The configuration twin-engine was an important pledge of safety and survival for Su-27, also enabling him to have a very good thrust/weight ratio.
The end result is the thrust/weight ratio of hydrogen-fueled engines is 30–50% lower than comparable engines using denser fuels.
The high thrust to weight ratio results in burnout at approximately 100,000 feet altitude within the atmosphere.
The second stage (24) employs uprated RL-10 engines (25) and has a thrust to weight ratio of 1.45 and can achieve orbit with a velocity change of approximately 24,500 feet per second.
The combined program was called Advanced Turbine Engine Gas Generator (ATEGG) with goals to improve thrust and reduce weight to achieve a thrust-to-weight ratio of 9.
In order to get maximum benefit from launching the stage vertically gravitational losses are minimized by a first stage thrust to weight ratio of 1.6.
The Chinese engines perform better in terms of fuel efficiency and thrust-weight ratio.
The Chinese engines perform better in terms of fuel efficiency and thrust-weight ratio, he said.
pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90 % of total rated thrust from start-up) of less than 30 ms.
Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90 % of total rated thrust from start-up) of less than 30 ms.
Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90 % of total rated thrust from start-up) of less than 30 ms.
Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90 % of total rated thrust from start-up) of less than 30 ms.
d. Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time' of less than 30 ms.
This invention can be used to retrofit an existing aircraft to achieve VTOL or manufacture a VTOL aircraft with a thrust-to-weight ratio smaller than 1.
Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90 % of total rated thrust from start-up) of less than 30 ms.
Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90% of total rated thrust from start-up) of less than 30 ms.
Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90 % of total rated thrust from start-up) of less than 30 ms.
Requêtes fréquentes français :1-200, -1k, -2k, -3k, -4k, -5k, -7k, -10k, -20k, -40k, -100k, -200k, -500k, -1000k,
Requêtes fréquentes anglais :1-200, -1k, -2k, -3k, -4k, -5k, -7k, -10k, -20k, -40k, -100k, -200k, -500k, -1000k,
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