A Device for Soft Separation of Spacecraft from Launch Vehicle
نویسندگان
چکیده
منابع مشابه
Trajectory 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...
متن کاملUsing Generic Telemetry Prognostic Algorithms for Launch Vehicle and Spacecraft Independent Failure Analysis Service
Current failure analysis practices use diagnostic technology developed over the past 100 years of designing and manufacturing electrical and mechanical equipment to identify root cause of equipment failure requiring expertise with the equipment under analysis. If the equipment that failed had telemetry embedded, prognostic algorithms can be used to identify the deterministic behavior in complet...
متن کاملMaterials for Launch Vehicle Structures
This chapter concerns materials for expendable and reusable launch vehicle (LV) structures. An emphasis is placed on applications and design requirements, and how these requirements are met by the optimum choice of materials. Structural analysis and qualification strategies, which cannot be separated from the materials selection process, are described. A launch vehicle is an airborne system tha...
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 کاملStage separation dynamic analysis of upper stage of a multistage launch vehicle using retro rockets
K e y w o r d s J e t t i s o n i n g system, Retro-rocket, Jet damping, Pyro, Relative velocity, Relative distance, Launch vehicle. N O M E N C L A T U R E Az launch azimuth (deg) h altitude of separation (km) I inertia tensor (kg-m 2) t Time (s) mM, ms mass of the ongoing and spent bodies (kg) RE, Rp, Rs Earth's equatorial radius, polar radius, radius at the surface (km) r, q, p body angular ...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Kosmičeskaâ tehnika. Raketnoe vooruženie
سال: 2018
ISSN: 2617-5525,2617-5533
DOI: 10.33136/stma2018.01.069