CN105444999B - A kind of static(al) suitable for miniature self-service captain's straight wing tests loading method - Google Patents
A kind of static(al) suitable for miniature self-service captain's straight wing tests loading method Download PDFInfo
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- CN105444999B CN105444999B CN201410383726.8A CN201410383726A CN105444999B CN 105444999 B CN105444999 B CN 105444999B CN 201410383726 A CN201410383726 A CN 201410383726A CN 105444999 B CN105444999 B CN 105444999B
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- 238000012360 testing method Methods 0.000 title claims abstract description 48
- 238000011068 loading method Methods 0.000 title claims abstract description 40
- 230000003068 static effect Effects 0.000 title claims abstract description 35
- 230000000694 effects Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 230000009471 action Effects 0.000 claims description 3
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- 239000002184 metal Substances 0.000 claims description 2
- 229910052751 metal Inorganic materials 0.000 claims description 2
- 238000004088 simulation Methods 0.000 claims description 2
- 238000012546 transfer Methods 0.000 claims description 2
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 claims 1
- 239000010931 gold Substances 0.000 claims 1
- 229910052737 gold Inorganic materials 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 abstract description 3
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- 238000004891 communication Methods 0.000 description 2
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- 230000008859 change Effects 0.000 description 1
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Abstract
A kind of static(al) suitable for miniature self-service captain's straight wing tests loading method, it is characterised in that loading device includes：The tangential bandage of wing (2), the constraint tangential bandage of wing (2) is opened up to be opened up to bandage (4) to mobile wing, wing load(ing) point hanging ring (8) on the tangential bandage of wing (2), between left and right wing below wing, connection left and right wing opens up the locking device (3) and load sandbag (7) to bandage (4).The present invention is designed using bandage frame-type, by aerofoil surface fetter it is some along it is tangential, open up to high intensity bandage, form external applied load and transmit frame, so that by the structural loads that the sandbag weight conversion of carry is aircraft wing (6), the static(al) for structure tests loading.The loading method and device are using simplicity, and loading is reliable, of low cost, adaptable, suitable for the slow test of all kinds of medium and small unmanned captain's straight wings.
Description
Technical field
A kind of static(al) the present invention relates to miniature self-service captain straight wing tests loading method, belongs to aviation aircraft structure
Test of static strength field, loads suitable for the structure static strength test of small drone high aspect ratio wing.
Background technology
Unmanned plane is the important means that battlefield is investigated in modern war.Small drone due to its with block dimension it is small,
The features such as vision stealth effect is good, manufacture cost is low, transport is flexible and convenient to use, battlefield mobility is high, is in modern war, in fact
The important weapon of the tactical missions such as investigation enemy's situation, information relaying, supplemental communication is spied in existing front.This kind of unmanned plane is usually great Zhan
String carries necessary communication, investigation equipment load, and have certain stagnant empty ability than long straight wing structure.Foreign well-known
Unmanned plane, such as " scanning hawk " unmanned plane, belong to this type.
Aircraft structure strength experiment typically refers to structural static test, it is by loading certain magnitude in aircraft surfaces
Basic load, by the deformation of measurement structure, strain regime, bearing capacity of the check flight in the case where design load acts on, so that
Flight safety, structure for aircraft provide safeguard safely.Wing is the prevailing lift face of aircraft, and the most important carrying of full machine
Component, it is most important safely for aircaft configuration.For small drone, since its wing is opened up to relatively large sized,
Structure is with respect to " elongated ", while wing is its main stand under load component again, therefore, with respect to other components such as fuselage, empennage, wing
Strength problem is the most prominent.The test of static strength technology of conventional airplane is comparatively ripe, there is dedicated loading equipemtn, can simulate
The in-flight Arbitrary Loads state of aircraft, however, this kind equipment is comparatively heavy, it is necessary to which the test site fixed, has
Certain experimental scale, cost is also higher, and the small drone slow test for being not suitable for low cost is carried out.
In addition, the test of aircaft configuration static(al) needs to apply the active force of certain magnitude in body structure surface, in simulated flight
Load is distributed.For small drone since its own structure size is small, the tangential scale of particularly wing is small, and the wing carries equipment and easily makes
Into special-shaped projection, wing structure external form minutia is various, therefore the distributed circuit difficulty of small drone aerofoil surface is big.
It is a kind of suitable for small drone architectural feature therefore, it is necessary to develop, using easy, of low cost, and have
The static(al) test loading method of certain versatility, and corresponding coordinative experiments device is developed, to realize that small drone static(al) is surveyed
Try the purpose of loading.
