Engineering Model Test Research Articles

Reliability research analysis on crack control standard for steel lined reinforced concrete penstocks

In view of the insufficiency of research about steel lined reinforced concrete penstocks in hydropower station crack control standard, the Monte Carlo method was combined with the crack width calculation formula of Dong Zhe-ren method to establish a reliability calculation method. According to the engineering example and model test parameters, the reliability index of the crack control standard for steel reinforced concrete penstocks in China were calculated, and the main influence factors were concluded. Studies indicates that the reliability level of crack control for steel lined reinforced concrete penstocks is of medium level or slightly lower. The influence of crack width limit, cover thickness and the effective reinforcement ratio on reliability level of crack control standard is significant.

The LISA Pathfinder interferometry—hardware and system testing

Preparations for the LISA Pathfinder mission have reached an exciting stage. Tests of the engineering model (EM) of the optical metrology system have recently been completed at the Albert Einstein Institute, Hannover, and flight model tests are now underway. Significantly, they represent the first complete integration and testing of the space-qualified hardware and are the first tests on an optical system level. The results and test procedures of these campaigns will be utilized directly in the ground-based flight hardware tests, and subsequently during in-flight operations. In addition, they allow valuable testing of the data analysis methods using the MATLAB-based LTP data analysis toolbox. This paper presents an overview of the results from the EM test campaign that was successfully completed in December 2009.

The Building of Water Conservancy Project Model Test Automatic Monitoring Agent Federation

In order to improve the prediction precision of the model test water conservancy project and speed up the experiment, through the introduction of the multi-agent theory, this paper puts forward a new type of automatic control system model which is based on multi-agent water project. The automatic system monitoring agency comprises the league system control agent, the flow control agent, water level control agent and velocity of flow control agent. These control agents are responsible for controlling the whole water engineering model test and three other major tasks including testing and adjusting the flow, the water level, velocity and the sending process. The result indicates that (“the final result, make the system control agent of the normal operation of the water model test project”. The system has many advantages. For example, it is a fast and convenient way for communication. This automation hydropower project model test is with great practical value.

Development of mechanical cryocoolers for Astro-H/SXS

The Soft X-ray Spectrometer (SXS) is a high-resolution spectrometer with an X-ray micro-calorimeter array onboard the Japanese X-ray astronomy satellite Astro-H, planned for launch in 2013. The micro-calorimeter is operated at cryogenic temperature of 50 mK provided by the Adiabatic Demagnetization Refrigerator (ADR) with a heat sink of 1.3 K liquid helium stored in the SXS Dewar. To extend the liquid helium lifetime to over 3 years in orbit, two types of mechanical cryocoolers are installed: 20 K-class double-staged Stirling (2ST) coolers and a 1 K-class Joule–Thomson (JT) cooler. Improvement of mechanical cryocoolers has been investigated and verified for higher reliability and cooling performance. The engineering model (EM) of upgraded mechanical cryocoolers was fabricated for a long lifetime test. The required cooling power of 200 mW at 20 K for the 2ST cooler and 10 mW at 1.7 K for the JT cooler are achieved by EM test.

Research Method and Two-Phase Flow Stability of the Steam Generator of HTR-10

A 10MW High Temperature Gas Cooled Reactor (HTR-10) designed by the Institute ofNuclear Energy Technology (INET) of Tsinghua University is being constructed now. The steam generator (SG) of the HTR-10 is one of the most important facilities for reactor safety. In order to investigate the thermal-hydraulic performance of the SG, a full scale HTR-10 Steam Generator Two Tube Engineering Model Test Facility (SGTM-10) was installed and tested at INET. This paper describes the SGTM-10 in detail. The test assembly of the SGTM-10 simulates practical thermal and structural parameters of the HTR-10. The SGTM-10 consisted of three separated loops, primary-helium loop, secondary-water loop, and third-cooling water loop. There are two parallel tubes arranged in the test assembly. The main experimental equipment is shown in this paper. Analysis shows that for once-through steam generator simulation experiment, the electric-heated simulation method could not match practical operating condition. The results may not reflect true phenomena. The main results of experiments, for example effects of the outlet pressure, effects of the heating power, effects of the inlet sub-cooling are described. Experiments indicated, when the heat load of the HTR-10 is more than 30% the SG will be stable.

