CN113919056B - Aircraft and system weight characteristic determination method thereof - Google Patents
Aircraft and system weight characteristic determination method thereof Download PDFInfo
- Publication number
- CN113919056B CN113919056B CN202111070911.8A CN202111070911A CN113919056B CN 113919056 B CN113919056 B CN 113919056B CN 202111070911 A CN202111070911 A CN 202111070911A CN 113919056 B CN113919056 B CN 113919056B
- Authority
- CN
- China
- Prior art keywords
- airplane
- coordinate system
- aircraft
- under
- body coordinate
- 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
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/02—Reliability analysis or reliability optimisation; Failure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Testing Of Balance (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The application belongs to the technical field of determining weight characteristics of airplanes and systems thereof, and particularly relates to an airplane and a method for determining weight characteristics of systems thereof, which comprises the following steps: constructing an airplane plane layout coordinate system; the gravity center coordinates of the airplane components are determined under the plane layout coordinates of the airplane; constructing an aircraft body coordinate system; converting the barycentric coordinates of the aircraft components calibrated under the plane layout coordinate system of the aircraft into the aircraft body coordinate system; and calculating the weight characteristics of the airplane and the system thereof under the airplane body coordinate system.
Description
Technical Field
The application belongs to the technical field of determining weight characteristics of airplanes and systems thereof, and particularly relates to an airplane and a method for determining the weight characteristics of the systems thereof.
Background
The weight characteristic refers to the characteristics of the single object or the complex system in terms of weight, gravity center, moment of inertia and the like, and is an inherent attribute of the single object or the complex system.
Currently, in the process of developing the airplane, the calculation and analysis of the weight characteristic of the airplane are mostly carried out after the airplane design is finished, and the use requirement of the weight characteristic data of the airplane lags behind, so that the development period of the airplane is too long.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft and a system weight characteristic determination method thereof that overcomes or mitigates at least one aspect of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
an aircraft and a system weight characteristic determination method thereof comprise the following steps:
constructing an airplane plane layout coordinate system;
the gravity center coordinates of the airplane components are determined under the plane layout coordinates of the airplane;
constructing an aircraft body coordinate system;
converting the barycentric coordinates of the aircraft components calibrated under the plane layout coordinate system of the aircraft into the aircraft body coordinate system;
and calculating the weight characteristics of the airplane and the system thereof under the airplane body coordinate system.
According to at least one embodiment of the present application, in the method for determining the weight characteristic of the aircraft and the system thereof, the transforming the barycentric coordinate calibrated by the aircraft component under the aircraft plane layout coordinate to the aircraft body coordinate system specifically includes:
wherein the content of the first and second substances,
x, Y, Z is the barycentric coordinate of the airplane component transformed to the airplane body coordinate;
P x 、P x 、P z the gravity center coordinates are calibrated for the aircraft components under an aircraft plane layout coordinate system;
X min 、X max 、Z min 、Z max reference points of front, back, left and right coordinates of the airplane in an airplane body coordinate system;
P xmin 、P xmax 、P zmin 、P zmax the coordinate points of the front, the back, the left and the right boundaries of the plane in the plane layout coordinate system of the plane are shown.
According to at least one embodiment of the present application, in the method for determining the weight characteristics of an aircraft and its system, the calculating the weight characteristics of the aircraft and its system in the aircraft body coordinate system specifically includes:
the airplane and the system thereof are decomposed into a tree-shaped product structure, and the weight characteristic of the airplane is calculated under an airplane body coordinate system.
According to at least one embodiment of the present application, in the method for determining the weight characteristic of the aircraft and the system thereof, the aircraft and the system thereof are decomposed into a tree-shaped product structure, and the weight characteristic of the aircraft is calculated in an aircraft body coordinate system, specifically:
W＝∑W i ；
I xy ＝∑I xyi +∑{W i ×[ΔX i ×ΔY i ]}；
wherein the content of the first and second substances,
w is the weight of the aircraft and its system nodes;
W i the weight of the airplane and the system child node i thereof;
x, Y, Z is the barycentric coordinate of the plane and its system nodes in the plane body coordinate system;
X i 、Y i 、Z i the gravity center coordinates of the airplane and the system sub-node i thereof under the airplane body coordinate system are obtained;
I x 、I y 、I z the moment of inertia around the x, y and z axes of the airplane and the system nodes thereof under the airplane body coordinate system;
I xy the method comprises the following steps of (1) taking an inertia product of an airplane and system nodes thereof on an xy plane under an airplane body coordinate system;
I xi 、I yi 、I zi the method comprises the following steps of (1) obtaining the inertia moment of an airplane and a system sub-node i thereof around x, y and z axes under an airplane body coordinate system; i is xyi The method comprises the following steps of (1) taking an inertia product of an airplane and a system sub-node i thereof on an xy plane under an airplane body coordinate system;
ΔX i 、ΔY i 、ΔZ i the distances of the gravity centers of the airplane and the system nodes and the child nodes i thereof in the directions of x, y and z under the airplane body coordinate system are shown.
