US3862584A - Fire ranging method for launchers of self-propelled missiles - Google Patents

Fire ranging method for launchers of self-propelled missiles Download PDF

Info

Publication number
US3862584A
US3862584A US348001A US34800173A US3862584A US 3862584 A US3862584 A US 3862584A US 348001 A US348001 A US 348001A US 34800173 A US34800173 A US 34800173A US 3862584 A US3862584 A US 3862584A
Authority
US
United States
Prior art keywords
missile
launcher
trial
trajectory
launched
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US348001A
Other languages
English (en)
Inventor
Hermann Karl Schmidt
Jean Michel Tauzin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
CNIM Groupe SA
Original Assignee
Constructions Navales et Industrielle de la Mediterranee CNIM SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Constructions Navales et Industrielle de la Mediterranee CNIM SA filed Critical Constructions Navales et Industrielle de la Mediterranee CNIM SA
Application granted granted Critical
Publication of US3862584A publication Critical patent/US3862584A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F41G3/142—Indirect aiming means based on observation of a first shoot; using a simulated shoot

Definitions

  • ABSTRACT A fire ranging method for launchers of self-propelled missiles consisting in measuring the angular deviation between the theoretical trajectory of the missile and the point where combustion of the acceleration propulsive charge ceases and in subjecting the launcher to an angular displacement in the opposite direction, the amplitude of said angular displacement being proportional to that of the measured deviation.
  • This invention relates to a fire ranging method for launchers of self-propelled missiles.
  • Ranging of self-propelled missiles is made very difficult owing to the magnitude of the deviations in accuracy caused by the effect of winds, this being particularly strong on missiles provided with a tail fin unit and having a relatively low speed of departure from the launcher.
  • the aim of the present invention is to provide amethod of ranging which obviates these various disadvantages.
  • a fire ranging method forlaunchers of self-propelled missiles in which the angular deviation between the theoretical trajectory of the missile and the point where combustion of the acceleration propulsive charge ceases is measured, and the launcher is subjected to angular movement in the opposite direction and with an amplitude proportional to that of the measured deviation, the proportion factor being adapted to the type of missile in question andis.determinedexperimentally.
  • FIG. 1 shows a curve illustrating diagrammatically the horizontal projection of the trajectory of a selfpropelled missile
  • FIG. 2 shows a diagram illustrating a visual method of ranging.
  • FIG. 3 is a schematic illustration illustrating a remote controlled method of ranging.
  • FIG. 1 illustrates, in a diagrammatic manner, the trajectory devia tion of a self-propelled missile.
  • the straight line AX shows the trajectory followed by the missile when there is no wind and the curve AY represents the trajectory followed by the missile when acted upon by a side wind from a direction perpendicular thereto, illustrated by. the vector V.
  • the trajectory of the missile is purely ballistic; the missile being situated in a mass of moving air, will be moved with the said mass of air, in other words the trajectory will bend in the reverse direction in the direction towards AX.
  • the launcher is equipped with a fixed grid-type collimator similar to that shown in FIG. 2, the optical axis of this collimator being strictly parallel to the axis of the launcher, and a visual reference mark represents the axis of the launcher. In the neutral position the reference mark is situated at the centre 0 of the collimator.
  • the operator locates the position B1 of themissile on his grid; he then engages the training mechanism and modifies the training setting so that the reference mark representing the axis of the launcher is situated on the grid in the position B2 symmetrical to B1 relatively to the centre 0 of the collimator.
  • the training mechanism is calculated so that the movement of the reference mark and the movement of the launcher are in the proportion l/k in order that the desired correction is automatically effected.
  • the sight comprises a reticle which the operator maintains by visually following the image of the missile until the end of the acceleration phase, the launcher being in a slave relationship whereby it is made to follow the movement of the sight in the reverse sense and with an amplitude which is in accordance with the value l/k.
  • This television camera can either be usedin combination with a grid in a similar fashion to the first constructional form or can be used to follow the missile visually in a manner similar to the second form.
  • a television camera is mounted on a launcher 12 such that its optical axis is parallel to the axis ofthe launcher 12.
  • the television camera 10 is coupled by conventional means, such as a cable 13, to a receiver 14.
  • the operator follows the missile on the receiver 14 during the acceleration trajectory section A-B (FIG. 1) until flame out in the same manner as was described above in connection with the use of the collimator of FIG. 2 and the appropriate launcher correction can then be made.
  • the appropriate launcher correction could be accomplished remotely by a correction signal to any conventional launcher repositioning mechanism 18.
  • This arrangement makes it possible to arrange the ranging means at the same place as the firing control means, all being under cover. Furthermore, it is possible to arrange that there should be some slight retention of the image on the screen, which facilitates the work of the operator entrusted with ranging; on the other hand it is possible to regulate the luminosity of this image relatively to the background.
  • this method makes it possible to obtain particularly inconspicuous ranging by carrying out for adjustment purposes, a first firing of a trial rocket of small size, the deviation of which will be observed in order to determine which correction has to be made.
  • the aerodynamic and propulsive features of the trial rocket are so determined that its acceleration trajectory corresponds as far as possible to the trajectory AB, even with different wind effects.
  • these features are determined so as to amplify the effect of certain deviation factors, the correction law being adapted appropriately.
  • the said rocket may be a blank but it may also be self-destroyable by means of any conventional destruct mechanism 20.
  • the trial rocket is fired; the correction angle is determined by means of this rocket, which explodes shortly after passing the point B, that is to say without a possibility of it being logged by the enemy; the launcher is trained and the real firing stage may then commence immediately.
  • This method thus eliminates all difficulties due to logging the point of impact, all the causes of errors due to too great a time lag between ranging tiring and real firing, and makes it possible to achieve complete surprise and to carry out ranging at night.
  • a fire ranging method for launchers of selfpropelled missiles comprising the step of firing a missile from a launcher, measuring the angular deviation between the theoretical trajectory of the missile and the actual location of the missile at the point where combustion of the missile propulsive charge ceases, moving the launcher in a direction opposite to the angular deviation at a predetermined proportional amplitude to that of the measured deviation, the predetermined proportion being a function of the particular missile being launched.
  • a method wherein the angular deviation is measured by tracking the missile with a television camera, transmitting a signal from said camera to a receiver remote from the launcher and transmitting a signal back to the launcher to effect moving of the launcher in the direction opposite to the angular deviation by said predetermined proportional amplitude.
  • a fire ranging method for launchers of selfpropelled missiles comprising the steps of launching a trial missile having propulsive and aerodynamic features which correspond during the combustion phase of flight of the trial missile to those of primary missiles to be launched from thelauncher, measuring the angular deviation between the theoretical trajectory of the trial missile and the actual location of the trial missile at the point where combustion of the propulsive charge ceases, moving the launcher in the direction opposite to the angular deviation at a predetermined proportional amplitude to that of the measured deviation, the predetermined proportion being a function of the particular missile being launched.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
US348001A 1972-04-19 1973-04-05 Fire ranging method for launchers of self-propelled missiles Expired - Lifetime US3862584A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7213720A FR2181148A5 (enrdf_load_stackoverflow) 1972-04-19 1972-04-19

