Automatic aircraft separation assurance

• US 20170084183A1
• Filed: 09/18/2015
• Published: 03/23/2017
• Est. Priority Date: 09/18/2015
• Status: Abandoned Application

• Current Assignee: Robert M. Knox
• Original Assignee: Robert M. Knox
• Inventors: Knox, Robert M.
• Application Number:
  US14/858,824
• Publication Number:
  US 20170084183A1
• Time in Patent Office: Days
• CPC Class Codes: G01C 23/00 Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
• CPC Class Codes: G01S 13/867 Combination of radar systems with cameras
• CPC Class Codes: G01S 13/933 of aircraft or spacecraft
• CPC Class Codes: G05D 1/101 specially adapted for aircraft
• CPC Class Codes: G08G 5/045 Navigation or guidance aids, e.g. determination of anti-collision manoeuvers radar or analogous systems specially adapted for anti-collision between aircraft G01S13/933

Abstract

The present invention replaces the use of a pilot information display method and instead relies upon an automated three dimensional aircraft tracking system using only aircraft tracking data supplied by internal spherical coverage dual mode sensor system. Separation is accurately predicted and minimum flight path separation (from all nearby aircraft) is automatically assured by signals to the aircraft flight control system without action or intervention by the pilot. When predicted separation is less than minimum separation for the host aircraft, flight control is temporarily removed from the pilot until the automated system redirects the flight path to enable the predicted separation to exceed the minimum separation for the host aircraft. When on-board sensor system predicts separation greater than required minimum, then flight control is returned to the pilot.

Claims

1. Automatic Aircraft Separation Assurance apparatus and method disposed aboard a host aircraft requiring minimum separation distance, said apparatus including a sensor suite, processor, separation assurance algorithms and pilot display, said method detecting and tracking all aircraft in the spherical field-of-regard of said host aircraft, said processor predicting said host aircraft separation distance, said pilot display informing pilot of predicted separation distance, said pilot display alerting pilot if flight control is removed from the pilot. Said processor operating said separation assurance algorithms on said sensor suite tracking data predicting said host vehicle tracking separation below specified minimum separation for said host aircraft, said AASA apparatus temporarily suspending pilot flight control, supplies direction/altitude commands to said host aircraft flight control system, indicates via said pilot display suspension of pilot flight control. Said direction/altitude commands enable increased tracking separation of said host aircraft to exceed said minimum separation distance. Said sensor suite track data processor separation assurance algorithms return pilot flight control when said separation distance exceeds said minimum separation distance.

2. The AASA apparatus of claim 1 further characterized by dual mode sensor suite for detection and tracking of aircraft in said spherical field-of-regard of said host aircraft.

3. The AASA apparatus of claim 1 further characterized by said dual mode sensor suite having first hemispherical dual mode sensor subsystem mounted and aligned with said host vehicle flight path direction plus second hemispherical dual mode sensor subsystem aligned with said first hemispherical dual mode sensor directed opposing said flight path direction.

4. The AASA apparatus of claim 1 further characterized by said hemispherical dual mode sensor subsystem consisting of a multiplicity of dual mode sector sensors arrayed on a hemispherical surface.

5. The AASA apparatus of claim 1 further characterized by said dual mode sector sensors covering a specified angular sector field-of-view of said hemispherical field-of-regard.

6. The AASA apparatus of claim 1 further characterized by said dual mode sector sensor consisting of three dimensional radar sensor disposed and aligned with two dimensional electro-optical video sensor sharing said sector field-of-view.

7. The AASA apparatus of claim 1 further characterized by said processor fusing output of said three dimensional radar sensor with output of said two dimensional electro-optical sensor to provide three dimensional tracking data for all detected aircraft in said sector field-of-view of said hemisphere field-of-regard.

8. The AASA apparatus of claim 1 further characterized by said processor combining three dimensional tracking data for said host aircraft in said sector field-of-view with three dimensional tracking data for said aircraft from all said dual mode sensor sectors in said first hemispherical field-of-regard.

9. The AASA apparatus of claim 1 further characterized by said processor three dimensional tracking data for said host aircraft spherical field-of-regard combining three dimensional tracking data for first hemispherical field-of-regard with three dimensional tracking data for said host aircraft second hemispherical field-of-regard.

10. The AASA apparatus of claim 1 further characterized by said processor predicting minimum separation distance enabled by said separation assurance algorithms operating on said three dimensional tracking data in said spherical field-of-regard.

11. The AASA apparatus of claim 1 further characterized by said processor temporarily disabling pilot flight control when said predicted separation distance is below said minimum separation distance for said host aircraft.

12. The AASA apparatus of claim 1 further characterized by said cockpit display of said predicted separation distance.

13. The AASA apparatus of claim 1 further characterized by said processor commands to said flight control system enabling change in said host aircraft direction and/or altitude to reduce predicted separation distance.

14. The AASA apparatus of claim 1 further characterized by said cockpit display indicator that pilot flight control has been disabled because said aircraft minimum separation distance has been breached.

15. The AASA apparatus of claim 1 further characterized by said cockpit display that pilot flight control has been restored when said minimum separation distance predicted by said processor has been exceeded.