CN101893504A - Stiffening rib of flight vehicle aerofoil experimental model - Google Patents
Stiffening rib of flight vehicle aerofoil experimental model Download PDFInfo
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- CN101893504A CN101893504A CN 201010234230 CN201010234230A CN101893504A CN 101893504 A CN101893504 A CN 101893504A CN 201010234230 CN201010234230 CN 201010234230 CN 201010234230 A CN201010234230 A CN 201010234230A CN 101893504 A CN101893504 A CN 101893504A
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Abstract
The invention relates to a stiffening rib of a flight vehicle aerofoil experimental model, wherein the original stiffening rib of the flight vehicle aerofoil experimental model, made of laminate plate material is replaced by the stiffening rib made of metal material. Steel material or aluminum material and the corresponding thickness can be selected according to the weight ratio of balance weight to total weight for the stiffening rib of the invention. The stiffening rib of a flight vehicle aerofoil low speed wind tunnel experimental model is provided with two through-holes, wherein a screw rod penetrates through the through-holes of the stiffening rib and a balance weight block, and nuts are used to lock and fix the massive balance weight block. The stiffening rib of the flight vehicle aerofoil experimental model can bear balance weight accounting for more than 50% of total weight, effectively reduce the unsafe factor when the massive balance weight block is fixed and avoid that the flight vehicle aerofoil experimental model is damaged in the wind tunnel experiment; and the stiffening rib has simple structure, high safety, reliable performance, true and accurate experimental result, low cost, high practicability and great use value.
Description
Technical field
The present invention relates to a kind of aircraft aerofoil model in wind tunnel stiffening rib, particularly about a kind of stiffening rib of aircraft aerofoil low speed flutter wind tunnel test model.
Background technology
In the manufacturing of aircraft aerofoil flutter test model an important job being arranged is exactly inertia simulation, and inertia simulation comprises the quality of simulating aerofoil, centroid position, and around the mass mement of inertia of stiff shaft, this process counterweight specific implementation.
In the design of aircraft aerofoil low speed flutter wind tunnel test model, the material of wing-surface test model stiffening rib is selected the manufacturing of aviation laminate for use always, account for model gross mass ratio when less in the weight mass of low speed flutter model, this method for designing is very successful, its advantage is easy to process, counterweight is installed simple, and therefore, this method for designing is used always.
Yet along with improving constantly of aircraft performance, during the modelling of aircraft aerofoil low speed flutter test in order to guarantee the true of inertia simulation, the ratio that weight mass accounts for the model gross mass increases greatly, and weight mass often surpasses 50% of model gross mass, sometimes even surpass 90%.Because the increase of weight mass, give the installation of balancing weight, fixedly cause very big difficulty, when the aircraft aerofoil low speed flutter test model that uses aviation laminate made stiffening rib carries out wind tunnel test, the balancing weight dropping situations often takes place, even cause model to damage, can damage wind-tunnel facilities when serious, directly influence wind tunnel test and normally carry out.
Especially account for 90% when above of model gross mass when the counterweight of low speed flutter wind tunnel test model, when carrying out inertia simulation with counterweight, bring very big difficulty to modelling, the stiffening rib that the aviation laminate is made is because sole mass is little, and the quality that can not replace a part of counterweight is to reduce the use amount of counterweight.The stiffening rib strength and stiffness that the aviation laminate is made are all very low, and stiffening rib itself also can't carry the balancing weight of big quality, so, can not satisfy the demand the aircraft aerofoil low speed flutter test modelling requirement of big quality counterweight of the stiffening rib of aviation laminate manufacturing.
In the aircraft aerofoil low speed flutter test modelling of single-spar construction pattern, making, the stiffening rib of being made by the aviation laminate is behind the balancing weight that big quality is installed, when test model carried out wind tunnel test, the situation that balancing weight comes off, test model damages repeatedly took place.