Publications (1)

Publication Number Publication Date
US3862584A true US3862584A (en) 1975-01-28

Family

ID=9097126

Family Applications (1)

Application Number Title Priority Date Filing Date
US348001A Expired - Lifetime US3862584A (en) 1972-04-19 1973-04-05 Fire ranging method for launchers of self-propelled missiles

Country Status (7)

Country Link
US (1) US3862584A (enrdf_load_stackoverflow)
JP (1) JPS4917099A (enrdf_load_stackoverflow)
DE (1) DE2315880A1 (enrdf_load_stackoverflow)
FR (1) FR2181148A5 (enrdf_load_stackoverflow)
GB (1) GB1380531A (enrdf_load_stackoverflow)
IL (1) IL41943A0 (enrdf_load_stackoverflow)
IT (1) IT981559B (enrdf_load_stackoverflow)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0261091A3 (en) * 1986-09-17 1989-03-15 Aktiebolaget Bofors A method and an apparatus for tracking a missile in its trajectory
EP0519315A1 (de) * 1991-06-20 1992-12-23 DIEHL GMBH & CO. Einrichtung zur Messung des Höhenprofils eines Bodenwindes
US5454265A (en) * 1991-06-20 1995-10-03 Diehl Gmbh & Co. Installation for the measurement of the altitude of a surface wind, particularly for improving the hitting accuracy of unguided projectiles
FR2762384A1 (fr) * 1997-04-18 1998-10-23 Rheinmetall Ind Ag Procede de pointage de l'arme d'un systeme d'arme et systeme d'arme pour la mise en oeuvre de ce procede
US5993215A (en) * 1998-05-15 1999-11-30 Kotsiopoulos; Thomas G. Training weapon with trigger actuated indicator light
US6237462B1 (en) * 1998-05-21 2001-05-29 Tactical Telepresent Technolgies, Inc. Portable telepresent aiming system
US20060178085A1 (en) * 2005-02-04 2006-08-10 Nicholas Sotereanos Remotely controlled vehicle
US7350744B1 (en) * 2006-02-22 2008-04-01 Nira Schwartz System for changing warhead's trajectory to avoid interception

