US3868883A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Guidance system
Assignee: McDonnell Douglas Corp
•
Filing: 1964-02-20
•
Granted: 1975-03-04
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Expires: 1984-02-20
Abstract
Abstract 1. Means for guiding an object along a line-of-sight path from a launching site to a target comprising an object having an aerodynamically stable shape with a front to rear axis oriented during flight to extend substantially on the line-of-sight between the launching site and the target, means at the launching site for launching the object on a course toward the target, means for causing the object to roll about its axis at a predetermined roll rate, a light source mounted on the object in position to project light rearwardly therefrom, means at the launching site for aiming and sighting on the target, other means at the launching site oriented with the aiming and sighting means for tracking the object during flight, said tracking means including light sensitive means and means for focusing light from the light source on the object into a spot on the light sensitive means, the position of said spot on the light sensitive means corresponding to the position of the object relative to the lineof-sight between launching means and the target as determined by the aiming and sighting means, means responsive to the vertical position and to changes in the vertical position of the light spot on the light sensitive means for producing first control signals, means responsive to the horizontal position of the light spot and to changes thereof for producing second control signals, means for sending commands corresponding to said first and second signals to the object, a plurality of one-shot thrust producing elements mounted at spaced locations about the surface of the object, means for sequentially exciting groups of said thrust producing elements to laterally displace the object in space, the combined thrust produced by each group of excited elements acting substantially through the center of gravity of the object, and means on the object responsive to said commands to control the frequency of excitation of succeeding groups of thruster elements and the angular orientation of the thrust produced by each group.
Inventors
- 👤 James M Tucker
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 14:53
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/30; F41G7/301; F41G7/305; F42; F42B; F42B15/00; F42B15/01; F42B15/04
Claims Analysis
Total Claims: 23
Claim 1
Independent Claim
329 words
Means for guiding an object along a line-of-sight path from a launching site to a target comprising an object having an aerodynamically stable shape with a front to rear axis oriented during flight to extend substantially on the line-of-sight between the launching site and the target, means at the launching site for launching the object on a course toward the target, means for causing the object to roll about its axis at a predetermined roll rate, a light source mounted on the object in position to project light rearwardly therefrom, means at the launching site for aiming and sighting on the target, other means at the launching site oriented with the aiming and sighting means for tracking the object during flight, said tracking means including light sensitive means and means for focusing light from the light source on the object into a spot on the light sensitive means, the position of said spot on the light sensitive means corresponding to the position of the object relative to the lineof-sight between launching means and the target as determined by the aiming and sighting means, means responsive to the vertical position and to changes in the vertical position of the light spot on the light sensitive means for producing first control signals, means responsive to the horizontal position of the light spot and to changes thereof for producing second control signals, means for sending commands corresponding to said first and second signals to the object, a plurality of one-shot thrust producing elements mounted at spaced locations about the surface of the object, means for sequentially exciting groups of said thrust producing elements to laterally displace the object in space, the combined thrust produced by each group of excited elements acting substantially through the center of gravity of the object, and means on the object responsive to said commands to control the frequency of excitation of succeeding groups of thruster elements and the angular orientation of the thrust produced by each group.
Claim 2
Dependent Claim
329 words
Means for guiding an object along a line-of-sight path from a launching site to a target comprising an object having an aerodynamically stable shape with a front to rear axis oriented during flight to extend substantially on the line-of-sight between the launching site and the target, means at the launching site for launching the object on a course toward the target, means for causing the object to roll about its axis at a predetermined roll rate, a light source mounted on the object in position to project light rearwardly therefrom, means at the launching site for aiming and sighting on the target, other means at the launching site oriented with the aiming and sighting means for tracking the object during flight, said tracking means including light sensitive means and means for focusing light from the light source on the object into a spot on the light sensitive means, the position of said spot on the light sensitive means corresponding to the position of the object relative to the lineof-sight between launching means and the target as determined by the aiming and sighting means, means responsive to the vertical position and to changes in the vertical position of the light spot on the light sensitive means for producing first control signals, means responsive to the horizontal position of the light spot and to changes thereof for producing second control signals, means for sending commands corresponding to said first and second signals to the object, a plurality of one-shot thrust producing elements mounted at spaced locations about the surface of the object, means for sequentially exciting groups of said thrust producing elements to laterally displace the object in space, the combined thrust produced by each group of excited elements acting substantially through the center of gravity of the object, and means on the object responsive to said commands to control the frequency of excitation of succeeding groups of thruster elements and the angular orientation of the thrust produced by each group.
