技术领域technical field
本发明属于飞机疲劳试验技术领域，具体涉及一种飞机地面侧向载荷的处理方法。The invention belongs to the technical field of aircraft fatigue tests, and in particular relates to a processing method for aircraft ground side loads.
背景技术Background technique
飞机结构全机疲劳试验是验证机体结构寿命能否满足使用要求的重要手段，设计人员制定试验实施方案时，要做大量的理论分析计算，确保试验加载不仅能真实的模拟飞机的受力状态，还要考虑试验实施规模、试验周期等问题。The fatigue test of the whole aircraft structure is an important means to verify whether the life of the aircraft structure can meet the service requirements. When the designer formulates the test implementation plan, he needs to do a lot of theoretical analysis and calculation to ensure that the test loading can not only truly simulate the stress state of the aircraft, but also Issues such as the scale of the test implementation and the test period should also be considered.
针对地面转弯工况，起落架侧向载荷较大，与之相对应的机身和机翼上的侧向载荷也较大。由于机翼结构特点，侧向载荷不易施加，通常转移到机身进行施加，这将导致机身侧向载荷过大。为满足机身侧向载荷的施加，且不出现局部超载问题，需要在机身两侧布置多个加载点，这将大大增加全机加载点的数量，延长试验周期。For ground turning conditions, the lateral load of the landing gear is relatively large, and the corresponding lateral loads on the fuselage and wings are also relatively large. Due to the structural characteristics of the wing, the side load is not easy to apply, and it is usually transferred to the fuselage for application, which will lead to excessive side load of the fuselage. In order to meet the application of side loads on the fuselage without local overloading, it is necessary to arrange multiple loading points on both sides of the fuselage, which will greatly increase the number of loading points on the whole machine and prolong the test period.
发明内容Contents of the invention
本发明的目的：为了解决上述问题，本发明提出了一种飞机地面侧向载荷的处理方法，在确保该部位考核准确以及其余部位不出现提前破坏的基础上，对飞机结构地面侧向载荷的施加方式进行调整，加快了试验进度，缩短了试验周期。Purpose of the present invention: in order to solve the above problems, the present invention proposes a processing method for aircraft ground lateral loads. On the basis of ensuring that the assessment of this position is accurate and that other positions do not occur in advance, the aircraft structure ground lateral loads The application method is adjusted to speed up the test progress and shorten the test cycle.
本发明的技术方案：一种飞机地面侧向载荷的处理方法，包括以下步骤；Technical solution of the present invention: a method for processing side loads on the ground of an aircraft, comprising the following steps;
步骤一、计算原始加载顺序时,全部起落架的垂向载荷总载ΣFz调整前；Step 1. When calculating the original loading sequence, the total vertical load ΣFz of all landing gears before adjustment ;
左、右主起落架同时施加工况1载荷，然后同时施加工况2载荷,或者左右主起落架同时施加工况2载荷，然后同时施加工况1载荷；The left and right main landing gears apply the load of working condition 1 at the same time, and then apply the load of working condition 2 at the same time, or the left and right main landing gears apply the load of working condition 2 at the same time, and then apply the load of working condition 1 at the same time;
左、右起落架施加工况1及工况2后并计算全部起落架的垂向载荷总载ΣFz调整前；After working condition 1 and working condition 2 are applied to the left and right landing gears, calculate the total vertical load ΣFz of all landing gears before adjustment ;
步骤二、改变对左、右起落架工况载荷加载顺序，使左、右主起落架侧向载荷保持短路；Step 2. Change the load loading order of the left and right landing gears, so that the lateral loads of the left and right main landing gears remain short-circuited;
步骤三、计算加载顺序调整后全部起落架的垂向载荷总载ΣFz调整后；Step 3, calculate the total vertical load ΣFz of all landing gears after the adjustment of the loading sequence;
步骤四、计算垂向载荷修正系数f；Step 4, calculating the vertical load correction factor f;
f＝ΣFz调整后/ΣFz调整前f = ΣFz after adjustment /ΣFz before adjustment
步骤五、对全机垂向载荷进行配平；Step five, trimming the vertical load of the whole machine;
将机身、机翼和尾翼各个部件的垂向载荷Fzi乘以载荷修正系数f；Multiply the vertical load Fzi of each component of the fuselage, wing and empennage by the load correction factor f;
步骤六、除全部起落架外，消除飞机其余部件侧向载荷；Step 6. Except for all the landing gears, eliminate the side loads of the remaining parts of the aircraft;
步骤七、对飞机全机滚转矩Mx、全机俯仰矩My、前起落架侧向载荷Fy及全机偏航矩Mz进行配平；Step 7, trimming the whole machine roll torque Mx, the whole machine pitch moment My, the nose landing gear lateral load Fy and the whole machine yaw moment Mz;
通过在左、右机翼施加垂向载荷Fz配平1来配平全机滚转矩Mx；Trim the overall machine roll torque Mx by applying vertical load Fz on the left and right wings Fztrim 1 ;
通过在前、后机身施加垂向载荷Fz配平2来配平全机俯仰矩My；Trim the whole machine pitching moment My by applying vertical load Fz trim 2 on the front and rear fuselage;
通过在前、后机身施加侧向载荷Fy配平来配平前起落架侧向载荷Fy和全机偏航矩Mz；Trim the side load Fy of the front landing gear and the yaw moment Mz of the whole aircraft by applying the side load Fytrim on the front and rear fuselages;
步骤八、对关键部位的疲劳裕度影响进行分析计算。Step 8: Analyzing and calculating the influence of fatigue margin on key parts.