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5470953A (en) * 1977-11-08 1979-06-07 Tomokichi Yamazaki *kinoko* cultivating method and container using raw log shaped culturing base having core rod
JPS5497252A (en) * 1978-01-18 1979-08-01 Michio Kasai Cultivation of mushroom
JPS55152960U (enrdf_load_stackoverflow) * 1979-04-20 1980-11-04
US4387865A (en) * 1980-08-25 1983-06-14 The United States Of America As Represented By The Secretary Of The Navy Method for steering a solid propellant ballistic vehicle
US4589225A (en) * 1983-03-11 1986-05-20 Stensaas Larry J Plant fertilization using a microbiological system for phosphorus extraction and distribution
JPS6345160U (enrdf_load_stackoverflow) * 1986-09-09 1988-03-26
JPH0789794B2 (ja) * 1988-03-07 1995-10-04 株式会社サイシン キノコの栽培方法
RU2229668C1 (ru) * 2003-01-04 2004-05-27 ОАО Научно-исследовательский институт приборостроения им. В.В. Тихомирова Огневая секция
RU2229085C1 (ru) * 2003-07-14 2004-05-20 ОАО "НИИ Приборостроения им. В.В.Тихомирова" Огневая секция
CN103848694A (zh) * 2014-03-23 2014-06-11 四川金堂海纳生物医药技术研究所 一种羊肚菌培养基的制备方法
CN104098373A (zh) * 2014-03-25 2014-10-15 四川金堂海纳生物医药技术研究所 一种羊肚菌专用营养包的配制方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US728716A (en) * 1902-05-19 1903-05-19 Elmer W Hubbard Sight for guns.
US1218706A (en) * 1914-10-28 1917-03-13 John B Semple Gun.

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US728716A (en) * 1902-05-19 1903-05-19 Elmer W Hubbard Sight for guns.
US1218706A (en) * 1914-10-28 1917-03-13 John B Semple Gun.

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0261091A3 (en) * 1986-09-17 1989-03-15 Aktiebolaget Bofors A method and an apparatus for tracking a missile in its trajectory
EP0519315A1 (de) * 1991-06-20 1992-12-23 DIEHL GMBH & CO. Einrichtung zur Messung des Höhenprofils eines Bodenwindes
US5454265A (en) * 1991-06-20 1995-10-03 Diehl Gmbh & Co. Installation for the measurement of the altitude of a surface wind, particularly for improving the hitting accuracy of unguided projectiles
FR2762384A1 (fr) * 1997-04-18 1998-10-23 Rheinmetall Ind Ag Procede de pointage de l'arme d'un systeme d'arme et systeme d'arme pour la mise en oeuvre de ce procede
US5993215A (en) * 1998-05-15 1999-11-30 Kotsiopoulos; Thomas G. Training weapon with trigger actuated indicator light
US6237462B1 (en) * 1998-05-21 2001-05-29 Tactical Telepresent Technolgies, Inc. Portable telepresent aiming system
US6679158B1 (en) * 1998-05-21 2004-01-20 Precision Remotes, Inc. Remote aiming system with video display
US20060178085A1 (en) * 2005-02-04 2006-08-10 Nicholas Sotereanos Remotely controlled vehicle
US8083569B2 (en) 2005-02-04 2011-12-27 Nicholas Sotereanos Remotely controlled vehicle
US7350744B1 (en) * 2006-02-22 2008-04-01 Nira Schwartz System for changing warhead's trajectory to avoid interception

Also Published As

Publication number Publication date
IT981559B (it) 1974-10-10
JPS4917099A (enrdf_load_stackoverflow) 1974-02-15
GB1380531A (en) 1975-01-15
DE2315880A1 (de) 1973-10-25
FR2181148A5 (enrdf_load_stackoverflow) 1973-11-30
IL41943A0 (en) 1973-06-29

Similar Documents

Publication Publication Date Title
US3862584A (en) Fire ranging method for launchers of self-propelled missiles
US4015258A (en) Weapon aiming system
US3598344A (en) Missile command system
KR20030005234A (ko) 정밀 포격 시뮬레이터 시스템 및 방법
RU2584210C1 (ru) Способ стрельбы управляемым снарядом с лазерной полуактивной головкой самонаведения
GB2107835A (en) Correcting, from one shot to the next, the firing of a weapon
US4086841A (en) Helical path munitions delivery
WO2021198569A1 (en) Target acquisition system for an indirect-fire weapon
RU2669690C1 (ru) Способ коррекции стрельбы из артиллерийских орудий
RU2343392C1 (ru) Способ управления стрельбой из пушки управляемым снарядом
RU2538509C1 (ru) Способ стрельбы управляемой ракетой
RU2351508C1 (ru) Вертолетный комплекс высокоточного оружия ближнего действия
RU2213926C1 (ru) Способ наведения управляемой ракеты
RU2331834C1 (ru) Способ наведения управляемой ракеты
RU2715466C1 (ru) Способ пристрелки цели с использованием специального реактивного снаряда
RU2596173C1 (ru) Система наведения высокоточного оружия
RU2549559C1 (ru) Способ управления комплексами вооружения формирований реактивной артиллерии при стрельбе
RU2439462C1 (ru) Способ управления высокоточным оружием
GB1264084A (enrdf_load_stackoverflow)
RU2436032C1 (ru) Способ наведения управляемой ракеты
DE3337873A1 (de) Geschoss fuer granatwerfersysteme
RU2496081C1 (ru) Способ управления движением летательного аппарата
RU2240486C1 (ru) Способ наведения управляемой ракеты
RU2290591C1 (ru) Способ наведения управляемой ракеты
US3779194A (en) Marine missiles for destruction of submarine targets