CN102147342A - Static test system for min-aircraft structure - Google Patents
Static test system for min-aircraft structure Download PDFInfo
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- CN102147342A CN102147342A CN 201010199168 CN201010199168A CN102147342A CN 102147342 A CN102147342 A CN 102147342A CN 201010199168 CN201010199168 CN 201010199168 CN 201010199168 A CN201010199168 A CN 201010199168A CN 102147342 A CN102147342 A CN 102147342A
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Abstract
The invention relates to a static test system for a min-aircraft structure, which comprises a bearing ceiling (3) comprising multiple sliding rails supported by multiple struts (103), wherein the sliding rail (104) is used for suspending a testing device and/or a testing piece; a bearing terrace (2) comprising multiple vertical rails (101) and multiple horizontal rails (102), wherein the position of the horizontal rail on the vertical rail can be changed randomly. The static test system has the advantages that: 1) a static test platform for a mini-aircraft is provided; therefore, a simple and practical test platform is provided for the design and manufacture of the mini-aircraft; 2) a good experimental platform is provided for teaching experiments so as to help the students have a general knowledge of the structure intensity of the mini-aircraft; 3) a design structure testing tool is provided for design personnel to improve the structure design and analysis capability.
Description
Technical field
The present invention relates to a kind of small aircraft structural static Testing System Design, belong to the structural design field of aviation aircraft.
Background technology
The present invention is mainly used in the test of static strength of parts such as micro air vehicle wing, empennage and complete machine, therefore the explanation of background technology is primarily aimed at this type test and launches.
In the design process of military and civil aircraft, all can carry out repeatedly test of static strength to each parts of aircraft and complete machine, can reach requirement with the intensity and toughness of checking aircraft, and in various degree improvement be done in design according to experimental result.And the designing and producing in the process of micro air vehicle, to the test of static strength of aircaft configuration do not enough.There is not a kind of test of static strength platform of measuring micro air vehicle that is specifically designed at present, all be to rely on designer's engineering experience to design roughly under a lot of situations, can't accomplish to analyze quantitatively, make design result can not reach very high precision, Flight Vehicle Structure is normally strong excessively, and it is unnecessary that there are some weight the part.Particularly to being used for the aircraft of research work, if the structural design of aircraft can be got more rationally, efficient is higher, and its useful load will enlarge markedly, and is helpful to the raising of aircraft flight performance.The slow test platform can also be tested Flight Vehicle Structure deviser's design result, and the result finds out the quality of design very intuitively by experiment, and the slip-stick artist is improved a lot to Flight Vehicle Structure design and analysis ability.
Summary of the invention
According to an aspect of the present invention, provide a kind of micro air vehicle structural static pilot system, it is characterized in that comprising:
A load ceiling, it comprises that described slide rail is used to hang test unit and experimental piece by many slide rails of many shore supports;
The load terrace comprises many vertical rails and many traverse rods, and the position of wherein said traverse rod on described vertical rail can at random change.
According to a further aspect of the present invention, the method for testing of utilizing above-mentioned micro air vehicle structural static pilot system is provided, comprising:
With messenger wire displacement transducer is hung below described load ceiling;
With stay cord the lower surface of described displacement transducer is connected with designated displacement measurement point on the described experimental piece.
According to a further aspect of the present invention, the method for testing of utilizing above-mentioned micro air vehicle structural static pilot system is provided, comprising:
Utilization comprises the branch force mechanisms of at least one lever and messenger wire, for each the predetermined load(ing) point on the described experimental piece applies definite load;
Change the direction of the total power on the described experimental piece that is applied to by a pulley that is installed on the load terrace.
Description of drawings
Fig. 1 is the whole diagrammatic sketch of static testing pad according to an embodiment of the invention.
Fig. 2 has shown that suspension type according to an embodiment of the invention is fixing and has hung the loading of weight formula.
Fig. 3 has shown the fixing and lever component force type loading of cantilevered according to an embodiment of the invention.
Fig. 4 has shown suspension type displacement measurement layout according to an embodiment of the invention.
Embodiment
Want the static strength of test vehicle, key be can each parts diverse location of measurement structure strain and displacement, and then finish strength test.
The present invention realizes experiment to the static strength of testpieces by the measurement to the strain at load test part diverse location place, displacement.Process is: experimental piece is fixed on load wall (1) or the load ceiling (3), utilize different load modes that experimental piece is applied definite load, by displacement and strain gauge means measurement result is fed back on the computer in real time again, draw the intensity and toughness data of experimental piece.
