CN107499534B - Method for processing airplane ground side load - Google Patents

Method for processing airplane ground side load Download PDF

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Publication number
CN107499534B
CN107499534B CN201710632303.9A CN201710632303A CN107499534B CN 107499534 B CN107499534 B CN 107499534B CN 201710632303 A CN201710632303 A CN 201710632303A CN 107499534 B CN107499534 B CN 107499534B
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load
landing gear
working condition
undercarriage
loads
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CN107499534A (en
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王亚芳
王新波
闵强
秦剑波
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Xian Aircraft Design and Research Institute of AVIC
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Xian Aircraft Design and Research Institute of AVIC
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems

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  • Manufacturing & Machinery (AREA)
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  • Aviation & Aerospace Engineering (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
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Abstract

The invention discloses a method for processing a ground side load of an airplane, and belongs to the field of airplane fatigue tests. The method comprises the following steps: step one, calculating the vertical load total load sigma F of all landing gears during the original loading sequenceBefore z adjustment(ii) a Changing the loading sequence of the working condition loads of the left main undercarriage and the right main undercarriage to keep the side loads of the left main undercarriage and the right main undercarriage short-circuited; step three, calculating the vertical load total load sigma F of all the landing gears after the loading sequence is adjustedAfter z is adjusted(ii) a Step four, calculating a vertical load correction coefficient f; step five, balancing the vertical load of the whole machine; sixthly, eliminating side loads of other parts of the airplane except all the undercarriage; step seven, balancing the rolling torque Mx, the pitching moment My, the side load Fy of the nose landing gear and the yawing moment Mz of the airplane; and step eight, calculating the influence of the fatigue margin of the key part. According to the invention, on the basis of ensuring that the examination of the part is accurate and the rest parts are not damaged in advance, the application mode of the ground side load is adjusted, and the test period is shortened.

