New answers tagged

1

Ram position feedback is sent back to the relevant channel in one of the two flight control computers via wire carrying an analogue signal. If it is a leading edge flap, aileron or rudder it is done twice. The big surfaces (Trailing Edge Flap and Horizontal Stab) are quad redundant. The signal is processed on a printed circuit board inside the box. There is ...


3

The shaft does not tilt, but the disk does. You understand the function of cyclic control correctly. It indeed changes the pitch of the individual blades, shifting the centre of lift. However, the blades are not strong enough to take that much bending load. If the rotor was completely stiff, they'd quickly break off. So instead the blades are allowed to ...


2

The blades are hinged near their roots, so they have some degree of freedom, and they flap up and down, so that the disk defined by the path of the blade tips is almost always at an angle with respect to the plane perpendicular to the rotational axle.


2

From your question, which is perfectly logical, there is one aspect that is leading you to an incorrect conclusion. In a helicopter Induced Drag does not increase with speed it reduces. In a fixed wing aircraft as the aerofoil travels through the air it will induce a flow downwards, exactly the same happens in a helicopter. Imagine being in the hover, as ...


0

Get lots of airspeed,pitch up within ac flight envelope limits and as you approach stall speed for your configuration, push forward so that 0 G is shown on the g meter, and keep it there. As you come over the top pull out again within it's so you neo not exceed Vne,Vmo or Mmo or g limit's for your planes . A parabola for a few minutes or second depending on ...


4

Like with two human pilots, you want control1 to be explicitly in one hands. With autopilot, it's the same: it should be either autopilot or you. In the case of 'breaching' the normal transfer protocol for whatever reason ("I have control" - "You have control", which in case of autopilot would be the autopilot disconnect button), there are two possible ...


3

As you mentioned, the main rotor thrust must support the weight of the helicopter in hover, and must also provide a propulsive force to overcome drag in forward flight. However, the induced drag is also a function of how the air is deflected downward by the rotor. The velocity of this downward deflection of air at the rotor is often called induced velocity....


1

The impact of these effects depend on the rotor design. E.g. a teetering rotor only includes the second effect you mentioned (tilted thrust vector), the 1st effect is absent. The first effect you mentioned increases as the "flap hinge" is moved away from the hub, giving more control force utilizing CF. You may be interested to know there's typically a 3rd ...


2

Yes, B737 pilots are trained in controlling th aeroplane using manual reversion. Both the forces at the controls and the aeroplane response to flight control inputs are quite different from those of the hydraulically powered elevator/aileron set-up. The difference in feel characteristics is quite pronounced, as we found in the past from flight control ...


2

It's a complicated answer, with many contributing factors in a multi-dimensional matrix. In a helicopter flying at forward speed, there are several stabilising stability factors and several de-stabilising ones. Before the helicopter can fly at speed, it needs to take off in a hover. The rotor provides the lift force to climb. Gravity applies down force in ...


-1

No ,the tail slides are not desirable for combat .The aircraft don't rise the nose per-say (pitching up) when maneuver he just Lower the tail by scoup in the elevator into the airflow below the aircraft .The fly by wire don't want to exceed the aircraft max AOA but sometimes the pilot with help from the inertia will go beyond safe AOA .So because the CG ...


1

Each control (collective, longitudinal cyclic, and lateral cyclic) can provide a specific range of blade root pitch. E.g. the collective may pitch the blade a total of 20 degrees from minimum to maximum position. The angle of attack (AOA) depends on the flight condition. The same "control blade angle" will result in a different AOA in descent compared ...


1

The main rotor often provides a pitch up moment about the CG, opposite to the diagram in the OP. This is due to it being located at a smaller station line, forward of the CG (even after accounting for tilt). The main rotor is flapped forward at speed, with its thrust tilted forward. However, the vector is still often positioned and oriented to provide a ...


0

In many ways helicopters are air planes in disguise. First, you draw the rotor with a slight dihedral. Now draw the lift vector for each rotor and you find: it will actually try to pitch the aircraft back upright (after forward acceleration goes to 0 (constant speed))! Even if the rotor were perfectly straight, its lifting force will not create a ...


1

Let's assume that the when the helicopter fuselage is horizontal (skids level), the CG is directly under the rotor mast. For a torque problem, we are free to choose any arbitrary pivot point, at least when rotational acceleration is zero and G-load is one, so no additional apparent inertial force due to rotational acceleration or G-loading acts upon the CG. ...


1

It does not truly matter what hand the “stick” is in. It matters how you were trained. It matters to what you have become accustomed. Case in point... In general, the pilot in command of a side-by-side pilot aircraft sits in the left seat. This is the seat in which most people begin their initial pilot training. You will typically control the control yoke ...


2

I am not sure what other organizations practice but I have been through simulator runs with a complete loss of hydraulics on the -800 and its something I never want to experience ever. The aircraft is still flyable, but now instead of being able to operate the yoke with ease, you will now find that it might even take two pilots to yank the control yokes and ...


Top 50 recent answers are included