Below in conjunction with the concrete technical scheme of implementing of description of drawings the present invention.
As shown in Figure 1, test-bed according to an embodiment of the invention comprises load wall (1), load terrace (2) and load ceiling (3).Load wall (1) is used for fixing cantilevered experimental piece, is furnished with a lot of fixed hole positions on its plate, relies on these holes to fix experimental piece.Load terrace (2) comprises many (being shown as two among Fig. 1) vertical rail (101) and many (being shown as two among Fig. 1) traverse rods (102), and wherein the position of traverse rod (102) on vertical rail (101) can at random change.Can be by the fixing various testing equipments of traverse rod (102).Load ceiling (3) comprises many (being shown as the six roots of sensation among Fig. 1) slide rails (104) that supported by many (being shown as four among Fig. 1) pillars (103), and slide rail can be hung various experimental pieces and/or test unit on (104), as displacement transducer.Experimental piece be fixed with dual mode---suspension type (being used for for example horizontal tail) and cantilevered (being used for for example wing).The suspension type fixed form utilizes messenger wire (as cable wire) etc. that experimental piece is hung in load ceiling (3) below, as hanging of horizontal tail; The cantilevered fixed form is to utilize web member such as bolt experimental piece to be fixed on the side plate of load wall (1), fixing as wing.
Load maintainer is used for loading given load at the diverse location of experimental piece.The load mode that the present invention adopts is divided into hangs weight formula and lever component force type, so load maintainer also correspondingly has two covers.
Hanging the major requirement of weight formula load mode has hook and weight, and in the embodiment of the invention as shown in Figure 2, weight (203) is connected with the respective loads point (201) of experimental piece (208) by messenger wire (202), gives the load that load(ing) point is determined.
Lever component force type charger is used to utilize lever principle with the transmission of a definite gross load by several bars, becomes the different loads of diverse location.In the embodiment of the invention as shown in Figure 3, lever component force type charger comprises a pulley (206) that is installed on the load terrace (2), is used to change the direction of total power; Optional, as to be connected in series a tension measurement device (205) is used to show load value; Comprise the branch force mechanisms of at least one lever (204) and messenger wire (202), be used to each load(ing) point to apply definite load.
Displacement measuring device
According to one embodiment of present invention, realize the measurement of displacement by hanging accurate draw-wire displacement sensor (302).Displacement transducer (302) is hung on experimental piece (308) top with messenger wire (301), and sensor (302) lower surface is connected with outstanding stay cord (303), is that displacement measurement point (304) is connected with assigned address on the experimental piece (308).When experimental piece (308) twisted flexural deformation, upper and lower displacement vertically can take place in displacement measurement point (304), drives the elongation and the shortening of stay cord, thereby obtains displacement change value.
Strain gauge means
The measurement of experimental piece diverse location strain realizes by the strain gauge (not shown).Utilize the strain testing system displacement of foil gauge can be changed the metering system that is converted to electric signal, obtain the strain value of diverse location.
With the wing is example, calculate gross load that wing should be subjected to and definite magnitude of load of each load(ing) point according to selected suitable overload factor, by load maintainer load is distributed on each load(ing) point (201) then, by measuring the static strength that wing is verified in gross load size, each position strain and displacement.If through overtesting, overload that wing can bear predetermined (as 1.25 times) shows that then the wing reliable design is reasonable.
Shown in the embodiment of Fig. 3 and 4, the root of wing (208,308) has the metal auricle (not shown) that is connected with fuselage, and the wing cantilevered ground that utilizes bolt will be furnished with the metal auricle is fixed with load wall (1).The slide rail (104) that utilizes load ceiling (3) above wing (Fig. 1) lifts displacement transducer (302); The below divides force mechanisms to connect each load(ing) point (201) with the lever that has been connected on the load terrace (2), and links to each other with as shown in Figure 3 gross load charger.A series connection tension measurement device (205) shows the gross load value in the gross load charger.Wing is inner pastes the foil gauge (not shown) at the point that will measure in advance, and the lead of drawing links to each other with the strainmeter (not shown).Displacement transducer (302) all links to each other with computer with strainmeter, so that real-time image data.
System checks that data are errorless in the energising back, with the data zero clearing, presses predetermined load and loads, and observes the value that gross load shows, stops to load the strain and the shift value of record each measurement point of wing this moment when arriving predetermined value.Load increases loading gradually.
