Evaluating the Satinê-T1 Hybrid Rocket Engine

Paper number

IAC-08.C4.2.9

Author

Mr. Steven Engelen, Technical University of Delft (TUDelft), The Netherlands

Coauthor

Mr. Louis Souverein, IUSTI, France

Coauthor

Mr. Hein Olthof, Delft University of Techonology (TU Delft), The Netherlands

Year

2008

Abstract

The Satinê project was initiated to increase engine performance compared to the solid rocket motors DARE (the Delft Aerospace Rocket Engineering student society) currently uses, without sacrificing too much of their inherent simplicity and ease of use. Its intended goal was to provide engines that would serve as moderately high thrust, high specific impulse parallel booster engines for the DEIMOS flight vehicles, which are powered by a liquid rocket engine. Currently however, these hybrid engines are considered to be used as main stage engines in some of DARE’s other projects, such as the CanSat launchers, as well.

The first step in this programme is the development of the Satinê-T1 engine, an 850N, 175 s Isp test engine with an aerospike nozzle. The engine itself was designed to be as flexible as possible, in order to test as many properties of hybrid engines as possible. It is a so-called battleship engine design, incorporating large safety factors to allow for some mishaps during testing. Two test engines were subsequently manufactured, and their dry mass of over 15 kilogram confirms their robust design, although it does not guarantee troublefree operation.

The engines are initially tested with a solid propellant charge, to verify functionality of the aerospike nozzle, since these engines are DARE’s first engines to use such a nozzle. A hot-burning solid test would also confirm the ability of the engine casing and the thermal liner to handle the operating conditions. Furthermore, it gives some insight into the thermal loads on the spike nozzle, allowing for fine-tuning of the design using different combinations of materials to withstand the heat loads.

Once the casings are considered fit for use, the required test stand modifications are completed, and the engines subjected to a series of tests in order to assess both the test stand performance, and their own performance. 

This paper describes these tests, and analyses their results.

Abstract document

IAC-08.C4.2.9.pdf

Manuscript document

IAC-08.C4.2.9.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.