Description

Method for processing airplane ground side load
Technical Field
The invention belongs to the technical field of airplane fatigue tests, and particularly relates to a method for processing airplane ground side loads.
Background
The airplane structure full-airplane fatigue test is an important means for verifying whether the service life of an airplane body structure can meet the use requirement, and a designer needs to do a large amount of theoretical analysis and calculation when making a test implementation scheme, so that the stress state of the airplane can be truly simulated by test loading, and the problems of test implementation scale, test period and the like are also considered.
For the ground turning working condition, the side load of the landing gear is larger, and the side load on the corresponding fuselage and wing is also larger. Due to the structural characteristics of the wings, side loads are not easy to apply, and are usually transferred to the fuselage for application, which causes the fuselage side loads to be overlarge. In order to meet the requirement of applying lateral loads to the machine body and avoid the problem of local overload, a plurality of loading points need to be arranged on two sides of the machine body, so that the number of the loading points of the whole machine is greatly increased, and the test period is prolonged.
Disclosure of Invention
The purpose of the invention is as follows: in order to solve the problems, the invention provides a method for processing the ground side load of the airplane, which adjusts the application mode of the ground side load of the airplane structure on the basis of ensuring that the assessment of the part is accurate and the rest parts are not damaged in advance, accelerates the test progress and shortens the test period.
The technical scheme of the invention is as follows: a method for processing the ground side load of an airplane comprises the following steps;
step one, calculating the vertical load total load sigma F of all landing gears during the original loading sequenceBefore z adjustment；
The left main undercarriage and the right main undercarriage simultaneously apply a working condition first load and then simultaneously apply a working condition second load, or the left main undercarriage and the right main undercarriage simultaneously apply a working condition second load and then simultaneously apply a working condition first load;
after the left main undercarriage and the right main undercarriage are subjected to the first working condition and the second working condition, calculating the vertical load total sigma F of all the undercarriagesBefore z adjustment；
Changing the loading sequence of the working condition loads of the left main undercarriage and the right main undercarriage to keep the side loads of the left main undercarriage and the right main undercarriage short-circuited;
step three, calculating the vertical load total load sigma F of all the landing gears after the loading sequence is adjustedAfter z is adjusted；
Step four, calculating a vertical load correction coefficient f;
f＝ΣFafter z is adjusted/ΣFBefore z adjustment
Step five, balancing the vertical load of the whole machine;
vertical orientation of fuselage, wing and empennage partsLoad FziMultiplying by a load correction factor f;
sixthly, eliminating side loads of other parts of the airplane except all the undercarriage;
step seven, carrying out balancing on the rolling torque Mx, the pitching moment My, the side load Fy of the nose landing gear and the yawing moment Mz of the airplane;
by applying vertical loads F to the left and right wingsz trim 1To trim the full rolling torque Mx;
by applying vertical loads F to the front and rear fuselagesz trim 2To trim the full-aircraft pitch moment My;
by applying side loads F to the front and rear fuselagey-trimTo trim the nose gear side load Fy and the full machine yaw moment Mz;
and step eight, analyzing and calculating the fatigue margin influence of the key parts.
Preferably, in the second step, during test loading, the loading sequence of the nose landing gear and the left main landing gear is unchanged, that is, firstly, a working condition first load is applied to the nose landing gear and the left main landing gear, then, a working condition second load is applied, and meanwhile, the loading sequence of the right main landing gear is changed, and firstly, a working condition second load is applied, then, a working condition first load is applied, so that the lateral loads of the left main landing gear and the right main landing gear are short-circuited.
Preferably, during test loading, the loading sequence of the nose landing gear and the right main landing gear is unchanged, namely, firstly, a working condition first load is applied to the nose landing gear and the right main landing gear, then, a working condition second load is applied, meanwhile, the loading sequence of the left main landing gear is changed, firstly, the working condition second load is applied, then, the working condition first load is applied, and the lateral loads of the left main landing gear and the right main landing gear are enabled to generate short circuit.
Preferably, in the first step, the entire landing gear includes: a nose landing gear, a left main landing gear and a right main landing gear.
Preferably, the first operating condition and the second operating condition are left turning and right turning respectively.
The technical scheme of the invention has the beneficial technical effects that: according to the method for processing the ground side load of the airplane, the strength of the connection structure of the undercarriage and the airplane body is mainly checked, the application mode of the ground side load of the airplane structure is adjusted on the basis of ensuring that the check of the part is accurate and the rest parts are not damaged in advance, the test progress is accelerated, and the test period is shortened.
Drawings
FIG. 1 is a schematic view of the load loading of left and right main landing gears during a left turn of the ground in the prior art;
FIG. 2 is a schematic view of the load loading of left and right main landing gears during a right turn on the ground in the prior art;
FIG. 3 is a schematic diagram illustrating the loading of the left and right main landing gears during a left turn on the ground after the right main landing gear loading sequence is adjusted according to a preferred embodiment of the method for processing the ground side load of the aircraft;
fig. 4 is a schematic view of the loading conditions of the left and right main landing gears when the ground turns right after the right main landing gear loading sequence is adjusted according to a preferred embodiment of the method for processing the ground side load of the aircraft.
Detailed Description
In order to make the implementation objects, 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 with reference to the accompanying 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 only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
A method for processing the ground side load of an airplane comprises the following steps;
1) and calculating the vertical load total load Sigma F of all the landing gears in the original loading sequenceBefore z adjustment；
The ground side load working condition comprises a left turning working condition I and a right turning working condition II, the front undercarriage, the left main undercarriage and the right main undercarriage under the original loading sequence firstly apply a left turning working condition I load, and then apply a right turning working condition II load, wherein the left turning working condition I load and the right turning working condition II load are as follows:
the first left-turn working condition is as follows:
a nose landing gear: fy1pre-10000N, Fz1pre-50000N;
left main landing gear: fy1left-70000N, Fz1Left 350000N;
right main landing gear: fy1D 170000N, Fz1Right 750000N;
ΣFbefore z adjustment＝Fz1Front + Fz1Left + Fz11150000N on right;
and a right turning working condition II:
a nose landing gear: fy2Former 10000N, Fz2pre-50000N;
left main landing gear: fy2170000N, Fz2Left 750000N;
right main landing gear: fy2Fz 70000N2Right 350000N;
ΣFbefore z adjustment＝Fz2Front + Fz2Left + Fz21150000N on right;
2) changing the loading sequence of the working condition loads of the left main undercarriage and the right main undercarriage to keep the side loads of the left main undercarriage and the right main undercarriage short-circuited;
during test loading, the loading sequence of the nose landing gear and the left main landing gear is unchanged, namely, a first working condition load is applied to the nose landing gear and the left main landing gear, then a second working condition load is applied, meanwhile, the loading sequence of the right main landing gear is changed, the second working condition load is applied firstly, then the first working condition load is applied, and the lateral loads of the left main landing gear and the right main landing gear are short-circuited. The adjusted rear left and right main landing gear loading conditions are shown in fig. 3 and 4, where the first and second operating condition landing gear loads are as follows:
the working condition I is as follows:
a nose landing gear: fy1pre-10000N, Fz1pre-50000N;
left main landing gear: fy1left-70000N, Fz1Left 350000N;
right main landing gear: fy2Fz 70000N2Right 350000N;
working conditions are as follows:
a nose landing gear: fy2Former 10000N, Fz2pre-50000N;
left main landing gear: fy2170000N, Fz2Left 750000N;
right main landing gear: fy1D 170000N, Fz1Right 750000N;
3) calculating the total vertical load sigma F of all the landing gears after the loading sequence is adjustedAfter z is adjusted；
The working condition I is as follows: sigma FAfter z is adjusted＝Fz1Front + Fz1Left + Fz2Right 750000N;
working conditions are as follows: sigma FAfter z is adjusted＝Fz2Front + Fz2Left + Fz11550000N on right;
4) and calculating a vertical load correction coefficient F ═ Sigma FAfter z is adjusted/ΣFBefore z adjustment；
The working condition I is as follows: f ═ Σ FAfter z is adjusted/ΣFBefore z adjustment＝0.652；
Working conditions are as follows: f ═ Σ FAfter z is adjusted/ΣFBefore z adjustment＝1.348。
5) Balancing the vertical load of the whole machine;
vertical loading F of fuselage, wing and empennage partsziMultiplying by a load correction factor f;
6) except all landing gears, the side load of other parts of the airplane is eliminated;
7) balancing the full-aircraft rolling torque Mx, the full-aircraft pitching moment My, the side load Fy of the nose landing gear and the full-aircraft yawing moment Mz of the airplane;
by applying vertical loads F to the left and right wingsz trim 1To trim the full rolling torque Mx;
by applying vertical loads F to the front and rear fuselagesz trim 2To trim the full-aircraft pitch moment My;
by applying side loads F to the front and rear fuselagey-trimTo trim the nose gear side load Fy and the full machine yaw moment Mz;
8) and analyzing and calculating the influence of the fatigue margin of the key part.
The method for processing the ground side load of the airplane greatly simplifies the application of the side load of the airplane body and the airplane wing, shortens the fatigue test period of the whole airplane and reduces the test cost on the basis of ensuring the accurate examination of the main examination part of the ground load.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (5)

