CN116161236A - Method for determining installation position error of aircraft nose airspeed tube - Google Patents
Method for determining installation position error of aircraft nose airspeed tube Download PDFInfo
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- CN116161236A CN116161236A CN202211604537.XA CN202211604537A CN116161236A CN 116161236 A CN116161236 A CN 116161236A CN 202211604537 A CN202211604537 A CN 202211604537A CN 116161236 A CN116161236 A CN 116161236A
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- aircraft nose
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- 238000009434 installation Methods 0.000 title claims abstract description 83
- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000004088 simulation Methods 0.000 claims abstract description 28
- 238000009530 blood pressure measurement Methods 0.000 claims description 9
- 230000003068 static effect Effects 0.000 claims description 8
- 238000005259 measurement Methods 0.000 claims description 6
- 238000010586 diagram Methods 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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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)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The application belongs to the technical field of aircraft nose airspeed tube installation position error determination, and in particular relates to an aircraft nose airspeed tube installation position error determination method, which comprises the following steps: determining the own characteristic installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds by wind tunnel tests; determining the error influence quantity of the turbulent flow installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds by using a simulation test; and superposing the own characteristic installation position error influence quantity and the turbulent installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds to obtain the installation position error of the aircraft nose airspeed tube.
Description
Technical Field
The application belongs to the technical field of aircraft nose airspeed tube installation position error determination, and particularly relates to an aircraft nose airspeed tube installation position error determination method.
Background
Currently, an airspeed head is usually arranged at the aircraft nose to measure and obtain aircraft flight parameters, but the aircraft nose airspeed head is influenced by the characteristics of the aircraft and the turbulence of the aircraft, and obvious installation position errors exist in the aircraft nose airspeed head to measure and obtain the aircraft flight parameters.
At present, the installation position error of the airspeed tube of the aircraft nose is determined by completely relying on a wind tunnel test, and the specific implementation mode of the method is that the airspeed tube is installed on the aircraft nose, the airspeed tube and the aircraft nose are subjected to the wind tunnel test together to determine the installation position error, and the installation position error of the airspeed tube of the aircraft nose is determined by adopting the technical scheme, so that a large amount of manpower and material resources are consumed, the period is long and the efficiency is low.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method of determining an error in the mounting position of a pitot tube of an aircraft nose that overcomes or mitigates at least one of the known technical drawbacks.
The technical scheme of the application is as follows:
an aircraft nose airspeed tube installation position error determination method comprises the following steps:
determining the own characteristic installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds by wind tunnel tests;
determining the error influence quantity of the turbulent flow installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds by using a simulation test;
and superposing the own characteristic installation position error influence quantity and the turbulent installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds to obtain the installation position error of the aircraft nose airspeed tube.
According to at least one embodiment of the present application, in the method for determining an installation position error of an aircraft nose airspeed tube, the determining, by wind tunnel test, an own characteristic installation position error influence of the aircraft nose airspeed tube at different wind speeds specifically includes:
determining the total pressure measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
determining the static pressure measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
determining the incidence angle measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
and determining the side slip angle measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube by wind tunnel tests.
According to at least one embodiment of the present application, in the method for determining an error in an installation position of an aircraft nose airspeed tube, the determining, by a simulation test, an error affecting amount of an aircraft turbulent installation position of the aircraft nose airspeed tube at different wind speeds specifically includes:
determining the error influence quantity of static pressure measurement aircraft turbulent flow installation position of the aircraft nose airspeed tube under different wind speeds by using a simulation test;
determining the error influence quantity of the turbulent flow installation position of the aircraft, which is measured by the attack angle of the aircraft nose airspeed tube at different wind speeds, through a simulation test;
and determining the sideslip angle of the aircraft nose airspeed tube at different wind speeds to measure the error influence quantity of the turbulent installation position of the aircraft by using a simulation test.
According to at least one embodiment of the present application, in the method for determining an error in an installation position of an aircraft nose airspeed tube, the determining an error influence amount of an aircraft turbulent installation position of the aircraft nose airspeed tube under different wind speeds by using a simulation test specifically includes:
and determining the error influence quantity of the turbulent flow installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds by using a CFD simulation test.
The application has at least the following beneficial technical effects:
the aircraft nose airspeed tube installation position error determination method is characterized in that the aircraft nose airspeed tube installation position error is divided into the characteristic installation position error influence quantity and the aircraft turbulence installation position error influence quantity, and the aircraft nose airspeed tube installation position error influence quantity and the aircraft turbulence installation position error influence quantity are respectively determined in a wind tunnel test mode and a simulation test mode under different wind speeds, so that the aircraft nose airspeed tube installation position error determination method has higher efficiency while ensuring accuracy, and can save a large amount of manpower and material resources.
