A model of a linear aerospike rocket nozzle that consists of coupled aerodynamic and structural analyses has been developed. A nonlinear computational fluid dynamics code is used to calculate the aerodynamic thrust, and a three-dimensional finite-element model is used to determine the structural response and weight. The model will be used to demonstrate multidisciplinary design optimization (MD...

BACKGROUNDS/AIMS The future liver remnant (FLR) is usually calculated as a ratio of the remnant liver volume (RLV) to the total functional liver volume (RLV/TFLV). In liver transplantation, it is generally accepted that the ratio of the graft volume to standard liver volume (SLV) needs to be at least 30% to 40% to fit the hepatic metabolic demands of the recipient. The aim of this study was to ...

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 ...

With a mission to Mars no longer merely an idea of science fiction, it is not too early to determine the technology requirements that will ultimately make it possible for humans to establish a long term outpost on Mars. One key aspect is the development of a reliable, reusable launch vehicle to shuttle astronauts between the Mars surface and low Martian orbit. This preliminary design study serv...

Over the last century chemical propellants have been the dominant fuel source for the aviation and aerospace industry, primarily because they are able to provide ample power for a limited cost. However, over the last decade as the price of chemical propellant continues to soar and their detrimental effect on our environment comes to light, there has been a surge to develop an alternative propul...

The thrust chamber’s inner wall suffers high temperature and pressure differences from the coolant channel, which limits life of rocket engine. Life prediction chamber really plays an important role in reusable launch vehicle propulsion systems. Porowski beam model is widely used liquid engine chambers, calculates caused by fatigue, creep, thinning after each firing cycle. In order to analyze c...

Having considered a number of possible future space activities and analysing their implications for future launch vehicle requirements in terms of economics, technological and policy aspects by overcoming the disadvantages of the current launch system, the development of the low-cost fully reusable new space transportation system to and from lower earth orbit, as driven by the clear need for af...

The nuclear thermal rocket (NTR) is a proven, high thrust propulsion technology that has twice the specific impulse (Isp ~900 s) of today’s best chemical rockets. During the Rover and NERVA (Nuclear Engine for Rocket Vehicle Applications) programs, twenty rocket reactors were designed, built and ground tested. These tests demonstrated: (1) a wide range of thrust; (2) high temperature carbide-ba...