优选地，所述步骤二中，试验加载时，前起落架和左主起落架加载顺序不变，即首先对前起落架和左主起落架施加工况1载荷，然后施加工况2载荷，与此同时，改变右主起落加载顺序，首先施加工况2载荷，然后施加工况1载荷，使左、右主起落架侧向载荷产生短路。Preferably, in said step 2, during the test loading, the loading sequence of the front landing gear and the left main landing gear remains unchanged, that is, the load of working condition 1 is first applied to the front landing gear and the left main landing gear, and then the load of working condition 2 is applied, At the same time, the loading sequence of the right main landing gear is changed, the load of working condition 2 is applied first, and then the load of working condition 1 is applied, so that the lateral loads of the left and right main landing gears are short-circuited.
优选地，试验加载时，前起落架和右主起落架加载顺序不变，即首先对前起落架和右主起落架施加工况1载荷，然后施加工况2载荷，与此同时，改变左主起落加载顺序，首先施加工况2载荷，然后施加工况1载荷，使左、右主起落架侧向载荷产生短路。Preferably, during the test loading, the loading sequence of the nose landing gear and the right main landing gear remains unchanged, that is, the load of working condition 1 is first applied to the nose landing gear and the right main landing gear, and then the load of working condition 2 is applied. At the same time, the left The loading sequence of the main landing gear is to first apply the load of working condition 2, and then apply the load of working condition 1, so that the lateral loads of the left and right main landing gears are short-circuited.
优选地，所述步骤一中，所述全部起落架包括：前起落架、左起落架及右起落架。Preferably, in the first step, all the landing gears include: front landing gear, left landing gear and right landing gear.
优选地，所述工况1和工况2分别为左转弯和右转弯。Preferably, the working conditions 1 and 2 are left turn and right turn respectively.
本发明技术方案的有益技术效果：本发明一种飞机地面侧向载荷的处理方法，主要考核部位为起落架与机身连接结构的强度，在确保该部位考核准确以及其余部位不出现提前破坏的基础上，对飞机结构地面侧向载荷的施加方式进行调整，加快了试验进度，缩短了试验周期。Beneficial technical effects of the technical solution of the present invention: the present invention is a method for processing side loads on the ground of an aircraft. The main assessment part is the strength of the connection structure between the landing gear and the fuselage. To ensure the accuracy of the assessment of this part and the absence of premature failure in other parts On this basis, the method of applying the lateral load on the ground of the aircraft structure is adjusted, which speeds up the test progress and shortens the test cycle.
附图说明Description of drawings
图1现有技术中地面左转弯时左、右起落架的载荷加载情况示意图；Fig. 1 is a schematic diagram of the loading situation of the left and right landing gears when the ground turns left in the prior art;
图2现有技术中地面右转弯时左、右起落架的载荷加载情况示意图；Fig. 2 is a schematic diagram of the loading situation of the left and right landing gears when the ground turns right in the prior art;
图3为本发明一种飞机地面侧向载荷的处理方法的一优选实施例的右主起落架加载顺序调整后，地面左转弯时左、右主起落架的加载情况示意图；Fig. 3 is a schematic diagram of the loading conditions of the left and right main landing gears when the ground turns left after the loading order of the right main landing gear is adjusted in a preferred embodiment of the method for processing side loads on the ground of an aircraft;
图4为本发明一种飞机地面侧向载荷的处理方法的一优选实施例的右主起落架加载顺序调整后，地面右转弯时左、右主起落架的加载情况示意图。Fig. 4 is a schematic diagram of the loading of the left and right main landing gears when the ground is turning right after the loading sequence of the right main landing gear is adjusted in a preferred embodiment of the method for processing side loads on the ground of an aircraft.