Claim 3
Dependent Claim
37 words
The means for guiding an object to a target defined in claim 1 including means for converting said first control signals into firing frequency commands which control the frequency at which the thrust producing elements are excited.
Claim 4
Dependent Claim
39 words
The means for guiding an object to a target defined in claim 1 including means for converting the second control signals into firing angle commands which control the direction in which the thrust producing elements are facing when excited.
Claim 5
Dependent Claim
53 words
The means for guiding an object to a target defined in claim 1 including means for producing third control signals based on a predetermined thruster excitation frequency sufficient to overcome the effects of gravity and air friction on the object, and means for combining said third control signals with the firing frequency commands.
Claim 6
Dependent Claim
312 words
In a line-of-sight guided missile system including a missile and a launching station, said launching station comprising means for aiming and firing the missile in a predetermined direction toward a target, means at the launching station for aiming and sighting on the target, said aiming and sighting means being movable to follow the target, means oriented with the aiming and sighting means for tracking the missile during flight to maintain the missile on the line-of-sight course as determined by the aiming and sighting means, said tracking means including a light source located on the missile in position to project light rearwardly therefrom, and means at the launching station responsive to said light including a light sensitive element, and means positioned to receive and focus said light into a spot on the light sensitive element, the location of the light spot on the light sensitive element corresponding to the location of the missile relative to the line-of-sight, means responsive to the vertical position of the light spot and to changes therein for producing first control signals, other means responsive to the horizontal position of the light spot and to changes in the position thereof for producing second control signals, means for converting said first and second signals into corresponding guidance commands, said missile including means for establishing a predetermined in flight roll rate, a plurality of thrust producing elements mounted at spaced locations about the surface of the missile, and means responsive to said guidance commands for energizing said thrust producing elements in a predetermined sequence at a frequency which is responsive to the vertical location of the light spot on the light sensitive element and at a firing angle responsive to the horizontal location of the light spot on the light sensitive element to laterally displace the missile in space in a direction to move the missile toward the desired line-of-sight course.
Claim 7
Dependent Claim
312 words
In a line-of-sight guided missile system including a missile and a launching station, said launching station comprising means for aiming and firing the missile in a predetermined direction toward a target, means at the launching station for aiming and sighting on the target, said aiming and sighting means being movable to follow the target, means oriented with the aiming and sighting means for tracking the missile during flight to maintain the missile on the line-of-sight course as determined by the aiming and sighting means, said tracking means including a light source located on the missile in position to project light rearwardly therefrom, and means at the launching station responsive to said light including a light sensitive element, and means positioned to receive and focus said light into a spot on the light sensitive element, the location of the light spot on the light sensitive element corresponding to the location of the missile relative to the line-of-sight, means responsive to the vertical position of the light spot and to changes therein for producing first control signals, other means responsive to the horizontal position of the light spot and to changes in the position thereof for producing second control signals, means for converting said first and second signals into corresponding guidance commands, said missile including means for establishing a predetermined in flight roll rate, a plurality of thrust producing elements mounted at spaced locations about the surface of the missile, and means responsive to said guidance commands for energizing said thrust producing elements in a predetermined sequence at a frequency which is responsive to the vertical location of the light spot on the light sensitive element and at a firing angle responsive to the horizontal location of the light spot on the light sensitive element to laterally displace the missile in space in a direction to move the missile toward the desired line-of-sight course.
