技术领域technical field
本发明属于强度试验技术领域，涉及一种被遮蔽翼面的载荷施加方法。The invention belongs to the technical field of strength tests and relates to a load applying method for a shielded airfoil.
背景技术Background technique
翼面被遮蔽，以往加载系统通过在非遮蔽区配载调整压心仅能保证翼面压心前部分翼面传力真实，不能考核全部翼面，且配载翼面施加载荷大于实际载荷，载荷施加区域试验风险大，另一种方式通过去除遮蔽面，在上翼面加载，试验不能获取加载过程的被遮蔽翼面干涉。The airfoil is covered. In the past, the loading system can only ensure the real force transmission of the part of the airfoil before the airfoil pressure center by stowage in the non-shielded area, and the entire airfoil cannot be assessed, and the load applied to the airfoil is greater than the actual load. The risk of the test in the area where the load is applied is high. Another way is to remove the shielding surface and load on the upper airfoil. The test cannot obtain the interference of the shielded airfoil during the loading process.
发明内容Contents of the invention
本发明的目的是提出一种被遮蔽翼面的载荷加载方法。The object of the present invention is to propose a load loading method for a shielded airfoil.
本发明的技术解决方案是，Technical solution of the present invention is,
步骤1:根据翼面载荷分布，给出下翼面后部拉压垫10上的载荷F3、前部拉压垫11的载荷F4，后部拉压垫10与前部拉压垫11之间的距离b，后部钢索8与后部拉压垫10的距离a、、前部钢索12与前部拉压垫11的距离c。确定可以开孔的区域。Step 1: According to the load distribution of the airfoil, the load F3 on the rear tension and pressure pad 10 of the lower airfoil, the load F4 of the front tension and pressure pad 11, and the distance between the rear tension and pressure pad 10 and the front tension and pressure pad 11 are given. The distance b, the distance a between the rear cable 8 and the rear tension and pressure pad 10, the distance c between the front cable 12 and the front tension and pressure pad 11. Identify areas where holes can be drilled.
步骤4:根据步骤2给出的距离a、b、c，将拉压垫粘贴到下翼面，根据F2的载荷的量级选择合适的钢索，Step 4: According to the distances a, b, and c given in step 2, the tension and pressure pads are pasted on the lower airfoil, and the appropriate steel cables are selected according to the magnitude of the load of F2,
步骤5:将拉压垫连接到下部钢梁上，下部钢梁通过钢索与上部钢梁连接，上部钢梁加载点与上翼面胶布带通过加载杠杆连接，实现载荷加载。Step 5: Connect the tension and pressure pad to the lower steel beam, the lower steel beam is connected to the upper steel beam through a steel cable, and the loading point of the upper steel beam is connected to the upper wing tape through a loading lever to realize load loading.
本发明的优点是：本发明通过下翼面拉压垫通过非考核区的开孔和上翼面的胶布带通过杠杆系统结合在一起，使得翼面载荷施加更加真实；保留了绝大部分的遮蔽区域，保证了试验件的完整性，且在实验过程中能够监测到翼面干涉情况；提高了载荷施加的准确性，提高工作效率，缩短试验周期The advantages of the present invention are: the present invention combines the lower airfoil tension and pressure pad through the opening of the non-examination area and the upper airfoil tape through the lever system, so that the application of the airfoil load is more realistic; most of the The shielded area ensures the integrity of the test piece, and the airfoil interference can be monitored during the experiment; the accuracy of load application is improved, the work efficiency is improved, and the test cycle is shortened
附图说明Description of drawings
图1是本发明加载理论设计示意图；Fig. 1 is a schematic diagram of the loading theory design of the present invention;
图2是本发明载荷施加示意图。Fig. 2 is a schematic diagram of load application in the present invention.
