nav inertial navigation bw

Inertial NavigationAdvantages

•instantaneous output of position and velocity

•completely self contained

•all weather global operation

•very accurate azimuth and vertical vector measurement

•error characteristics are known and can be modeled quite well

•works well in hybrid systems

Inertial NavigationDisadvantages

•Position/velocity information degrade with time (1-2NM/hour).

•Equipment is expensive ($250,000/system) - older systems had relatively high failure rates and were expensive to maintain

•newer systems are much more reliable but still expensive to repair

•Initial alignment is necessary - not much of a disadvantage for commercial airline operations (12-20 minutes)

Inertial Navigation – Basic Principle•If we can measure the acceleration of a vehicle we can

•integrate the acceleration to get velocity

•integrate the velocity to get position

•Then, assuming that we know the initial position and velocity we can determine the position of the vehicle at ant time t.

Inertial Navigation – The Fly in the Ointment

•The main problem is that the accelerometer can not tell the difference between vehicle acceleration and gravity

•We therefore have to find a way of separating the effect of gravity and the effect of acceleration

Inertial Navigation – The Fly in the Ointment

This problem is solved in one of two ways

1. Keep the accelerometers horizontal so that they do not sense the gravity vector

This is the STABLE PLATFORM MECHANIZATION

2. Somehow keep track of the angle between the accelrometer axis and the gravity vector and subtract out the gravity component

This is the STRAPDOWN MECHANIZATION

Inertial Navigation – STABLE PLATFORM

The original inertial navigation systems (INS) were implemented using the STABLE PLATFORM

mechanization but all new systems use the STRAPDOWN system

We shall consider the stable platform first because it is the easier to understand

Inertial Navigation – STABLE PLATFORM

There are three main problems to be solved:

1. The accelerator platform has to be mechanically isolated from the rotation of the aircraft

2. The aircraft travels over a spherical surface and thus the direction of the gravity vector changes with position

3. The earth rotates on its axis and thus the direction of the gravity vector changes with time

Inertial Navigation – Aircraft Axes Definition

The three axes of the aircraft are:

1. The roll axis which is roughly parallel to the line joining the nose and the tail

Positive angle: right wing down

2. The pitch axis which is roughly parallel to the line joining the wingtips

Positive angle: nose up

3. The yaw axis is vertical

Positive angle: nose to the right

Inertial Navigation – Aircraft Axes Definition

ROLL

PITCHY

AW

http://www.ion.org/publications/online-tutorial-intertial.cfm

Inertial Navigation – Platform IsolationThe platform is isolated from the aircraft rotation by means of a gimbal system

•The platform is connected to the first (inner) gimbal by two pivots along the vertical (yaw) axis. This isolates it in the yaw axis

•The inner gimbal is the connected to the second gimbal by means of two pivots along the roll axis. This isolates the platform in the roll axis.

•The second gimbal is connected to the INU (Inertial Navigation Unit) chassis by means of two pivots along the pitch axis. This isolates it in the pitch axis.

Inertial Navigation – Platform IsolationNow the platform can be completely isolated from the

aircraft rotations

Inertial Navigation – Gyroscopes

To keep the platform level we must be able to:

•Sense platform rotation and

•Correct for it

To do this we mount gyroscopes on the stable platform and install small motors at each of the gimbal pivots.

The gyroscopes sense platform rotation in any of the three axes and then send a correction signal to the pivot motors which then rotates the relevant gimbal to maintain the platform at the correct attitude

Inertial Navigation – Alignment

Before the INS can navigate it must do two things:

•Orient the platform perpendicular to the gravity vector

•Determine the direction of True North

Also it must be given:

•Initial Position: Input by the Pilot (or navigation computer)

•Velocity: This is always zero for commercial systems

Inertial Navigation – Orientation

In the alignment mode the INU uses the accelerometers to send commands to the pivot motors to orient the platform so that the output of the accelerometers is zero.

Note that the earth (and therefore the INU) is rotating so that it will be necessary to rotate the platform in order to keep it level.

Inertial Navigation – Gyrocompassing

•The rotation of the platform to keep it level is used to determine the direction of True North relative to the platform heading.


The platform is being rotated around the X and Y axes at measured rates:

RX=ΩcosΦcosα

RY=ΩcosΦsinα

Since Ω is known (15.05107 º/hour) we have two equations in two unknowns and can calculate

Φ (Latitude) and α (platform heading)

Inertial Navigation – NavigationOnce the INU has been aligned it can be put into

NAVIGATE mode .

In navigate mode, the outputs of the accelerometers are used to determine the vehicle’s position and the gyroscopes are used to keep the platform level.

This involves

1. compensating for the earth’s rotation

2. compensating for travel over the earth’s (somewhat) spherical surface

Inertial Navigation – Schuler OscillationTo compensate for the travel over the surface of

the earth the platform must be rotated by an amount d/R where d is the distance travelled and R is the radius of curvature of the earth

sR

θ

Inertial Navigation – Schuler OscillationThis leads to a phenomenon know as Schuler oscillation

At the end of the alignment procedure the accelerometers are almost never perfectly level.

Inertial Navigation – Schuler Oscillation

Assume for now that the aircraft remains at rest

The measured acceleration causes the INU to compute a velocity and hence a change in position.

This in turn causes the gyros to rotate the platform


Assume for now that the aircraft remains at rest

The measured acceleration causes the INU to think that it is moving an it computes a velocity and hence a change in position.

