Sentence examples for thrust liquid from inspiring English sources

Small thrust liquid pulsed rocket engines operating in pulsed mode have gained a good reputation in attitude control applications for their potential reliability and efficiency.

Also under CCDev, Blue Origin is ready to start conducting tests of its BE-3 engine thrust chamber assembly — the engine's combustion chamber and nozzle — for the BE-3's 100,000 pounds of thrust, liquid oxygen/liquid hydrogen-fueled rocket motor.

As compared to traditional low-thrust liquid fuel rocket engines attitude control this method gives an opportunity to increase favorable conditions period in running gravity-sensitive technological processes on board the laboratory.

Initially only low-thrust liquid-fuel systems were used for spacecraft onboard propulsion.

Its October test in the Mojave used a version of a 13,600-kg-thrust (30,000-lb) liquid engine that it is developing for the US Air Force's Advanced Upper Stage Engine Program, which aims to find a more capable and affordable upper-stage motor to sit atop the Atlas 5 and Delta 4 rockets it uses to launch most national security payloads.

The objective of work outlined in this paper was to prove experimentally the energy efficiency of Zel'dovich thermodynamic cycle (cycle with detonative combustion of fuel) by direct comparison of thrust performances of liquid-propellant rocket engine (LRE) prototypes operating in continuous-detonation and continuous-combustion modes using gaseous hydrogen as fuel and gaseous oxygen as oxidizer.

The V-2 was 14 metres (47 feet) long, weighed 12,700 13,200 kg (28,000 29,000 pounds) at launching, and developed about 60,000 pounds of thrust, burning alcohol and liquid oxygen.

In addition, an oscillatory motion of the flexible robot body can generate a thrust force in the liquid.

Liquid oxygen and kerosene (Jet A-1) were burned in a range of mixture ratios (2.12 3.07) and chamber pressures (57.3 82.3 bar) in small liquid rocket thrust chambers.

In the present work, a carbon fiber reinforced composite has been adopted to replace the typical heavy metallic closeout structure of a regeneratively cooled thrust chamber of a liquid rocket engine.

The present study proposed a unified framework to simulate multi-physical processes which are crucial for trade-off design of liquid rocket thrust chambers among propulsive performance, regenerative cooling, and pressure budget.