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Unified management of collective pitch of the main rotor, and engines
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Unified management of collective pitch of the main rotor, and engines

Joint collective control of the main rotor and engine

 

Management NV and common step motors helicopter collective pitch lever carried 1, which is cinematically connected to the slide by a lever AP 10 and 8 levers at the same time the fuel assembly located on the engines.

Collective pitch lever with locking system in any position to the left of the pilot seat. For fixing lever are friction device with manual or hydraulic control.

Changes associated with collective pitch control of the helicopter engine power or by mechanical kinematic link, either automatically via the speed regulator. In both cases, it provides maintenance of the set speed when changing HB collective pitch, as at the same time the engine power is adjusted accordingly. In the case of the mechanical coupling step with the gas knob step has a special correction rotation handle coupled to the throttle (fuel lever) of the motor. With this handle, the pilot can adjust the speed HB within limits regardless of its steps.

Automatic speed control when changing its HB collective pitch angle of attack and airspeed of the helicopter is usually carried out by changing the fuel supply to the engine. Autonomous control system of the power plant can be located directly inside the engine. It provides a change in its capacity as a hand in a range from idle

before take-off mode, and automatic maintenance of the set speed constant NV. This engine control system can work without manual operation "step-gas", ie collective pitch lever can only change the value of the step without moving the lever of the fuel supply, which should be transferred to the "automatic". Rebuilding speed controller, it is possible to change the range limit, it is necessary to obtain optimal operating conditions of the power plant as a function of altitude and airspeed.

collective control

There's also another system of automatic speed control NV, in which the stabilizer is used - an automatic fuel control is included in the board manual "step-gas" through the sliding rod. The pilot may at any time intervene in the management. The stabilizer may be turned off in the event of any malfunction. Sliding Rod working on stabilizing the speed is automatically set as the neutral position, the capacity for normal manual control.

The range of the stabilizer speed through the sliding rod may be up to 40-50% full stroke of the lever on the fuel delivery engines. The inclusion of a stabilizer in incomplete speed control range increases the safety in his refusal. At the same time, the presence of manual control allows the pilot to change modes when sudden flight to intervene in the management and to increase the range required stabilizer. When one of the automatic engine displays running engine to increase capacity up to take-off and more - depending on your flight mode. In the presence of a stabilizer handle speed correction pilot does not use, but it should be retained for use in case of failure of automation.

On helicopters with two or more engines, other than of a "step-gas", establishes a system of separate power control engines. The reduction of engine power is achieved by moving the lever down (away from you), an increase - moving the lever up (to itself). These levers are substantially on the ground in the separate engine testing and in emergency cases in flight, if necessary restarting of a failed engine.

To separate off the engines in the cockpit has control handle stop valves, located in a convenient place to manage.

For emergency engine shutdown (in case of fire) the pilot can further cut off fuel to the engine by means of fire hydrants.

To improve the characteristics of balancing single-rotor helicopter collective control NV, usually associated with the stabilizer 4. Especially important this relationship is to go to the modes of motor planning and autorotation. The control unit is connected to the slider stabilizer AP.

The dependence of changes in the angle of installation of the stabilizer of the total step HB.

To change when the collective pitch HB minimize deviation AP ring, thrust 3, reaching a rocking longitudinal or transverse control must be long enough and spaced far as possible perpendicular to the direction of movement of the slide. The significance of this relationship is small junk. In light helicopters can be used special kinematics, completely eliminating the relationship of longitudinal and transverse control of the collective pitch. However, the use of such a circuit for heavy helicopters lead to a substantial increase in weight of the mechanical element control wiring.

Kinematic HB control circuit may be configured so that the three channels operate simultaneously three MG. Such kinematic scheme of the State Control HB ensures the independence of control channels NV, to create an optimal KSS AP and reduce the need to strengthen security on stocks GIs.

 

Comments

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I will not go into the details of the assembly, but the above options work only considered the ideal in other cases it situatsii.tak emergency such as the angle of attack depends on HB gidracha. so for example during acceleration and angle of rise-takeoff will be dramatically different. that is, a start on my part is necessary because when overclocking HB angle must change towards umenscheniya degrees step. I want to give a special dimension to the critical angle of attack of the propeller.

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