1. A method for processing the ground side load of an airplane is characterized by comprising the following steps:
step one, calculating the vertical load total load sigma F of all landing gears during the original loading sequencez adjustmentFront side；
The left main undercarriage and the right main undercarriage simultaneously apply a working condition first load and then simultaneously apply a working condition second load, or the left main undercarriage and the right main undercarriage simultaneously apply a working condition second load and then simultaneously apply a working condition first load;
after the left main undercarriage and the right main undercarriage are subjected to the first working condition and the second working condition, calculating the vertical load total sigma F of all the undercarriagesBefore z adjustment；
Changing the loading sequence of the working condition loads of the left main undercarriage and the right main undercarriage to keep the side loads of the left main undercarriage and the right main undercarriage short-circuited;
step three, calculating the vertical load total load sigma F of all the landing gears after the loading sequence is adjustedAfter z is adjusted；
Step four, calculating a vertical load correction coefficient f;
f＝ΣFafter z is adjusted/ΣFBefore z adjustment
Step five, balancing the vertical load of the whole machine;
vertical loading F of fuselage, wing and empennage partsziMultiplying by a load correction factor f;
sixthly, eliminating side loads of other parts of the airplane except all the undercarriage;
step seven, carrying out balancing on the rolling torque Mx, the pitching moment My, the side load Fy of the nose landing gear and the yawing moment Mz of the airplane;
by applying vertical loads F to the left and right wingsz trim 1To trim the full rolling torque Mx;
by applying vertical loads F to the front and rear fuselagesz trim 2To trim the full-aircraft pitch moment My;
by applying side loads F to the front and rear fuselagey-trimTo trim the nose gear side load Fy and the full machine yaw moment Mz;
and step eight, analyzing and calculating the fatigue margin influence of the key parts.
2. A method of handling aircraft ground side loads according to claim 1, wherein: in the second step, during test loading, the loading sequence of the nose landing gear and the left main landing gear is unchanged, namely, firstly, a working condition first load is applied to the nose landing gear and the left main landing gear, then a working condition second load is applied, meanwhile, the loading sequence of the right main landing gear is changed, firstly, the working condition second load is applied, then, the working condition first load is applied, and the lateral loads of the left main landing gear and the right main landing gear are caused to generate short circuit.
3. A method of handling aircraft ground side loads according to claim 1, wherein: in the second step, during test loading, the loading sequence of the nose landing gear and the right main landing gear is unchanged, namely, firstly, a working condition first load is applied to the nose landing gear and the right main landing gear, then a working condition second load is applied, meanwhile, the loading sequence of the left main landing gear is changed, firstly, the working condition second load is applied, then, the working condition first load is applied, and the lateral loads of the left main landing gear and the right main landing gear are short-circuited.
4. A method of handling aircraft ground side loads according to claim 1, wherein: in the first step, the entire landing gear includes: a nose landing gear, a left main landing gear and a right main landing gear.
5. A method of handling aircraft ground side loads according to claim 1, wherein: the working condition I and the working condition II are respectively a left turn and a right turn.
CN201710632303.9A 2017-07-28 2017-07-28 Method for processing airplane ground side load Active CN107499534B (en)

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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
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
CN111452994B (en) * 2020-04-22 2023-03-24 中国飞机强度研究所 Aircraft nose landing gear supporting device
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

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