CN105836155B - A kind of aircraft structure strength tests double floor beam loading device - Google Patents
A kind of aircraft structure strength tests double floor beam loading device Download PDFInfo
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- CN105836155B CN105836155B CN201610156967.8A CN201610156967A CN105836155B CN 105836155 B CN105836155 B CN 105836155B CN 201610156967 A CN201610156967 A CN 201610156967A CN 105836155 B CN105836155 B CN 105836155B
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Abstract
The present invention relates to aircraft structure strength experiment loading technique field, double floor beam loading device is tested more particularly to a kind of aircraft structure strength.Aircraft structure strength tests double floor beam loading device, including：Loader；Load crossbeam；Main loading rod assembly, act on loading crossbeam；Two combining leverages, the bottom at loading crossbeam both ends are connected by connecting the combining leverage of monaural and corresponding end respectively；Two floor level beam charging assemblies, are connected with combining leverage and floor level；Two power transmission components, are connected with combining leverage；Two cargo deck beam charging assemblies, are connected with power transmission component and cargo deck.The aircraft structure strength experiment double floor beam loading device of the present invention, floor level beam and cargo deck beam can be loaded simultaneously, so as to adapt to the loading demand of novel large passenger plane bilayer engine room floor beam, the intensity of cabin joist and dependency structure can fully be verified so that result of the test is more accurate, more efficient effect.
Description
Technical field
The present invention relates to aircraft structure strength experiment loading technique field, tested more particularly to a kind of aircraft structure strength
Double floor beam loading device.
Background technology
, it is necessary to simulate the passenger-cargo load of cabin and fuselage is pneumatic in current complete aircraft structural static/fatigue test
Inertial load is loaded.Generally this fractional load is fully transferred to out of my cabin, paste by fuselage skin in conventional experiment
The means such as rubberized tape are loaded, can not although this simplified processing does not interfere with the strength modification of fuselage main force support structure
Fuselage interior structural bearing characteristic accurately is obtained, have ignored engine room floor beam and the strength modification of related support structure.Also have one
A little experiments are loaded directly into cabin individual layer joist, if but loading it mechanism and being directly in use to double-deck engine room structure
In aircraft structure test, it may be difficult to avoid interfering between load maintainer, while increase excessive engine opening, to full-scale
The precision and efficiency of aircraft structure test adversely affect.
The content of the invention
It is an object of the invention to provide a kind of aircraft structure strength to test double floor beam loading device, at least to solve
Existing experiment loading unit test accuracy, the problem of efficiency is low.
The technical scheme is that：
A kind of aircraft structure strength tests double floor beam loading device, including：
Crossbeam is loaded, positioned at the top of floor level and cargo deck；
Main loading rod assembly, act on the loading crossbeam, the loading crossbeam is applied for controllably vertical
In the loading force of the floor level；
Loader, for applying the loading force to the loading crossbeam；
Two combining leverages, using the midpoint of the loading crossbeam axis as origin, it is symmetricly set on the loading crossbeam two
Bottom is held, and two combining leverages are parallel with the loading crossbeam, the bottom at the loading crossbeam both ends passes through respectively
The combining leverage for connecting monaural and corresponding end connects；
Two floor level beam charging assemblies, using the midpoint of the loading crossbeam axis as origin, it is symmetricly set on described
Crossbeam both ends end is loaded, positioned at the top and the one of the combining leverage of the floor level beam charging assembly of same one end
End is fixedly connected, and the bottom of each floor level beam charging assembly is fixedly attached to the floor level of corresponding end
Upper surface；
Two power transmission components, set using the midpoint of the loading crossbeam axis as origin symmetry, positioned at the institute of same one end
The top end for stating power transmission component is respectively fixedly connected with to the other end bottom of the combining leverage；
Two cargo deck beam charging assemblies, set using the midpoint of the loading crossbeam axis as origin symmetry, Mei Gesuo
State cargo deck beam charging assembly bottom be fixedly attached to corresponding end the cargo deck upper surface, positioned at same one end
The bottom terminal ends of the power transmission component in portion are respectively fixedly connected with to the top of the cargo deck beam charging assembly.
