2005 Vol. 20, No. 3

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Multi-Way Heteroscedastic Analysis
FU Hui-min, WU Wen-juan
2005, 20(3): 345-350.
Abstract PDF(305KB) icon1583 icon450
Abstract:
A method for multi-way heteroscedastic analysis is presented,which detailedly discusses the heteroscedastic analysis of one,two and multiple factors,in the condition of the same coefficient of variation in all states.It can test whether the multiple populations have a certain kind of different means,and estimate their parameters.With small sample,it can test the results of simulation or digital design and analyze the influence of each factor in the results.And then,it can point out which factors have been simulated correctly and which haven’t.Furthermore,this method can correct the results of simulation or digital design according to the experimental data.
Regression Analysis Method for Incomplete Data
WANG Hua-sheng, FU Hui-min
2005, 20(3): 351-354.
Abstract PDF(269KB) icon1844 icon459
Abstract:
Based on the order statistics of incomplete data,a regression analysis method for incomplete data is presented.The regression equation for incomplete data is established,and the best unbiased integral estimators of the regression parameters and their covariance matrix are also given.The regression analysis methods for incomplete data from extreme distribution,Weibull distribution and normal distribution are discussed in detail.As the cross information among the test data in different states is fully exploited,this present method can reach higher precision than the traditional method.
Simulation of Boundary Layer Transition
YANG Lin, ZOU Zheng-ping, NING Fang-fei, CHEN Mao-zhang
2005, 20(3): 355-360.
Abstract PDF(612KB) icon1916 icon460
Abstract:
The Abu-Ghannam and Shaw (AGS) model was added to the turbulent model in order to simulate the process of laminar to turbulent transition.Flat plate and turbine cascade boundary layer was studied and compared to the experimental data.The results show that the transition process could be better simulated by the transition model,but the simulation shows little deviation from the test data under great change of pressure gradient.
Design and Experimental Study of the Inlet Temperature Distortion Generator
HOU Min-jie, LIU Da-xiang, WANG Hui-ru
2005, 20(3): 361-367.
Abstract PDF(442KB) icon1709 icon463
Abstract:
The Temperature Distortion Generator (TDG) design specifications,design technique and the technology of its fabrication were presented.The TDG was tested and calibrated using a turbojet engine and a turbofan engine.The test results indicate that the specifications of this TDG satisfy the requirements of engine temperature distortion testing.The equipment is highly reliable,controllable and stable.
Influence Factor Analysis of the MHD Controlled Scramjet Inlet Design
BAO Wen, CHANG Jun-tao, NIU Wen-yu, YU Da-ren
2005, 20(3): 368-372.
Abstract PDF(292KB) icon1787 icon452
Abstract:
The basic principle and one-dimensional mathematic model of MagnetoHydrodynamic (MHD) controlled inlet were presented.Based on the influence factors analysis of MHD controlled inlet design,including magnetic field intensity,load factor and variation rate of cross section, the effect of design parameters on the exit aerodynamic parameters was given,which provided the basis of MHD controlled inlet design.A set of design parameters were given.The simulation results show that the application of MHD control technology to inlet design can effectively regulate combustor incoming flow state,improve specific impulse and extend the operating range of flight Mach number.
Design and Performance Calculation of the Mixed-Compression Fixed-Geometry Axisymmetric Supersonic Inlets
CHEN Bing, XU Xu, WANG Yuan-guang, CAI Guo-biao
2005, 20(3): 373-379.
Abstract PDF(625KB) icon1859 icon425
Abstract:
Geometric design method of mixed-compression fixed-geometry axisymmetric supersonic ramjet inlet was presented.Performance calculations of inlet under on-or off-design conditions were carried out with special attention to the detached bow shock calculation during subcritical operations.The influence of flight Mach number and altitude on inlet critical condition performance has been evaluated.The inlet-engine matching mechanism was investigated, and the fuel supply characteristics were obtained to maintain the optimum inlet performance.The successful study provides a good reference to the design of ramjet supersonic inlets.
Determination of the Main Components’ Sizefor an Isentropic Light Piston Wind Tunnel
LI Li-ren, LIN Xia
2005, 20(3): 380-383.