Therefore in the design of aircraft aerofoil low speed flutter wind tunnel test model, the stiffening rib that existing designing technique adopts the aviation laminate to make, counterweight at the low speed flutter model accounted for the ratio of model gross mass above 50% o'clock, counterweight often comes off when wind tunnel test, less reliable, security is low, simultaneously because the wing-surface test model rapid wear, active loss is bigger, has improved experimentation cost.When the counterweight of low speed flutter test model accounts for 70% when above of model gross mass, need very big balancing weight when carrying out inertia simulation with counterweight, the stiffening rib that the aviation laminate is made is because quality is little and intensity is low, can not replace the quality of counterweight also can't carry the counterweight of big quality, therefore, the technology that adopts the aviation laminate to make stiffening rib of flight vehicle aerofoil experimental model can not satisfy designing requirement.
Summary of the invention
Purpose of the present invention: be difficult to carry out big counterweight than test in order to solve prior art aircraft aerofoil low speed flutter test model, easy impaired problem, the invention provides and a kind of big quality counterweight can be installed on aircraft aerofoil low speed flutter test model, and can guarantee aircraft aerofoil low speed flutter test model fragile, not safe and reliable stiffening rib of flight vehicle aerofoil experimental model in wind tunnel test.
In order to solve the problems of the technologies described above, the invention provides following technical scheme: a kind of stiffening rib of flight vehicle aerofoil experimental model, be provided with and be used for the through hole that girder passed or be provided with balancing weight, wherein, described stiffening rib is made by metal material, and thickness is 3～6 millimeters.
Described stiffening rib material is steel, aluminium, iron, copper.
When weight mass account for the model gross mass 50% the time, described stiffening rib is made by the aluminium sheet material of 4～6 millimeters thick.
When weight mass account for the model gross mass 70% the time, described stiffening rib is made by the steel of 3～6 millimeters thick.
When weight mass accounts for the model gross mass greater than 80% the time, described stiffening rib can be not less than 6 millimeters steel by thickness and make.
Beneficial effect of the present invention: be different from the aircraft aerofoil low speed flutter test model stiffening rib that prior art manufactures and designs, the present invention replaces the aircraft aerofoil low speed flutter test model stiffening rib of aviation laminate made with metal material, its strength and stiffness are better than the stiffening rib that the aviation laminate is made greatly, the balancing weight of fixing big quality that can be firm on the stiffening rib improves the security of test model in the wind tunnel test process greatly.The wing-surface test model stiffening rib that metal material is made, quality is several times to tens times of the stiffening rib made of aviation laminate, can substitute the quality of counterweight, thereby can effectively reduce the use amount and the processing capacity of test model counterweight, therefore can reduce the loosening of the balancing weight installed on the stiffening rib of aircraft wings surface model aviation laminate manufacturing and come off, improve the reliability and the security of aircraft wing-surface test model, guarantee carrying out smoothly of wind tunnel test, reduced the damage of aircraft wing-surface test model in the test simultaneously, reduce experimentation cost, therefore had bigger economic worth and actual use value.
Description of drawings
Fig. 1 is the structural representation of stiffening rib of flight vehicle aerofoil experimental model one better embodiment of the present invention;
Fig. 2 is the wiring layout that stiffening rib of flight vehicle aerofoil experimental model one better embodiment of the present invention is installed big quality balancing weight;
Fig. 3 is the side view of Fig. 2;
Wherein, 1-stiffening rib, 2-girder, 3-set nut, 4-screw rod, 5-balancing weight.
Embodiment
The present invention is further illustrated below by embodiment:
Please consult Fig. 1, Fig. 2 and Fig. 3 simultaneously, wherein, Fig. 1 is the structural representation of stiffening rib of flight vehicle aerofoil experimental model one better embodiment of the present invention, and Fig. 2 installs the wiring layout of big quality counterweight, and Fig. 3 is the side view of Fig. 2.Wherein, described stiffening rib 1 is made for the metal material with higher stiffness and intensity, can be steel, aluminum, iron material or the higher metal of other rigidity, in the present embodiment, is made by aluminum.Have one in the middle of the described stiffening rib 1 and be used for the through hole that girder 2 passes, this through hole is a rectangle, and size is consistent with girder 2 cross sections, makes in wind tunnel test, and aerofoil stiffening rib 1 can fixedly secure on girder 2, is difficult for loosening.And be bonded with epoxy resin between girder 2 and the stiffening rib through hole, be beneficial to improve the fastness of the two connection.