This in turn causes the gyros to rotate the platform


The direction of the rotation tends to level the accelerometer but when it is level, the computer has built up a considerable speed and thus overshoots. (this is like pulling a pendulum off centre and letting it go)


Characteristics of the oscillation:

a=-gsinθ or –gθ for small angles

θ = s/R where R is the radius of curvature

R

g

dt

d

R

a

dt

sd

Rdt

d

2

2

2

2

2

2 1differentiating twice


This is a second order differential equation whose solution is:

θ = θ0cos(ωt)

where θ0 is the initial tilt angle and

R

g

R

g

The period of this oscillation is 84 minutes

Inertial Navigation – Accelerometers

Requirements:

•high dynamic range (10-4 g to 10g)

•low cross coupling

• good linearity

• little or no asymmetry

Exacting requirements dictate the use of Force-Rebalance type of devices


Types:

•Pendulum

•floating

•flexure pivot

•Vibrating String or Beam

• MEMS (micro electromechanical systems)


Floated Pendulum


Flexure Pivot Pendulum


Vibrating Beam


MEMS


Three main types:

Spinning Mass

Ring Laser

MEMS


Spinning Mass:

Rigidity in Space:

A spinning mass has a tendency to maintain its orientation in INERTIAL space

Its rigidity (or resistance to change) depends on its moment of inertia and its angular velocity about the spin axis (INU gyros spin at around 25,000 RPM)

Precession;

If a torque τ is applied perpendicular to the spinning mass it will respond by rotating around an axis 90 degrees to the applied torque. I.e. ω× τ


Construction:


Spinning Mass Gyros:

Disadvantages:

•sensitive to shock during installation and handling (Pivots can be damaged)

•requires several minutes to get up to speed and temperature

•expensive


Ring Laser Gyro: (RLG) in service since 1986

Advantages over spinning mass gyros:

•more rugged

•inherently digital output

•large dynamic range

•good linearity

•short warm up time


Ring Laser Gyro: (RLG) in service since 1986

General Principle:


Ring Laser Gyro

Problems:

•Lock-in at low rotation rates due to weak coupling between the two resonant systems (coupling due to mirror backscatter)

Analagous to static friction (stiction) in mechanical systems

Causes a dead zone

Alleviated by “dithering” the gyro at a few hundred Hz

•Random loss of pulses at the output ( causes “drift”)


Fibre Optic Gyro

Similar concept to RLG except that amplification is not usesd

Two strands of optical fibre are wound in opposite directions on a coil form

Laser light is sent from a single source down both fibres

The outputs of the two fibres are combined at a photodiode

Rotation of the coil around its axis causes the two paths to have different lengths and the output of the photodiode provides a light dark pattern. Each cycle indicates an increment of angular rotation


Fibre Optic Gyro

Has the advantage of being rugged and relatively cheap

Sensitivity increases with length of fibre

Unfortunately, the longer the fibre, the lower the output signal.

Used on low performance systems


MEMS Gyro

All gyros to date have been quite large

in fact the sensitivity of spinning mass gyros and RLGs are a direct function of their size.

Efforts are being made to apply MEMS technology to gyros as well as to accelerometers

Inertial Navigation – GyroscopesMEMS Gyro

The MEMS gyro uses the Coriolis Effect

In a rotating system (such as the earth) moving objects appear to deflected perpendicular to their direction of travel.

The effect is a function of the velocity if the object and the rate of rotation


MEMS Gyro

In a MEMS gyro the times of a tuning fork are the moving object

MEMS gyros exhibit high drift rates and thus are not suitable for commercial aviation use

They are used in conjunction with GPS in “coupled” systems which use the best characteristics of each

Inertial Navigation – Strapdown SystemsThe main problem for an INS is to separate the vehicle acceleration from the effect of gravity on the accelerometers

In the stable platform, this is done by maintaining the accelerometers perpedicular to the gravity vector which allows us to ignore the effect of gravity

Another approach is to keep track of the gravity vector and subtract its effect from the outputs of the accelerometers

This is an analytical or computational implementation

Inertial Navigation – Strapdown Systems

As the name implies, the accelerometers are fixed or “strapped down” to the chassis of the INU and hence to the aircraft.

Since the gravity vector is three dimensional, three accelerometers are required to keep track of it.

In addition, three RLGs are mounted with their axes aligned with the x,y, and z axes (roll, pitch and yaw) of the aircraft respectively.


Alignment:

During the alignment procedure, the INS measures the direction of the gravity vector. Notice that the outputs of the accelerometers are proportional to the Direction Cosines of the gravity vector


Example:

If the outputs of the accelerometers are:

ax = 0.085773

ay = 0.085773

az = 9.805265

What are the roll and pitch angles?

Example:

If the roll and pitch angles are Φ and Θ respectively

aX = gsin Θ Note:

aY = gsin Φcos Θ

aZ = gcos Φcos Θ

Therefore: Θ=sin-1(aX/g)

and Φ= sin-1(aY/gcos Θ)


222ZYX aaag

Example:

Thus g = 9.806 m/s2

Θ = sin-1(0.085773/ 9.806 ) = 1º

Φ = sin-1(0.085773/(9.806 x 1) = 1º



Note that during alignment the RLGs on the x and y axes give a direct readout of the two platform rates required for gyrocompassing


Note:

The sensitivity of Ring Laser Gyro is:

N=4A/λL

Where: N is the number of fringes per radian

A is the area enclosed by the path

L is the Length of the path

λ is the wave length of the light

Note that the larger the area, the more sensitive the gyro

nav inertial navigation bw

Documents

roll axis

accelrometer axis

vertical yaw axis

gravity vector changes

effect of gravity

accelerator platform

nose upthe yaw axis

gravity componentthis