CN202244077U - Dual-redundancy yawing-preventing control system for braking of airplane - Google Patents
Dual-redundancy yawing-preventing control system for braking of airplane Download PDFInfo
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- CN202244077U CN202244077U CN2011202948354U CN201120294835U CN202244077U CN 202244077 U CN202244077 U CN 202244077U CN 2011202948354 U CN2011202948354 U CN 2011202948354U CN 201120294835 U CN201120294835 U CN 201120294835U CN 202244077 U CN202244077 U CN 202244077U
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Abstract
本实用新型涉及一种飞机刹车双余度防偏航控制系统，系统包括刹车控制器、电磁液压锁、刹车控制阀，本实用新型采用两套液压源进行供压，每套液压源进一个电磁液压锁，每个电磁液压锁后接两个刹车控制阀，两个电磁液压锁对四个刹车机轮中两个内侧的刹车控制阀和两个外侧的刹车控制阀的供油进行分别控制，当任意液压源失效时，对应的电磁液压锁关闭，使系统能保持一半的刹车能力，当一个刹车控制阀失效时，其上端的电磁液压锁关闭，同时切断其下游的两个刹车控制阀供油，保证刹车系统的对称性；当任意电磁液压锁故障关闭时，其下端的两个刹车阀对称丧失刹车能力同样保证刹车的对称性，防止飞机刹车偏航，提高飞机的安全性。
The utility model relates to an aircraft brake double-redundancy anti-yaw control system. The system includes a brake controller, an electromagnetic hydraulic lock, and a brake control valve. The utility model uses two sets of hydraulic sources for pressure supply, and each set of hydraulic sources enters an electromagnetic Hydraulic locks, each electromagnetic hydraulic lock is connected with two brake control valves, and the two electromagnetic hydraulic locks control the oil supply of the two inner brake control valves and the two outer brake control valves of the four brake wheels respectively. When any hydraulic source fails, the corresponding electromagnetic hydraulic lock is closed, so that the system can maintain half of the braking capacity. oil, to ensure the symmetry of the braking system; when any electromagnetic hydraulic lock fails to close, the two brake valves at the lower end will lose their braking ability symmetrically and also ensure the symmetry of the braking, preventing the aircraft from yaw and improving the safety of the aircraft.
Description
技术领域 technical field
本实用新型涉及一种飞机刹车双余度防偏航控制系统。The utility model relates to an aircraft brake double redundancy anti-yaw control system.
背景技术 Background technique
飞机刹车控制系统作为重要的机载设备，刹车系统能否正常工作将严重影响飞机安全，目前，飞机刹车控制系统，大多采用一套液压源供压，在左右机轮各设置一个刹车控制阀，一套液压源同时供左侧刹车控制阀和右侧刹车控制阀；左侧刹车阀控制左侧机轮刹车压力，右侧刹车阀控制右侧机轮的刹车压力；当左右刹车控制阀输出压力差别较大时，飞机容易发生偏航甚至侧翻，由于飞机刹车系统采用一套液压源供压，当液压源失效后，刹车系统即不可用，严重影响飞机使用安全。As an important airborne device, the aircraft brake control system, whether the brake system can work normally will seriously affect the safety of the aircraft. At present, most of the aircraft brake control systems use a set of hydraulic pressure supply, and a brake control valve is installed on the left and right wheels. A set of hydraulic source supplies both the left brake control valve and the right brake control valve; the left brake valve controls the brake pressure of the left wheel, and the right brake valve controls the brake pressure of the right wheel; when the left and right brake control valves output pressure When the difference is large, the aircraft is prone to yaw or even roll over. Since the aircraft brake system uses a hydraulic source for pressure, when the hydraulic source fails, the brake system is unavailable, which seriously affects the safety of the aircraft.
发明内容 Contents of the invention
本发明的目的是：提供一种飞机刹车双余度防偏航控制系统，能保证在系统发生故障时保证飞机仍具有刹车能力，并且能防止飞机在刹车过程发生偏航，有效提高飞机的安全性。The purpose of the present invention is to provide an aircraft brake dual-redundancy anti-yaw control system, which can ensure that the aircraft still has the braking ability when the system fails, and can prevent the aircraft from yawing during the braking process, effectively improving the safety of the aircraft sex.
