CN107499534A - A kind of processing method of aircraft floor lateral load - Google Patents
A kind of processing method of aircraft floor lateral load Download PDFInfo
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- CN107499534A CN107499534A CN201710632303.9A CN201710632303A CN107499534A CN 107499534 A CN107499534 A CN 107499534A CN 201710632303 A CN201710632303 A CN 201710632303A CN 107499534 A CN107499534 A CN 107499534A
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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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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
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Abstract
The invention discloses a kind of processing method of aircraft floor lateral load, belongs to aircraft fatigue experiment field.Including：Step 1: when calculating original loading sequence, the vertical load of whole undercarriages always carries Σ FBefore z adjustment；Step 2: changing to left and right undercarriage operating loading loading sequence, left and right main starting is fallen frame lateral load and keep short circuit；Step 3: the vertical load for calculating whole undercarriages after loading sequence adjustment always carries Σ FAfter z adjustment；Step 4: calculate vertical load correction factor f；Step 5: to full machine vertical load trim；Step 6: in addition to whole undercarriages, aircraft remaining part lateral load is eliminated；Step 7: machine rolling square Mx complete to aircraft, full machine pitching square My, nose-gear lateral load Fy and the driftage square Mz trims of full machine；Step 8: the tired nargin of key position is influenceed to calculate.The present invention is adjusted to the applying mode of load to ground side on the basis of ensuring that the position examines accurate and remaining position to occur without premature degradation, shortens the test period.
Description
Technical field
The invention belongs to aircraft fatigue experimental technique field, and in particular to a kind of processing side of aircraft floor lateral load
Method.
Background technology
The full machine fatigue test of aircaft configuration is to verify that can body structural life-time meet the important means of requirement, design
When personnel formulate experiment embodiment, substantial amounts of theoretical analysis and calculation is done, it is ensured that experiment loading can not only really simulate winged
The stress of machine, it is also contemplated that the problems such as experiment implement scale, test period.
For ground turning condition, undercarriage lateral load is larger, the lateral load on corresponding fuselage and wing
Lotus is also larger.Due to wing structure feature, lateral load is not easy to apply, and is typically transferred to fuselage and is applied, and this will cause machine
Body lateral load is excessive.To meet the application of fuselage lateral load, and part overloading problem is occurred without, it is necessary in fuselage both sides cloth
Multiple load(ing) points are put, this will greatly increase the quantity of full machine load(ing) point, extend the test period.
The content of the invention
The purpose of the present invention：In order to solve the above problems, the present invention proposes a kind of processing of aircraft floor lateral load
Method, on the basis of ensuring that the position examines accurate and remaining position to occur without premature degradation, to aircaft configuration ground side
It is adjusted to the applying mode of load, accelerates experiment progress, shorten the test period.
Technical scheme：A kind of processing method of aircraft floor lateral load, comprises the following steps；
Step 1: when calculating original loading sequence, the vertical load of whole undercarriages always carries Σ FBefore z adjustment；
Left and right main starting falls frame while applies the load of operating mode 1, then applies the load of operating mode 2, or left and right main landing gear simultaneously
Apply the load of operating mode 2 simultaneously, then apply the load of operating mode 1 simultaneously；
Left and right undercarriage, which applies after operating mode 1 and operating mode 2 and calculates the vertical loads of whole undercarriages, always carries Σ FBefore z adjustment；
Step 2: changing to left and right undercarriage operating loading loading sequence, left and right main starting is set to fall the holding of frame lateral load
Short circuit；
Step 3: the vertical load for calculating whole undercarriages after loading sequence adjustment always carries Σ FAfter z adjustment；
Step 4: calculate vertical load correction factor f；
F=Σ FAfter z adjustment/ΣFBefore z adjustment
Step 5: trim is carried out to full machine vertical load；
By the vertical load F of fuselage, wing and empennage all partsziIt is multiplied by Load correction factor f；
Step 6: in addition to whole undercarriages, aircraft remaining part lateral load is eliminated；
Step 7: machine rolling square Mx complete to aircraft, full machine pitching square My, nose-gear lateral load Fy and full machine driftage square
Mz carries out trim；
By applying vertical load F in left and right wingZ trims 1Carry out the full machine rolling square Mx of trim；
By applying vertical load F in forward and backward fuselageZ trims 2Carry out the full machine pitching square My of trim；
By applying lateral load F in forward and backward fuselageY trimsCome trim nose-gear lateral load Fy and full machine driftage square
Mz；
Step 8: the tired nargin of key position is influenceed to carry out analysis calculating.
Preferably, in the step 2, when experiment loads, nose-gear and left main loading sequence are constant, i.e., first
The load of operating mode 1 first is applied to nose-gear and left main, then applies the load of operating mode 2, at the same time, changes right master and rise and fall
Loading sequence, apply the load of operating mode 2 first, then apply the load of operating mode 1, left and right main starting is fallen frame lateral load and produce short circuit.
