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Technical Information

Catalogue No: C0584
Category: Flight Control
Object Type: Sensor/Transducer
Object Name: Accelerometer
Part No: 12-014-01
Serial No: 001/72
Manufacturer: Elliott Bros (London) Ltd
Division: Unknown
Platform(s): Jindivik
Year of Manufacture: 1972
Dimensions: Width (mm): 66
Height (mm): 59
Depth (mm): 87
Weight (g): 209
Location: Rack RAA09 [Main Store]

Type No. 12-014-01
Ref. No.
Ser. No. 001/72
Code No.
Modification Record -
[inspection mark]


This is likely to be an Integrating Gyroscopic Accelerometer. A green paper label adhered to this unit indicates it was fitted to Jindivik.
The Accelerometer was mounted on the centre fuselage bulk head.

Accelerometers measure the linear acceleration of the moving vehicle in the sensor or body frame, but in directions that can only be measured relative to the moving system (since the accelerometers are fixed to the system and rotate with the system but are not aware of their own orientation). Accelerometers are electromechanical devices that will measure acceleration forces. These forces may be static, like the constant force of gravity, or they could be dynamic - caused by moving or vibrating the accelerometer. By measuring the amount of static acceleration due to gravity, you can find out the angle the device is tilted at with respect to the earth. By sensing the amount of dynamic acceleration, you can analyse the way the device is moving.

An Integrating Gyroscopic Accelerometer is a type of accelerometer that can measure acceleration and simultaneously integrates the acceleration against time to produce a speed measure.

The sensing element is a pendulous mass, free to pivot by being mounted on a bearing. A spinning gyroscope is attached such that it would restrain the pendulum against "falling" in the direction of acceleration. The pendulous mass and its attached gyroscope are themselves mounted on a pedestal that can be rotated by an electric torque motor. The rotational axis of this pedestal is mutually orthogonal to the spin axis of the gyroscope as well as the axis that the pendulum is free to move in. The axis of rotation of this pedestal is also in the direction of the measured acceleration.

The position of the pendulum is sensed by precision electrical contacts or by optical or electromagnetic means. Should acceleration displace the pendulum arm from its null position the sensing mechanism will operate the torque motor and rotate the pedestal such that the property of gyroscopic precession restores the pendulum to its null position. The rate of rotation of the pedestal gives the acceleration while the total number of rotations of the shaft gives the speed, hence the term "integrating". A further level of integration of shaft rotations by either electronic means or by mechanical means, can record the displacement or distance travelled, this latter mechanical method being used by early guidance systems prior to the availability of suitable digital computers.

In most implementations the gyroscope itself is cantilevered on the end of the pendulum arm to act as the pendulous mass itself. Up to three such instruments may be required for each dimension of an INS with the three accelerometers mounted orthogonally generally on a platform stabilized gyroscopically within a system of gimbals.


By tracking both the current angular velocity of the system and the current linear acceleration of the system measured relative to the moving system, it is possible to determine the linear acceleration of the system in the inertial reference frame. Performing integration on the inertial accelerations (using the original velocity as the initial conditions) using the correct kinematic equations yields the inertial velocities of the system and integration again (using the original position as the initial condition) yields the inertial position.

Inertial navigation combines the constant direction-seeking properties of gyroscope with accelerometers and integrators to provide a navigation system with the following properties:

(1)   Its own initial definition of True North on the ground, by the technique known as gyro-compassing.

(2)   A memory of the direction of True North.

(3) Definition of the local vertical under all flight conditions.

(4) Provision of aircraft plan velocity and position.

(5) If fitted with a third vertical accelerometer whose integrated outputs are monitored by barometric height, it can also provide instantaneous vertical velocity.

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