CN107609248A - Aircraft flutter model design method based on increasing material manufacturing - Google Patents
Aircraft flutter model design method based on increasing material manufacturing Download PDFInfo
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- CN107609248A CN107609248A CN201710792108.2A CN201710792108A CN107609248A CN 107609248 A CN107609248 A CN 107609248A CN 201710792108 A CN201710792108 A CN 201710792108A CN 107609248 A CN107609248 A CN 107609248A
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Abstract
The present invention relates to aircraft flutter test technical field, specifically provide the aircraft flutter model design method based on increasing material manufacturing, shape data according to real structure, beam, wall, rib, the structure occupy-place of edge strip, the structure that rigidity is not provided is removed in flutter model structure, it is equivalent in proportion that rigidity is carried out according to the material of real structure and the increasing material material of flutter model, determine the physical dimension of flutter model, construction weight distribution is calculated according to the material data for increasing material, inertial properties according to real structure again, calculating needs the weight and position of centre of gravity of counterweight, inside the upwind position of flutter model, increase the local harden structure for supporting and reinforcing, obtain flutter model.
Description
Technical field
The present invention relates to aircraft flutter test technical field, the aircraft flutter model more particularly to based on increasing material manufacturing
Design method.
Background technology
Flutter Problem is one of the problem of part Vehicle Structure Strength must face, and except simulation calculation is carried out, wind-tunnel tries
Test and understand the important means of buffet characteristic.For Large Scale Space Vehicle, full scale wind tunnel test is done, no matter from cost to wind-tunnel
Ability is all difficult to technical difficulty etc. is many-sided, so most flutter wind tunnel experiments is blown by using flutter model
What wind was realized.For the structural dynamic characteristics of real simulation structure, usual flutter scale model needs to simulate real structure
Stiffness characteristics, mass property.Traditional flutter model generally use metal roof beam structure, d type frame, covering, balancing weight etc. are realized to true
The simulation of real structure.With flourishing for Aeronautics and Astronautics industry, many new aircaft configurations are also brought to flutter model design
New challenge.
The content of the invention
The invention provides the aircraft flutter model design method based on increasing material manufacturing, comprise the following steps：
Step 1, according to the structure occupy-place of the shape data, beam, wall, rib, edge strip of real structure, in flutter model structure
Middle remove does not provide the structure of rigidity, and rigidity is carried out in proportion etc. according to the material of real structure and the increasing material material of flutter model
Effect, determine the physical dimension of flutter model, equivalent formulation E0I0=nE1I1, wherein E0For real structure elasticity modulus of materials, I0
For real structure cross sectional moment of inertia, n is real structure and the ratio of rigidity of model, E1For cast material modulus of elasticity, I1For model pair
Answer structural section the moment of inertia；
Step 2, construction weight distribution, then the inertial properties according to real structure are calculated according to the material data for increasing material,
Calculating needs the weight and position of centre of gravity of counterweight；
Step 3, inside the upwind position of flutter model, increase the local harden structure for supporting and reinforcing.
Aircraft flutter model design method provided by the invention based on increasing material manufacturing, is made using increases material manufacturing technology
Based on flutter model, more convenient, saving labour can be made than conventional model, so as to produce more preferable economic benefit.
Brief description of the drawings
Embodiment below with reference to accompanying drawing description is exemplary, it is intended to for the explanation and illustration present invention, and can not be managed
Solve as the limitation to protection scope of the present invention.
Fig. 1 is a kind of flow chart of illustrative examples of the present invention.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.
It should be noted that：In the accompanying drawings, from beginning to end same or similar label represent same or similar element or
Element with same or like function.Described embodiment is part of the embodiment of the present invention, rather than whole implementation
Example, in the case where not conflicting, the feature in embodiment and embodiment in the application can be mutually combined.Based in the present invention
Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made,
Belong to the scope of protection of the invention.
Herein, " schematic " expression " serving as example, example or explanation ", will should not be described herein as " showing
Any diagram, the embodiment of meaning property " are construed to a kind of preferred or more advantageous technical scheme.
The invention provides the aircraft flutter model design method based on increasing material manufacturing, flutter model requirement is：Accurately
Profile, structure, stiffnes s equivalent, the inertial properties that can bear and transmit load it is equivalent.The design method comprises the following steps：
Step 1, the structural parameters of flutter model are obtained according to the parameter of real structure contracting ratio：According to the outer of real structure
The structure occupy-place of graphic data, beam, wall, rib, edge strip, the structure that rigidity is not provided is removed in flutter model structure, according to true
The material of structure and the increasing material material progress rigidity of flutter model are equivalent in proportion, determine the physical dimension of flutter model, such as
Beam, wall, rib, edge strip, the sectional dimension etc. of covering.Equivalent formulation is E0I0=nE1I1, wherein E0For real structure elastic properties of materials mould
Amount, I0For real structure cross sectional moment of inertia, n is real structure and the ratio of rigidity of model, E1For cast material modulus of elasticity, I1For
Model counter structure cross sectional moment of inertia.
