CN112763304A - Fatigue test loading spectrum forming method and device and fatigue performance testing method - Google Patents
Fatigue test loading spectrum forming method and device and fatigue performance testing method Download PDFInfo
- Publication number
- CN112763304A CN112763304A CN202011543471.9A CN202011543471A CN112763304A CN 112763304 A CN112763304 A CN 112763304A CN 202011543471 A CN202011543471 A CN 202011543471A CN 112763304 A CN112763304 A CN 112763304A
- Authority
- CN
- China
- Prior art keywords
- load
- spectrum
- fatigue
- forming
- loading
- 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.)
- Granted
Links
- 238000001228 spectrum Methods 0.000 title claims abstract description 118
- 238000009661 fatigue test Methods 0.000 title claims abstract description 41
- 238000000034 method Methods 0.000 title claims abstract description 37
- 238000012360 testing method Methods 0.000 title claims abstract description 36
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 238000006243 chemical reaction Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000009194 climbing Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000003595 spectral effect Effects 0.000 description 2
- 238000004590 computer program Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/0202—Control of the test
- G01N2203/0208—Specific programs of loading, e.g. incremental loading or pre-loading
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0676—Force, weight, load, energy, speed or acceleration
Landscapes
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to a fatigue test loading spectrum forming method and device and a fatigue performance testing method, belongs to the technical field of aircraft environmental engineering, and solves the problems that an existing load loading control system cannot directly identify a structural fatigue load spectrum and cannot apply loads. A fatigue test loading spectrum forming method comprises the following steps: determining the load direction applied on each loading section of the structural member to be tested and the load value corresponding to the load direction to form a load condition table; generating a plurality of step instructions according to the load condition table and the change time of the load and the load change sequence; and according to the structure of the flight-continuation-flight fatigue load spectrum, forming a load sequence block spectrum corresponding to the load working condition by the multiple step instructions according to different load working conditions. The structure fatigue loading spectrum can be converted into a fatigue test loading spectrum identified by the loading control system, and the test efficiency is improved on the basis of ensuring the test accuracy and effectiveness.
Description
Technical Field
The invention relates to the technical field of aircraft environmental engineering, in particular to a fatigue test loading spectrum forming method and device and a fatigue performance testing method.
Background
The structural fatigue load spectrum is an important condition and basis for the fatigue performance assessment of the structural member. The application of the fatigue load in the structural fatigue performance assessment test is realized through a load loading control system, but the load loading control system cannot directly identify a structural fatigue load spectrum and cannot apply the load. Conversion from a fatigue load spectrum (the fatigue load spectrum is a load or stress with the size and the direction periodically or irregularly changed along with time) to a fatigue test loading spectrum is required to be performed, and the fatigue test loading spectrum which can be identified by a loading control system is converted, so that the fatigue performance assessment of the structural member is successfully completed. A reasonable and efficient load equivalent conversion method is needed, and the test feasibility and the test efficiency are improved. The realization of the fatigue load spectrum is completed by a load loading control system. However, the original fatigue load spectrum cannot be directly realized on a loading control system, appropriate equivalent conversion is required, and the converted spectrum is called a fatigue test loading spectrum.
Disclosure of Invention
In view of the foregoing analysis, embodiments of the present invention provide a method and an apparatus for forming a fatigue test loading spectrum, and a method for testing fatigue performance, so as to solve the problem that the existing load loading control system cannot directly identify a structural fatigue load spectrum and cannot apply a load.
In one aspect, an embodiment of the present invention provides a method for forming a fatigue test loading spectrum, including: determining the load direction applied on each loading section of the structural member to be tested and the load value corresponding to the load direction to form a load condition table; generating a plurality of step instructions according to the load condition table and the change time of the load and the load change sequence; and according to the structure of the flight-continuation-flight fatigue load spectrum and different load working conditions, forming the plurality of step instructions into a load sequence block spectrum corresponding to the load working conditions.
