US3706283A - Tracer device for a rocket - Google Patents

Tracer device for a rocket Download PDF

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Publication number
US3706283A
US3706283A US49054A US3706283DA US3706283A US 3706283 A US3706283 A US 3706283A US 49054 A US49054 A US 49054A US 3706283D A US3706283D A US 3706283DA US 3706283 A US3706283 A US 3706283A
Authority
US
United States
Prior art keywords
rocket
sheath
axis
tracer
tracer device
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
US49054A
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English (en)
Inventor
Jean Marie Germain Bouisse
Charles Etienne Georges Martel
Franck Pier Villey-Desmeserets
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.)
Etat Francais
Original Assignee
Etat Francais
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 Etat Francais filed Critical Etat Francais
Application granted granted Critical
Publication of US3706283A publication Critical patent/US3706283A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/38—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of tracer type

Definitions

  • a tracer device is provided for a rocket and comprises June 23, 1969 France "6920265 at lea t one heath arranged at the rear of the rocket and containing a pyrotechnical charge whose com- U-S. Cl.
  • An object of the present invention is to remedy the aforesaid drawbacks in a novel way.
  • the tracer device for a rocket or similar vehicle comprises at least one sheath arranged at the rear of the rocket and containing a pyrotechnical charge whose combustion produces a flame allowing the rocket to be followed along its trajectory and the tracer device is characterized in that the sheath terminates in a nozzle of convergent-divergent form, the centerline of the sheath being at an angle to the longitudinal axis of the rocket so as to direct the flame into the region between the inner boundary of the air streams emerging behind the rocket an the outer boundary of the propellant gas jet.
  • the sheath is fitted at an inclination on one of the ends of a rotatable cylindrical block which is embedded at its other end in a housing extending parallel to the longitudinal axis of the rocket.
  • the angle between the axis of the sheath and theaxis of the cylindrical block lies between 25 and 60.
  • the nozzle of the sheath allows the incandescent particles issuing from the combustion of the pyrotechnical charge to be given sufficient velocity for them to cross the turbulent zone and reach the region where the flows of propellent gas and air run side-by-side, whereby there is produced an extension of the flame.
  • Proper guidance of the flame is obtained through the adjustment of the inclination of the sheath on the cylindrical block in conjunction with the adjustment of the latter in the housing.
  • FIG. 1 diagrammatically illustrates the aerodynamic phenomena occurring at the rear of a rocket equipped with a tracer device according to the invention and moved under the effect of a propellent;
  • FIG. 2 shows partly broken away and in section two components of the tracer device
  • FIG. 4 is an axial section of a sheath containing the pyrotechnic charge inside the element of the device.
  • FIG. 1 of the drawing therein is seen the rear portion of a rocket F as shown in motion in the air.
  • the rear portion of the rocket F is provided with stabilizing fins a.
  • a propellent gas jet b issues from a nozzle c at the rear of the rocket and the gas jet b expands progressively and approaches the air stream layer d which travels along the body of rocket F.
  • a space e is formed between the inner boundary f of the air stream layer d and the outer boundary g of jet b. In this space are produced vortices b particularly at the rear face of rocket F.
  • rocket F carries at its rear a tracer device for emitting a flame 2, and this device comprises two elements 1 which are embedded by means of a synthetic resin 3 in housings 4 arranged diametrically around nozzle 0 of rocket F.
  • Each element 1 is composed of a sheath 5 mounted perpendicularly at its base 6 at the center of a sloping surface 7 of a cylindrical block 8 which is secured in housing 4.
  • the axis of sheath 5 is offset by an angle i from the axis of the cylindrical block 8.
  • the magnitude of angle 1' is between 25 and At its free end, sheath 5 terminates in a nozzle comprising a convergent portion 9 and a divergent portion 10.
  • Sheath 5 is a one-piece body and is lined internally with a polyester resin layer 11 containing a refractory metal oxide.
  • the sheath 5 contains in its cylindrical portion a pyrotechnical charge 12, the combustion of which gives rise to flame 2 emerging at the outlet of the divergent portion 10.
  • the casing of sheath 5 is constituted of metal, graphite or a thermosetting molded plastic.
  • the molded plastic material is advantageously fabricated from a base of phenolic molding powder containing asbestos.
  • the internal lining of polyester resin 11 in sheath 5 containing the refractory charge insures the thermal safety of the jacket of the sheath.
  • the refractory metal oxide is magnesium oxide.
  • Other metallic oxides resistant to heat are suitable such as zirconium oxide and the like.
  • the tracer device produces flame 2 directed at an inclination with respect to the longitudinal axis of rocket F toward the region where the air stream layer 0! and the gas jet b come together.
  • This is achieved through adjusting the angle i of sheath 5 on block 8, the value of i resulting from a preadjustment of the position of block 8 around its axis before it is secured in the housing 4.
  • block 8 may be rotatably mounted in the housing and after suitable adjustment it becomes embedded in resin 3.
  • surface 7 of block 8 is a sloping surface, and therefore the angle i between the axis of the sheath 5 and the axis of the block 8 depends on the position of the block 8 around its axis.
  • the discharge velocity of the incandescent particles in flame 2 is remarkably increased by the nozzle end of sheath 5, so that flame 2 easily crosses the turbulence zone h and is, in a fashion, seized by the air and gas flows, the result of which is to lengthen flame 2.
  • a tracer device comprising means for producing a tracer flame at the rear portion of the rocket between the outer boundary of the propellent jet and the inner boundary of the air stream layer, said means comprising a sheath supported in said rear portion of the rocket andhaving an outlet nozzle, the axis of said nozzle being outwardly inclined at a rearwardly diverging angle with respect to the longitudinal axis of the rocket, and means in said sheath for generating said tracer flame.
  • a tracer device as claimed in claim 7 comprising asbestos in said thermosetting plastic material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
US49054A 1969-06-23 1970-06-23 Tracer device for a rocket Expired - Lifetime US3706283A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6920965A FR2050724A5 (de) 1969-06-23 1969-06-23

