2020年10月27日 · Given a bypass flowrate of 73 lb/sec at -367 deg F, a nozzle cooling flowrate of 47 lb/sec, and a mixed exit temperature of -193 deg F, we can do a mass-flowrate-weighted average calculation to get a nozzle cooling exit hydrogen temperature of 77 deg F, or 536 deg R, roughly matching the graph above for the nozzle wall temps at the exit.

2017年6月18日 · There are many kinds of nozzles, and many ways to manufacture them. Here is a sampling. Actively cooled nozzles such as the the SSME and F-1 nozzles were constructed by fabricating the individual tubes that made up the cooling channels (1080 tubes in the case of the SSME) and brazing them together in an autoclave.

Rocket nozzle on V2 showing the classic shape. Expansion-deflection nozzle (or Pintle Injector) is a type of propellant injection device for a rocket engine that was first used on a flight vehicle during the Apollo Program in the Lunar Excursion Module's descent engine. Pintle injectors are currently used in SpaceX's Merlin engines:

2020年4月12日 · At the exit plane the Space Shuttle Main Engine (SSME) nozzle was about 2 inches thick. This was a regeneratively cooled nozzle built up of tubing with a manifold encircling the exit. Source: SSME Orientation (annotation mine) Three SSME nozzles in the engine shop at KSC and a closeup. Source: personal photos

2016年11月2日 · The gas at the narrowest part (the throat) of a convergent-divergent nozzle used in a rocket engine is ideally moving at the Mach 1, the speed of sound. This creates a choked flow condition. After the throat, the gas expands, the temperature drops, and because of the Venturi effect, it speeds to beyond Mach 1.

The force from the rocket engine is transmitted to the rocket structure by the Thrust Frame Adapter. This is a framework rated to handle the newtons of force created by the engine. The spacecraft's load-bearing skeleton is built on top of the thrust frame adapter, and the spacecraft components are attached to the skeleton. (image source)

2020年9月16日 · The efficiency of rocket engine nozzles depends greatly on their expansion ratio an how well the ambient pressure matches the rocket nozzles exit pressure. An optimal expansion ratio means that there is a straight stream of exhaust leaving the rocket, while under- or overexpansion ( picture ) are inefficient, possibly fatal if the exhaust is ...

2022年1月4日 · A rocket chemical system can gave a hundred or so individual species including ionized atoms. Reaction schemes to be analyzed can compromize hundreds of competing reactions. An ineffectively designed nozzle can keep a propellent from releasing all it's energy into gas velocity and result in a performance decrement.

2024年7月21日 · From a search for "Rao rocket nozzle" (on startpage com) I was able to download two of Rao's papers (Jet Propulsion journal of June 1958 as rao_1958.pdf and ARS Journal of Nov. 1961). NASA publication 19830016278.pdf Perfect Bell Nozzle Parametric and Optimization Curves of May 1983 by Tuttle and Blount is available from ntrs.nasa.gov

2020年6月6日 · The hardest part of the engine to mass produce is the electro-plating of nickel cobalt on the chamber. We create this thick metal jacket that takes the primary stress of the pressure vessel and it’s plated one molecule at a time.