具体实施方式detailed description
为使本发明实施的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行更加详细的描述。在附图中，自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。所描述的实施例是本发明一部分实施例，而不是全部的实施例。下面通过参考附图描述的实施例是示例性的，旨在用于解释本发明，而不能理解为对本发明的限制。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。下面结合附图对本发明的实施例进行详细说明。In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.
在本发明的描述中，需要理解的是，术语“中心”、“纵向”、“横向”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明保护范围的限制。In describing the present invention, it is to be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the Means that a device or element must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of the invention.
一种飞机地面侧向载荷的处理方法，包括以下步骤；A method for processing side loads on the ground of an aircraft, comprising the following steps;
1)、计算原始加载顺序时,全部起落架的垂向载荷总载ΣFz调整前；1) When calculating the original loading sequence, the total vertical load ΣFz of all landing gear before adjustment ;
地面侧向载荷工况包括左转弯工况1和右转弯工况2，原始加载顺序下前起落架、左起落架及右起落架首先施加左转弯工况1载荷，然后施加右转弯工况2载荷，其中左转弯工况1载荷和右转弯工况2载荷如下：The ground lateral load conditions include left turn condition 1 and right turn condition 2. Under the original loading sequence, the nose landing gear, left landing gear and right landing gear first apply the load of left turn condition 1, and then apply the load of right turn condition 2 The loads, where the load of left turn condition 1 and the load of right turn condition 2 are as follows:
左转弯工况1：Left turn condition 1:
前起落架：Fy1前＝-10000N，Fz1前＝50000N；Front landing gear: Fy1 front = -10000N, Fz1 front = 50000N;
左主起落架：Fy1左＝-70000N，Fz1左＝350000N；Left main landing gear: Fy1 left = -70000N, Fz1 left = 350000N;
右主起落架：Fy2右＝70000N，Fz2右＝350000N；Right main landing gear: Fy2 right=70000N, Fz2 right=350000N;
ΣFz调整前＝Fz1前+Fz1左+Fz1右＝1150000N；ΣFz before adjustment = Fz1 front + Fz1 left + Fz1 right = 1150000N;
右转弯工况2：Right turn condition 2:
前起落架：Fy2前＝10000N，Fz2前＝50000N；Front landing gear: Fy2 front = 10000N, Fz2 front = 50000N;
左主起落架：Fy2左＝170000N，Fz2左＝750000N；Left main landing gear: Fy2 left = 170000N, Fz2 left = 750000N;
右主起落架：Fy1右＝-170000N，Fz1右＝750000N；Right main landing gear: Fy1 right = -170000N, Fz1 right = 750000N;
ΣFz调整前＝Fz2前+Fz2左+Fz2右＝1150000N；ΣFz before adjustment = Fz2 front + Fz2 left + Fz2 right = 1150000N;
2)、步骤二、改变对左、右起落架工况载荷加载顺序，使左、右主起落架侧向载荷保持短路；2), step 2, change the load loading sequence of the left and right landing gears, so that the lateral loads of the left and right main landing gears remain short-circuited;
试验加载时，前起落架和左主起落架加载顺序不变，即首先对前起落架和左主起落架施加工况1载荷，然后施加工况2载荷，与此同时，改变右主起落加载顺序，首先施加工况2载荷，然后施加工况1载荷，使左、右主起落架侧向载荷产生短路。调整后左、右主起落架加载情况如图3和图4所示，其中工况1和工况2起落架载荷如下：During the test loading, the loading sequence of the nose landing gear and the left main landing gear remains unchanged, that is, the load of working condition 1 is first applied to the nose landing gear and the left main landing gear, and then the load of working condition 2 is applied. At the same time, the loading of the right main landing gear is changed. In sequence, the load of working condition 2 is applied first, and then the load of working condition 1 is applied, so that the lateral loads of the left and right main landing gears are short-circuited. The loading conditions of the left and right main landing gears after adjustment are shown in Fig. 3 and Fig. 4, where the loads of the landing gear in working condition 1 and working condition 2 are as follows:
