Measuring and testing – Dynamometers – Responsive to multiple loads or load components
Patent
1984-02-15
1986-05-06
Ruehl, Charles A.
Measuring and testing
Dynamometers
Responsive to multiple loads or load components
2160, 7386258, G01L 522
Patent
active
045863873
DESCRIPTION:
BRIEF SUMMARY
This invention relates to a flight test aid and in particular it relates to a unit that is arranged to measure the force that is applied by a pilot to the control column of an aircraft in order to adjust the ailerons and elevators whilst manoeuvering the aircraft in flight.
It is necessary when flight testing an aircraft to know how much force must be applied to the control column in order to perform various manoeuvers.
The object of the present invention is to provide a simple and effective device that, rather than requiring special preparation of the aircraft to be tested by fitting load measuring equipment to the control column, is an independent unit that may be carried by the pilot and thus be applicable to any aircraft that it is necessary to test.
The invention uses at least two force sensors that are fitted to a glove or some similar article that may be worn on the hand of the pilot in the case of a control column, the sensor being fitted across the palm and heel of the thumb, hereinafter referred to as a palm force sensor, and across the fingers, hereinafter referred to as a finger force sensor and being positioned so that they are interfaced between the hand and the column where they sense the forces exerted by the hand on the column, the palm force sensor sensing force used when pushing the column, and the finger force sensor sensing the force used when pulling the column.
By turning the hand to position the sensors on the lateral surfaces of the control column it is possible to measure the forces required to roll the aircraft to either the right or the left.
In its preferred form the sensors contain flexible sacs filled with a fluid such as silicone oil that are connected by small flexible tubes to pressure transducers, these in turn being connected to electronic circuits that convert the signals from the transducers into a form suitable for visual display by digital or other means or for connection to a recording device.
The two sensors are generally of different dimensions because of the limitations imposed by their positions, the finger force sensor preferably spans two fingers only as the first and fourth fingers generally should be left free to operate switches on the control column. It is therefore necessary that the electronic circuits can adjust the signal from each of the transducers to give the required force reading. It is also necessary to remove any component of the reading brought about by the pilot's hand gripping the control column.
These objectives are achieved by adjusting the magnitude of the output signal from each transducer, by opposing them in sign thus creating a difference that cancels out the grip component of the signals allowing the force components to be identified and displayed. The signals may also be fed into other electronic data gathering and processing equipment to provide repeat displays, information on the maximum forces used during a manoeuver, or permanent record of the forces exerted during the course of the tests.
The display unit may be mounted on the glove itself or, by use of appropriate electrical connections, on the pilot's knee pad or some convenient part of the cockpit structure to make it easier for the pilot to read the display during the flight.
Thus the invention relates to a flight test aid comprising means to measure force that is applied by a pilot to the control column of an aircraft to adjust the aileron and elevators or other control surfaces while manoeuvering the aircraft in flight, having a first force sensor, a second force sensor, display means to indicate force in the sensors, and means to locate the sensors between the hand of a pilot and the control column, the means being arranged to locate the sensors on substantially opposite sides of the control column when the pilot grasps the control column.
According to a variation the sensors may be applied to the rudder pedals.
In order that the invention may be more fully understood an embodiment thereof will now be described with reference to the accompanying drawings in which:
FIG. 1
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Clarke Robert E.
Menadue William I.
Morgan Garth A.
Ruehl Charles A.
The Commonwealth of Australia
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