本发明的技术方案是：一种刹车双余度防偏航控制系统，包括刹车控制器[1]、第一电磁液压锁[21]、第二电磁液压锁[22]、第一～第四刹车控制阀[31～34]、第一～第四机轮刹车装置[41～44]；第一电磁液压锁[21]、第二电磁液压锁[22]分别与刹车控制器[1]电气连接，第一电磁液压锁[21]出口分别与第一刹车控制阀[31]和第二刹车控制阀[32]连接；第二电磁液压锁[22]出口分别与第三刹车控制阀[33]和第四刹车控制阀[34]连接；第一刹车控制阀[31]和第一机轮刹车装置[41]连接，第二刹车控制阀[32]与第四机轮刹车装置[44]连接；第三刹车控制阀[33]与第二机轮刹车装置[42]连接，第四刹车控制阀[34]与第三机轮刹车装置[43]连接；第一～第四机轮刹车装置[41～44]分别控制第一～第四机轮，第一机轮和第四机轮为对称外侧机轮，第二机轮和第三机轮为对称内侧机轮。The technical solution of the present invention is: a dual-redundancy brake anti-yaw control system, including a brake controller [1], a first electromagnetic hydraulic lock [21], a second electromagnetic hydraulic lock [22], first to fourth Brake control valve [31～34], first～fourth machine wheel brake device [41～44]; connection, the outlet of the first electromagnetic hydraulic lock [21] is respectively connected with the first brake control valve [31] and the second brake control valve [32]; the outlet of the second electromagnetic hydraulic lock [22] is respectively connected with the third brake control valve [33] ] is connected with the fourth brake control valve [34]; the first brake control valve [31] is connected with the first wheel brake device [41], and the second brake control valve [32] is connected with the fourth wheel brake device [44] connection; the third brake control valve [33] is connected with the second wheel brake device [42], and the fourth brake control valve [34] is connected with the third wheel brake device [43]; the first to fourth wheel brakes Device [41～44] controls the first～fourth machine wheel respectively, and the first machine wheel and the fourth machine wheel are symmetrical outer machine wheels, and the second machine wheel and the third machine wheel are symmetrical inner machine wheels.
当任意液压源失效时，对应的液压锁关闭，使系统能保持一半的刹车能力，当一个刹车控制阀失效时，其上端的电磁液压锁关闭，同时切断其下游的两个刹车控制阀供油，保证刹车系统的对称性；当任意电磁液压锁故障关闭时，其下端的两个刹车阀对称丧失刹车能力同样保证刹车的对称性，防止飞机刹车偏航，提高飞机的安全性。When any hydraulic source fails, the corresponding hydraulic lock is closed, so that the system can maintain half of the braking capacity. When a brake control valve fails, the electromagnetic hydraulic lock at the upper end is closed, and the oil supply to the two downstream brake control valves is cut off at the same time. , to ensure the symmetry of the braking system; when any electromagnetic hydraulic lock fails to close, the two brake valves at the lower end will lose their braking capacity symmetrically and also ensure the symmetry of the braking, preventing the aircraft from yaw and improving the safety of the aircraft.
本发明具有的优点和有益效果是：本实用新型能保证在系统发生故障时保证飞机仍具有刹车能力，并且能防止飞机在刹车过程发生偏航，提高了飞机的安全性。The advantages and beneficial effects of the present invention are: the utility model can ensure that the aircraft still has the braking ability when the system fails, and can prevent the aircraft from yawing during the braking process, thereby improving the safety of the aircraft.
附图说明 Description of drawings
图1为本实用新型结构示意图，其中，1：刹车控制器，21：第一电磁液压锁，22：第二电磁液压锁，31～34：第一～第四刹车控制阀，41～44：第一～第四机轮刹车装置。Fig. 1 is a structural diagram of the utility model, wherein, 1: brake controller, 21: first electromagnetic hydraulic lock, 22: second electromagnetic hydraulic lock, 31-34: first to fourth brake control valves, 41-44: Braking devices for the first to fourth wheels.
具体实施方式 Detailed ways
下面结合说明书附图对本实用新型作具体说明。Below in conjunction with accompanying drawing, the utility model is described in detail.