Step 2, construction weight is calculated by software according to the material data for increasing material and is distributed, then according to real structure
Inertial properties, the weight and position of centre of gravity for needing counterweight are calculated, the weight size of needs is converted into by increasing material density of material
It is added in designed model.
Step 3, during wind tunnel test, the structure stress situation of windward side is even more serious compared with other positions, therefore
Inside the upwind position of flutter model, increase the local harden structure for supporting and reinforcing, the local harden structure is to overall firm
Degree influences negligible.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can readily occur in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (1)
1. the aircraft flutter model design method based on increasing material manufacturing, it is characterised in that comprise the following steps：
Step 1, according to the structure occupy-place of the shape data, beam, wall, rib, edge strip of real structure, in flutter model structure
It is equivalent in proportion according to the material of real structure and the increasing material material progress rigidity of flutter model except the structure for not providing rigidity,
Determine the physical dimension of flutter model, equivalent formulation E0I0=nE1I1, wherein E0For real structure elasticity modulus of materials, I0For
Real structure cross sectional moment of inertia, n are the ratio of rigidity of real structure and model, E1For cast material modulus of elasticity, I1It is corresponding for model
Structural section the moment of inertia；
Step 2, construction weight distribution, then the inertial properties according to real structure are calculated according to the material data for increasing material, are calculated
Go out to need the weight and position of centre of gravity of counterweight；
Step 3, inside the upwind position of flutter model, increase the local harden structure for supporting and reinforcing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710792108.2A CN107609248A (en) | 2017-09-05 | 2017-09-05 | Aircraft flutter model design method based on increasing material manufacturing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710792108.2A CN107609248A (en) | 2017-09-05 | 2017-09-05 | Aircraft flutter model design method based on increasing material manufacturing |
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| Publication Number | Publication Date |
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| CN107609248A true CN107609248A (en) | 2018-01-19 |
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| CN201710792108.2A Pending CN107609248A (en) | 2017-09-05 | 2017-09-05 | Aircraft flutter model design method based on increasing material manufacturing |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111310315A (en) * | 2020-01-21 | 2020-06-19 | 哈尔滨工程大学 | Design method for improving aeroelastic stability of beam structure based on ultra-high-speed aircraft |
| CN112140553A (en) * | 2020-07-30 | 2020-12-29 | 中山大学 | 3D printing-based navigation body manufacturing method capable of controllably positioning high-precision center of mass |
| CN112611538A (en) * | 2020-11-24 | 2021-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Design parameter control method for transonic flutter wind tunnel model processing |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101509825A (en) * | 2009-03-13 | 2009-08-19 | 西安交通大学 | Aeroplane buffet air tunnel model integration design and manufacturing method |
| US20170334557A1 (en) * | 2014-12-19 | 2017-11-23 | Sikorsky Aircraft Corporation | Delta fuselage for vertical take-off and landing (vtol) aircraft |
-
2017
- 2017-09-05 CN CN201710792108.2A patent/CN107609248A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101509825A (en) * | 2009-03-13 | 2009-08-19 | 西安交通大学 | Aeroplane buffet air tunnel model integration design and manufacturing method |
| US20170334557A1 (en) * | 2014-12-19 | 2017-11-23 | Sikorsky Aircraft Corporation | Delta fuselage for vertical take-off and landing (vtol) aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111310315A (en) * | 2020-01-21 | 2020-06-19 | 哈尔滨工程大学 | Design method for improving aeroelastic stability of beam structure based on ultra-high-speed aircraft |
| CN111310315B (en) * | 2020-01-21 | 2022-09-09 | 哈尔滨工程大学 | Design method for improving aeroelastic stability of beam structure based on ultra-high-speed aircraft |
| CN112140553A (en) * | 2020-07-30 | 2020-12-29 | 中山大学 | 3D printing-based navigation body manufacturing method capable of controllably positioning high-precision center of mass |
| CN112611538A (en) * | 2020-11-24 | 2021-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Design parameter control method for transonic flutter wind tunnel model processing |
| CN112611538B (en) * | 2020-11-24 | 2022-05-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Design parameter control method for transonic flutter wind tunnel model processing |
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| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Yu Jiaxin Inventor after: Hu Xin Inventor after: Hu Jialiang Inventor after: Bai Nan Inventor after: Wang Hezhe Inventor before: Yu Jiaxin Inventor before: Hu Xin Inventor before: Hu Jialiang Inventor before: Bai Nan Inventor before: Wang Hezhe |
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Application publication date: 20180119 |
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| RJ01 | Rejection of invention patent application after publication |