CN207045788U - A kind of T tails aircraft vertical fin spar testpieces - Google Patents
A kind of T tails aircraft vertical fin spar testpieces Download PDFInfo
- Publication number
- CN207045788U CN207045788U CN201720969357.XU CN201720969357U CN207045788U CN 207045788 U CN207045788 U CN 207045788U CN 201720969357 U CN201720969357 U CN 201720969357U CN 207045788 U CN207045788 U CN 207045788U
- Authority
- CN
- China
- Prior art keywords
- edge strip
- spar
- web
- testpieces
- utility
- 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
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
It the utility model is related to a kind of T tails aircraft vertical fin spar testpieces, it includes web, the edge strip for being symmetricly set in web both sides and the edge strip crimp being connected with edge strip, the web, edge strip and edge strip crimp are integrated configuration, the edge strip is perpendicular to web, and the thickness of the edge strip is more than the thickness of web, edge strip crimp is parallel to the web.For T tails aircraft vertical fin spar testpieces of the present utility model testing program more of the prior art, have the following advantages that：1) by the edge strip and edge strip crimp for the spar testpieces that the former covering in former spar is assigned in the utility model, can accurately simulate support of the covering to spar；2) short form test part designs；3) experiment difficulty is reduced, saves experimentation cost.
Description
Technical field
The utility model belongs to aircraft structure test technical field, more particularly to a kind of T tails aircraft vertical fin spar testpieces.
Background technology
Aircraft tail structure is generally divided into two kinds, and one kind is horizontal tail structure, and one kind is vertical fin structure.Horizontal tail is symmetrically
It is arranged in airplane tail group, substantially horizontal position；And vertical fin include it is a variety of, one of which is just T-shaped empennage, T-shaped empennage by
Formed perpendicular to the vertical fin of afterbody and the horizontal tail vertical with vertical fin.
For T-shaped empennage aircraft, because horizontal tail height is placed in vertical fin wing tip, vertical fin spar is except bearing asymmetric motor-driven cause
Shearing load, still suffer from be poised for battle it is motor-driven caused by Tensile or Compressive Loading, this is different from traditional low-set-tail aircraft.Spar is born
The complexity of load brings difficulty to the design of spar testpieces.The design of conventional flap beam test part frequently with diagonal stretch plate or
Person's single cantilever beam method.This two kinds of testpieces are designed for shear-type load, and Tensile or Compressive Loading can not be considered to spar
Influence.
If interception spar typical segment directly carries out spar compressive load experiment, due to lacking branch of the covering to spar flange
Support, spar flange end free, edge strip can shift to an earlier date unstable failure, and the actual stand under load of this and spar on aircraft is not inconsistent.
In the prior art, in experiment if desired for support of the simulation covering to spar flange, it is necessary to carry out box section experiment, such as
Box section structure described in Fig. 1, existing spar include former web 1 ' and former edge strip 2 ', and former edge strip 2 ' is fixed with former covering 3 ', internal
It is made up of stringer 4 ', is compressed box section during experiment.But the component level of box section will be risen to the experiment of the part level of spar
Experiment, test class improve one-level, and testpieces production and the expense tested greatly increase.
Utility model content
The purpose of this utility model is to provide a kind of T tails aircraft vertical fin spar testpieces, for solving at present to try spar
Test in part or using the relatively low single-blade beam test of precision, or the problem of using cost higher box section testpieces.
To reach above-mentioned purpose, the technical solution adopted in the utility model is：A kind of T tails aircraft vertical fin spar testpieces,
It includes web, the edge strip for being symmetricly set in web both sides and the edge strip crimp being connected with edge strip, the web, edge strip and edge
Bar crimp is integrated configuration, and the edge strip is perpendicular to web, and the thickness of the edge strip is more than the thickness of web, and edge strip crimp is put down
Row is in the web.
The preferred embodiment of the utility model one, the thickness of the edge strip crimp are more than the thickness of web and/or edge strip 2
Degree.
The preferred embodiment of the utility model one, airplane tail in the material and real structure of the empennage beam test part
The material of spar is identical.