一种刹车双余度防偏航控制系统，包括刹车控制器1，第一电磁液压锁21、第二电磁液压锁22，第一～第四刹车控制阀31～34、第一～第四机轮刹车装置41～44；第一电磁液压锁21、第二电磁液压锁22分别与刹车控制器1电气连接，第一电磁液压锁21出口分别与第一刹车控制阀31和第二刹车控制阀32连接；第二电磁液压锁22出口分别与第三刹车控制阀33和第四刹车控制阀34连接；第一刹车控制阀31和第一机轮刹车装置41连接，第二刹车控制阀32与第四机轮刹车装置44连接；第三刹车控制阀33与第二机轮刹车装置42连接，第四刹车控制阀34与第三机轮刹车装置43连接；第一～第四机轮刹车装置41～44分别控制第一～第四机轮，第一机轮和第四机轮为对称外侧机轮，第二机轮和第三机轮为对称内侧机轮。A brake dual-redundancy anti-yaw control system, comprising a brake controller 1, a first electromagnetic hydraulic lock 21, a second electromagnetic hydraulic lock 22, first to fourth brake control valves 31 to 34, first to fourth brake control valves Wheel brake devices 41-44; the first electromagnetic hydraulic lock 21 and the second electromagnetic hydraulic lock 22 are electrically connected to the brake controller 1 respectively, and the outlet of the first electromagnetic hydraulic lock 21 is respectively connected to the first brake control valve 31 and the second brake control valve 32 connected; the outlet of the second electromagnetic hydraulic lock 22 is respectively connected with the third brake control valve 33 and the fourth brake control valve 34; the first brake control valve 31 is connected with the first wheel brake device 41, and the second brake control valve 32 is connected with The fourth wheel brake device 44 is connected; the third brake control valve 33 is connected with the second wheel brake device 42, and the fourth brake control valve 34 is connected with the third wheel brake device 43; the first to fourth wheel brake devices 41～44 respectively control the first～fourth machine wheels, the first machine wheel and the fourth machine wheel are symmetrical outer machine wheels, and the second machine wheel and the third machine wheel are symmetrical inner machine wheels.
第一电磁液压锁21由1#液压源供压，第二电磁液压锁22由2#液压源供压，在需要刹车时，刹车控制器1对第一、第二电磁液压锁21、22供电，1#液压源通过第一电磁液压锁21将压力供给第一刹车控制阀31和第二刹车控制阀32；2#液压源通过第二电磁液压锁22将压力供给第三刹车控制阀33和第四刹车控制阀34。The first electromagnetic hydraulic lock 21 is supplied with pressure by the 1# hydraulic source, and the second electromagnetic hydraulic lock 22 is supplied with pressure by the 2# hydraulic source. When braking is required, the brake controller 1 supplies power to the first and second electromagnetic hydraulic locks 21 and 22. , the 1# hydraulic source supplies pressure to the first brake control valve 31 and the second brake control valve 32 through the first electromagnetic hydraulic lock 21; the 2# hydraulic source supplies pressure to the third brake control valve 33 and the third brake control valve 32 through the second electromagnetic hydraulic lock 22 The fourth brake control valve 34 .
在不需要刹车时，刹车控制器1同时切断对第一、第二电磁液压锁21、22的供电，这时刹车系统的第一电磁液压锁21、第一刹车控制阀31和第二刹车控制阀32都和1#液压源回油连通；第二电磁液压锁22、第三刹车控制阀33和第四刹车控制阀34都和2#液压源回油连通，将第一～第四机轮刹车压力彻底释放掉。When the brakes are not needed, the brake controller 1 cuts off the power supply to the first and second electromagnetic hydraulic locks 21 and 22 at the same time. The valve 32 is connected to the oil return of the 1# hydraulic source; the second electromagnetic hydraulic lock 22, the third brake control valve 33 and the fourth brake control valve 34 are all connected to the oil return of the 2# hydraulic source, and the first to fourth wheels The brake pressure is completely released.
当第一电磁液压锁21故障时，能同时将第一刹车控制阀31和第二刹车控制阀32的供油切断；当第二电磁液压锁22故障时，能同时将第三刹车控制阀33和第四刹车控制阀34的供油切断，保证飞机刹车的均衡性，当第一刹车控制阀31或第二刹车控制阀32中任一发生故障，刹车控制器1将第一电磁液压锁21供电切断；当第三刹车控制阀33或第四刹车控制阀34中任一发生故障，刹车控制器1将第二电磁液压锁22供电切断，同样能保证刹车和均衡性，防止飞机刹车偏航。When the first electromagnetic hydraulic lock 21 fails, the oil supply of the first brake control valve 31 and the second brake control valve 32 can be cut off at the same time; and the oil supply of the fourth brake control valve 34 are cut off to ensure the balance of the aircraft brake. When any failure occurs in the first brake control valve 31 or the second brake control valve 32, the brake controller 1 will first electromagnetic hydraulic lock 21 Cut off the power supply; when any one of the third brake control valve 33 or the fourth brake control valve 34 breaks down, the brake controller 1 cuts off the power supply of the second electromagnetic hydraulic lock 22, which can also ensure the braking and balance, and prevent the aircraft from braking and yaw .
