US3575362A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Adaptive missile control system incorporating a supervisory loop
Assignee: Individual
•
Filing: 1968-10-03
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Granted: 1971-04-20
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Expires: 1988-10-03
Abstract
Abstract An adaptive missile control system having a supervisory loop operative during high speed and low altitude of the missile in which high dynamic pressures are effective on the control surfaces requiring small deflection actuation of the control surfaces which supervisory loop is inoperative during low speed and high altitudes of the missile to provide adaptive control to the control surfaces for equally effective missile guidance control in accordance with the speed of the missile and the density of the air through which it travels.
Inventors
- 👤 William M Hammond
- 👤 Willis G Martin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 06:01
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/30; F41G7/301; G; G05; G05D; G05D1/00; G05D1/10; G05D1/107
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
259 words
A nonlinear passive adaptive missile control system utilizing a supervisory loop with on-off switching elements to accomplish gain control by varying the on-off switching output levels comprising: a missile having control surfaces to maneuver same in roll, pitch, and yaw attitudes and having sensor means for sensing the roll, pitch, and yaw attitudes; an actuator means coupled to each control surface to drive same, two being pitch actuators and two being yaw actuators; an on-off switching means for each actuator having a supply voltage input, a control voltage input, and an output coupled, respectively, to each actuator for powering same; a roll channel, a pitch channel, and a yaw channel, each channel having one input, respectively, of roll reference voltage, pitch command voltage, and yaw command voltage and another input, respectively, of roll attitude sensor signal, pitch attitude signal, and yaw attitude signal coupled respectiVely to said roll, pitch, and yaw sensing means, and each channel with an output coupled to said switching means; a supervisory loop having an output coupled in common to all of said supply voltage inputs of said on-off switching means and having one input coupled to said roll channel output and another input of roll limit cycle amplitude reference voltage to compare the voltages of the two inputs to vary the output supply voltage whereby the supervisory loop controls the supply voltage amplitude to said actuators through said on-off switching means until it saturates after which a constant supply voltage is applied in accordance with the on-off switching means as controlled from said channels.
Claim 2
Dependent Claim
259 words
A nonlinear passive adaptive missile control system utilizing a supervisory loop with on-off switching elements to accomplish gain control by varying the on-off switching output levels comprising: a missile having control surfaces to maneuver same in roll, pitch, and yaw attitudes and having sensor means for sensing the roll, pitch, and yaw attitudes; an actuator means coupled to each control surface to drive same, two being pitch actuators and two being yaw actuators; an on-off switching means for each actuator having a supply voltage input, a control voltage input, and an output coupled, respectively, to each actuator for powering same; a roll channel, a pitch channel, and a yaw channel, each channel having one input, respectively, of roll reference voltage, pitch command voltage, and yaw command voltage and another input, respectively, of roll attitude sensor signal, pitch attitude signal, and yaw attitude signal coupled respectiVely to said roll, pitch, and yaw sensing means, and each channel with an output coupled to said switching means; a supervisory loop having an output coupled in common to all of said supply voltage inputs of said on-off switching means and having one input coupled to said roll channel output and another input of roll limit cycle amplitude reference voltage to compare the voltages of the two inputs to vary the output supply voltage whereby the supervisory loop controls the supply voltage amplitude to said actuators through said on-off switching means until it saturates after which a constant supply voltage is applied in accordance with the on-off switching means as controlled from said channels.
Claim 3
Dependent Claim
158 words
A nonlinear passive adaptive missile control system as set forth in claim 1 wherein: said channels each include a first summing network, a lead-lag network, and a second summing network with said pitch and yaw channels having an inverter between said lead-lag and second summing networks, said one and other inputs being to said first summing network, the outputs of said second summing networks being to said control input of said on-off switching means, the output from said pitch channel lead-lag network and from said inverter therein being to said second summing networks controlling the on-off switching circuits of the pitch actuators, and the output from said yaw channel lead-lag network and from said inverter therein being to said second summing networks controlling the on-off switching circuits of the yaw actuators to switch the respective on-off switching circuits to conduct supply voltage to the actuators whenever an error voltage exists between the inputs to said first summing network.
Claim 4
Dependent Claim
95 words
A nonlinear passive adaptive missile control system as set forth in claim 2 wherein: said supervisory loop includes a full wave rectifier, a third summing network, a multiplier, an integrating network, and a limiter, in that order, from said one input to said supply voltage output, said other input of said roll limit cycle amplitude reference voltage being the second input to said third summing network to vary the output supply voltage from a maximum limit to a minimum limit proportional to the integral of the sum of the inputs to said third summing network.
Claim 5
Dependent Claim
69 words
A nonlinear passive adaptive missile control system as set forth in claim 3 wherein: said actuators are one, two, three, and four from top to bottom, two and four being coupled to control surfaces for pitch control and one and three being coupled to control surfaces for yaw control whereby the pitch control surfaces and the yaw control surfaces will be actuated in unison in the same angular directions.
Claim 6
Dependent Claim
28 words
A nonlinear passive adaptive missile control system as set forth in claim 4 wherein said roll attitude sensor producing said sensor signal is a gyroscope in said missile.
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) | 1974-04-19 | 1974-10-19 | 1975-04-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-04-19 | 1978-10-19 | 1979-04-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-04-19 | 1982-10-19 | 1983-04-20 | $7700.00 | Window Closed / Lapsed |