CN105444999A - Static test loading method for long straight wings of small unmanned air vehicle - Google Patents
Static test loading method for long straight wings of small unmanned air vehicle Download PDFInfo
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- CN105444999A CN105444999A CN201410383726.8A CN201410383726A CN105444999A CN 105444999 A CN105444999 A CN 105444999A CN 201410383726 A CN201410383726 A CN 201410383726A CN 105444999 A CN105444999 A CN 105444999A
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- 238000012360 testing method Methods 0.000 title claims abstract description 54
- 238000011068 loading method Methods 0.000 title claims abstract description 37
- 230000003068 static effect Effects 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 claims abstract description 9
- 230000000694 effects Effects 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 6
- 239000000725 suspension Substances 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 4
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 2
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Abstract
A static test loading method for long straight wings of a small unmanned air vehicle is characterized in that: a loading device includes wing chordwise tie belts (2), wing spanwise tie belts (4) which can constraint spanwise movement of the wing chordwise tie belts (2), wing loading point hanging rings (8) which are located on the wing chordwise tie belts (2), a locking device (3) which is located between a left wing and a right wing and under the wings and connects the spanwise tie belts (4) of the left wing and the right wing, and loading sandbags (7). According to the method, a tie belt frame design can be adopted, and a plurality of chordwise high-strength tie belts and spanwise high-strength tie belts constrained on a surface of the wings can form an outer load transmission frame, so that the weight of the loading sandbags can be converted into the load of the wings of the air vehicle, and the method can be used for static test loading of a structure. The loading method and device are easy to use, are reliable in loading, are low in cost, are good in adaptability, and can be used for static tests of various medium-sized unmanned air vehicles and various small unmanned air vehicles.
Description
Technical field
The present invention relates to a kind of static(al) test loading method of miniature self-service captain straight wing, belong to aviation aircraft structure static strength test field, the structure static strength test being applicable to SUAV (small unmanned aerial vehicle) high aspect ratio wing loads.
Background technology
Unmanned plane is the important means of battlefield investigation in modern war.SUAV (small unmanned aerial vehicle) due to its have that block dimension is little, vision stealth effect is good, low cost of manufacture, transport are flexible and convenient to use, battlefield mobility high, be in modern war, realize the important weapon that the tactical missions such as investigation enemy's situation, information relay, supplemental communication are spied in front.This kind of unmanned plane is generally the long straight wing structure of high aspect ratio, carries necessary communication, investigation equipment load, and has certain stagnant empty ability.The unmanned plane of foreign well-known, as " scanning hawk " unmanned plane, belongs to this type.
Aircraft structure strength test typically refers to structural static test, it is the basic load by loading certain magnitude at aircraft surfaces, by measuring distortion, the strain regime of structure, the load-bearing capacity of check flight under design load effect, thus provide safeguard for the flight safety of aircraft, structural safety.Wing is the prevailing lift face of aircraft, is also the topmost load bearing component of full machine, most important for aircaft configuration safety.For SUAV (small unmanned aerial vehicle), because the exhibition of its wing is relatively large to size, relatively " elongated ", wing is again its main stand under load parts to structure simultaneously, and therefore, other parts such as relative fuselage, empennage, the strength problem of wing is the most outstanding.The test of static strength technology of conventional airplane is comparatively ripe, there is special loading equipemtn, can the in-flight Arbitrary Loads state of simulated aircraft, but, this kind equipment is comparatively heavy, needs fixing test site, has certain experimental scale, cost is also higher, and the SUAV (small unmanned aerial vehicle) slow test being not suitable for low cost is carried out.
In addition, the test of aircaft configuration static(al) needs the acting force applying certain magnitude at body structure surface, the load diatibution in simulated flight.SUAV (small unmanned aerial vehicle) due to himself physical dimension little, particularly the tangential yardstick of wing is little, and the wing carries equipment and easily causes special-shaped projection, and wing structure external form minutia is various, and therefore the distributed circuit difficulty of SUAV (small unmanned aerial vehicle) aerofoil surface is large.