In addition, also offer the through hole that is used to install balancing weight 5 on the stiffening rib 1,4 balancing weights 5 are installed in the both sides of stiffening rib 2 respectively in the present embodiment, and pass through hole on balancing weight 5 and the stiffening rib 1 by screw rod 4, and are locked by set nut 3.Wherein, the quality of described 4 balancing weights 5 accounts for the ratio of model gross mass about 50%.Be about 50% the requirement that the counterweight that satisfies aircraft aerofoil low speed flutter wind tunnel test model accounts for the model gross mass, described stiffening rib 1 can adopt the aluminum manufacturing, between thickness adopts 4～6 millimeters.Because therefore the stiffening rib that the strength and stiffness of metal stiffening rib are made significantly better than the aviation laminate, can carry the balancing weight of big quality, and can satisfy the requirement of aircraft aerofoil low speed flutter test Model Design fully.
Course of new aircraft wing-surface test model aerofoil profile frame section stiffening rib 1 of the present invention is made by metal material, the strength and stiffness of aerofoil stiffening rib 1 have been improved, the quality of aerofoil stiffening rib can substitute the quality of counterweight, reduce the use amount of counterweight, simultaneously can carry the balancing weight of big quality, improved the security of aircraft aerofoil low speed flutter wind tunnel test model effectively, it can impairedly not destroyed in wind tunnel test.
Described in addition stiffening rib should account for the ratio of model gross mass according to gross mass, the weight mass of aircraft aerofoil low speed flutter wind tunnel test model, metal material manufacturings such as the steel of selection suitable thickness, aluminium, to satisfy under the structural strength requirement, guarantee the wind tunnel test simulation precision of model.When the weight mass of aircraft aerofoil low speed flutter test model accounted for 50% left and right sides of model gross mass, described stiffening rib 1 can adopt the aluminum manufacturing, between thickness adopts 4～6 millimeters.And be about 70% the requirement that the weight mass that satisfies aircraft aerofoil low speed flutter test model accounts for the model gross mass, described stiffening rib 1 can adopt the steel manufacturing, between thickness adopts 3～6 millimeters.When the counterweight of aircraft aerofoil low speed flutter test model accounts for the model gross mass greater than 80% the time, described stiffening rib 1 can adopt the steel manufacturing, and thickness adopts greater than 6 millimeters.
When the stiffening rib of flight vehicle aerofoil experimental model that adopts metal material to make, through evidence, not only can bear mass ratio and surpass 50% counterweight, even the ratio that the quality of counterweight accounts for the model gross mass reaches 90%, through choosing suitable material and certain thickness metal stiffening rib, in finishing the whole process of all test subjects, none comes off the balancing weight on the described wing-surface test model stiffening rib, and the whole test model remains intact.Therefore described metal stiffening rib proves through actual tests, has greatly improved the security and the reliability of aircraft aerofoil low speed flutter test model, has reduced the test loss, has saved experimentation cost.
Aircraft aerofoil flutter test model aerofoil profile frame section metal stiffening rib of the present invention in sum, solved on the aircraft aerofoil flutter test model big quality counterweight a unstable difficult problem has been installed, in the wind tunnel test process, can solve coming off of balancing weight, the damage of avoiding the aircraft wing-surface test model to be subjected to, improve the security of aircraft aerofoil low speed flutter wind tunnel test model, reduce experimentation cost greatly, described stiffening rib of flight vehicle aerofoil experimental model just changes aviation laminate material into metal material simultaneously, do not increase new structure, with low cost, dependable performance has practicality widely.
Claims (5)
1. stiffening rib of flight vehicle aerofoil experimental model is provided with and is used for the through hole that girder (2) passed or be provided with balancing weight (5), and it is characterized in that: described stiffening rib (1) is made by metal material, and thickness is 3～6 millimeters.
2. stiffening rib of flight vehicle aerofoil experimental model according to claim 1 is characterized in that: described stiffening rib (1) material is steel, aluminium, iron, copper.
3. stiffening rib of flight vehicle aerofoil experimental model according to claim 1 is characterized in that: when weight mass account for the model gross mass 50% the time, described stiffening rib (1) is made by the aluminium sheet material of 4～6 millimeters thick.
4. stiffening rib of flight vehicle aerofoil experimental model according to claim 1 is characterized in that: when weight mass account for the model gross mass 70% the time, described stiffening rib (1) is made by the steel of 3～6 millimeters thick.
