Hinge moment coefficient is
function of control surface geometry, aircraft specification, angle of attack, and surface deflection
. A hinge moment prediction tool is developed based on the Roskam’s method to calculate hinge moment coefficient. … Control force is one kind of cueing aspect in aircraft.
What is hinge moment in aircraft?
“Hinge moment” is
the technical name for the force required to deflect a control surface
. In small, relatively slow airplanes, hinge moments are not very large; pilots move the controls with ease. But as control surfaces get larger and speeds get higher, hinge moments grow rapidly.
What is the hinge moment?
The hinge moment is
the moment acting about the hinge line of a control surface that must be overcome to move the control surface when a pilot exerts force command on the control stick
.
What is elevator hinge moment?
The elevator hinge moment is commonly defined as: (1) where is the aerodynamic elevator hinge moment, is
the planform area of the elevator
and is the mean chord of the elevator (not the whole airfoil, just the section aft of the hinge line). Generally, it is not possible to determine an analytical expression for .
What does stick free mean?
The condition where the hinge moment is equal to zero
is called the “stick free” condition. Under these conditions, the aerodynamic characteristics including the neutral point change. … All stick free conditions are obtained by setting the hinge moment equal to zero.
What is rate of turn in aviation?
In turning flight,
the number of degrees of heading change per unit of time
(usually measured in seconds) is referred to as the rate of turn. By definition, a rate one or standard rate turn is accomplished at 3°/second resulting in a course reversal in one minute or a 360° turn in two minutes.
Which of the following is correct for hinge moment?
Which of the following is correct for hinge moment? Explanation: Hinge moment coefficient is
function of number of factors
such as tail angle of attack, tail setting angle, etc. Due to downwash the angle of attack at tail will be more. Lifting property of an airfoil and sphere will be different.
What is a horn balance?
Horn Balances. The horn balance is
a section of the control surface at the tip that extends forward of the hinge line
. It extends outboard of the tip of the fixed surface the control surface rides on, hence the term “overhanging or overhung balance.”
What is the purpose of a servo tab?
A servo tab is a small hinged device installed on an aircraft control surface
to assist the movement of the control surfaces
.
What is the stick fixed neutral point?
The determination of the stick-fixed neutral point consists of
finding the c.g. position for which the slope of the η
trim
– C
L
curve becomes zero
. In general, it is not usually necessary to achieve this actual condition in flight, as it can be found by extrapolation from flight tests at more forward c.g. positions.
What is a Dutch roll in an aircraft?
Answer: Dutch roll is
a natural aerodynamic phenomenon in swept-wing aircraft
. It is caused by the design having slightly weaker directional stability than lateral stability. The result is the tail of the airplane seeming to “wag” or move left and right with slight up and down motion.
What is an inset hinge balance?
A form of aerodynamic balance and a method of reducing hinge movement
. The hinge line is set inside the control surface by 20 to 25% of the chord length, thus reducing the movement arm.
What is aerodynamic balancing?
[‚e·ro·dī′nam·ik ′bal·əns] (engineering)
A balance used for the measurement of the forces exerted on the surfaces of instruments exposed to flowing air
; frequently used in tests made on models in wind tunnels.
What does stick-fixed mean?
adjective.
Aeronautics
.
Of or relating to flight during
which the control column is held in a fixed position.
What is the difference between stick-fixed and stick-free stability?
In the analysis of stick-fixed longitudinal static stability it is assumed that the
elevator deflection remains constant even after the disturbance
. The analysis of the longitudinal static stability when the elevator is free to rotate about its hinge line is called stick-free stability.
Which of the following is correct to trim an aircraft at positive AOA?
Explanation: To trim an aircraft at positive AOA, it is required that
aircraft has positive value of zero lift moment coefficient
. Hence, to trim aircraft at a positive angle of attack, aircraft should be designed with Cm0 positive i.e., Cm0>0.
