# Introduction#

The following definitions will be revision, but a thorough understanding of them is imperative for the remainder of this course.

## Newton’s laws of motion#

In this course we utilise Newtonian Mechanics - Newton’s laws should be familiar, and you should be able to recite them:

1. An object remains at rest or in a state of uniform motion unless acted on by an external, unbalanced force.

2. Net force acting on rigid body is equal to its absolute momentum flux, or $$\sum\vec{F}=m\cdot a_{abs}$$.

3. Every action force has a reaction force that is equal in magnitude, and opposite in direction.

Newton’s second law will be used in this section to derive the full six degree of freedom (6DoF) equations of motion for unconstrained aircraft flight. Before diving into the derivation, further definitions are required:

• Most of the quantities used are easiest to define in different axes systems

• A thorough understanding of relative motion will need to be employed

### Reference Frames and Aircraft Axis Systems#

All motion is relative - there is no luminiferous aether1, and there is no universal ‘grid system’ in which we can define position or motion. In the absence of this, we define different axes systems depending on what helps to simplify the mathematics that we need to use - it is easier to define forces in an axis system where those forces are aligned with the reference system.

Newton’s laws are only valid in an inertial reference frame - one that is not moving. We use the Earth as our inertial reference frame - this is not actually the case as it is obviously moving, but for flight mechanics purposes, we rely on the fact that the rotation of the Earth is slow compared to aircraft motions.

#### A note on vector notation#

To differentiate vector quantities from scalar quantities, several conventions are commonplace. If $$U, V, W$$ are vector components, the vector may be defined using

• Boldface $$\displaystyle\mathbf{U}=[U,V,W]^T$$

• Arrow $$\vec{U}=[U,V,W]^T$$

• Underline $$\underline{U}=[U,V,W]^T$$

I tend to use $$\vec{U}$$ in typeset documents as it causes the least conflicts when using LaTeX. When writing on the board, I tend to use $$\underline{U}$$ notation as it is easier - but sometimes I’ll draw an arrow if I’m feeling adventurous3. I don’t mind which you use, as long as you are consistent within a single derivation. Just be aware that things change between sources.

#### Earth Axes#

We utilise the Earth axis system, see Figure :red:EarthAxes, because, for our purposes, it is an inertial reference frame - so we require this in order to utilise Newton’s second law. We make some simplifications, and impose the following:

• Assume the Earth is a flat plane 4

• NED (North, East Down) = $$x_E, x_E, x_E$$

#### Aircraft Body Axes#

We also require a frame of reference that is fixed to the aircraft because:

1. That is the frame of reference in which the pilot sits, so we require one to determine forces on them

2. Moments/products inertia, and centre of gravity position are easily defined in an axis system fixed to the aircraft

This axis system is usually defined with its origin at the aircraft centre of gravity.\

$$x$$ is defined positive forward, and may be defined along the propeller rotation axis for a single-engine propeller-driven aircraft, along the floor for a large transport aircraft, or along the wing root chord line.

$$y$$ is defined along the starboard axis along a plane equidistant vertically from both wings at each spanwise location ($$Y_B$$ does not not travel along a wing dihedral angle).

$$z$$ is defined down, normal to the plane defined by the $$x$$, $$y$$ intersection.

We can normally define thrust in aircraft body axes, and we may also define aerodynamic forces in body axes (as normal and axial force), but it is more convenient to define aerodynamic in stability axes as lift and drag.

#### Stability Axes#

Warning

Note that the nomenclature of wind/stability systems is inconsistent depending on which textbook you look at. The version presented herein is the most common, and the most sensible

Aircraft, in general, are usually flown at some angle of attack, $$\alpha$$ - which means that the incident freestream velocity is not aligned with the aircraft body axes. Lift and drag are defined parallel to, and normal to the incident flow vector, so we require an axes set called stability axes - $$[x_s, y_s, z_s]$$.

We rotate the aircraft body axes through $$\alpha$$, around $$y$$ - thus $$y=y_s$$.

The $$x/y$$ planes of body and stability axes intersect along the shared $$y, y_s$$ axis - [fig:stabilityplanes]{reference-type=”ref” reference=”fig:stabilityplanes”}.

The $$x/z$$ planes of body are co-planar, but rotated about $$\alpha$$ - [fig:stabilityplanesXZ]{reference-type=”ref” reference=”fig:stabilityplanesXZ”}.

It is important to note that this treatment neglects sideslip $$\beta$$ - so we are treating $$V_\infty$$ as the projection of the relative wind into the aircraft body $$x_b/z_b$$ plane.

Aircraft data is usually defined in the stability axes system - it is important, however, to have an appreciation of wind axes.