CN205440856U - Nose wheel steering and swing reducing mechanism of nose landing gear of airplane - Google Patents
Nose wheel steering and swing reducing mechanism of nose landing gear of airplane Download PDFInfo
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- CN205440856U CN205440856U CN201520939282.1U CN201520939282U CN205440856U CN 205440856 U CN205440856 U CN 205440856U CN 201520939282 U CN201520939282 U CN 201520939282U CN 205440856 U CN205440856 U CN 205440856U
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- 230000007246 mechanism Effects 0.000 title claims abstract description 67
- 239000011553 magnetic fluid Substances 0.000 claims abstract description 28
- 230000010355 oscillation Effects 0.000 claims description 12
- 230000005672 electromagnetic field Effects 0.000 abstract description 4
- 230000008859 change Effects 0.000 description 7
- 239000008187 granular material Substances 0.000 description 7
- 239000007788 liquid Substances 0.000 description 6
- 230000014759 maintenance of location Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000013016 damping Methods 0.000 description 3
- 239000010720 hydraulic oil Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 239000004094 surface-active agent Substances 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004899 motility Effects 0.000 description 1
- -1 or organosilicon Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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Abstract
The utility model provides a nose wheel of aircraft nose landing gear turns and subtracts pendulum mechanism, can subtract the parameter of pendulum according to the corresponding regulation nose landing gear of nose wheel swing condition, can adapt to multiple different road surface and operational aspect. The front wheel turning and swing reducing mechanism comprises a swing reducing mechanism shell, a turning actuator and a swing sensor, wherein the turning actuator is arranged in the swing reducing mechanism shell and used for realizing turning and swing reduction; the swing sensor is used for detecting the swing amplitude and the frequency of the nose landing gear of the airplane, wherein the front wheel turning and swing reducing mechanism is injected with a magnetic fluid in a swing reducing mechanism shell, the front wheel turning and swing reducing mechanism is provided with a controllable electromagnetic field with an electromagnetic coil in the swing reducing mechanism shell, and the magnetic fluid has the characteristic that the viscosity can be changed along with the magnetic field intensity generated by the controllable electromagnetic field in a positive correlation mode.
Description
Technical field
This utility model relates to aircraft nose landing gear, systems the Nose Wheel Steering of a kind of aircraft nose landing gear being capable of during aircraft taxi making the turning of nose-gear subtract pendulum subtracts swinging mechanism.
Background technology
At present, in civil aircraft, the nose-gear of aircraft realizes turning by turning actuator and subtracts pendulum.Turning actuator such as has rack-and-pinion actuator, push-and-pull turning actuator etc..
Utilize the hydraulic fluid chamber in the turning actuator of hydraulic actuation to play the effect making the turning of undercarriage subtract pendulum, but this method exists nose-gear and subtracts that the parameter of pendulum is non-adjustable, cannot adapt to the shortcomings such as face, multiple road and ruuning situation.
It addition, utilize the turning actuator (EMA, ElectromechanicalActuator) of electrical actuation cannot realize subtracting the effect of pendulum, so that set up special shimmy damping device, thus, number of elements increases, and structure becomes complicated.
Therefore, how can provide a kind of can solve current nose-gear and subtract the problem that the parameter of pendulum is non-adjustable, cannot adapt to face, multiple road and ruuning situation, and the Nose Wheel Steering that can solve to utilize the turning actuator of electrical actuation cannot realize subtracting the aircraft nose landing gear of the problem of pendulum subtracts swinging mechanism and becomes as technical problem urgently to be resolved hurrily.
Utility model content
This utility model is made for solving above-mentioned technical problem, its object is to provide a kind of can regulate nose-gear accordingly according to front wheel shimmy situation and subtract the parameter of pendulum, it is possible to the Nose Wheel Steering of the aircraft nose landing gear adapting to multiple not people having a common goal face and ruuning situation subtracts swinging mechanism.