Therefore, need to develop a kind of SUAV (small unmanned aerial vehicle) architectural feature that is applicable to, easy to use, with low cost, and there is the static(al) test loading method of certain versatility, and develop corresponding coordinative experiments device, to realize the object that the test of SUAV (small unmanned aerial vehicle) static(al) loads.
Summary of the invention
The present inventor recognizes, SUAV (small unmanned aerial vehicle) wing static(al) test loading method and device, should realize along wing exhibition to load diatibution, the position of load(ing) point should keep relatively fixing in process of the test, namely tangential, open up to fricton-tight, and multistage loadings in process of the test can be realized, simulate the load of different magnitude, and should low, the charger easy accessibility of cost, and the installation of charger need to do any transformation to aircraft body structure.
Consider above-mentioned needs, the present inventor is complicated, changeable for SUAV (small unmanned aerial vehicle) construction profile, static(al) test is difficult to the difficult problem effectively loaded, provide a kind of the static(al) test loading method and the scheme that are applicable to miniature self-service captain straight wing, easy to use, with low cost, do not affect housing construction, and there is certain versatility.
According to an aspect of the present invention, provide a kind of static(al) loading device for testing being applicable to miniature self-service captain straight wing, it is characterized in that comprising:
Airfoil chord is to bandage; The wing exhibition of constraint airfoil chord to bandage exhibition to movement is to bandage; Be positioned at airfoil chord to the wing load(ing) point suspension ring on bandage; Between wing lower aerofoil, left and right wing, connect the locking device of left and right wing exhibition to bandage; Load sandbag.
According to another aspect of the present invention, provide the static(al) test loading method of the long straight wing of a kind of baby plane, it is characterized in that comprising:
A) along aircraft wing exhibition to arranging some erect-positions, as load(ing) point and bandage erect-position, the load in simulated flight is along exhibition to distribution;
B) at each erect-position place, by airfoil chord to bandage along airfoil chord to winding with one circuit and locking, thus in static(al) test, load is evenly passed to wing exhibition to erect-position section by bandage;
C) at upper surface of the airfoil bandage apart from leading edge 1/4 chord length point position, carry sandbag load, the position of carry simulate airfoil chord to position of action point; Wherein aircraft is for being inverted attitude;
D) open up to bandage to arranging the wing longitudinally connected along wing exhibition on the upper and lower surface of wing, adopt bonding hasp to connect, be both convenient to quick assembling, enough exhibition can be provided again to constraint, and stable connection, prevent load(ing) point in test process along exhibition to slippage;
E) the left and right described wing exhibition longitudinally connected on surface arranges locking device between bandage under the wings of an airplane, for connect the exhibition of left and right wing to bandage and carry on airframe.
Advantage of the present invention comprises:
1) loading Position is relatively fixing, and location is reliable, has enough constraining force constraints; 2) charger is easy to loading and unloading, does not need to do any variation to aircaft configuration, can realize Fast Installation and loading; 3) there is the ability of multistage loadings, the ladder increasing or decreasing of load can be realized; 4) practical, with low cost being convenient to is transformed, and can be applicable to the situation that SUAV (small unmanned aerial vehicle) structure external form is complicated, special-shaped projection is many.
The main scope of application of the present invention: application is mainly miniature self-service captain straight wing configuration, also can be used for the medium or high aspect ratio configuration of conventional light aircraft.
Accompanying drawing explanation
Fig. 1 shows charger according to an embodiment of the invention macroscopic view schematic diagram.
Fig. 2 show installation from airfoil chord to bandage (2) be connected.
Fig. 3 shows the connection diagram of the left and right wing exhibition of connection according to an embodiment of the invention to the locking device (3) of bandage (4).
Fig. 4 shows load sandbag (7) loading on wing.
