On the development of testing facilities for the scientific testing center of the rocket and space industry for developmental testing of advanced cryogenic propulsion systems

2021 ◽  
pp. 88-97
Author(s):  
Nikolay P. SIZYAKOV ◽  
Igor A. YURIEV ◽  
Ayvengo G. GALEEV
Keyword(s):  
Propulsion System ◽  
Test Facility ◽  
Launch Vehicles ◽  
Propulsion Systems ◽  
Safety Measures ◽  
Experimental Development ◽  
Space Industry ◽  
Calculation Results ◽  
Testing Center ◽  
Scientific Testing

The paper provides a review of materials on the development of testing facilities in the Scientific Testing Center of the Rocket and Space Industry and the issues involved in raising the efficiency and safety of experimental development of advanced cryogenic propulsion systems for launch vehicles intended for exploration of the near and deep space. It shows that the most dangerous tests are those that are conducted on engines and propulsion systems that use oxygen, methane and hydrogen as propellant components. They may involve containment failure in the propellant system in off-nominal situations — emergency releases of propellant components, explosions and fires. It provides calculation results for overpressure in the shock-wave front depending on the mass of the released hydrogen and the factor of its contribution to the explosion. It formulates special and additional safety measures for engine and propulsion system tests in a test facility. Key words: test facility (test stand), propulsion system, safety, off-nominal situation, cryogenic propellant components.

ON THE DEVELOPMENT OF TESTING FACILITIES FOR THE SCIENTIFIC TEST-ING CENTER OF THE ROCKET AND SPACE INDUSTRY FOR DEVELOPMENTAL TESTING OF ADVANCED CRYOGENIC PROPULSION SYSTEMS

2021 ◽  
pp. 88-97
Author(s):  
Nikolay P. SIZYAKOV ◽  
Igor A. YURIEV ◽  
Ayvengo G. GALEEV
Keyword(s):  
Propulsion System ◽  
Test Facility ◽  
Launch Vehicles ◽  
Propulsion Systems ◽  
Safety Measures ◽  
Experimental Development ◽  
Space Industry ◽  
Calculation Results ◽  
Testing Center ◽  
Scientific Testing

The paper provides a review of materials on the development of testing facilities in the Scientific Testing Center of the Rocket and Space Industry and the issues involved in raising the efficiency and safety of experimental development of advanced cryogenic propulsion systems for launch vehicles intended for exploration of the near and deep space. It shows that the most dangerous tests are those that are conducted on engines and propulsion systems that use oxygen, methane and hydrogen as propellant components. They may involve containment failure in the propellant system in off-nominal situations — emergency releases of propellant components, explosions and fires. It provides calculation results for overpressure in the shock-wave front depending on the mass of the released hydrogen and the factor of its contribution to the explosion. It formulates special and additional safety measures for engine and propulsion system tests in a test facility. Key words: test facility (test stand), propulsion system, safety, off-nominal situation, cryogenic propellant components.

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.

A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities

2005 ◽  
Vol 127 (1) ◽  
pp. 8-17 ◽  
Author(s):  
Milt Davis ◽  
Peter Montgomery
Keyword(s):  
System Performance ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Flight Simulation ◽  
Propulsion System ◽  
Test Facility ◽  
Flight Testing ◽  
Test Environment ◽  
Ground Test ◽  
Aircraft System

Testing of a gas turbine engine for aircraft propulsion applications may be conducted in the actual aircraft or in a ground-test environment. Ground test facilities simulate flight conditions by providing airflow at pressures and temperatures experienced during flight. Flight-testing of the full aircraft system provides the best means of obtaining the exact environment that the propulsion system must operate in but must deal with limitations in the amount and type of instrumentation that can be put on-board the aircraft. Due to this limitation, engine performance may not be fully characterized. On the other hand, ground-test simulation provides the ability to enhance the instrumentation set such that engine performance can be fully quantified. However, the current ground-test methodology only simulates the flight environment thus placing limitations on obtaining system performance in the real environment. Generally, a combination of ground and flight tests is necessary to quantify the propulsion system performance over the entire envelop of aircraft operation. To alleviate some of the dependence on flight-testing to obtain engine performance during maneuvers or transients that are not currently done during ground testing, a planned enhancement to ground-test facilities was investigated and reported in this paper that will allow certain categories of flight maneuvers to be conducted. Ground-test facility performance is simulated via a numerical model that duplicates the current facility capabilities and with proper modifications represents planned improvements that allow certain aircraft maneuvers. The vision presented in this paper includes using an aircraft simulator that uses pilot inputs to maneuver the aircraft engine. The aircraft simulator then drives the facility to provide the correct engine environmental conditions represented by the flight maneuver.