Preferably, during experiment loading, nose-gear and starboard main landing gear loading sequence are constant, i.e., first to nose-gear and
Starboard main landing gear applies the load of operating mode 1, then applies the load of operating mode 2, at the same time, changes left master and rises and falls loading sequence, first
Apply the load of operating mode 2, then apply the load of operating mode 1, left and right main starting is fallen frame lateral load and produce short circuit.
Preferably, in the step 1, whole undercarriages include：Nose-gear, left undercarriage and right landing gear.
Preferably, the operating mode 1 and operating mode 2 are respectively to turn left and turn right.
The advantageous effects of technical solution of the present invention：A kind of processing method of aircraft floor lateral load of the present invention, it is main
Intensity of the position for undercarriage and body connection structure is examined, is ensuring that position examination is accurate and remaining position occurs without
On the basis of premature degradation, the applying mode of aircaft configuration ground lateral load is adjusted, accelerates experiment progress, is shortened
Test period.
Brief description of the drawings
Fig. 1 in the prior art ground turn left when left and right undercarriage load load condition schematic diagram；
Fig. 2 in the prior art ground turn right when left and right undercarriage load load condition schematic diagram；
Fig. 3 adds for a kind of starboard main landing gear of a preferred embodiment of the processing method of aircraft floor lateral load of the present invention
After load order adjusts, left and right main starting falls the load condition schematic diagram of frame when ground is turned left；
Fig. 4 adds for a kind of starboard main landing gear of a preferred embodiment of the processing method of aircraft floor lateral load of the present invention
After load order adjusts, left and right main starting falls the load condition schematic diagram of frame when ground is turned right.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
Part of the embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
A kind of processing method of aircraft floor lateral load, comprises the following steps；
1) when, calculating original loading sequence, the vertical load of whole undercarriages always carries Σ FBefore z adjustment；
The lateral load working condition in ground includes left-hand bend operating mode 1 and right-hand bend operating mode 2, nose-gear under original loading sequence,
Left undercarriage and right landing gear apply the load of left-hand bend operating mode 1 first, then apply the load of right-hand bend operating mode 2, wherein turning left
The load of operating mode 1 and the load of right-hand bend operating mode 2 are as follows：
Left-hand bend operating mode 1：
Nose-gear：Fy1Before=- 10000N, Fz1Before=50000N；
Left main：Fy1A left side=- 70000N, Fz1A left side=350000N；
Starboard main landing gear：Fy2The right side=70000N, Fz2The right side=350000N；
ΣFBefore z adjustment=Fz1Before+Fz1A left side+Fz1The right side=1150000N；
Right-hand bend operating mode 2：
Nose-gear：Fy2Before=10000N, Fz2Before=50000N；
Left main：Fy2A left side=170000N, Fz2A left side=750000N；
Starboard main landing gear：Fy1The right side=- 170000N, Fz1The right side=750000N；
ΣFBefore z adjustment=Fz2Before+Fz2A left side+Fz2The right side=1150000N；
2), Step 2: changing to left and right undercarriage operating loading loading sequence, left and right main starting is made to fall frame lateral load guarantor
Hold short circuit；
During experiment loading, nose-gear and left main loading sequence are constant, i.e., nose-gear and left master are risen first
Fall frame and apply the load of operating mode 1, then apply the load of operating mode 2, at the same time, change right master and rise and fall loading sequence, apply work first
The load of condition 2, then apply the load of operating mode 1, left and right main starting is fallen frame lateral load and produce short circuit.Adjust rear left and right main landing gear
As shown in Figure 3 and Figure 4, wherein operating mode 1 and the landing-gear load of operating mode 2 is as follows for load condition：
Operating mode 1：
Nose-gear：Fy1Before=- 10000N, Fz1Before=50000N；
Left main：Fy1A left side=- 70000N, Fz1A left side=350000N；
Starboard main landing gear：Fy2The right side=70000N, Fz2The right side=350000N；
Operating mode 2：
Nose-gear：Fy2Before=10000N, Fz2Before=50000N；
Left main：Fy2A left side=170000N, Fz2A left side=750000N；
Starboard main landing gear：Fy1The right side=- 170000N, Fz1The right side=750000N；
3), the vertical load for calculating whole undercarriages after loading sequence adjusts always carries Σ FAfter z adjustment；
Operating mode 1：ΣFAfter z adjustment=Fz1Before+Fz1A left side+Fz2The right side=750000N；
Condition 2 altogether：ΣFAfter z adjustment=Fz2Before+Fz2A left side+Fz1The right side=1550000N；
4) vertical load correction factor f=Σ F, are calculatedAfter z adjustment/ΣFBefore z adjustment；
Operating mode 1：F=Σ FAfter z adjustment/ΣFBefore z adjustment=0.652；
Operating mode 2：F=Σ FAfter z adjustment/ΣFBefore z adjustment=1.348.