其中：1 遮蔽翼面 2 遮蔽面非考核区 3 被遮蔽翼面 4 上部钢梁 5 上部钢索 6 杠杆 7 胶布带钢索 8 后部钢索 9 下部钢梁 10 后部拉压垫 11 前部拉压垫 12 前部钢索 13 上翼面胶布带 14 加载钢索 a 下部钢梁后部钢索 8 与后部拉压垫 10 的距离 b 下部钢梁上后部拉压垫 10 与前部拉压垫 11 的距离 c 下部钢梁上前部拉压垫 11 与前部钢索 12 的距离 d 上部钢梁后部钢索 8 与载荷施加钢索的距离 e 上部钢梁前部钢索 12 与载荷施加钢索的距离 F1 后部钢索 8 上载荷F2 前部钢索 12 上载荷 F3 后部拉压垫 10 载荷 F4 前部拉压垫 11 载荷 F 上部钢梁载荷Among them: 1 Shielded airfoil 2 Non-examination area of shielded surface 3 Shaded airfoil 4 Upper steel beam 5 Upper steel cable 6 Lever 7 Tape belt steel cable 8 Rear steel cable 9 Lower steel beam 10 Rear tension pad 11 Front Tension and pressure pad 12 Front steel cable 13 Upper wing adhesive tape 14 Loading steel cable a The distance between the rear steel cable 8 of the lower steel beam and the rear tension and pressure pad 10 b The distance between the rear tension and pressure pad 10 and the front of the lower steel beam The distance between tension and pressure pad 11 c The distance between the front tension and pressure pad 11 on the lower steel beam and the front steel cable 12 d The distance between the rear steel cable 8 of the upper steel beam and the load applying steel cable e The front steel cable 12 of the upper steel beam Distance from the load-applying cable F1 rear cable 8 load F2 front cable 12 load F3 rear tension pad 10 load F4 front tension pad 11 load F upper beam load
具体实施方式Detailed ways
下面结合附图对本发明作详细说明。The present invention will be described in detail below in conjunction with the accompanying drawings.
步骤1:根据翼面载荷分布，给出下翼面后部拉压垫10上的载荷F3、前部拉压垫11的载荷F4，后部拉压垫10与前部拉压垫11之间的距离b，后部钢索8与后部拉压垫10的距离a、、前部钢索12与前部拉压垫11的距离c。确定可以开孔的区域。Step 1: According to the load distribution of the airfoil, the load F3 on the rear tension and pressure pad 10 of the lower airfoil, the load F4 of the front tension and pressure pad 11, and the distance between the rear tension and pressure pad 10 and the front tension and pressure pad 11 are given. The distance b, the distance a between the rear cable 8 and the rear tension and pressure pad 10, the distance c between the front cable 12 and the front tension and pressure pad 11. Identify areas where holes can be drilled.
步骤4:根据步骤2给出的距离a、b、c，将后部拉压垫10、前部拉压垫11粘贴到下翼面3，根据F2的载荷的量级选择合适的前部钢索12，选择合适的开孔直径。Step 4: According to the distances a, b, and c given in step 2, stick the rear tension and pressure pad 10 and the front tension and pressure pad 11 to the lower airfoil 3, and select the appropriate front steel according to the magnitude of the load of F2 Cable 12, select the appropriate hole diameter.
步骤5:将后部拉压垫10、前部拉压垫11连接到下部钢梁9上，下部钢梁9通过后部钢索8、前部钢索12与上部钢梁4连接，上部钢梁4加载点与上翼面胶布带13通过加载杠杆6通过胶布带钢索7连接，实现载荷加载。Step 5: the rear tension and pressure pad 10 and the front tension and pressure cushion 11 are connected to the lower steel beam 9, the lower steel beam 9 is connected with the upper steel beam 4 by the rear steel cable 8, the front steel cable 12, and the upper steel beam The loading point of the beam 4 is connected with the adhesive tape 13 on the upper wing surface through the loading lever 6 through the adhesive tape steel cable 7 to realize load loading.
