2023-11-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310764246.5A Pending CN117002747A (en) | 2023-06-26 | 2023-06-26 | Method and device for monitoring performance test flight of aircraft pollution runway |
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| Country | Link |
|---|---|
| CN (1) | CN117002747A (en) |
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2023
- 2023-06-26 CN CN202310764246.5A patent/CN117002747A/en active Pending
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