The beneficial effects of the above technical scheme are as follows: the embodiment of the application provides a fatigue test loading spectrum forming method, which is used for converting a structural fatigue loading spectrum into a test loading spectrum identified by a loading control system, and improving the test efficiency on the basis of ensuring the test accuracy and effectiveness.
Based on the further improvement of the method, before the forming of the load situation table, the method further comprises the following steps: analyzing different flight phases of the aircraft to determine a plurality of load working conditions, wherein the structural part to be tested is the aircraft or a part in the aircraft; determining the course load, the lateral load and/or the longitudinal load of each load working condition; and dividing the heading load, the side load and/or the longitudinal load into an X-direction load, a Y-direction load and a Z-direction load respectively to determine a load application direction.
Based on the further improvement of the method, the plurality of load conditions comprise ground sliding, departure maneuver, climbing gust, level flight gust and level flight maneuver.
Based on the further improvement of the method, the X-direction load is an axial load; the Y-direction load is a vertical load; and the Z-direction load is a horizontal load, wherein the Z-direction load is perpendicular to the X-direction load and the Y-direction load.
Based on a further improvement of the above method, forming the load situation table further comprises: dividing the load in the X direction into a load in the + X direction and a load in the-X direction; dividing the load in the Z direction into a load in the + Z direction and a load in the-Z direction; and the Y-direction load is a vertically downward load.
Based on a further development of the above method, the load situation table is formed according to the following principle: firstly, applying a load in the Y direction; and then applying the X-direction load and the Z-direction load, wherein the symmetrical direction load is applied by the following sequence: sequentially applying a load in the direction of + X or a load in the direction of-X, a zero load in the direction of X and a load in the direction of-X or a load in the direction of + X; and sequentially applying a + Z-direction load or a-Z-direction load, a zero load in the Z direction and a-Z-direction load or a + Z-direction load.
In a further development of the above method, the components in the aircraft comprise a tow sub, a tank compartment and a warhead compartment.
In another aspect, an embodiment of the present invention provides a fatigue performance testing method, including: transmitting the load sequence block spectrum described in the above embodiments to a load loading control system; the load loading control system automatically identifies the load sequence block spectrum, then displays a fatigue test loading spectrum graph on a display according to the load sequence block spectrum and applies load to the structural member to be tested so as to determine the fatigue performance of the structural member to be tested.
In another aspect, an embodiment of the present invention provides a fatigue test loading spectrum forming apparatus, including: the load condition table forming module is used for determining the load direction applied to each loading section of the structural member to be tested and the load value corresponding to the load direction to form a load condition table; the step instruction generating module is used for generating a plurality of step instructions according to the load condition table and the change time of the load and the load change sequence; and the load sequence block spectrum generation module is used for forming a load sequence block spectrum corresponding to the load working condition by the plurality of step instructions according to the structure of the flight-continuation-flight fatigue load spectrum and different load working conditions.
Based on the further improvement of the device, the fatigue test loading spectrum forming device further comprises: the load working condition determining module is used for analyzing different flight phases of the aircraft to determine a plurality of load working conditions; and a heading, lateral and longitudinal load determination module for determining a heading load, a lateral load and/or a longitudinal load for each of the plurality of load conditions; and the load application direction determining module is used for dividing the heading load, the lateral load and/or the longitudinal load into an X-direction load, a Y-direction load and a Z-direction load respectively so as to determine the load application direction.
Compared with the prior art, the invention can realize at least one of the following beneficial effects:
1. the structural fatigue load spectrum is converted into the test loading spectrum identified by the loading control system, and the test efficiency is improved on the basis of ensuring the test accuracy and effectiveness.
2. Dividing the load in the X direction into a load in the + X direction and a load in the-X direction; dividing the load in the Z direction into a load in the + Z direction and a load in the-Z direction; and the Y-direction load is a vertically downward load so as to facilitate the load control system to apply the load.
3. The symmetrical directional load is applied by the following sequence: sequentially applying a load in the direction of + X or a load in the direction of-X, a zero load in the direction of X and a load in the direction of-X or a load in the direction of + X; and sequentially applying a load in the + Z direction or the-Z direction, a zero load in the Z direction and a load in the-Z direction or the + Z direction, so as to facilitate the load adjustment of the loading control system.
