CN1189356C - Method for lengthening aircraft tyre service life - Google Patents
Method for lengthening aircraft tyre service life Download PDFInfo
- Publication number
- CN1189356C CN1189356C CNB031374735A CN03137473A CN1189356C CN 1189356 C CN1189356 C CN 1189356C CN B031374735 A CNB031374735 A CN B031374735A CN 03137473 A CN03137473 A CN 03137473A CN 1189356 C CN1189356 C CN 1189356C
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- aircraft
- tyre
- friction wheel
- swing arm
- aircraft tyre
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Abstract
The present invention discloses a method for lengthening the service life of an aircraft tyre. After a landing gear of an aircraft is laid down, a hanging aircraft tyre is driven to rotate by a drive device, and the rotation direction of the tyre mutually corresponds to the advance direction of the aircraft. When the aircraft is grounded at rotation speed, the linear speed of the surface of the tyre is close to or consistent with the advance speed of the aircraft so as to reduce the sliding friction between the aircraft tyre and the ground surface when the aircraft tyre is grounded instantly. The part of the present landing gear is only simply improved for the present invention to cause the aircraft tyre to rotate so as to reduce the relative speed between the aircraft type and the ground surface when the aircraft type is grounded instantly. The loss which results from sliding friction when the tyre is grounded instantly is reduced, the service life of the aircraft tyre is extended, the safety factor of the aircraft tyre is improved, and the running cost of the aircraft is reduced.
Description
Technical field
The present invention relates to a kind of aircraft tyre method in service life that prolongs, this method be specially adapted to by alighting gear take off the landing various aircrafts.
Background technology
Therefore in the air accident of plane accident, most of accidents occur in taking off of aircraft or the landing process, and by the take off aircraft of landing of alighting gear, the safe reliability of its tire is vital.Can find by the landing process of taking off of observing aircraft, contact to earth moment, have one blue or green cigarette and rise, observe airstrip and can see, having a lot of to deceive impression in the place that aircraft tyre has just contacted to earth at aircraft tyre.These phenomenons all illustrate in the aircraft landing process, aircraft contact to earth moment aircraft tyre and ground between violent cliding friction has taken place, and the consequence of this cliding friction is the wearing and tearing of having quickened aircraft tyre, greatly reduces the safe reliability of aircraft tyre.For aircraft safety, adopt two kinds of methods to solve in the prior art usually: the first improves tire intensity; Its two be reduce the tire access times (can use originally 100 times as certain tire, for improve safety factor only use just changed for 50 times).Obviously, these two kinds of methods all have certain limitation, and the raising of tire intensity can be subjected to the restriction of factors such as material, production technology, and under the condition of comprehensive various factors, the intensity of aircraft tyre is the highest at present.Adopt the method that reduces access times,, improved cost greatly, the waste that also brings resource simultaneously though improved safety factor.
Summary of the invention
The objective of the invention is to overcome the above-mentioned problems in the prior art, by reduce as far as possible aircraft contact to earth moment tire and ground between cliding friction reduce Tyte Wear, improve the safety factor of tire, prolong the service life of tire.
The invention provides a kind of like this aircraft tyre method in service life that prolongs, after aircraft is opened alighting gear, utilize an actuating device to make unsettled aircraft tyre rotate, the tyre rotation direction is corresponding with the aircraft working direction, the linear velocity of velocity of rotation surface of tyre when contacting to earth and aircraft speed of advance near or consistent, to reduce contact to earth cliding friction between moment and ground of aircraft tyre.
Further, described actuating device is a kind of Vidacare corp, hinged installation is by the swing arm of hydraulic efficiency gear control on alighting gear, swing arm one end is installed one by motor-driven actuating device, have a friction wheel on the actuating device, behind the aircraft drop, swing arm under hydraulic efficiency gear control to lower swing, friction wheel is pressed against on the aircraft tyre, machine operation drives friction wheel from rotation subsequently, and the friction wheel that is rotating drives aircraft tyre by friction force and rotates along the direction consistent with heading, when the moment that aircraft tyre soon contacts to earth, handle upwards swing of swing arm, make friction wheel break away from the contact condition with aircraft tyre.