For T tails aircraft vertical fin spar testpieces of the present utility model testing program more of the prior art, have as follows
Advantage：
1) support of the covering to spar is simulated, passes through the spar being assigned to the former covering in former spar in the utility model
In the edge strip and edge strip crimp of testpieces, support of the covering to spar can be accurately simulated；
2) short form test part designs, otherwise former testpieces is single-blade girder construction, otherwise it is the component-level of box section structure, it is right
In single-blade girder construction, it can not simulate the support to spar of covering, and for the component of box section structure, testpieces is complicated,
Design difficulty increases；
3) experiment difficulty is reduced, experimentation cost is saved, for the box section structure in former testing program, the experiment of component-level
Its cost can increased dramatically, and the utility model greatly reduces experimentation cost by the way that component-level is reduced into part level,
The time of manufacture testpieces is saved, valuable time has been saved for airplane design.
Brief description of the drawings
Accompanying drawing herein is merged in specification and forms the part of this specification, show meet it is of the present utility model
Embodiment, and for explaining principle of the present utility model together with specification.
Fig. 1 is the box section structure schematic diagram of prior art.
Fig. 2 is the T tail aircraft vertical fin spar testpieces front views of the embodiment of the utility model one.
Fig. 3 is the T tail aircraft vertical fin spar testpieces front views of the embodiment of the utility model one.
Fig. 4 is that the T tail aircraft vertical fin spars testpieces of the embodiment of the utility model one clamps schematic diagram.
Reference：
1 '-former web, 2 '-former edge strip, 3 '-former covering, 4 '-stringer；
1- webs, 2- edge strips, 3- edge strip crimps.
Embodiment
To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the embodiment of the utility model is further described in more detail.
As shown in Figures 2 and 3 be T tails aircraft vertical fin spar testpieces of the present utility model, it include web 1, symmetrically
The edge strip crimp 3 for being arranged at the edge strip 2 of the both sides of web 1 and being connected with edge strip 2, web 1, edge strip 2 and edge strip crimp 3 are integrated
Configuration, edge strip 2 is perpendicular to web 1, and edge strip crimp 3 is parallel to web 1.The structure being made up of web 1 and edge strip 2 substantially with box section
Former spar structure in testpieces is identical, however, to ensure that before the spar testpieces in the utility model destroys, edge strip 2 can not
Unstability, and the width of edge strip 2 are less than effective carrying width that the former covering 3 ' in former spar contacts with former edge strip 2, this practicality
The thickness of new edge strip 2 should be greater than the thickness of web 1, it is furthermore preferred that the thickness of the edge strip 2 ' in the utility model should be situated between
Between the thickness of former edge strip 2 ' and the former thickness of edge strip 2 ' and the former thickness of covering 3 ' sum.
In the utility model, the structural parameters of web 1 should be identical with the former parameter of spar structure median ventral plate 1 ', i.e. this practicality
The width and thickness of web 1 ' in new are identical with the width and thickness of former web 1 ', to reach the purpose of experiment examination.
In the utility model, the thickness of edge strip crimp 3 is more than the thickness of web 1 and/or edge strip 2.Due to former testpieces
For box section structure, box section structure has a former covering 3 ', and former covering 3 ' bears multidirectional power, and the spar in the utility model
In testpieces, no stressed-skin construction, the assembly test part for changing box section structure is the spar structure of single structure, and what former covering 3 ' was born
The power of the equidirectional born with former edge strip 2 ' has been assigned on edge strip 2 of the present utility model, therefore edge strip 2 thickeies, still
Power perpendicular to the former direction of edge strip 2 ' is unallocated, therefore is provided with edge strip crimp 3, and the power in direction is larger, therefore is thickeied.
Finally, the material of empennage beam test part and airplane tail in real structure or former testing program are made in the utility model
The material of spar is identical.
The T tail aircraft vertical fin spars testpieces clamping schematic diagram being illustrated in figure 4 in the utility model, by the way that T tails are flown
Machine vertical fin spar testpieces is arranged in testing machine, and extruding is carried out to testpieces can complete to test.
For T tails aircraft vertical fin spar testpieces of the present utility model testing program more of the prior art, have as follows
Advantage：
1) support of the covering to spar is simulated, passes through the wing being assigned to the former covering 3 ' in former spar in the utility model
In the edge strip 2 and edge strip crimp 3 of beam test part, support of the covering to spar can be accurately simulated；
2) short form test part designs, otherwise former testpieces is single-blade girder construction, otherwise it is the component-level of box section structure, it is right
In single-blade girder construction, it can not simulate the support to spar of covering, and for the component of box section structure, testpieces is complicated,
Design difficulty increases；
3) experiment difficulty is reduced, experimentation cost is saved, for the box section structure in former testing program, the experiment of component-level
Its cost can increased dramatically, and the utility model greatly reduces experimentation cost by the way that component-level is reduced into part level,
The time of manufacture testpieces is saved, valuable time has been saved for airplane design.
