Rocket

About: Rocket is a research topic. Over the lifetime, 14018 publications have been published within this topic receiving 95852 citations. The topic is also known as: rockets.

A Contribution to the Development of Actual Continuous Detonation Wave Engine

Abstract: During past years, MBDA performed some theoretical and experimental works, mainly in cooperation with LCD laboratory at ENSMA Poitiers, on Pulsed Detonation Engine (PDE) These studies aimed at obtaining a preliminary demonstration of the feasibility of the PDE in both rocket and airbreathing modes and at verifying the interest of such a PDE for operational application : rocket and airbreathing mode experimental evaluation, effect of filling coefficient, effect of a nozzle, thermal, mechanical, acoustic and vibrations environment generated, evaluation of different fuels, performance code development Due to its thermodynamic cycle, the pulsed detonation engine (PDE) has theoretically a higher performance than an other classical propulsion concept using the combustion process (+ 20 to 25% in term of thermal efficiency) Nevertheless, it is necessary to verify that this advantage is not fully compensated by the difficulties, which could be encountered for practical use of the PDE concept or by the complex technology, which could be needed to implement it in an operational flying system Moreover, a PDE a priori generates a severe vibration environment, which can imply higher more severe requirement for all on-board vehicle equipments or subsystems After some in house studies performed in national and international cooperation, MBDA is now focusing its efforts to the development of a demonstration engine led in cooperation with Singapourian DSO in order to really assess the feasibility and the interest of this propulsion concept

Another photon rocket

Abstract: An axially symmetric Robinson - Trautman metric of Petrov type II is interpreted as referring to a rocket accelerated by the anisotropic emission of null fluid. The rocket loses no energy as gravitational radiation.

Onboard Guidance for Reusable Rockets: Aerodynamic Descent and Powered Landing

Abstract: This paper describes a novel general on-board guidance strategy which can be applied toboth the aerodynamically-controlled descent and the powered landing phase of reusable rockets.The proposed guidance method is based on sequential convex optimization applied to a Cartesianrepresentation of the equations of motion. The contributions are an exploitation of convexand non-convex contributions, which are processed separately to maximize the computationalefficiency of the approach, the inclusion of highly nonlinear terms represented by aerodynamicaccelerations, a complete reformulation of the problem based on the use of Euler angle rates ascontrol means, an improved transcription based on the use of a generalized hp pseudospectralmethod, and a dedicated formulation of the aerodynamic guidance problem for reusable rockets.The problem is solved for a 40 kN-class reusable rocket. Results show that the proposedtechnique is a very effective methodology able to satisfy all the constraints acting on the system,and can be potentially employed online to solve the entire descent phase of reusable rockets inreal-time.

A digitalized solar ultraviolet spectrum

Abstract: Digitalized solar ultraviolet spectrum obtained in rocket experiments for use in analysis of upper atmosphere experiments

The Interaction of a Rocket Exhaust with the Lunar Surface

Abstract: Exhaust flow simulation to describe effects of erosion and loss of visibility occurring when exhausting jet impinges dusty lunar surface