Patent US4844383A successfully refreshed from Google Patents.
US4844383A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Apparatus for redundant axis stabilization and control of an aircraft
Assignee: Northrop Grumman Litef GmbH
•
Filing: 1987-05-22
•
Granted: 1989-07-04
•
Expires: 2007-05-22
Abstract
Abstract Apparatus for stabilization and control of an aircraft includes a pair of strapdown devices that are rigidly fixed in space relative to one another. Each device includes two two-axis gyroscopes, permitting the generation of triple redundancy. The measurement axes (M 11 , M 12 and M 21 , M 22 ) have different arrangements in the horizontal plane. The redundant axis of each strapdown device is arranged in such a way (preferably at 45 degrees) that an allocation to the two horizontal measurement axes is provided by computational transformation.
Inventors
- 👤 Wolfgang Hassenpflug
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 15:23
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/0055; G05D1/0077; G01; G01C; G01C21/00; G01C21/10; G01C21/12; G01C21/16; G01C21/166; G05D1/08; G05D1/0808
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
89 words
Apparatus for stabilization and control of an aircraft comprising, in combination: (a) a pair of strapdown devices, said devices being rigidly oriented in space with respect to each other; (b) each of said devices including two two-axis measuring gyroscopes; (c) measurement axes of said gyroscopes of each device having different arrangements in the horizontal plane so that triple redundancy of measurement is provided by said apparatus for at least two aircraft axes; and (d) said arrangement of measurement axes in the horizontal plane is defined by a computational transformation.
Claim 2
Dependent Claim
89 words
Apparatus for stabilization and control of an aircraft comprising, in combination: (a) a pair of strapdown devices, said devices being rigidly oriented in space with respect to each other; (b) each of said devices including two two-axis measuring gyroscopes; (c) measurement axes of said gyroscopes of each device having different arrangements in the horizontal plane so that triple redundancy of measurement is provided by said apparatus for at least two aircraft axes; and (d) said arrangement of measurement axes in the horizontal plane is defined by a computational transformation.
Claim 3
Dependent Claim
18 words
Apparatus as defined in claim 1 wherein said strapdown devices are located at separated positions within said aircraft.
Claim 4
Dependent Claim
104 words
Apparatus as defined in claim 1 wherein said gyroscopes of each device are arranged so that; (a) the spin axes are orthogonal; (b) the spin axis of the first gyroscope is aligned with the yaw axis of the aircraft; (c) the spin axis of the second gyroscope is aligned with the pitch axis of the aircraft; (d) a first measurement axis of said second gyroscope is aligned in the direction of said yaw axis; and; (e) the measurement axes of said first gyroscope are orthogonal and oriented at an angle of 45 degrees with respect to the second measurement axis of said second gyroscope.
Claim 5
Dependent Claim
95 words
Apparatus as defined in claim 1 wherein said gyroscopes of said strapdown devices are arranged as follows: (a) the spin axis of the first gyroscope is aligned with the yaw axis of said aircraft; (b) the spin axis of the second gyroscope is aligned at a right angle to that of said first gyroscope and at 45 degrees to a preselected aircraft axis; (c) one measurement axis of said second gyroscope is aligned with the yaw axis of said aircraft; and; (d) the measurement axis of said first gyroscope is aligned with said preselected axis.
Claim 6
Dependent Claim
14 words
Apparatus as defined in claim 4 wherein said preselected axis is the pitch axis.
Claim 7
Dependent Claim
14 words
Apparatus as defined in claim 4 wherein said preselected axis is the roll axis.
Claim 8
Dependent Claim
111 words
A strapdown device for stabilization and control of an aircraft comprising, in combination: (a) a pair of two-axis measuring gyroscopes; (b) the spin axes of said gyroscopes are orthogonal; (c) the spin axis of the first gyroscope is aligned with the yaw axis of said aircraft; (d) the spin axis of the second gyroscope is aligned with the pitch axis of said aircraft; (e) a first measurement axis of said second gyroscope is aligned in the direction of said yaw axis; and (f) the measurement axes of said first gyroscope are orthogonal and oriented at an angle of 45 degrees with respect to the second measurement axis of said second gyroscope.
Claim 9
Dependent Claim
111 words
A strapdown device for stabilization and control of an aircraft comprising, in combination: (a) a pair of two-axis measuring gyroscopes; (b) the spin axes of said gyroscopes are orthogonal; (c) the spin axis of the first gyroscope is aligned with the yaw axis of said aircraft; (d) the spin axis of the second gyroscope is aligned with the pitch axis of said aircraft; (e) a first measurement axis of said second gyroscope is aligned in the direction of said yaw axis; and (f) the measurement axes of said first gyroscope are orthogonal and oriented at an angle of 45 degrees with respect to the second measurement axis of said second gyroscope.
Claim 10
Dependent Claim
99 words
A strapdown device for stabilization and control of an aircraft comprising in combination (a) a pair of two axis measuring gyroscopes; (b) the spin axis of the first gyroscope is aligned with the yaw axis of said aircraft; (c) the spin axis of the second gyroscope is aligned at a right angle to that of said first gyroscope and at 45 degrees to a preselected aircraft axis; (d) one measurement axis of said second gyroscope is aligned with the yaw axis of said aircraft; and; (e) the measurement axis of said first gyroscope is aligned with said preselect axis.
Claim 11
Dependent Claim
99 words
A strapdown device for stabilization and control of an aircraft comprising in combination (a) a pair of two axis measuring gyroscopes; (b) the spin axis of the first gyroscope is aligned with the yaw axis of said aircraft; (c) the spin axis of the second gyroscope is aligned at a right angle to that of said first gyroscope and at 45 degrees to a preselected aircraft axis; (d) one measurement axis of said second gyroscope is aligned with the yaw axis of said aircraft; and; (e) the measurement axis of said first gyroscope is aligned with said preselect axis.
Claim 12
Dependent Claim
16 words
A strapdown device is defined in claim 8 wherein said preselected axis is the pitch axis.
Claim 13
Dependent Claim
16 words
A strapdown device as defined in claim 8 wherein said preselected axis is the roll axis.
References Cited (Backward Citations)
US2550806A
Cited
US3158340A
Cited
US3391568A
Cited
US3489004A
Cited
US3463909A
Cited
US3614401A
Cited
US3918309A
Cited
US4179818A
Cited
US4125017A
Cited
US4212443A
Cited
US4280188A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1992-07-03 | 1993-01-02 | 1993-07-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-07-03 | 1997-01-02 | 1997-07-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-07-03 | 2001-01-02 | 2001-07-04 | $7700.00 | Window Closed / Lapsed |