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منابع مشابه
The Utilization of High Fidelity Simulation in the Support of UAV Launch Phase Design: Three Case Studies
Improvement of the launch phase of a jet powered Unmanned Aerial Vehicle (UAV) with Jet Assisted Take Off (JATO), has been the subject of attention in the UAV industry. Use of flight simulation tools reduces the risk and required some amount of flight testing for complex aerospace systems. Full nonlinear equations of motion are used to study and simulate this maneuver and three case studies of ...
متن کاملPerformance Evaluation of the High-altitude Launch Technique to Orbit Using Atmospheric Properties
The purpose of this paper is to perform the feasibility and performance evaluation of the High-altitude launch technique using high altitude atmospheric Properties to near earth orbits. The current propulsion transportation system from Earth to space has been deemed by many to be expensive, unreliable, and an unnecessarily dangerous means of travel to space. It is suggested in this paper to ana...
متن کاملRobust Integral Sliding-Mode Control of an Aerospace Launch Vehicle
An analysis of on-line autonomous robust tracking controller based on variable structure control is presented for an aerospace launch vehicle. Decentralized sliding-mode controller is designed to achieve the decoupled asymptotic tracking of guidance commands upon plant uncertainties and external disturbances. Development and application of the controller for an aerospace launch vehicle during a...
متن کاملThe finite element analysis of the linear hybrid reluctance motor for the electromagnetic launch system
The Electromagnetic Aircraft Launch System (EMALS) is being developed utilizing electrical and electronic technologies. EMALS is emerging in order to replace the existing steam catapult on naval carriers. Recently, the double-sided linear launcher has drawn increasing attention of researchers. This paper presents the design and analysis of the Linear Hybrid Reluctance Motor (LHRM). This new mot...
متن کاملNonlinear Optimal Control Techniques Applied to a Launch Vehicle Autopilot
This paper presents an application of the nonlinear optimal control techniques to the design of launch vehicle autopilots. The optimal control is given by the solution to the Hamilton-Jacobi-Bellman (HJB) equation, which in this case cannot be solved explicity. A method based upon Successive Galerkin Approximation (SGA), is used to obtain an approximate optimal solution. Simulation results invo...
متن کاملTrajectory Optimization for a Multistage Launch Vehicle Using Nonlinear Programming
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...
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عنوان ژورنال:
دوره 105 شماره
صفحات -
تاریخ انتشار 1990