Drawings
FIG. 1 is a flow chart of an aircraft and a method for determining a system weight characteristic thereof according to an embodiment of the present application;
fig. 2 is a schematic diagram of an aircraft and its systems broken down into a tree-like product structure.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
An aircraft and a system weight characteristic determination method thereof comprise the following steps:
constructing an airplane plane layout coordinate system;
the gravity center coordinates of the airplane components are determined under the plane layout coordinates of the airplane;
constructing an aircraft body coordinate system;
transforming the barycentric coordinates calibrated by the aircraft components under the plane layout coordinate system of the aircraft into an aircraft body coordinate system;
and calculating the weight characteristics of the airplane and the system thereof under the airplane body coordinate system.
With respect to the aircraft and the method for determining the system weight characteristic thereof disclosed in the above embodiments, it can be understood by those skilled in the art that the aircraft plane layout coordinate system refers to a coordinate system used for defining an aircraft plane layout chart when a scale of the aircraft plane layout chart is not considered; the aircraft body coordinate system is a space rectangular coordinate system for calculating the gravity center of the aircraft, usually the reverse course of an X axis is positive, a Y axis is vertical to a horizontal reference surface and upwards, and a Z axis accords with a right-hand rule.
For the aircraft and the method for determining the weight characteristic of the system thereof disclosed in the above embodiments, those skilled in the art can understand that the barycentric coordinates of the aircraft components are specified under the plane layout coordinates of the aircraft, that is, the barycentric coordinates of the aircraft components are specified in the plane layout diagram, and specifically, relevant technicians can determine the barycentric coordinates in the plane layout diagram in a mouse click manner in real time according to the aircraft design experience and the adjustment of the overall arrangement scheme of the aircraft, and convert the barycentric coordinates to the plane body coordinate system through coordinate transformation, so that the weight characteristics of the aircraft and the system thereof can be calculated under the plane body coordinate system.
In some optional embodiments, in the method for determining the weight characteristic of the aircraft and the system thereof, the barycentric coordinates of the aircraft component calibrated in the aircraft plane layout coordinates are transformed into the aircraft body coordinate system, specifically:
wherein, the first and the second end of the pipe are connected with each other,
x, Y, Z is the barycentric coordinate of the airplane component transformed to the airplane body coordinate;
P x 、P x 、P z the gravity center coordinates are calibrated for the airplane components under an airplane plane layout coordinate system;
X min 、X max 、Z min 、Z max the reference points of the front, back, left and right coordinates of the airplane in the airplane body coordinate system correspond to the minimum value and the maximum value of the coordinates of the airplane in the direction X, Z;
P xmin 、P xmax 、P zmin 、P zmax the coordinate points of the front, the back, the left and the right boundaries of the plane in the plane layout coordinate system of the plane are shown.
In some optional embodiments, in the method for determining the weight characteristic of the aircraft and the system thereof, the calculating the weight characteristic of the aircraft and the system thereof in the aircraft body coordinate system specifically includes:
the airplane and the system thereof are decomposed into a tree-shaped product structure, and the weight characteristic of the airplane is calculated under an airplane body coordinate system.
As for the method for determining the weight characteristics of the aircraft and the system thereof disclosed in the above embodiments, those skilled in the art can understand that the aircraft and the system thereof are composed of a plurality of subsystems and components thereof, and can be decomposed into a tree-like product structure, and the aircraft and the system thereof can be decomposed into a tree-like product structure, so that the components of the aircraft with different maturity and data sources thereof (including weight characteristic basic metadata, a weight characteristic statistical formula, and weight characteristic combination calculation) can be unified under the tree-like data structure framework to calculate the weight characteristics of the aircraft and the system thereof, as shown in fig. 2.
