工程研究——跨学科视野中的工程2025，Vol.17Issue(3)：328-337,10.DOI:10.3724/j.issn.1674-4969.20240059
双发放宽静稳定布局电传客机单发停车对飞机操纵性及稳定性的影响研究
Influence of Single Engine Failure on Control and Stability Characteristics on Twin-Engine Relaxed Static Stability Fly-by-Wire Passenger Aircraft
摘要
Abstract
With the increasing popularity of fly-by-wire technology,the relaxed static stability(RSS)configuration has gradually been applied on civil aircraft.In aviation,an aircraft is said to have relaxed static stability if has low or negative longitudinal static stability.An aircraft with relaxed static stability will have a tendency to change its pitch and bank angles spontaneously.When disturbed,the aircraft will experience prolonged short period motion and it may take much longer to return to the trimmed state.Yet the design requirements for aircraft hydraulic and flight control systems have also been rising.The electronic flight control system(EFCS)has to react fast to address the stability problem.The deflection rates of flight control surfaces are directly proportional to the flow rate of hydraulic fluid inside the electro-hydraulic servo actuators.The stability augmentation can only be achieved when hydraulic flow rate is guaranteed.The engines are the main source of the aircraft secondary powers.Hydraulic power comes from Engine Driven Pumps(EDP),which is powered by engine accessory gear box.Single engine failure will have direct impact on flight performance and handling qualities,and the degrade of secondary power may aggravate the above effects.By analyzing the design characteristic of aerodynamic configuration,electric power system,hydraulic system and flight control system,the impact of single engine failure on hydraulic and flight control was sorted out.The Airbus A320 aircraft was taken as an example,the impact of losing engine 1(ENG 1)and ENG 2 on its hydraulic system and fly-by-wire flight control was analyzed respectively.The made up of A320 hydraulic power was discussed and it was revealed that the EDPs contributed most of the hydraulic flow for flight control.Although the power transfer unit(PTU)can compensate for losing one of the EDPs,the flight control may still suffer from insufficient hydraulic power when losing one engine.The hydraulic flow distribution on flight control surfaces was discussed.And flight control users were divided into two categories:primary users and secondary users.The primary users included ailerons,elevators,rudder,spoilers,trimmable horizontal stabilizers,yaw damper actuators and wingtip brakes,which were crucial in flight control and needed to be pressurized at any time in flight.Secondary users included PTU and hydraulic motors which actuated the slats and wing flaps,which consumed greater amount of hydraulic flow and may not be pressurized while primary users needed high power input.Possible hazards to controllability and stability were analyzed.The result shows that while fly-by-wire passenger aircraft adopts an efficient aerodynamic design,the longitudinal and directional stability is weakened to a certain extent,which needs to be compensated by stability augmentation function of fly-by-wire.The highly augmented flight control requires high deflection rate on control surfaces,the hydraulic flow rate should be guaranteed to greatest extent.In the case of single engine failure,the control and stability characteristics of these aircraft are determined by the bare airframe,flight control law and hydraulic/control surface,which is more complex than those of a conventional aircraft.关键词
放宽静稳定布局/电传操纵/液压系统/飞行控制/适航审定Key words
relaxed static stability/fly-by-wire/hydraulic system/flight control/airworthiness certification引用本文复制引用
周堃,刘超,袁忠大,杨振博,梁卫颖..双发放宽静稳定布局电传客机单发停车对飞机操纵性及稳定性的影响研究[J].工程研究——跨学科视野中的工程,2025,17(3):328-337,10.基金项目
广东省高职院校产教融合创新平台项目:航空维修工程技术产教融合创新平台(2024CJPT012) （2024CJPT012）
