It was also found that the liftoff thrust to weight ratio (T/W) on the booster-orbiter should be 1.3. This leads to a low dry weight and still ... DO Stanley,TA Talay,RA Lepsch,... 被引量: 3发表: 1991年 Long-term/strategic scenario for reusable booster stages - ScienceDirect (Fig...
Perhaps more conventional – if only slightly- were Harry Ricardo’s plans for diesel two-strokes. Andrew Nahum’sexcellent paper‘Two-Stroke or Turbine’ examines these engines in detail, but these were to be ‘sprint’ engines of very high power/weight ratio, with the added advantage of run...
and high temperature, the research object was expanded to a nonlinear dynamatics system of linear paramter uncertain in control maxtrix, the paper provided adaptive adjust function to compensate the influence from the unce...
A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and
The small cross section of the 292 series bearings have favourable speed, space and weight characteristics. Smaller and more cost-effective equipment can be designed for longer bearing service life or higher output as a result of the high com- bined load carrying capacity of SKF spherical roller...
Remaining burn time (time to go) λ¯: Unit vector defining average thrust direction λ¯˙: Rate vector defining desired turning rate τ: Ratio of vehicle mass to mass flow rate μ: Earth gravitational constant -2967(1964) Google Scholar ...
Additionally, to avoid flow separation in the nozzle, it was necessary to have a relatively low area ratio which led to a decrease in potential performance. The overall design requirements above were broken down into more specific requirements. This complete set of requirements was used as an ...
the spacing between them has a significant impact on the performance of these new aircraft configurations. A testbed was designed and validated to investigate the effects of parameters such as axial distance and lateral distance between rotors on the thrust performance of the Staggered Rotor System. ...
Although these margins are clearly defined for static operating conditions, when the aeroengine undergoes harsh maneuvers, the compressor faces a fast increase in the pressure ratio with a quasi-constant mass flow [33]. Considering the causality of shaft speed, pressure and mass-flow, the ...
However, it is noticeable that there was no metallic surface spalling due to the solid contact. It can be clearly seen that a tribochemical reaction took place in the area of the highest slide to roll ratio. As a reminder, this area is at the two ends of a roller element in ...