In some optional embodiments, in the method for determining the weight characteristic of the aircraft and the system thereof, the aircraft and the system thereof are decomposed into a tree-shaped product structure, and the weight characteristic of the aircraft is calculated in an aircraft body coordinate system, specifically:
W＝∑W i ；
I xy ＝∑I xyi +∑{W i ×[ΔX i ×ΔY i ]}；
wherein the content of the first and second substances,
w is the weight of the aircraft and its system nodes;
W i the weight of the airplane and the system sub-node i thereof can be measured by related techniquesThe operator can calculate according to the known information, and can give according to experience under the condition of lacking relevant confidence;
x, Y, Z is the barycentric coordinate of the airplane and the system nodes thereof under the airplane body coordinate system;
X i 、Y i 、Z i the gravity center coordinates of the airplane and the system sub-node i thereof under the airplane body coordinate system are obtained;
I x 、I y 、I z the moment of inertia around the x, y and z axes of the airplane and the system nodes thereof under the airplane body coordinate system;
I xy the method comprises the following steps of (1) taking an inertia product of an airplane and system nodes thereof on an xy plane under an airplane body coordinate system;
I xi 、I yi 、I zi the method comprises the following steps of (1) obtaining the inertia moment of an airplane and a system sub-node i thereof around x, y and z axes under an airplane body coordinate system; i is xyi The method comprises the following steps of (1) taking an inertia product of an airplane and a system sub-node i thereof on an xy plane under an airplane body coordinate system;
ΔX i 、ΔY i 、ΔZ i the distances of the gravity centers of the airplane and the system nodes and the child nodes i thereof in the directions of x, y and z under the airplane body coordinate system are shown.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (1)
1. An aircraft and a system weight characteristic determination method thereof are characterized by comprising the following steps:
constructing an airplane plane layout coordinate system;
the gravity center coordinates of the airplane components are determined under the plane layout coordinates of the airplane;
constructing an aircraft body coordinate system;
converting the barycentric coordinates of the aircraft components calibrated under the plane layout coordinate system of the aircraft into the aircraft body coordinate system;
calculating the weight characteristics of the airplane and the system thereof under an airplane body coordinate system;
the method is characterized in that the barycentric coordinate calibrated by the aircraft component under the plane layout coordinate of the aircraft is converted into the aircraft body coordinate system, and specifically comprises the following steps:
wherein the content of the first and second substances,
x, Y, Z is the barycentric coordinate of the airplane component transformed to the airplane body coordinate;
P x 、P x 、P z the gravity center coordinates are calibrated for the airplane components under an airplane plane layout coordinate system;
X min 、X max 、Z min 、Z max reference points of front, back, left and right coordinates of the airplane in an airplane body coordinate system;
P xmin 、P xmax 、P zmin 、P zmax coordinate points of the front, rear, left and right boundaries of the plane in a plane layout coordinate system of the plane are set;
the method for calculating the weight characteristics of the aircraft and the system thereof under the aircraft body coordinate system specifically comprises the following steps:
decomposing the airplane and the system thereof into a tree-shaped product structure, and calculating the weight characteristic of the airplane under an airplane body coordinate system;
the method is characterized in that the airplane and the system thereof are decomposed into a tree-shaped product structure, and the weight characteristic of the airplane is calculated under an airplane body coordinate system, and specifically comprises the following steps:
W＝∑W i ；
I xy ＝∑I xyi +∑{W i ×[ΔX i ×ΔY i ]}；
wherein, the first and the second end of the pipe are connected with each other,
w is the weight of the aircraft and its system nodes;
W i the weight of the airplane and the system child node i thereof;
x, Y, Z is the barycentric coordinate of the airplane and the system nodes thereof under the airplane body coordinate system;
X i 、Y i 、Z i the gravity center coordinates of the airplane and the system sub-node i thereof under the airplane body coordinate system are obtained;
I x 、I y 、I z the moment of inertia around the x, y and z axes of the airplane and the system nodes thereof under the airplane body coordinate system;
I xy the method comprises the following steps of (1) taking an inertia product of an airplane and system nodes thereof on an xy plane under an airplane body coordinate system;
I xi 、I yi 、I zi the method comprises the following steps of (1) obtaining the inertia moment of an airplane and a system sub-node i thereof around x, y and z axes under an airplane body coordinate system; i is xyi The method comprises the following steps of (1) obtaining an inertia product of an airplane and a system sub-node i thereof on an xy plane under an airplane body coordinate system;