Claim 8
Dependent Claim
311 words
A missile guidance system comprising a missile of aerodynamically stable shape having a plurality of thrust producing elements mounted at spaced locations therearound adjacent to the surface thereof, each of said elements including a charge and means when the charge is detonated for producing thrust in a predetermined direction, means for sequentially exciting predetermined ones of said elements whereby the combined thrust force produced thereby acts through the center of gravity of the missile to laterally displace the missile in space without turning the missile, means for rotating the missile during flight, light radiating means located on the missile, and a launching station including means for launching and tracking the missile, said launching means including means for aiming and sighting on a target, means for launching a missile along an initial course toward the target, other means at the launching sight oriented with the aiming and sighting means for tracking the missile, said tracking means including a light sensitive element positioned to receive light radiated by the light radiating means on the missile, means for focusing said light into a spot on the sensitive element, the position of said spot on the sensitive element corresponding with the position of the missile relative to the desired flight path as determined by the aiming and sighting means, means responsive to the position of said spot on the sensitive means for producing first command signals corresponding to the vertical positions of the missile relative to the lIne-of-sight path and second command signals corresponding to the horizontal positions of the missile relative to the line-of-sight path, said means on the missile for sequentially energizing the thrust producing elements at a frequency under control of the first command signals and at a firing angle under control of the second command signals to laterally displace the missile in space in the direction of the desired flight path.
Claim 9
Dependent Claim
311 words
A missile guidance system comprising a missile of aerodynamically stable shape having a plurality of thrust producing elements mounted at spaced locations therearound adjacent to the surface thereof, each of said elements including a charge and means when the charge is detonated for producing thrust in a predetermined direction, means for sequentially exciting predetermined ones of said elements whereby the combined thrust force produced thereby acts through the center of gravity of the missile to laterally displace the missile in space without turning the missile, means for rotating the missile during flight, light radiating means located on the missile, and a launching station including means for launching and tracking the missile, said launching means including means for aiming and sighting on a target, means for launching a missile along an initial course toward the target, other means at the launching sight oriented with the aiming and sighting means for tracking the missile, said tracking means including a light sensitive element positioned to receive light radiated by the light radiating means on the missile, means for focusing said light into a spot on the sensitive element, the position of said spot on the sensitive element corresponding with the position of the missile relative to the desired flight path as determined by the aiming and sighting means, means responsive to the position of said spot on the sensitive means for producing first command signals corresponding to the vertical positions of the missile relative to the lIne-of-sight path and second command signals corresponding to the horizontal positions of the missile relative to the line-of-sight path, said means on the missile for sequentially energizing the thrust producing elements at a frequency under control of the first command signals and at a firing angle under control of the second command signals to laterally displace the missile in space in the direction of the desired flight path.
Claim 10
Dependent Claim
256 words
Missile guidance means comprising a missile having a body of aerodynamically stable shape, means for launching the missile along a predetermined line-of-sight path, said means including a launching tube containing a propellant which when ignited propels the missile therefrom in the direction the tube is facing, means at the launch site for aiming and sighting on a target, means on the missile for establishing a predetermined in flight missile roll rate, means on the missile for projecting light rearwardly therefrom toward the launch site, a plurality of rows of thruster elements positioned at spaced locations about the missile body, each of said elements including a charge capable when excited of producing outward thrust, means for controlling the excitation of said thruster elements including means for sequentially exciting predetermined ones of said elements whereby the combined thrust produced acts effectively through the center of gravity of the missile to laterally displace it in space, means at the launching site for tracking the missile during flight, said tracking means including a light sensitive element, and means for focusing light received from the missile into a spot on the light sensitive means, means connected to the light sensitive means for producing first and second signals corresponding respectively to the vertical and horizontal positions of the light spot relative to preselected spot thereon which corresponds to the location of the desired line-of-sight flight path, and means including a roll gyro and associated commutator means on the missile for energizing the thruster elements under control of said first and second signals.
Claim 11
Dependent Claim
256 words
Missile guidance means comprising a missile having a body of aerodynamically stable shape, means for launching the missile along a predetermined line-of-sight path, said means including a launching tube containing a propellant which when ignited propels the missile therefrom in the direction the tube is facing, means at the launch site for aiming and sighting on a target, means on the missile for establishing a predetermined in flight missile roll rate, means on the missile for projecting light rearwardly therefrom toward the launch site, a plurality of rows of thruster elements positioned at spaced locations about the missile body, each of said elements including a charge capable when excited of producing outward thrust, means for controlling the excitation of said thruster elements including means for sequentially exciting predetermined ones of said elements whereby the combined thrust produced acts effectively through the center of gravity of the missile to laterally displace it in space, means at the launching site for tracking the missile during flight, said tracking means including a light sensitive element, and means for focusing light received from the missile into a spot on the light sensitive means, means connected to the light sensitive means for producing first and second signals corresponding respectively to the vertical and horizontal positions of the light spot relative to preselected spot thereon which corresponds to the location of the desired line-of-sight flight path, and means including a roll gyro and associated commutator means on the missile for energizing the thruster elements under control of said first and second signals.