Preferably, each main loading rod assembly includes：
Main loading pull bar, positioned at the top of the loading crossbeam, top is connected with the loader；
Two are divided loading pull bar upwards, and two described to divide the top of loading pull bar to be fixedly connected with to the main loading upwards
The bottom of pull bar, two tops for dividing loading pull bar bottom to be respectively connecting to the loading crossbeam upwards, and described in two
Divide the distance at loading pull bar bottom to the midpoint of the loading crossbeam axis equal upwards.
Preferably, each main loading rod assembly includes：
Two are divided loading pull bar downwards, and two described to divide the top of loading pull bar to be respectively connecting to the loading crossbeam downwards
Bottom, two described to be divided to downwards loading pull bar between two combining leverages, and two point loadings downwards are drawn
The distance at bar top to the midpoint of the loading crossbeam axis is equal, two described divide downwards the bottom of loading pull bar with it is described
Loader connects.
Preferably, each floor level beam charging assembly includes：
Piece first loading beam, one end end of the combining leverage of corresponding end, which is bolted to described first, to be added
At the axis point midway of carrier beam, and positioned at the bottom of first loading beam；
Two be parallel to each other and positioned at same level the second loading beams, and two second loading beams with it is described
First loading beam is vertical, is respectively fixedly disposed at the bottom at the first loading beam axial direction both ends；
Four are parallel to each other and positioned at the 3rd loading beams of same level, the bottoms of four the 3rd loading beams with
The upper surface of the floor level is fixedly connected, wherein two the 3rd loading beams are respectively fixedly disposed at one described second
The bottom at loading beam axial direction both ends, in addition two the 3rd loading beams be respectively fixedly disposed at another second loading beam
The bottom at axial both ends.
Preferably, each cargo deck beam charging assembly includes：
Piece the 4th loading beam, the bottom of a power transmission component of corresponding end are bolted to connection to described
Four loading beam tops；
Two be parallel to each other and positioned at same level the 5th loading beams, and two the 5th loading beams with it is described
4th loading beam is vertical, is respectively fixedly disposed at the bottom at the 4th loading beam axial direction both ends；
Four are parallel to each other and positioned at the 6th loading beams of same level, the bottoms of four the 6th loading beams with
The upper surface of the floor level is fixedly connected, wherein two the 6th loading beams are respectively fixedly disposed at one the described 5th
The bottom at loading beam axial direction both ends, in addition two the 6th loading beams be respectively fixedly disposed at another 5th loading beam
The bottom at axial both ends.
Preferably, the power transmission component includes：
Two transmission rods, the top of two transmission rods are hinged to the same of the combining leverage bottom of corresponding end
Opening position, two transmission rod bottoms are respectively fixedly connected with to the top of the 4th loading beam, and two transmission rods
The distance at bottom to the midpoint of the 4th loading beam is equal.
The advantage of the invention is that：
In the aircraft structure strength experiment double floor beam loading device of the present invention, it can be added by two floor level beams
Carry component to load floor level beam, cargo deck beam is loaded by two cargo deck beam charging assemblies, from
And the loading demand of novel large passenger plane bilayer engine room floor beam is adapted to, it can fully verify cabin joist and dependency structure
Intensity so that test structure is more accurate, more efficient effect.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of aircraft structure strength experiment double floor beam loading device of the present invention；
Fig. 2 is the front view of aircraft structure strength experiment double floor beam loading device of the present invention；
Fig. 3 is that charging assembly is connected with floor level in aircraft structure strength experiment double floor beam loading device of the present invention
Structural representation；
Fig. 4 is the structural representation of charging assembly in aircraft structure strength experiment double floor beam loading device of the present invention.
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.
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.
1 to Fig. 4 aircraft structure strength of the present invention experiment double floor beam loading device is done further below in conjunction with the accompanying drawings
Describe in detail.
The invention provides a kind of aircraft structure strength to test double floor beam loading device, can include loader, master
Load rod assembly 1, loading crossbeam 2, combining leverage 3, floor level beam charging assembly 4, power transmission component 5 and cargo deck beam
The grade part of charging assembly 6.
