Helicopter airspeed indicating system

• US 4,300,200 A
• Filed: 11/23/1979
• Issued: 11/10/1981
• Est. Priority Date: 12/01/1978
• Status: Expired due to Term

• Current Assignee: Westland Aircraft Limited
• Original Assignee: Westland Aircraft Limited
• Inventors: Doe, Reginald A.
• Primary Examiner(s): Wise, Edward J.
• Application Number:
  US06/096,829
• Time in Patent Office: 718 Days
• Field of Search: 364/565, 364/567, 364/431, 364/432, 364/433, 364/426, 244/17.13, 73/509, 73/510, 73/530
• US Class Current: 702/144
• CPC Class Codes: G01P 5/00 Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft application of speed-measuring devices for measuring volume of fluid G01F

Abstract

This invention provides a helicopter airspeed indicating system for providing an indication of a theoretical airspeed of a helicopter in which it is fitted. The airspeed is calculated using measured weight and power values and a known relationship between power, weight and airspeed characteristics of the helicopter, and is particularly useful for providing an indication of helicopter airspeed at the low end of an overall speed range.

Claims

1. An on board apparatus for estimating the low end airspeed of a helicopter during flight comprising:

means for determining the helicopter applied power;

means for determining the weight of the helicopter;

means for storing predetermined confirmed measurements of the airspeed of the helicopter at various applied powers and weights;

means for determining an estimated airspeed using the determined power and weight and the stored measurements, and for outputting a signal; and

indicator means coupled to said determining means and responsive to said signal for displaying the estimated airspeed.

2. An airspeed apparatus as claimed in claim 1 wherein said means for storing measurements and said means for determining an estimated airspeed is a computer.

3. An airspeed apparatus as claimed in claim 2 wherein said computer compensates the determined applied power for power absorbed in vertical, horizontal and lateral accelerations and in rate of climb such that the compensated applied power is equivalent to the power for level flight conditions.

4. An airspeed apparatus as claimed in claim 3 further including means to actuate the airspeed apparatus as the helicopter leaves the ground.

5. An airspeed apparatus as claimed in claim 4 further including means to deactuate the airspeed apparatus when a maximum speed is exceeded.

6. An airspeed apparatus as claimed in claim 3 further including means for determining the position of the center of gravity of the helicopter.

7. An airspeed apparatus as claimed in claim 3 wherein said means to determine applied power and weight are continuously updated.

8. An on board method for estimating the low end airspeed of a helicopter during flight comprising the steps of:

determining the helicopter applied power;

determining the weight of the helicopter;

determining an estimated airspeed of the helicopter and outputting a signal based on predetermined confirmed measurements of the airspeed of the helicopter at various applied powers and weights; and

displaying the estimated airspeed on an indicator responsive to the outputted signal.

9. A method for estimating airspeed as claimed in claim 8 wherein the predetermined measurements are stored in a computer.

10. A method for estimating airspeed as claimed in claim 9 further including the step of compensating the determined value of applied power to an equivalent level flight power by accounting for power being absorbed by vertical, horizontal and lateral acceleration and by rate of climb.

11. A method for estimating airspeed as claimed in claim 10 further including the steps of:

assigning the airspeed an initial value of zero;

determining an estimated power from the stored measurements in the computer using the initial airspeed value and determined weight;

comparing the estimated power with the equivalent level flight power;

displaying the airspeed value where the estimated value is within a predetermined limit of the equivalent power value;

adjusting the airspeed value by a pre-selected increment; and

repeating the comparison of estimated power with equivalent power using the adjusted airspeed value and new determination of applied power and weight such that a continuous, iterative determination of airspeed is conducted.