In the invention, the technical schemes can be combined with each other to realize more preferable combination schemes. Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, wherein like reference numerals are used to designate like parts throughout.
FIG. 1 is a flow chart of a fatigue test loading spectrum forming method according to an embodiment of the invention.
FIG. 2 is a fatigue test loading spectra plot according to an embodiment of the present invention.
Fig. 3 is a block diagram of a fatigue test loading spectrum forming apparatus according to an embodiment of the present invention.
Detailed Description
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate preferred embodiments of the invention and together with the description, serve to explain the principles of the invention and not to limit the scope of the invention.
The invention discloses a method for forming a fatigue test loading spectrum. As shown in fig. 1, the fatigue test loading spectrum forming method includes: step S102, determining the load direction applied on each loading section of the structural member to be tested and the load value corresponding to the load direction to form a load condition table; step S104, generating a plurality of step instructions according to the load condition table and the change time of the load and the load change sequence; and step S106, according to the structure of the flight-continuation-flight fatigue load spectrum and according to different load working conditions, forming a load sequence block spectrum corresponding to the load working conditions by the multiple step instructions.
Compared with the prior art, the fatigue test loading spectrum forming method provided by the embodiment converts the structural fatigue loading spectrum into the test loading spectrum (namely the loading sequence block spectrum) identified by the loading control system, and improves the test efficiency on the basis of ensuring the test accuracy and effectiveness.
Hereinafter, with reference to fig. 1 and 2, step S102, step S104, and step S106 of the fatigue test loading spectrum forming method will be described in detail.
Referring to fig. 1, in step S102, a load direction applied to each loading section of the structural member to be tested and a load value corresponding to the load direction are determined to form a load condition table. In the embodiment, the load direction applied to each loading section of the structural member to be tested and the load value corresponding to the load direction are determined according to the fatigue load spectrum.
Firstly, generating the fatigue load spectrum comprises the following three steps: first, different flight phases of the aircraft are analyzed to determine a plurality of load conditions. In an embodiment, the structure under test is an aircraft or a component in an aircraft, and the component in the aircraft includes a hangar joint, a tank compartment, a warhead compartment, and possibly other aircraft structures. The plurality of load conditions include ground taxiing, departure maneuvers, climb gusts, level flight gusts, and level flight maneuvers. Next, a heading load, a side load, and/or a longitudinal load for each load condition is determined. Finally, the heading load, the side load and/or the longitudinal load are divided into an X-direction load, a Y-direction load and a Z-direction load respectively. The load in the X direction is an axial load; the Y-direction load is a vertical load; the Z-direction load is a horizontal direction load, wherein the Z-direction load is perpendicular to the X-direction load and the Y-direction load.
After generating the fatigue load spectrum, forming a load case table further comprises: firstly, the load direction (X, Y and Z-direction load) applied on each loading section of the structural member to be tested and the load value corresponding to the load direction are determined according to the flying-continuing-flying fatigue load spectrum. Next, dividing the X-direction load into a + X-direction load and a-X-direction load; dividing the load in the Z direction into a load in the + Z direction and a load in the-Z direction; the Y-direction load is divided into vertically downward loads. The load case table is formed according to the following principle: firstly, applying a load in the Y direction; then, an X-direction load and a Z-direction load are applied, wherein the symmetrical-direction load is applied by the following sequence: sequentially applying a load in the direction of + X or a load in the direction of-X, a zero load in the direction of X and a load in the direction of-X or a load in the direction of + X; and sequentially applying a + Z-direction load or a-Z-direction load, a zero load in the Z direction and a-Z-direction load or a + Z-direction load.