In order to solve above-mentioned technical problem, first aspect of the present utility model provides the Nose Wheel Steering of a kind of aircraft nose landing gear to subtract swinging mechanism, including subtracting swinging mechanism housing, turning actuator and oscillation gauge, wherein: above-mentioned turning actuator is arranged on the above-mentioned inside subtracting swinging mechanism housing, it is used for realizing turning and subtracts pendulum；Above-mentioned oscillation gauge is for detecting amplitude of fluctuation and the frequency of above-mentioned aircraft nose landing gear, it is characterized in that, above-mentioned the subtracting in swinging mechanism housing subtracting swinging mechanism at above-mentioned Nose Wheel Steering is injected with magnetic fluid, and subtracting swinging mechanism above-mentioned at above-mentioned Nose Wheel Steering to subtract to be provided with in swinging mechanism housing and have the controllable electric magnetic field of solenoid, above-mentioned magnetic fluid has the characteristic that viscosity can change to positive correlation with magnetic field intensity produced by above-mentioned controllable electromagnetic field.
According to configured as described above, utilizing the variable characteristic of the parameter (viscosity) of magnetic fluid, can realize difference subtracts the adaptability that pendulum requires, also can carry out active subtracts pendulum damping, improves the comfortableness of birdman.
It addition, according to configured as described above, either utilize the turning actuator of hydraulic actuation, still utilize the turning actuator of electrical actuation, all can be reliably achieved and subtract pendulum.
It is on the basis of the Nose Wheel Steering of the aircraft nose landing gear of first aspect of the present utility model subtracts swinging mechanism that the Nose Wheel Steering of the aircraft nose landing gear of second aspect of the present utility model subtracts swinging mechanism, it is characterized in that, above-mentioned magnetic fluid is the stable suspension mixed by base load liquid, magnetic retention granule and surfactant.
It is on the basis of the Nose Wheel Steering of the aircraft nose landing gear of second aspect of the present utility model subtracts swinging mechanism that the Nose Wheel Steering of the aircraft nose landing gear of the third aspect of the present utility model subtracts swinging mechanism, it is characterized in that, when there is no magnetic, the above-mentioned magnetic retention granule of above-mentioned magnetic fluid in above-mentioned base load liquid in arranging disorderly, when above-mentioned generation magnetic field, controllable electric magnetic field, the above-mentioned magnetic retention granule of above-mentioned magnetic fluid in magnetic field can polarized and in ordered arrangement.
According to configured as described above, magnetic fluid under the action of a magnetic field, and can make the parameters such as the viscosity of self can change with magnetic field, thus changes overall permanence.
It is on the basis of the Nose Wheel Steering of the aircraft nose landing gear of first aspect of the present utility model subtracts swinging mechanism that the Nose Wheel Steering of the aircraft nose landing gear of fourth aspect of the present utility model subtracts swinging mechanism, it is characterized in that, above-mentioned turning actuator is the turning actuator utilizing hydraulic actuation, uses the medium that above-mentioned magnetic fluid is used as in above-mentioned turning actuator.
In traditional turning actuator utilizing hydraulic actuation, use hydraulic oil as medium therein, but in this utility model, according to configured as described above, owing to using above-mentioned magnetic fluid to replace traditional hydraulic oil to be used as the medium in above-mentioned turning actuator, therefore, it is possible to nose-gear subtracts that the parameter of pendulum is non-adjustable, cannot adapt to face, multiple road and the such technical problem of ruuning situation present in solution prior art.
It is on the basis of the Nose Wheel Steering of the aircraft nose landing gear of first aspect of the present utility model subtracts swinging mechanism that the Nose Wheel Steering of the aircraft nose landing gear of the 5th aspect of the present utility model subtracts swinging mechanism, it is characterized in that, above-mentioned turning actuator is the turning actuator utilizing electrical actuation, subtract in swinging mechanism above-mentioned subtracts swinging mechanism housing at above-mentioned Nose Wheel Steering and there is magnetic current body cavity, above-mentioned magnetic fluid is injected into above-mentioned magnetic fluid intracavity, and above-mentioned controllable electric magnetic field is installed in above-mentioned magnetic current body cavity.
According to configured as described above, it is not necessary to set up special shimmy damping device, in combination with electrical actuation turning system, save space and the energy uses, electricity turning actuator can be made to be reliably achieved and subtract pendulum.
It is on the basis of the Nose Wheel Steering of the aircraft nose landing gear of the 5th aspect of the present utility model subtracts swinging mechanism that the Nose Wheel Steering of the aircraft nose landing gear of the 6th aspect of the present utility model subtracts swinging mechanism, it is characterized in that, above-mentioned magnetic current body cavity is arranged on the two ends of above-mentioned turning actuator.
