Operation of solid rockets in comparison with hybrid rockets during the STERN project

Schüttauf, Katharina; Stamminger, Andreas; Lappöhn, Karsten; Ciezki, Helmut; Kitsche, Wolfgang

doi:10.2514/6.2016-2613

Cited by 4 publications

(2 citation statements)

References 2 publications

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“…It is, however, rarely considered for use in launch vehicles (despite some examples: [21]) due to low performance. It is mostly implemented in suborbital vehicles [2,22,23], commonly being used by student and hobbyist rocketry groups [24]. The limited heritage and thermal sensitivity make it a rare choice for satellite propulsion developments.…”

Section: Introductionmentioning

confidence: 99%

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

et al. 2021

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This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.

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Section: Introductionmentioning

confidence: 99%

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

et al. 2021

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“…Also, of particular interest in current hybrid rocket design efforts are the economic considerations, with low-cost solutions being evaluated. [2][3][4] [5][6] [7] [8] Unlike more conventional rocket designs that utilize a liquid fuel and liquid oxidizer (liquid fuel rocket motor) or a solid oxidizer entrained within a solid fuel grain (solid fuel rocket motor), a hybrid design typically incorporates a liquid oxidizer and a solid fuel grain. This configuration leverages the advantages of both the liquid fuel rocket, which is the ability to start and stop the motor as well as throttling the thrust level, and the solid fuel rocket, which is a higher thrust density for a given motor size.…”

Section: Introductionmentioning

confidence: 99%

Development of a Concept Hybrid Rocket Demonstrator

Birch

2022 ASEE Annual Conference &Amp; Exposition Proceedings

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Most conventional rockets are of an either solid fuel or liquid fuel configuration. Nearly all production rocket motors produced throughout modern history are one of these two types. Conversely, a hybrid rocket utilizes a solid fuel grain and liquid oxidizer, thus capitalizing on the inherent advantages of both designs. A hybrid rocket exploits the power density (power per unit volume) of a solid fuel rocket, and the start-stop and throttling capability of a liquid fuel rocket. To date, only a few hybrid rocket designs have been developed to a production level configuration. This type of rocket motor technology remains largely in the experimental domain. [1] The Concept Hybrid Rocket Demonstrator (CHRD) is a small scale, modular, low-cost hybrid rocket design, for use in hybrid rocket research as well as educational applications in senior capstone curriculum for an undergraduate Mechanical or Aerospace Engineering or Engineering Technology program. Basic research activities include investigations of rocket fuel types and fuel grain port configurations, ignition systems, oxidizer delivery systems, rocket nozzle materials and aerodynamics, instrumentation schemes, and analytic modeling of rocket performance using computational software.The first generation of CHRD has been designed, fabricated, and tested successfully. A small rocket motor approximately two inches in diameter and ten inches long was fired multiple times during the spring of 2021, with preliminary results of rocket performance being documented. The current rocket prototype was the product of two consecutive academic years of senior capstone teams' efforts. The design, fabrication, and testing were supervised by a Mechanical Engineering faculty, who assumed the role of project manager and chief investigator.

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