Journal ArticleDOI
On use of hybrid rocket propulsion for suborbital vehicles
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TLDR
In this article, the authors present results of optimisation of sounding rockets using hybrid propulsion and provide insight into the sensitivity of different design parameters on performance of hybrid sounding rockets and delve into the potential and challenges of using hybrid rocket technology for expendable suborbital applications.About:
This article is published in Acta Astronautica.The article was published on 2018-04-01. It has received 28 citations till now. The article focuses on the topics: Rocket & Spacecraft propulsion.read more
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Journal ArticleDOI
Development of the ILR-33 “Amber” sounding rocket for microgravity experimentation
Blazej Marciniak,Adam Okninski,Bartosz Bartkowiak,Michal Pakosz,Kamil Sobczak,Wojciech Florczuk,Damian Kaniewski,Jan Matyszewski,Pawel Nowakowski,Dawid Cieslinski,Grzegorz Rarata,Pawel Surmacz,Dominik Kublik,Damian Rysak,Jaromir Smetek,Piotr Wolanski +15 more
TL;DR: The ILR-33 sounding rocket for microgravity experiments has been developed at the Institute of Aviation in Warsaw, Poland as discussed by the authors, which enables performing experiments in microgravity for almost 150 seconds with an apogee over 100 km.
Journal ArticleDOI
Effect of multi-location swirl injection on the performance of hybrid rocket motor
Bala Vignesh,Rajiv Kumar +1 more
TL;DR: In this paper, the effect of multi-location swirl injection on the improvement of regression rate and combustion efficiency of hybrid rocket by using two different length to diameter (L/D) ratio of the motor.
Journal ArticleDOI
Numerical and experimental investigation of throttleable hybrid rocket motor with aerospike nozzle
TL;DR: In this paper, the performance of the throttleable hybrid rocket motors with the aerospike nozzle and that with the de Laval nozzle were compared. And the results showed that the combination of throttleable HRMs and the aeraspike nozzle has the advantages to improve performance of HRMs theoretically.
Journal ArticleDOI
Transient investigation of nozzle erosion in a long-time working hybrid rocket motor
Hui Tian,Hui Tian,He Lingfei,He Lingfei,Yu Ruipeng,Yu Ruipeng,Sheng Zhao,Pengfei Wang,Guobiao Cai,Guobiao Cai,Yuanjun Zhang,Yuanjun Zhang +11 more
TL;DR: In this article, an unsteady numerical model of carbon-based nozzle erosion is established, and a dynamic grid technique is adopted to simulate the regression process of the nozzle surface, based on which numerical simulations on a hydrogen peroxide(HP)/hydroxyl-terminated polybutadiene (HTPB) hybrid motor have been performed in a long-time working process.
Journal ArticleDOI
Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer
Adam Okninski,Pawel Surmacz,Bartosz Bartkowiak,Tobiasz Mayer,Kamil Sobczak,Michal Pakosz,Damian Kaniewski,Jan Matyszewski,Grzegorz Rarata,Piotr Wolanski +9 more
TL;DR: The ILR-33 AMBER suborbital rocket as mentioned in this paper uses 98% hydrogen peroxide as an oxidizer to achieve in-flight utilization for the first time in 2017.
References
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Book
Rocket Propulsion Elements
TL;DR: In this paper, the authors defined and defined the fundamentals of solid propellant rocket propulsion systems, including propulsion system design, propulsion system parameters, and propulsion system performance analysis, as well as propulsion system testing.
Journal ArticleDOI
Scale-Up Tests of High Regression Rate Paraffin-Based Hybrid Rocket Fuels
TL;DR: In this paper, a class of paraffin-based fuels that burn at surface regression rates that are three to four times that of conventional hybrid fuels is identified, which is a natural attribute of the fuel material, and the use of oxidizing additives or other regression rate enhancement schemes is not required.
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Solid-Fuel Regression Rate Behavior of Vortex Hybrid Rocket Engines
TL;DR: In this paper, the authors investigate the behavior and properties of a vortex hybrid engine with a cylindrical fuel port, where the oxidizer is injected through a swirl injector located between the aft end of the fuel grain and the inlet to the converging portion of the exit nozzle.
Book
A Method of Reaching Extreme Altitudes
TL;DR: In this paper, the authors state the general principles and possibilities of the method of reaching great altitudes with multiple charge rockets, from which the exploded gases are ejected with high efficiency.