# US 4,397,430 A · Simplified homing system for a missile of the shell or rocket type > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 4,397,430 A - Document ID: US4397430A - Status: Granted - Kind: A - Application number: 06/230,117 - Filed: 1981-01-26 - Granted: 1983-08-09 - Earliest claimed: 1980-01-29 - Assignees: Societe Europeenne de Propulsion - Inventors: Richard Heidmann; Dino Crapiz - Web page: https://patentgrep.com/patent/US4397430A ## CPC - F41G 7/2253: {Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target} - F41G 7/222: {for spin-stabilized missiles} - F41G 7/2293: {using electromagnetic waves other than radio waves} - F41G: WEAPON SIGHTS; AIMING (optical aspects thereof G02B) ## Abstract The simplified homing system comprises an accelerometric device mounted directly on the missile structure and associated with discriminating means for delivering signals representative of the lateral acceleration .gamma..sub.ext of the missle due to outside forces and the centrifugal acceleration .gamma..sub.c due to the rolling; target detection means directly mounted on the missile structure; passive means ensuring the keeping up of the rolling movement of the missile; means for determining from information supplied by the accelerometric device and discriminating means and by target detection means the serviceable values related to the vector V indicating the relative speed of the missile with respect to the air in a reference system related to the missile and to the vector u.sub.c representing the direction of the target with respect to the axis of the missile and means for elaborating a guiding force F.sub.p from the said predetermined serviceable values related to the vectors V and u.sub.c. ## Claims ### Claim 1 Simplified homing system for a missile of the shell or rocket type which is not actively stabilized against rolling, comprising means for detecting a target, which means are directly mounted on and associated with the missile; an accelerometric device mounted directly on the missile structure and including at least one accelerometer having a sensing axis radial with respect to the missile axis to detect the lateral acceleration of the missile; means for elaborating a guiding force F.sub.p applied to the missile via actuators acting on rudders, said elaborating means including passive means for ensuring the keeping up of the rolling movement of the missile; means associated with the accelerometric device for discriminating the lateral acceleration .gamma..sub.ext of the missile due to outside forces and the centrifugal acceleration .gamma..sub.c due to the rolling; means for determining the serviceable values related to the vector V indicating the relative speed of the missile with respect to the air in a reference system related to the missile from information supplied by the accelerometric device and the associated discriminator means; and means for determining serviceable values related to the vector u.sub.c representing the direction of the target with respect to the axis of the missile from target detection means, wherein the means for elaborating a guiding force F.sub.p elaborates said force from the said predetermined serviceable values related to the vectors V and u.sub.c. ### Claim 2 (depends on 1) Missile homing system as claimed in claim 1, wherein the discriminator means associated with the accelerometric device comprise a circuit to determine the mean value of the signal supplied by the said accelerometer and a circuit for measuring the peak-to-peak amplitude of the said signal supplied by the said accelerometer to supply respectively a signal indicative of the centrifugal acceleration .gamma..sub.c of the missile and a signal indicative of the lateral acceleration .gamma..sub.ext of the missile due to outside forces. ### Claim 3 (depends on 1) Missile homing system as claimed in claim 1, wherein the acelerometric device comprises at least two accelerometers having radial sensing axes placed at 180.degree. from each other in a plane perpendicular to the axis of the missile. ### Claim 4 (depends on 1) Missile homing system as claimed in claim 1, wherein the accelerometer device comprises at least two accelerometers having radial sensing axes placed at 90.degree. from each other in a plane perpendicular to the axis of the missile. ### Claim 5 (depends on 3) Missile homing system as claimed in claim 3, wherein the discriminator means associated with the accelerometer device comprise a circuit summing up the signals supplied by the said accelerometers and a circuit for substracting the signals supplied by the said accelerometers to produce respectively a signal indicative of the centrifugal acceleration .gamma..sub.c of the missile and a signal indicative of the lateral acceleration of the missile .gamma..sub.ext due to outside forces. ### Claim 6 (depends on 1, 2, 3, 4, 5) Missile homing system as claimed in any one of claims 1 to 5, wherein the means to determine the serviceable values related to the vector V comprise square root extracting means to determine the rolling speed .omega. of the missile