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US3568954A
Expired / Lapsed
US
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Directional control-automatic meteorological compensation (d.c.-automet) inertial guidance system for artillery missiles
Assignee: Individual
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Filing: 1966-04-04
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Granted: 1971-03-09
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Expires: 1986-04-04
Abstract
Abstract A missile system disposed for flight in a planned trajectory ending at a target. The trajectory includes booster propulsion and sustainer propulsion phases of flight. The missile is controlled in the booster propulsion phase by means of a directionally controlled (D.C.) inertial guidance system which controls thrust direction. Booster control means is provided for creating pressure differentials across the propulsive gases of the booster motor for thrust vectoring the missile to maintain the missile in the trajectory during the booster propulsion phase of flight. In the sustainer phase of flight, the missile is controlled by an automatic meteorological compensation inertial guidance system (AUTOMET) which controls thrust magnitude. Sustainer control means is provided for varying the thrust of the sustainer to maintain the difference in the actual and desired velocities at null and thus maintain zero net axial force on the missile in the sustainer phase of flight. The system is, therefore, known as the D.C.-AUTOMET guidance system. Previous inertial guidance systems utilized a stabilized platform having a number of accelerometers mounted thereon. A plurality of gyroscopes were needed to provide a reference for the stabilized platform. Furthermore, in guidance systems of this type, very expensive precision instruments were required to perform the guidance and control functions.
Inventors
- 👤 William C Mccorkle Jr
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 15:09
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66; F42B10/661; F41; F41G; F41G7/00; F41G7/34; F41G7/36
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
247 words
A missile disposed for flight according to a planned trajectory ending in a target including booster propulsion and sustainer propulsion phases of flight, said missile provided with a booster motor disposed for providing substantially constant thrust during operation thereof, and a sustainer motor disposed for providing thrust during the booster and sustainer phase of flight with the magnitude of the thrust being variable in the sustainer phase; a gyro mounted in the missile with the spin axis along the longitudinal axis of the missile, said gyro disposed for providing a signal voltage proportionate to the amount of deviation of said missile axis from said spin axis responsive to said deviations; booster control means disposed for actuation by said gyro signal voltage for creating pressure differentials across the propulsive gases of said booster motor for thrust vectoring of said missile to restore said missile axis in alignment with said gyro spin axis during said booster propulsion phase of flight; accelerometer means mounted along said longitudinal axis of said missile for producing a signal voltage proportionate to the difference between the actual missile velocity and a desired velocity, said accelerometer signal disposed for terminating booster thrust when said difference in actual and desired velocity is null; sustainer control means actuatable by said accelerometer signals for varying the thrust of said sustainer to maintain the difference in said actual and desired velocities at null and thus maintain zero net axial force on said missile in the sustainer phase of flight.
Claim 2
Dependent Claim
247 words
A missile disposed for flight according to a planned trajectory ending in a target including booster propulsion and sustainer propulsion phases of flight, said missile provided with a booster motor disposed for providing substantially constant thrust during operation thereof, and a sustainer motor disposed for providing thrust during the booster and sustainer phase of flight with the magnitude of the thrust being variable in the sustainer phase; a gyro mounted in the missile with the spin axis along the longitudinal axis of the missile, said gyro disposed for providing a signal voltage proportionate to the amount of deviation of said missile axis from said spin axis responsive to said deviations; booster control means disposed for actuation by said gyro signal voltage for creating pressure differentials across the propulsive gases of said booster motor for thrust vectoring of said missile to restore said missile axis in alignment with said gyro spin axis during said booster propulsion phase of flight; accelerometer means mounted along said longitudinal axis of said missile for producing a signal voltage proportionate to the difference between the actual missile velocity and a desired velocity, said accelerometer signal disposed for terminating booster thrust when said difference in actual and desired velocity is null; sustainer control means actuatable by said accelerometer signals for varying the thrust of said sustainer to maintain the difference in said actual and desired velocities at null and thus maintain zero net axial force on said missile in the sustainer phase of flight.
Claim 3
Dependent Claim
65 words
A missile as in claim 1 wherein said booster control means includes a plurality of injector valves mounted around the periphery of said booster motor and connected to a source of fluid under pressure, said valves disposed for selective actuation to control the direction of thrust from said booster, and actuating means disposed for actuation of said valves in response to signals from said gyro.
Claim 4
Dependent Claim
48 words
A missile as in claim 2 wherein said actuating means includes mechanism electrically connected to said gyro to receive error signals therefrom in pitch and yaw and to selectively actuate said injector valves for diverting the direction of thrust of said booster motor to correct for said errors.
Claim 5
Dependent Claim
91 words
A missile as in claim 3 wherein said booster motor of said missile is provided with a plurality of fixed jet vanes disposed therein, said jet vanes mount at an angle to the longitudinal axis of said missile and projecting interiorly of said booster motor to produce a roll torque on said missile; and, fins mounted on the outer periphery of said missile and canted at an angle to the longitudinal axis of said missile for maintaining a predetermined roll of said missile in response to initiation of said roll torques.
Claim 6
Dependent Claim
47 words
A missile as in claim 4 with said missile including a pair of propellant tanks connected to said booster and sustainer motors, said tanks provided with pistons disposed for movement therein for forcing said propellants to said booster and sustainer motors; and, means for moving said pistons.
Claim 7
Dependent Claim
64 words
A missile as in claim 4 wherein said sustainer control means includes a throttling valve communicating with said sustainer motor and said propellants to proportionately control flow of said propellants to said sustainer motor to vary the thrust thereof in response to the difference in thrust and drag of the missile; said throttling valve being disposed for actuation by said accelerometer output signal voltage.
Claim 8
Dependent Claim
27 words
A missile as in claim 6 wherein said sustainer motor is disposed in said missile with its longitudinal axis coincident with the longitudinal axis of said missile.
Claim 9
Dependent Claim
17 words
A missile as in claim 7 wherein said booster motor is concentrically disposed about said sustainer motor.
Claim 10
Dependent Claim
39 words
A missile as in claim 8 wherein said means for moving said pistons comprises a gas generator disposed for ignition for produCing gases for exerting pressure on said pistons for movement thereof to force propellant from said propellant tanks.
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) | 1974-03-08 | 1974-09-07 | 1975-03-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-03-08 | 1978-09-07 | 1979-03-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-03-08 | 1982-09-07 | 1983-03-09 | $7700.00 | Window Closed / Lapsed |