FR2568679A1 - ROCKET, PARTICULARLY PYROTECHNICAL ROCKET. - Google Patents

Abstract

THE INVENTION RELATES TO A PROJECTILE INCLUDING A CONTACT HEAD1 CONNECTED TO A CONTAINER3 WHICH CONTAINS A PYROTECHNIC, ANTIRADAR, FUMIGEN OR OTHER CHARGE AND AN IGNITION UNIT1 BURST33 TO IGNITE THIS CHARGE AND SPLIT IT AT A CERTAIN HEIGHT41. OF THE CONTAINER 3. THE ACTION OF UNIT33 IS TRIGGERED BY A DELAY IGNITION COMPOSITION31 CONNECTED TO A PROPULSIVE OR EJECTION CHARGE15 CONTAINED IN A CENTRAL CHAMBER13 OF HEAD1 AND LIT BY A BEAD17 WHICH IS CONNECTED BY FIRE LINES AND FROM CONTACT RINGS9 ON HEAD1 TO CORRESPONDING CONTACTS IN A LAUNCHING POT 55.

Description

The invention relates to a rocket or other projectile

  appealing to a contact head and an efficient charging container connected to the head and possibly closed by a cover, the external lateral wall of the contact head carrying contact rings connected by ignition lines to an ignition bead arranged inside the contact head in a propellant charge chamber in the form of a boot for receiving a propellant charge or ejection, the propellant charge chamber being closed in a substantially gas-tight manner relative to the exterior by a cover screwed to the bottom part of the contact head and by a sealing means at the bushings for the ignition lines, a delay ignition composition forming a connection between the propellant charge chamber and the effective loading container being

  arranged gas tight relative to the outside in the upper part

  contact head or in the bottom of the charging container e-

  effective, the delay ignition composition being in connection, either with

  a burst ignition unit located in the effective charging container

  cace and comprising an ignition / burst charge to ignite an effective charge, in particular a pyrotechnic charge, and to split the wall of the effective charge container, either with an expelling charge chamber containing an expelling charge intended to expel the effective charge, with cover tearing off at the head of the effective charge receptacle, the contact head and the effective charge receptacle

  being securely connected to each other by screws.

  We already know (see for example the patents of the Federal Republic of Germany 11 85 510 and 14 28 657) of the rockets which consist essentially of a container of effective load, filled with a given load, a smoke composition for example , and a contact head which is connected to this receptacle by a delayed ignition composition and in which is disposed a propellant charge with electric initiation-detonation for ejecting the entire projectile from a launching pot or to fire the delay ignition composition, unless this latter function is fulfilled by a

  manual tear-off igniter.

  Rockets are also already known which contain, as an effective charge, anti-radar strips or filaments or a charge with infrared radiation; as a rule, such rockets

  are fired from ships to shield them from enemy fire.

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  Rocket or anti-radar filament rockets are designed to form in a very short time, in less than five seconds for example, a large anti-radar cloud, of about 300 m2 for example, at a determined height above the surface from the sea, a height of 40 to 60 m for example. Such a cloud forms a reflection or radar echo surface and therefore constitutes a decoy for

  enemy target finders.

  Infrared rockets contain an effective charge which is ignited by an igniter after ejection and is suspended from a parachute. Such an infrared radiation charge irradiates a

  amount of thermal energy which is normally greater than that ir-

  struck off by the object to be protected. Devices sensitive to infrared radiation

  red, some missiles for example, are thus attracted by infrared radiation rockets and deflected from their objectives. Rockets or other bodies emitting infrared radiation suitable for this application must have burning times as long as possible, minimum burning times of 40 seconds for example, and have a falling or falling speed as low as possible, less of

2 meters per second for example.

  There are also already anti-rocket combinations

  radar and infrared radiation rockets, with which a charge emitting infrared radiation is obtained suspended in a cloud of strips or other anti-radiation elements. Such combinations of course produce both radar and machine interference

  sensitive to infrared radiation.

  These include the rockets mentioned above

  above in the German magazines "Wehrtechnik" 5, 1975, page 217, "Inter-

  Nationale Wehrrevue "2, 1976, pages 217 to 220 and" Internationale Wehrrevue "3, 1977, page 500. United States Patent No. 3,674,174 describes,

  for example, a special device for dispensing pyro-

  techniques, smoke pots or reflective materials for radar. However, the known rockets drawn from launch pots unfortunately have a whole series of disadvantages which strongly limit

their application.

