Overview on hybrid propulsion

Abstract

Aside of research works, this historical survey shows propulsion units used by students for small satellites and for gas generation, or those for the Space Ship One, even if LOx/HTPB was studied and tested in large motors for its potential very low cost; however, this combination highlights a series of technical problems without any performance advantage over the existing LOx/Kerosene family and never been operational for ETO applications. The particularity of hybrid propulsion is to use the state-of-the-art of both liquids and solids; the only show stopper is the propellant itself. The past work focused on LOx/HTPB (selected for its low cost) appears to be a dead-end (combustion problems and global low performances resulting from a high level of residuals). The solution that appears through the past experience is the addition of hydrides to a binder (HTPB or other) or to a binder and a homogeneous fuel or a mixture of both, with or without others additives; within these solutions some will not present any manufacturing problem and some may have a low cost. Nevertheless, the studies of the following phases have to demonstrate the compatibility of the potential regression rate range with a high-performance global design of a hybrid Motor and the manufacturing at a reasonable cost of a hydride giving a high level of performances.

Variations and Control of Thrust and Mixture Ratio in Hybrid Rocket Motors

“…This solution has been tested successfully in several occasions, for example by ONERA [70,71], UTC [10][11][12] and in the JIRAD program [20], reaching throttling ratio as high as 10:1.…”

Development and Test of Magnesium-Based Additive for Hybrid Rockets Fuels

“…In order to study the combustion characteristics of paraffin doped with different percentages of Magnesium Boride a series of test were carried out at the RMA Laboratory for Energetic Materials and its facilities are equipped with chemical laboratory, sensor calibration set up and a test bunker. The regression rate calculations were performed as proposed by [4] but taking into account the different fuel geometry.…”

“…The addition of energetic and/or nano-sized combustible particles can also increase mass-burning rates of the solid fuels [4] and at the same time produce more robust solid fuel grains. In this way, this research was conducted with the aim to develop a class of new paraffin-based fuels and this paper presents the initial results based on a commercial Magnesium Diboride (MgB2) powder used as additive to the baseline fuel.…”

“…MSc, faculty of Gama at University of Brasilia, artur.bertoldi@aerospace.unb.br 2. PhD student, chemistry department at Royal Military Academy of Belgium, mohammed.bouziane@dymasec.be3 PhD student, aero-thermo-mechanics department at Université Libre de Bruxelles, da.hae.lee@ulb.ac.be 4. Professor, aero-thermo-mechanics department at Université Libre de Bruxelles, patrick.hendrick@ulb.ac.be 5.…”

Development and Testing of a Lab-scale Test-bench for Hybrid Rocket Engines

“…The early development of hybrid rocket motors (HRMs) backdates to the 1930 [1], but only recently they have renewed interest as research topic due to a demand for cost-cutting related to the development of liquid engines and safety concerns about solid propulsion systems. In the hybrids, once that the oxidizer and fuel are in distinct parts of 1 PhD student, chemistry department at Royal Military Academy of Belgium, mohammed.bouziane@dymasec.be 2 Prof. MSc, faculty of Gama at University of Brasilia, artur.bertoldi@aerospace.unb.br. 3 Postdoc, aero-thermo-mechanics department at Université Libre de Bruxelles, praskovia.milova@ulb.ac.be.…”