Further, described actuating device is the actuating device that a kind of blast air blows, hinged installation is by the swing arm of hydraulic efficiency gear control on alighting gear, swing arm one end is installed the actuating device that an impeller drives, have a friction wheel on the actuating device, also be provided with the blast air inlet tube that airflow delivery outlet and impeller are complementary in the swing arm simultaneously, the engines tail entraining air stream can enter this inlet tube, conducting by valve control inlet tube, behind the aircraft drop, swing arm under hydraulic efficiency gear control to lower swing, friction wheel is pressed against on the aircraft tyre, open the valve on the introduction pipeline subsequently, impeller is rotation and the work of drive friction wheel under the blowing of the blast air that inlet tube is introduced, and the friction wheel that is rotating drives aircraft tyre by friction force and rotates along the direction consistent with heading, when the moment that aircraft tyre soon contacts to earth, upwards swing of control swing arm makes friction wheel break away from the contact condition with aircraft tyre.
Further, described actuating device is the actuating device that a kind of blast air blows, hinged installation is by the swing arm of hydraulic efficiency gear control on alighting gear, swing arm one end is installed the actuating device that an impeller drives, have a friction wheel on the actuating device, also be provided with the blast air inlet tube that airflow delivery outlet and impeller are complementary in the swing arm simultaneously, the flow guiding disc that is provided with on the air-flow input port of inlet tube and the alighting gear links to each other, under the state of aircraft high-speed travel, blast air can enter inlet tube by flow guiding disc, behind the aircraft drop, swing arm under hydraulic efficiency gear control to lower swing, friction wheel is pressed against on the aircraft tyre, impeller is rotation and the work of drive friction wheel under the blowing of the blast air that inlet tube is introduced, and the friction wheel that is rotating drives aircraft tyre by friction force and rotates along the direction consistent with heading, when the moment that aircraft tyre soon contacts to earth, upwards swing of control swing arm makes friction wheel break away from the contact condition with aircraft tyre.
Further, described actuating device is the actuating device that a kind of blast air blows, blading on the wheel hub of aircraft tyre, the corresponding blast air inlet tube of leaf position on airflow delivery outlet and the aircraft tyre wheel hub is set in the swing arm simultaneously, the flow guiding disc that is provided with on the air-flow input port of inlet tube and the alighting gear links to each other, under the state of aircraft high-speed travel, blast air can enter inlet tube by flow guiding disc, behind the aircraft drop, blast air enters inlet tube under the guiding of flow guiding disc, airflow delivery outlet output from inlet tube, blowing aircraft tyre by the blade on the aircraft tyre wheel hub rotates along the direction consistent with heading, when the moment that aircraft tyre soon contacts to earth, upwards swing of control swing arm makes friction wheel break away from the contact condition with aircraft tyre.
The present invention only needs that present undercarriage is partly carried out very simple improvement just can make that aircraft tyre rotates, thereby reduce contact to earth relative velocity between moment and the ground of aircraft tyre, to reduce the loss that tire caused because of cliding friction in the moment of contacting to earth, prolong the service life of aircraft tyre, improve the safety factor of aircraft tyre, reduced the operating cost of aircraft.
Description of drawings
Fig. 1 is the embodiment of the invention 1 structural representation;
Fig. 2 is Fig. 1 right elevation;
Fig. 3 is the embodiment of the invention 2 structural representations;
Fig. 4 is Fig. 3 right elevation;
Fig. 5 is the embodiment of the invention 3 structural representations;
Fig. 6 is the embodiment of the invention 4 structural representations;
Fig. 7 is Fig. 6 right elevation.