With the horizontal tail is example, and the suspension type fixed form adopts lifting rope that testpieces is hung in load ceiling (3) below, and the weight (203) of determining quality links to each other with load(ing) point (201) on the horizontal tail by lifting rope (202).Displacement transducer (302) is positioned at horizontal tail top, is hung under the load ceiling (3), stretches out on stay cord (303) and the horizontal tail and wants the each point (304) of Displacement Measurement value to link to each other.
System checks that every data are errorless in the energising back, with the data zero clearing, presses predetermined load and loads, and writes down the strain and the shift value of each measurement point.After finishing weight is taken off and, be replaced by bigger load and load the data zero clearing.The mode that increases gradually of load is up to reaching predetermined test load like this.
Advantage of the present invention comprises: 1) provide a kind of slow test platform of micro air vehicle, for designing and producing of this class aircraft provides a kind of simple and practical experiment porch; 2) for education experiment provides good experiment porch, being convenient to the student has preliminary understanding to the structural strength of small aircraft; 3) for providing of designer a kind of test instrument of project organization, help to improve structural design and analysis ability.
Should be understood that, in above narration and explanation to just explanation but not determinate of description that the present invention carried out, and do not breaking away under the prerequisite of the present invention that limits as appended claims, can carry out various changes, distortion and/or correction the foregoing description.
Claims (8)
1. micro air vehicle structural static pilot system is characterized in that comprising:
A load ceiling (3), it comprises many slide rails (104) that supported by many pillars (103), described slide rail (104) is used to hang test unit and/or experimental piece;
Load terrace (2) comprises many vertical rails (101) and many traverse rods (102), and the position of wherein said traverse rod on described vertical rail can at random change.
2. according to the micro air vehicle structural static pilot system of claim 1, it is characterized in that further comprising:
Load wall (1) is used for fixing experimental piece, is furnished with a plurality of fixed hole positions on the plate of wherein said load wall (1), relies on these holes to fix experimental piece.
3. according to the micro air vehicle structural static pilot system of claim 1 or 2, it is characterized in that further comprising:
Displacement transducer (302);
Messenger wire (301) is used for described displacement transducer (302) is hung in described load ceiling (3) below;
Stay cord (303), the lower surface of its displacement transducer (302) is connected with designated displacement measurement point (304) on the described experimental piece (308).
4. according to the micro air vehicle structural static pilot system of claim 1 or 2, it is characterized in that further comprising lever component force type charger, described lever component force type charger comprises:
A pulley (206) that is installed on the load terrace (2) is used for direction and position of action point that change is applied to the total power on the described experimental piece (208);
Comprise the branch force mechanisms of at least one lever (204) and messenger wire (202), be used to each the predetermined load(ing) point (201) on the described experimental piece (208) to apply definite load.
5. according to the micro air vehicle structural static pilot system of claim 4, it is characterized in that further comprising:
A tension measurement device (205) that is connected in series between described pulley (206) and the described minute force mechanisms is used to show load value.
6. utilize a kind of method of testing of micro air vehicle structural static pilot system, described micro air vehicle structural static pilot system comprises:
A load ceiling (3), it comprises many slide rails (104) that supported by many pillars (103), described slide rail (104) is used to hang test unit and/or experimental piece (208,308);
Load terrace (2) comprises many vertical rails (101) and many traverse rods (102), and the position of wherein said traverse rod on described vertical rail can at random change,
Described method of testing is characterised in that and comprises:
With messenger wire (301) displacement transducer (302) is hung in described load ceiling (3) below;
With stay cord (303) lower surface of described displacement transducer (302) is connected with designated displacement measurement point (304) on the described experimental piece (308).
7. utilize a kind of method of testing of micro air vehicle structural static pilot system, described micro air vehicle structural static pilot system comprises:
A load ceiling (3), it comprises many slide rails (104) that supported by many pillars (103), described slide rail (104) is used to hang test unit and experimental piece (208,308);
Load terrace (2) comprises many vertical rails (101) and many traverse rods (102), and the position of wherein said traverse rod on described vertical rail can at random change,
Described method of testing is characterised in that and comprises:
Utilization comprises the branch force mechanisms of at least one lever (204) and messenger wire (202), for each the predetermined load(ing) point (201) on the described experimental piece (208) applies definite load;
Change the direction of the total power on the described experimental piece (208) that is applied to by a pulley (206) that is installed on the load terrace (2).
