Patent US4343035A successfully refreshed from Google Patents.
US4343035A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Heading reference system
Assignee: Individual
•
Filing: 1980-04-14
•
Granted: 1982-08-03
•
Expires: 2000-04-14
Abstract
Abstract An aircraft heading reference system including a rate gyro for sensing the yaw rate ψ of the aircraft and producing electrical signals representative thereof; a rate gyro for sensing the pitch rate θ of the aircraft and producing electrical signals representative thereof; an air speed sensor for sensing air speed ν of the aircraft and producing electrical signals representative thereof; a roll angle computer circuit responsive to the electrical signals representative of the yaw rate, pitch rate, and air speed for determining an electrical signal representative of the roll angle φ according to the expression: ψ+θ tan φ=(tan φ/cos φ·(g/ν) and a yaw and pitch computer circuit, responsive to the pitch rate θ, yaw rate ψ, and roll angle φ electrical signals for resolving the yaw and pitch rates about the roll angle φ to provide an electrical signal representative of the heading rate of the aircraft.
Inventors
- 👤 Walter E. Tanner
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 17:08
CPC Classifications
G; G01; G01C; G01C23/00; G01C21/00; G01C21/10; G01C21/12; G01C21/16; G01C21/166
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
128 words
An aircraft heading reference system comprisng: means for sensing the yaw rate ψ of the aircraft and producing electrical signals representative thereof; means for sensing the pitch rate θ of the aircraft and producing electrical signals representative thereof; means for sensing the air speed ν of the aircraft and producing electrical signals representative thereof; means, responsive to said electrical signals representative of said yaw rate, pitch rate, and air speed, for determining an electrical signal representative of the roll angle φ according to the expression: ψ+θtanφ=(tanφ/cosφ) (g/ν); and means, responsive to said pitch rate θ, yaw rate ψ, and roll angle φ electrical signals, for resolving said yaw and pitch rates about said roll angle for providing an electrical signal representative of the heading rate of the aircraft.
Claim 2
Dependent Claim
128 words
An aircraft heading reference system comprisng: means for sensing the yaw rate ψ of the aircraft and producing electrical signals representative thereof; means for sensing the pitch rate θ of the aircraft and producing electrical signals representative thereof; means for sensing the air speed ν of the aircraft and producing electrical signals representative thereof; means, responsive to said electrical signals representative of said yaw rate, pitch rate, and air speed, for determining an electrical signal representative of the roll angle φ according to the expression: ψ+θtanφ=(tanφ/cosφ) (g/ν); and means, responsive to said pitch rate θ, yaw rate ψ, and roll angle φ electrical signals, for resolving said yaw and pitch rates about said roll angle for providing an electrical signal representative of the heading rate of the aircraft.
Claim 3
Dependent Claim
30 words
The reference system of claim 1 in which said means for sensing yaw rate and said means for sensing pitch rate each includes a single degree of freedom rate gyro.
Claim 4
Dependent Claim
28 words
The heading reference system of claim 1 in which said means for sensing yaw rate and said means for sensing pitch rate each includes a rate integrating gyro.
Claim 5
Dependent Claim
67 words
The heading reference system of claim 1 in which said means for determining includes a first divider circuit responsive to the acceleration of gravity as dividend and air speed as the divisor; a subtractor circuit for subtracting the pitch rate from the output of said first divider circuit; a second divider circuit responsive to the yaw rate as dividend and output from the subtractor circuit as divisor.
Claim 6
Dependent Claim
81 words
The heading reference system of claim 4 further comprising arc-tan calculating circuit including a squaring circuit and third divider circuit each responsive to the output from said second divider circuit, said third divider circuit having a divisor input of three; a multiplier circuit responsive to the outputs of said squaring circuit and third divider circuit and a second subtractor circuit for subtracting the output of said multiplier circuit from the output of said second divider circuit to obtain the roll angle.
Claim 7
Dependent Claim
36 words
The heading reference system of claim 1 in which said means for determining includes means for determination of the roll angle φ from the error expression: ##EQU6## for roll angles no greater than approximately fifty-seven degrees.
Claim 8
Dependent Claim
28 words
The heading reference system of claim 1 in which said means for determining includes means for determination of the roll angle from the error expression: X=|ψ|+θtanφ-(g/ν) (sinφ/cos.sup.2 φ).
Claim 9
Dependent Claim
94 words
The heading reference system of claim 1 in which said means for resolving includes a ROM sin table and ROM cos table; a ROM addressing circuit responsive to the roll angle for reading out the respective values for the roll angle; a first multiplier circuit responsive to the ROM sin table readout and the pitch rate; a second multiplier circuit responsive to the ROM cos table readout and the yaw rate; and an adder circuit responsive to the output of said first and second multiplier circuits for producing the heading rate of the aircraft.
Claim 10
Dependent Claim
24 words
The heading reference system of claim 1, further including means for integrating said signal representations of heading rate to provide the instantaneous heading angle.
Claim 11
Dependent Claim
22 words
The heading reference system of claim 9, further including display means responsive to said means for integrating for manifesting the instantaneous heading.
Claim 12
Dependent Claim
21 words
The heading reference system of claim 9, further including means for computing and manifesting the latitude and longitude of the aircraft.
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) | 1985-08-02 | 1986-02-01 | 1986-08-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-08-02 | 1990-02-01 | 1990-08-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-08-02 | 1994-02-01 | 1994-08-03 | $7700.00 | Window Closed / Lapsed |