The content of the invention
Present inventors have recognized that small drone wing static(al) test loading method and device, be able to should realize along machine
The span to load be distributed, the position of load(ing) point be able to should keep being relatively fixed during experiment, i.e., tangential, open up to no cunning
It is dynamic, and can realize multistage loadings during experiment, simulate different magnitude of load, and should also cost is low, loading device
It is convenient for disassembly and assembly, and the installation of loading device need not do aircraft body structure any transformation.
In view of above-mentioned needs, the present inventor is complicated, changeable for small drone construction profile, and static(al) test is difficult to have
Imitate the problem of loading, there is provided a kind of static(al) suitable for miniature self-service captain's straight wing tests loading method and scheme, uses
It is easy, of low cost, do not influence housing construction, and there is certain versatility.
According to an aspect of the invention, there is provided a kind of static(al) suitable for miniature self-service captain's straight wing tests loading
Device, it is characterised in that including：
The tangential bandage of wing；The constraint tangential bandage of wing is opened up to be opened up to bandage to mobile wing；Positioned at the tangential bandage of wing
On wing load(ing) point hanging ring；Between wing lower aerofoil, left and right wing, connection left and right wing opens up the locking dress to bandage
Put；Load sandbag.
According to another aspect of the present invention, there is provided a kind of static(al) test loading method of long straight wing of baby plane,
It is characterized by comprising：
A) opened up along aircraft wing to some erect-positions of setting, as load(ing) point and bandage erect-position, the load edge in simulated flight
Open up to distribution；
B) at each erect-position, the tangential bandage of wing is wound with one circuit and locked along wing is tangential, so as to be surveyed in static(al)
Load is uniformly transferred by bandage in examination and is opened up to wing to erect-position section；
C) at upper surface of the airfoil bandage is away from 1/4 chord length point position of leading edge, carry sandbag load, the position of carry simulates
The tangential position of action point of wing；Wherein aircraft is inversion posture；
D) open up to setting longitudinally connected wing to open up to bandage along wing on the upper and lower surface of wing, connected using bonding hasp
Connect, not only easy to quick assembling, but also enough exhibitions can be provided to constraint, and stable connection, prevent load(ing) point during the test
Extend to sliding；
E) the left and right longitudinally connected wing on surface is opened up to locking device is set between bandage under the wings of an airplane, is used for
Left and right wing is connected to open up to bandage and carry on airframe.
Advantages of the present invention includes：
1) loading Position is relatively fixed, and positioning is reliable, and there is enough restraining forces to fetter；2) loading device handling side
Just, it is not necessary to any variation is done to aircaft configuration, you can realize Fast Installation and loading；3) there is the ability of multistage loadings, can
To realize the ladder increasing or decreasing of load；4) it is highly practical, it is of low cost easy to transformation, small drone knot can be suitable for
Situation more than complicated, the special-shaped projection of structure external form.
The main scope of application of the present invention：Application is mainly miniature self-service captain's straight wing configuration, also be can be used for normal
Advise that lightweight aircraft is medium or high aspect ratio configuration.
Brief description of the drawings
Fig. 1 shows loading device macroscopic view schematic diagram according to an embodiment of the invention.
Fig. 2 shows the installation and connection of the tangential bandage of wing (2).
Fig. 3 shows that the left and right wing of connection according to an embodiment of the invention opens up the locking device to bandage (4)
(3) connection diagram.
Fig. 4 shows loading of the load sandbag (7) on wing.
Fig. 5 shows in an example of the present invention that the tangential bandage of wing (2) is opened up to bandage (4) with wing and is bound by survey
The effect in kind taken a flight test on the wing (6) of machine object (1).
Fig. 6 is shown in the examples detailed above of the present invention, and under wing maximum carry state, wing mount point hanging ring (8) is with carrying
The most harsh stand under load material object effect of the hook (9) of lotus sandbag (7).
Fig. 7 shown in the examples detailed above of the present invention, complete machine implementation result that maximum carry state is got off the plane.
Fig. 8 shown in the examples detailed above of the present invention, strain result curve that slow test measures.
Embodiment
The present invention using bandage frame-type design, by aerofoil surface fetter it is some along it is tangential, open up to high intensity tie up
Band, forms external applied load and transmits frame, so as to be the structural loads of aircraft wing (6) by the sandbag weight conversion of carry, for opening
Exhibition is tested for the static(al) of aircraft object (1).Aircraft object (1) is small-sized long straight wing configuration unmanned plane, main structural components
For fuselage (5) and wing (6).
