Design and testing of an upper stage hybrid propulsion system using hydrogen peroxide oxidizer

2000 ◽  
Author(s):  
A. Prince ◽  
R. Carpenter ◽  
T. Boardman ◽  
T. Abel ◽  
S. Claflin
Keyword(s):  
Hydrogen Peroxide ◽  
Propulsion System ◽  
Hybrid Propulsion ◽  
Upper Stage ◽  
Design And Testing

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

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.

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.

Upper Stage Propulsion System for H-IIA Launch Vehicle

2002 ◽  
Author(s):  
Masumi Fujita ◽  
Hiroshi Aoki ◽  
Toshihiko Nakagawa ◽  
Tatsuru Tokunaga ◽  
Masaaki Yasui ◽  
...  
Keyword(s):  
Launch Vehicle ◽  
Propulsion System ◽  
Upper Stage

A New Type of Gas Turbine Based-Hybrid Propulsion System: Part 1—Concept Development, Definition of Mission Parameters and Preliminary Sizing

2000 ◽  
Author(s):  
Emiliano Cioffarelli ◽  
Enrico Sciubba
Keyword(s):  
Gas Turbine ◽  
Combustion Engine ◽  
Development Program ◽  
Propulsion System ◽  
Medium Size ◽  
Passenger Cars ◽  
Worst Case ◽  
Hybrid Propulsion ◽  
Wide Range ◽  
Definition Of

Abstract A hybrid propulsion system of new conception for medium-size passenger cars is described and its preliminary design developed. The system consists of a turbogas set operating at fixed rpm, and a battery-operated electric motor that constitutes the actual “propulsor”. The battery pack is charged by the thermal engine which works in an electronically controlled on/off mode. Though the idea is not entirely new (there are some concept cars with similar characteristics), the present study has important new aspects, in that it bases the sizing of the thermal engine on the foreseen “worst case” vehicle mission (derived from available data on mileage and consumption derived from road tests and standard EEC driving mission cycles) that they can in fact be accomplished, and then proceeds to develop a control strategy that enables the vehicle to perform at its near–peak efficiency over a wide range of possible missions. To increase the driveability of the car, a variable-inlet vane system is provided for the gas turbine. After developing the mission concept, and showing via a thorough set of energy balances (integrated over various mission profiles), a preliminary sizing of the turbogas set is performed. The results of this first part of the development program show that the concept is indeed feasible, and that it has important advantages over both more traditional (Hybrid Vehicles powered by an Internal Combustion Engine) and novel (All-Electric Vehicle) propulsion systems.

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