Patent US3900175A successfully refreshed from Google Patents.
US3900175A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Guidance system for an anti-aircraft missile
Assignee: Saab Bofors AB
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Filing: 1973-06-19
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Granted: 1975-08-19
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Expires: 1993-06-19
Abstract
Abstract A guidance system for an anti-aircraft missile comprising a missile launcher and a sighting device disposed close to the launcher. The sighting device has a sight-line which is rotatable about an azimuth axis as well as an elevation axis perpendicular to the azimuth axis and which is intended to be kept continuously pointing at a target towards which the launched missile is to be guided. The launcher is coupled to the sighting device so that the launching direction is always parallel to the direction of the sightline of the sighting device. Further, the system includes means for determining the deviation of the missile from the sight-line in two orthogonal directions perpendicular to the sight-line and for producing a yaw control signal representing the deviation of the missile in the first direction and a pitch control signal representing the deviation of the missile in the second direction. The missile is provided with rudder or flight control means responsive to the yaw control signal and the pitch control signal for influencing the flight direction of the missile in a yaw plane in response to the yaw control signal and in a pitch plane perpendicular to the yaw plane in response to the pitch control signal. The missile includes also a direction reference gyroscope which defines the yaw plane of the missile as the plane perpendicular to the reference direction of the gyroscope and the pitch plane of the missile as the plane perpendicular to the yaw plane and extending through the longitudinal axis of the missile.
Inventors
- 👤 Gunnar Sten Gustav Eckerstrom
- 👤 Sven Willner Eriksson
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 21:08
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/30; F41G7/301; F41G7/303
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
418 words
In a guidance system for an anti-aircraft missile adapted to be launched from a launching device, comprising a sighting device disposed close to said launching device and having a sight-line movable about an azimuth axis and an elevation axis perpendicular to the azimuth axis and intended to be kept pointing at a target during the guidance of a launched missile towards the target, said launching device being coupled to said sighting device so as to have its launching direction substantially parallel to the direction of said sight-line at the instant of launching the missile; means for determining the deviation of the launched missile from said sight-line in a two-axes orthogonal coordinate system having a first axis and a second axis lying in a plane perpendicular to the sight-line with its origin coinciding with the sight-line and for producing a first deviation signal representing the deviation of the missile from the sight-line in the direction of said first coordinate axis and a second deviation signal representing the deviation of the missile from the sight-line in the direction of said second coordinate axis; and flight control means in said missile responsive to said deviation signals for influencing the direction of flight of the missile in a yaw control plane extending through the longitudinal axis of the missile in response to said first deviation signal and in a pitch control plane extending through the longitudinal axis of the missile perpendicularly to said yaw control plane in respone to said second deviation signal so as to control the missile to fly along said sight-line, said flight control means including attitude sensing means for determining the orientation in space of said yaw and pitch control planes, the improvement comprising that said attitude sensing means include a direction reference gyro mounted in a locked position relative to the missile before the launching of the missile with its reference direction perpendicular to the plane parallel to the elevation axis of the sight-line and to the launching direction of the launching device and adapted to be released in said position relative to the missile at the launching of the missile and subsequently to define a plane perpendicular to its reference direction as said yaw control plane for said flight control means, and that after the launching of the missile said coordinate system is rotated about the sight-line through an angle phi in response to the movements of the sight-line of the siGhting device, the value of said angle phi corresponding at least approximately to the expression
Claim 2
Dependent Claim
418 words
In a guidance system for an anti-aircraft missile adapted to be launched from a launching device, comprising a sighting device disposed close to said launching device and having a sight-line movable about an azimuth axis and an elevation axis perpendicular to the azimuth axis and intended to be kept pointing at a target during the guidance of a launched missile towards the target, said launching device being coupled to said sighting device so as to have its launching direction substantially parallel to the direction of said sight-line at the instant of launching the missile; means for determining the deviation of the launched missile from said sight-line in a two-axes orthogonal coordinate system having a first axis and a second axis lying in a plane perpendicular to the sight-line with its origin coinciding with the sight-line and for producing a first deviation signal representing the deviation of the missile from the sight-line in the direction of said first coordinate axis and a second deviation signal representing the deviation of the missile from the sight-line in the direction of said second coordinate axis; and flight control means in said missile responsive to said deviation signals for influencing the direction of flight of the missile in a yaw control plane extending through the longitudinal axis of the missile in response to said first deviation signal and in a pitch control plane extending through the longitudinal axis of the missile perpendicularly to said yaw control plane in respone to said second deviation signal so as to control the missile to fly along said sight-line, said flight control means including attitude sensing means for determining the orientation in space of said yaw and pitch control planes, the improvement comprising that said attitude sensing means include a direction reference gyro mounted in a locked position relative to the missile before the launching of the missile with its reference direction perpendicular to the plane parallel to the elevation axis of the sight-line and to the launching direction of the launching device and adapted to be released in said position relative to the missile at the launching of the missile and subsequently to define a plane perpendicular to its reference direction as said yaw control plane for said flight control means, and that after the launching of the missile said coordinate system is rotated about the sight-line through an angle phi in response to the movements of the sight-line of the siGhting device, the value of said angle phi corresponding at least approximately to the expression
Claim 3
Dependent Claim
34 words
A guidance system as claimed in claim 1, wherein the value of the angle phi is determined by the expression phi ( Chi -Chi o) sin gamma o as an approximation to the expression
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) | 1978-08-18 | 1979-02-17 | 1979-08-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-08-18 | 1983-02-17 | 1983-08-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-08-18 | 1987-02-17 | 1987-08-19 | $7700.00 | Window Closed / Lapsed |