Navigational indicating system for rotary wing aircraft

• US 7,324,016 B1
• Filed: 11/22/2005
• Issued: 01/29/2008
• Est. Priority Date: 11/22/2005
• Status: Expired due to Fees

• Current Assignee: the united states of america as represented by the secretary of the navy
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Milgram, Judah H.
• Primary Examiner(s): Lee; Benjamin C.
• Assistant Examiner(s): PHAM, LAM P
• Application Number:
  US11/288,070
• Time in Patent Office: 798 Days
• Field of Search: 340/946, 340/978, 340/981, 362/470, 244/17.11, 416/5, 731/78.H, 701/14
• US Class Current: 340/981
• CPC Class Codes: B64C 27/023 Construction of the blades; Coating of the blades
• CPC Class Codes: B64C 27/46 Blades
• CPC Class Codes: B64D 2203/00 Aircraft or airfield lights using LEDs
• CPC Class Codes: B64D 47/06 for indicating aircraft presence

Abstract

Red, green and white colored lights are emitted from navigation orientation indicating light emitting devices mounted within a helicopter rotor blade near its tip. The light emissions from such devices are under control to respectively indicate passage of the rotor blade through limited arcuate portions of the travel path of the rotor blade end tip. Operational control over the light emitting devices is effected by data processing of outputs from air-speed responsive sensors on the blade end tip.

Claims

1. In combination with a helicopter having a rotor blade with a leading edge;

a system for indicating navigational orientation of the aircraft during flight, comprising;

light emitting means within said rotor blade for emission of signal light therefrom;

airspeed-responsive sensor means operatively connected to the light emitting means for establishing on and off phases of the light emission therefrom; and

data processing means operatively connected to the sensor means for determining proper timing of the on and off phases of the light emission.

2. The combination as defined in claim 1, wherein said signal light emitted from the light emitting means is of different colors.

3. The combination as defined in claim 2, wherein the light emitting means comprises a matrix of differently colored lamp devices that are switched on or off at the same time;

and a transparent protective aerodynamic cap covering the light emitting means.

4. The combination as defined in claim 1, wherein the light emitting means comprises a series of electroluminescent panels.

5. The combination as defined in claim 1, wherein said airspeed-responsive sensor is a stagnation pressure sensor.

6. The combination as defined in claim 1, wherein said airspeed-responsive sensor is a hot-wire anemometer.

7. The combination as defined in claim 1, wherein said airspeed-responsive sensor is an acoustic sensor.

8. The combination as defined in claim 1, wherein the data processing means identifies a low-airspeed operating condition of the rotary wing aircraft based on signal from the airspeed-responsive sensor, switching on the light-emitting means continuously.

9. The combination as defined in claim 1 wherein the light emitting means includes light sources compatible with night-vision sensors.

10. The combination as defined in claim 9, wherein the system includes:

switching control means for switching operation of the light emitting means between a standard red/green/white color pattern and a monochromatic pattern compatible with night-vision sensors.