After the load condition table is formed, the process proceeds to step S104, and a plurality of step commands are generated in order of load change from the load condition table and the change time of the load. The load control system can apply the load in chronological order based on the step instructions. For example, a plurality of step commands are generated according to the ground taxi heading and the Y-direction load, the X-direction load and the Z-direction load in the load condition table and the change thereof. For example, the following 5 step instructions: the first step of the command is to apply a Y-direction load, the second step of the command is to apply a Y-direction load and a-X-direction load, the third step of the command is to apply a Y-direction load, the fourth step of the command is to apply a Y-direction load and an X-direction load, and the fifth step of the command is to apply a Y-direction load. In addition, a plurality of step commands, for example, 32 step commands, are generated according to the ground sliding heading, the ground sliding longitudinal direction, the ground sliding lateral direction, the departure maneuver longitudinal direction, the climbing gust lateral direction, the flat flying gust longitudinal direction, the flat flying gust lateral direction, the Y-direction load, the X-direction load, the Z-direction load and the change thereof in the load condition table.
And S106, forming a load sequence block spectrum corresponding to the load working condition by the multiple step instructions according to the structure of the flight-continuation-flight fatigue load spectrum and different load working conditions. The step commands generated in step S104 above are combined into a load sequence block spectrum corresponding to the load conditions. The load loading control system can automatically identify the load sequence block spectrum.
The invention further discloses a fatigue performance testing method. The fatigue performance testing method comprises the following steps: the load sequence block spectrum described in the above embodiment is transmitted to the load loading control system, for example, directly transmitted to the load loading control system through an upper computer and the like storing the load sequence block spectrum, without manually inputting the load sequence block spectrum to the load loading control system; and the load loading control system automatically identifies the load sequence block spectrum, then displays a fatigue test loading spectrum graph on the display according to the load sequence block spectrum and applies load to the structural member to be tested so as to determine the fatigue performance of the structural member to be tested.
Compared with the prior art, the fatigue test loading spectrum forming method provided by the embodiment displays the fatigue test loading spectrum diagram on the display according to the load sequence block spectrum, and can check each load loaded in the fatigue test on the display. In addition, the upper computer and the like which store the load sequence block spectrum are directly transmitted to the load loading control system, the load sequence block spectrum does not need to be manually input into the load loading control system, and the preparation time of the fatigue test is greatly shortened.
The invention discloses a fatigue test loading spectrum forming device in another specific embodiment, which comprises: a load condition table forming module 302, configured to determine a load direction applied to each loading section of the structural member to be tested and a load value corresponding to the load direction to form a load condition table; a step instruction generating module 304, configured to generate a plurality of step instructions according to the load condition table and the change time of the load and according to the load change sequence; and a load sequence block spectrum generation module 306, configured to form a load sequence block spectrum corresponding to the load working condition from multiple step instructions according to the structure of the flight-continuation-flight fatigue load spectrum and according to different load working conditions.
The fatigue test loading spectrum forming device also comprises a load working condition determining module which is used for analyzing different flight stages of the aircraft so as to determine a plurality of load working conditions; a heading, lateral and longitudinal load determination module for determining a heading load, a lateral load and/or a longitudinal load for each of a plurality of load conditions; and the load application direction determining module is used for dividing the heading load, the side load and/or the longitudinal load into an X-direction load, a Y-direction load and a Z-direction load respectively to determine the load application direction.
Hereinafter, the fatigue test loading spectrum forming method is described in detail by way of specific examples.
The practice of the invention is illustrated in a typical fatigue loading spectrum for a typical structure.
The typical fatigue load spectrum of a typical structure test piece is generally divided into different task sections (load working conditions), including ground sliding, departure maneuver, climbing gust, level flying maneuver and the like. As shown in table 1. The exemplary structural member may be the entire aircraft or one or more portions of the aircraft structure. Such as a hanging joint, an oil tank cabin, a warhead cabin and the like.
TABLE 1 typical fatigue load spectra
According to the load spectrum in table 1, the load in the X direction is divided into + X direction and-X direction, the load in the Z direction is divided into + Z direction and-Z direction, and the load in the Y direction is vertically downward. The fatigue load spectrum in table 1 was decomposed into 5 load sections and 37 load cases to form a load case table, as shown in table 2, according to the principle of applying the Y-direction load first, then applying the Y-direction load, and then applying the X-direction and Z-direction loads.