Drawings
FIG. 1 is a schematic illustration of determining aircraft nose airspeed tube mounting position errors based solely on wind tunnel tests;
FIG. 2 is a schematic diagram of a method for determining an error in the mounting position of a pitot tube of an aircraft nose provided in an embodiment of the present application;
FIG. 3 is a schematic diagram of determining the own characteristic installation position error influence quantity of an aircraft nose airspeed tube under different wind speeds by wind tunnel test according to the embodiment of the application;
FIG. 4 is a schematic diagram of determining the error influence of the turbulent installation position of the aircraft nose airspeed tube at different wind speeds through simulation tests provided by the embodiment of the application.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below with reference to fig. 1-4.
An aircraft nose airspeed tube installation position error determination method, as shown in fig. 2, comprises the following steps:
determining the own characteristic installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds by wind tunnel tests;
determining the error influence quantity of the turbulent flow installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds by using a simulation test;
and superposing the own characteristic installation position error influence quantity and the turbulent installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds to obtain the installation position error of the aircraft nose airspeed tube.
In some optional embodiments, in the method for determining an installation position error of an aircraft nose airspeed tube, the determining, by wind tunnel test, an own characteristic installation position error influence amount of the aircraft nose airspeed tube at different wind speeds specifically includes:
determining the total pressure measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
determining the static pressure measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
determining the incidence angle measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
and determining the side slip angle measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube by wind tunnel tests.
In some optional embodiments, in the method for determining an error in mounting position of an aircraft nose airspeed tube, the determining, by a simulation test, an error influencing amount of an aircraft turbulent mounting position of the aircraft nose airspeed tube at different wind speeds specifically includes:
determining the error influence quantity of static pressure measurement aircraft turbulent flow installation position of the aircraft nose airspeed tube under different wind speeds by using a simulation test;
determining the error influence quantity of the turbulent flow installation position of the aircraft, which is measured by the attack angle of the aircraft nose airspeed tube at different wind speeds, through a simulation test;
and determining the sideslip angle of the aircraft nose airspeed tube at different wind speeds to measure the error influence quantity of the turbulent installation position of the aircraft by using a simulation test.
In some optional embodiments, in the method for determining an installation position error of an aircraft nose airspeed tube, the determining, by using a simulation test, an aircraft turbulence installation position error influence amount of the aircraft nose airspeed tube at different wind speeds specifically includes:
and determining the error influence quantity of the turbulent flow installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds by using a CFD simulation test.
For the method for determining the installation position error of the aircraft nose airspeed tube disclosed by the embodiment, those skilled in the art can understand that the installation position error influence quantity of the aircraft nose airspeed tube influenced by the characteristics of the aircraft nose airspeed tube is mainly related to the parameters such as the geometric shape of the total pressure hole, the arrangement position of the static pressure hole, the appearance of the airspeed tube, the windward angle weathervaning position, the sideslip angle weathervaning position, the geometric dimension and the like of the airspeed tube, and is difficult to accurately determine in a simulation mode.
For the method for determining the installation position error of the aircraft nose airspeed tube disclosed by the embodiment, those skilled in the art can also understand that the aircraft nose airspeed tube is positioned at the front end of the aircraft nose, when the aircraft sideslips at a larger attack angle, the airflow separation on the aircraft nose is not large, the disturbance quantity of the space position is less influenced by the viscosity of the disturbance quantity of the wall surface of the aircraft nose, and the influence quantity of the aircraft vortex installation position error of the aircraft nose airspeed tube under different wind speeds can be determined more accurately through simulation tests, which mainly is the influence quantity of different aircraft vortex on the static pressure hole measuring position, the attack angle wind vane measuring position and the sideslip angle wind vane measuring position of the aircraft nose airspeed tube under different wind speeds, as shown in fig. 4, the method has higher efficiency and can save a large quantity of manpower and material resources.
For the method for determining the mounting position error of the aircraft nose airspeed tube disclosed by the embodiment, those skilled in the art can understand that the error of the mounting position error of the aircraft nose airspeed tube is divided into the self-characteristic mounting position error influence quantity and the aircraft turbulence mounting position error influence quantity, and the error is determined in a wind tunnel test mode and a simulation test mode respectively under different wind speeds, so that the accuracy is ensured, the efficiency is higher, and a large amount of manpower and material resources can be saved.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (4)
1. The method for determining the installation position error of the aircraft nose airspeed tube is characterized by comprising the following steps of:
determining the own characteristic installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds by wind tunnel tests;
determining the error influence quantity of the turbulent flow installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds by using a simulation test;
and superposing the own characteristic installation position error influence quantity and the turbulent installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds to obtain the installation position error of the aircraft nose airspeed tube.
