US4280188A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Survivable redundant vector sensors for systems with differing maximum output requirements
Assignee: Grumman Corp
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Filing: 1979-06-28
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Granted: 1981-07-21
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Expires: 1999-06-28
Abstract
Abstract Six sensors are oriented to position their input axes on the surface of a cone. The cone angle is optimized to permit the use of sensors with identical range capacity despite the fact that the maximum input along each of the orthogonal axes differs. The optimization of cone angle minimizes the average total error amplification due to skewing and change of sensor maximum rate capability to provide data closely approximating that derived from a non skewed, orthogonal, sensor array. The sensors may be gyroscope or accelerometer which are packaged in assemblies of two identical sensors each.
Inventors
- 👤 Warren D. Weinstein
- 👤 Jean A. Boudreau
- 👤 Donald Gertz
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 06:09
CPC Classifications
G; G01; G01C; G01C21/00; G01C21/10; G01C21/12; G01C21/16; G01C21/183; G01C21/188; G01C21/166; Y; Y10; Y10T; Y10T74/00; Y10T74/12; Y10T74/1221
Claims Analysis
Total Claims: 32
Claim 1
Independent Claim
109 words
A vector sensing system for measuring triad rates or accelerations of an aircraft comprising six identical vector sensors, each sensor having a predetermined input axis; means for mounting said sensors in said aircraft with their input axes arranged in a non-orthogonal relationship relative to one another and with their input axes defining the surface of a cone having its axis coincident with the axis of maximum input to the aircraft, said cone having a central half angle such that an average total amplification factor is minimum; and a data management means responsive to the output signals of said sensors to resolve said outputs into aircraft axes rates or accelerations.
Claim 2
Dependent Claim
109 words
A vector sensing system for measuring triad rates or accelerations of an aircraft comprising six identical vector sensors, each sensor having a predetermined input axis; means for mounting said sensors in said aircraft with their input axes arranged in a non-orthogonal relationship relative to one another and with their input axes defining the surface of a cone having its axis coincident with the axis of maximum input to the aircraft, said cone having a central half angle such that an average total amplification factor is minimum; and a data management means responsive to the output signals of said sensors to resolve said outputs into aircraft axes rates or accelerations.
Claim 3
Dependent Claim
24 words
A system of claim 1, wherein said means for mounting includes means for mounting the six sensors in three packages each containing two sensors.
Claim 4
Dependent Claim
10 words
A system of claim 2, wherein each package is identical.
Claim 5
Dependent Claim
26 words
A system of claim 2, wherein said packages are mounted on a common bulkhead of said aircraft to minimize the effect of bending of the aircraft.
Claim 6
Dependent Claim
23 words
A system of claim 1, wherein said sensors are each oriented with their input axes symmetrically spaced on the surface of said cone.
Claim 7
Dependent Claim
24 words
A system of claim 5, wherein two of said sensors input axes are coplanar with the plane defined by the yaw and roll axes.
Claim 8
Dependent Claim
27 words
A system of claim 6, wherein said vector sensors are rate sensors whose input axes are arranged to define a cone having a half angle of 77°.
Claim 9
Dependent Claim
22 words
A system of claim 6, wherein said vector sensors are accelerometers; and the half angle of the cone is about 63° 26'.
Claim 10
Dependent Claim
21 words
A system of claim 5, wherein one of said sensor axis lies in a plane displaced 30° from the yaw-roll plane.
Claim 11
Independent Claim
96 words
A method of measuring triad rates or accelerations in an aircraft in which the maximum rate requirements about the axes of the aircraft differ which comprises the steps of: providing six vector sensors having identical maximum rate capacities; positioning the sensors with their input axes defining a cone having its axes coincident with the axis of maximum input to the aircraft, said cone having a central half angle selected to minimize the average total amplification factor; and utilizing the output of said sensors to resolve the rates or accelerations along the roll, pitch and yaw axes.
Claim 12
Independent Claim
96 words
A method of measuring triad rates or accelerations in an aircraft in which the maximum rate requirements about the axes of the aircraft differ which comprises the steps of: providing six vector sensors having identical maximum rate capacities; positioning the sensors with their input axes defining a cone having its axes coincident with the axis of maximum input to the aircraft, said cone having a central half angle selected to minimize the average total amplification factor; and utilizing the output of said sensors to resolve the rates or accelerations along the roll, pitch and yaw axes.
Claim 13
Dependent Claim
21 words
A method of claim 10 including the steps of arranging the six rate sensors in three packages containing two sensors each.
Claim 14
Dependent Claim
18 words
A method of claim 10, wherein said sensors are each symmetrically spaced on the surface of said cone.
Claim 15
Dependent Claim
20 words
A method of claim 12, wherein said sensors are gyroscopes and said cone axis is coincident with the roll axis.
Claim 16
Dependent Claim
12 words
A method of claim 13, wherein the central half angle is 77°.
Claim 17
Dependent Claim
31 words
A method of claim 13, including the steps of mounting said sensors on a common bulkhead located aft of the anti node of the first mode of vibration of the aircraft.
Claim 18
Dependent Claim
20 words
A method of claim 12, wherein said sensors are accelerometers and said cone axis is coincident with the yaw axis.
Claim 19
Dependent Claim
14 words
A method of claim 16, wherein the central half angle is about 63° 26'.
Claim 20
Dependent Claim
86 words
A vector sensing system for measuring triad rates or accelerations of an aircraft comprising six identical vector sensors, each sensor having a pre-determined input axis; means for mounting said sensors in said aircraft with their input axes arranged in a non-orthogonal relationship relative to one another and with their input axes defining the surface of a cone having its axis coincident with the axis of maximum input to the aircraft, said cone having a central half angle such that an average total amplification factor is minimum.
Claim 21
Dependent Claim
86 words
A vector sensing system for measuring triad rates or accelerations of an aircraft comprising six identical vector sensors, each sensor having a pre-determined input axis; means for mounting said sensors in said aircraft with their input axes arranged in a non-orthogonal relationship relative to one another and with their input axes defining the surface of a cone having its axis coincident with the axis of maximum input to the aircraft, said cone having a central half angle such that an average total amplification factor is minimum.
Claim 22
Dependent Claim
24 words
A system of claim 18, wherein said means for mounting includes means for mounting the six sensors in three packages each containing two sensors.
Claim 23
Dependent Claim
10 words
A system of claim 19, wherein each package is identical.
Claim 24
Dependent Claim
26 words
A system of claim 19, wherein said packages are mounted on a common bulkhead of said aircraft to minimize the effect of bending of the aircraft.
Claim 25
Dependent Claim
23 words
A system of claim 18, wherein said sensors are each oriented with their input axes symmetrically spaced on the surface of said cone.
Claim 26
Dependent Claim
24 words
A system of claim 22, wherein two of said sensor input axes are coplanar with the plane defined by the yaw and roll axes.
Claim 27
Dependent Claim
27 words
A system of claim 23, wherein said vector sensors are rate sensors whose input axes are arranged to define a cone having a half angle of 77°.
Claim 28
Dependent Claim
22 words
A system of claim 23, wherein said vector sensors are accelerometers; and the half angle of the cone is about 63° 26'.
Claim 29
Dependent Claim
21 words
A system of claim 22, wherein one of said sensor axis lies in a plane displaced 30° from the yaw-roll plane.
Claim 30
Dependent Claim
20 words
A system of claim 22, wherein said sensors are gyroscopes and said cone axis is coincident with the roll axis.
Claim 31
Dependent Claim
28 words
A system of claim 26, wherein said sensors are mounted on a common bulkhead located aft of the antinode of the first mode of vibration of the aircraft.
Claim 32
Dependent Claim
20 words
A system of claim 22, wherein said sensors are accelerometers and said cone axis is coincident with the yaw axis.
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) | 1984-07-20 | 1985-01-19 | 1985-07-21 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-07-20 | 1989-01-19 | 1989-07-21 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-07-20 | 1993-01-19 | 1993-07-21 | $7700.00 | Window Closed / Lapsed |