And the ground sliding stage comprises a ground sliding course section, a longitudinal section and a lateral section.
TABLE 2 load situation table
And step two, defining step instructions according to the load condition table and the change time of each load condition and the load change sequence.
And step three, forming a load sequence block spectrum by all the step instructions according to different task profiles.
Each task profile is defined as a load sequence block spectrum. The load sequence block spectrum consists of different step instructions. The execution sequence of the step instructions is based on the principle that the load in the Y direction is applied first, and then the load in the X direction and the load in the Z direction are applied. Taking the ground taxi heading profile as an example, a load sequence block spectrum is formed as shown in table 3 below.
TABLE 3 load sequence block spectra (ground taxi course)
| Step order number | Load situation numbering | Step order number | Load situation numbering | |
| 1 | condition_1 | 2 | condition_2 | |
| 3 | condition_3 | 4 | condition_4 | |
| 5 | condition_5 |
And step four, carrying out different cycles on the load sequence block spectrums, and drawing a load loading spectrum graph. The load loading spectral diagram of fig. 1 is a real application example. In practical tests, fatigue loads are applied to the test piece according to the loading spectrum.
Each sequence block spectrum corresponds to a different load profile, each load profile is cycled for a certain number of times, and load loading spectral lines are formed according to the fixed sequence of the load profiles (refer to fig. 2).
The structural fatigue load spectrum can not be directly realized on a loading control system, and the invention provides a reasonable and efficient load equivalent conversion method. According to the spectrum compiling principle of the flight-continuation-flight fatigue load spectrum, the structural fatigue load spectrum is converted into a test loading spectrum which can be used for loading control system identification, and the test feasibility is improved.
Compared with the prior art, the fatigue test loading spectrum forming method provided by the embodiment converts the structural fatigue loading spectrum into the test loading spectrum identified by the loading control system by adopting a reasonable load equivalent conversion method, and improves the test efficiency on the basis of ensuring the test accuracy and effectiveness. The fatigue performance assessment method can be applied to fatigue performance assessment tests of various aircrafts.
Compared with the prior art, the invention can realize at least one of the following beneficial effects:
1. the structural fatigue load spectrum is converted into the test loading spectrum identified by the loading control system, and the test efficiency is improved on the basis of ensuring the test accuracy and effectiveness.
2. Dividing the load in the X direction into a load in the + X direction and a load in the-X direction; dividing the load in the Z direction into a load in the + Z direction and a load in the-Z direction; and the Y-direction load is a vertically downward load so as to facilitate the load control system to apply the load.
3. The symmetrical directional load is applied by the following sequence: sequentially applying a load in the direction of + X or a load in the direction of-X, a zero load in the direction of X and a load in the direction of-X or a load in the direction of + X; and sequentially applying a load in the + Z direction or the-Z direction, a zero load in the Z direction and a load in the-Z direction or the + Z direction, so as to facilitate the load adjustment of the loading control system.
Those skilled in the art will appreciate that all or part of the flow of the method implementing the above embodiments may be implemented by a computer program, which is stored in a computer readable storage medium, to instruct related hardware. The computer readable storage medium is a magnetic disk, an optical disk, a read-only memory or a random access memory.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Claims (10)
1. A fatigue test loading spectrum forming method is characterized by comprising the following steps:
determining the load direction applied on each loading section of the structural member to be tested and the load value corresponding to the load direction to form a load condition table;
generating a plurality of step instructions according to the load condition table and the change time of the load and the load change sequence; and
and according to the structure of the flight-continuation-flight fatigue load spectrum and different load working conditions, forming the plurality of step instructions into a load sequence block spectrum corresponding to the load working conditions.
