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The particular take-off distance required may be shorter than the available runway length. In this case a lower thrust may be used. Lower thrust settings increase engine life and reduce maintenance costs. The take-off thrust available from a civil engine is a constant value up to a particular ambient temperature.
The required take-off thrust was 14,500 lb which would normally be set by advancing the thrust levers to give an EPR reading of 2.04. Due to EPR probe icing the value set, i.e. 2.04, was erroneous and actually equivalent to 1.70 which gave an actual thrust of only 10,750 lb.
Aircraft engine performance refers to factors including thrust or shaft power for fuel consumed, weight, cost, outside dimensions and life. It includes meeting regulated environmental limits which apply to emissions of noise and chemical pollutants, and regulated safety aspects which require a design that can safely tolerate environmental hazards such as birds, rain, hail and icing conditions.
When the energy is available, arcjets are well suited to keeping stations in orbit and can replace monopropellant rockets. Aerojet MR-510 series arcjet engines are currently used on Lockheed Martin A2100 satellites using hydrazine as a propellant, [ 3 ] providing over 585 s average specific impulse at 2 kW .
The thrust efficiency is the actual thrust as percentage of this. If, e.g., solar power is used, this restricts a {\displaystyle a} ; in the case of a large v e {\displaystyle v_{\text{e}}} the possible acceleration is inversely proportional to it, hence the time to reach a required delta-v is proportional to v e {\displaystyle v_{\text{e ...
High propellant density makes for compact size as well. These features plus simplicity and low cost make solid propellant rockets ideal for military and space applications. Their simplicity also makes solid rockets a good choice whenever large amounts of thrust are needed and the cost is an issue.
The Pratt & Whitney PW6000 is a high-bypass turbofan jet engine designed for the Airbus A318 with a design thrust range of 18,000–24,000 lbf (80–107 kN). Design and development [ edit ]
It could deliver up to 57,000 lbf (250 kN) of thrust with a specific impulse of 279 s (2.74 km/s) or 239 s (2.34 km/s) at sea level. Thrust was variable from 50 to 100 percent , and the restart capability allowed it to be shut down and restarted during flight when necessary.