US3735944A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Dual mode guidance and control system for a homing missile
Assignee: United States Department of the Navy
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Filing: 1971-06-25
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Granted: 1973-05-29
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Expires: 1991-06-25
Abstract
Abstract A missile guidance system having two control modes alternatively controlling the thrust vector of the missile. The first control mode provides turning commands for substantially aligning the missile towards an airborne target, and the second control mode controls the missile on a homing path in pursuit of the target once the missile is aligned. A threshold detector operates switches for selectively enabling the control modes, where the first mode is enabled at an angular rate of the target line-ofsight above a predetermined threshold and the second mode is enabled at a light-of-sight rate below the threshold. The first mode provides thrust vector control signals corresponding to a signal sum of the component angle signals of the line-of-sight emitted by a narrow field of view infrared sensor mounted on the missile and continuously locked on to the target, angular rate signals of the line-of-sight, and acceleration signals emitted by an accelerometer having orthogonal sensing axes normal to the line-of-sight. The second mode provides thrust vector control signals corresponding to the difference between the signal sum of the first mode and accelerometer signals emitted by an accelerometer mounted on the missile having orthogonal sensing axes normal to the missile.
Inventors
- 👤 R J Bannett
- 👤 R S Hal
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 04:04
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/008; F41G7/20; F41G7/22; F41G7/2253; F41G7/2273; F41G7/2293
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
279 words
A guidance system for an air-to-air homing thrust vector controlled missile, comprising in combination: sensor means formed to be mounted on the missile for providing two signals indicative of orthogonal component angles between a target line-of-sight and the longitudinal axis of the missile; first accelerometer means formed to be operatively mounted on the missile for providing two signals indicative of orthogonal accelerations in a plane normal to the target line-of-sight; second accelerometer means formed to be mounted on the missile for providing two signals indicative of orthogonal accelerations in a plane normal to the longitudinal axis of the missile; differentiator means connected to receive said sensor means signals for providing signals indicative of the respective rates thereof; first and second summing means respectively connected to receive corresponding ones of the signals from said first accelerometer means, said sensor means and said differentiator means for providing output signals indicative of the sums thereof; first and second subtracter means respectively connected to receive corresponding ones of the signals from said first and second summing means and said second accelerometer means for providing difference signals; threshold means connected to receive said differentiator means signals for combining them according to a predetermined relationship indicative of the structural loading and for producing an output signal when a preselected limit thereof is exceeded; and first and second switch means respectively connected to receive corresponding ones of the signals from said first and second subtracter means, and said threshold means for selectively transmitting said subtracter signals in absence of a threshold means signal, and for selectively transmitting said summing means signals in presence of a threshold means signal for controlling the thrust vector of the missile.
Claim 2
Dependent Claim
279 words
A guidance system for an air-to-air homing thrust vector controlled missile, comprising in combination: sensor means formed to be mounted on the missile for providing two signals indicative of orthogonal component angles between a target line-of-sight and the longitudinal axis of the missile; first accelerometer means formed to be operatively mounted on the missile for providing two signals indicative of orthogonal accelerations in a plane normal to the target line-of-sight; second accelerometer means formed to be mounted on the missile for providing two signals indicative of orthogonal accelerations in a plane normal to the longitudinal axis of the missile; differentiator means connected to receive said sensor means signals for providing signals indicative of the respective rates thereof; first and second summing means respectively connected to receive corresponding ones of the signals from said first accelerometer means, said sensor means and said differentiator means for providing output signals indicative of the sums thereof; first and second subtracter means respectively connected to receive corresponding ones of the signals from said first and second summing means and said second accelerometer means for providing difference signals; threshold means connected to receive said differentiator means signals for combining them according to a predetermined relationship indicative of the structural loading and for producing an output signal when a preselected limit thereof is exceeded; and first and second switch means respectively connected to receive corresponding ones of the signals from said first and second subtracter means, and said threshold means for selectively transmitting said subtracter signals in absence of a threshold means signal, and for selectively transmitting said summing means signals in presence of a threshold means signal for controlling the thrust vector of the missile.
Claim 3
Dependent Claim
29 words
A guidance system according to claim 1 further comprising: said first and second accelerometer means being parallel sensing axes when the target line-of-sight and the missile axis are parallel.