Fig. 5 shows in an example of the present invention, airfoil chord open up to bandage (2) and wing be bound by wing (6) from testing airplane object (1) to bandage (4) on effect in kind.
Fig. 6 shows in above-mentioned example of the present invention, under the maximum carry state of wing, and wing mount point suspension ring (8) effect in kind with the harshest stand under load of the hook (9) of load sandbag (7).
Fig. 7 shows in above-mentioned example of the present invention, the complete machine implementation result that maximum carry state is got off the plane.
Fig. 8 shows in above-mentioned example of the present invention, the strain result curve that slow test records.
Embodiment
The present invention adopts bandage frame-type to design, by aerofoil surface constraint some along tangential, open up to high strength bandage, form external applied load and transmit framework, thus be the structural loads of aircraft wing (6) by the sandbag weight conversion of carry, test for the static(al) carried out for aircraft object (1).Aircraft object (1) for small-sized long straight wing configuration unmanned plane, main structural components be fuselage (5) and wing (6).
The technical scheme of specific embodiment of the invention is described below in conjunction with accompanying drawing.
Miniature self-service captain straight wing charger according to an embodiment of the invention as shown in Figure 1, Figure 2, Figure 3, Figure 4.The main body of charger of the present invention adopts canvas strip design.Namely along aircraft wing (6) exhibition to arranging some erect-positions, as load(ing) point and bandage erect-position, the load in simulated flight is simultaneously along exhibition to distribution; Each erect-position place, by airfoil chord to bandage (2) along airfoil chord to winding with one circuit, with bonding hasp (11) locking, can evenly pass to wing exhibition to erect-position section by load by bandage in static(al) test; Upper surface of the airfoil (in static(al) test, aircraft is for being inverted attitude) bandage is near leading edge 1/4 chord length point position, be provided with metal suspension ring (8), for carry sandbag load, simultaneously the position of suspension ring (8) simulate airfoil chord to position of action point; The upper and lower surface of wing is opened up to bandage (4) along wing exhibition to being provided with the wing longitudinally connected, also bonding hasp (11) is adopted to connect, both quick assembling was convenient to, enough exhibition can be provided again to constraint, and stable connection, prevent load(ing) point in test process along exhibition to slippage; The left and right longitudinal direction of wing lower surface connects between bandage (4) and is provided with locking device (3), connect left and right wing longitudinally connect bandage (4) and carry on airframe (5).According to one embodiment of present invention, locking device (3) is for being similar to the structure (shown in Fig. 3) of lock ring.In a specific embodiment according to the present invention, wing exhibition pass to bandage (4) from the bottom of locking device (3) and walk around this device around post (12), then pass (as shown in Fig. 3 upper left) from the gap around post (12) and this device.By regulating through the length of the bandage of locking device (3), left and right wing can be regulated to open up degree of tightness to bandage (4), and by bonding hasp (11) locking, for left and right bandage provides enough exhibition to constraint.Meanwhile, wing exhibition, to the constraint reaction around post (12) of bandage (4) by locking device (3), makes this device have certain self-locking effect.Carry load is simulated with the load sandbag (7) of link (10) with hook (9), bottom by top, can realize the multistage loadings of static(al) test.
Example: tested object is the small-sized long straight wing unmanned plane of the span about 1.7 meters, and aircraft whole machine weight is about 20kg, aerofoil surface exists because steering wheel installation, rudder face install the special-shaped projection caused.The multistage loadings that load increment is 20% can be realized in test process; In test, maximum load can reach 44kg, and carry mode is still effective, moves or come off without mount point; Static(al) test result (straining with load increment change) shows that this loading scheme linearity good (as shown in Figure 8) meets aircraft static(al) test basic demand.Total cost of manufacture of this example static(al) loading device for testing is only Renminbi more than 600 yuan, and this type of slow test external coordination cost, up to even hundreds thousand of unit of tens thousand of unit, and needs fixing test site, special auxiliary facility and experimental prototype usually, with high costs.
