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A minimum control speed flight test method for fixed-wing twin-engine propeller aircraft suitable for ccar and far23 parts
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A fixed-wing and propeller technology, applied in the field of flight test, can solve the problems of high power, large climb angle, etc., and achieve the effect of not difficult to execute, easy to operate, and improve comfort
Active Publication Date: 2017-12-19
HARBIN
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Summary
Abstract
Description
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Problems solved by technology
[0003] The purpose of the invention: to solve the problem of excessive climb angle caused by high power in the minimum control speed flight test of fixed-wing aircraft
Method used
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Examples
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Effect test
Embodiment 1
[0014] An example of the minimum control speed in the air of Yun 12F aircraft taking off with flaps at 0 degrees
[0015] 1. The aircraft is at an altitude of 3,000 feet, with flaps at 0 degrees, the landing gear retracted, the maximum continuous power of both engines, trim at a speed of 97 knots, and the feathering switch in the ready position;
[0016] 2. Reduce the engine power to about two-thirds of the maximum continuous power, that is, 2000 foot-pounds, maintain a controlled flight speed of approximately 97 knots, and establish a stable climb;
[0017] 3. Increase the power of the twin engines to the maximum continuous power, and control the steering wheel at the same time, and adjust the speed of the aircraft to 85 knots under the condition of increasing the maximum continuous power;
[0018] 4. Turn off the left engine suddenly, make it stop and feather the engine, and keep the right engine at the maximum continuous power state;
[0019] 5. After 2 seconds of dynamic ...
Embodiment 2
[0021] An example of the minimum control speed in the air for take-off of Yun 12F aircraft with flaps 10 degrees
[0022] 1. The aircraft is at an altitude of 3,000 feet, with flaps at 10 degrees, the landing gear retracted, the maximum continuous power of both engines, trim at a speed of 88 knots, the feathering switch in the ready position, and hold for 10 seconds;
[0023] 2. Increase the engine power to about two-thirds of the maximum continuous power, that is, 2000 foot-pounds, maintain a controlled flight speed of approximately 88 knots, and establish a stable climb;
[0024] 3. Increase the power of the twin engines to the maximum continuous power, and control the steering wheel at the same time, and adjust the speed of the aircraft to 84 knots under the condition of increasing the maximum continuous power;
[0025] 4. Turn off the left engine suddenly, make it stop and feather the engine, and keep the right engine at the maximum continuous power state;
[0026] 5. Aft...
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PUM
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Abstract
The invention discloses a minimum control speed flight test method, applicable to CCAR and FAR23, of a fixed-wing double-engine propeller-driven aircraft and belongs to the technical field of a flight test. The adopted technical scheme is that a new speed balance point is adopted; suitable middle power is used for replacing full-engine continuous maximum rating stable state; the key engine is cut off immediately after the power is rapidly increased to a required maximum power state. The minimum control speed flight test method disclosed by the invention has the advantage of mainly solving the problem that in a flight test the angle of climb is too large because the engines of some fixed-wing airplanes are relatively large in power.
Description
technical field [0001] The invention discloses a minimum control speed flight test method applicable to CCAR and FAR23 fixed-wing twin-engine propeller aircraft, and belongs to the technical field of flight test. Background technique [0002] The purpose of this invention is to propose a minimum control speed flight test method for a fixed-wing twin-engine propeller aircraft. In the past, the basic idea of the flight test was to keep the aircraft flying straight and trimmed at 1.5 times the stall speed at the take-off power of the twin engines, and adjust to the predetermined critical engine After the stop speed, the critical engine is turned off, and the other engine maintains the take-off power, and finally determines the target data required for this flight test. This method is applicable to most of the aircraft, but there are few aircraft in the world represented by the Y-12F aircraft, and the aircraft with relatively large power and based on the Airworthiness Certific...
Claims
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Application Information
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