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| Cooling of electronic equipment cabinets |
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| Data processing device for FM multi-channel broadcasting |
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Power management process
| Details |
Inventors: Young, Harvey R.;
Assignee: The United States of America as represented by the Secretary of the Army (Washington, DC)
Primary Examiner: Casaregola; Louis J.
Assistant Examiner:
Attorney, Agent or Firm: Lane; Anthony T., Gibson; Robert P., Wilson, Jr.; Norman L.
A power management system is disclosed for an advanced helicoptor having h lift and thrust propulsion units and at least one power plant which comprises, a signal generator for generating a first signal which is proportional to the power available from the power plant, a power use gage connected to the lift propulsion unit which has an output that varies according to the amount of power used by that propulsion unit and a circuit which is connected to the power use gage and which receives the first signal for generating a second signal which is proportional to the amount of power remaining. The circuit is either used to power an indicator which indicates to the pilot the amount of power remaining for the thrust propulsion unit, or can be connected directly to a limit actuator for limiting the amount of power the pilot can apply to the thrust propulsion unit. |
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DETAILED DESCRIPTION The underlying concept of the invention is to subtract the torque (or power) required to drive the rotor(s) from the total available engine torque (or power) and make the remaining torque (or power) available to power the thrusting device (prop or fan).
Since the rotor torque (or power) changes with atmospheric and/or flight condition changes, a method is needed to perform the subtraction, i.
e.
engine torque minus rotor torque, in real time, and use the remainder as a signal to establish the setting (or limits) of the blade pitch of the thrusting device.
DETAILED DESCRIPTION OF THE INVENTION In an advanced helicoptor equipped with a propeller for forward thrust augmentation, the main rotor provides 100% of the lift and is capable of producing forces that cause the helicoptor to translate forwardly, to the side, or rearwardly.
The propellor develops thrust that accelerates or decelerates the helicoptor and/or maintains a steady speed, but in the longitudinal axis only.
In operation at lower speeds, the pilot has the option of using only the main rotor for forward acceleration or of using only the propeller or a combination of forces developed by the rotor and propeller.
At higher speeds, as rotor stall is encountered, the propellor would produce most or all of the required forward thrust.
This however is only one possible configuration of an advanced, high speed helicoptor.
Other configurations may use fans rather than props, dual rotors rather than a single rotor, a conventional tail rotor in lieu of a fan-in-fin, and multiple engines.
The principle of this invention can be applied to any of these helicoptor configurations.
A common method of measuring torque supplied to a helicoptor rotor is to strain gage the rotor shaft and use a pre-calibrated strain-to-torque relationship for determining the instantaneous torque supplied to the rotor.
Rotor power can be derived by simply multiplying torque by shaft rotational speed and dividing by a constant to obtain horsepower
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