Fig. 5-Fig. 7 is the field condition picture of this test case of display, and Fig. 8 is test result curve.As can be seen from the test result curve of Fig. 8, applying the aerofoil surface strain value that charger of the present invention and method record increases linear with load, and the linearity is good, illustrate that multistage loadings of the present invention is effective, test data is steady, dispersed little, is ideal static(al) test result.
Claims (7)
1. the static(al) test loading method of the long straight wing of baby plane, is characterized in that comprising:
A) along aircraft wing (6) exhibition to arranging some erect-positions, as load(ing) point and bandage erect-position, the load in simulated flight is along exhibition to distribution;
B) at each erect-position place, by airfoil chord to bandage (2) along airfoil chord to winding with one circuit and locking, thus in static(al) test, load is evenly passed to wing exhibition to erect-position section by bandage;
C) at upper surface of the airfoil bandage apart from leading edge 1/4 chord length point position, carry sandbag load, the position of carry simulate airfoil chord to position of action point; Wherein aircraft is for being inverted attitude;
D) open up to bandage (4) to arranging the wing longitudinally connected along wing exhibition on the upper and lower surface of wing, bonding hasp (11) is adopted to connect, both quick assembling was convenient to, enough exhibition can be provided again to constraint, and stable connection, prevent load(ing) point in test process along exhibition to slippage;
E) the left and right described wing exhibition longitudinally connected on surface arranges locking device (3) between bandage (4) under the wings of an airplane, for connect the exhibition of left and right wing to bandage (4) and carry on airframe (5).
2. the static(al) test loading method of the long straight wing of baby plane according to claim 1, is characterized in that:
Described step C comprises: arrange metal suspension ring (8) in the position of carry sandbag load, for sandbag load described in carry, the position of suspension ring (8) simulate airfoil chord to position of action point.
3. the static(al) test loading method of the long straight wing of baby plane according to claim 1, is characterized in that: aircraft is for being inverted attitude;
4. the static(al) test loading method of the long straight wing of baby plane according to claim 1, is characterized in that:
Described step B) in, airfoil chord is locked to bandage (2) bonding hasp (11).
5. the static(al) test loading method of the long straight wing of baby plane according to claim 1, is characterized in that:
Described step D) in, wing exhibition is locked to bandage (4) bonding hasp (11).
6. the static(al) test loading method of the long straight wing of baby plane according to claim 1, is characterized in that:
Locking device (3), for being similar to the structure of lock ring, for regulating left and right wing to open up to the degree of tightness of bandage (4), for left and right wing exhibition provides enough exhibition to constraint to bandage (4), and has certain self-locking effect.
7. the static(al) test loading method of the long straight wing of baby plane according to claim 1, is characterized in that:
Carry load is simulated by the load sandbag (7) of top buckle, bottom band, can realize the multistage loadings of static(al) test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| CN105444999A true CN105444999A (en) | 2016-03-30 |
| CN105444999B CN105444999B (en) | 2018-04-13 |
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Cited By (6)
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| CN106017877A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Loading method in movable surface limit 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 |
| CN109612659A (en) * | 2018-12-28 | 2019-04-12 | 湖北航天技术研究院总体设计所 | A kind of load charger of abnormity configuration bay 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 |
| WO2024061148A1 (en) * | 2022-09-19 | 2024-03-28 | 峰飞航空科技(昆山)有限公司 | Test frame for strength of wings under static loads |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017877A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Loading method in movable surface limit load test |
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| 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 |
| CN109612659A (en) * | 2018-12-28 | 2019-04-12 | 湖北航天技术研究院总体设计所 | A kind of load charger of abnormity configuration bay 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 |
| WO2024061148A1 (en) * | 2022-09-19 | 2024-03-28 | 峰飞航空科技(昆山)有限公司 | Test frame for strength of wings under static loads |
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