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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 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 ]
An arcjet rocket or arcjet thruster is a form of electrically powered spacecraft propulsion, in which an electrical discharge is created in a flow of propellant [1] [2] (typically hydrazine or ammonia).
In the same month, NASA negotiated a finalized contract for SLS stages with Boeing, as Modification 127 to the existing Stages contract. This contract adjustment accounted for production and delivery, in full, of the first two core stages. [35] In spring and summer of 2015, the Space Launch System as a whole went through its critical design review.
is the initial value of the state vector; is the final value of the state vector; Sometimes, it is also useful to subject the system to control constraints because in case of continuous low-thrust transfer, there are always bounds on the availability of thrust.
Specific thrust is the thrust per unit air mass flowrate of a jet engine (e.g. turbojet, turbofan, etc.) and can be calculated by the ratio of net thrust/total intake airflow. [ 1 ] Low specific thrust engines tend to be more efficient of propellant (at subsonic speeds), but also have a lower effective exhaust velocity and lower maximum airspeed.
By service entry in 2018, 4,000 hours and 8,000 cycles of testing should be completed. [2] In 2021, General Electric tendered Passport to the USAF to be assessed in a contest against Rolls-Royce and Pratt & Whitney to reengine the B-52H Stratofortress. [9] The contract was awarded to Rolls-Royce. [10]
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.