Using equivalent burn time to improve regression characterization of CAMUI type hybrid rocket engine

2017 ◽  
Author(s):  
Tor Viscor ◽  
Harunori Nagata
Keyword(s):  
Rocket Engine ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

scholarly journals The HyEnD stern hybrid sounding rocket project

2019 ◽  
Author(s):  
M. Kobald ◽  
C. Schmierer ◽  
U. Fischer ◽  
K. Tomilin ◽  
A. Petrarolo ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Operating Conditions ◽  
Chamber Pressure ◽  
Sounding Rocket ◽  
Small Scale ◽  
Stable Operation ◽  
Hybrid Rocket ◽  
Wide Range ◽  
Hybrid Rocket Engine

The student team Hybrid Engine Development (HyEnD) of the University of Stuttgart is taking part with the Institute of Space Systems (IRS) in the DLR educational program STERN (Studentische Experimentalraketen). This program supports students at German universities to design, build, and launch an experimental rocket within a 3-year project time frame. HyEnD is developing a hybrid rocket called HEROS (Hybrid Experimental Rocket Stuttgart) with a design thrust of 10 kN, a total impulse of over 100 kN·s, and an expected liftoff weight up to 175 kg. HEROS is planned to be launched in October 2015 from Esrange in Sweden to an expected flight altitude of 40 to 50 km. The current altitude record for amateur rockets in Europe is at approximately 21 km. The propulsion system of HEROS is called HyRES (Hybrid Rocket Engine Stuttgart) and uses a paraffin-based solid fuel and nitrous oxide (N2O) as a liquid oxidizer. The development and the test campaign of HyRES is described in detail. The main goals of the test campaign are to achieve a combustion efficiency higher than 90% and provide stable operation with low combustion chamber pressure fluctuations. The successful design and testing of the HyRES engine was enabled by the evaluation and characterization of a small-scale demonstrator engine. The 500-newton hybrid rocket engine, called MIRAS (MIcro RAkete Stuttgart), has also been developed in the course of the STERN project as a technology demonstrator. During this test campaign, a ballistic characterization of paraffin-based hybrid rocket fuels with different additives in combination with N2O and a performance evaluation were carried out. A wide range of operating conditions, fuel compositions, injector geometries, and engine configurations were evaluated with this engine. Effects of different injector geometries and postcombustion chamber designs on the engine performance were analyzed. Additionally, the appearance of combustion instabilities under certain conditions, their effects, and possible mitigation techniques were also investigated. Concluding, the development and construction of an advanced, lightweight hybrid sounding rocket for the given requirements and budget within the DLR STERN program are described herein. The most important parts include a high thrust hybrid rocket engine, the development of a light weight oxidizer tank, pyrotechnical valves, carbon fiber rocket structure, recovery systems, and onboard electronics.

Rotational and Quasiviscous Cold Flow Models for Axisymmetric Hybrid Propellant Chambers

2010 ◽  
Vol 132 (10) ◽  
Author(s):  
Joseph Majdalani ◽  
Michel Akiki
Keyword(s):  
Rocket Engine ◽  
Navier Stokes ◽  
Mathematical Treatment ◽  
Hybrid Rocket ◽  
Mean Flow ◽  
Viscous Effects ◽  
Navier Stokes Equation ◽  
Flow Models ◽  
Hybrid Rocket Engine ◽  
Wall Injection

In this work, we present two simple mean flow solutions that mimic the bulk gas motion inside a full-length, cylindrical hybrid rocket engine. Two distinct methods are used. The first is based on steady, axisymmetric, rotational, and incompressible flow conditions. It leads to an Eulerian solution that observes the normal sidewall mass injection condition while assuming a sinusoidal injection profile at the head end wall. The second approach constitutes a slight improvement over the first in its inclusion of viscous effects. At the outset, a first order viscous approximation is constructed using regular perturbations in the reciprocal of the wall injection Reynolds number. The asymptotic approximation is derived from a general similarity reduced Navier–Stokes equation for a viscous tube with regressing porous walls. It is then compared and shown to agree remarkably well with two existing solutions. The resulting formulations enable us to model the streamtubes observed in conventional hybrid engines in which the parallel motion of gaseous oxidizer is coupled with the cross-streamwise (i.e., sidewall) addition of solid fuel. Furthermore, estimates for pressure, velocity, and vorticity distributions in the simulated engine are provided in closed form. Our idealized hybrid engine is modeled as a porous circular-port chamber with head end injection. The mathematical treatment is based on a standard similarity approach that is tailored to permit sinusoidal injection at the head end.

Optimization of a H2O2 Gas Generator for a Hybrid Rocket Engine

2013 ◽  
Author(s):  
Martina Faenza ◽  
Federico Moretto ◽  
Alberto Bettella ◽  
Daniele Pavarin
Keyword(s):  
Rocket Engine ◽  
Hybrid Rocket ◽  
Gas Generator ◽  
Hybrid Rocket Engine

90% Hydrogen Peroxide/Polyethylene Solid Fuel Hybrid Rocket Engine

2005 ◽  
Author(s):  
Nobuo Tsujikado ◽  
Masatoshi Koshimae ◽  
Rikiya Ishikawa ◽  
Kazuki Kitahara ◽  
Atsushi Ishihara
Keyword(s):  
Hydrogen Peroxide ◽  
Solid Fuel ◽  
Rocket Engine ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine
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