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The thrust-to-weight ratio is usually calculated from initial gross weight at sea level on earth [6] and is sometimes called thrust-to-Earth-weight ratio. [7] The thrust-to-Earth-weight ratio of a rocket or rocket-propelled vehicle is an indicator of its acceleration expressed in multiples of earth's gravitational acceleration, g 0. [5]
This page is an incomplete list of orbital rocket engine data and specifications. Current, Upcoming, and In-Development rocket engines ... Thrust: weight ratio [b ...
Thrust Thrust-to-weight ratio (kg) (lb) (kN) (lbf) RD-0410 nuclear rocket engine [1] [2] 2,000 4,400 ... Merlin 1D rocket engine, full-thrust version 467 1,030 825
Rocket technology can combine very high thrust (meganewtons), very high exhaust speeds (around 10 times the speed of sound in air at sea level) and very high thrust/weight ratios (>100) simultaneously as well as being able to operate outside the atmosphere, and while permitting the use of low pressure and hence lightweight tanks and structure.
In that case the thrust-to-weight ratio [nb 3] of the rocket engine limits the maximum acceleration that can be designed. It turns out that rocket engines generally have truly excellent thrust to weight ratios (137 for the NK-33 engine; [ 90 ] some solid rockets are over 1000 [ 2 ] : 442 ), and nearly all really high-g vehicles employ or have ...
Measuring and making comparisons of rocket engine thrust is more complicated than it may first appear. Based on actual measurement the liftoff thrust of Apollo 15 was 7,823,000 lbf (34.80 MN), which equates to an average F-1 thrust of 1,565,000 lbf (6.96 MN) – slightly more than the specified value. [citation needed
On November 24, 2013, Elon Musk stated that the engine was actually operating at 85% of its potential, and they anticipated to be able to increase the sea-level thrust to about 730 kN (165,000 lbf) and a thrust-to-weight ratio of 180. [31] This version of the Merlin 1D was used on Falcon 9 Full Thrust and first flew on Flight 20.
The engine's mass was 14,560 pounds (6,600 kg). With this thrust, the engine had a thrust-to-weight ratio of 51.2 and a specific impulse of 410 seconds (4.0 km/s) in a vacuum and 365 seconds (3.58 km/s) at sea level. [9] The RS-68 was gimbaled hydraulically and was capable of throttling between 58% and 102% thrust. [10]