Fundamental and Applied Energetics

Hypersonic studies in the ATD 5 test cell

ATD 5 test cell with the JAPHAR dual mode ramjet engine
Full size: 70 Ko

The ATD 5 test bench which is unique in Europe was created in 1993 for the PREPHA program (Research Program on Advanced Hypersonic Propulsion) to test on ground scramjet engines. This program funded by the defence and research ministries was initiated in an international context of renewed interest from the United States and Japan for future launchers using air breathing propulsion.

In 1998, the JAPHAR program (Joint Air breathing Propulsion for Hypersonic Application Research) launched jointly by ONERA and DLR allowed to continue this effort and to test new scramjet geometries taking into account the lessons learned from the PREPHA.

In 2001, the PROMETHEE program began. It is aimed at flying an experimental vehicle propelled by a dual mode ramjet. Within the frame of this study a new engine is currently being developed. Instead of pure gaseous hydrogen used up to now, this engine will use a mixture of methane and hydrogen as fuel in order to reduce the needed tank volume for the flight experiment compared to a pure hydrogen tank.

Test set up

The ATD 5 test cell, located on the Onera Palaiseau site, near Paris, is especially dedicated to study physical and chemical phenomena linked to supersonic combustion and also to evaluate combustion chamber performances or injection system behaviour.

The maximum test conditions correspond to a flight simulation between 35 to 40 km in altitude for a Mach 7.5 hypersonic speed which leads to about 40 bar in total pressure and 2400 K in total temperature.

The main features of the test bench are the following:

• chamber inflow area: 1 dm²,
• mass flow: 4 kg/s,
• total pressure: 40 bar,
• total temperature: 2400 K,
• hydrogen mass flow rate: 0.3 kg/s.

Instrumentation

386 measurements are at disposal with 90 temperatures, 4 liquid flow rates and 292 pressures. The acquisition frequency lies between 10 to 100 Hz depending on the measurement type or the needs. Non stationary pressures can also be recorded.

In addition to those measurements this test bench is equipped with a calorimeter that allows to determine experimentally the combustion efficiency.

Finally, optical diagnostics such as laser tomography, schlieren techniques, spontaneous OH emission, laser velocimetry, pyrometry or infra red cameras can be used.

Performed studies

Since 1993, many tests have been conducted in this test cell. In particular :

• Composite structure test for PROMETHEE and A3CP programs,
• CH₄/H₂ scramjet tests for the PROMETHEE/LEA program,
• JAPHAR dual mode ramjet tests at Mach 4.9, 5.8 and 7.6,
• PREPHA scramjet chamber tests,
• hydrogen cooled composite materials tests,
• injection devices and flame stabilization systems studies,
• simple wall injection studies,
• study of liquid kerosene penetration in a supersonic flow...

Japhar - essai à Mach 4.9

Example of experimental results obtained at Mach 4.9 for the JAPHAR engine

Pressure field

Sonic zones (blue)

Prospects

The future studies will be carried out in the frame of the LEA program, part of the PROMETHEE program. The aim is to develop a flight ready engine for the CLEA flight demonstrator that should fly within the next 5 years. This new variable geometry engine will be heavily tested in the ATD5 test cell.

Some publications

1. O. Dessornes, ONERA, Palaiseau, M. Bouchez, MBDA, Bourges : “Combustion experiments of liquid kerosene and hydrogen/methane mixing in a dual mode ramjet”, 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference, AIAA-2005-3400, May 2005.
2. C. Bouquet and R. Fischer, Snecma Propulsion Solide, Le Haillan, France; A. Luc-Bouhali and O. Dessornes, ONERA, Palaiseau, France; J. Thebault and P. Soyris, Snecma Propulsion Solide, Le Haillan, France : « Fully Ceramic Composite Heat Exchanger Qualification for Advanced Combustion Chambers », 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference, AIAA 2005-3433, may 2005
3. O. Dessornes, D. Scherrer, ONERA, France : « Weighing of the JAPHAR dual mode ramjet engine », 11th AIAA/AAAF International Space Planes and Hypersonic Systems and Technologies Conference, AIAA-2002-5187, september/october 2002
4. O.Dessornes, D. Scherrer, P. Novelli, ONERA, France : “Testing and weighing of the JAPHAR dual mode ramjet engine”, 15th International Symposium on air breathing engines, ISABE-2001-1135
5. O. Dessornes, D. Scherrer, P. Novelli, “tests of the japhar dual mode ramjet engine”, 10th AIAA/NAL-NASDAS-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, AIAA-200-1886, april 2001

Last Update: 5 May 2006 - © ONERA 2009 - Terms of use