CN111079296B - Aircraft component and aircraft flight load assessment method - Google Patents
Aircraft component and aircraft flight load assessment method Download PDFInfo
- Publication number
- CN111079296B CN111079296B CN201911327126.9A CN201911327126A CN111079296B CN 111079296 B CN111079296 B CN 111079296B CN 201911327126 A CN201911327126 A CN 201911327126A CN 111079296 B CN111079296 B CN 111079296B
- Authority
- CN
- China
- Prior art keywords
- aircraft
- flight
- aircraft component
- loading
- component
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Abstract
The application belongs to the technical field of aircraft flight load assessment, and particularly relates to an aircraft component flight load assessment method, which comprises the following steps: determining the loading rule of the aircraft component; picking flight parameters of the aircraft under typical flight conditions; extracting extracted flight parameters at a first preset time interval, and extracting flight parameters extracted at overload moment and typical parameter peak-to-valley moment; performing multidimensional interpolation on the extracted flight parameters to obtain available flight parameters; based on the loading rule of the aircraft component and the available flight parameters, obtaining the loading condition of the aircraft component changing along with time; extracting the loading condition of the aircraft component at a second preset time interval, and extracting the loading condition of the aircraft component at the moment of loading peak and valley values of the aircraft component; the aircraft component flight load is evaluated based on the extracted aircraft component loading conditions. Furthermore, it relates to an aircraft flight load assessment method based on the above aircraft component flight load assessment method.
Description
Technical Field
The application belongs to the technical field of aircraft flight load assessment, and particularly relates to an aircraft component and an aircraft flight load assessment method.
Background
The specific condition of the flight load of the aircraft is known, and the performance of the aircraft can be effectively mastered, so that the aircraft can be better controlled.
At present, the aircraft flight load is estimated mostly by modeling and calculating methods, the efficiency is low, the accuracy and the relevance of the result are difficult to ensure, and related professionals are required to carry out the method.
The present application has been made in view of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide an aircraft component and a method of aircraft flight load assessment that overcomes or alleviates at least one of the disadvantages of the prior art.
The technical scheme of the application is as follows:
one aspect provides a method of aircraft component flight load assessment, comprising:
determining the loading rule of the aircraft component;
picking flight parameters of the aircraft under typical flight conditions;
extracting extracted flight parameters at a first preset time interval, and extracting flight parameters extracted at overload moment and typical parameter peak-to-valley moment;
performing multidimensional interpolation on the extracted flight parameters to obtain available flight parameters;
based on the loading rule of the aircraft component and the available flight parameters, obtaining the loading condition of the aircraft component changing along with time;
extracting the loading condition of the aircraft component at a second preset time interval, and extracting the loading condition of the aircraft component at the moment of loading peak and valley values of the aircraft component;
the aircraft component flight load is evaluated based on the extracted aircraft component loading conditions.
According to at least one embodiment of the application, the law of loading of the aircraft component comprises the law of variation of the loading of the aircraft component with weight, center of gravity, altitude, speed, overload, pitch angle speed, roll angle speed, tail wing yaw angle, aileron, rudder yaw angle under different flight conditions.
In accordance with at least one embodiment of the present application, typical flight conditions of an aircraft include aircraft takeoff, climb, training/fight, return.
According to at least one embodiment of the application, the first predetermined time interval is 0.2s-0.5s.
According to at least one embodiment of the application, the second predetermined time interval is shown as 1s.
Another aspect provides a method of aircraft flight load assessment, comprising:
evaluating a plurality of aircraft component flight loads by any of the aircraft component flight load evaluation methods described above;
and evaluating the flight load of the aircraft based on the evaluation result of the flight load of each aircraft component.
According to at least one embodiment of the application, the plurality of aircraft components includes at least a tail wing.
In accordance with at least one embodiment of the present application, when the aircraft component is a tail wing, the exemplary parameter peaks and valleys in the aircraft component flight load assessment method include tail wing deflection angle peaks and valleys.