F212 技術試験衛星VIII型(ETS-VIII)搭載展開型ラジエータの開発(オーガナイズドセッション22 : 熱輸送デバイス)

High-powered satellites are required to obtain more heat rejection area. Deployable radiator, which is stowed during launch and deployed in orbit to obtain the additional heat rejection area, is key bus technology. This paper presents a design and engineering model test of developed deployable radiator on ETS-VIII (Engineering Test Satellite VIII) using RELHP (Reservoir Embedded Loop Heat Pipe). RELHP has an evaporator, condenser and transport lines to circulate a fluid, and that utilizes the evaporation and condensation of the working fluid to transfer heat. Developed RELHP has following characteristics. (1) It has 1.0 micron pore diameter fine-poured wick to achieve more higher heat transport capability. (2) It can start-up at any time by supplying the wick with working fluid, because liquid reservoir is located in the evaporator itself. Results of the thermal balance test and analysis will be described and discussed.

Characterisation of the Advanced Microwave Sounding Unit, AMSU-B

The Advanced Microwave Sounding Unit, AMSU-B, is a five channel microwave radiometer to be flown later this decade on the series of polar orbiting spacecraft NOAA-K, L and M. It will provide global data in support of synoptic weather forecasting by sounding the water vapour content of the atmosphere from the ‘window’ channels at 89 and 150 GHz to the strong resonance line at 183.3 GHz. It has a scan period of 2 2 3 seconds and provides 90 earth view pixels each of nominal beam width 1.1 degrees during earth scan. The key radiometric requirements of the instrument are to provide a temperature sensitivity of 1 to 1.2K depending on channel, a linearity within 0.3 of the temperature sensitivity and a beam efficiency of 95%. This paper describes the design of the AMSU-B, the ground based buy-off tests and results obtained for the Proto-Flight Model (PFM), Flight 2 (FM2) and Flight 3 (FM3) Models in the context of these requirements. The Engineering Model testing is described in reference /1/.

Road vehicle model testing in a blockage tolerant wind tunnel

Abstract A passive form of blockage-tolerant wind tunnel designed for wind engineering model testing is under development in the department laboratory. Its test section provides low blockage corrections for test models by a sequence of uniformly spaced ring airfoils replacing the usual side walls and ceiling. These are surrounded by an annular plenum, and a solid floor forms a chord of the circular ross section and represents the ground. Current testing is on models simulating large truck-trailer combinations, and preliminary results indicate pressure distributions and drag coefficients unaffected by blockage for values as high as 29%.

Ｈ‐ＩＩロケットの開発

The development program of the H-II Rocket has been initiated in 1985, and now engineering model test is being progressed. The H-II Rocket is a new expendable launch vehicle to meet a demand of space activities in the 1990's, with capability of placing a 2 ton class satellite into geostationary earth orbit (GEO). After trade-off studies, LOX/LH2 propulsion system with a single main engine (LE-7) of staged combustion cycle has been selected for the 1st stage of the H-II Rocket, considering its high performance and the accumulated experience in cryogenic propulsion system technology through development of the 2nd stage (LOX/LH2) of the H-I Rocket, of which the first test flight was successfully launched in August, 1986. And the 2nd stage propulsion system will be developed by upgrading modification (tank volume increase and engine thrust up) of the H-I Rocket 2nd stage. This paper shows an outline of the propulsion systems of H-II Rocket 1st and 2nd stages, and the technical problem including the technics which was gained in the development of H-I 2nd stage propulsion system.