A Doe Study on the Hypergolicity of Hydrogen Peroxide With a Rocket Liquid Fuel Based on Monoethanolamine and Ethanol

Maschio, Leandro José; Pereira, Luís Gustavo Ferroni; Meyer, William Müller; Marques, Rodrigo Intini; Vieira, Ricardo

doi:10.1615/intjenergeticmaterialschemprop.2018029025

Cited by 7 publications

(4 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Oxidizer The best oxidizer-propellant combination seems to be pyrrole with 95% hydrogen peroxide. Nevertheless, EEC ignites within 16 milliseconds of contact with HP95 [60], while pyrrole without CuCl 2 catalyst ignites slowly. Pyrrole with 2% CuCl 2 catalyst ignites quickly, but it gives residue on storage [59].…”

Section: Fuelmentioning

confidence: 99%

See 1 more Smart Citation

Feasibility Study For Multiply Reusable Space Launch System

Shubov¹

2021

Preprint

View full text Add to dashboard Cite

A novel concept of orbital launch system in which all stages are reusable is presented. The first two stages called Midpoint Delivery System (MPDS) deliver the next stages to a midpoint. A midpoint is defined by an altitude of 100 km to 120 km and horizontal velocity of 2.8 km/s to 3.2 km/s. MPDS stages decelerate in the atmosphere and perform vertical landing on barges. These stages can be reused daily for many years. The payload is delivered from the midpoint to a 400 km Low Earth Orbit by one or two stage rocket called Midpoint to Orbit Delivery System (MPTO). All of MPTO engines are delivered to LEO. These engines do not return to Earth themselves. They are returned to Earth in packs of 50 to 100 by a Reentry Vehicle. Overall, the fully and multiply reusable launch system

show abstract

Section: Fuelmentioning

confidence: 99%

“…Forth, it is hypergolic with EEC -the mixture of 61% monoethanolamine, 30% ethanol, and 9% hydrated copper nitrate. On contact, EEC ignites with a delay of only 1.6 • 10 −2 s [60].…”

Section: Hypergolic Propellant For Mpto Enginesmentioning

confidence: 99%

Feasibility Study For Multiply Reusable Space Launch System

Shubov¹

2021

Preprint

View full text Add to dashboard Cite

show abstract

“…Despite not having disclosed the IDT, they reported that formulations with furfuryl alcohol ignited faster than those without it for the same catalyst amount. The idea of a blend was further investigated by Maschio et al [28] via DOE. An optimal formulation, capable of igniting in less than 16 ms with 90% HTP, was determined using as fuel components MEA, ethanol, and copper (II) nitrate trihydrate.…”

Section: Secondary Aminesmentioning

confidence: 99%

Monoethanolamine-Based Fuels Hypergolic with Rocket-Grade Hydrogen Peroxide

Caffiero,

Carlotti,

Maggi

2024

Aerospace

View full text Add to dashboard Cite

The object of this work is to study the ignition performances of promising catalytically promoted amino-based green fuels to be used in combination with rocket-grade hydrogen peroxide. The main hypergolic parameter, the ignition delay time, was experimentally determined with an automated drop test setup. Additionally, the kinematic viscosity was experimentally measured, while the CEA2 software was used to determine the ideal rocket performances of the propellants. Three inorganic copper salts were selected as catalysts to be used in combination with monoethanolamine in concentrations ranging from 0.5 wt% to 20 wt%. Then, N,N-dimethylethylenediamine was introduced as part of a blend with monoethanolamine to target the high viscosity and low gravimetric specific impulse of the fuel for the pure monoethanolamine case. Due to the reduced monoethanolamine and low additive content, some formulations were observed to be characterized by gravimetric specific impulse higher than 320 s, and kinematic viscosity lower than 5 cSt while retaining ignition delay times shorter than 30 ms with 98 wt% HTP. Finally, the addition of ethanol to the blend was preliminarily investigated to improve the additive solubility. The effects on the ignition delay time were found to depend on the concentration ratio of the two amines.

show abstract

“…EEC is a mixture of 61% monoethanolamine, 30% ethanol, and 9% hydrated copper nitrate. 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

View full text Add to dashboard Cite

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.

show abstract

A Doe Study on the Hypergolicity of Hydrogen Peroxide With a Rocket Liquid Fuel Based on Monoethanolamine and Ethanol

Cited by 7 publications

References 0 publications

Feasibility Study For Multiply Reusable Space Launch System

Feasibility Study For Multiply Reusable Space Launch System

Monoethanolamine-Based Fuels Hypergolic with Rocket-Grade Hydrogen Peroxide

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

Contact Info

Product

Resources

About