The specific embodiment
As shown in Figure 1 and Figure 2, swing arm 3 is hinged on the alighting gear 1, and hydraulic actuating cylinder 5 control swing arms 3 are around its hinge swing.Swing arm 3 ends are equipped with actuating device 6, and electrical motor 7 drives actuating device 6 work, and actuating device 6 one end output shafts are provided with friction wheel 4.
The arrow A direction flight of aircraft landing forward position, behind the drop 1, modulated pressure cylinder 5 makes swing arm 3 to lower swing, friction wheel 4 is pressed on the aircraft tyre 2, energized makes electrical motor 7 work, friction wheel 4 rotates under the driving of electrical motor 7, actuating device 6, and rotates along the arrow B direction by friction force drive aircraft tyre 2.By the rotating speed at control motor 7, the linear velocity of aircraft tyre 2 tyre surfaces is equaled or near the ground-surface relatively flying speed of aircraft.After aircraft tyre 2 reached predetermined speed, before it landed, operating hydraulically operated cylinder 5 lifted swing arm 3, made friction wheel 4 break away from contact condition with aircraft tyre 2.Like this, in aircraft landing in a flash, have only very little between aircraft tyre 2 and the ground even do not have relative speed difference, thereby eliminated between aircraft tyre 2 and the ground the violent relative friction that produces in aircraft landing moment, thereby reduced the frictional loss of aircraft tyre, improved its service life.
In Fig. 3, embodiment illustrated in fig. 42, the driving power of actuating device 6 by electronic become pneumatic.The air communication piping 8 of driving engine being discharged from exhaust opening of engine is incorporated into the impeller 10, drives impeller 10 work, and drive actuating device 6 work.From the driving engine to the impeller on 10 the pipeline by the valve (not shown) is set, control the work of impeller 10.Pipeline 8 and alighting gear 1 relative fixed (not shown), and in order not influence the normal folding and unfolding of alighting gear, pipeline 8 links to each other with pipeline on being communicated to driving engine by flexible pipe.
In embodiment illustrated in fig. 53, the air-flow that the blast air in the pipeline 8 is produced when being the aircraft high-speed flight is incorporated into air-flow in the pipeline 8 by arc deflector 9, drives impeller 10 work.Deflecting plate and alighting gear 1 relative fixed, and, the flexible pipe of suitable length is set on the pipeline 8 for guaranteeing the normal swing of swing arm 3.Deflecting plate 9 can be other suitable shapes.
Among Fig. 6, embodiment illustrated in fig. 74, one group of blade 11 is set on the wheel hub of aircraft tyre 2, the position of the airflow delivery outlet of the pipeline 8 that joins with arc deflector 9 is corresponding with blade 11.During aircraft landing, behind the drop 1, the blast air of arc deflector 9 guidings on blade 11, rotates aircraft tyre by pipeline 8 winding-ups under the driving of blast air.The size by adjusting arc deflector 9 and the diameter of pipeline 8 can be limited in the rotating speed of aircraft tyre in certain scope, so that it is identical or close with the preceding flying speed of aircraft landing.
Claims (4)
1. one kind prolongs the aircraft tyre method in service life, it is characterized in that, after aircraft is opened alighting gear, utilizing an actuating device to drive friction wheel rotates, driving unsettled aircraft tyre by the friction wheel that rotates by friction force again rotates, the tyre rotation direction is corresponding with the aircraft working direction, the linear velocity of velocity of rotation surface of tyre when contacting to earth and aircraft speed of advance near or consistent, with reduce to contact to earth moment aircraft tyre and ground between force of sliding friction.
2. the method in prolongation aircraft tyre as claimed in claim 1 service life, it is characterized in that, described actuating device is a kind of Vidacare corp, hinged installation is by the swing arm of hydraulic efficiency gear control on alighting gear, swing arm one end is installed one by motor-driven actuating device, have a friction wheel on the actuating device, behind the aircraft drop, swing arm under hydraulic efficiency gear control to lower swing, friction wheel is pressed against on the aircraft tyre, machine operation drives friction wheel from rotation subsequently, the friction wheel that is rotating drives aircraft tyre by friction force and rotates along the direction consistent with heading, when the moment that aircraft tyre soon contacts to earth, handle upwards swing of swing arm, make friction wheel break away from the contact condition with aircraft tyre.