Below in conjunction with the technical solution of the specific implementation of the brief description of the drawings present invention.
Miniature self-service captain straight wing loading device according to an embodiment of the invention as shown in Figure 1, Figure 2, Fig. 3, Fig. 4 institute
Show.The main body of loading device of the present invention uses canvas strip design.Opened up along aircraft wing (6) to some erect-positions of setting, as
Load(ing) point and bandage erect-position, while the load in simulated flight is extended to distribution；At each erect-position, by the tangential bandage of wing (2)
Wind with one circuit along wing is tangential, with bonding hasp (11) lock, static(al) test in can by load by bandage uniformly transfer to
Wing is opened up to erect-position section；Upper surface of the airfoil (aircraft is inversion posture in static(al) test) bandage is away from 1/4 chord length point position of leading edge
Near, equipped with metal hanging ring (8), the position for carry sandbag load, while hanging ring (8) simulates the tangential application point of wing
Position；Open up to equipped with longitudinally connected wing and opened up to bandage (4), also using bonding hasp (11) along wing in the upper and lower surface of wing
Connection, not only easy to quick assembling, but also can provide enough exhibitions to constraint, and stable connection, prevent load(ing) point in test process
In extend to sliding；Locking device (3) is equipped between the left and right longitudinally connected bandage (4) of wing lower surface, connects left and right machine
The longitudinally connected bandage of the wing (4) and carry is on airframe (5).According to one embodiment of present invention, locking device (3) is
Similar to the structure of lock ring (shown in Fig. 3).In a specific embodiment according to the present invention, wing is opened up to bandage (4) from lock
The bottom of tight device (3), around column (12), is then pierced by across and around the device from around gap of the column (12) with the device
(as shown in Fig. 3 upper lefts).By adjusting the length through the bandage of locking device (3), left and right wing can be adjusted and opened up to bandage
(4) elastic, and locked by being bonded hasp (11), enough exhibitions are provided to constraint for left and right bandage.Meanwhile wing open up to
Bandage (4) makes the device have certain self-locking effect by the constraint reaction around column (12) of locking device (3).Carry carries
Lotus carries load sandbag (7) simulation of hook (9), bottom with link (10), it can be achieved that static(al) test adds step by step by top
Carry.
Example：Test object be about 1.7 meters of the span small-sized long straight wing unmanned plane, aircraft whole machine weight about 20kg, machine
Wing surface exists due to special-shaped projection caused by steering engine installation, rudder face installation.It is 20% that load increment can be achieved in test process
Multistage loadings；Maximum load can reach 44kg in test, and carry mode is still effective, and no mount point is mobile or comes off；Static(al)
Test result (strain and change with load increment) shows that the loading scheme linearity is good (as shown in Figure 8), meets aircraft static(al)
Test basic demand.Total cost of manufacture of the example static(al) loading device for testing is only more than 600 yuan of RMB, and usually such
Slow test external coordination is of high cost up to tens thousand of members even hundreds thousand of members, and needs fixed test site, special auxiliary facility and
Experimental prototype, it is with high costs.
Fig. 5-Fig. 7 is the field condition picture for showing the test case, and Fig. 8 is test result curve.From the test of Fig. 8
As can be seen that the aerofoil surface strain value that the loading device of the application present invention and method measure is in load increase in result curve
Linear relationship, and the linearity is good, illustrates that multistage loadings of the present invention are effective, test data is steady, dispersiveness is small, is ideal
Static(al) test result.
Claims (7)
1. the static(al) test loading method of miniature self-service captain's straight wing, it is characterised in that including：
A) opened up along unmanned plane wing (6) to some erect-positions of setting, as load(ing) point and bandage erect-position, the load edge in simulated flight
Open up to distribution；
B) at each erect-position, the tangential bandage of wing (2) is wound with one circuit and locked along wing is tangential, so as to be tested in static(al)
Middle uniformly transfer load by bandage is opened up to erect-position section to wing；
C) at upper surface of the airfoil bandage is away from 1/4 chord length point position of leading edge, carry sandbag load, the position of carry simulates wing
Tangential position of action point；Wherein unmanned plane is inversion posture；
D) opened up on the upper and lower surface of wing along wing to setting longitudinally connected wing to open up to bandage (4), using bonding hasp (11)
Connection, not only easy to quick assembling, but also can provide enough exhibitions to constraint, and stable connection, prevent load(ing) point in test process
In extend to sliding；
E) the left and right longitudinally connected wing on surface is opened up to locking device (3) is set between bandage (4) under the wings of an airplane, is used
In connecting, left and right wing is opened up to bandage (4) and carry is on unmanned aerial vehicle body (5).
