• Corpus ID: 116969405

Alternative geometry hybrid rockets for spacecraft orbit transfer

  title={Alternative geometry hybrid rockets for spacecraft orbit transfer},
  author={Gary S. Haag},
  • G. Haag
  • Published 1 August 2001
  • Physics
A Miniaturized Green End-Burning Hybrid Propulsion System for CubeSats
Conventional hybrid rocket motors with thrust levels greater than 5 N rely on forced convection within the boundary layer as the primary heat-transfer mechanism for fuel vaporization. For hybrid
Fuel regression behavior of swirling-injection end-burning hybrid rocket engine
Typical hybrid rockets, using solid plastic fuel and liquid oxidizer, have the potential to become non-explosive propulsion systems based on boundary layer combustion (Takahashi and Shimada, 2018).
Experimental Study and a Short Kinetic Model for High-Temperature Oxidation of Methyl Methacrylate
ABSTRACT Synthetic and natural polymeric esters find applications in transport and construction sectors, where fire safety is an important concern. One polymer that is widely used is poly (methyl
Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism
A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This
Hybrid propulsion system for CubeSat applications
The CubeSats platform has become a common basis for the development and flight of very small, low cost spacecraft-particularly amongst University groups. The smallest CubeSats are just 1 litre in
Development and Three-dimensional Numerical Simulation of a Double-tube Hybrid Rocket Motor
This paper presents a new concept of Hybrid Rocket Motor (HRM) called Double-tube. In this configuration, the gaseous oxidizer is injected using a head end injector and an inner tube with injector
Characterisation of multiple concentric vortices in hybrid rocket combustion chambers
Recent developments in hybrid rocket technology involve producing a coaxial bidirectional vortex flow field through use of tangential oxidiser injection at the base of the combustion chamber. This is


Preliminary CFD analysis of the vortex hybrid rocket chamber and nozzle flow field
A laboratory scale hybrid rocket engine of a unique new design was found to achieve significantly higher fuel regression rates than in classic hybrids operating at similar conditions with similar
A series of static engine firings were conducted to investigate the solid-fuel regression rate behavior and operating characteristics of vortex hybrid rocket engines. The vortex hybrid engine
Thrust Modulation in Hybrid Rocket Engines
An experimental investigation of hybrid rocket engines (HRE) is performed to study the throttling performance within a thrust range of 10:1. In order to improve the throttling properties over the
Reconstruction Technique for Reducing Hybrid-Rocket Combustion Test Data
A new integral technique has been developed for the purpose of analyzing combustion test data in hybrid rocket firings. The method, which utilizes a complete reconstruction of the regression history,
Characterization of Fuel Regression in a Radial Flow Hybrid Rocket
Reliable ignition and stable combustion have been achieved in a lab-scale radial-e ow hybrid rocket engine. The device utilizes 85% hydrogen peroxide and polyethylene and was tested at chamber
Combustion Experiments in Hydrogen Peroxide/Polyethylene Hybrid Rocket with Catalytic Ignition
Resultsfrom 100 tests oflab-scalehybrid rocketmotorsusing hydrogen peroxideand polyethylenearepresented herein. The bulk of the tests utilized 85% hydrogen peroxide with low-density polyethylene. A
Boundary layers in rotating flows
Boundary-layer problems in rotating flows are unique, inasmuch as for many applications a strong interaction exists between the boundary layer and the outer flow. Although such problems may be solved