ROTATING ALONG THE ROLL ANGLE WITH DIRECTION GYROSCOPE TO THE TARGET ACQUISITION ZONE BY THE HOMING HEAD ROCKET OUTPUTTING METHOD AND SYSTEM FOR ITS IMPLEMENTATION Russian patent published in 2018 - IPC F41G7/00 

Abstract RU 2659622 C1

FIELD: rocket equipment.

SUBSTANCE: invention relates to the control systems, in particular to rocket equipment with homing heads, and can be used in guided weapon systems located on the aerial delivery vehicles. In the rotating along the roll angle with direction gyroscope to the target acquisition zone by the homing head rocket outputting method, including the transport-launch container orientation before the missile launching relative to the target line of sight at given angles ϕH, θH, uncaging the direction gyroscope before the missile lift-off, missile longitudinal axis deviations on the yaw and pitch angles measurement relative to the memorized in the moment of its position direction gyroscope uncaging during the missile flight and the control commands generation to the actuator in proportion to the measured angular deviations before the target acquisition by the homing head, in addition, during the missile launching preparation process, measuring the carrier roll angle and the target line of sight angles relative to the associated with the carrier coordinates system, and at the time of the direction gyroscope uncaging, memorizing the carrier roll angle γH0 and the target line of sight angles ϕY0, ϕZ0, calculating the transport-launch container orientation errors relative to the predetermined direction, generating the transport-launch container orientation errors correction signals UΔθ, UΔϕ and command of the missile programmed turn in the vertical plane and summarizing them with the missile measured deviations by the yaw and pitch angles. To implement the method, introduced are memory device, by its five inputs connected to the corresponding on-board digital computer five outputs, the first and second functional converters, which inputs are connected to the memory device first and second outputs, respectively, phase shifter, which first and second inputs are connected to the first and second functional converters outputs, respectively, phase shifter third input is connected to the on-board digital computer sixth output, and the phase shifter first and second outputs are connected to the commands generation unit fourth and fifth inputs, respectively, which first, second and third outputs are connected to the commands generator sixth, seventh and eighth inputs, respectively, in-series connected gyro-coordinator with the roll angle sensor and the modulation signals generator, which first and second outputs are connected to the actuator third and fourth inputs, respectively, and to the control commands generator ninth and tenth inputs, respectively, which eleventh input is connected to the direction gyroscope second output, and the control commands generator third and fourth outputs are connected to the homing head first and second inputs, respectively.

EFFECT: increase in the reliability based on the targets hitting increased probability with ensuring the missiles with the direction gyroscope output to the located at long ranges targets emission homing head acquisition zone high accuracy, due to the transport-launch container relative to the target line of sight orientation errors calculation and their subsequent compensation.

3 cl, 3 dwg

Similar patents RU2659622C1

Title Year Author Number
METHOD OF LONG-RANGE TARGET CAPTURE OF ZONE MISSILE HOMING HEAD AND LONG MISSILE GUIDANCE SYSTEM 2015
  • Gusev Andrej Viktorovich
  • Fimushkin Valerij Sergeevich
  • Nedosekin Igor Alekseevich
  • Minakov Vladimir Mikhajlovich
  • Grankin Aleksej Nikolaevich
RU2583347C1
SHORT-RANGE HIGHLY ACCURATE WEAPONRY HELICOPTER COMPLEX 2007
  • Klevenkov Boris Zinov'Evich
  • Pavlov Aleksandr Mikhajlovich
  • Tarasov Viktor Ivanovich
  • Ovsenev Sergej Sergeevich
  • Ivanov Vjacheslav Viktorovich
RU2351508C1
GYRO TARGET FOLLOW-UP DEVICE OF SELF-GUIDED ROLLING MISSILE 2009
  • Gusev Andrej Viktorovich
  • Morozov Vladimir Ivanovich
  • Nedosekin Igor' Alekseevich
  • Minakov Vladimir Mikhajlovich
RU2397435C1
METHOD FOR EXPELLING MISSILE TO TRACK INITIATION AREA WITH TARGET SEEKING HEAD, AND SYSTEM FOR ITS IMPLEMENTATION (VERSIONS) 2013
  • Gusev Andrej Viktorovich
  • Morozov Vladimir Ivanovich
  • Nedosekin Igor' Alekseevich
  • Minakov Vladimir Mikhajlovich
  • Leonova Elena L'Vovna
  • Grankin Aleksej Nikolaevich
RU2542691C1
MISSILE GUIDANCE SYSTEM 1998
  • Babichev V.I.
  • Zbrankov Ju.V.
  • Koechkin N.N.
RU2138768C1
METHOD OF FLIGHT CONTROL OF AIR-TO-SURFACE HOMING MISSILE AND DEVICE FOR ITS REALIZATION 1997
  • Kegeles A.L.
  • Khejfets L.N.
  • Mikhajlova S.Ja.
  • Smol'Skij G.N.
  • Oreliov G.R.
  • Kirsanov A.I.
  • Toporov V.N.
  • Fomin Ju.A.
RU2111439C1
ROTATING SELF-GUIDED MISSILE 2018
  • Grachikov Dmitrij Viktorovich
  • Dulov Aleksandr Alekseevich
  • Emelyanov Andrej Fedorovich
  • Kolomnikov Sergej Evgenevich
  • Kuzin Aleksandr Vasilevich
  • Makarov Dmitrij Viktorovich
  • Pitikov Sergej Viktorovich
  • Pustygin Boris Nikolaevich
  • Uspenskij Andrej Igorevich
RU2694934C1
METHOD OF MISSILE PLACING INTO TRACK INITIATION AREA BY HOMING HEAD AND DEVICE FOR ITS IMPLEMENTATION 2015
RU2613016C1
METHOD FOR INERTIAL GUIDANCE OF ROLL SHELL 2015
  • Babichev Viktor Ilich
  • Gusev Andrej Viktorovich
  • Morozov Vladimir Ivanovich
  • Shigin Aleksandr Viktorovich
  • Rabinovich Vladimir Isaakovich
  • Dolgova Tatjana Savvovna
  • Akulinin Sergej Igorevich
  • Monkin Valerij Borisovich
  • Balzamov Igor Anatolevich
RU2584403C1
GUIDANCE SYSTEM OF GUIDED MISSILE 2001
  • Zbrankov Ju.V.
  • Babichev V.I.
  • Koechkin N.N.
  • Rabinovich V.I.
RU2217692C2

RU 2 659 622 C1

Authors

Gusev Andrej Viktorovich

Morozov Vladimir Ivanovich

Nedosekin Igor Alekseevich

Minakov Vladimir Mikhajlovich

Leonova Elena Lvovna

Grankin Aleksej Nikolaevich

Dates

2018-07-03Published

2017-08-29Filed