Abstract PDF(275KB) icon1674 icon443
Abstract:
Isentropic light piston wind tunnel is a kind of short working duration tunnel.It is adequate to be used for the research work of instantaneous heat transfer measurement.Based on the understanding of the wind tunnel characteristics,a method for determining the sizes of its main components was presented.Pressure ratio and working time duration trun are key parameters to the determination of the tube size, and the mass of the piston depends on the allowed peak value of the matching pressure oscillation.
Research of the Secondary Flow and Vacuum Impact on the Thrust Measurement
HOU Min-jie, LIU Zhi-you, WEN Gang
2005, 20(3): 384-388.
Abstract PDF(321KB) icon2036 icon489
Abstract:
Through the analysis of the impact on engine thrust measurement system of both chamber cooling air flow and vacuum caused by the chamber internal and external pressure difference,both their action mechanisms and their essential distinction were clarified.Moreover,the test method for determining their impact on the engine thrust measurement system of the altitude simulated test facility was theoretically reasoned.
Numerical Investigation of Two-Dimensional Nozzle with Trailing Edge Modification
LI Rong-song, WANG Qiang, Eriqitai
2005, 20(3): 389-393.
Abstract PDF(540KB) icon1709 icon367
Abstract:
The numerical simulation of three dimensional internal and external flows for non-vectoring two-dimensional nozzles with or without trailing edge modification was conducted by means of time marching finite volume method.The difference between the modified and unmodified nozzle was found.Two couple of counter-rotating streamwise strong vortices which can enhance the jet flow mixing appeared around the modified nozzle trailing edge.And these induced vortices have greater effect on temperature distribution of the exhaust plume.The result of this research shows that the design of trailing edge modification can evidently reduce the length of high temperature domain of the exhaust plume and may be benefit to the reduction of infrared radiation.
Reynolds Number Effects on Performance and Aerodynamic Stabilities of the Turbofan Engines
XIAO Hong, WU Hu, LIAN Xiao-chun
2005, 20(3): 394-398.
Abstract PDF(328KB) icon1905 icon431
Abstract:
Wassell’s model and experimental correlations were synthesized.The effects of Reynolds number were taking into consideration to modify the characteristics of compressors and turbines.The performance and aerodynamic stability of three turbofan engines were calculated with modified compressors and turbines characteristics.Investigation shows that:Reynolds number almost has no influence on the engine performance and aerodynamic stability at low altitude,but has significant influence at high altitude with low flight speed.The turbine inlet total temperature and engine thrust are increased.The percentage increase of thrust and specific fuel consumption are 3%～6% and 8%～10% respectively,while the engine surge margin is decreased in the range of 19%～39%.It means that the effects of Reynolds number must be taken into account in turbofan engine performance simulation at high altitude with low flight speed.
Investigation of Methods Improving Turbofan Engine Multi-Mission Adaptability
LI Zhi-gang, WU Xue-hui, TAO Zeng-yuan
2005, 20(3): 399-402.
Abstract PDF(270KB) icon1747 icon441
Abstract:
To improve the multi-mission adaptability of the reheat turbofan engine,two methods were brought forward. Performance of turbofan engines can be improve by taking advantage of the heat sink capability of reheat fuel.Effect on engine performance of precooling was calculated to analyze the feasibility of the two methods on the assumption that the precooling effectiveness can achieve the anticipated value.The results validate the feasibility of the two methods.They are also very useful in improving the performance of the turbofan engine.
Centrifugal Compressor Warm-up Effecton Turboshaft Engine Starting Charateristics
CAI Jian-bin, CHENG Ben-lin, LIU Jie, LI Feng-chun
2005, 20(3): 403-406.
Abstract PDF(435KB) icon2003 icon448
Abstract:
A mathematical model was introduced for the calculation of component material warm-up effect on centrifugal compressor efficiency during turboshaft engine starting.According to the turboshaft engine’s starting fuel flow,starting characteristics was calculated and compared with the engine test data to verify the accuracy of the model.Then,the model was used to analyze component material warm-up effect on the turboshaft engine starting characteristics.
Structure Reliability Evaluation of a Gas Turbine Disk
JIANG Xiang-hua, YANG Xiao-guang, WANG Yan-rong
2005, 20(3): 407-412.
Abstract PDF(603KB) icon1649 icon453
Abstract:
Some deficiencies existed in the traditional deterministic stress and fatigue analysis of gas turbine disk,for example,it cannot quantify the influence of discrepancies in the structure design variables.The stress-strength interference method and Fuzzy Probability Integral (FPI) method,which can quantify these discrepancies,were applied to evaluate the structure reliability of the turbine disk.Result shows FPI method is rapid and effective.The influence of approximations existing in the interference method was also studied.At the end FPI method was used to evaluate the whole disk reliability distribution.This result is helpful not only for understanding the reliability level of the whole disk but also for the further design of the disk.
