3. The normal fuzzy attitude control system of the pitch channel is designed based on rigid model of a launch vehicle, which is used to send satellite A. In order to improve the normal fuzzy controller's performance, no-quantification analytic fuzzy method is adopted; and is validated by simulation.

The starting flows past a pitching oscillation Karmam-Trafftz airfoil with 0.12 relative thickness are investigated by numerical calculations for the unsteady N-S equations at Reynolds number 1 000. The emphasis of this study is put on the relation between the complicated vortex structure and the pressure distribution on the body.

The frequency of unsteady wall pressure at the optimum measuring pressure point is in agreement with frequency of delta wing model undergoing a pitching oscillation. The time lag phenomenon among optimum measuring pressure points is presented.

Based on the principle of formation of conjugate tooth contour, the equations of the cam's pitch curve are derived.

The continuity and symmetry of the cam's pitch curve are also analyzed.

The satellite passes chosen for the detailed analysis and modeling lay approximately along the cusp/cleft band from afternoon till prenoon MLT sectors, thus emphasizing the pitch-angle dispersion role with respect to the dispersion due to convection.

Some conclusions about the regime of pitch-angular diffusion into the loss cone are made.

It is assumed that in such a cascade each i-th system (group) of profiles has its own pitch ti (i=1, 2,?, s) and constant phase shift αi of the oscillations between neighboring profiles.

Hydrodynamic problem of the pitching of a catamaran on shallow water

The problem of calculating the pitching of multihull vessels, which are widely used in world shipping, has been inadequately developed.

In the present paper, the method of [4] is used to solve the hydrodynamic problem of the pitching of a catamaran.

The linear problem of inviscid incompressible flow around a high-aspect-ratio wing at an angle of attack and in the presence of steady pitching and rolling rotation is considered.

Many-loop hysteresis of the pitching characteristics of an airplane model with a high-aspect-ratio straight wing at Re = 0.33 × 106 is studied.

The satellite passes chosen for the detailed analysis and modeling lay approximately along the cusp/cleft band from afternoon till prenoon MLT sectors, thus emphasizing the pitch-angle dispersion role with respect to the dispersion due to convection.

The pitch moment coefficient related to the angular velocity of vibration is determined.

A pitch extraction method is considered that employs a decision function whose maximum is greater than the possible spurious maxima of the analyzed signal on the pitch period.

We use data on open star clusters (OSCs) from the Homogeneous Catalog of OSC Parameters to determine some of the parameters of the spiral structure of our Galaxy: the pitch angle of the spiral arms

An increase in the magnetic field strength is shown to have no significant effect on the pitch-angle distribution of the accelerated particles in the solar chromosphere.

Visualization of flow around a pitching airfoil with a rotating nose demonstrates the technically interesting concept of dynamic separation without dynamic stall.

PIV-measurements of the flow above a pitching airfoil were conducted in a transonic wind tunnel.

A high-speed phase-locked interferometry system has been designed and developed for real-time measurements of dynamic stall flow over a pitching airfoil.

A high-speed phase-locked interferometry system has been designed and developed for real-time measurements of dynamic stall flow over a pitching airfoil.

At a pitching rate of 76 million cells per g of mash an ethanol yield of 20.4% (v/v) was obtained.

This paper presents a numerical solution of unsteady supersonic flows for sideslipping wings by means of the characteristic lines network method of unsteady supersonic sources distributed on the wing plane. This paper provides the oscillating mode of undulatory, pitching and rolling harmonic oscillations of the wings with sideslip angles and the methods to calculate its lift, moment coefficient and dynamic stability derivatives (including cross-coupling derivatives). The dynamic stability derivatives of a typical...

This paper presents a numerical solution of unsteady supersonic flows for sideslipping wings by means of the characteristic lines network method of unsteady supersonic sources distributed on the wing plane. This paper provides the oscillating mode of undulatory, pitching and rolling harmonic oscillations of the wings with sideslip angles and the methods to calculate its lift, moment coefficient and dynamic stability derivatives (including cross-coupling derivatives). The dynamic stability derivatives of a typical wing with sideslip angle equal to zero were worked out both by analytical formula in conformity with the conventional quasi-stationary theory and by the present method, and were compared and examined. The results show that the present method is satisfactory.

This paper analyzes the problem of large pitch angle oscillation of a R.P.V.in a flight test,provides a new and quite simple physical simulation method,repeats the oscillation phenomenon in the air successfully,finds out the reasons of failure and presents the improvements.Through several flight tests and applications,it is proved that the conclusions are correct and the improvements are effectual.

A new type of inertial navigation system combining customary platform type with strap-down one is put forward. In this system the azimuth rate platform without azimuth stabilized loop, coordinate-resolver and azimuth syn chronzer is adopted. The azimuth angles of platform and vehicle will be obtained by an integrator from azimuth rate signals measured by an azimuth gyroscope supported on a horizontal gimbal. This type of inertial navigation system is suitable for vehicles without large-pitching maneuver, such...

A new type of inertial navigation system combining customary platform type with strap-down one is put forward. In this system the azimuth rate platform without azimuth stabilized loop, coordinate-resolver and azimuth syn chronzer is adopted. The azimuth angles of platform and vehicle will be obtained by an integrator from azimuth rate signals measured by an azimuth gyroscope supported on a horizontal gimbal. This type of inertial navigation system is suitable for vehicles without large-pitching maneuver, such as transports, aerodynamic and ballistic missiles.Operational principles of the azimuth rate platform, mechanization equations, distinguishing features of initial alignment, and calibration and compensation for drifts of gyroscopes are discussed in this paper. Error propagation characteristics caused by various error sources for navigation positioning, velocity and attitude are simulated on a digital computer. Simplicity in platform structure, small volume and weight, high reliability, possibility of calibration and compensation for drifts of the azimuth gyroscope are the distinctive advantages of this inertial navigation system.Moreover, by using a specific optical system referring to given azimuth angles of land marks and geographical latitudes, it is possible to accomplish not only fast alignment, but also calibration and compensation of horizontal gyroscope.