5. stiffening rib of flight vehicle aerofoil experimental model according to claim 1 is characterized in that: when weight mass accounts for the model gross mass greater than 80% the time, described stiffening rib (1) can be not less than 6 millimeters steel by thickness and make.
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| CN 201010234230 CN101893504B (en) | 2010-07-20 | 2010-07-20 | Stiffening rib of flight vehicle aerofoil experimental model |
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| CN 201010234230 CN101893504B (en) | 2010-07-20 | 2010-07-20 | Stiffening rib of flight vehicle aerofoil experimental model |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102935897A (en) * | 2011-08-15 | 2013-02-20 | 中国航空工业集团公司西安飞机设计研究所 | Hollow beam for high-speed flutter model with high aspect ratio and production method thereof |
| CN103617323A (en) * | 2013-11-27 | 2014-03-05 | 中国飞行试验研究院 | Flutter data processing framework based on flight test |
| RU2578832C2 (en) * | 2014-07-24 | 2016-03-27 | Российская Федерация, в лице Министерства промышленности и торговли Российской Федерации (Минпромторг России) | Blade of aerodynamic model of propeller |
| CN105571812A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Universal rectifying device for low-speed flutter model |
| CN108036916A (en) * | 2017-11-16 | 2018-05-15 | 大连理工大学 | A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model |
| CN114323561A (en) * | 2021-12-30 | 2022-04-12 | 中国特种飞行器研究所 | Watertight hull test model device with high gravity inertia degree and high degree of freedom adjustment |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2578915C1 (en) * | 2014-11-27 | 2016-03-27 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Dynamically similar aerodynamic model of aircraft bearing surface |
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| GB2414242A (en) * | 2003-03-17 | 2005-11-23 | Corus Aluminium Walzprod Gmbh | Method for producing an integrated monolithic aluminium structure and aluminium product machined from that structure |
| CN101629867A (en) * | 2009-06-05 | 2010-01-20 | 中国航空工业集团公司西安飞机设计研究所 | Protector for wing-surface test model |
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2010
- 2010-07-20 CN CN 201010234230 patent/CN101893504B/en active Active
Patent Citations (2)
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| GB2414242A (en) * | 2003-03-17 | 2005-11-23 | Corus Aluminium Walzprod Gmbh | Method for producing an integrated monolithic aluminium structure and aluminium product machined from that structure |
| CN101629867A (en) * | 2009-06-05 | 2010-01-20 | 中国航空工业集团公司西安飞机设计研究所 | Protector for wing-surface test model |
Non-Patent Citations (1)
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| 《第七届全国空气弹性学术交流会论文》 20011231 高飞 复合材料翼面低速颤振模型设计研究 142-145 1-5 , 2 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102935897A (en) * | 2011-08-15 | 2013-02-20 | 中国航空工业集团公司西安飞机设计研究所 | Hollow beam for high-speed flutter model with high aspect ratio and production method thereof |
| CN103617323A (en) * | 2013-11-27 | 2014-03-05 | 中国飞行试验研究院 | Flutter data processing framework based on flight test |
| RU2578832C2 (en) * | 2014-07-24 | 2016-03-27 | Российская Федерация, в лице Министерства промышленности и торговли Российской Федерации (Минпромторг России) | Blade of aerodynamic model of propeller |
| CN105571812A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Universal rectifying device for low-speed flutter model |
| CN105571812B (en) * | 2014-10-11 | 2017-12-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general fairing of low-speed flutter model |
| CN108036916A (en) * | 2017-11-16 | 2018-05-15 | 大连理工大学 | A kind of multi-functional rib for supersonic wind tunnel all movable rudder surface model |
| CN114323561A (en) * | 2021-12-30 | 2022-04-12 | 中国特种飞行器研究所 | Watertight hull test model device with high gravity inertia degree and high degree of freedom adjustment |
| CN114323561B (en) * | 2021-12-30 | 2023-10-20 | 中国特种飞行器研究所 | Watertight hull test model device with gravity center inertia and high freedom degree adjustment |
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| Publication number | Publication date |
|---|---|
| CN101893504B (en) | 2013-03-06 |
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