2. the static(al) test loading method of miniature self-service captain straight wing according to claim 1, it is characterised in that：
The step C includes：Metal hanging ring (8) is set in the position of carry sandbag load, for sandbag load described in carry, gold
The position for belonging to hanging ring (8) simulates the tangential position of action point of wing.
3. the static(al) test loading method of miniature self-service captain straight wing according to claim 1, it is characterised in that：Unmanned plane is
It is inverted posture.
4. the static(al) test loading method of miniature self-service captain straight wing according to claim 1, it is characterised in that：
The step B) in, the tangential bandage of wing (2) is locked with bonding hasp (11).
5. the static(al) test loading method of miniature self-service captain straight wing according to claim 1, it is characterised in that：
The step D) in, wing is opened up locks to bandage (4) bonding hasp (11).
6. the static(al) test loading method of miniature self-service captain straight wing according to claim 1, it is characterised in that：
Locking device (3) is the structure similar to lock ring, is opened up for adjusting left and right wing to the elastic of bandage (4), is left and right
Wing is opened up to bandage (4) and provides enough exhibitions to constraint, and has certain self-locking effect.
7. the static(al) test loading method of miniature self-service captain straight wing according to claim 1, it is characterised in that：
Carry sandbag load is by sandbag load (7) simulation of top buckle, bottom band, it can be achieved that static(al) test adds step by step
Carry.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410383726.8A CN105444999B (en) | 2014-08-06 | 2014-08-06 | A kind of static(al) suitable for miniature self-service captain's straight wing tests loading method |
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| CN201410383726.8A CN105444999B (en) | 2014-08-06 | 2014-08-06 | A kind of static(al) suitable for miniature self-service captain's straight wing tests loading method |
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| CN105444999B true CN105444999B (en) | 2018-04-13 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017877B (en) * | 2016-05-16 | 2018-11-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of load loading method in active face Ultimate load test |
| CN108168855A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint launch slow test method |
| CN109612659B (en) * | 2018-12-28 | 2021-08-10 | 湖北航天技术研究院总体设计所 | Load loading device of special-shaped cabin section |
| CN110346098A (en) * | 2019-07-05 | 2019-10-18 | 傅明尧 | A kind of wing slow test hanging apparatus |
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
| CN218382145U (en) * | 2022-09-19 | 2023-01-24 | 峰飞航空科技(昆山)有限公司 | Wing static load strength test frame |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2319675A (en) * | 1940-07-20 | 1943-05-18 | Goodrich Co B F | Loading patch for stress-testing aircraft |
| US2382491A (en) * | 1943-08-11 | 1945-08-14 | Fred H Loftus | Furnace unloader |
| US2505887A (en) * | 1944-12-11 | 1950-05-02 | Lockheed Aircraft Corp | Control for fluid-pressure actuated devices |
| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| CN101685039A (en) * | 2008-09-23 | 2010-03-31 | 中国农业机械化科学研究院 | Method for testing field ground load calibration of airplane wing and calibration device thereof |
| CN103303493A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Wing load applying device for large aircraft strength test |
| CN103487277A (en) * | 2013-10-11 | 2014-01-01 | 沈阳航空航天大学 | Multifunctional universal test bed for static test on light airplane |
| CN103808505A (en) * | 2014-03-06 | 2014-05-21 | 哈尔滨工业大学 | Wing static load experiment device |
-
2014
- 2014-08-06 CN CN201410383726.8A patent/CN105444999B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2319675A (en) * | 1940-07-20 | 1943-05-18 | Goodrich Co B F | Loading patch for stress-testing aircraft |
| US2382491A (en) * | 1943-08-11 | 1945-08-14 | Fred H Loftus | Furnace unloader |
| US2505887A (en) * | 1944-12-11 | 1950-05-02 | Lockheed Aircraft Corp | Control for fluid-pressure actuated devices |
| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| CN101685039A (en) * | 2008-09-23 | 2010-03-31 | 中国农业机械化科学研究院 | Method for testing field ground load calibration of airplane wing and calibration device thereof |
| CN103303493A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Wing load applying device for large aircraft strength test |
| CN103487277A (en) * | 2013-10-11 | 2014-01-01 | 沈阳航空航天大学 | Multifunctional universal test bed for static test on light airplane |
| CN103808505A (en) * | 2014-03-06 | 2014-05-21 | 哈尔滨工业大学 | Wing static load experiment device |
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