Claim 4
Dependent Claim
61 words
A guidance system according to claim 2 further comprising: rate sensing means formed to be mounted on the missile for providing signals indicative of the lateral and vertical angular rates of the missile; and third and fourth subtracter means respectively connected to receive said first and second switch means transmitted signals and said rate sensing means signals for providing difference signals.
Claim 5
Dependent Claim
76 words
A guidance system according to claim 3 further comprising: third switch means formed to be mounted on the missile responsive to Launch separation from an aircraft; time delay means connected to said third switch means and initiated thereby; and gate means connected to receive the signals from said third and fourth subtracter means and said time delay means for transmitting said third and fourth subtracter means signals at a predetermined time after the missile is launched.
Claim 6
Dependent Claim
242 words
A guidance system for an air-to-air homing thrust vector controlled missile comprising, in combination: sensor means formed to be mounted on the missile for providing a signal indicative of the angle between a target line-of-sight and the longitudinal axis of the missile; first accelerometer means formed to be operatively mounted on the missile for providing a signal indicative of the acceleration normal to the target line-of-sight; second accelerometer means formed to be mounted on the missile for providing a signal indicative of acceleration normal to the longitudinal axis of the missile; differentiator means connected to receive said sensor means signal for providing a signal indicative of the rate thereof; summing means connected to receive the signals from said first accelerometer means, said sensor means and said differentiator means for providing output signals indicative of the sum thereof; first subtracter means connected to receive the signals from said summing means and said second accelerometer means for providing a difference signal; threshold means connected to receive said differentiator means signal for determining the structural loading according to a predetermined relationship indicative of the structural loading and for producing an output signal when a preselected limit thereof is exceeded; and first switch means connected to receive the signals from said subtracter means, and said threshold means for selectively transmitting said subtracter means signal in absence of a threshold means signal, and for selectively transmitting said summing means signal in presence of a threshold means signal.
Claim 7
Dependent Claim
242 words
A guidance system for an air-to-air homing thrust vector controlled missile comprising, in combination: sensor means formed to be mounted on the missile for providing a signal indicative of the angle between a target line-of-sight and the longitudinal axis of the missile; first accelerometer means formed to be operatively mounted on the missile for providing a signal indicative of the acceleration normal to the target line-of-sight; second accelerometer means formed to be mounted on the missile for providing a signal indicative of acceleration normal to the longitudinal axis of the missile; differentiator means connected to receive said sensor means signal for providing a signal indicative of the rate thereof; summing means connected to receive the signals from said first accelerometer means, said sensor means and said differentiator means for providing output signals indicative of the sum thereof; first subtracter means connected to receive the signals from said summing means and said second accelerometer means for providing a difference signal; threshold means connected to receive said differentiator means signal for determining the structural loading according to a predetermined relationship indicative of the structural loading and for producing an output signal when a preselected limit thereof is exceeded; and first switch means connected to receive the signals from said subtracter means, and said threshold means for selectively transmitting said subtracter means signal in absence of a threshold means signal, and for selectively transmitting said summing means signal in presence of a threshold means signal.
Claim 8
Dependent Claim
29 words
A guidance system according to claim 1 further comprising: said first and second accelerometer means having parallel sensing axes when the target line-of-sight and the missile axis are parallel.
Claim 9
Dependent Claim
58 words
A guidance system according to claim 2 further comprising: rate sensing means formed to be mounted on the missile for providing a signal indicative of the angular rate of the missile; and second subtracter means connected to receive said switch means transmitted signal and said rate sensing means signal for providing a signal indicative of the difference thereof.
Claim 10
Dependent Claim
73 words
A guidance system according to claim 7 further comprising: second switch means formed to be mounted on the missile responsive to the launch separation from an aircraft; time delay means connected to said second switch means and initiated thereby; and gate means connected to receive the signals from said second subtracter means and said time delay means for transmitting said second subtracter means signal at a predetermined time after the missile is launched.
References Cited (Backward Citations)
US2826380A
Cited
US3077333A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-05-28 | 1976-11-27 | 1977-05-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-05-28 | 1980-11-27 | 1981-05-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-05-28 | 1984-11-27 | 1985-05-29 | $7700.00 | Window Closed / Lapsed |