Drawings
Fig. 1 is a flowchart of a method for aircraft component flight load assessment provided by an embodiment of the present application.
Detailed Description
The application is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the application and not limiting of the application. It should be further noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
It should be noted that, in the description of the present application, terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like indicate directions or positional relationships based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the apparatus or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; 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 application can be understood by those skilled in the art according to the specific circumstances.
The application is described in further detail below with reference to fig. 1.
One aspect provides a method of aircraft component flight load assessment, comprising:
the loading rule of the aircraft component is determined, and the loading rule can be obtained by calculating the load of mass working conditions under the allowable flight condition;
picking flight parameters under the typical flight condition of the aircraft, namely picking the flight parameters under the typical flight condition in the flight parameter record of one flight mission of the aircraft, namely removing the flight parameters under the atypical flight condition, wherein the atypical condition generally mainly comprises the conditions of ground preparation, take-off running, landing running and the like of the aircraft;
extracting extracted flight parameters at first preset time intervals, namely extracting one flight parameter from the extracted flight parameters at first preset time intervals, and extracting the flight parameters extracted at overload moment and typical parameter peak-valley moment, namely retaining the flight parameters extracted at the overload moment and the typical parameter peak-valley moment, so that the extracted flight parameters comprise main characteristic changes;
performing multidimensional interpolation on the extracted flight parameters to obtain available flight parameters;
based on the loading rule of the aircraft component and the available flight parameters, obtaining the loading condition of the aircraft component changing along with time;
extracting the loading situation of the aircraft component at second preset time intervals, namely extracting one loading situation of the aircraft component every second preset time in the loading situation of the aircraft component, and extracting the loading situation of the aircraft component at the moment of loading peak value and valley value of the aircraft component, namely retaining the loading situation of the aircraft component at the moment of loading peak value and valley value of the aircraft component;
the aircraft component flight load is evaluated based on the extracted aircraft component loading conditions.
For the aircraft component flight load assessment method disclosed in the above embodiment, it can be understood by those skilled in the art that the method can be performed in an external field, has low requirements on related professions, has high efficiency, and can ensure the validity of the result.
In some alternative embodiments, the loading law of the aircraft component includes the law of variation of the loading of the aircraft component with weight, center of gravity, altitude, speed, overload, pitch angle speed, roll angle speed, tail deflection angle, aileron, rudder deflection angle under different flight conditions.
In some alternative embodiments, typical flight conditions of an aircraft include aircraft takeoff, climb, training/fight, return.
In some alternative embodiments, the first predetermined time interval is 0.2s-0.5s.
In some alternative embodiments, the second predetermined time interval is shown as 1s.
Another aspect provides a method of aircraft flight load assessment, comprising:
evaluating a plurality of aircraft component flight loads by any of the aircraft component flight load evaluation methods described above;
and evaluating the overall change condition of the flight load of the aircraft based on the evaluation result of the flight load of each aircraft component.
For the aircraft flight load evaluation method disclosed in the above embodiment, it can be understood by those skilled in the art that the aircraft flight load evaluation method is implemented based on the above aircraft component flight load evaluation method, and based on the evaluation of the above aircraft component flight load evaluation method to obtain a plurality of aircraft component flight load results, the aircraft flight load is evaluated, so that the evaluation result of the aircraft flight load can be obtained.
In some alternative embodiments, the plurality of aircraft components includes at least a tail wing.
In some alternative embodiments, where the aircraft component is a tail wing, the peak-to-valley values of typical parameters in the aircraft component flight load assessment method include a tail wing deflection angle peak-to-valley value.
Thus far, the technical solution of the present application has been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of protection of the present application is not limited to these specific embodiments. Equivalent modifications and substitutions for related technical features may be made by those skilled in the art without departing from the principles of the present application, and such modifications and substitutions will fall within the scope of the present application.