ΔX i 、ΔY i 、ΔZ i the distances of the gravity centers of the airplane and the system nodes and the child nodes i thereof in the directions of x, y and z under the airplane body coordinate system are shown.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111070911.8A CN113919056B (en) | 2021-09-13 | 2021-09-13 | Aircraft and system weight characteristic determination method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111070911.8A CN113919056B (en) | 2021-09-13 | 2021-09-13 | Aircraft and system weight characteristic determination method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113919056A CN113919056A (en) | 2022-01-11 |
| CN113919056B true CN113919056B (en) | 2022-09-20 |
Family
ID=79234602
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111070911.8A Active CN113919056B (en) | 2021-09-13 | 2021-09-13 | Aircraft and system weight characteristic determination method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113919056B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114199457B (en) * | 2022-02-17 | 2022-06-03 | 中国航空工业集团公司沈阳飞机设计研究所 | 500 kilogram-level aircraft complete machine weight characteristic high-precision measurement method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104317996A (en) * | 2014-10-15 | 2015-01-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for designing and evaluating center of gravity of airplane |
| RU2013157671A (en) * | 2013-12-24 | 2015-06-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Ульяновская государственная сельскохозяйственная академия имени П.А. Столыпина" | METHOD FOR DETERMINING SYSTEM TILT ANGLES FROM TWO FLAT MIRRORS |
| CA2893712A1 (en) * | 2014-06-16 | 2015-12-16 | Thales | Method and device for determining a control set point of an aircraft, associated computer program and aircraft |
| CN112146738A (en) * | 2019-06-28 | 2020-12-29 | 西安京东天鸿科技有限公司 | Aircraft weighing method and system |
-
2021
- 2021-09-13 CN CN202111070911.8A patent/CN113919056B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2013157671A (en) * | 2013-12-24 | 2015-06-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Ульяновская государственная сельскохозяйственная академия имени П.А. Столыпина" | METHOD FOR DETERMINING SYSTEM TILT ANGLES FROM TWO FLAT MIRRORS |
| CA2893712A1 (en) * | 2014-06-16 | 2015-12-16 | Thales | Method and device for determining a control set point of an aircraft, associated computer program and aircraft |
| CN104317996A (en) * | 2014-10-15 | 2015-01-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for designing and evaluating center of gravity of airplane |
| CN112146738A (en) * | 2019-06-28 | 2020-12-29 | 西安京东天鸿科技有限公司 | Aircraft weighing method and system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113919056A (en) | 2022-01-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10832475B2 (en) | Method for constructing three-dimensional solid model with geometric error and computer-readable storage medium | |
| US11295522B2 (en) | Three-dimensional (3D) model creation and incremental model refinement from laser scans | |
| CN113919056B (en) | Aircraft and system weight characteristic determination method thereof | |
| CN110458174A (en) | A kind of unordered accurate extracting method of cloud key feature points | |
| US6931294B2 (en) | Method for generating three-dimensional CAD models of complex products or systems | |
| US8843352B2 (en) | System and methods facilitating interfacing with a structure design and development process | |
| CN103392180A (en) | Global deformation for a modeled object | |
| CN107622530B (en) | Efficient and robust triangulation network cutting method | |
| CN110866332A (en) | Complex cable assembly assembling method and system | |
| US20100148002A1 (en) | Configurable Cockpit System Based On Design Parameters | |
| CN102985950A (en) | Method for creating three-dimensional shape data, apparatus for creating three-dimensional shape data, and computer-readable storage medium | |
| CN105957146B (en) | Linear engineering three-dimensional geological modeling method | |
| CN112596727A (en) | Web end lightweight display method suitable for Revit BIM model | |
| CN110210063A (en) | A method of architectural elevation is quickly generated based on CAD | |
| CN110414181A (en) | A kind of design method of the heat insulating decorative board exterior wall based on BIM | |
| Chawner et al. | Summary of the 1st AIAA geometry and mesh generation workshop (GMGW-1) and future plans | |
| CN110188151A (en) | A kind of method and electronic device generating indoor map based on CAD and GIS | |
| CN106971043A (en) | The method for building up and device of a kind of nested grid | |
| Zhang et al. | A systematic review of automated BIM modelling for existing buildings from 2D documentation | |
| CN115310325A (en) | Multi-disciplinary coupling analysis framework and method for air refueling of hose taper sleeve | |
| Ren et al. | Intuitive and efficient roof modeling for reconstruction and synthesis | |
| Wang et al. | EQSM: An efficient high quality surface grid generation method based on remeshing | |
| CN116628838A (en) | Method and system for calculating weight center of gravity of open hole of ship body structure based on CAA development | |
| JP4966898B2 (en) | Program, apparatus, and method for generating neutral plane mesh data | |
| CN112487534A (en) | BIM technology-based method for analyzing net height of building |
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 |