Aircraft ground collision avoidance and autorecovery systems device
First Claim
1. An aircraft ground collision avoidance system comprising:
- (a) means for computing a flyup, said flyup computing means receiving sensor signals which represent aircraft flight states and calculating preferred aircraft flyup altitudes at which an automatic aircraft flyup should be initiated, wherein each aircraft flyup altitude of said preferred aircraft flyup altitudes is calculated by determining the aircraft altitude which is lost (Δ
Z) during a recovery maneuver due to a current aircraft flight state; and
(b) means for automatically controlling an aircraft, said automatic aircraft controlling means receiving aircraft flight data and implementing an automatic aircraft flyup when said preferred aircraft flyup altitude is achieved, wherein said aircraft flight states and data include aircraft angle of attack and bank angle, said preferred aircraft flyup altitude is provided to said automatic aircraft controlling means by said flyup computing means.
1 Assignment
0 Petitions
Accused Products
Abstract
The invention comprises an aircraft ground collision avoidance system which utilizes a flight control computer for monitoring aircraft flight states and calculating preferred aircraft flyup altitudes at which automatic aircraft flyups should be initiated. The flyup altitude is determined by calculating aircraft altitude to be lost during a recovery maneuver from a current aircraft flight state. The invention also comprises an aircraft autopilot for monitoring aircraft flight states and initiating an automatic aircraft flyup when so directed by the flight control computer. The monitored aircraft states include aircraft airspeed, angle of attack, bank angle and velocity. Sensor lag, aircraft load factor and engine throttle position are also considered in determining when to conduct an automatic aircraft flyup.
125 Citations
26 Claims
-
1. An aircraft ground collision avoidance system comprising:
-
(a) means for computing a flyup, said flyup computing means receiving sensor signals which represent aircraft flight states and calculating preferred aircraft flyup altitudes at which an automatic aircraft flyup should be initiated, wherein each aircraft flyup altitude of said preferred aircraft flyup altitudes is calculated by determining the aircraft altitude which is lost (Δ
Z) during a recovery maneuver due to a current aircraft flight state; and(b) means for automatically controlling an aircraft, said automatic aircraft controlling means receiving aircraft flight data and implementing an automatic aircraft flyup when said preferred aircraft flyup altitude is achieved, wherein said aircraft flight states and data include aircraft angle of attack and bank angle, said preferred aircraft flyup altitude is provided to said automatic aircraft controlling means by said flyup computing means. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16)
-
-
17. A method of automatically avoiding aircraft ground collision comprising the steps of:
-
entering a preselected aircraft flight floor altitude in an aircraft flight computer; monitoring aircraft flight states with said flight computer, said flight states including air speed, altitude and flight path angles; calculating by said flight computer the amount of altitude to be lost during recovery maneuver if the monitored flight states, when extrapolated would indicate a loss of altitude; adding by said flight computer the amount of altitude to be lost as indicated by the monitored flight states during the recovery maneuver to the preselected floor altitude to determine a flyup altitude; comparing by said flight computer the flyup altitude to aircraft altitude; and sending a command via said flight computer to an autopilot to commence initiation of an automatic flyup maneuver if aircraft altitude is less than the preselected aircraft flight floor altitude. - View Dependent Claims (18, 19, 20, 21, 22)
-
-
23. An autopilot for automatically performing an aircraft altitude recovery comprising:
-
(a) an angle of attack limiter including an angle of attack detector, for producing an angle of attack signal that limits aircraft angle of attack to within an aircraft stall margin during aircraft altitude recovery; (b) a g-force limiter including a g-force detector for producing a signal that prevents overloading of aircraft structures during aircraft altitude recovery; (c) a bank angle recovery signal generating means including a bank angle detector, generating a signal for controlling aircraft elevators to promote aircraft altitude recovery; (d) an elevator summing junction for combining signals from said angle of attack limiter, said g-force limiter and said bank angle recovery generating means to provide a sum signal to control aircraft elevators to achieve aircraft recovery without exceeding aircraft flight capabilities; (e) a roll rate limiter including a roll rate detector, for providing a signal to eliminate excessive aircraft roll; and (f) an aileron summing junction for combining signals from said roll rate limiter and the bank angle detector to provide a sum signal to control aircraft ailerons to achieve level flight and aircraft altitude recovery. - View Dependent Claims (24, 25, 26)
-
Specification