Claim 12
Dependent Claim
37 words
The guidance means defined in claim 7 wherein said first signals control the firing frequency of the thruster elements and said second signals control the angular orientation of the thruster elements at the time they are fired.
Claim 13
Dependent Claim
242 words
In combination a missile and missile launching means comprising a missile having an aerodynamically stable body including means thereon for rotating said body at a predetermined roll rate, thrust producing means on the body capable when fired of producing thrust to laterally displace the missile in space relative to its forward movement, said last named means including a plurality of thruster elements arranged in substantially parallel circumferentially spaced rows about the surface of the missile, control means in the missile having a connection to each of said thruster elements, other means connected to the control means for controlling the frequency and angular orientation of the thruster elements at the time they are fired, said last named means including tracking means comprising a light source located on the missile in position to project light rearwardly therefrom, and a light sensitive element located at the launching means including means for focusing light received from said light source in a spot thereon, means associated with the light sensitive means for producing first control signals responsive to the vertical position of the light spot on the light sensitive means, other means for producing second control signals responsive to the horizontal position of the light spot on the light sensitive means, and means connecting the tracking means with the thruster element, control means including a spool mounted on the missile and a wire link wound on the spool and having one end connected to the launching means.
Claim 14
Dependent Claim
242 words
In combination a missile and missile launching means comprising a missile having an aerodynamically stable body including means thereon for rotating said body at a predetermined roll rate, thrust producing means on the body capable when fired of producing thrust to laterally displace the missile in space relative to its forward movement, said last named means including a plurality of thruster elements arranged in substantially parallel circumferentially spaced rows about the surface of the missile, control means in the missile having a connection to each of said thruster elements, other means connected to the control means for controlling the frequency and angular orientation of the thruster elements at the time they are fired, said last named means including tracking means comprising a light source located on the missile in position to project light rearwardly therefrom, and a light sensitive element located at the launching means including means for focusing light received from said light source in a spot thereon, means associated with the light sensitive means for producing first control signals responsive to the vertical position of the light spot on the light sensitive means, other means for producing second control signals responsive to the horizontal position of the light spot on the light sensitive means, and means connecting the tracking means with the thruster element, control means including a spool mounted on the missile and a wire link wound on the spool and having one end connected to the launching means.
Claim 15
Dependent Claim
47 words
In the combination set forth in claim 9 means for determining the time rate of change of the vertical and horizontal positions of the light sPot on the light sensitive elements, and means for combining said time rate changes respectively with the first and second control signals.
Claim 16
Dependent Claim
25 words
In the combination set forth in claim 9 means for producing a control signal component to compensate for the effects of gravity of the missile.
Claim 17
Dependent Claim
27 words
In the combination set forth in claim 9 each of said thruster elements is oriented on the missile to produce lateral and forward thrust components when fired.
Claim 18
Dependent Claim
24 words
In the combination set forth in claim 9 means for modifying the second control signals to compensate for the roll rate of the missile.
Claim 19
Dependent Claim
246 words
Means for guiding a missile along a line-of-sight flight path comprising a missile having an aerodynamically stable shape, means for launching the missile along a predetermined line-of-sight flight path, means for establishing a predetermined in flight missile roll rate, means associated with the launching means for sighting on a target, and means oriented with the sighting means for tracking the missile, said tracking means includng a light source on the missile and means at the launching site responsive to the light from said source, said light responsive means including a light sensitive element and means for focusing the light received from the source into a spot on said light sensitive element, means responsive to the position of the light spot on the light sensitive means relative to a predetermined position corresponding to the line-of-sight flight path established by the sighting means, said means including means for producing first control signals responsive to the vertical displacement and rate of change thereof of the missile relative to the line-of-sight flight path and second control signals responsive to the horizontal displacement and rate of change thereof of the missile relative to the line-of-sight flight path, means for transmitting said first and second control signals to the missile, and means on the missile for converting said first and second signals into commands for guidance purposes, said converting means including roll gyro means having a predetermined axial orientation and commutator means movable relative to the axis of the roll gyro means.