3. the method in prolongation aircraft tyre as claimed in claim 1 service life, it is characterized in that, described actuating device is the actuating device that a kind of blast air blows, hinged installation is by the swing arm of hydraulic efficiency gear control on alighting gear, swing arm one end is installed the actuating device that an impeller drives, have a friction wheel on the actuating device, also be provided with the blast air inlet tube that airflow delivery outlet and impeller are complementary in the swing arm simultaneously, the engines tail entraining air stream can enter this inlet tube, conducting by valve control inlet tube, behind the aircraft drop, swing arm under hydraulic efficiency gear control to lower swing, friction wheel is pressed against on the aircraft tyre, opens the valve on the introduction pipeline subsequently, impeller is rotation and the work of drive friction wheel under the blowing of the blast air that inlet tube is introduced, the friction wheel that is rotating drives aircraft tyre by friction force and rotates along the direction consistent with heading, when the moment that aircraft tyre soon contacts to earth, upwards swing of control swing arm makes friction wheel break away from the contact condition with aircraft tyre.
4. the method in prolongation aircraft tyre as claimed in claim 1 service life, it is characterized in that, described actuating device is the actuating device that a kind of blast air blows, hinged installation is by the swing arm of hydraulic efficiency gear control on alighting gear, swing arm one end is installed the actuating device that an impeller drives, have a friction wheel on the actuating device, also be provided with the blast air inlet tube that airflow delivery outlet and impeller are complementary in the swing arm simultaneously, the flow guiding disc that is provided with on the air-flow input port of inlet tube and the alighting gear links to each other, under the state of aircraft high-speed travel, blast air can enter inlet tube by flow guiding disc, behind the aircraft drop, swing arm under hydraulic efficiency gear control to lower swing, friction wheel is pressed against on the aircraft tyre, open valve subsequently, impeller drives friction wheel from rotation under the blowing of the blast air that inlet tube is introduced, the friction wheel that is rotating drives aircraft tyre by friction force and rotates along the direction consistent with heading, when the moment that aircraft tyre soon contacts to earth, upwards swing of control swing arm makes friction wheel break away from the contact condition with aircraft tyre.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031374735A CN1189356C (en) | 2003-06-25 | 2003-06-25 | Method for lengthening aircraft tyre service life |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031374735A CN1189356C (en) | 2003-06-25 | 2003-06-25 | Method for lengthening aircraft tyre service life |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200410078252 Division CN1257087C (en) | 2003-06-25 | 2003-06-25 | Method of elongating service life of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1456477A CN1456477A (en) | 2003-11-19 |
| CN1189356C true CN1189356C (en) | 2005-02-16 |
Family
ID=29411815
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB031374735A Expired - Fee Related CN1189356C (en) | 2003-06-25 | 2003-06-25 | Method for lengthening aircraft tyre service life |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1189356C (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102180260B (en) * | 2011-04-17 | 2015-12-02 | 黑龙江大学 | Aircraft tire driver |
| FR3011531B1 (en) * | 2013-10-04 | 2017-04-21 | Messier Bugatti Dowty | AIRCRAFT IMPELLER EQUIPPED WITH TRAINING MEANS FOR ROTATING WHEELS CARRIED BY THE LICENSOR |
| CN103879564A (en) * | 2014-04-04 | 2014-06-25 | 黄野 | Special tool for aircraft to slide on ground |
| CN112407260B (en) * | 2020-11-05 | 2022-08-12 | 北京空间机电研究所 | Composite nose landing gear buffer with pre-lifting and pre-rotating light structure |
-
2003
- 2003-06-25 CN CNB031374735A patent/CN1189356C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN1456477A (en) | 2003-11-19 |
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