Publications (1)

Publication Number Publication Date
US3706283A true US3706283A (en) 1972-12-19

Family

ID=9036213

Family Applications (1)

Application Number Title Priority Date Filing Date
US49054A Expired - Lifetime US3706283A (en) 1969-06-23 1970-06-23 Tracer device for a rocket

Country Status (5)

Country Link
US (1) US3706283A (de)
JP (1) JPS5012680B1 (de)
DE (1) DE2030722C3 (de)
FR (1) FR2050724A5 (de)
GB (1) GB1277999A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0229457A1 (de) * 1985-10-31 1987-07-22 British Aerospace Public Limited Company Leuchtsatz für Rakete
CN111596610A (zh) * 2020-05-19 2020-08-28 苏州诺达佳自动化技术有限公司 一种具有运行轨迹测控功能的工控机控制***

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3212271C1 (de) * 1982-04-02 1983-10-06 Bayern Chemie Gmbh Flugchemie Mit einer metallischen Abdeckung versehener pyrotechnischer Leuchtsatz fuer fernlenkbare Flugkoerper
DE3905748A1 (de) * 1989-02-24 1993-06-03 Dornier Gmbh Scheinziel
DE4437729C1 (de) * 1994-10-21 1996-04-25 Buck Chem Tech Werke Verfahren zum Schützen von eine IR-Strahlung abgebenden Objekten, insbesondere Schiffen, gegen Flugkörper

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2829596A (en) * 1954-12-17 1958-04-08 Unexcelled Chemical Corp Tracking flares
US2986999A (en) * 1958-06-03 1961-06-06 Willy A Fiedler Externally mounted, jet-ignited tracking flare
US3070955A (en) * 1958-09-20 1963-01-01 Bofors Ab Rocket driven missile including luminous material
US3145657A (en) * 1962-10-09 1964-08-25 Aeronca Mfg Corp Missile assembly

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1473180A (de) * 1967-06-01
US3354645A (en) * 1966-01-03 1967-11-28 United Aircraft Corp Method and apparatus for producing a non-axial thrust vector
FR1601136A (en) * 1968-12-10 1970-08-10 Pyro technically charged tracer for guid- - ing projectiles and missiles

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2829596A (en) * 1954-12-17 1958-04-08 Unexcelled Chemical Corp Tracking flares
US2986999A (en) * 1958-06-03 1961-06-06 Willy A Fiedler Externally mounted, jet-ignited tracking flare
US3070955A (en) * 1958-09-20 1963-01-01 Bofors Ab Rocket driven missile including luminous material
US3145657A (en) * 1962-10-09 1964-08-25 Aeronca Mfg Corp Missile assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Webster s Third New International Dictionary 1965 page 1359 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0229457A1 (de) * 1985-10-31 1987-07-22 British Aerospace Public Limited Company Leuchtsatz für Rakete
US4721042A (en) * 1985-10-31 1988-01-26 British Aerospace Plc Missiles with annular flare
CN111596610A (zh) * 2020-05-19 2020-08-28 苏州诺达佳自动化技术有限公司 一种具有运行轨迹测控功能的工控机控制***

Also Published As

Publication number Publication date
JPS5012680B1 (de) 1975-05-13
DE2030722B2 (de) 1981-01-29
DE2030722A1 (de) 1971-03-25
GB1277999A (en) 1972-06-14
FR2050724A5 (de) 1971-04-02
DE2030722C3 (de) 1981-11-05

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