  One of these drawbacks is that the effective load container for these rockets is usually a boot made of sheet metal,

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  therefore having a crimped longitudinal joint, as well as a crimped bottom.

  However, the lateral crimping excludes the precise adaptation of the reci-

  effective charge point at the launch pot; the same applies to the crimped bottom, in which a separate fixing plate must also be provided, by which the effective charging container must be able to be securely connected to the contact head and in which other elements must be able to be placed. necessary devices, such as organs of

  support or fixing for loads. The making of such a reci-

  pient is therefore not only expensive, it also has disadvantages

  serious for the intended application. The lack of precision and the varia-

  tion - resulting from the crimped side seal - in the adjustment of the container in the launching pot, in effect, always provide for a certain clearance or annular slot, which is never exactly the same, between the

  outer surface of the side wall of the container and the inner surface

  of the launching pot, so that, when firing such a rocket, when the propellant charge in the contact head chamber is ignited, combustion gas always escapes, the

  quantity is also uncontrollable due to dimensional variations

  nelles of said annular slot, gas which ejects the rocket from the launch pot. The annular gap which results from the design of these rockets therefore results in a loss of ejection energy. The fact that this annular slot is uncontrollable in its size has, however, a far more serious consequence: the firing height of the various rockets depends on the size of the annular slot and is therefore not exactly reproducible, even if all the other conditions are

exactly the same.

  Particular disadvantages, however, also result from the construction of the contact head of known rockets. For example, contact rings do not resist oxidation well enough

  and the electrical connections between the contact rings and the pearl

  The light inside the contact head and which is connected to the chamber containing the propellant charge does not allow a sufficiently tight isolation from the atmosphere. This frequently results in misfire by failure of the ignition mechanism, while the possible storage time of rockets as such or in

  the corresponding launch pots is already limited.

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  Another serious drawback of the known rocket is that its propellant charge chamber projects from the bottom part of the contact head and is moreover eccentric. This arrangement stems from the fact that conventional rockets generally contain in addition a tear-off igniter for manual ignition in the bottom part of the contact head, an igniter which also projects from this bottom. If it is necessary to provide the two elements, the chamber and the igniter, they can only be arranged eccentrically. On the central zone left free of the bottom part of such a contact head must be able to apply the spacer provided in the bottom of the launching pot and having to ensure the precise relative arrangement of the contact rings and the blades contact of the launch pot. On known devices, this function can be fulfilled neither by the projecting load chamber nor by the tear-off igniter. The eccentric arrangement of the propellant charge chamber in the contact head also results in

  the disadvantage that the combustion gases cannot attack immediately

  the center of the launch pot but only the regions located next to the center, which leads to spins and, consequently, to different ranges of the rockets. Even if the tear-off igniter were completely eliminated on the known devices, the charging chamber could not be placed in the center of the contact head, because

  of the particular construction used so far for these rooms.

  The eccentric position of the load chamber has the additional disadvantage

  It is necessary to have storytelling constructions in the efficient charging container in order to be able to mount devices in its center which must be connected to the charging chamber in the contact head.

  via the delay ignition composition.

  The completely different conformation of known rockets, in particular with regard to the effective charging receptacle and the contact head, necessarily means that these rockets are not suitable for firing and spreading thin pyrotechnic sheets

  combustibles (flares) or antiradar filaments (fine metallic wires).

  For this, it is necessary, until now, to use relatively expensive constructions. Even these, however, do not allow

  fully satisfactory and effective formation of the desired decoy clouds.

  All known simple rockets also have the disadvantage

  due to the shortcomings described above in the construction

  tion, that they do not sufficiently resist the influence of

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  the sea and harsher atmospheric influences from the maritime environment. The disadvantages which have just been listed limit

  very strongly the possibilities of application of known rockets; linen-

  vention therefore aims to create a new rocket that does

not these drawbacks.