2. The method for determining the mounting position error of a pitot tube of an aircraft nose according to claim 1, wherein,
the method for determining the self-characteristic installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds by wind tunnel tests specifically comprises the following steps:
determining the total pressure measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
determining the static pressure measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
determining the incidence angle measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube, by a wind tunnel test;
and determining the side slip angle measurement installation position error influence quantity of the aircraft nose airspeed tube under different wind speeds, which is influenced by the characteristics of the aircraft nose airspeed tube by wind tunnel tests.
3. The method for determining the mounting position error of a pitot tube of an aircraft nose according to claim 1, wherein,
the simulation test is used for determining the error influence quantity of the turbulent installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds, and the simulation test specifically comprises the following steps:
determining the error influence quantity of static pressure measurement aircraft turbulent flow installation position of the aircraft nose airspeed tube under different wind speeds by using a simulation test;
determining the error influence quantity of the turbulent flow installation position of the aircraft, which is measured by the attack angle of the aircraft nose airspeed tube at different wind speeds, through a simulation test;
and determining the sideslip angle of the aircraft nose airspeed tube at different wind speeds to measure the error influence quantity of the turbulent installation position of the aircraft by using a simulation test.
4. The method for determining the mounting position error of a pitot tube of an aircraft nose according to claim 1, wherein,
the simulation test is used for determining the error influence quantity of the turbulent installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds, and the method specifically comprises the following steps:
and determining the error influence quantity of the turbulent flow installation position of the aircraft nose airspeed tube of the aircraft under different wind speeds by using a CFD simulation test.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210426683.1A CN114987789A (en) | 2022-04-21 | 2022-04-21 | Aircraft nose airspeed head for indicating aircraft speed state and position error configuration method thereof |
| CN2022104266831 | 2022-04-21 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116161236A true CN116161236A (en) | 2023-05-26 |
| CN116161236B CN116161236B (en) | 2024-03-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210426683.1A Withdrawn CN114987789A (en) | 2022-04-21 | 2022-04-21 | Aircraft nose airspeed head for indicating aircraft speed state and position error configuration method thereof |
| CN202211604537.XA Active CN116161236B (en) | 2022-04-21 | 2022-12-13 | Method for determining installation position error of aircraft nose airspeed tube |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210426683.1A Withdrawn CN114987789A (en) | 2022-04-21 | 2022-04-21 | Aircraft nose airspeed head for indicating aircraft speed state and position error configuration method thereof |
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| CN (2) | CN114987789A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115042994A (en) * | 2022-05-26 | 2022-09-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for determining mounting position error of aircraft nose airspeed head |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101246078A (en) * | 2008-03-18 | 2008-08-20 | 北京航空航天大学 | Amending method for positional error of total static pressure sensor on low-speed unmanned aerial vehicle |
| EP2799890A1 (en) * | 2013-05-03 | 2014-11-05 | Thales | Method and system for determining the speed of an aircraft relative to the air |
| CN112379115A (en) * | 2020-11-02 | 2021-02-19 | 何海涛 | Airspeed tube structure capable of automatically deicing |
| CN112697380A (en) * | 2020-12-10 | 2021-04-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Standard airspeed tube position error calibration structure |
| CN112881004A (en) * | 2021-01-11 | 2021-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Airspeed tube wind tunnel check test device and check test method |
-
2022
- 2022-04-21 CN CN202210426683.1A patent/CN114987789A/en not_active Withdrawn
- 2022-12-13 CN CN202211604537.XA patent/CN116161236B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101246078A (en) * | 2008-03-18 | 2008-08-20 | 北京航空航天大学 | Amending method for positional error of total static pressure sensor on low-speed unmanned aerial vehicle |
| EP2799890A1 (en) * | 2013-05-03 | 2014-11-05 | Thales | Method and system for determining the speed of an aircraft relative to the air |
| CN112379115A (en) * | 2020-11-02 | 2021-02-19 | 何海涛 | Airspeed tube structure capable of automatically deicing |
| CN112697380A (en) * | 2020-12-10 | 2021-04-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Standard airspeed tube position error calibration structure |
| CN112881004A (en) * | 2021-01-11 | 2021-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Airspeed tube wind tunnel check test device and check test method |
Non-Patent Citations (1)
| Title |
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| 郑刘;陈志敏;: "飞机机头气动补偿空速管的设计", 航空学报, no. 07, pages 1189 - 1194 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114987789A (en) | 2022-09-02 |
| CN116161236B (en) | 2024-03-19 |
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