Loader (not shown) is used to apply loading force, can select as a variety of suitable loading equipemtns, such as make
Dynamic cylinder.Loading crossbeam 2 can use a variety of suitable beam structures, positioned at floor level and the tip position of cargo deck
Place.Main loading rod assembly 1 is acted on loading crossbeam 2, and loading crossbeam 2 is applied for controllably (manual control loader)
Perpendicular to the loading force of floor level.
Combining leverage 3 includes two, and two combining leverages 3 are symmetricly set on using the midpoint for loading the axis of crossbeam 2 as origin
The both ends bottom of crossbeam 2 is loaded, and two combining leverages 3 are parallel with loading crossbeam 2, the bottom at loading crossbeam 2 both ends leads to respectively
The combining leverage 3 for crossing connection monaural (not shown) and corresponding end connects.
Floor level beam charging assembly 4 includes two, and two floor level beam charging assemblies 4 are to load the axis of crossbeam 2
Midpoint is origin, loading crossbeam 2 both ends end is symmetricly set on, positioned at the top of the floor level beam charging assembly 4 of same one end
Portion is fixedly connected with one end (the left side left end of combining leverage 3 or the right-hand member of right side combining leverage 3 in Fig. 1) of combining leverage 3,
And the bottom of each floor level beam charging assembly 4 is fixedly attached to the upper surface of the floor level of corresponding end.
Power transmission component 5 includes two, and two power transmission components 5 are set using the midpoint for loading the axis of crossbeam 2 as origin symmetry, position
It is respectively fixedly connected with to the other end of combining leverage 3 and (combines on the left of in Fig. 1 in the top end of the power transmission component 5 of same one end
The right-hand member of lever 3 or the left end of right side combining leverage 3) bottom.Above-mentioned loading crossbeam 2 is transferred load to by connecting monaural
Combining leverage 3, combining leverage 3 is according to load of the arm of force score of design with main cabin and cargo hold (mainly by connecting monaural
Position selected to realize), so as to which loading force to be passed to the floor level beam charging assembly 4 and power transmission component 5 at both ends.
Cargo deck beam charging assembly 6 includes two, and two cargo deck beam charging assemblies 6 are to load the axis of crossbeam 2
Midpoint is set for origin symmetry, and the bottom of each cargo deck beam charging assembly 6 is fixedly attached to the cargo deck of corresponding end
Upper surface, be respectively fixedly connected with positioned at the bottom terminal ends of the power transmission component 5 of same one end to cargo deck beam charging assembly 6
Top；Above-mentioned loading force is transferred to cargo deck beam charging assembly 6 by being transferred to power transmission component 5 again.
In the aircraft structure strength experiment double floor beam loading device of the present invention, it can be added by two floor level beams
Carry component 4 to load floor level beam, cargo deck beam loaded by two cargo deck beam charging assemblies 6,
So as to adapt to the loading demand of novel large passenger plane bilayer engine room floor beam, cabin joist and dependency structure can be fully verified
Intensity so that test structure is more accurate, more efficient effect；In addition, system has sufficient intensity and stability, it is ensured that examination
Test safety.
In the aircraft structure strength experiment double floor beam loading device of the present invention, power transmission component 5 can be set as needed
It is set to a variety of suitable structures；In the present embodiment, power transmission component 5 includes two transmission rods 51, and the top of two transmission rods 51 is equal
It is hinged at the same position of the bottom of combining leverage 3 of corresponding end, two bottoms of transmission rod 51, which are respectively fixedly connected with to the 4th, to be added
The top of carrier beam 61, and the distance at two bottoms of transmission rod 51 to the midpoints of the 4th loading beam 61 is equal.
In the aircraft structure strength experiment double floor beam loading device of the present invention, the structure of main loading rod assembly 1 can
To carry out suitable setting as needed.In a preferred embodiment of the invention, main loading rod assembly 1 includes main loading pull bar
11 and two divide loading pull bar 12 upwards；Positioned at the top of loading crossbeam 2, top is connected main loading pull bar 11 with loader；
Two are divided loading pull bar 12 upwards, and two are divided the top of loading pull bar 12 to be fixedly connected with to the bottom of main loading pull bar 11 upwards
End, two are divided the top that the bottom of loading pull bar 12 is respectively connecting to load crossbeam 2 upwards, and two are divided the bottom of loading pull bar 12 upwards
Hold the distance at the midpoint of the loading axis of crossbeam 2 equal；Loader passes through main loading pull bar 11 and two point loading drawings upwards
Bar 12 from top to bottom applies load to loading crossbeam 2.
Further, in above preferred embodiment, main loading rod assembly 1 can also divide loading pull bar downwards including two
13, two are divided downwards the bottom that the top of loading pull bar 13 is respectively connecting to load crossbeam 2, and two are divided 13, loading pull bar downwards
Between two combining leverages 3, and two are divided downwards the top of loading pull bar 13 to the distance phase at the midpoint of the loading axis of crossbeam 2
Deng two are divided the bottom of loading pull bar 13 to be connected with loader downwards；In still another load mode, pass through two loaders
Loading pull bar 13 is divided to apply load from top to bottom to loading crossbeam 2 downwards by two.
In the aircraft structure strength experiment double floor beam loading device of the present invention, the knot of floor level beam charging assembly 4
Structure can carry out suitable selection as needed；In the present embodiment, each floor level beam charging assembly 4 includes the first loading beam
41st, the second loading beam 42 and the 3rd loading beam 43.
The quantity of first loading beam 41 is one, and one end end of the combining leverage 3 of corresponding end is bolted to the
At the axis point midway of one loading beam 41, and positioned at the bottom of the first loading beam 41.The quantity of second loading beam 42 is two,
Two second loading beams 42 are parallel to each other and are located at same level, and two second loading beams 42 hang down with the first loading beam 41
Directly, it is respectively fixedly disposed at the bottom at 41 axial both ends of the first loading beam.The quantity of 3rd loading beam 43 is four, four the 3rd
Loading beam 43 is parallel to each other and is located at same level, and the upper surface of the bottoms of four the 3rd loading beams 43 with floor level is consolidated
Fixed connection, wherein two the 3rd loading beams 43 are respectively fixedly disposed at the bottom at a 42 axial both ends of the second loading beam, in addition
Two the 3rd loading beams 43 are respectively fixedly disposed at the bottom at another second loading beam, 42 axial both ends.
Equally, the structure of cargo deck beam charging assembly 6 can carry out suitable selection as needed；In the present embodiment,
Each cargo deck beam charging assembly 6 includes the 4th loading beam 61, the 5th loading beam 62 and the 6th loading beam 63.
The quantity of 4th loading beam 61 is one, and the bottom of a power transmission component 5 of the corresponding end of the 4th loading beam 61 passes through
Bolt is fixedly attached to the top of the 4th loading beam 61.The quantity of 5th loading beam 62 is two, and two the 5th loading beams 62 are mutual
It is parallel and be located at same level, and two the 5th loading beams 62 are vertical with the 4th loading beam 61, are respectively fixedly disposed at
The bottom at four loading beams, 61 axial both ends.The quantity of 6th loading beam 63 be four, four the 6th loading beams 63 be parallel to each other and
Positioned at same level, the bottom of four the 6th loading beams 63 is fixedly connected with the upper surface of floor level, wherein two
Six loading beams 63 are respectively fixedly disposed at the bottom at a 62 axial both ends of the 5th loading beam, and two the 6th loading beams 63 divide in addition
The bottom at another 5th loading beam, 62 axial both ends is not fixedly installed on.
It should be noted that between above-mentioned 3rd loading beam 43 and floor level and the 6th loading beam 63 and floor level
Between can use a variety of suitable connected modes；In the present embodiment, especially as shown in figure 3, being opened on floor (joist)
Provided with slide rail 71, opened up on slide rail 71 it is fluted, the 3rd loading beam 43 or the 6th loading beam 63 by through the first bolt 72
It is slidably arranged in groove, in suitable position by screwing the first bolt 72 to be fixed.
It should also be noted that, in the aircraft structure strength experiment double floor beam loading device of the present invention, it is above-mentioned respectively to connect
Socket part point is mentioned to be fixedly connected, and in addition to being particularly described, may each comprise the modes such as bolt connection, welding, riveting, and this
It is preferably bolt connection in embodiment.In addition, the whole loading system that the present invention invents is static determinacy, the length of above-mentioned each beam can
It is designed according to test requirements document, so as to which accurately distribution loads point load.
Further, in floor level beam charging assembly 4 includes more loading beams and cargo deck beam charging assembly 6
Including more loading beams between, a variety of suitable connected modes can be used；In the present embodiment, especially as shown in figure 4, respectively adding
It is bolted between carrier beam, or is attached using the combination of additional ears and bolt, is repeated no more.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can readily occur in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (6)
1. a kind of aircraft structure strength tests double floor beam loading device, it is characterised in that including：
Crossbeam (2) is loaded, positioned at the top of floor level and cargo deck；
Main loading rod assembly (1), act on the loading crossbeam (2), for controllably applying to the loading crossbeam (2)
Perpendicular to the loading force of the floor level；
Loader, for applying the loading force to the loading crossbeam (2)；
Two combining leverages (3), using the midpoint of described loading crossbeam (2) axis as origin, it is symmetricly set on the loading crossbeam
(2) both ends bottom, and two combining leverages (3) are parallel with the loading crossbeam (2), described loading crossbeam (2) both ends
Bottom respectively by connect monaural and corresponding end the combining leverage (3) connect；
Two floor level beam charging assemblies (4), using the midpoint of described loading crossbeam (2) axis as origin, it is symmetricly set on institute
Loading crossbeam (2) both ends end is stated, is combined positioned at the top of the floor level beam charging assembly (4) of same one end with described
One end of lever (3) is fixedly connected, and the bottom of each floor level beam charging assembly (4) is fixedly attached to corresponding end
The floor level upper surface；
Two power transmission components (5), set using the midpoint of described loading crossbeam (2) axis as origin symmetry, positioned at same one end
The top end of the power transmission component (5) is respectively fixedly connected with to the other end bottom of the combining leverage (3)；
Two cargo deck beam charging assemblies (6), set using the midpoint of described loading crossbeam (2) axis as origin symmetry, each
The bottom of the cargo deck beam charging assembly (6) is fixedly attached to the upper surface of the cargo deck of corresponding end, is located at
Bottom terminal ends with the power transmission component (5) of one end are respectively fixedly connected with to the cargo deck beam charging assembly (6)
Top.
2. aircraft structure strength according to claim 1 tests double floor beam loading device, it is characterised in that Mei Gesuo
Stating main loading rod assembly (1) includes：
Main loading pull bar (11), positioned at the top of the loading crossbeam (2), top is connected with the loader；
Two are divided loading pull bar (12) upwards, and two described to divide the top of loading pull bar (12) to be fixedly connected with to the master upwards
Load the bottom of pull bar (11), two described to divide loading pull bar (12) bottom to be respectively connecting to the loading crossbeam (2) upwards
Top, and two it is described upwards divide loading pull bar (12) bottom to it is described load crossbeam (2) axis midpoint distance it is equal.
3. aircraft structure strength according to claim 1 tests double floor beam loading device, it is characterised in that Mei Gesuo
Stating main loading rod assembly (1) includes：
Two are divided loading pull bar (13) downwards, and two described to divide the top of loading pull bar (13) to be respectively connecting to the loading downwards
The bottom of crossbeam (2), two described to be divided to downwards loading pull bar (13) between two combining leverages (3), and two institutes
State and divide the distance at loading pull bar (13) top to the midpoint of described loading crossbeam (2) axis equal downwards, two described downward point
The bottom of loading pull bar (13) is connected with the loader.
4. the aircraft structure strength experiment double floor beam loading device according to Claims 2 or 3, it is characterised in that every
The individual floor level beam charging assembly (4) includes：
Piece first loading beam (41), one end end of the combining leverage (3) of corresponding end are bolted to described
At the axis point midway of one loading beam (41), and positioned at the bottom of first loading beam (41)；
Two be parallel to each other and positioned at same level the second loading beams (42), and two second loading beams (42) with
First loading beam (41) vertically, is respectively fixedly disposed at the bottom at the axial both ends of first loading beam (41)；
Four are parallel to each other and positioned at the 3rd loading beam (43) of same level, the bottom of four the 3rd loading beams (43)
Upper surface with the floor level is fixedly connected, wherein two the 3rd loading beams (43) are respectively fixedly disposed at one
The bottom at the axial both ends of second loading beam (42), in addition two the 3rd loading beams (43) be respectively fixedly disposed at another
The bottom at the second loading beam (42) axial both ends described in root.
5. the aircraft structure strength experiment double floor beam loading device according to Claims 2 or 3, it is characterised in that every
The individual cargo deck beam charging assembly (6) includes：
Piece the 4th loading beam (61), the bottom of a power transmission component (5) of corresponding end are bolted to connection to institute
State the 4th loading beam (61) top；
Two be parallel to each other and positioned at same level the 5th loading beams (62), and two the 5th loading beams (62) with
4th loading beam (61) vertically, is respectively fixedly disposed at the bottom at the axial both ends of the 4th loading beam (61)；
Four are parallel to each other and positioned at the 6th loading beam (63) of same level, the bottom of four the 6th loading beams (63)
Upper surface with the floor level is fixedly connected, wherein two the 6th loading beams (63) are respectively fixedly disposed at one
The bottom at the axial both ends of the 5th loading beam (62), in addition two the 6th loading beams (63) be respectively fixedly disposed at another
The bottom at the 5th loading beam (62) axial both ends described in root.
6. aircraft structure strength according to claim 5 tests double floor beam loading device, it is characterised in that the biography
Power component (5) includes：
Two transmission rods (51), the top of two transmission rods (51) are hinged to the combining leverage (3) bottom of corresponding end
At the same position at end, two transmission rod (51) bottoms are respectively fixedly connected with to the top of the 4th loading beam (61),
And the distance at midpoint of two transmission rod (51) bottoms to the 4th loading beam (61) is equal.
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| CN201610156967.8A CN105836155B (en) | 2016-03-18 | 2016-03-18 | A kind of aircraft structure strength tests double floor beam loading device |
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| CN201610156967.8A CN105836155B (en) | 2016-03-18 | 2016-03-18 | A kind of aircraft structure strength tests double floor beam loading device |
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| CN105836155B true CN105836155B (en) | 2018-01-30 |
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| CN109606620A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of longitudinally reinforced structure of cargo deck stringer |
| CN109606619A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of cargo deck stringer posting structure |
| CN111409855A (en) * | 2020-04-13 | 2020-07-14 | 中国飞机强度研究所 | Fuselage lateral and heading load combined applying device and load applying method |
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| GB590320A (en) * | 1941-04-11 | 1947-07-15 | Siam | Improvements in or relating to apparatus for research on landing gears for aircraft |
| CN201233310Y (en) * | 2008-07-04 | 2009-05-06 | 中国第一汽车集团公司 | Strength test device for remaining member of side sliding door of automobile |
| CN202024893U (en) * | 2011-01-30 | 2011-11-02 | 交通运输部公路科学研究所 | Combined-function security detection device for vehicle structure |
| CN103674734B (en) * | 2012-09-14 | 2017-03-22 | 中国国际海运集装箱(集团)股份有限公司 | Floor strength grade detection device and floor strength grade detection method |
| CN104139867A (en) * | 2013-05-10 | 2014-11-12 | 中国飞机强度研究所 | System and method for loading airframe payload |
| CN203336187U (en) * | 2013-05-10 | 2013-12-11 | 中国飞机强度研究所 | Limiting stopper for fixing of floor bevel loading device |
| CN203275184U (en) * | 2013-05-27 | 2013-11-06 | 北京强度环境研究所 | Multi-stage pressing type lever mechanism device |
| CN104477407B (en) * | 2014-11-27 | 2018-07-13 | 中国飞机强度研究所 | A kind of joist biaxial loadings fixing device |
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