2. The method of forming a fatigue test loading spectrum according to claim 1, further comprising, before forming the load case table:
analyzing different flight phases of the aircraft to determine a plurality of load working conditions, wherein the structural part to be tested is the aircraft or a part in the aircraft;
determining the course load, the lateral load and/or the longitudinal load of each load working condition; and
and dividing the heading load, the side load and/or the longitudinal load into an X-direction load, a Y-direction load and a Z-direction load respectively to determine a load application direction.
3. The method of forming a fatigue test loading spectrum according to claim 2, wherein the plurality of load conditions include ground taxiing, departure maneuver, climb gusts, level fly gusts, and level fly maneuver.
4. The fatigue test loading spectrum forming method according to claim 2,
the X-direction load is an axial load;
the Y-direction load is a vertical load; and
the Z-direction load is a horizontal load, wherein the Z-direction load is perpendicular to the X-direction load and the Y-direction load.
5. The method of forming a fatigue test loading spectrum according to claim 4, wherein forming a load case table further comprises:
dividing the load in the X direction into a load in the + X direction and a load in the-X direction;
dividing the load in the Z direction into a load in the + Z direction and a load in the-Z direction; and
the Y-direction load is divided into a vertically downward load.
6. The method for forming a fatigue test loading spectrum according to claim 5, wherein the load condition table is formed according to the following principle:
firstly, applying a load in the Y direction; and
then applying the X-direction load and the Z-direction load, wherein the symmetrical direction load is applied by the following sequence:
sequentially applying a load in the direction of + X or a load in the direction of-X, a zero load in the direction of X and a load in the direction of-X or a load in the direction of + X; and
and sequentially applying a + Z direction load or a-Z direction load, a zero load in the Z direction and a-Z direction load or a + Z direction load.
7. The method of forming a fatigue test loading spectrum according to any one of claims 2 to 6, wherein the components in the aircraft include a hangar joint, a tank compartment, and a warhead compartment.
8. A fatigue performance testing method is characterized by comprising the following steps:
transmitting the load sequence block spectrum of any of the above claims 1 to 7 to a load loading control system; and
the load loading control system automatically identifies the load sequence block spectrum, then displays a fatigue test loading spectrum graph on a display according to the load sequence block spectrum and applies load to the structural member to be tested so as to determine the fatigue performance of the structural member to be tested.
9. A fatigue test loading spectrum forming device is characterized by comprising:
the load condition table forming module is used for determining the load direction applied to each loading section of the structural member to be tested and the load value corresponding to the load direction to form a load condition table;
the step instruction generating module is used for generating a plurality of step instructions according to the load condition table and the change time of the load and the load change sequence; and
and the load sequence block spectrum generation module is used for forming a load sequence block spectrum corresponding to the load working condition by the plurality of step instructions according to the structure of the flight-continuation-flight fatigue load spectrum and different load working conditions.
10. The fatigue test loading spectrum forming apparatus according to claim 9, further comprising:
the load working condition determining module is used for analyzing different flight phases of the aircraft to determine a plurality of load working conditions;
a heading, lateral and longitudinal load determination module for determining a heading load, a lateral load and/or a longitudinal load for each of the plurality of load conditions; and
and the load application direction determining module is used for dividing the heading load, the side load and/or the longitudinal load into an X-direction load, a Y-direction load and a Z-direction load respectively so as to determine the load application direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011543471.9A CN112763304B (en) | 2020-12-23 | 2020-12-23 | Fatigue test loading spectrum forming method and device and fatigue performance testing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011543471.9A CN112763304B (en) | 2020-12-23 | 2020-12-23 | Fatigue test loading spectrum forming method and device and fatigue performance testing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112763304A true CN112763304A (en) | 2021-05-07 |
