The CAI course ware of the aircraft hydraulic system was exploited based on VB6.0 platform and applied to the teaching and experimental teaching of the core specialized course—Aircraft Systems. It has achieved good results.

O-rings are widely used for sealing in aircraft systems. Strict quality control in O-ring production process is a criticle factor for implementing the sealing safety in aircraft systems.

This thesis is a survey of Civil Aviation English, an ESP (English for Specific Purpose) English, especially with the highlight on the lexical characteristics of the professional language used in the two major aircraft systems, Boeing and Airbus.

As aircraft systems become increasingly complex and the radio frequency spectra becomes more extensive,it is necessary to adopte a new approach to analysis of electromagnetic interference (EMI) in aircraft.

Technology of radar absorbing materials (RAM) is one of the important stealth technologies,and widely applied in stealth weapons,especially stealth aircraft systems.

The technology of radarwave absorbing material (RAM) is one of the most important stealthy technologies,and is widely applied in stealthy weapon,especially in stealthy aircraft systems.

This paper describes results of reliability verification for a ceratin typ e of aircraft for initial field verification in China,it also gives check and a nalysis on the basic reliabilit y of aircraft systems and main airborne equipmen t,points out the problems a vailable and puts forward the solutions to them.

Aerodynamic coefficient identification for time-varying aircraft system has been studied. Usually, the time-varying system identification is quite difficult. On the basis of practical measurement in flight tests and by analyzing trend of the coefficients in aircraft time-varying differential equations, it is possible to transform the individual time-varying coefficient into a known function multi- plied by an unknown constant. These unknown constants are referred to as undefined coefficients....

Aerodynamic coefficient identification for time-varying aircraft system has been studied. Usually, the time-varying system identification is quite difficult. On the basis of practical measurement in flight tests and by analyzing trend of the coefficients in aircraft time-varying differential equations, it is possible to transform the individual time-varying coefficient into a known function multi- plied by an unknown constant. These unknown constants are referred to as undefined coefficients. With the aid of the Newton-Raphson method extended to the time-varying coefficient differential equations the undefined coefficients can be evaluated by iteration calculation. In this way the complicated time-varying aircraft identification can be carried out.In order to verify this calculation the aerodynamic coefficients of an aircraft have been evaluated by the data taken from one of its unsteady flight, and the reliability of aerodynamic coefficients obtained from this identification has been discussed. The calculation results matched very well the test data and made a contribution to the improvement of aircraft fight tests.

An aero-engine can be regarded as a subsystem of the aircraft system. It is obvious that engine performances, weight and dimensions have a strong effect on the aircraft flight performances. For a given flight mission, the optimal engine scheme must be able to meet the flight requirements with the greatest possibility. From the viewpoint of system engineering, a method for integrated selection of the optimal engine cycle parameters and the control scheme is proposed, which takes the matching...

An aero-engine can be regarded as a subsystem of the aircraft system. It is obvious that engine performances, weight and dimensions have a strong effect on the aircraft flight performances. For a given flight mission, the optimal engine scheme must be able to meet the flight requirements with the greatest possibility. From the viewpoint of system engineering, a method for integrated selection of the optimal engine cycle parameters and the control scheme is proposed, which takes the matching and interaction between the engine and the aircraft. A rapid method for predicting turbojet or turbofan engine off-design performances was adopted and an empirical formula estimating the engine weight was developed.An optimization of an augmented engine scheme meeting the requirements of a modification has been accomplished as an example. The results show that the optimum cycle parameters and the control scheme are quite different if the mission, the requirements of modification or the technical constraints are varied. Therefore, the integrated selection of engine cycle parameters is of great importance.

The effects of external combined resistance (total resistive value,3-30 Cm H2O·L-1·S) on respiratory flow rate,mask cavity pre sure swing (p) and respiratory discomfort were studied in 114 pilots unde- light physical loading conditions ( 250 Kg·m·min-1).The experimental data of 17 physiological and psychophysical variables were analysed by correlation,stepwise regression and probit analysis.The results showed that p or extra respira-tory work per unit ventilation ( W/L ) might be selected as an objective index...

The effects of external combined resistance (total resistive value,3-30 Cm H2O·L-1·S) on respiratory flow rate,mask cavity pre sure swing (p) and respiratory discomfort were studied in 114 pilots unde- light physical loading conditions ( 250 Kg·m·min-1).The experimental data of 17 physiological and psychophysical variables were analysed by correlation,stepwise regression and probit analysis.The results showed that p or extra respira-tory work per unit ventilation ( W/L ) might be selected as an objective index for respiratory discomfort,with p being more applicable in practical work.The probit analysis reveals that 90% of pilots breathing through aircraft oxygen system should experience no respiratory discomfort,if the p does not exceed 6.1 Cm H2O,or W/L not exceed 0.047 Kg·m·L-1 and that 90% should experience a lesser than mild degree of discomfort,if the P does not exceed 7,9 Cm H2O,or W/L not exceed 0.061 Kg·m·L-1 The significance of our findings for revising current physiological standard of aircraft system is discussed.