Accompanying drawing explanation
Fig. 1 is the schematic diagram schematically illustrating and having the aircraft nose landing gear that Nose Wheel Steering of the present utility model subtracts swinging mechanism.
Fig. 2 is to represent the structure chart that Nose Wheel Steering of the present utility model subtracts swinging mechanism, it illustrates above-mentioned Nose Wheel Steering and subtracts turning actuator, magnetic current body cavity that swinging mechanism had etc..
Fig. 3 (a) and Fig. 3 (b) is to represent the figure that the magnetic fluid used in the magnetic current body cavity of the above-mentioned Fig. 2 characteristic (such as mobility or viscosity etc.) when not having Shi Heyou magnetic field, magnetic field changes.
Detailed description of the invention
Hereinafter, referring to the drawings, Nose Wheel Steering of the present utility model is subtracted swinging mechanism 100 to be described in detail.
First, with reference to Fig. 1, Nose Wheel Steering of the present utility model is subtracted position that swinging mechanism 100 installed, i.e. the structure of aircraft nose landing gear 10 illustrates.Fig. 1 is the schematic diagram schematically illustrating and having the aircraft nose landing gear 10 that Nose Wheel Steering of the present utility model subtracts swinging mechanism 100.
Undercarriage (Undercarriage) supports airborne vehicle when being that land for taking off in airborne vehicle bottom or ground (or water surface) slides, and for the accessories apparatus in ground (or water surface) movement.Undercarriage is the parts that only one supports whole airplane, and therefore, it is the inseparable scarce some of aircraft, and without undercarriage, aircraft just can not be at ground moving.It addition, after taking off, undercarriage can be regained depending on aeroplane performance.
In order to adapt to take off, alighting run the needs with ground taxi, in the bottom of aircraft nose landing gear 10 equipped with carrying airtyred wheel 20.Additionally, aircraft nose landing gear 10 also includes that load pillar 30, amortisseur 40 (with reference to Fig. 2), jack 50, Nose Wheel Steering subtract swinging mechanism 100.
Wheel 20 and amortisseur are connected on body A by above-mentioned load pillar 30, and will land and bump stroke in sliding passes to body A.Above-mentioned amortisseur 40 is arranged on the inside of load pillar 30.Above-mentioned Nose Wheel Steering subtracts swinging mechanism 100 can increase the motility that aircraft floor is turned.
Then, with reference to Fig. 2, Nose Wheel Steering is subtracted swinging mechanism 100 and is further described.Fig. 2 is to represent the structure chart that Nose Wheel Steering of the present utility model subtracts swinging mechanism 100, it illustrates above-mentioned Nose Wheel Steering and subtracts turning actuator 130, magnetic current body cavity 160 that swinging mechanism 100 had etc..
Specifically, as in figure 2 it is shown, above-mentioned Nose Wheel Steering subtracts swinging mechanism 100 includes: subtract swinging mechanism housing 110, turning motors 120, turning actuator 130, fixed support 140, oscillation gauge 150 and magnetic current body cavity 160.
Above-mentioned turning actuator 130 and magnetic current body cavity 160 are arranged on the above-mentioned inside subtracting swinging mechanism housing 110, and above-mentioned turning motors 120, fixed support 140 and oscillation gauge 150 are arranged on the above-mentioned outside subtracting swinging mechanism housing 110.
More particularly, above-mentioned turning motors 120 is arranged on the above-mentioned outside subtracting swinging mechanism housing 110, such as be arranged on above-mentioned subtract swinging mechanism housing 110 with on the side of load pillar 30 opposite side of aircraft nose landing gear 10, for driving above-mentioned Nose Wheel Steering to subtract swinging mechanism 100, particularly turning actuator 130 action.
Above-mentioned turning actuator 130 e.g. rack-and-pinion actuator etc., shown in figure 2 is rack-and-pinion actuator (utilizing the turning actuator of electrical actuation).Above-mentioned turning actuator 130 is arranged on the above-mentioned central part subtracted within swinging mechanism housing 110, in above-mentioned turning actuator 130 by being provided with gear part 131 on the side of load pillar 30 side of aircraft nose landing gear 10, this gear part 131 engages with the outer peripheral face of the load pillar 30 of aircraft nose landing gear 10.
