Fuel Regression Rate Characterization Using a Laboratory Scale Nitrous Oxide Hybrid Propulsion System

2006 ◽  
Author(s):  
Kevin Lohner ◽  
Jonny Dyer ◽  
Eric Doran ◽  
Zachary Dunn ◽  
Greg Zilliac
Keyword(s):  
Nitrous Oxide ◽  
Propulsion System ◽  
Laboratory Scale ◽  
Regression Rate ◽  
Hybrid Propulsion

scholarly journals Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages

Aerospace ◽  
2021 ◽  
Vol 8 (7) ◽  
pp. 190
Author(s):  
Francesco Barato
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Diameter Ratio ◽  
Propulsion System ◽  
Burning Time ◽  
Regression Rate ◽  
Hybrid Propulsion ◽  
Deep Impact ◽  
Time Ratio ◽  
Hybrid Rockets

Ablative-cooled hybrid rockets could potentially combine a similar versatility of a liquid propulsion system with a much simplified architecture. These characteristics make this kind of propulsion attractive, among others, for applications such as satellites and upper stages. In this paper, the use of hybrid rockets for those situations is reviewed. It is shown that, for a competitive implementation, several challenges need to be addressed, which are not the general ones often discussed in the hybrid literature. In particular, the optimal thrust to burning time ratio, which is often relatively low in liquid engines, has a deep impact on the grain geometry, that, in turn, must comply some constrains. The regression rate sometime needs to be tailored in order to avoid unreasonable grain shapes, with the consequence that the dimensional trends start to follow some sort of counter-intuitive behavior. The length to diameter ratio of the hybrid combustion chamber imposes some packaging issues in order to compact the whole propulsion system. Finally, the heat soak-back during long off phases between multiple burns could compromise the integrity of the case and of the solid fuel. Therefore, if the advantages of hybrid propulsion are to be exploited, the aspects mentioned in this paper shall be carefully considered and properly faced.

AQUASONIC – A Sounding Rocket Based on Hybrid Propulsion

2016 ◽  
Vol 831 ◽  
pp. 3-13 ◽  
Author(s):  
Uwe Apel ◽  
Alexander Baumann ◽  
Christian Dierken ◽  
Thilo Kunath
Keyword(s):  
Nitrous Oxide ◽  
Propulsion System ◽  
Main Element ◽  
Sounding Rocket ◽  
Launch Vehicles ◽  
Flight Altitude ◽  
Hybrid Propulsion ◽  
Space Industry ◽  
Space Agency ◽  
Research Organisations

The AQUASONIC project is aimed to develop a sounding rocket including a hybrid propulsion system based on the propellant combination nitrous oxide and polyethylene. It takes place in the frame of the STERN (Student Experimental Rockets) programme founded by the German Space Agency (DLR) in order to promote students in the area of launch vehicles. Main element of the project is the AQUASONIC rocket, which shall reach a flight altitude of 5-6 km and a velocity of MACH 1. All major activities like design, manufacturing, verification and, finally, the launch campaign will be performed by students. The rocket shall be launched at Esrange Space Centre (Sweden) in 2016. Thus, students are able to apply their skills and knowledge to a real project like it is conducted by the space industry or research organisations.

Modeling and Control of Hybrid Propulsion System for Ground Vehicles

2018 ◽  
Author(s):  
Yuan Zou ◽  
Junqiu Li ◽  
Xiaosong Hu ◽  
Yann Chamaillard
Keyword(s):  
Propulsion System ◽  
Ground Vehicles ◽  
Hybrid Propulsion ◽  
Modeling And Control ◽  
And Control

Electric Machines Calculation for a Hybrid Propulsion System of Commuter Airliner

2020 ◽  
Author(s):  
Anton Varyukhin ◽  
Viktor Zakharchenko ◽  
Mikhail Gordin ◽  
Flyur Ismagilov ◽  
Vyacheslav Vavilov ◽  
...  
Keyword(s):  
Electric Machines ◽  
Propulsion System ◽  
Hybrid Propulsion

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

2021 ◽  
pp. 095441002110253
Author(s):  
Babak Aryana
Keyword(s):  
High Performance ◽  
Static Condition ◽  
Propulsion System ◽  
Hybrid Propulsion ◽  
Pulse Detonation ◽  
Low Emission ◽  
Wide Range ◽  
Exit Nozzle ◽  
Distributed Propulsion ◽  
Detonation Process

This two-part article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part A of this article explains the design process comprising intake, compressor, detonation process, diffuser, axial turbine, and the exit nozzle. The main target is to design a high-performance low emission propulsion system capable of serving in a wide range of altitudes and flight Mach numbers that covers altitudes up to 20,000 m and flight Mach number up to the hypersonic edge. Designing the propulsion set, the design point is considered at the static condition in the sea level. Design results show the propulsion set can satisfy all requirements necessary for its mission.

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