  According to the invention, a rocket of the type indicated at the start

  is essentially characterized in that the charging chamber propels

  sive is arranged in the middle of the contact head and is provided with a screwed cover, closing in a gas-tight manner and having a thread on a solid edge, which constitutes at the same time, at least in its part

  central, a massive support intended to cooperate with a spacer -

  provided in a launching pot, the cover portions located between the edge and the solid support forming rupture zones in the form of windows

for the exhaust gas outlet.

  The contact head and its screwed cover are advantageous.

  molded parts, which can be manufactured in the best way by injection molding of plastics suitable for this purpose,

of polystyrene for example.

  The support formed on the screwed cover of the propellant charge chamber in the contact head is preferably produced in the form of a rib extending, diametrically for example, from one point of the edge of the cover to another. The rib thus formed constitutes a solid support for the spacing piece of the launching pot and, at the same time, a gripping element for screwing the cover by hand in the charging chamber arranged in the middle of the bottom of the contact head. . Around the solid edge of the screwed cover is preferably arranged an annular seal ensuring a gas tight closure of the chamber

propellant charge.

  In addition, at least the part adjacent to the contact rings of the firing lines preferably consists of pins

  of connection welded on the inner side of the contact rings and

  pouring at least the outer side wall of the contact head to project into the interior volume of the contact head between

  this outer wall and the side wall of the charging chamber pro-

  pulsating. At least a part of the connection pins and the parts of the contact rings directed towards the external wall of the contact head

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  are preferably embedded by casting in the outer side wall of the contact head. The part of the external wall of the contact head carrying the connection pins is preferably made, at least in part, in the internal volume comprised between the external lateral wall of the contact head and the lateral wall of the charging chamber , like a rib. The surface of the connection pins is advantageously knurled and the pins themselves are preferably profiled, the best still being a square profile which ensures a particularly solid seat and a particularly large seal of the connection pins in the material of the head. contact. The use of contact rings on which connection pins are already welded during injection molding of the base body of the contact head provides the same advantage, that is to say an adequate and tight fit of these components. in the contact head. It is advantageous that

  the connection pins extend only into the internal volume

  between the outer side wall of the contact head and the side wall of the load chamber and that, from there, they are connected by connecting wires passing through bushings in the side wall of the load chamber propellant to the ignition pearl located in this chamber, the latter being insulated in a gas-tight manner with respect to said interior volume of the contact head by a sealing means combined with the bushings. The rib containing the connection pins in the internal volume between the external side wall of the contact head and the side wall of the charging chamber is therefore produced so as to leave free, in this internal volume, at least one side of the connection pins, on which the corresponding connecting wires can be soldered leading to the ignition bead located in the charging chamber. The external surface of the contact head therefore has no welding or connection points exposed to attack by the surrounding atmosphere. The pins

  connection rings and contact rings integral with them are preferably

  brass rence. To protect them against corrosion, these parts are

preferably golden in addition.

  In the upper part of the contact head is arranged, in the middle, a delay ignition composition which establishes the connection between the propellant charge chamber in the bottom part of the contact head and the bottom of the effective charge container. or more

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  specifically, an ignition / burst unit or an expulsion charge chamber disposed in this bottom. The delay ignition composition is advantageously screwed into the upper part of the contact head; for this purpose, it is preferable that the contact head additionally carries a threaded socket which is disposed in the center of the upper part of the contact head. Around the propellant charge chamber, the contact head also has at least two holes for the screws used for fixing the contact head to the bottom of the effective charge container, these holes being advantageously arranged so that the heads fixing screws are completely embedded and can be covered by flush caps with the bottom of the contact head. These caps can be conventional pieces of polyethylene. The best solution consists in forming the holes for the reception of the screws in the contact head during the molding of this one. The upper part of the

  side wall of the contact head is also pre-shaped

  ference so as to allow, in combination with the bottom of the effective loading container and a seal arranged between them, a separation

  practically sealed between these two elements. The best is that this par-

  upper tie is grooved for this purpose. It is preferable to provide connecting ribs between the side wall of the load chamber arranged in the middle of the contact head and the outer side wall

  of the contact head, for mutual stabilization.