Application of the Improved Whole Transfer Matrix Methodto the Calculation of Complex Rotor Critical Speed
LI Yu-xi, WANG San-min
2005, 20(3): 413-417.
Abstract PDF(472KB) icon2087 icon452
Abstract:
A new method based on the whole transfer matrix method (WTMM) was proposed.The Riccati transformation and singularity elimination were applied to the whole transfer matrix equation, and the formula of Riccati transfer matrix of coupling element and non-coupling element was derived.This improved method can avoid drawbacks of traditional method,and it is easy to develop a general computer program.Finally,a numerical example was given.The results show that the method is effective and accurate.
Modified Strain range Partitioning Method
HU Xu-teng, SONG Ying-dong
2005, 20(3): 418-423.
Abstract PDF(363KB) icon1771 icon433
Abstract:
According to the character that for the high strength,low ductility alloys,the inelastic strains is small and difficult to determine,a modified method of Strain Range Partitioning (SRP) was presented.Plasticity and creep are not partitioned,and three basic kinds of inelastic strain ranges are defined in the modified SRP as follows:tensile plasticity-compressive plasticity was designated as pp inelastic strain range,tensile plasticity and creep-compressive plasticity was designated as cp inelastic strain range and tensile plasticity-compressive plasticity and creep was designated as pc inelastic strain range.The linear damage rule was applied to predict the life of cc type cycle that contains both tensile creep and compressive creep.The modified SRP was evaluated for its ability to predict creep-fatigue behavior of thermomechanically processed advanced nickel-base superalloy used for turbine disks,Rene’95,at 650℃.The result indicates that the predictive ability of the modified SRP is better than SRP, and the prediction of the is mostly within a scatter band of 2 compared to the baseline test data.
Experimental Study on Rotor System Vibration Control of a Squeeze MR Fluid Damper
WANG Jian-xiao, MENG Guang, CHEN Yun-xi
2005, 20(3): 424-428.
Abstract PDF(338KB) icon1905 icon475
Abstract:
Refer to the rotor and supporting structure of small aero-engines,a single-disk rotor system supported on a squeeze MR fluid damper was designed and manufactured.The unbalance response of the system at different control currents was experimentally studied.It was found that the effects of the magnetic pulling force on the first critical speed and the amplitude can be omitted.The oil film reaction force can diminish the amplitude at the critical speeds without damper,and increase the critical speeds.The damper will have the best effect in minimizing the vibration within the specified range at all working speed by using on-off control method.The research shows that the squeeze MR fluid damper has the advantages such as structure simplicity,high effectiveness,quick response,etc.,and this kind of damper has a promising potential future in vibration control of high-speed flexible rotor systems.
Numerical Analysis of the Modeled Blade/Casing Containment
YU Ya-bin, CHEN Wei
2005, 20(3): 429-433.
Abstract PDF(314KB) icon1627 icon466
Abstract:
The nonlinear transient response of the modeled casing under the impact of cracked blade was calculated numerically.The explicit nonlinear finite element program LS-DYNA was used for the numerical computations.Different containment ring thickness and construction and different blade material and rotating speed were simulated.The casing response under different strain rate was calculated and compared.The impact of material properties on casing response was also evaluated.The calculated results are in good coincidence with experiment.
Shaft Element Method for the Analysis of Lateral-Torsional Coupling Vibration of a Complex Gear-Rotor System
OU Wei-lin, WANG San-min, YUAN Ru
2005, 20(3): 434-439.
Abstract PDF(389KB) icon1989 icon461
Abstract:
In the complex gear-rotor system with unparallel axes and multiple branches,based on sub-structure theory, each simple rotor was regarded as an axis element,and the gear meshing forces were considered as exciting forces of the element,then the vibration equations of all axes were established with lumped mass method in local coordinate system.In global coordinate system,all these vibration equations were synthesized to the lateral-torsional coupling vibration equation of the complex gear-rotor system.Through numerical calculation,the natural frequency and dynamic response of the system can be obtained.At last,the mode and lateral-torsional passive vibration of an aero-engine starting transmission system was analyzed with the axis element method proposed in this paper.
Study of Compression Fatigue Mechanism of Ni-Based Powder Metallurgy Superalloys
WANG An-qiang, YUE Zhu-feng, YANG Zhi-guo
2005, 20(3): 440-443.
Abstract PDF(451KB) icon1651 icon405
Abstract:
Static compressive test for the studying of compression strength and compression fatigue mechanism of Ni-based Powder Metallurgy (PM) superalloys were conducted and compared to the tensile-tensile strain fatigue.It can be seen that the compressive strength limit of PM is very high,50% higher than the tensile strength limit.The fatigue test with different loading proved that the compression fatigue property of PM was better than the tensile fatigue property,because the compression fatigue failure was very hard to occur.The fatigue mechanism of PM was also investigated using the Scanning Electronic Microscope (SEM).The photos of SEM show that the formation and spreading of the microcrack finally cause the crack.In the compressive fatigue test,the photos show no evidence of crack.
Numerical Analysis of Flow and Experimental Investigation of Labyrinth Sealing Characteristicsat Rotational and Static States
WANG Suo-fang, LV hai-feng
2005, 20(3): 444-449.
Abstract PDF(580KB) icon1625 icon412
Abstract:
The standard k-ε turbulence model and RNG k-ε turbulence model were employed to compute the flow characteristics of the labyrinth sealing in the given reference.Compared to their test data,the maximum errors were 2.5% and 15.9% respectively.The computations of annular straight-through sealing with four-tooth and seven-tooth at rotational and static states were carried out with the non-structure grid and SIMPLE method.The sealing effects for different number of tooth and rotational speeds were experimentally investigated.The relations between pressure ratio and leaking coefficient were also explored.The results show that the rotational speed plays a small role on sealing effectiveness,and makes a change of the leaking coefficient within 3.6%.Under low pressure ratio condition,the leaking coefficient goes up a little with the increase of pressure ratio with the same change of Taylor number.
Method with Cartesian Gridfor Simulating Convecti on Heat Transfer of Viscous Fluid
XIE Xiao-jun, KANG Ning
2005, 20(3): 450-455.
Abstract PDF(674KB) icon1830 icon420
Abstract:
A body fitted method with unstructured Cartesian grids for simulating natural convection heat transfer of viscous fluid was studied.Cartesian grids were used and irregular volumes on boundary vicinity were reserved,and thus these grids were fully body fitted.Based on this method,natural convection-diffusion and the convection heat transfer with moving upper boundary in the 2-D inclined cavity were computed.The computed results are compared with those of STAR-CD and show good coincidence.
Design and Experimental Research of Compound Air-cooled Turbine Guide Vane
GUO Wen, JI Hong-hu, CAI Yi, LIU Yu-fang, HU Yan-li, PAN Bing-hua
2005, 20(3): 456-459.
Abstract PDF(282KB) icon1742 icon448
Abstract:
In modern aircraft engines,different kind of cooling techniques such as film showerhead,film spills internal heat transfer enhancement and pin-fin with impingement were used together to keep the turbine blades and guide vanes operating safely.Design and experimental research of compound air-cooled turbine guide vane were presented.The overall cooling characteristics of a real vane was tested and calculated at elevated pressures and temperatures.Experimental results show that the cooling characteristics of the vane are superior while the cooling mass flow ratios varies between 6% and 16%,and the calculation results are in good agreement with the experiments.
Methods for Gas Temperature Measurement by Gas Analysis
ZHONG Hua-gui, JI Hong-hu, LI Ji-bao
2005, 20(3): 460-466.
Abstract PDF(427KB) icon1978 icon415
Abstract:
Two computational methods,Efficiency/Air Excess Coefficient Method (EAEC) and Enthalpy Conservation Method (ECE),for gas temperature measurement based on gas components analysis were presented.The EAEC method uses air excess coefficient and combustion efficiency for gas temperature calculation.EAEC method can further be divided into reheat method and full components method.For the ECE method,the gas temperature is calculated based on gas components and their enthalpy.These methods have already been used for the gas temperature measurement at the exit of the high temperature rise combustor.
Determination of the Similarity Criteria for Thermally Driven Heat Transfer in Centrifugal Force Field
YANG Min, CHANG Hai-ping, MAO Jun-kui, BAI Yun-feng
2005, 20(3): 467-471.
