An innovative concept is proposed for atmospheric entry probe deceleration, wherein one or more deployed rotors (in autorotation or wind- turbine flow states) on the aft end of the probe effect controlled descent. This concept is particularly oriented toward probes intended to land safely on the surface of Venus. Initial work on design trade studies is discussed.
Rotary-Wing Decelerators for Probe Descent Through the Atmosphere of Venus
2004
8 pages
Report
No indication
English
Astrophysics , Spacecraft Trajectories & Flight Mechanics , Deceleration , Planetary atmospheres , Rotary wings , Venus(Planet) , Atmosphere entry , Probes , Buoyancy , Descent , Landing , Trim(Aerodynamics) , Autorotation , Spacecraft trajectories , Rotors , Surfaces , Terrain , Pitch(Inclination) , Symposia , Surface temperature , Wind turbine flow state , Decadal study , New frontiers program , Venera technique , Tessera , Dense atmosphere , High surface temperatures , Rw(Rotary wing) , Rw decelerators , Engineering design analysis , Descent rate control , Descent trajectory control , Soft flare landings , Pitch control , Fineness ratio
Rotary Wing Decelerators for Miniature Atmospheric Entry Probes
British Library Conference Proceedings | 2009
|Rotary Wing Decelerators for Miniature Atmospheric Entry Probes
British Library Conference Proceedings | 2009
|