Developing, implementing and transferring lean quality initiatives from the aerospace industry to all industries

2000 ◽  
Vol 10 (4) ◽  
pp. 248-256 ◽  
Author(s):  
Dennis F.X. Mathaisel ◽  
Clare L. Comm
Keyword(s):  
Automobile Industry ◽  
Lean Manufacturing ◽  
Motor Vehicle ◽  
Aerospace Industry ◽  
Launch Vehicles ◽  
Quality Initiatives ◽  
Space Operations ◽  
Space Industry ◽  
The Us ◽  
Japanese Companies

Japanese companies, particularly Toyota, first began building quality into their products and becoming lean. Consequently, researchers associated with the international motor vehicle industry initially identified the “lean” manufacturing paradigm in the US automobile industry. Building upon their successes, the US aerospace industry initiated a study to ascertain whether a similar initiative focused on launch vehicles and spacecraft would bring value to military and commercial aerospace stakeholders in their ongoing efforts to be lean. This paper presents the findings of this investigation. It explores the relevance and value of the lean concepts to the US defense launch vehicle, spacecraft, and space operations industries, and it ascertains if there is interest within space industry firms in establishing a lean initiative similar to that of the automotive industry. Further, the relevance of lean manufacturing to other industries is considered.

Progress of the 40 MW-Class Advanced Humid Air Turbine Tests

2013 ◽  
Vol 135 (11) ◽  
Author(s):  
Manabu Yagi ◽  
Hidefumi Araki ◽  
Hisato Tagawa ◽  
Tomomi Koganezawa ◽  
Chihiro Myoren ◽  
...  
Keyword(s):  
Metal Surface ◽  
Control Method ◽  
Cooling System ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Test Facility ◽  
Humid Air ◽  
Air Turbine ◽  
Calculation Results ◽  
Flow Compressor

A 40 MW-class test facility has been constructed to verify practicability of applying the advanced humid air turbine (AHAT) system to a heavy-duty gas turbine. Verification tests have been carried out from January 2012, and interaction effects between the key components were established. First, water atomization cooling (WAC) was confirmed to contribute to both increased mass flow rate and pressure ratio for the axial-flow compressor. The good agreement between measured and calculated temperatures at the compressor discharge was also confirmed. These results demonstrated the accuracy of the developed prediction model for the WAC. Second, a control method that realized both flame stability and low nitrogen oxides (NOx) emissions was verified. Although the power output and air humidity were lower than the rated values, NOx concentration was about 10 ppm. Finally, a hybrid nozzle cooling system, which utilized both compressor discharged air and humid air, was developed and tested. The metal surface temperatures of the first stage nozzles were measured, and they were kept under the permissible metal temperature. The measured temperatures on the metal surface reasonably corresponded with calculation results.

The Design of Water-Jet Propulsion Systems for Hydrofoil Craft

1965 ◽  
Vol 2 (01) ◽  
pp. 15-25
Author(s):  
Joseph Levy
Keyword(s):  
Water Jet ◽  
Propulsion System ◽  
Specific Design ◽  
Propulsion Systems ◽  
Propulsive Efficiency ◽  
Jet Propulsion ◽  
Performance Curves

This paper contains a brief description of the water-jet propulsion system as applied to hydrofoil craft, and a discussion of the salient hydrodynamic aspects of the problem of fitting the main propulsion system to the specified thrust-versus-speed requirements. The factors that affect the overall propulsive efficiency and the weight of the system are discussed at some length; procedures for optimization of performance at the design cruising speed are outlined; finally, the processes by which the performance at off-design conditions may be evaluated are discussed and illustrated with performance curves for one specific design.

