research on sub-orbiter reusable launch vehicle projection and aerodynamics characteristics analysis
- Paper number
IAC-08.D2.10.4
- Author
Mr. Cai Yu, China
- Year
2008
- Abstract
In order to satisfy the launch market demand for small satellite, reduce the launch cost and promote the innovative technology, Research on several future launch project is carried by CALT, and Sub-orbit Reusable Launch Vehicle is selected from these projects. Aerodynamic configuration design is based on technology elements for Reusable Launch Vehicle and adaptability correction is adapted for system design requirement. Research on aerodynamic configuration design, numerical computation analysis for boost flight stage and entry flight stage is carried out. These work include: general aerodynamics characteristic computation, flight aerodynamic lift to drag ratio characteristic, lognitudinal and directional stability characteristic, flow separation for high angle of attack flight, safety flight corridor, aerodynamic control face efficiency and effect for the whole aircraft aerodynamic characteristics, developing patch grid and mixed grid technology for complex configuration to improve grid building efficient and quality, developing the parallel computation and distributed computation technology based on cluster computer to improve the computation efficiency, developing the multi-grid technology to accelerate numerical computation. Carry out the general aerodynamic force wind tunnel test for typical condition, and compare the numerical result with the wind tunnel test result. Keywords: Sub-orbiter Reusable Launch Vehicle; Aerodynamics Characteristics
- Abstract document
- Manuscript document
IAC-08.D2.10.4.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.