US4347572A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method and apparatus for an aircraft climb-out guidance system
Assignee: Boeing Co
•
Filing: 1979-11-02
•
Granted: 1982-08-31
•
Expires: 1999-11-02
Abstract
Abstract An aircraft guidance system operable during both takeoff and go-around maneuvers allows safe operation even under adverse wind shear conditions. Initially the system controls vertical speed to achieve an acceptable, minimum climb rate regardless of airspeed loss. Should excess thrust exist such that the acceptable minimum climb rate is exceeded, increased vertical speed and airspeed are commanded. When the climb rate significantly exceeds the acceptable minimum, airspeed is controlled to a specified value. Should the aircraft ever approach the "stick shaker" condition, an override command limits aircraft angle of attack.
Inventors
- 👤 James W. Berwick, Jr.
- 👤 Robert J. Bleeg
- 👤 Vincent E. McFaddin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 22:17
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0653; G05D1/0661
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
98 words
A method for determining the climb-out guidance of an aircraft comprising the descending priority steps of: (a) performing controls (b) through (d) below but under no circumstances allowing aircraft angle of attack to exceed a predetermined stick shaker value; (b) controlling vertical speed to achieve a predetermined acceptable, minimum climb rate regardless of airspeed loss; (c) commanding both increased vertical speed and airspeed control in response to excess thrust upon exceeding said acceptable minimum climb rate; and (d) controlling airspeed to a specified value in response to achieving a climb rate significantly higher than said minimum climb rate.
Claim 2
Independent Claim
98 words
A method for determining the climb-out guidance of an aircraft comprising the descending priority steps of: (a) performing controls (b) through (d) below but under no circumstances allowing aircraft angle of attack to exceed a predetermined stick shaker value; (b) controlling vertical speed to achieve a predetermined acceptable, minimum climb rate regardless of airspeed loss; (c) commanding both increased vertical speed and airspeed control in response to excess thrust upon exceeding said acceptable minimum climb rate; and (d) controlling airspeed to a specified value in response to achieving a climb rate significantly higher than said minimum climb rate.
Claim 3
Dependent Claim
37 words
The method of claim 1 wherein step (d) comprises the further step of: specifying an airspeed value based upon: (i) a pilot selected value; (ii) a predetermined function of flap position; or (iii) an externally programmed value.
Claim 4
Independent Claim
24 words
The method of either of claims 1 or 2 including the further step of: (e) displaying said determined climb-out guidance on a suitable display.
Claim 5
Independent Claim
25 words
The method of either of claims 1 or 2 including the further step of: (e) controlling a provided aircraft autopilot with said determined climb-out guidance.
Claim 6
Dependent Claim
116 words
Apparatus for generating a climb-out guidance command signal for an aircraft comprising: minimum means for comparing the aircraft's actual altitude rate with a minimum reference altitude rate and generating an error command signal in response thereto; transition rate means for producing a predeterminedly increased altitude rate and airspeed command signal in response to the aircraft exceeding said minimum reference altitude rate; final airspeed command means responsive to the aircraft exceeding said minimum altitude rate by a significant margin to produce an airspeed command signal indicative of a predetermined specified value; and stick shaker override means producing an overriding command signal for predeterminedly limiting aircraft angle of attack responsive to an aircraft airspeed approaching a stall value.
Claim 7
Dependent Claim
116 words
Apparatus for generating a climb-out guidance command signal for an aircraft comprising: minimum means for comparing the aircraft's actual altitude rate with a minimum reference altitude rate and generating an error command signal in response thereto; transition rate means for producing a predeterminedly increased altitude rate and airspeed command signal in response to the aircraft exceeding said minimum reference altitude rate; final airspeed command means responsive to the aircraft exceeding said minimum altitude rate by a significant margin to produce an airspeed command signal indicative of a predetermined specified value; and stick shaker override means producing an overriding command signal for predeterminedly limiting aircraft angle of attack responsive to an aircraft airspeed approaching a stall value.
Claim 8
Dependent Claim
24 words
The apparatus of claim 5 wherein the minimum means minimum reference level is a function of the number of operating engines on the aircraft.
Claim 9
Dependent Claim
28 words
The apparatus of claim 5 wherein the transition rate means further comprises means for generating said increased altitude rate and airspeed command signal at a predetermined linear rate.
Claim 10
Dependent Claim
44 words
The apparatus of claim 5 wherein the final airspeed command means includes means operable during go-around operation of the aircraft to compare actual aircraft airspeed with a desired value based on flap position and produce an error command signal in response to said comparison.
Claim 11
Dependent Claim
31 words
The apparatus of claim 5 wherein the final airspeed command means includes means operable during takeoff of the aircraft to produce an airspeed command signal responsive to a pilot selected value.
Claim 12
Dependent Claim
44 words
The apparatus of claim 9 wherein said final airspeed means further comprises means to compute a minimum desired airspeed value based on predetermined aircraft related parameters and override said pilot selected value should said pilot selected value be less than said minimum desired value.
Claim 13
Dependent Claim
25 words
The apparatus of claim 5 further including means for adapting said command signals such that they are suitable for display on an attitude director indicator.
Claim 14
Dependent Claim
24 words
The apparatus of claim 5 further including means for adapting said command signals such that they are suitable for controlling an aircraft automatic pilot.
References Cited (Backward Citations)
US3241792A
Cited
US3522729A
Cited
US3662976A
Cited
US3681580A
Cited
US3691356A
Cited
US3774017A
Cited
US3963197A
Cited
US3822047A
Cited
US3837603A
Cited
US3814912A
Cited
US3925640A
Cited
US3908934A
Cited
US4093158A
Cited
US4027839A
Cited
US4044975A
Cited
US4071893A
Cited
US4189118A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1985-08-30 | 1986-03-01 | 1986-08-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-08-30 | 1990-03-01 | 1990-08-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-08-30 | 1994-03-01 | 1994-08-31 | $7700.00 | Window Closed / Lapsed |