Above-mentioned fixed support 140 is arranged on the above-mentioned outside subtracting swinging mechanism housing 110, be such as arranged on above-mentioned subtract swinging mechanism housing 110 by the side of load pillar 30 side of aircraft nose landing gear 10.Above-mentioned fixed support 140 has the stationary plane 141 that the outer peripheral face of the load pillar 30 with aircraft nose landing gear 10 matches, and utilizes above-mentioned stationary plane 141, is fixed the load pillar 30 of aircraft nose landing gear 10.
Above-mentioned oscillation gauge 150 is provided with a pair, and one of them oscillation gauge 150 is arranged at above-mentioned fixed support 140, and another oscillation gauge 150 is arranged at above-mentioned amortisseur 40.
It is arranged on above-mentioned subtracting inside swinging mechanism housing 110 at above-mentioned magnetic current body cavity 160, and is arranged on the two ends of above-mentioned turning actuator 130.It is injected with magnetic fluid 161, it addition, be provided with the controllable electric magnetic field 162 with solenoid (not shown) in above-mentioned magnetic current body cavity 160 in above-mentioned magnetic current body cavity 160.
Fig. 3 (a) and Fig. 3 (b) is to represent the figure that the magnetic fluid 162 used in the magnetic current body cavity 160 of the above-mentioned Fig. 2 characteristic (such as mobility or viscosity etc.) when not having Shi Heyou magnetic field, magnetic field changes.
Above-mentioned magnetic fluid 161 is the stable suspension mixed by base load liquid (usually fluid, or organosilicon, water etc.), magnetic retention granule 161A (usually ferrum granule) and surfactant.As shown in Fig. 3 (a), when there is no magnetic, magnetic retention granule 161A in arranging disorderly, and once produces magnetic field in base load liquid in controllable electric magnetic field 162, so as shown in Fig. 3 (b), magnetic retention granule 161A can in magnetic field can polarized and in ordered arrangement.Correspondingly, magnetic fluid 161 under the action of a magnetic field, and can make the parameters such as the viscosity of self can change to positive correlation with the intensity in magnetic field, thus changes overall permanence.More particularly, magnetic fluid 161 is different with magnetic field intensity produced by controllable electric magnetic field 162, can change to viscosity from the liquid with strong mobility and greatly approximate and viscoelastic liquid.
Flow through the electric current of above-mentioned solenoid (not shown) by control and control magnetic field intensity and the direction in controllable electric magnetic field 162, thus control the characteristics such as the viscosity of magnetic fluid, and then control nose-gear and subtract the intensity of pendulum, adapt to different subtract pendulum situation.
More particularly, above-mentioned controllable electric magnetic field 162 is mainly made up of solenoid, this solenoid is powered by power-supply system (can share power supply wiring with above-mentioned turning actuator 130, save circuit weight), the electric current of solenoid is controlled by controller (not shown), the controller signal by oscillation gauge 150, judge the swing situation of now wheel 20 (front-wheel), the size of current of solenoid is regulated accordingly according to swing situation, change electromagnetic field intensity, thus change magnetic fluid characteristic, produce and suitable subtract pendulum effect.
Magnetic current body cavity magnetic field controls to be subtracted by magnetic fluid the control logic realization of pendulum, its cardinal principle is amplitude of fluctuation and the frequency of the aircraft nose landing gear 10 detected according to oscillation gauge 150, control field supply and regulate magnetic field intensity, make Nose Wheel Steering subtract swinging mechanism 100 and make and required subtract pendulum intensity accordingly.
Those of ordinary skill in the art will be readily apparent other advantage and amendment.Therefore, on it is wider range of for, this utility model is not limited to detail shown and described herein and representative embodiment.Therefore, it can make amendment on the premise of the spirit or scope of the general inventive concept limited without departing from such as appended claims and equivalent thereof.