8. according to the method for testing of claim 7, it is characterized in that further comprising:
Utilize a tension measurement device (205) that is connected in series between described pulley (206) and the described minute force mechanisms to show load value.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN 201010199168 CN102147342A (en) | 2010-06-12 | 2010-06-12 | Static test system for min-aircraft structure |
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| CN 201010199168 CN102147342A (en) | 2010-06-12 | 2010-06-12 | Static test system for min-aircraft structure |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102991726A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Loading system and method for airplane structure test |
| CN103630347A (en) * | 2013-11-26 | 2014-03-12 | 成都发动机（集团）有限公司 | Motor substitution equipment for static force test of airplane wing |
| CN105181474A (en) * | 2015-10-10 | 2015-12-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft antenna housing negative pressure aerodynamic load static strength testing device |
| CN105486493A (en) * | 2014-09-17 | 2016-04-13 | 北京强度环境研究所 | Hold-down release simulation test device and application method thereof |
| CN105571841A (en) * | 2015-12-13 | 2016-05-11 | 中国飞机强度研究所 | Wallboard structure overload test equipment |
| CN106092169A (en) * | 2016-05-31 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of roller track channel type stryctyrak test supports device |
| CN106742052A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter body slow test suspension |
| CN106885727A (en) * | 2017-03-23 | 2017-06-23 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft semi-closed structure experiment loading unit |
| CN108528758A (en) * | 2018-05-04 | 2018-09-14 | 中电科芜湖钻石飞机制造有限公司 | General-purpose aircraft mechanical property testing system |
| CN111398040A (en) * | 2020-03-20 | 2020-07-10 | 上海交通大学 | Oblique reverse thrust cascade static test device for aircraft engine |
| CN112326436A (en) * | 2020-10-29 | 2021-02-05 | 合肥工业大学 | Device and method for testing mechanical properties of inner curtain cloth assembly of airship |
| CN114813000A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Load monitoring device and method for buffeting test of aircraft key structure |
| 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 (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102991726A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Loading system and method for airplane structure test |
| CN103630347A (en) * | 2013-11-26 | 2014-03-12 | 成都发动机（集团）有限公司 | Motor substitution equipment for static force test of airplane wing |
| CN103630347B (en) * | 2013-11-26 | 2016-05-18 | 成都发动机（集团）有限公司 | Aircraft wing slow test engine alternate device |
| CN105486493B (en) * | 2014-09-17 | 2017-12-22 | 北京强度环境研究所 | A kind of Hold down and release simulation test device and its application method |
| CN105486493A (en) * | 2014-09-17 | 2016-04-13 | 北京强度环境研究所 | Hold-down release simulation test device and application method thereof |
| CN105181474A (en) * | 2015-10-10 | 2015-12-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft antenna housing negative pressure aerodynamic load static strength testing device |
| CN105181474B (en) * | 2015-10-10 | 2018-11-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft radome Pneumatic negative-pressure load test of static strength device |
| CN105571841A (en) * | 2015-12-13 | 2016-05-11 | 中国飞机强度研究所 | Wallboard structure overload test equipment |
| CN105571841B (en) * | 2015-12-13 | 2018-04-13 | 中国飞机强度研究所 | A kind of wall panel structure overload test equipment |
| CN106092169B (en) * | 2016-05-31 | 2018-10-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of roller track channel type stryctyrak test support device |
| CN106092169A (en) * | 2016-05-31 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of roller track channel type stryctyrak test supports device |
| CN106742052A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter body slow test suspension |
| CN106885727A (en) * | 2017-03-23 | 2017-06-23 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft semi-closed structure experiment loading unit |
| CN108528758A (en) * | 2018-05-04 | 2018-09-14 | 中电科芜湖钻石飞机制造有限公司 | General-purpose aircraft mechanical property testing system |
| CN108528758B (en) * | 2018-05-04 | 2023-08-15 | 中电科芜湖钻石飞机制造有限公司 | Universal aircraft mechanical property test system |
| CN111398040A (en) * | 2020-03-20 | 2020-07-10 | 上海交通大学 | Oblique reverse thrust cascade static test device for aircraft engine |
| CN112326436A (en) * | 2020-10-29 | 2021-02-05 | 合肥工业大学 | Device and method for testing mechanical properties of inner curtain cloth assembly of airship |
| CN114813000A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Load monitoring device and method for buffeting test of aircraft key structure |
| 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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Application publication date: 20110810 |