The piston pump is the key power component in the civil aircraft hydraulic system,and the most common pump used in the aviation field is the pressure compensated variable displacement type.In this review paper,a basic...The piston pump is the key power component in the civil aircraft hydraulic system,and the most common pump used in the aviation field is the pressure compensated variable displacement type.In this review paper,a basic introduction to the civil aircraft piston pump is presented,including the classification,structure,working principle,design features,and achievements by some research groups.Then,the future directions of the aircraft pump are reported from various perspectives.Further,the critical technologies are analyzed and summarized in detail from six thrust areas:friction couples,noise reduction,inlet boost,thermal management,fault diagnosis and health management,and mechanical seal.Finally,the challenges and limitations of the research on the aircraft pump are discussed to provide valuable insight for future scholars.展开更多
为了提高汽油机部分负荷下的燃油经济性,该文通过改变废气再循环率(EGR,exhaust gas recirculation)和过量空气系数,在一台增压进气道喷射汽油机上进行试验,研究了过量空气系数与EGR耦合对发动机部分负荷下燃油经济性和排放的影响。结...为了提高汽油机部分负荷下的燃油经济性,该文通过改变废气再循环率(EGR,exhaust gas recirculation)和过量空气系数,在一台增压进气道喷射汽油机上进行试验,研究了过量空气系数与EGR耦合对发动机部分负荷下燃油经济性和排放的影响。结果表明:随着EGR率和过量空气系数α的增加,燃烧循环变动率变大,燃烧持续期变长,且EGR是影响两者的主要因素;泵气损失显著减少,有效燃油消耗率显著降低,与EGR率=0和过量空气系数α=1条件下相比,EGR率=20%和过量空气系数α=1.1条件下的有效燃油消耗率降低了8.37%;随着EGR率的增加,THC(total hydrocarbon)排放增加,但NOx排放显著降低,高达约80%。因此,将三效催化转化器和EGR技术相结合,燃烧稀混合气,可以在满足欧Ⅴ排放法规的同时,大幅提高汽油机部分负荷下的燃油经济性。展开更多
The high degree of centerline curvature and cross-stream pressure gradient in S-inlet ducts gives rise to boundary layer separation and secondary flows, which result in poor pressure recovery and non-uniform flow in t...The high degree of centerline curvature and cross-stream pressure gradient in S-inlet ducts gives rise to boundary layer separation and secondary flows, which result in poor pressure recovery and non-uniform flow in the outlet interface with the engine. The flowfield in ducts is three-dimensional due to the existence of secondary flow, so ordinary two-dimensional actuations have poor effect on reforming the flow. Synthetic jet actuations extended in different spanwise positions were employed to manipulate the flow, and compared with the two-dimensional actuation, The interaction mechanics between flow separation and secondary flow was studied at first. It was found that the secondary flow enhanced Ol~ weakened flow separation depending on the spanwise position of synthetic jet actuators. Moreover, the J flow separation enhanced the secondary flow, thus causing lower pressure recovery and flow distortion in the duct outlet. The actuators located at different spanwise positions will weaken the secondary flows by improving the flow separation to get energetic and uniform main flow.展开更多
In this paper,a model reference adaptive control(MRAC)augmentation method of a linear controller is proposed for air-breathing hypersonic vehicle(AHV)during inlet unstart.With the development of hypersonic flight tech...In this paper,a model reference adaptive control(MRAC)augmentation method of a linear controller is proposed for air-breathing hypersonic vehicle(AHV)during inlet unstart.With the development of hypersonic flight technology,hypersonic vehicles have been gradually moving to the stage of weaponization.During the maneuvers,changes of attitude,Mach number and the back pressure can cause the inlet unstart phenomenon of scramjet.Inlet unstart causes significant changes in the aerodynamics of AHV,which may lead to deterioration of the tracking performance or instability of the control system.Therefore,we firstly establish the model of hypersonic vehicle considering inlet unstart,in which the changes of aerodynamics caused by inlet unstart is described as nonlinear uncertainty.Then,an MRAC augmentation method of a linear controller is proposed and the radial basis function(RBF)neural network is used to schedule the adaptive parameters of MRAC.Furthermore,the Lyapunov function is constructed to prove the stability of the proposed method.Finally,numerical simulations show that compared with the linear control method,the proposed method can stabilize the attitude of the hypersonic vehicle more quickly after the inlet unstart,which provides favorable conditions for inlet restart,thus verifying the effectiveness of the augmentation method proposed in the paper.展开更多
基金financially supported by the National Natural Science Foundation of China(No.51775013)the Aeronautical Science Foundation of China(No.2016ZC09007).