Claims (7)
1. A method of aircraft component flight load assessment comprising:
determining the loading rule of the aircraft component;
picking flight parameters of the aircraft under typical flight conditions;
extracting extracted flight parameters at a first preset time interval, and extracting flight parameters extracted at overload moment and typical parameter peak-to-valley moment;
performing multidimensional interpolation on the extracted flight parameters to obtain available flight parameters;
based on the loading rule of the aircraft component and the available flight parameters, obtaining the loading condition of the aircraft component changing along with time;
extracting the loading condition of the aircraft component at a second preset time interval, and extracting the loading condition of the aircraft component at the moment of loading peak and valley values of the aircraft component;
estimating the flight load of the aircraft component based on the extracted loading condition of the aircraft component;
the loading rules of the aircraft components comprise the change rules of the loading of the aircraft components along with weight, gravity center, altitude, speed, overload, pitch angle speed, roll angle speed, tail wing deflection angle, aileron and rudder deflection angle under different flight conditions.
2. The aircraft component flying load assessment method according to claim 1,
typical flight conditions for such aircraft include aircraft take-off, climb, training/fight, return.
3. The aircraft component flying load assessment method according to claim 1,
the first predetermined time interval is 0.2s-0.5s.
4. The aircraft component flying load assessment method according to claim 1,
the second predetermined time interval is shown as 1s.
5. A method of aircraft flight load assessment comprising:
evaluating a plurality of aircraft component flying loads with the aircraft component flying load evaluation method of any one of claims 1-4;
and evaluating the flight load of the aircraft based on the evaluation result of the flight load of each aircraft component.
6. The method of aircraft flight load assessment according to claim 5,
the plurality of aircraft components includes at least a tail wing.
7. The method of aircraft flight load assessment according to claim 5,
when the aircraft component is a tail wing, the peak-valley value of typical parameters in the aircraft component flight load evaluation method is a peak-valley value comprising the deflection angle of the tail wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911327126.9A CN111079296B (en) | 2019-12-20 | 2019-12-20 | Aircraft component and aircraft flight load assessment method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911327126.9A CN111079296B (en) | 2019-12-20 | 2019-12-20 | Aircraft component and aircraft flight load assessment method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111079296A CN111079296A (en) | 2020-04-28 |
| CN111079296B true CN111079296B (en) | 2023-09-08 |
Family
ID=70316282
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911327126.9A Active CN111079296B (en) | 2019-12-20 | 2019-12-20 | Aircraft component and aircraft flight load assessment method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111079296B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113704874B (en) * | 2021-08-03 | 2024-02-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for analyzing structural design load of complex loaded air inlet channel |
| CN114136416B (en) * | 2021-11-30 | 2022-08-23 | 中国商用飞机有限责任公司 | Flight weight monitoring method and system for aircraft, storage medium and electronic equipment |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2109063A2 (en) * | 1999-10-29 | 2009-10-14 | Safegate International AB | Aircraft identification and docking guidance systems |
| CN103984848A (en) * | 2014-04-17 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for modifying load characteristic curve of aircraft arrestment device |
| CN104331605A (en) * | 2014-10-15 | 2015-02-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Configuration method for man-machine interactive airplane mission payload |
| CN105335579A (en) * | 2015-11-25 | 2016-02-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Flight load design method for aircraft with high aspect ratio |
| CN109323841A (en) * | 2018-11-23 | 2019-02-12 | 中国航空工业集团公司沈阳飞机设计研究所 | The coordination approach of wing load and distributed load based on grid |
| CN109460596A (en) * | 2018-10-29 | 2019-03-12 | 成都飞机工业（集团）有限责任公司 | A kind of all-wing aircraft unmanned plane non-linear load calculation method |
