US4757964A
Expired / Lapsed
US
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Method for controlling the attitude of a spinning body in orbit
Assignee: Raytheon Co
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Filing: 1986-07-17
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Granted: 1988-07-19
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Expires: 2006-07-17
Abstract
Abstract A method for passively stabilizing the attitude of a spinning orbiting body subject to orbital precession to maintain the spin axis orientation of the body essentially fixed and stable relative to the orbital plane. The preferred embodiment comprises selecting a body mass geometry and orbital parameters, including an orbit inclination, an orbital rate and a rate of regression of orbit line of nodes, so that the precessional motion of the body and the orbit are equal and opposite in direction and locating the spin axis of the body in a plane containing the north axis of the body and the orbit normal and between the north axis and the orbit normal, so that the gravity gradient precession of the spin axis equals the regressional motion of the orbit normal to produce a planar equilibrium configuration.
Inventors
- 👤 John E. McIntyre
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 12:48
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/28; B64G1/281; B64G1/244
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
183 words
A method of passively stabilizing the attitude of a spinning earth-orbiting body having as its orbital parameters an orbit inclination i, an orbital rate Ω o and a rate of regression of orbit line of nodes γ, so that the spin axis orientation angle φ o of said body remains essentially fixed and stable relative to the orbital plane of said body, even when the orbit of said body is precessing, which comprises: selecting a mass geometry σ for said body defined by the ratio of said body's spin inertia to said body's transverse inertia; selecting a spin rate Ω for said body so that said spin axis orientation angle φ o for said body is an equilibrium solution to the following relationship ##EQU15## where for an xyz orbital coordinate system having z along the orbit normal axis and x at the ascending node ##EQU16## and z o is a solution to the quartic k.sup.2 z.sub.o.sup.4 -2 k cos i z.sub.o.sup.3 +(2-k.sup.2) z.sub.o.sup.2 +2 k cos i z.sub.o -cos.sup.2 i=0 and initially orienting said body in orbit with said spin axis orientation angle.
Claim 2
Independent Claim
183 words
A method of passively stabilizing the attitude of a spinning earth-orbiting body having as its orbital parameters an orbit inclination i, an orbital rate Ω o and a rate of regression of orbit line of nodes γ, so that the spin axis orientation angle φ o of said body remains essentially fixed and stable relative to the orbital plane of said body, even when the orbit of said body is precessing, which comprises: selecting a mass geometry σ for said body defined by the ratio of said body's spin inertia to said body's transverse inertia; selecting a spin rate Ω for said body so that said spin axis orientation angle φ o for said body is an equilibrium solution to the following relationship ##EQU15## where for an xyz orbital coordinate system having z along the orbit normal axis and x at the ascending node ##EQU16## and z o is a solution to the quartic k.sup.2 z.sub.o.sup.4 -2 k cos i z.sub.o.sup.3 +(2-k.sup.2) z.sub.o.sup.2 +2 k cos i z.sub.o -cos.sup.2 i=0 and initially orienting said body in orbit with said spin axis orientation angle.
Claim 3
Dependent Claim
33 words
The method of claim 1 wherein the spin axis of said body is located in a plane defined by the polar axis of the earth and the orbit plane normal of the body.
Claim 4
Dependent Claim
21 words
The method of claim 2 wherein the spin axis of the body is oriented between polar north and the orbit normal.
Claim 5
Independent Claim
156 words
A method of passively stabilizing the attitude of a spinning earth-orbiting body which is precessing, the method serving to maintain the spin axis orientation of said body essentially fixed and stable relative to the orbital plane of said body, even when the orbit of said body is also precessing, the method comprising: selecting a body mass geometry and orbital parameters comprising an orbit inclination, an orbital rate and a rate of regression of orbit line of nodes so that the precessional motions of said body and said orbit are equal and opposite in direction; locating the spin axis of said body in a plane defined by the earth polar axis and the orbit normal of the body and between said polar axis and said orbit normal; and selecting the spin axis angle so that the gravity gradient precession of said spin axis equals the regressional motion of the orbit normal to produce an axis equilibrium configuration.
Claim 6
Independent Claim
156 words
A method of passively stabilizing the attitude of a spinning earth-orbiting body which is precessing, the method serving to maintain the spin axis orientation of said body essentially fixed and stable relative to the orbital plane of said body, even when the orbit of said body is also precessing, the method comprising: selecting a body mass geometry and orbital parameters comprising an orbit inclination, an orbital rate and a rate of regression of orbit line of nodes so that the precessional motions of said body and said orbit are equal and opposite in direction; locating the spin axis of said body in a plane defined by the earth polar axis and the orbit normal of the body and between said polar axis and said orbit normal; and selecting the spin axis angle so that the gravity gradient precession of said spin axis equals the regressional motion of the orbit normal to produce an axis equilibrium configuration.
Claim 7
Dependent Claim
21 words
The method of claim 4, further including the step of initially orienting said body in orbit with said spin axis angle.
Claim 8
Dependent Claim
141 words
An earth orbiting system in which a spinning satellite is located in orbit about the earth, the system comprising: a spinning orbiting body having a mass geometry defined by the ratio of the body's spin inertia to the body's transverse inertia and a selected spin rate consistent with desired orbital parameters satisfying the following definitions: ##EQU17## where ##EQU18## Ω o =orbital rate Ω=spin rate γ=rate of regression of orbit line of nodes and wherein the spin axis of the orbiting body is at an angle φ o defined as: ##EQU19## where, for an xyz orbital coordinate system having z along the orbit normal axis and x at the ascending node, the following relations hold: ##EQU20## and z o is a solution to the quartic k.sup.2 z.sub.o.sup.4 -2 k cos i z.sub.o.sup.3 +(1-k.sup.2) z.sub.o.sup.2 +2 k cos i z.sub.o -cos.sup.2 i=0 .
Claim 9
Dependent Claim
141 words
An earth orbiting system in which a spinning satellite is located in orbit about the earth, the system comprising: a spinning orbiting body having a mass geometry defined by the ratio of the body's spin inertia to the body's transverse inertia and a selected spin rate consistent with desired orbital parameters satisfying the following definitions: ##EQU17## where ##EQU18## Ω o =orbital rate Ω=spin rate γ=rate of regression of orbit line of nodes and wherein the spin axis of the orbiting body is at an angle φ o defined as: ##EQU19## where, for an xyz orbital coordinate system having z along the orbit normal axis and x at the ascending node, the following relations hold: ##EQU20## and z o is a solution to the quartic k.sup.2 z.sub.o.sup.4 -2 k cos i z.sub.o.sup.3 +(1-k.sup.2) z.sub.o.sup.2 +2 k cos i z.sub.o -cos.sup.2 i=0 .
References Cited (Backward Citations)
US3271565A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1991-07-19 | 1992-01-18 | 1992-07-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1995-07-19 | 1996-01-18 | 1996-07-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1999-07-19 | 2000-01-18 | 2000-07-19 | $7700.00 | Window Closed / Lapsed |