CN105468853A - Aircraft arresting hook load spectrum compilation method - Google Patents
Aircraft arresting hook load spectrum compilation method Download PDFInfo
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- CN105468853A CN105468853A CN201510845550.8A CN201510845550A CN105468853A CN 105468853 A CN105468853 A CN 105468853A CN 201510845550 A CN201510845550 A CN 201510845550A CN 105468853 A CN105468853 A CN 105468853A
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Abstract
The invention discloses an aircraft arresting hook load spectrum compilation method, belonging to the technical field of aeronautical engineering. The method comprises the following steps of: firstly, actually measuring a plurality of arresting loads of the arresting hook and converting the arresting loads into overload; secondly, drawing a cumulative frequency curve of arresting overload, and performing maximum value correction and smoothing for the curve; finally, performing equivalent damage reducing for the corrected arresting overload distribution to light stage and heavy stage overloads through a Miner linear damage theory, obtaining 90% light arresting overload spectrum and 10% heavy arresting overload, and providing a load curve of one-time arresting. In the method provided by the invention, according to actual service condition and stress characteristic of the arresting hook, an arresting hook load spectrum compilation method is established according to an aircraft strength and stiffness specification on the basis of being according to a small amount of actual measurement data, engineering personnel is helped to perform life analysis and fatigue test verification for the arresting hook, and thus, service life of the arresting hook can be determined.
Description
Technical field
The invention belongs to aeronautical engineering technical field, be specifically related to a kind of aircraft arrestment hook loading spectrum preparation method.
Background technology
Arrester hook is contained in airplane tail group to hook when landing the hooked device that on ground or warship, check cable makes aircraft stop rapidly.Be that aircraft can realize blocking the critical component of warship, because kinetic energy when warship by aircraft is large, blocks and stop apart from short, so the load that arrester hook bears is larger.In prior art, also do not work out aircraft arrestment hook loading spectrum, in order to ensure that arrester hook is bearing the life-span under harsh load, durability analysis and torture test checking need be carried out, so the loading spectrum that establishment can represent the actual loading conditions of arrester hook is absolutely necessary to arrester hook.
Summary of the invention
In order to solve the problem, the present invention proposes a kind of aircraft arrestment hook loading spectrum preparation method, on the basis of research aircraft arrester hook mechanical characteristic, based on warship (land) measured data by a small amount of aircraft arrestment, in conjunction with ship-board aircraft strength and stiffness specification, measured data is added up, processes, finally develop arrester hook loading spectrum.
Aircraft arrestment hook loading spectrum preparation method of the present invention, is characterized in that, comprising:
S1, survey the multiple of described arrester hook and block load and be translated into overload;
S2, draw and block the cummulative frequency curve of overload, and maximal value correction and round and smooth process are carried out to curve;
S3, revised overload distribution Miner linear cumulative damage law of blocking is carried out equivalent damage conversion to light, heavy two-stage overload, obtain 90% gently block transship compose and 10% heavily block overload, and provide the curve of load once blocked.
Preferably, block blocking when load comprises aircraft landing described in and block load when warship by load and aircraft.
In such scheme preferably, blocking overload during multiple aircraft landing is averaged respectively with the overload of blocking during multiple warship, if both mean value differences are greater than threshold value, then respectively loading spectrum is worked out to aircraft landing and warship.
In such scheme preferably, described threshold value is 0.5.
, in described step S3, equivalent damage convert formula is as follows in such scheme preferably:
In formula: A
d---the equivalent number of times after conversion;
X
ai---amplitude overload at different levels;
A
i---amplitude overload occurrence number at different levels;
X
ak---the amplitude overload of the conversion level determined;
The S-N rate of curve of m---matching.
The present invention is according to the actual service condition of arrester hook and mechanical characteristic, on the basis according to a small amount of measured data, according to strength of aircraft and rigidity specifcation, establish a kind of arrester hook loading spectrum preparation method, be conducive to engineering staff and durability analysis and torture test checking are carried out to arrester hook, thus determine the serviceable life of arrester hook.
Accompanying drawing explanation
Overload cummulative frequency curve schematic diagram when Fig. 1 is the aircraft landing of a preferred embodiment of aircraft arrestment hook loading spectrum preparation method of the present invention.
Fig. 2 is the aircraft of a preferred embodiment of aircraft arrestment hook loading spectrum preparation method of the present invention overload cummulative frequency curve schematic diagram when warship.
Fig. 3 is the loading spectrum schematic diagram of a preferred embodiment of aircraft arrestment hook loading spectrum preparation method of the present invention.
