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Beijing, China

Shang X.-S.,Navel Academy of Armament | Wu Z.-F.,The 31st Research Institute of CASIC | He Y.-F.,CPLA 8.1 Parachute Brigade
Tuijin Jishu/Journal of Propulsion Technology | Year: 2013

Solid rocket motor underwater test parameters change dramatically and signals often overlap severely. In order to solve the problem arisen due to this in data processing, the denoising method based on soft threshold wavelet transform was proposed and the analysis and processing of data for testing the thrust of solid rocket motor under water was performed. Comparison with conventional method shows that this method can divid dynamic data into the approximate component to reflect 'low frequency' characteristics and the detail components to reflect the 'high frequency' characteristics. This method is convenient for analysis of the motor performance test data. Variation characteristics of the data can be well retained in the simultaneous removal of test data interference. It can meet the requirements of the engineering application for data processing in solid rocket motor underwater test.

Shang X.-S.,Navel Academy of Armament | He Y.-F.,The Air Force Parachute Brigade | Li Y.-G.,Navel Academy of Armament | Cai F.-C.,The Third Academy of CASI
Tuijin Jishu/Journal of Propulsion Technology | Year: 2015

In order to adapt the requirements of wide TBCC engine inlet Mach number, based on the best Oswatitsch wave theory and CFD technology, considering the influence of factors such as the variable specific heat, shock wave and boundary layer disturbance, the design points of the inlet are determined to be Ma=4, H=21300 m and Ma=6, H=26600 m. Two-step hypersonic mixed compression inlet of TBCC engine has been carried on the preliminary design, analysis and comparison for the performance of the two kinds of scheme at design points, non-design points and the two dimensional flow field. Calculation results indicate that without considering viscous effects, along the flight path, the inlet design can satisfy the TBCC performance requirements and the present inlet has the good internal and external flow features. ©, 2015, Editorial Department of Journal of Propulsion Technology. All right reserved.

Shang X.-S.,Navel Academy of Armament | Wang Y.,Beihang University | Wu Z.-H.,Navel Academy of Armament
Tuijin Jishu/Journal of Propulsion Technology | Year: 2013

Taking a hypersonic missile as the application object, the installation characteristics of jet pre-cooling engine (SteamJet) was calculated. The model of the missile-steamJet engine integrated analysis was established. The determining method about the hypersonic missile lift and drag characteristics was set up. As combining with the mission profile, the missile weight and engine model, the constraint analysis for climbing and acceleration mission period were completed. With climbing rate of 100 m/s, 80 m/s and 50 m/s, the hypersonic missiles mission analysis was performed for cruising Mach number 4.0, 5.0 and 6.0 states. Calculation results show that the establishment of missile-engine integrated constrain analysis and mission analysis model is reasonable. Although missile dimbing rate and acceleration for equipment SteamJet engine is lower than the ramjet engine, the missile range is greatly improved, thus the application of SteamJet in hypersonic missile is feasible.

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