Other
Scientific paper
Feb 2005
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563..387o&link_type=abstract
Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,
Other
Scientific paper
The scramjet flight test, Hyshot 2, flew on the 30 July 2002. The programme, led by the University of Queensland, had the primary objective of obtaining supersonic combustion data in flight for comparison with measurements made in a shock tunnel. QinetiQ was one of the project sponsors, and also provided aerodynamic data and trajectory predictions for the ballistic re-entry of the spinning sounding rocket. This paper presents the reconstruction of the Hyshot2 trajectory from onboard measurements with accelerometers, pressure transducers, a magnetometer and a horizon sensor. LIST OF SYMBOLS a orbit semi major axis, m av acceleration along the velocity vector, m.s-2 ay acceleration along the body y axis b orbit semi minor axis, m e orbit eccentricity f ratio of drag to axial force g local gravity, m.s-2 h length of Earth tangent, m kyy radius of gyration, 123cm m UQ-Orion mass, 239kg p vehicle spin pN Nitrogen tank pressure, kPa r distance from the centre of the Earth, m t time from ignition s u horizontal velocity, m.s-1 xa distance from the centre of gravity to the accelerometer, 131cm xF distance from the centre of gravity to the cold gas thruster, 194cm Ath cold gas nozzle throat area, 14.5mm2 B magnetic flux in global coordinates, Gauss CF Thrust Coefficient H angular momentum vector Ixx Roll inertia Iyy Pitch inertia, 361kgm2 M Mach number Pa fuelled intake pressure Pb unfuelled intake pressure Pt pitot pressure, kPa Re radius of the Earth, km T horizon sensor period, s V velocity along the flight path, m.s-1 x, y, z body axes, m X, Y, Z global axes, m latitude, rad longitude, rad flight path angle, rad angle of the horizon sensor sight from the vehicle, rad Pitch, rad angle between the centre of the Earth, the horizon sensor and the horizon, rad angle around the great circle, rad density, kg/m3 angle of attack, rad horizon sensor pulse duration, s Roll angle, rad half the roll angle through which reflected light from the Earth is sensed, rad angle of inclination of the orbit plane, rad Yaw angle, rad azimuth, rad Subscripts 0 ignition, t=0s 1 end of launch rail, t=0.5s 2 end of launch / start of space phase, t=60.5s 3 apogee, t=286.6s 4 end of space phase, t=512.8s 5 start of re-entry phase, t=508.1s Superscript Inertial coordinate system
Cain T.
Owen Richard
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