Embodiment
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Aircraft arrestment hook loading spectrum preparation method of the present invention, mainly comprises the following steps:
S1, survey the multiple of described arrester hook and block load and be translated into overload;
S2, draw and block the cummulative frequency curve of overload, and maximal value correction and round and smooth process are carried out to curve;
S3, revised overload distribution Miner linear cumulative damage law of blocking is carried out equivalent damage conversion to light, heavy two-stage overload, obtain 90% gently block transship compose and 10% heavily block overload, and provide the curve of load once blocked.
Be understandable that, described overload is effect aerodynamic force aboard and the overload making a concerted effort to be called with the ratio of aircraft gravity aircraft of motor power.The size that aircraft can bear overload weighs the important parameter of air maneuver.Transship larger, aircraft stressed larger, be the safety ensureing aircraft, the overload of aircraft can not be excessive.Pilot also can be greater than one or be less than one and bear overweight and weightless because of overload in maneuvering flight.The maximum overload that pilot can bear generally can not more than 8.
In the present embodiment, through actual measurement and the relation between the landing weight that is converted to and overload peak value, and the relation between warship weight and overload peak value see the following form 1.
Table 1 blocks overload
In the present embodiment, blocking overload during multiple aircraft landing is averaged respectively with the overload of blocking during multiple warship, if both mean value differences are greater than threshold value, then respectively loading spectrum is worked out to aircraft landing and warship.Such as, described threshold value is 0.5.Upper table after providing overload form, also need to land and overload respectively calculating mean value and maximum, the minimum value of warship, last 3 row of upper table 1 are to provide.Blocking overload average of landing is n
x=3.56, maximal value is n
xmax=5.03.The overload average of blocking warship is n
x=2.69, maximal value is n
xmax=3.99.Block landing overload values to be greater than and to block warship, therefore, need to work out respectively to block and land and block warship arrester hook loading spectrum.
Afterwards, draw the overload cummulative frequency curve blocking and land with blocking warship respectively, then the overload cummulative frequency curve that blocks of actual measurement is revised.Concrete modification method is: for blocking the overload cummulative frequency curve that lands, mainly reducing maximal value, curve is carried out round and smooth process, and revised overload maximal value of blocking gets n by airplane design index
xmax=4.5.For blocking warship overload cummulative frequency curve, carry out round and smooth process.Revised overload cummulative frequency curve is shown in accompanying drawing 1 and accompanying drawing 2 respectively.It should be noted that, in Fig. 1 and Fig. 2, y-axis is overload values, and x-axis is that the number of times that overload occurs adds up, such as x=1000, y=2.2, then represent, the number of times of overload >=2.2 is 1000 times, in like manner, in Fig. 1, x=100, actual measurement y=4.7, represent that the number of times of overload >=4.7 is 100 times.Revised overload of blocking occurs that frequency is in table 2.
Table 2 is revised blocks overload
According to the regulation in specification GJB2754-96, overload will be blocked and be divided into gently, weigh two-stage, and the ratio determining light, heavy two-stage overload occurrence number is 0.9:0.1.Utilize Miner linear cumulative damage law that revised overload of blocking is carried out equivalent damage conversion to light, heavy two-stage overload.Formula is as follows:
In formula: A
d---the equivalent number of times after conversion;
X
ai---amplitude overload at different levels;
A
i---amplitude overload occurrence number at different levels;
X
ak---the amplitude overload of the conversion level determined;
The S-N rate of curve of m---matching is m=5 as calculated.
For the ratio ensureing light, the heavy two-stage overload number of times after conversion is 0.9:0.1, through tentative calculation, the 1st ~ 22nd grade of overload of being blocked land is toward n
xafter=3.5 grades of upper conversions, number of times is about 900 times.By the 23rd ~ 24th grade of overload toward n
xafter=4.5 grades of upper conversions, number of times is about 100 times.So, following two ranks can be divided into by blocking overload:
N
x=3.5, once blocking frequency of occurrence is 0.9 time.
N
x=4.5, once blocking frequency of occurrence is 0.1 time.
In like manner, the 1st ~ 9th grade of overload of being blocked by aircraft carrier is toward n
xafter=2.5 grades of upper conversions, number of times is about 900 times.By the 10th ~ 15th grade of overload toward n
xafter=3.5 grades of upper conversions, number of times is about 100 times.So, following two ranks can be divided into by blocking overload:
N
x=2.5, once blocking frequency of occurrence is 0.9 time.
N
x=3.5, once blocking frequency of occurrence is 0.1 time.
According to specification GJB2754-96, for 90% block warship, lateral overload n
z=0.6, other 10% block warship, lateral overload n
z=1.0.During loading spectrum arrangement, consider various factors, blocking with 200 times is 1 spectrum block, and arrangement is in table 3.
