US4319219A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Automatic approach landing and go-around control system for aircraft
Assignee: Boeing Co
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Filing: 1980-06-30
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Granted: 1982-03-09
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Expires: 2000-06-30
Abstract
Abstract A system for providing an aircraft pilot and/or autothrottle and go-around pitch axis control with information when a go-around should be initiated during an approach in response to either a hazardous flight status of the aircraft or to wind shear encounter by the aircraft. The present system utilizes a gain schedule control law based on the bug speed set by the pilot and on pilot go-around criteria to trigger a go-around signal for the pilot and/or the automatic control systems.
Inventors
- 👤 Karl J. Rein-Weston
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 15:09
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0615; G05D1/0638; G01; G01C; G01C23/00; G01C5/00; G01C5/005; G05D1/0653; G05D1/0676
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
80 words
In combination in an aircraft: means for providing a signal representative of instantaneous vertical speed; means for providing an air data derived signal representative of airspeed; means responsive to said signal representative of instantaneous vertical speed and said air data derived signal representative of airspeed for providing a signal representative of energy rate; and display means responsive to said signal representative of instantaneous vertical speed and said signal representative of energy rate for simultaneously displaying vertical speed and energy rate.
Claim 2
Dependent Claim
80 words
In combination in an aircraft: means for providing a signal representative of instantaneous vertical speed; means for providing an air data derived signal representative of airspeed; means responsive to said signal representative of instantaneous vertical speed and said air data derived signal representative of airspeed for providing a signal representative of energy rate; and display means responsive to said signal representative of instantaneous vertical speed and said signal representative of energy rate for simultaneously displaying vertical speed and energy rate.
Claim 3
Dependent Claim
84 words
In combination in an aircraft having an automatic approach landing and go-around control system; means for providing a first signal representative of airspeed, said first signal representative of airspeed derived from air data information; means for providing a second signal representative of altitude; means for providing a third signal representative of instantaneous vertical speed; and circuit means responsive to said first, second, and third signals for providing a go-around trigger to initiate a go-around maneuver of said automatic approach landing and go-around control system.
Claim 4
Dependent Claim
84 words
In combination in an aircraft having an automatic approach landing and go-around control system; means for providing a first signal representative of airspeed, said first signal representative of airspeed derived from air data information; means for providing a second signal representative of altitude; means for providing a third signal representative of instantaneous vertical speed; and circuit means responsive to said first, second, and third signals for providing a go-around trigger to initiate a go-around maneuver of said automatic approach landing and go-around control system.
Claim 5
Dependent Claim
83 words
In combination in an aircraft pilot instrument panel: a two-pointer display instrument for simultaneously displaying instantaneous vertical speed and energy rate; a plurality of push-button operated switching means which illuminate in the ON condition, each of said plurality of push-button operated switching means associated with a respective predetermined headwind component reading in knots; and a further push-button operated switching means which illuminates in the ON condition, said further push-button operated switching means coupled to associated circuitry for enabling arming of a go-around trigger.
Claim 6
Dependent Claim
83 words
In combination in an aircraft pilot instrument panel: a two-pointer display instrument for simultaneously displaying instantaneous vertical speed and energy rate; a plurality of push-button operated switching means which illuminate in the ON condition, each of said plurality of push-button operated switching means associated with a respective predetermined headwind component reading in knots; and a further push-button operated switching means which illuminates in the ON condition, said further push-button operated switching means coupled to associated circuitry for enabling arming of a go-around trigger.
Claim 7
Dependent Claim
141 words
In combination in an aircraft having a pitch axis control system responsive to go-around trigger control signals: means for generating a first signal representative of specific energy rate of the aircraft; means for generating a second signal representative of desired rate of descent of the aircraft; means for subtracting said first signal from said second signal thereby generating a third signal; an autothrottle control system; means for coupling said third signal to said autothrottle control system for advancing or retarding the throttles in response to wind shear encountered by the aircraft; and multiplier circuit means responsive to a signal representative of radio altitude and said third control signal for providing a fourth control signal; circuit means coupled between said multiplier circuit means and said pitch axis control system for processing said fourth control signal and providing said go-around trigger control signals.
Claim 8
Dependent Claim
141 words
In combination in an aircraft having a pitch axis control system responsive to go-around trigger control signals: means for generating a first signal representative of specific energy rate of the aircraft; means for generating a second signal representative of desired rate of descent of the aircraft; means for subtracting said first signal from said second signal thereby generating a third signal; an autothrottle control system; means for coupling said third signal to said autothrottle control system for advancing or retarding the throttles in response to wind shear encountered by the aircraft; and multiplier circuit means responsive to a signal representative of radio altitude and said third control signal for providing a fourth control signal; circuit means coupled between said multiplier circuit means and said pitch axis control system for processing said fourth control signal and providing said go-around trigger control signals.
Claim 9
Dependent Claim
19 words
The invention according to claim 4 further including go-around warning indicator means responsive to said go-around trigger control signals.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1985-03-08 | 1985-09-07 | 1986-03-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-03-08 | 1989-09-07 | 1990-03-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-03-08 | 1993-09-07 | 1994-03-09 | $7700.00 | Window Closed / Lapsed |