| CN112763304B CN112763304B (en) | 2023-11-07 |
Family
ID=75695397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011543471.9A Active CN112763304B (en) | 2020-12-23 | 2020-12-23 | Fatigue test loading spectrum forming method and device and fatigue performance testing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112763304B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| CN102680221A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test method for full-aircraft main operating system of aircraft |
| CN106557599A (en) * | 2015-09-29 | 2017-04-05 | 中国飞机强度研究所 | A kind of space force system loading spectrum preparation method |
| CN107499534A (en) * | 2017-07-28 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of processing method of aircraft floor lateral load |
| US20200130866A1 (en) * | 2018-10-29 | 2020-04-30 | Honeywell International Inc. | Structural usage monitoring system and method |
-
2020
- 2020-12-23 CN CN202011543471.9A patent/CN112763304B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| CN102680221A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test method for full-aircraft main operating system of aircraft |
| CN106557599A (en) * | 2015-09-29 | 2017-04-05 | 中国飞机强度研究所 | A kind of space force system loading spectrum preparation method |
| CN107499534A (en) * | 2017-07-28 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of processing method of aircraft floor lateral load |
| US20200130866A1 (en) * | 2018-10-29 | 2020-04-30 | Honeywell International Inc. | Structural usage monitoring system and method |
Non-Patent Citations (4)
| Title |
|---|
| 刘克格 等: "飞机起落架载荷谱实测与编制方法", 《航空学报》 * |
| 刘晓明 等: "民机飞行载荷谱编制方法", 《北京航空航天大学学报》 * |
| 朱锦杰: "飞机起落架地面疲劳试验系统设计", 《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》 * |
| 赵朋飞 等: "装备关重件腐蚀-疲劳环境/载荷试验谱编制方法研究", 《装备环境工程》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112763304B (en) | 2023-11-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Haskins et al. | 8.4. 2 error cost escalation through the project life cycle | |
| CN102682173A (en) | Optimization design method based on self-adaptive radial basis function surrogate model for aircraft | |
| Moerland et al. | On the design of a strut-braced wing configuration in a collaborative design environment | |
| CN110795780A (en) | XGboost algorithm-based cable-stayed bridge finite element correction method | |
| CN105912823A (en) | N-2-1 positioning based skin and stringer assembling deviation analyzing method of airplane | |
| CN106017953B (en) | A kind of test method and system for large and complex structure experimental study | |
| CN107748808B (en) | Reliability index distribution optimization method, system and medium based on interval constraint | |
| CN110455477B (en) | Method for acquiring vibration load spectrum of solid rocket cabin section structure | |
| CN112763304B (en) | Fatigue test loading spectrum forming method and device and fatigue performance testing method | |
| Fry | Industrial mathematics | |
| Gupta et al. | Input design for identification of aircraft stability and control derivatives | |
| CN104598745B (en) | A kind of moon ground reenters at a high speed return flight quality appraisal procedure | |
| Piperni et al. | The application of multi-disciplinary optimization technologies to the design of a business jet | |
| Li et al. | Industrial big data visualization: a case study using flight data recordings to discover the factors affecting the airplane fuel efficiency | |
| KR101672763B1 (en) | The method for generating interface of simulation and the realtime simulation apparatus | |
| Wennagel et al. | IDEAS, Integrated Design and Analysis System | |
| Koch et al. | Simulation-based verification for parallelization of model-based applications | |
| Cunningham Jr et al. | A system analysis study comparing reverse engineered combinatorial testing to expert judgment | |
| CN109388855A (en) | Digital aircraft simulation result artificial intelligence compares and the method for inspection | |
| Poncelet et al. | In-orbit vibration testing of spacecraft structures | |
| Berssin | Panel Test for New Developed Airbus A321 ACF Overwing Door and Surrounding Structure | |
| CN115438556B (en) | Method, device and equipment for predicting structural rigidity degradation rate of flexible inflatable aircraft | |
| Ilić | Wind Tunnel Operation and Testing in the Twenty-First Century: The Case of VTI’s Test Facilities | |
| Carrasco et al. | USE OF TAGUCHI DESIGN OF EXPERIMENTS TO DETERMINE ALPLS ASCENT DEL TA-V SENSITIVITIES AND TOTAL MASS SENSITIVITIES TO RELEASE CONDITIONS AND VEHICLE PARAMETERS | |
| Li et al. | The top-level design architecture of iron bird |
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 |