工况1：Working condition 1:
前起落架：Fy1前＝-10000N，Fz1前＝50000N；Front landing gear: Fy1 front = -10000N, Fz1 front = 50000N;
左主起落架：Fy1左＝-70000N，Fz1左＝350000N；Left main landing gear: Fy1 left = -70000N, Fz1 left = 350000N;
右主起落架：Fy2右＝70000N，Fz2右＝350000N；Right main landing gear: Fy2 right=70000N, Fz2 right=350000N;
工况2：Working condition 2:
前起落架：Fy2前＝10000N，Fz2前＝50000N；Front landing gear: Fy2 front = 10000N, Fz2 front = 50000N;
左主起落架：Fy2左＝170000N，Fz2左＝750000N；Left main landing gear: Fy2 left = 170000N, Fz2 left = 750000N;
右主起落架：Fy1右＝-170000N，Fz1右＝750000N；Right main landing gear: Fy1 right = -170000N, Fz1 right = 750000N;
3)、计算加载顺序调整后全部起落架的垂向载荷总载ΣFz调整后；3), calculate the vertical load total load ΣFz of all landing gears after the adjustment of the loading sequence;
工况1：ΣFz调整后＝Fz1前+Fz1左+Fz2右＝750000N；Working condition 1: ΣFz adjusted = Fz1 front + Fz1 left + Fz2 right = 750000N;
共况2：ΣFz调整后＝Fz2前+Fz2左+Fz1右＝1550000N；Co-condition 2: ΣFzadjusted = Fz2 front + Fz2 left + Fz1 right = 1550000N;
4)、计算垂向载荷修正系数f＝ΣFz调整后/ΣFz调整前；4), calculate the vertical load correction factor f = ΣFz after adjustment /ΣFz before adjustment ;
工况1：f＝ΣFz调整后/ΣFz调整前＝0.652；Working condition 1: f = ΣFz after adjustment /ΣFz before adjustment = 0.652;
工况2：f＝ΣFz调整后/ΣFz调整前＝1.348。Working condition 2: f = ΣFz after adjustment /ΣFz before adjustment = 1.348.
5)、对全机垂向载荷进行配平；5) Trim the vertical load of the whole machine;
将机身、机翼和尾翼各个部件的垂向载荷Fzi乘以载荷修正系数f；Multiply the vertical load Fzi of each component of the fuselage, wing and empennage by the load correction factor f;
6)、除全部起落架外，消除飞机其余部件侧向载荷；6), except for all the landing gear, eliminate the side load of other parts of the aircraft;
7)、对飞机全机滚转矩Mx、全机俯仰矩My、前起落架侧向载荷Fy及全机偏航矩Mz进行配平；7) Trimming the aircraft's overall roll moment Mx, overall aircraft pitch moment My, nose landing gear lateral load Fy, and overall aircraft yaw moment Mz;
通过在左、右机翼施加垂向载荷Fz配平1来配平全机滚转矩Mx；Trim the overall machine roll torque Mx by applying vertical load Fz on the left and right wings Fztrim 1 ;
通过在前、后机身施加垂向载荷Fz配平2来配平全机俯仰矩My；Trim the whole machine pitching moment My by applying vertical load Fz trim 2 on the front and rear fuselage;
通过在前、后机身施加侧向载荷Fy配平来配平前起落架侧向载荷Fy和全机偏航矩Mz；Trim the side load Fy of the front landing gear and the yaw moment Mz of the whole aircraft by applying the side load Fytrim on the front and rear fuselages;
8)、对关键部位的疲劳裕度影响进行分析计算。8) Analyze and calculate the influence of fatigue margin on key parts.
本发明一种飞机地面侧向载荷的处理方法，在确保地面载荷主要考核部位考核准确的基础上，大大简化了机身和机翼侧向载荷的施加，缩短全机疲劳试验周期，降低试验成本。The method for processing the lateral load on the ground of an aircraft greatly simplifies the application of the lateral load on the fuselage and the wing on the basis of ensuring accurate assessment of the main assessment parts of the ground load, shortens the fatigue test period of the whole aircraft, and reduces the test cost.
最后需要指出的是：以上实施例仅用以说明本发明的技术方案，而非对其限制。尽管参照前述实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的精神和范围。Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: they can still modify the technical solutions described in the aforementioned embodiments, or perform equivalent replacements for some of the technical features; and these The modification or replacement does not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.