Inlet Duct-Engine Exhaust Nozzle Airflow Matching for the Supersonic Transport

1968 ◽  
Vol 72 (690) ◽  
pp. 490-497
Author(s):  
J. B. Taylor
Keyword(s):  
Propulsion System ◽  
Operating Conditions ◽  
Design Parameters ◽  
Gas Generator ◽  
Propulsion Systems ◽  
Engine Exhaust ◽  
Supersonic Transport ◽  
Reliable Performance ◽  
Jet Nozzle ◽  
Secondary Air

Propulsion systems selected for commercial transports must provide efficient and reliable performance over a broad range of conditions. These aeroplanes are used over both short and long route segments, on non-standard days, and at a range of altitudes to meet air-line schedule requirements. This paper covers some of the design parameters that were considered in the integration of the induction system, secondary air system, jet nozzle and the basic turbojet gas generator for the SST. During recent years some of the most important gains in propulsion efficiency have resulted from the development of inlets, engines and exhaust nozzles which are matched over a broad range of operating conditions. An efficient propulsion system for a supersonic transport depends upon very close matching of these components. This, of course, requires a better understanding of the capabilities and limitations of each of these major components. For the supersonic transport, 50% or more of the gross weight will be comprised of propulsion system and fuel and less than 10% will be payload.

scholarly journals CATHARE Assessment of Natural Circulation in the PKL Test Facility during Asymmetric Cooldown Transients

2012 ◽  
Vol 2012 ◽  
pp. 1-10 ◽  
Author(s):  
Anis Bousbia Salah ◽  
Jacques Vlassenbroeck
Keyword(s):  
Natural Circulation ◽  
Test Facility ◽  
Steam Generators ◽  
Calculation Results ◽  
The Impact

Results of the CATHARE code calculations related to asymmetric cooldown tests in the PKL facility are presented. The test under consideration is the G2.1 experiment performed within the OECD/NEA PKL-2 project. It consists of carrying out a cooldown under natural circulation conditions in presence of two (out of four) emptied Steam Generators (SGs) and isolated on their secondary sides. The main goal of the current study is to assess the impact of a chosen cooldown strategy upon the occurrence of a Natural Circulation Interruption (NCI) in the inactive (i.e., noncooling) loops. For this purpose, three G2.1 test runs were investigated. The calculation results emphasize, mainly, the effect of the cooldown strategy, and the conditions that could lead to the occurrence of the NCI phenomenon.

Thermal-Hydraulic Studies of the Steam Separation in Horizontal Steam Generator at PGV Test Facility

2009 ◽  
Author(s):  
Yuriy V. Parfenov ◽  
Oleg I. Melikhov ◽  
Vladimir I. Melikhov ◽  
Ilya V. Elkin
Keyword(s):  
Steam Generator ◽  
Nuclear Power ◽  
Test Facility ◽  
Evolutionary Development ◽  
Pressurized Water Reactor ◽  
Pressurized Water ◽  
Tube Bundles ◽  
Horizontal Steam Generator ◽  
Calculation Results ◽  
Steam Separation

A new design of nuclear power plant (NPP) with pressurized water reactor “NPP-2006” was developed in Russia. It represents the evolutionary development of the designs of NPPs with VVER-1000 reactors. Horizontal steam generator PGV-1000 MKP with in-line arrangement of the tube bundles will be used in “NPP-2006”. PGV test facility was constructed at the Electrogorsk Research and Engineering Center on NPP Safety (EREC) to investigate the process of the steam separation in steam generator. The description of the PGV test facility and tests, which will be carried out at the facility in 2009, are presented in this paper. The experimental results will be used for verification of the 3D thermal-hydraulic code STEG, which is developed in EREC. STEG pretest calculation results are presented in the paper.

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