from the centrifugal acceleration .gamma..sub.c supplied by the discriminator means, circuits for detecting extrema of the lateral acceleration .gamma..sub.ext supplied by the discriminator means, means for integrating the rolling speed .omega. controlled by the extrema detection circuits to supply a signal indicative of the rolling angle j between the projection of the vector V on a plane perpendicular to the axis of the missile and a reference axis of the said plane related to the missile, means for supplying an approximation signal of the lift force F.beta. of the actuators from the steering angle .beta. given by a steering indicator, means to determine the component F.beta. cos j of the approximate lift force F.beta. in the plane of incidence, from signals supplied by the approximation means of the lift force F.beta. of the actuators and the said integration means, means for elaborating the total force F related to the acceleration .gamma..sub.ext, means for substracting the component F.beta. cos j with respect to the total force F in order to determine the force P due to the lift of the missile and means for restoring the value i of the angular position of the vector V from the force P. ### Claim 7 (depends on 1, 2, 3, 4, 5) Missile homing system as claimed in any one of claims 1 to 5, wherein the target detection means comprise an optical system associated with at least one bar comprising a plurality of infrared detectors aligned and forming a predetermined angle .theta., with the axis of the missile and wherein the means to determine the serviceable values related to the vector u.sub.c indicative of the direction missile-target comprise at least a circuit to determine the angle .delta. between the said vector u.sub.c and the axis of the missile from the identification of the excited detectors, and means for integrating the rolling speed .omega. given by the square root extracting means, from the centrifugal acceleration .gamma..sub.c to give a signal indicative of a rolling angle .phi., between a detection plane defined by the vector u.sub.c and the axis of the missile and an axial reference plane related to the missile. ### Claim 8 (depends on 7) Missile homing system as claimed in claim 7, wherein the target detection means comprise at least one radial bar of infrared detectors forming a predetermined angle with the axis of the missile, which angle can vary between about 60.degree. and 90.degree.. ### Claim 9 (depends on 1, 2, 3, 4, 5) Missile homing system as claimed in any one of claims 1 to 5, wherein the target detection means comprise a system for electronically scanning the target detection field. ### Claim 10 (depends on 1, 2, 3, 4, 5) Missile homing system as claimed in any one of claims 1 to 5, wherein said system is applied to the guidance of a shell- or rocket type missile equipped with an assembly of non-guided sub-charges dropped at a small distance from the detected target. ### Claim 11 (depends on 6) Missile homing system as claimed in claim 6, wherein the target detection means comprises an optical system associated with at least one bar comprising a plurality of infrared detectors aligned and forming a predetermined angle .theta., with the axis of the missile and wherein the means to determine the serviceable values related to the vector u.sub.c indicative of the direction missile-target comprise at least a circuit to determine the angle .delta. between the said vector u.sub.c and the axis of the missile from the identification of the excited detectors, and means for integrating the rolling speed .omega. given by the square root extracting means, from the centrifugal acceleration .gamma..sub.c to give a signal indicative of a rolling angle .phi., between a detection plane defined by the vector u.sub.c and the axis of the missile and an axial reference plane related to the missile. ### Claim 12 (depends on 11) Missile homing system as claimed in claim 11, wherein the target detection means comprise at least one radial bar of infrared detectors forming a predetermined angle with the axis of the missile, which angle can vary between about 60.degree. and 90.degree.. ### Claim 13 (depends on 6) Missile homing system as claimed in claim 6, wherein the target detection means comprise a system for electronically scanning the target detection field. ### Claim 14 (depends on 6) Missile homing systems as claimed in claim 6, wherein said system is applied to the guidance of a shell- or rocket type missile equipped with an assembly of non-guided sub-charges dropped at a small distance from the detected target. ### Claim 15 (depends on 7) Missile homing systems as claimed in claim 7, wherein said system is applied to the guidance of a shell- or rocket type missile equipped with an assembly of non-guided sub-charges dropped at a small distance from the detected target. ### Claim 16 (depends on 8) Missile homing systems as claimed in claim 8, wherein said system is applied to the guidance of a shell or rocket type missile equipped with an assembly of non-guided sub-charges dropped at a small distance from the detected target.