In above-mentioned embodiment of the present utility model, it is to be illustrated as a example by rack-and-pinion actuator (utilizing the turning actuator of electrical actuation) by above-mentioned turning actuator 130, but this utility model is not limited to this, it can also be the turning actuator 130 utilizing hydraulic actuation, in this case, use magnetic fluid 161 as the medium in turning actuator 130, replacement conventional hydraulic oil, and the amplitude of fluctuation of the aircraft nose landing gear 10 detected according to oscillation gauge 150 and frequency, control field supply and regulate magnetic field intensity, thus change magnetic fluid characteristic, buffer and stop the swing of nose-gear wheel, produce and suitable subtract pendulum effect.
Claims (4)
1. the Nose Wheel Steering of an aircraft nose landing gear (10) subtracts swinging mechanism (100), including subtracting swinging mechanism housing (110), turning actuator (130) and oscillation gauge (150), wherein: described turning actuator (130) be arranged on described in subtract the inside of swinging mechanism housing (110), be used for realizing turning and subtract pendulum；Described oscillation gauge (150) is used for detecting amplitude of fluctuation and the frequency of described aircraft nose landing gear (10), it is characterised in that
Subtract to subtract described in swinging mechanism (100) at described Nose Wheel Steering and swinging mechanism housing (110) is injected with magnetic fluid (161), and subtract to subtract described in swinging mechanism (100) swinging mechanism housing (110) is provided with at described Nose Wheel Steering and there is the controllable electric magnetic field (162) of solenoid
Described magnetic fluid (161) has viscosity can be with the characteristic that changes of the ground of magnetic field intensity positive correlation produced by described controllable electric magnetic field (162).
2. the Nose Wheel Steering of aircraft nose landing gear (10) as claimed in claim 1 subtracts swinging mechanism (100), it is characterised in that
Described turning actuator (130) is the turning actuator utilizing hydraulic actuation,
Use the medium that described magnetic fluid (161) is used as in described turning actuator (130).
3. the Nose Wheel Steering of aircraft nose landing gear (10) as claimed in claim 1 subtracts swinging mechanism (100), it is characterised in that
Described turning actuator (130) is the turning actuator utilizing electrical actuation,
In subtracting swinging mechanism housing (110) described in described Nose Wheel Steering subtracts swinging mechanism (100), there is magnetic current body cavity (160),
Described magnetic fluid (161) is injected in described magnetic current body cavity (160), and described controllable electric magnetic field (162) is installed in described magnetic current body cavity (160).
4. the Nose Wheel Steering of aircraft nose landing gear (10) as claimed in claim 3 subtracts swinging mechanism (100), it is characterised in that
Described magnetic current body cavity (160) is arranged on the two ends of described turning actuator (130).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520939282.1U CN205440856U (en) | 2015-11-23 | 2015-11-23 | Nose wheel steering and swing reducing mechanism of nose landing gear of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520939282.1U CN205440856U (en) | 2015-11-23 | 2015-11-23 | Nose wheel steering and swing reducing mechanism of nose landing gear of airplane |
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| Publication Number | Publication Date |
|---|---|
| CN205440856U true CN205440856U (en) | 2016-08-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520939282.1U Active CN205440856U (en) | 2015-11-23 | 2015-11-23 | Nose wheel steering and swing reducing mechanism of nose landing gear of airplane |
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| CN (1) | CN205440856U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592022A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft turn mechanism |
| CN110435881A (en) * | 2019-08-20 | 2019-11-12 | 中航飞机起落架有限责任公司 | It is a kind of for aircraft nose wheel electric turning and the composite control method for subtracting pendulum |
| CN114194631A (en) * | 2021-12-29 | 2022-03-18 | 江苏龙源振华海洋工程有限公司 | Fixing device is used in transportation of high protection nature fan part |
-
2015
- 2015-11-23 CN CN201520939282.1U patent/CN205440856U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592022A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft turn mechanism |
| CN110435881A (en) * | 2019-08-20 | 2019-11-12 | 中航飞机起落架有限责任公司 | It is a kind of for aircraft nose wheel electric turning and the composite control method for subtracting pendulum |
| CN114194631A (en) * | 2021-12-29 | 2022-03-18 | 江苏龙源振华海洋工程有限公司 | Fixing device is used in transportation of high protection nature fan part |
| CN114194631B (en) * | 2021-12-29 | 2022-12-13 | 江苏龙源振华海洋工程有限公司 | Fixing device is used in transportation of high protection nature fan part |
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