Claim 20
Dependent Claim
246 words
Means for guiding a missile along a line-of-sight flight path comprising a missile having an aerodynamically stable shape, means for launching the missile along a predetermined line-of-sight flight path, means for establishing a predetermined in flight missile roll rate, means associated with the launching means for sighting on a target, and means oriented with the sighting means for tracking the missile, said tracking means includng a light source on the missile and means at the launching site responsive to the light from said source, said light responsive means including a light sensitive element and means for focusing the light received from the source into a spot on said light sensitive element, means responsive to the position of the light spot on the light sensitive means relative to a predetermined position corresponding to the line-of-sight flight path established by the sighting means, said means including means for producing first control signals responsive to the vertical displacement and rate of change thereof of the missile relative to the line-of-sight flight path and second control signals responsive to the horizontal displacement and rate of change thereof of the missile relative to the line-of-sight flight path, means for transmitting said first and second control signals to the missile, and means on the missile for converting said first and second signals into commands for guidance purposes, said converting means including roll gyro means having a predetermined axial orientation and commutator means movable relative to the axis of the roll gyro means.
Claim 21
Dependent Claim
284 words
Means for guiding a missile along a line-of-sight path from a launching station to a target comprising a missile having a body of aerodynamically stable shape, means at the launching station for launching the missile along a predetermined line-of-sight path, means for establishing a predetermined in flight missile roll rate, said missile includng a plurality of thruster elements positioned at spaced locations on the missile body, each of said elements including a charge of a material capable when excited of producing thrust and each of said elements having means for directing the thrust produced thereby laterally outwardly from the missile body, a light source located at the rear of the missile, means at the launching site for sighting on a target, other means oriented with the sighting means for responding to the light from the light source on the missile, said last named means including a light sensitive element and means for focusing light received from the light source into a spot on said light sensitive element, means for producing electrical signals corresponding to the vertical and horizontal positions of the light spot on the light sensitive element relative to a predetermined position thereon corresponding to the line-of-sight established by the sighting means, means for transmitting said signals to the missile, and means for converting said signals into firing frequency commands based on the vertical position and changes thereof in the position of the light spot relative to the predetermined position on the light sensitive element and firing angle commands based on the horizontal position and changes thereof in the position of the light spot relative to the predetermined position, said commands controlling respectively the firing frequency and firing direction of the thruster elements.
Claim 22
Dependent Claim
284 words
Means for guiding a missile along a line-of-sight path from a launching station to a target comprising a missile having a body of aerodynamically stable shape, means at the launching station for launching the missile along a predetermined line-of-sight path, means for establishing a predetermined in flight missile roll rate, said missile includng a plurality of thruster elements positioned at spaced locations on the missile body, each of said elements including a charge of a material capable when excited of producing thrust and each of said elements having means for directing the thrust produced thereby laterally outwardly from the missile body, a light source located at the rear of the missile, means at the launching site for sighting on a target, other means oriented with the sighting means for responding to the light from the light source on the missile, said last named means including a light sensitive element and means for focusing light received from the light source into a spot on said light sensitive element, means for producing electrical signals corresponding to the vertical and horizontal positions of the light spot on the light sensitive element relative to a predetermined position thereon corresponding to the line-of-sight established by the sighting means, means for transmitting said signals to the missile, and means for converting said signals into firing frequency commands based on the vertical position and changes thereof in the position of the light spot relative to the predetermined position on the light sensitive element and firing angle commands based on the horizontal position and changes thereof in the position of the light spot relative to the predetermined position, said commands controlling respectively the firing frequency and firing direction of the thruster elements.
Claim 23
Dependent Claim
40 words
The means for guiding an object from a launching site along a line-of-sight flight path to a target defined in claim 15 wherein means are provided on the missile for storing portions of the command impulses until they are needed.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-03-03 | 1978-09-02 | 1979-03-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-03-03 | 1982-09-02 | 1983-03-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-03-03 | 1986-09-02 | 1987-03-04 | $7700.00 | Window Closed / Lapsed |