文摘The piston pump is the key power component in the civil aircraft hydraulic system,and the most common pump used in the aviation field is the pressure compensated variable displacement type.In this review paper,a basic introduction to the civil aircraft piston pump is presented,including the classification,structure,working principle,design features,and achievements by some research groups.Then,the future directions of the aircraft pump are reported from various perspectives.Further,the critical technologies are analyzed and summarized in detail from six thrust areas:friction couples,noise reduction,inlet boost,thermal management,fault diagnosis and health management,and mechanical seal.Finally,the challenges and limitations of the research on the aircraft pump are discussed to provide valuable insight for future scholars.
文摘为了提高汽油机部分负荷下的燃油经济性,该文通过改变废气再循环率(EGR,exhaust gas recirculation)和过量空气系数,在一台增压进气道喷射汽油机上进行试验,研究了过量空气系数与EGR耦合对发动机部分负荷下燃油经济性和排放的影响。结果表明:随着EGR率和过量空气系数α的增加,燃烧循环变动率变大,燃烧持续期变长,且EGR是影响两者的主要因素;泵气损失显著减少,有效燃油消耗率显著降低,与EGR率=0和过量空气系数α=1条件下相比,EGR率=20%和过量空气系数α=1.1条件下的有效燃油消耗率降低了8.37%;随着EGR率的增加,THC(total hydrocarbon)排放增加,但NOx排放显著降低,高达约80%。因此,将三效催化转化器和EGR技术相结合,燃烧稀混合气,可以在满足欧Ⅴ排放法规的同时,大幅提高汽油机部分负荷下的燃油经济性。
基金supported by the National Natural Science Foundation of China (Grant No. 50976007)
文摘The high degree of centerline curvature and cross-stream pressure gradient in S-inlet ducts gives rise to boundary layer separation and secondary flows, which result in poor pressure recovery and non-uniform flow in the outlet interface with the engine. The flowfield in ducts is three-dimensional due to the existence of secondary flow, so ordinary two-dimensional actuations have poor effect on reforming the flow. Synthetic jet actuations extended in different spanwise positions were employed to manipulate the flow, and compared with the two-dimensional actuation, The interaction mechanics between flow separation and secondary flow was studied at first. It was found that the secondary flow enhanced Ol~ weakened flow separation depending on the spanwise position of synthetic jet actuators. Moreover, the J flow separation enhanced the secondary flow, thus causing lower pressure recovery and flow distortion in the duct outlet. The actuators located at different spanwise positions will weaken the secondary flows by improving the flow separation to get energetic and uniform main flow.
基金supported by the Foundation of Shanghai Aerospace Science and Technology(SAST2016077)。
文摘In this paper,a model reference adaptive control(MRAC)augmentation method of a linear controller is proposed for air-breathing hypersonic vehicle(AHV)during inlet unstart.With the development of hypersonic flight technology,hypersonic vehicles have been gradually moving to the stage of weaponization.During the maneuvers,changes of attitude,Mach number and the back pressure can cause the inlet unstart phenomenon of scramjet.Inlet unstart causes significant changes in the aerodynamics of AHV,which may lead to deterioration of the tracking performance or instability of the control system.Therefore,we firstly establish the model of hypersonic vehicle considering inlet unstart,in which the changes of aerodynamics caused by inlet unstart is described as nonlinear uncertainty.Then,an MRAC augmentation method of a linear controller is proposed and the radial basis function(RBF)neural network is used to schedule the adaptive parameters of MRAC.Furthermore,the Lyapunov function is constructed to prove the stability of the proposed method.Finally,numerical simulations show that compared with the linear control method,the proposed method can stabilize the attitude of the hypersonic vehicle more quickly after the inlet unstart,which provides favorable conditions for inlet restart,thus verifying the effectiveness of the augmentation method proposed in the paper.