| CN109583044A (en) * | 2018-11-09 | 2019-04-05 | 中国直升机设计研究所 | Lifting airscrew flight load prediction technique based on RBF neural |
| CN109979037A (en) * | 2019-03-19 | 2019-07-05 | 四川函钛科技有限公司 | QAR parametric synthesis visual analysis method and system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8849603B2 (en) * | 2008-11-21 | 2014-09-30 | The Boeing Company | Systems and methods for control system verification and health assessment |
-
2019
- 2019-12-20 CN CN201911327126.9A patent/CN111079296B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2109063A2 (en) * | 1999-10-29 | 2009-10-14 | Safegate International AB | Aircraft identification and docking guidance systems |
| CN103984848A (en) * | 2014-04-17 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for modifying load characteristic curve of aircraft arrestment device |
| CN104331605A (en) * | 2014-10-15 | 2015-02-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Configuration method for man-machine interactive airplane mission payload |
| CN105335579A (en) * | 2015-11-25 | 2016-02-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Flight load design method for aircraft with high aspect ratio |
| CN109460596A (en) * | 2018-10-29 | 2019-03-12 | 成都飞机工业（集团）有限责任公司 | A kind of all-wing aircraft unmanned plane non-linear load calculation method |
| CN109583044A (en) * | 2018-11-09 | 2019-04-05 | 中国直升机设计研究所 | Lifting airscrew flight load prediction technique based on RBF neural |
| CN109323841A (en) * | 2018-11-23 | 2019-02-12 | 中国航空工业集团公司沈阳飞机设计研究所 | The coordination approach of wing load and distributed load based on grid |
| CN109979037A (en) * | 2019-03-19 | 2019-07-05 | 四川函钛科技有限公司 | QAR parametric synthesis visual analysis method and system |
Non-Patent Citations (1)
| Title |
|---|
| 侯乔乔 等.基于应变测量的飞行载荷测试方法研究.《2013年中国航空学会结构强度专业学术交流会论文集》.2013,48-52. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111079296A (en) | 2020-04-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111079296B (en) | Aircraft component and aircraft flight load assessment method | |
| CN109282786B (en) | Height measuring method and device for fixed-wing unmanned aerial vehicle | |
| EP3043332A1 (en) | Aircraft flight information generation device, aircraft flight information generation method, and aircraft flight information generation program | |
| CN107861522A (en) | Unmanned target drone control system | |
| CN109240327A (en) | A kind of fixed wing aircraft mission phase recognition methods | |
| CN101853531A (en) | Helicopter flight state identification method based on presort technology and RBF (Radial Basis Function) neural network | |
| CN109785462A (en) | Aircraft oil consumption computing system | |
| CN108609202A (en) | Flight is jolted prediction model method for building up, prediction technique and system | |
| CN114065399A (en) | Unmanned aerial vehicle flight performance calculation method considering complex meteorological conditions | |
| RU2011148891A (en) | METHOD AND SYSTEM OF CALCULATION OF TAKEOFF WEIGHT OF AIRCRAFT | |
| CN114936426A (en) | Method for calculating structural life of fighter | |
| CN106934225A (en) | A kind of electric inspection process multi-rotor unmanned aerial vehicle system efficiency evaluation method | |
| CN111062092B (en) | Helicopter flight spectrum compiling method and device | |
| CN113468828A (en) | Method for calculating aerial flight bump intensity index of airplane | |
| Yang et al. | Design of a gust-attenuation controller for landing operations of unmanned autonomous helicopters | |
| CN112099520A (en) | Unmanned aerial vehicle landing control method and device, unmanned aerial vehicle and storage medium | |
| CN107065912A (en) | The method and device of sense aircraft landing | |
| CN114118802A (en) | Helicopter flight risk assessment method based on analytic hierarchy process | |
| CN110930639A (en) | Airborne wind shear alarm system and method for helicopter | |
| CN106372307B (en) | Civil aircraft airflow angle estimation method based on pneumatic model | |
| CN106920041A (en) | A kind of overhead transmission line fixed-wing UAS selection method | |
| Zheng et al. | Risk prediction method of aircraft hard landing based on flight data | |
| Fuller et al. | Evolution and future development of airplane gust loads design requirements | |
| CN114048552B (en) | Rotor wing surface large water drop mass flow calculation method considering secondary impact and terminal | |
| Weishaeupl et al. | Experimental evaluation of the drag curves of small fixed wing UAVs |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |