US3647162A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Flight control circuit for missile spinning about its longitudinal axis
Assignee: Airbus Defence and Space GmbH
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Filing: 1969-08-19
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Granted: 1972-03-07
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Expires: 1989-08-19
Abstract
Abstract A flight control circuit is provided for a missile spinning about its longitudinal axis and provided with at least one control member influencing its trajectory. The missile is stabilized about at least one of its pitch and yaw axes by at least one gyroscope having a gyro rotor shaft operatively associated with at least one position pickup indicating the position of the rotor shaft. Each position pickup is mounted rigidly on the missile frame in a plane containing the longitudinal axis of the missile and which plane also included the line of action of the control member. Each position pickup is connected directly to actuating means for the control member.
Inventors
- 👤 Heinz-Dieter Muller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 16:47
CPC Classifications
B; B64; B64C; B64C17/00; B64C17/02; B64C17/06; F; F42; F42B; F42B15/00; F42B15/01
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
216 words
A flight control circuit, for a missile constantly spinning about its longitudinal axis during flight and provided with at least one control member influencing its trajectory, the missile having a frame and being stabilized about at least one of its pitch and yaw axes by at least one gyroscope, mounted in the frame so as to be stationary in space, and having a rotor whose shaft is operatively associated with at least one position pickup indicating the position of the rotor shaft relative to the missile frame, to sense deviations of the missile from a preselected trajectory: said flight control circuit comprising, in combination, means connecting each position pickup to the missile frame and fixed in a plane containing the longitudinal axis of the missile and which plane also includes the line of action of said control member, for cooperation with said rotor shaft during said spinning of the missile; actuating means for said control member; and means connecting each position pickup directly to said actuating means to operate said control member in accordance with sensed deviations of the missile relative to a preselected missile trajectory; each position pickup effecting actuation of its associated control member during a time period proportional to the magnitude of a sensed deviation of the missile from the preselected missile trajectory.
Claim 2
Dependent Claim
216 words
A flight control circuit, for a missile constantly spinning about its longitudinal axis during flight and provided with at least one control member influencing its trajectory, the missile having a frame and being stabilized about at least one of its pitch and yaw axes by at least one gyroscope, mounted in the frame so as to be stationary in space, and having a rotor whose shaft is operatively associated with at least one position pickup indicating the position of the rotor shaft relative to the missile frame, to sense deviations of the missile from a preselected trajectory: said flight control circuit comprising, in combination, means connecting each position pickup to the missile frame and fixed in a plane containing the longitudinal axis of the missile and which plane also includes the line of action of said control member, for cooperation with said rotor shaft during said spinning of the missile; actuating means for said control member; and means connecting each position pickup directly to said actuating means to operate said control member in accordance with sensed deviations of the missile relative to a preselected missile trajectory; each position pickup effecting actuation of its associated control member during a time period proportional to the magnitude of a sensed deviation of the missile from the preselected missile trajectory.
Claim 3
Dependent Claim
91 words
A flight control circuit for a missile, as claimed in claim 1, in which each position pickup comprises an element which, during each rotation of the missile about its longitudinal axis, enters into operative connection with one end of the associated gyro rotor shaft; the duration of the Maintenance of this operative connection, referred to one rotation of the missile about its longitudinal axis, varying directly with the magnitude of the inclination of the associated gyro rotor shaft relative to the rotor shaft position when the missile has such preselected trajectory.
Claim 4
Dependent Claim
58 words
A flight control circuit for a missile, as claimed in claim 2, in which each element is a triangular contact element; an energizing circuit for said actuating means including a source of potential, said triangular contact element, and said gyro rotor shaft; said triangular contact element closing said energizing circuit upon engagement with the associated gyro rotor shaft.
Claim 5
Dependent Claim
47 words
A flight control circuit for a missile, as claimed in claim 3, in which said contact element is mounted on the missile frame for displacement longitudinally of the missile frame in said plane in accordance with an external guiding signal to change the trajectory of the missile.
Claim 6
Dependent Claim
108 words
A flight control circuit for a missile, as claimed in claim 3, in which each triangular contact element has its apex facing said gyro rotor shaft; the apex of each contact element, when the missile has such preselected trajectory, contacting the associated gyro rotor shaft momentarily during each rotation of the missile; each contact element being displaced from the plane of relative rotation of its associated gyro rotor shaft when the missile deviates in a first direction from the preselected trajectory, and having an increasing time of contact with its associated gyro rotor shaft when the missile deviates in a second and opposite direction from its preselected trajectory.
Claim 7
Dependent Claim
83 words
A flight control circuit for a missile, as claimed in claim 2, including a pair of triangular contact elements each secured to a respective opposite end of a gyro rotor shaft; a pickup maintained connected with the missile frame and cooperable with said triangular contact elements; an energizing circuit for said actuating means including a source of potential, said pickup, said contact elements and said gyro rotor shaft; each of said triangular contact elements closing said energizing circuit upon contact with said pickup.
Claim 8
Dependent Claim
36 words
A flight control circuit for a missile, as claimed in claim 1, in which said flight control circuit is part of a missile guided by remote control from a control station through a guide control circuit.
Claim 9
Dependent Claim
37 words
A flight control circuit for a missile, as claimed in claim 7, in which said flight control circuit is switched off responsive to receipt, at the missile, of the first guiding signal from the guide control circuit.
References Cited (Backward Citations)
US2838255A
Cited
US3188019A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-03-07 | 1975-09-06 | 1976-03-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-03-07 | 1979-09-06 | 1980-03-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-03-07 | 1983-09-06 | 1984-03-07 | $7700.00 | Window Closed / Lapsed |