The arrangement of table 3 arrester hook loading spectrum
Respectively course is transshipped n
xwith lateral overload n
znamely course load and the side load of arrester hook is obtained after being multiplied by the weight of aircraft, P is the making a concerted effort of course load and side load on arrester hook, after obtaining and making a concerted effort, and specification more, produce the loading spectrum of practical operation, the arrester hook loading spectrum typically once blocked is shown in accompanying drawing 3.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (5)
1. an aircraft arrestment hook loading spectrum preparation method, is characterized in that, comprising:
S1, survey the multiple of described arrester hook and block load and be translated into overload;
S2, draw and block the cummulative frequency curve of overload, and maximal value correction and round and smooth process are carried out to curve;
S3, revised overload distribution Miner linear cumulative damage law of blocking is carried out equivalent damage conversion to light, heavy two-stage overload, obtain 90% gently block transship compose and 10% heavily block overload, and provide the curve of load once blocked.
2. aircraft arrestment hook loading spectrum preparation method as claimed in claim 1, is characterized in that: described in block blocking when load comprises aircraft landing and block load when warship by load and aircraft.
3. aircraft arrestment hook loading spectrum preparation method as claimed in claim 2, it is characterized in that: blocking overload during multiple aircraft landing is averaged respectively with the overload of blocking during multiple warship, if both are greater than threshold value at mean value difference, then respectively loading spectrum is worked out to aircraft landing and warship.
4. aircraft arrestment hook loading spectrum preparation method as claimed in claim 1, is characterized in that: described threshold value is 0.5.
5. aircraft arrestment hook loading spectrum preparation method as claimed in claim 1, it is characterized in that: in described step S3, equivalent damage convert formula is as follows:
In formula: A
d---the equivalent number of times after conversion;
X
ai---amplitude overload at different levels;
A
i---amplitude overload occurrence number at different levels;
X
ak---the amplitude overload of the conversion level determined;
The S-N rate of curve of m---matching.
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| CN201510845550.8A CN105468853A (en) | 2015-11-26 | 2015-11-26 | Aircraft arresting hook load spectrum compilation method |
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| CN201510845550.8A CN105468853A (en) | 2015-11-26 | 2015-11-26 | Aircraft arresting hook load spectrum compilation method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106446809A (en) * | 2016-09-09 | 2017-02-22 | 南京航空航天大学 | Aeroengine load spectrum filtering method based on rain-flow counting method |
| CN106529094A (en) * | 2016-11-30 | 2017-03-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Typical flight action-based aircraft severe load spectrum compilation method |
| CN113609583A (en) * | 2021-08-01 | 2021-11-05 | 辽宁通用航空研究院 | Flight load spectrum compiling method |
| CN113704875A (en) * | 2021-08-03 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Undercarriage damage assessment method under condition of random takeoff and landing weight |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102003979A (en) * | 2009-09-01 | 2011-04-06 | 中国农业机械化科学研究院 | System and method for reading load spectrum actual measuring experimental data |
| CN102680221A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test method for full-aircraft main operating system of aircraft |
| EP2645055A1 (en) * | 2012-03-27 | 2013-10-02 | Alenia Aermacchi S.p.A. | Method for evaluating the structural compatibility of an aircraft for use on rough runways |
| CN103984815A (en) * | 2014-05-12 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Multi-type information representative landing load spectrum compilation method |
-
2015
- 2015-11-26 CN CN201510845550.8A patent/CN105468853A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102003979A (en) * | 2009-09-01 | 2011-04-06 | 中国农业机械化科学研究院 | System and method for reading load spectrum actual measuring experimental data |
| EP2645055A1 (en) * | 2012-03-27 | 2013-10-02 | Alenia Aermacchi S.p.A. | Method for evaluating the structural compatibility of an aircraft for use on rough runways |
| CN102680221A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test method for full-aircraft main operating system of aircraft |
| CN103984815A (en) * | 2014-05-12 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Multi-type information representative landing load spectrum compilation method |
Non-Patent Citations (1)
| Title |
|---|
| 刘克格 等: "飞机起落架载荷谱实测与编制方法", 《航空学报》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106446809A (en) * | 2016-09-09 | 2017-02-22 | 南京航空航天大学 | Aeroengine load spectrum filtering method based on rain-flow counting method |
| CN106529094A (en) * | 2016-11-30 | 2017-03-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Typical flight action-based aircraft severe load spectrum compilation method |
| CN113609583A (en) * | 2021-08-01 | 2021-11-05 | 辽宁通用航空研究院 | Flight load spectrum compiling method |
| CN113609583B (en) * | 2021-08-01 | 2024-01-09 | 辽宁通用航空研究院 | Flight load spectrum compiling method |
| CN113704875A (en) * | 2021-08-03 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Undercarriage damage assessment method under condition of random takeoff and landing weight |
| CN113704875B (en) * | 2021-08-03 | 2023-07-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Landing gear damage assessment method under condition of random take-off and landing weight |
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Application publication date: 20160406 |
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