Tripropellant rocket engine thrust chamber tests o

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Three-component of rocket engine thrust chamber test

To the flame structure, but difficult to get a more detailed flame structure. Three million full-size thrust chamber with regenerative cooling scheme, the two characteristic length of the three-component thrust chamber for the heat transfer calculations. -} L _-● 6 pan to avoid the rocket 32, 2006 from the thrust chamber wall temperature distribution shows that the maximum temperature appears in the throat, a large cooling heat in the throat area is small, so the throat, the highest temperature, is the most easily burned areas. From the thrust on the wall fin wall temperature curve shows the temperature in the 300-400K, the highest temperature in the throat 600-700K, because the temperature is lower than the thrust chamber wall materials, the thermal fatigue of a zirconium copper temperature, so the full-size thrust chamber cooling is feasible. 5 tripropellant application of rocket engine propulsion system on the sub-orbital vehicle to analyze, select three per engine propulsion system as a sub-orbital vehicle, compared with the hydrogen-oxygen engine,[link widoczny dla zalogowanych], three-component sub-orbital aircraft engines there for three advantages: 1. Reduce the quality of tank structure; 2. Reduce the launch vehicle size; 3. Larger take-off thrust-weight ratio. Sub-orbital vehicle concept of the overall program shown in Figure 8. Figure 8 suborbital aerodynamic shape Fig. 8Reaerodynamicconfigurationofsub-orbiter aerodynamic build sub-orbital spacecraft, propulsion, control and trajectory such as system design and performance analysis model,[link widoczny dla zalogowanych], built on the basis of the overall performance of sub-orbital vehicle model, and the establishment of a special sub-orbital vehicle's overall performance analysis software. Respectively as the take-off weight and flight range performance goals,[link widoczny dla zalogowanych], compared the liquid hydrogen / liquid oxygen engine, liquid oxygen / kerosene engine and hydrogen / liquid oxygen / kerosene engine three kinds of three-component sub-orbital vehicle programs, the results show that the hydrogen / LOX / kerosene engine as the three-component sub-orbital spacecraft propulsion system has performance advantages. Figure 8 LO, RP, and LH, respectively, liquid oxygen,[link widoczny dla zalogowanych], kerosene and liquid hydrogen, L and D, respectively, the total length of the aircraft and airframe diameter. 6 Conclusion The theoretical analysis, cold and hot test and numerical simulation of three-component engine research, development,[link widoczny dla zalogowanych], pilot testing of the technology for three-component thrust chamber of the development and laid a good foundation for basic research. Through long-term of the LOX / kerosene / hydrogen rocket engine tripropellant comprehensive study to deepen the three-component nozzle of the three-component performance and understanding of the combustion process, the nozzle design and performance analysis, combustion analysis, job conditions process studies, combustion stability, operating parameters and structural parameters on the combustion properties of the three groups of six per engine applications has made great progress. Thermal test results show that: oxygen Adjustable Venturi cavitation three-component model can be used to condition the engine regulation; and liquid hydrogen / liquid oxygen engine, the hydrogen / kerosene engine compared to liquid hydrogen / kerosene / liquid oxygen III -component sub-orbital vehicle engine applications have a performance advantage. Considering the flow characteristics, properties and atomization on the combustion properties of three-component nozzle should be given priority within the nozzle and the centrifugal type with external mixing nozzle. Centrifugal nozzle can improve the quality of the three-component spray nozzle; inner roller and outer nozzle flow characteristics of premixed-type complex, less effect than external mixing type spray outside the nozzle is significantly better. Three-component thrust chamber combustion efficiency increases with the hydrogen content was increased the overall trend, while improving the combustion stability; but premixed centrifugal nozzles with three exceptions per thruster. The best value of the oxygen coefficient of more than about 0.8-a 0.85, smaller than this value, I will promote the increase of the oxygen coefficient of combustion efficiency. Successfully achieved the status of the process of changing jobs, the performance index is proposed and analyzed the changes in law. Regenerative cooling heat transfer results show that the program full-size three-component thrust chamber of the liquid hydrogen flow to meet the cooling requirements.