Spacecraft Propulsion System Test Capability at the NASA White Sands Test Facility

1993 ◽  
Author(s):  
Pleddie Baker ◽  
Richard Gorham
Keyword(s):  
Propulsion System ◽  
Test Facility ◽  
White Sands ◽  
Spacecraft Propulsion

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.

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.

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.

A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities

2002 ◽  
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.

A Fault Isolation Method Based on Analytical Redundancy Relations for Spacecraft Propulsion System

2012 ◽  
Vol 232 ◽  
pp. 331-336 ◽  
Author(s):  
Xiao Hui Peng ◽  
Zheng Yan ◽  
Yan Jun Li ◽  
Jian Jun Wu
Keyword(s):  
Diagnostic Criteria ◽  
Fault Isolation ◽  
Propulsion System ◽  
Time Varying ◽  
Isolation Method ◽  
Analytical Redundancy ◽  
Tendency Analysis ◽  
Time Invariant ◽  
Signature Matrix ◽  
Spacecraft Propulsion

Based on time-varying characters of spacecraft propulsion system, which generates tremendous difficulty to establish diagnostic criteria artificially, the fault isolation method based on Analytical Redundancy Relations (ARRs) generating from Diagnostic Bond Graph (DBG) has been proposed. The ARRs for Spacecraft Propulsion System are built on time-invariant structural characters, which can overcome the challenges from artificially establishing time-varying diagnostic criteria beforehand. By the tendency analysis of the residuals of ARRs, the fault signature matrix can be established. Then faults are isolated by comparison of observed signature and fault signature. Through the analysis of isolation results of a spacecraft propulsion system, it shows that ARRs is valid and practicable at fault isolation with rapid rates.

The Development of a Japanese 20N Thruster Valve for a Spacecraft Propulsion System

2006 ◽  
Author(s):  
Taiichi Nagata ◽  
Kenichi Kushiki ◽  
Kenichi Kajiwara ◽  
Yoshiharu Sugimura ◽  
Masayuki Kobayashi ◽  
...  
Keyword(s):  
Propulsion System ◽  
Spacecraft Propulsion

Thermal analysis of spacecraft propulsion system and its validation

2004 ◽  
Vol 18 (5) ◽  
pp. 847-856 ◽  
Author(s):  
Cho Young Han ◽  
Joon-Min Choi
Keyword(s):  
Thermal Analysis ◽  
Propulsion System ◽  
Spacecraft Propulsion
Sign in / Sign up

Export Citation Format

Share Document