Abstract PDF(299KB) icon2048 icon435
Abstract:
Basic governing equations were established to investigate flow and heat transfer characteristics of the thermally driven liquid flow in the enclosure circulation channels in centrifugal force field.From the dimensionless governing equations,the primary similarity criteria,which affect the thermally driven heat transfer were gained.Experiments based on theoretical analysis were carried out to investigate the details of heat transfer of water in centrifugal force field.Through curve fitting of the test data,the similarity criteria for thermally driven heat transfer in centrifugal force field were obtained.
Numerical Simulation of Glaze Ice Accretion Process
CHEN Wei-jian, ZHANG Da-lin
2005, 20(3): 472-476.
Abstract PDF(336KB) icon2007 icon437
Abstract:
A numerical simulation approach taking the wall roughness effect into account was presented to simulate the glaze ice accretion.Incorporating the biphase model of air and supercooled water droplets in the Eulerian coordinate,this approach has been carried out to simulate the glaze ice accretion on the NACA0012 airfoil.The final ice shape at different temperature was obtained.The comparison with the experimental data indicates that the current approach is applicable and effective.
Effect of the Combustion Chamber Cylindrical Section Diameter on the Pulse-Jet Engine Performance
ZHOU Hong-ping, XU Lin-yun, RU Yu, ZHOU Feng-fang
2005, 20(3): 477-482.
Abstract PDF(378KB) icon1855 icon405
Abstract:
A test system was established for the testing of the gas pressure in the Helmholtz type pulse-jet engine combustion chamber.The gas pulsating condition can be monitored in a real time manner.Number of impulse,stability of the pressure waves,etc.were used as indices to evaluate the stability of operation,and thus,the operating stability of the pulse-jet engine can be monitored and controlled during testing.The relations between the combustion chamber cylindrical section diameter and the parameters such as the gas pressure wave form in the combustion chamber,the working frequency of the pulse-jet engine,the specific fuel consumption and the excess air coefficient were investigated.It can be concluded that the diameter has no significant effect,but the opening of the throttle remarkably affects the parameters.
Thermal Analysis of Aeroengine Bearing Compartment
GE Zhi-mei, HAN Zhen-xing, ZHANG En-he, LI Guo-quan, XING Jun
2005, 20(3): 483-486.
Abstract PDF(486KB) icon1900 icon477
Abstract:
Thermal analysis of aeroengine bearing compartment was conducted using the finite element analysis and calculation program based on 2D axisymmetrical steady-state heat transfer model.The program was developed using axisymmetrical triangle annular cell FORTRAN.The engineering software ALGOR and ANSYS were used for pre-processing and post-processing respectively,while AUTOCAD was used for the direct input of graphic data and semi-automatic grid-drawing and decoding.Empirical formulae were adopted to calculate friction heat and heat transfer coefficient.The application of this model to an engine shows satisfactory results.
Fuzzy Adaptive PID Control for an Unmanned Helicopter Engine
HUANG Xiang-hua, PENG Zhao-yong
2005, 20(3): 487-493.
Abstract PDF(394KB) icon2010 icon402
Abstract:
Complex engine control strategy,including constant fuel supply,constant speed control and forward-feed compensation control rule was proposed for an unmanned helicopter engine.Fuzzy adaptive PID controller was built in a flight control computer.Adopting fuzzy rule and fuzzy inference were used to adjust PID parameters on-line and thus to make engine start smoothly and keep constant rotor speed at all power settings.It is proved by hardware-in-loop simulation,engine ground test,tethered test and flight test that the engine control strategy designed has quick transient response and it is robust to disturbance such as overall pitch variation.The results show that the main rotor yields best aerodynamic efficiency at all flight status,and thus the flight performance of the unmanned helicopter can be improved.
Chaos based Fuzzy Neural Networks Control for Aeroengines
HOU Sheng-li, WU Yun, LIU Jian-xun, LI Ying-hong
2005, 20(3): 494-498.
Abstract PDF(284KB) icon1577 icon409
Abstract:
The fuzzy rule and the weights in fuzzy neural networks controller are difficult to determine.In consideration of this problem,a kind of control scheme optimized via chaos algorithm was put forward for the aircraft engines.The chaos algorithm was applied to the design of the aeroengine control system to optimize the parameters of the fuzzy neural networks controller.The simulation results show that not only the design of the aeroengine fuzzy PID controller is improved by the chaos algorithm, but also the fuzzy neural networks controller behaves effectively.
