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Volume 40 Issue 4
Apr.  2014
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Journal of Beijing University of Aeronautics and Astronautics  > 2014  >  40(4): 473-478.
Jiang Yazhong, Jiang Chongwen, Gao Zhenxun, et al. Mass estimation method and its application for horizontal takeoff horizontal landing two stage to orbit system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(4): 473-478. doi: 10.13700/j.bh.1001-5965.2013.0299(in Chinese)
Citation: Jiang Yazhong, Jiang Chongwen, Gao Zhenxun, et al. Mass estimation method and its application for horizontal takeoff horizontal landing two stage to orbit system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(4): 473-478. doi: 10.13700/j.bh.1001-5965.2013.0299(in Chinese)
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Mass estimation method and its application for horizontal takeoff horizontal landing two stage to orbit system

doi: 10.13700/j.bh.1001-5965.2013.0299

  • National Laboratory for Computational Fluid Dynamics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 28 May 2013
  • Publish Date: 20 Apr 2014
    Abstract
  • Aiming at transportation missions to low global orbit, a mass estimation method was proposed for horizontal takeoff horizontal landing two stage to orbit (TSTO) transportation systems considering thrust-drag characteristics in different flight stages and specific impulse variations in different engine modes. Three schemes of turbine based combined cycle-reusable rocket (TBCC-RR), rocket based combined cycle-reusable rocket (RBCC-RR), and reusable rocket-reusable rocket (RR-RR) were designed and compared for a mission to deliver 8 t payloads to a 200 km orbit. Influences of several parameters on design results were analyzed, including the separation point, throat-drag ratio and structure mass fraction of the first stage vehicle. The position of separation point has a great influence on TSTO schemes. If a RBCC vehicle is used as the first stage, it's recommended that the separation take place when the scramjet is turn off. Though TBCC-RR scheme leads to a smaller gross takeoff mass, RBCC-RR scheme has a smaller structure mass. The most effective way for gross mass reduction is to cut down the structure mass fraction and another approach is to improve throat-drag ratio of the vehicle.

     

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