本实用新型能保证在系统发生故障时保证飞机仍具有刹车能力，并且能防止飞机在刹车过程发生偏航，提高了飞机的安全性。The utility model can ensure that the aircraft still has the braking ability when the system fails, and can prevent the aircraft from yaw during the braking process, thereby improving the safety of the aircraft.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011202948354U CN202244077U (en) | 2011-08-15 | 2011-08-15 | Dual-redundancy yawing-preventing control system for braking of airplane |
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| CN2011202948354U CN202244077U (en) | 2011-08-15 | 2011-08-15 | Dual-redundancy yawing-preventing control system for braking of airplane |
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| CN2011202948354U Expired - Lifetime CN202244077U (en) | 2011-08-15 | 2011-08-15 | Dual-redundancy yawing-preventing control system for braking of airplane |
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Cited By (10)
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| CN103786877A (en) * | 2014-01-26 | 2014-05-14 | 北京航空航天大学 | Multi-wheel aircraft braking system based on energy regenerative braking device and control method thereof |
| CN103899488A (en) * | 2012-12-26 | 2014-07-02 | 邵汉琦 | Wind Turbines |
| CN103963761A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Deceleration rate control-based antiskid braking system and method for airplane |
| CN105015765A (en) * | 2015-08-11 | 2015-11-04 | 中国航空工业集团公司西安飞机设计研究所 | Braking redundancy actuating system |
| CN105523177A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft brake ground protection system and method thereof |
| CN105523178A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft double-redundancy anti-skid control system |
| US9845148B2 (en) | 2012-11-16 | 2017-12-19 | Airbus Operations Limited | Aircraft landing gear longitudinal force control |
| CN108116667A (en) * | 2017-12-06 | 2018-06-05 | 西安航空制动科技有限公司 | Airplane hydraulic pressure brake system with independent antiskid function |
| CN117141715A (en) * | 2023-09-22 | 2023-12-01 | 西安航空制动科技有限公司 | Airplane redundancy wheel brake control system and switching method thereof |
| US12291183B2 (en) | 2022-10-26 | 2025-05-06 | Goodrich Corporation | Advanced locked wheel protection functionality |
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- 2011-08-15 CN CN2011202948354U patent/CN202244077U/en not_active Expired - Lifetime
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| CN111114761A (en) * | 2012-11-16 | 2020-05-08 | 空中客车营运有限公司 | Aircraft landing gear longitudinal force control |
| US9845148B2 (en) | 2012-11-16 | 2017-12-19 | Airbus Operations Limited | Aircraft landing gear longitudinal force control |
| CN111114761B (en) * | 2012-11-16 | 2023-09-29 | 空中客车营运有限公司 | Aircraft landing gear longitudinal force control |
| CN104955729B (en) * | 2012-11-16 | 2020-02-07 | 空中客车营运有限公司 | Aircraft landing gear longitudinal force control |
| CN103899488B (en) * | 2012-12-26 | 2016-12-28 | 邵汉琦 | Wind power generator |
| CN103899488A (en) * | 2012-12-26 | 2014-07-02 | 邵汉琦 | Wind Turbines |
| CN103963761A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Deceleration rate control-based antiskid braking system and method for airplane |
| US10093288B2 (en) | 2014-01-26 | 2018-10-09 | Beihang University | Multi-wheel aeroplane braking system based on self-energy-regenerative braking device and controlling method therefor |
| CN103786877B (en) * | 2014-01-26 | 2016-01-13 | 北京航空航天大学 | Multi-wheel aircraft braking system and its control method based on self-feeding braking device |
| CN103786877A (en) * | 2014-01-26 | 2014-05-14 | 北京航空航天大学 | Multi-wheel aircraft braking system based on energy regenerative braking device and control method thereof |
| CN105523177A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft brake ground protection system and method thereof |
| CN105523178A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft double-redundancy anti-skid control system |
| CN105015765A (en) * | 2015-08-11 | 2015-11-04 | 中国航空工业集团公司西安飞机设计研究所 | Braking redundancy actuating system |
| CN108116667A (en) * | 2017-12-06 | 2018-06-05 | 西安航空制动科技有限公司 | Airplane hydraulic pressure brake system with independent antiskid function |
| US12291183B2 (en) | 2022-10-26 | 2025-05-06 | Goodrich Corporation | Advanced locked wheel protection functionality |
| CN117141715A (en) * | 2023-09-22 | 2023-12-01 | 西安航空制动科技有限公司 | Airplane redundancy wheel brake control system and switching method thereof |
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