Study on Mathematic model of Aeroengine Starting Systems Based on Moment Characteristics
SU Wei-sheng, SUN Jian-guo, CHENG Lan, HU Shi-min
2005, 20(3): 499-502.
Abstract PDF(264KB) icon2386 icon482
Abstract:
To describe the starting process of aeroengines,analyze the relationship between starting moment and the engine moment characteristics and its loading in the starting process,the mathematic model of aeroengine starting system was developed,and the computing method of time of start was given in this paper.Simulation results show that the given mathematic model for aeroengine starting system is feasible.
Study of MAPS Methods for Turbofan Engine Performance Seeking Control
WANG Fang, FAN Si-qi, WU Dan, REN Xin-yu
2005, 20(3): 503-507.
Abstract PDF(526KB) icon1862 icon456
Abstract:
Model-Assisted Pattern Search method (MAPS) was applied to the study of performance seeking control using an aircraft engine nonlinear component level model.MAPS algorithm is one of the direct search method,in which partial derivative doesn’t need to calculate.Kriging algorithm was used to construct a sequence of surrogate models in order to reduce the amount of calculations and increase speed of optimization.Then,MAPS algorithm was applied to three control modes separately,including minimum fuel flow mode,maximum thrust mode and afterburning maximum thrust mode.Calculation results are presented in this paper.
Compressor Casing Static Pressure Forecasting Via Phase Space Reconstruction and Neural Network
WU Yun, LI Ying-hong, WEI Xun-kai, ZHANG Pu
2005, 20(3): 508-511.
Abstract PDF(428KB) icon1808 icon405
Abstract:
A novel forecasting model for compressor casing wall pressure based on phase space reconstruction and radial basis function network was established.Phase space for the experimental pressure data was reconstructed, and corresponding chaotic characteristics were analyzed.Number of network input variables was determined through the computed minimum embedding dimension of the reconstructed phase space.The network’s topology was optimized via K-means clustering method,and the maximum effective forecasting steps was determined by computing the largest Lyapunov exponent of the examined pressure time series.Taking advantage of the strong nonlinear mapping capability of the radial basis function neural network,nonlinear forecasting of the measured time series was realized.The forecasting results successfully validate the feasibility and effectiveness of the newly developed algorithm,which may serve as a promising trend monitoring method for axial flow compressors.
Numerical and Experimental Investigation of the Fan Structure Effects on Performance
YANG Chun, LI Qiu-shi, YAN Wei, LU Ya-jun
2005, 20(3): 512-517.
Abstract PDF(333KB) icon1664 icon397
Abstract:
By means of numerical simulation and experimental investigation,some comparison analysis of the different axial fan structure effects on performance was done.Through the analysis,causes of how improperly designed structures that were made by the production condition limitations affected the overall fan performance were found,in the meanwhile,locations of main loss generation were found also.The results show that the fan structure must be taken into consideration in the process of the original design,and thus the design aerodynamic parameters can be adjusted to match the actual structure of the products.
Research on Genetic Algorithm Appliedto Sequencing of Compressor Vanes
TANG Shao-jun, WANG Xu, ZHU Bin
2005, 20(3): 518-522.
Abstract PDF(450KB) icon1809 icon439
Abstract:
Genetic algorithm was applied to optimize sequencing of compressor vanes.This paper gives the detail calculation procedures,the selection methods of coding feasible solutions of the compressors vane sequencing,chiasm operator and variation operator in the computation.The adaptation functions were established and the evaluation methods to optimize them were also given.The idiographic computing examples indicate that the genetic algorithm has preferable efficiency and satisfactory accuracy.
Ground Ignition Test of an Orbit Maneuver H2/O2 Thruster Based on Gas Dynamic Resonance Igniter
SONG Ya-na, YU Nan-Jia, MA Bin, ZHOU Wen-lu, HUANG Xiang
2005, 20(3): 523-528.
Abstract PDF(372KB) icon2210 icon410
Abstract:
Orbit maneuver hydrogen-oxygen thruster based on gas dynamic resonance igniter is a novel chemical propulsion technology especially prospective in space station application.Through large amounts of experimental investigation on adopted coaxial hydrogen-oxygen resonance igniter features,the thruster head ignition as well as thruster ground test were successfully conducted.The thruster ground tests included single-impulse,double-impulse and 3.0 seconds sustained run.Based on these ignition experiments and tests,thruster that met the proposed technical targets was developed.

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