A dry clutch model with thermal dynamics is added to a driveline model of a heavyduty truck equipped with an automated manual transmission. The model captures driveline oscillations and can be used to simulate how different clutch-control strategies affect vehicle performance, drivability and comfort. Parameters are estimated to fit a heavy-duty truck and the complete model is validated with re...

Abstract This paper introduces the current situation of verticality adjustment launch vehicles at home and abroad, analyses problems risks existing in abroad. A new scheme for vertical a vehicle is proposed this paper. The compares old schemes with actual application certain type vehicle. cancels level measuring instrument on rocket, simplifies operation rocket launching site, reduces design re...

This work is an example of application of nonlinear programming to a problem of three-dimensional trajectory optimization for multistage launch vehicles for geostationary orbit missions. The main objective is to minimize fuel consumption or equivalently to maximize the payload. The launch vehicle considered here, Europa-II, consists of 5 thrust phases and 2 coast phases. Major parameters of the...

Vibrations of launch vehicle conical fairings are investigated. Fairings simulated using thin conic shells. The modal analysis a elastic shell is based on the use developed finite element model an inhomogeneous shell. In general, technique makes it possible to investigate geometrically nonlinear deformation, stability, and post-buckling behavior wide class structure implemented at each step sta...

An overview of some of the activities in hypersonic airbreathing aerodynamics and propulsion airframe integration is presented for the Space Vehicle Technology Institute. The Institute is a multi-university joint NASA-DoD program that was created as a center for research and education in future launch vehicle technologies. Perhaps more than any other type of flight vehicle, next generation spac...

In this paper, a real-time capable Nonlinear Model Predictive Controller (NMPC) is implemented for the attitude control of an upper stage launch vehicle with liquid propellant. A mass spring model is used as an analogy to simulate the disturbance generated by the sloshing propellant. For the implementation of the NMPC, an optimal control problem (OCP) is defined with finite time horizon. The ob...