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535667.1ACN105486494B (en) | 2014-10-11 | 2014-10-11 | A kind of load applying method of shielded aerofoil |
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535667.1ACN105486494B (en) | 2014-10-11 | 2014-10-11 | A kind of load applying method of shielded aerofoil |
| Publication Number | Publication Date |
|---|---|
| CN105486494A CN105486494A (en) | 2016-04-13 |
| CN105486494Btrue CN105486494B (en) | 2018-07-24 |
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410535667.1AActiveCN105486494B (en) | 2014-10-11 | 2014-10-11 | A kind of load applying method of shielded aerofoil |
| Country | Link |
|---|---|
| CN (1) | CN105486494B (en) |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163963A (en)* | 2018-08-24 | 2019-01-08 | 中国飞机强度研究所 | A kind of test load rubberized tape setting-out template and method |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3472799B2 (en)* | 2000-02-29 | 2003-12-02 | 防衛庁技術研究本部長 | Airfoil for blade |
| 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 |
| CN102991727A (en)* | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Constraint system of airplane structure test |
| 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 |
| CN103558020A (en)* | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Method for applying test load to movable wing surface of aerofoil in process of large deformation of aerofoil |
| CN103994878A (en)* | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Integration test verification method of airplane movable wing surface |
| CN104075868A (en)* | 2014-05-30 | 2014-10-01 | 西北工业大学 | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3472799B2 (en)* | 2000-02-29 | 2003-12-02 | 防衛庁技術研究本部長 | Airfoil for blade |
| 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 |
| CN102991727A (en)* | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Constraint system of airplane structure test |
| 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 |
| CN103558020A (en)* | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Method for applying test load to movable wing surface of aerofoil in process of large deformation of aerofoil |
| CN103994878A (en)* | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Integration test verification method of airplane movable wing surface |
| CN104075868A (en)* | 2014-05-30 | 2014-10-01 | 西北工业大学 | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system |
| Publication number | Publication date |
|---|---|
| CN105486494A (en) | 2016-04-13 |
| Publication | Publication Date | Title |
|---|---|---|
| CN104865123B (en) | Plane draw bar intensity, stiffness test fixture and its application method | |
| CN103558019B (en) | A kind of three slide rail wing flap test methods simulating wing distortion | |
| CN107902105B (en) | Apparatus and method for simulating reliability of airborne missile connection strength | |
| CN105022868A (en) | Calculation method for ultimate strength and fatigue strength of yaw bearing connecting bolt of wind turbine | |
| CN102680221A (en) | Fatigue test method for full-aircraft main operating system of aircraft | |
| EP2644747A3 (en) | Fiber-reinforced barrier coating, method of applying barrier coating to component and turbomachinery component | |
| Guo et al. | The interface crack problem for a functionally graded coating-substrate structure with general coating properties | |
| CN105319039A (en) | Vibration fatigue testing method for large-bypass-ratio engine fan blade with shoulder | |
| CN105486494B (en) | A kind of load applying method of shielded aerofoil | |
| CN109573098B (en) | Full-size fatigue test high vertical tail load loading design method | |
| CN102147342A (en) | Static test system for min-aircraft structure | |
| CN104075868A (en) | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system | |
| CN104897392A (en) | Auricle loaded test method and loading system | |
| CN105136658A (en) | Rubber vulcanization pipe adhesion detection apparatus | |
| CN106840620A (en) | A kind of device suitable for composite wing slow test loading | |
| CN205691426U (en) | A kind of system for detecting end part of composite insulator gold utensil crimp quality | |
| CN101672743B (en) | Simulation test estimation system and test method for construction of inner stayguy suspended holding rod split tower | |
| CN109506913A (en) | A kind of tailskid test of static strength load charger | |
| CN205173176U (en) | Bolt is test block for ultrasonic testing | |
| CN106240842B (en) | A kind of asymmetric fuselage bulkhead four-point bending test method and device | |
| WO2012044733A3 (en) | Non-contact determination of joint integrity between a tsv die and a package substrate | |
| CN202486039U (en) | Testing clamp for coating adhesion | |
| CN204202992U (en) | Bolt shearing test clamp and testing machine | |
| CN203177766U (en) | Testing fixture for outside plate of automobile front anticollision beam | |
| CN204789134U (en) | Aircraft traction lever intensity, rigidity test anchor clamps |
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |