Press Release on Rocket Engines Research: September-2018

Hastening the dawn of hybrid rocket engines

Hybrid burster analysis being done by a University of Alabama in city (UAH) engineering science degree student may hasten the day once an easier, safer, additional economical rocket propels area missions.

At UAH’s Johnson Propulsion Center, Matthew Hitt has experimented with variable solid fuel grain sizes to visualize however they burn at completely different combustion chamber pressures and chemical agent flow rates in a shot to enhance the performance of hybrid engines. [1]

 

LAGRANGIAN APPROACH TO AXISYMMETRIC SPRAY SIMULATION OF PINTLE INJECTOR FOR LIQUID ROCKET ENGINES

Movable pin injectors ar put in in bipropellant rocket engines to manage the mass rate of flow of the propellants and permit deep asphyxiation with high combustion performance. a skinny liquid sheet is made by ejecting the liquid radially round the finish of the pin. This sheet is broken by axially injecting a gas propellant from associate degree annulate gap round the pin nozzle. The device options a movable pin rod, that permits the thickness of the liquid sheet to be modified. the amount of fluid modeling is employed to estimate the variable thickness of the liquid sheet, that is adequate to the pin gap up to a crisis. [2]

 

Structural Design of Thrust Measurement System for Cryogenic Rocket Engines

The Center for house Exploration and Technology analysis (cSETR) at The University of American state at city (UTEP) has been the leader in world on the event of O (LO2) and Liquid methane series (LCH 4) propulsion technologies. one in every of the comes being developed at cSETR may be a suborbital vehicle whose mission is to judge performance parameters, demonstrate restart capability, and demonstrate the system operation in microgravity. This vehicle, referred to as mythical being, can use a 500-lbf LO 2-LCH4 rocket which will be throttled right down to 100-lbf. To accomplish this goal, UTEP partnered with the city County to lease a plot of land next to associate degree airdrome in Fabens, Texas. [3]

 

Multidisciplinary optimisation of bipropellant rocket engines using H2O2 as oxidizer

Today’s rocket chemical propulsion systems for in-orbit use suppose hepatotoxic liquid rocket propellants. the necessity for environmentally-friendly satellite and upper-stage superior engines is seen. This paper covers the subject of optimization of fixed Transfer Orbit apogee bipropellant rocket engines, exploitation extremely targeted oxide as oxidizing agent and lamp oil as fuel. Performance, structural and warmth transfer analyses area unit delineated . [4]

 

Improvement of Cryogenic Space Rocket Engine Ignition: Inert Gas Sweep Effects

Ignition of refrigerant engines of house launchers is typically preceded by a transient part throughout that feeding lines of the combustion chamber square measure sweptwing by associate degree element. This sweeping flow is also prolonged for many milliseconds whereas propellants injection begins.

Despite the very fact that this transient could generate instabilities influencing the ignition method, connected oscillations haven’t been investigated. Experiments were dispensed with atomic number 7 flowing in an exceedingly full scale gadget of HMB7 engine (equipping Ariane five launcher) in thermo-hydrodynamic conditions of similitude with O flow in HM7B (actual oxider propellant of HM7B). [5]

Reference

[1] Hastening the dawn of hybrid rocket engines

Date: July 8, 2015, Source: University of Alabama Huntsville (web link)

[2] LAGRANGIAN APPROACH TO AXISYMMETRIC SPRAY SIMULATION OF PINTLE INJECTOR FOR LIQUID ROCKET ENGINES

Radhakrishnan K, Son M, Lee K, Koo J. LAGRANGIAN APPROACH TO AXISYMMETRIC SPRAY SIMULATION OF PINTLE INJECTOR FOR LIQUID ROCKET ENGINES. Atomization and Sprays. 2018;28(5). (web link)

[3] Structural Design of Thrust Measurement System for Cryogenic Rocket Engines

Moreno Tarango AJ. Structural Design of Thrust Measurement System for Cryogenic Rocket Engines. (web link)

[4] Multidisciplinary optimisation of bipropellant rocket engines using H2O2 as oxidizer

Okninski A, Kindracki J, Wolanski P. Multidisciplinary optimisation of bipropellant rocket engines using H2O2 as oxidiser. Aerospace Science and Technology. 2018 Sep 3. (web link)

[5] Improvement of Cryogenic Space Rocket Engine Ignition: Inert Gas Sweep Effects

Philippe Fauquet-Alekhine1*

1Laboratory for Research in Science of Energy, Montagret, France. (Web link)

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