5) trim, is carried out to full machine vertical load；
By the vertical load F of fuselage, wing and empennage all partsziIt is multiplied by Load correction factor f；
6), in addition to whole undercarriages, aircraft remaining part lateral load is eliminated；
7), machine rolling square Mx complete to aircraft, full machine pitching square My, nose-gear lateral load Fy and full machine driftage square Mz enter
Row trim；
By applying vertical load F in left and right wingZ trims 1Carry out the full machine rolling square Mx of trim；
By applying vertical load F in forward and backward fuselageZ trims 2Carry out the full machine pitching square My of trim；
By applying lateral load F in forward and backward fuselageY trimsCome trim nose-gear lateral load Fy and full machine driftage square
Mz；
8), the tired nargin of key position is influenceed to carry out analysis calculating.
A kind of processing method of aircraft floor lateral load of the present invention, ensuring that it is accurate that landing load mainly examines position to examine
Really on the basis of, enormously simplify the application of fuselage and wing lateral load, shorten the full machine fatigue test cycle, reduce experiment into
This.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (5)
1. a kind of processing method of aircraft floor lateral load, it is characterised in that comprise the following steps：
Step 1: when calculating original loading sequence, the vertical load of whole undercarriages always carries Σ FBefore z adjustment；
Left and right main starting falls frame while applies the load of operating mode 1, then applies the load of operating mode 2 simultaneously, or left and right main landing gear is simultaneously
Apply the load of operating mode 2, then apply the load of operating mode 1 simultaneously；
Left and right undercarriage, which applies after operating mode 1 and operating mode 2 and calculates the vertical loads of whole undercarriages, always carries Σ FBefore z adjustment；
Step 2: changing to left and right undercarriage operating loading loading sequence, left and right main starting is fallen frame lateral load and keep short circuit；
Step 3: the vertical load for calculating whole undercarriages after loading sequence adjustment always carries Σ FAfter z adjustment；
Step 4: calculate vertical load correction factor f；
F=Σ FAfter z adjustment/ΣFBefore z adjustment
Step 5: trim is carried out to full machine vertical load；
By the vertical load F of fuselage, wing and empennage all partsziIt is multiplied by Load correction factor f；
Step 6: in addition to whole undercarriages, aircraft remaining part lateral load is eliminated；
Step 7: machine rolling square Mx complete to aircraft, full machine pitching square My, nose-gear lateral load Fy and full machine driftage square Mz enter
Row trim；
By applying vertical load F in left and right wingZ trims 1Carry out the full machine rolling square Mx of trim；
By applying vertical load F in forward and backward fuselageZ trims 2Carry out the full machine pitching square My of trim；
By applying lateral load F in forward and backward fuselageY trimsCome trim nose-gear lateral load Fy and full machine driftage square Mz；
Step 8: the tired nargin of key position is influenceed to carry out analysis calculating.
2. the processing method of aircraft floor lateral load as claimed in claim 1, it is characterised in that：In the step 2, examination
When testing loading, nose-gear and left main loading sequence are constant, i.e., apply work to nose-gear and left main first
The load of condition 1, then apply the load of operating mode 2, at the same time, change right master and rise and fall loading sequence, apply the load of operating mode 2 first, so
The after-applied load of operating mode 1, left and right main starting is fallen frame lateral load and produce short circuit.
3. the processing method of aircraft floor lateral load as claimed in claim 1, it is characterised in that：In the step 2, examination
When testing loading, nose-gear and starboard main landing gear loading sequence are constant, i.e., apply work to nose-gear and starboard main landing gear first
The load of condition 1, then apply the load of operating mode 2, at the same time, change left master and rise and fall loading sequence, apply the load of operating mode 2 first, so
The after-applied load of operating mode 1, left and right main starting is fallen frame lateral load and produce short circuit.
4. the processing method of aircraft floor lateral load as claimed in claim 1, it is characterised in that：In the step 1, institute
Stating whole undercarriages includes：Nose-gear, left undercarriage and right landing gear.
5. the processing method of aircraft floor lateral load as claimed in claim 1, it is characterised in that：The operating mode 1 and operating mode 2
Respectively turn left and turn right.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710632303.9A CN107499534B (en) | 2017-07-28 | 2017-07-28 | Method for processing airplane ground side load |
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| CN201710632303.9A CN107499534B (en) | 2017-07-28 | 2017-07-28 | Method for processing airplane ground side load |
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| 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 |
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| 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 |
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| 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 |
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| 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 |
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