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| CN201710632303.9ACN107499534B (en) | 2017-07-28 | 2017-07-28 | A kind of processing method of aircraft ground side load |
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| CN201710632303.9ACN107499534B (en) | 2017-07-28 | 2017-07-28 | A kind of processing method of aircraft ground side load |
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| CN201710632303.9AActiveCN107499534B (en) | 2017-07-28 | 2017-07-28 | A kind of processing method of aircraft ground side load |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109684678A (en)* | 2018-12-04 | 2019-04-26 | 中国航空工业集团公司西安飞机设计研究所 | Full machine fatigue test multi-wheel and multi-support undercarriage fatigue load optimized treatment method |
| CN109866941A (en)* | 2019-03-28 | 2019-06-11 | 中国飞机强度研究所 | The accurate applying method of load during undercarriage large deformation following loading |
| CN110861783A (en)* | 2019-11-20 | 2020-03-06 | 中国飞机强度研究所 | Parallel fuselage course unidirectional constraint method and system |
| CN111452994A (en)* | 2020-04-22 | 2020-07-28 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN112763304A (en)* | 2020-12-23 | 2021-05-07 | 北京机电工程研究所 | Fatigue test loading spectrum forming method and device and fatigue performance testing method |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1514213A (en)* | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | On-site calibration test method and device for whole machine ground load |
| 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 |
| US20130168499A1 (en)* | 2011-10-11 | 2013-07-04 | Victor A. Grossman | Rapid store load system for aircraft and method of operation thereof |
| CN103625653A (en)* | 2013-12-04 | 2014-03-12 | 中国飞机强度研究所 | Included angle constraining method for full-scale fatigue test |
| CN104058101A (en)* | 2014-06-24 | 2014-09-24 | 中国飞机强度研究所 | Method for applying normal load under large deformation condition of wings |
| CN106240841A (en)* | 2016-07-07 | 2016-12-21 | 中国飞机强度研究所 | A kind of gear test charger |
| CN106428623A (en)* | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1514213A (en)* | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | On-site calibration test method and device for whole machine ground load |
| US20130168499A1 (en)* | 2011-10-11 | 2013-07-04 | Victor A. Grossman | Rapid store load system for aircraft and method of operation thereof |
| 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 |
| CN103625653A (en)* | 2013-12-04 | 2014-03-12 | 中国飞机强度研究所 | Included angle constraining method for full-scale fatigue test |
| CN104058101A (en)* | 2014-06-24 | 2014-09-24 | 中国飞机强度研究所 | Method for applying normal load under large deformation condition of wings |
| CN106240841A (en)* | 2016-07-07 | 2016-12-21 | 中国飞机强度研究所 | A kind of gear test charger |
| CN106428623A (en)* | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
| Title |
|---|
| 何永乐等: "航空机轮径侧向联合载荷试验及滚转试验侧向加载分析", 《航空精密制造技术》* |
| 娄锐等: "飞机起落架回转地面载荷特性研究", 《航空工程进展》* |
| 杜星等: "全机结构试验起落架随动加载技术研究", 《科学技术与工程》* |
| 范瑞娟等: "通用飞机全尺寸疲劳验证试验技术", 《航空科学技术》* |
| 谭申刚: "《大型飞机结构疲劳试验设计技术》", 30 June 2016* |
| 郭兰中等: "飞机疲劳试验工程优化方法", 《兰州工业高等专科学校学报》* |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109684678A (en)* | 2018-12-04 | 2019-04-26 | 中国航空工业集团公司西安飞机设计研究所 | Full machine fatigue test multi-wheel and multi-support undercarriage fatigue load optimized treatment method |
| CN109684678B (en)* | 2018-12-04 | 2023-04-18 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue load optimization processing method for multi-wheel multi-support undercarriage in full-machine fatigue test |
| CN109866941A (en)* | 2019-03-28 | 2019-06-11 | 中国飞机强度研究所 | The accurate applying method of load during undercarriage large deformation following loading |
| CN109866941B (en)* | 2019-03-28 | 2022-04-01 | 中国飞机强度研究所 | Accurate load application method in large deformation follow-up loading process of undercarriage |
| CN110861783A (en)* | 2019-11-20 | 2020-03-06 | 中国飞机强度研究所 | Parallel fuselage course unidirectional constraint method and system |
| CN110861783B (en)* | 2019-11-20 | 2021-05-25 | 中国飞机强度研究所 | Parallel fuselage course unidirectional constraint method and system |
| CN111452994A (en)* | 2020-04-22 | 2020-07-28 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN111452994B (en)* | 2020-04-22 | 2023-03-24 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN112763304A (en)* | 2020-12-23 | 2021-05-07 | 北京机电工程研究所 | Fatigue test loading spectrum forming method and device and fatigue performance testing method |
| CN112763304B (en)* | 2020-12-23 | 2023-11-07 | 北京机电工程研究所 | Fatigue test loading spectrum forming method and device and fatigue performance testing method |
| Publication number | Publication date |
|---|---|
| CN107499534B (en) | 2020-05-15 |
| Publication | Publication Date | Title |
|---|---|---|
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