Assessing the Performance of a Green Liquid Fuel Hypergolic With Hydrogen Peroxide in a 50 N Bipropellant Thruster

Maschio, Leandro José; Araújo, Emmanuel Péres de; Pereira, Luís Gustavo Ferroni; Gouvêa, Leonardo Henrique; Vieira, Ricardo

doi:10.1615/intjenergeticmaterialschemprop.2020032684

Cited by 4 publications

(2 citation statements)

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“…On contact, EEC ignites with a delay of only 1.6 • 10 −2 s [24]. A 50 N thruster using EEC and 90% hydrogen peroxide has been tested [25].…”

Section: Available Liquid Propellantsmentioning

confidence: 99%

Electric Rocket Launcher Aircraft—Drone-Launched Short Range Rocket System

Shubov

2023

Aerospace

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This paper is concerned with the idea of a significant improvement of state-of-the-art short-range rockets by means of using rocket artillery systems. Such a system consists of a rocket launcher aircraft (RLA) and a drone-launched short range rocket (DLSRR). An RLA is a reusable first stage of a military rocket. A DLSRR is the expendable second stage, which flies to the target. RLA-DLSRR systems have not yet been built, but they have been described in previous works by the author. State-of-the-art rocket systems are completely expendable and, hence, extremely expensive. No rocket artillery system with a reusable first stage has been built so far. Civilian spaceships with reusable first stages have been successful since 2015. In an electrically pumped rocket engine, the fuel and oxidizer are pumped into a combustion chamber by an electric-motor-driven pump. The electric motor is powered by a battery bank. Electrically pumped rocket engines would further decrease the cost of RLA-DLSRR systems. These engines are less expensive and more reliable then conventional rocket engines. In the present paper, it is shown that commercially available lithium polymer battery banks, as well as high specific power electric motors, provide sufficient power for the rocket engines needed for RLA-DLSRR systems. In the example given, it is calculated that an ERLA–DLSRR system with a liftoff mass of 15 tons can deliver a 210 kg payload to a range of up to 567 km with an impact velocity of up to 2415 m/s.

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“…On contact, EEC ignites with a delay of only 1.6 • 10 −2 s [24]. A 50 N thruster using EEC and 90% hydrogen peroxide has been tested [25].…”

Section: Available Liquid Propellantsmentioning

confidence: 99%

Electric Rocket Launcher Aircraft—Drone-Launched Short Range Rocket System

Shubov

2023

Aerospace

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“…The chemical reaction between the fuel and the oxidizer occurs so 6 rapidly that enough heat is generated to continue the combustion reaction in the engine, producing thrust. Maschio et al, presented the design and firing test of a 50 N bipropellant thruster based on the H 2 O 2 90 wt% − monoethanolamine-ethanol hypergolic pair catalyzed by cupric ions [9]. They performed 5 s firing test, conducted under a swirl injection scheme, yielded average values of 50.38 N, 147 s, and 1210 m/s for thrust, I sp , and c*, respectively, with the target value of 5 bar for the chamber pressure being reached after 2 s of operation.…”

Section: Hypergolic Systems With Hydrogen Peroxide Oxidizermentioning

confidence: 99%

Hypergolic Systems based on Hydrogen Peroxide Oxidizer

Türker

2023

EJCS

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Hydrogen peroxide, H2O2, is a promising and nontoxic oxidant. In recent years considerable attention has been paid to the development of hypergolic system compositions, because the use of them not only markedly simplifies the engine design and rocket system operation but also provides the possibility of their repeated use. Moreover, their high performance, high environmental compatibility and low toxicity make them highly preferable. The present review considers recent works on hypergolic systems involving hydrogen peroxide as the oxidizer and various green propellants of organic and inorganic nature with or without certain additives.

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