It is described above, optimal embodiment only of the present utility model, but the scope of protection of the utility model is not
This is confined to, any one skilled in the art can readily occur in the technical scope that the utility model discloses
Change or replacement, should all cover within the scope of protection of the utility model.Therefore, the scope of protection of the utility model should be with
The scope of the claims is defined.
Claims (3)
1. a kind of T tails aircraft vertical fin spar testpieces, it is characterised in that the T tails aircraft vertical fin spar testpieces includes web
(1) the edge strip crimp (3) for, being symmetricly set in the edge strip (2) of web both sides and being connected with edge strip (2), the web (1), edge
Bar (2) and edge strip crimp (3) are integrated configuration, and the edge strip (2) is perpendicular to web (1), and the thickness of the edge strip (2) is more than
The thickness of web (1), edge strip crimp (3) is parallel to the web (1).
2. T tails aircraft vertical fin spar testpieces according to claim 1, it is characterised in that the thickness of the edge strip crimp (3)
Degree is more than web (1) and/or the thickness of edge strip (2).
3. T tails aircraft vertical fin spar testpieces according to claim 1, it is characterised in that the empennage beam test part
Material is identical with the material of airplane tail spar in real structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720969357.XU CN207045788U (en) | 2017-08-04 | 2017-08-04 | A kind of T tails aircraft vertical fin spar testpieces |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720969357.XU CN207045788U (en) | 2017-08-04 | 2017-08-04 | A kind of T tails aircraft vertical fin spar testpieces |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207045788U true CN207045788U (en) | 2018-02-27 |
Family
ID=61500037
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720969357.XU Active CN207045788U (en) | 2017-08-04 | 2017-08-04 | A kind of T tails aircraft vertical fin spar testpieces |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207045788U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114239150A (en) * | 2021-12-27 | 2022-03-25 | 中国航空工业集团公司西安飞机设计研究所 | Airplane inflection connecting structure and anti-fatigue design method thereof |
-
2017
- 2017-08-04 CN CN201720969357.XU patent/CN207045788U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114239150A (en) * | 2021-12-27 | 2022-03-25 | 中国航空工业集团公司西安飞机设计研究所 | Airplane inflection connecting structure and anti-fatigue design method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Hariharan et al. | Simulation of rotor in hover: Current state, challenges and standardized evaluation | |
| CN105527069B (en) | A kind of transonic wind tunnel test support device, its installation method and application | |
| US10317322B2 (en) | Combined loading in composite materials | |
| CN104931250B (en) | A kind of full machine loading dynamic test method of high-lift system | |
| CN105930616A (en) | Load distribution method for statically indeterminate structure of dynamic wing surface of aircraft | |
| CN207045788U (en) | A kind of T tails aircraft vertical fin spar testpieces | |
| Bender et al. | Investigation of the effect of wrinkle features on wind turbine blade sub-structure strength | |
| CN106354934A (en) | Stiffened wallboard damage tolerance analysis method based on finite element analysis solving | |
| CN104200016A (en) | Multi-control-surface aircraft modal calculation and verification method | |
| CN102136019A (en) | Composite material structural strength analytical method | |
| CN105302994A (en) | Finite element simulation method of beam_plate shell structure | |
| CN106372274A (en) | Method for determining low-load cutoff limit of continuous flight load spectrum | |
| CN109383846A (en) | A kind of T tail aircraft vertical fin spar testpieces | |
| CN203606224U (en) | Process equipment for detecting riveting quality of rivets | |
| III et al. | One dimensional morphing structures for advanced aircraft | |
| CN109238634B (en) | Hypersonic aircraft wind tunnel test model control surface device | |
| CN107918696A (en) | The multi- scenarios method analysis method and computer program of phased array antenna | |
| CN105253323A (en) | Transverse-support-equipped compression test tool for composite material reinforcement plate | |
| CN107451315A (en) | A kind of strength check methods based on hatch door detail model | |
| Souders et al. | VORLAX 2020: Benchmarking Examples of a Modernized Potential Flow Solver | |
| CN108645591A (en) | A kind of V-type tail support device for flat fusion aircraft in transonic wind tunnel | |
| CN207292477U (en) | A kind of micro- truss aerofoil flutter model | |
| CN111017185B (en) | Laminar flow technology verification machine | |
| CN207550540U (en) | flutter model | |
| CN205643010U (en) | Ribbed wallboard compression test spare |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |