CN203324004U - Aircraft seat comprehensive test bench - Google Patents
Aircraft seat comprehensive test bench Download PDFInfo
- Publication number
- CN203324004U CN203324004U CN2013204031758U CN201320403175U CN203324004U CN 203324004 U CN203324004 U CN 203324004U CN 2013204031758 U CN2013204031758 U CN 2013204031758U CN 201320403175 U CN201320403175 U CN 201320403175U CN 203324004 U CN203324004 U CN 203324004U
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- pitching
- roll
- support
- whirligig
- seat
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- Expired - Fee Related
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Abstract
An aircraft seat comprehensive test bench comprises a supporting base; the supporting base is provided with a horizontal rolling rotary device; the horizontal rolling rotary device is provided with a self-rotation horizontal rolling support; a pitching rotary device is rotatingly and movably connected with the horizontal rolling support and is fixedly connected with a driving device which is fixedly mounted on the horizontal rolling support; the pitching rotary device is provided with a seat positioning plate connected with a seat model; and the supporting base is also provided with a control device used for controlling the pitching rotary device and the horizontal rolling rotary device. The aircraft seat comprehensive test bench provided by the utility model can be compatible with test requirements of different types of seats, such that a multi-purpose function can be realized, and therefore, test cost can be reduced; and at the same time, various attitudes of the seats in flight can be simulated, and test and research of the safety performance of the seats can be facilitated. The aircraft seat comprehensive test bench of the utility model is advantageous in safe and reliable operation.
Description
Technical field
The utility model relates to a kind of security test device, particularly a kind of aircraft seat multi-function test stand.
Background technology
Seat is one of aircraft vitals, and one of its effect is for the occupant provides the comfortable environment of taking, and is in case of emergency can realize the effect of occupant's lifesaving when aircraft on the other hand.Therefore, the attitude control performance test of seat in flight course is very necessary.At present, the specialized equipment of still not testing for seat flight attitude control performance.
Summary of the invention
Technical problem to be solved in the utility model is to provide a kind of aircraft seat multi-function test stand, simulation seat many attitude: realize in 0 ° to ± 90 ° scope of seat pitching stepless adjustable, realize in 0 ° to ± 180 ° scope of seat roll stepless adjustable, energy positive lock after seat is adjusted to predeterminated position, the chair angle control accuracy is 0.5 °.
For solving the problems of the technologies described above, the technical scheme that the utility model adopts is: a kind of aircraft seat multi-function test stand, comprise base for supporting, base for supporting is provided with the roll whirligig, be provided with the roll support of self-driven rotation in described roll whirligig, the pitching whirligig is rotatable to be flexibly connected with the roll support, and is fixedly connected with the drive unit on being fixedly mounted on the roll support, and the pitching whirligig is provided with the seat location-plate for being connected with seat model;
Also be provided with for controlling the control device of pitching whirligig and roll whirligig.
Described base for supporting is provided with column, and in the roll whirligig, the roll main shaft rotatably is fixedly connected with the roll support through column, and described roll support is provided with two parallel cantilevers, and the pitching support is rotatable to be arranged between two cantilevers.
Described roll main shaft is rotatable to be bearing in the roll axle box, and is connected with the roll transmission shaft by the roll gear pair, and the roll transmission shaft is connected with the roll servomotor by the roll speed reduction unit.
Also be provided with the roll sensor on roll transmission shaft or roll main shaft.
In described pitching whirligig, the pitching support is by pitching turning axle and the rotatable flexible connection of roll support, the pitching turning axle of at least one end of pitching support is fixedly connected with the output shaft of pitching speed reduction unit, the input shaft of pitching speed reduction unit is fixedly connected with the pitching servomotor, and the pitching speed reduction unit is fixedly connected with the roll support.
Also be provided with pitch sensor on the pitching turning axle.
In described pitching support, two pitching otic placode two ends are fixedly connected with by the pitching cross bar, and the pitching cross bar is provided with the seat location-plate, and pitching otic placode middle part is provided with the pitching axis hole coordinated with the pitching turning axle.
On column, also be provided with for lifting by crane the seat boom hoisting of seat model, in described seat boom hoisting, the lifting back shaft is fixedly connected with column, the lifting back shaft is provided with semi-girder, the free end of semi-girder is provided with suspension hook, winding plant is connected with suspension hook, and winding plant also is electrically connected to control device.
Also be provided with a plurality of castors under described base for supporting.
Also be provided with a plurality of screw jack under described base for supporting.
A kind of aircraft seat multi-function test stand that the utility model provides, testing requirements that can compatible different model seat, reach " one multiplex ", reduced the cost of test.Simultaneously, can simulate the in-flight various attitudes of seat, be conducive to the test and study of seat security performance.Handling safety of the present utility model is reliable.
The accompanying drawing explanation
Below in conjunction with drawings and Examples, the utility model is described in further detail:
Fig. 1 is main TV structure schematic diagram of the present utility model.
Fig. 2 is the axle geodesic structure schematic diagram that waits of the present utility model.
The schematic diagram such as geodesic structure such as axle such as grade that Fig. 3 is boom hoisting in the utility model.
The schematic diagram such as geodesic structure such as axle such as grade that Fig. 4 is roll axle box in the utility model.
Fig. 5 be in the utility model the roll axle box cross-sectional view.
Fig. 6 be in the utility model pitching whirligig and roll whirligig etc. axle geodesic structure schematic diagram.
The schematic diagram such as geodesic structure such as axle such as grade that Fig. 7 is pitching support in the utility model.
In figure: seat model 1, base for supporting 2, seat boom hoisting 3, pitching whirligig 4, roll whirligig 5, control device 6, castor 7, screw jack 8, suspension hook 9, semi-girder 10, winding plant 11, semi-girder case 12, lifting back shaft 13, roll main shaft 14, roll axle box 15, end cap 16, roll sensor 17, roll speed reduction unit 18, roll servomotor 19, roll transmission shaft 20, roll gear pair 21, roll support 22, pitching support 23, pitch sensor 24, pitching speed reduction unit 25, pitching servomotor 26, pitching otic placode 27, pitching turning axle 28, pitching cross bar 29, pitching axis hole 30, seat location-plate 31, column 32.
Embodiment
In Fig. 1-2, a kind of aircraft seat multi-function test stand, comprise base for supporting 2, base for supporting 2 is provided with roll whirligig 5, be provided with the roll support 22 of self-driven rotation in described roll whirligig 5, pitching whirligig 4 is rotatable to be flexibly connected with roll support 22, and is fixedly connected with the drive unit on being fixedly mounted on roll support 22, and pitching whirligig 4 is provided with the seat location-plate 31 for being connected with seat model 1; Wherein roll whirligig 5 is stepless adjustable for seat model 1 is realized in 0 ° to ± 180 ° scope of seat roll, and pitching whirligig 4 is stepless adjustable for seat model 1 is realized in 0 ° to ± 90 ° scope.Structure, make the posture of aircraft seat in needs thus.
Also be provided with for controlling the control device 6 of pitching whirligig 4 and roll whirligig 5.Control device 6 in this example is for sending control signal, to control the anglec of rotation of pitching whirligig 4 and roll whirligig 5, and provide power supply, at this in routine Fig. 1, control device 6 is positioned at a side of base for supporting 2, but control device 6 integrally is located at, on base for supporting 2, is also feasible.
In Fig. 1,4,5, described base for supporting 2 is provided with column 32, in roll whirligig 5, roll main shaft 14 rotatably is fixedly connected with roll support 22 through column 32, thereby makes roll support 22 take roll main shaft 14 as the axle center rotation at column 32.Described roll support 22 is provided with two parallel cantilevers, and pitching support 23 is rotatable to be arranged between two cantilevers.Roll support 22 provides basis for rotatablely moving of pitching support 23.
In Fig. 5, described roll main shaft 14 is rotatable to be bearing in roll axle box 15, and is connected with roll transmission shaft 20 by roll gear pair 21, and roll transmission shaft 20 is connected with roll servomotor 19 by roll speed reduction unit 18.Driven the rotation of roll main shaft 14 by roll servomotor 19.
Also be provided with roll sensor 17 on roll transmission shaft 20 or roll main shaft 14.The roll sensor 17 arranged can pass to control device 6 by the rotation angle information of roll main shaft 14, to realize the automatic control of process of the test.
In Fig. 6,7, in described pitching whirligig 4, pitching support 23 is by pitching turning axle 28 and the rotatable flexible connection of roll support 22, the pitching turning axle 28 of pitching support 23 at least one ends is fixedly connected with the output shaft of pitching speed reduction unit 25, the input shaft of pitching speed reduction unit 25 is fixedly connected with pitching servomotor 26, and pitching speed reduction unit 25 is fixedly connected with roll support 22.The pitching support 23 that rotarily drives by pitching servomotor 26 rotates, thereby drives seat model 1 pitching rotation.
Also be provided with pitch sensor 24 on pitching turning axle 28.The pitch sensor 24 arranged can pass to control device 6 by the rotation angle information of pitching support 23,
In Fig. 7, in described pitching support 23, two pitching otic placode 27 two ends are fixedly connected with by pitching cross bar 29, and pitching cross bar 29 is provided with seat location-plate 31, and pitching otic placode 27 middle parts are provided with the pitching axis hole 30 coordinated with pitching turning axle 28.Seat location-plate 31 is for being fixedly connected with seat model 1.
In Fig. 1-3, on column 32, also be provided with for lifting by crane the seat boom hoisting 3 of seat model 1, in described seat boom hoisting 3, lifting back shaft 13 is fixedly connected with column 32, lifting back shaft 13 is provided with semi-girder 10, the free end of semi-girder 10 is provided with suspension hook 9, and winding plant 11 is connected with suspension hook 9, and winding plant 11 also is electrically connected to control device 6.Because the weight of seat model 1 is heavier, the seat boom hoisting 3 of setting can significantly reduce the labour intensity in process of the test.By winding plant 11, seat model 1 is lifted to suitable position, and then seat model 1 is connected with seat location-plate 31.
Optimize as in Fig. 1,2, described base for supporting also is provided with a plurality of castors 7 for 2 times.Structure, be convenient to the movement of whole testing table thus.Described base for supporting also is provided with a plurality of screw jack 8 for 2 times.Structure, can guarantee in process of the test that firm supporting is reliable thus, after test, can pack up again, is convenient to mobile.
Claims (10)
1. an aircraft seat multi-function test stand, comprise base for supporting (2), it is characterized in that: base for supporting (2) is provided with roll whirligig (5), be provided with the roll support (22) of self-driven rotation in described roll whirligig (5), pitching whirligig (4) is rotatable to be flexibly connected with roll support (22), and be fixedly connected with the drive unit on being fixedly mounted on roll support (22), pitching whirligig (4) is provided with the seat location-plate (31) for being connected with seat model (1);
Also be provided with for controlling the control device (6) of pitching whirligig (4) and roll whirligig (5).
2. a kind of aircraft seat multi-function test stand according to claim 1, it is characterized in that: described base for supporting (2) is provided with column (32), in roll whirligig (5), roll main shaft (14) rotatably is fixedly connected with roll support (22) through column (32), described roll support (22) is provided with two parallel cantilevers, and pitching support (23) is rotatable to be arranged between two cantilevers.
3. a kind of aircraft seat multi-function test stand according to claim 2, it is characterized in that: described roll main shaft (14) is rotatable to be bearing in roll axle box (15), and be connected with roll transmission shaft (20) by roll gear pair (21), roll transmission shaft (20) is connected with roll servomotor (19) by roll speed reduction unit (18).
4. a kind of aircraft seat multi-function test stand according to claim 3, is characterized in that: on roll transmission shaft (20) or roll main shaft (14), also be provided with roll sensor (17).
5. according to the described a kind of aircraft seat multi-function test stand of claim 2-4 any one, it is characterized in that: in described pitching whirligig (4), pitching support (23) is by pitching turning axle (28) and the rotatable flexible connection of roll support (22), the pitching turning axle (28) of at least one end of pitching support (23) is fixedly connected with the output shaft of pitching speed reduction unit (25), the input shaft of pitching speed reduction unit (25) is fixedly connected with pitching servomotor (26), and pitching speed reduction unit (25) is fixedly connected with roll support (22).
6. a kind of aircraft seat multi-function test stand according to claim 5, is characterized in that: also be provided with pitch sensor (24) on pitching turning axle (28).
7. a kind of aircraft seat multi-function test stand according to claim 6, it is characterized in that: in described pitching support (23), two pitching otic placodes (27) two ends are fixedly connected with by pitching cross bar (29), pitching cross bar (29) is provided with seat location-plate (31), and pitching otic placode (27) middle part is provided with the pitching axis hole (30) coordinated with pitching turning axle (28).
8. a kind of aircraft seat multi-function test stand according to claim 2, it is characterized in that: on column (32), also be provided with for lifting by crane the seat boom hoisting (3) of seat model (1), in described seat boom hoisting (3), lifting back shaft (13) is fixedly connected with column (32), lifting back shaft (13) is provided with semi-girder (10), the free end of semi-girder (10) is provided with suspension hook (9), winding plant (11) is connected with suspension hook (9), and winding plant (11) also is electrically connected to control device (6).
9. according to claim 1-4, the described a kind of aircraft seat multi-function test stand of 6-8 any one, it is characterized in that: also be provided with a plurality of castors (7) under described base for supporting (2).
10. a kind of aircraft seat multi-function test stand according to claim 9, is characterized in that: also be provided with a plurality of screw jack (8) under described base for supporting (2).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2013204031758U CN203324004U (en) | 2013-07-08 | 2013-07-08 | Aircraft seat comprehensive test bench |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2013204031758U CN203324004U (en) | 2013-07-08 | 2013-07-08 | Aircraft seat comprehensive test bench |
Publications (1)
Publication Number | Publication Date |
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CN203324004U true CN203324004U (en) | 2013-12-04 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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CN2013204031758U Expired - Fee Related CN203324004U (en) | 2013-07-08 | 2013-07-08 | Aircraft seat comprehensive test bench |
Country Status (1)
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CN (1) | CN203324004U (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103335836A (en) * | 2013-07-08 | 2013-10-02 | 三峡大学 | Integrated test bench of aircraft seats |
CN105021393A (en) * | 2015-08-12 | 2015-11-04 | 沈阳旭阳中冶座椅有限公司 | Seat rotation test machine |
CN108645605A (en) * | 2018-04-28 | 2018-10-12 | 广东工业大学 | A kind of civil aviation passenger aircraft seat static test experiment porch and test method |
-
2013
- 2013-07-08 CN CN2013204031758U patent/CN203324004U/en not_active Expired - Fee Related
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103335836A (en) * | 2013-07-08 | 2013-10-02 | 三峡大学 | Integrated test bench of aircraft seats |
CN103335836B (en) * | 2013-07-08 | 2015-10-21 | 三峡大学 | Aircraft seat multi-function test stand |
CN105021393A (en) * | 2015-08-12 | 2015-11-04 | 沈阳旭阳中冶座椅有限公司 | Seat rotation test machine |
CN105021393B (en) * | 2015-08-12 | 2018-03-02 | 沈阳旭阳中冶座椅有限公司 | Seat rotary test rig |
CN108645605A (en) * | 2018-04-28 | 2018-10-12 | 广东工业大学 | A kind of civil aviation passenger aircraft seat static test experiment porch and test method |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131204 Termination date: 20140708 |
|
EXPY | Termination of patent right or utility model |