Study on payload mass of rocket/dual-mode scramjet combined propulsion powered cruise vehicle

Research output: Contribution to journalArticlepeer-review

Abstract

For rocket/dual-mode scramjet(RDMSJ) combined propulsion powered cruise vehicle operating in near space, vehicle mass was divided into several components utilizing the"from top to bottom"mass assessment method, and payload mass assessment model was established. Under the system requirements of takeoff mass of 3 000 kg, cruise range of 1 500 km, some factors affecting the payload mass were investigated, including gas pressure /turbo pump feeding system, liquid hydrogen /JP-10 fuel, thrust to weight ratio of vehicle, and cruise range. Response surface models were established for payload mass and propulsion system mass responding to cruise range. The investigation results show that, for JP-10 fueled vehicle with gas pressure feeding system, the payload mass is 313 kg; if the vehicle is fueled by liquid hydrogen with neither feeding system, it can not carry any payload. The maximum cruise range of JP-10 fueled vehicle is 2270 km without any payload on board. The thrust to weight ratio of RDMSJ powered vehicle should be greater than 1.2 to maintain a lower level of propellant consumption.

Original languageEnglish
Pages (from-to)442-447
Number of pages6
JournalGuti Huojian Jishu/Journal of Solid Rocket Technology
Volume37
Issue number4
DOIs
StatePublished - 1 Aug 2014

Keywords

  • Hypersonic vehicle
  • Near space
  • Payload
  • Rocket/dual-mode scramjet combined propulsion

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