  In a particularly preferred embodiment of the rocket according to the invention, the seal placed between the contact head and the effective charging container assumes the shape of a ring

  sealing protruding radially, the outside diameter of which

  corresponds at least to the inside diameter of the launch pot. Such a sealing ring ensures on the one hand the sealed closure of the portion of the launching pot containing the contact head and on the other hand prevents that the combustion gases formed during the ignition of the propellant charge contained in the contact head does not escape through an annular gap - even minimal - between the side wall of the effective load container and the inner surface of the launch pot. The flexibility of such a sealing ring also makes it possible to compensate for dimensional tolerances

  between the launch pot and this container. This arrangement according to the

  vention ensures a confinement which is always the same for the pro-

  pulsating and, therefore, reproducible firing ranges. The seal ring

  it is preferably made of oil-resistant nitrile rubber.

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  It is also advantageous to have a fixing plate in the bottom of the effective charging container, by which the container and the contact head can be securely fixed to each other by means of the screws and which can, if necessary if necessary, by an appropriate conformation, to fulfill still other functions necessary for such rockets. This is how it is possible, for example, to have ignition / burst units or expulsion charge chambers on this

  fixing plate. However, in a particular embodiment-

  Preferably, the bottom of the efficient load container is reinforced and used as a fixing plate, so that a separate fixing plate can be dispensed with. When using an efficient loading container comprising a separate fixing plate at the bottom, it is advantageous to place an additional seal between this plate and the bottom of the container itself, an annular seal by

  example, which provides a gas-tight connection between the two elements.

  The reinforced execution of the bottom of the container and its use as a fixing plate are made possible by the manufacture of this container, according to a particularly preferred embodiment of the invention, in the form of a stamped aluminum boot of small thickness. wall, since the realization of a thick bottom poses no difficulty

  if the container is produced by stamping. The use of alu-

  minimum for the manufacture of such a deep-drawn container allows the removal of

  sion of any seal on the container, which is linked to advantages par-

  particular, as already apparent from the above. The wall thickness of the container is adapted each time to the envisaged application. The head

  container is normally closed by a lid, which is pre-

  also made of aluminum and attached to the head of the boot

  aluminum by crimping. Depending on the application of the rocket, the thick-

  The wall of the aluminum boot is chosen so that its side wall, after the ignition of a load in the container, is opened without tearing off the crimped cover, so that the wall of the container is fractionated as desired if the effective charge consists of thin pyrotechnic sheets (f lares) for example, in which case the effective charge container contains in the middle an ignition / burst unit provided for this purpose and comprising a socket filled with an ignition / burst charge, either remains intact, having sufficient resistance when the charge contained in the container is ignited, in which case only the cover provided at the head of the aluminum boot is

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  torn off, with the consequence that the effective charge is emptied by the head

  of the container. In the latter case, a room containing a load of ex-

  a suitable outlet is arranged on the bottom of the effective loading container

  cace, this charge of expulsion ensuring that the effective charge, preferably consisting of filaments or anti-radiation strips, is expelled by

  the head of the container with tearing off the cover of the head thereof.

  However, appropriate measures make it possible to use the same aluminum can for the two applications mentioned above, which can

  the wall thickness is for example 0.25 millimeter. It is therefore pos-

  always use the same aluminum box, ensuring the confin

definite necessary.

  Depending on the envisaged application of the rocket which is the subject of the invention, two embodiments of

  preferred invention, defined again below.

  In the first embodiment, the effective charge container contains an ignition / burst unit comprising an ignition / burst charge to ignite the effective charge contained in the container and / or to split the wall of this container, the

  ignition / burst charge being in contact, by the ignition composition

  late mage, with the propellant charge contained in the

  load of the contact head and being switched on by it via the

  middle of ignition & delay composition. The ignition / flash unit

  preferably consists of a socket filled with an ignition / burst charge which is placed in the middle of the fixing plate or of the reinforced bottom serving as a fixing plate for the charging container

  effective. This ignition / burst unit preferably extends practically

  only up to the lid at the head of this container. The socket of the ignition / burst unit is preferably also made of aluminum, as the

  container, its wall thickness being for example 0.25 millimeter.

  The use of aluminum as the material for the sleeve of the aluminum unit

  lighting / bursting, the effective charging container and the lid of the latter brings, in addition to the advantage of the ease of manufacture of these elements, the advantage that said elements are provided at the same time with corrosion resistance and compatibility desired with most pyrotechnic compositions, so that special corrosion protection can be dispensed with. In addition, the aluminum used as the constituent material of said elements can burn with the charges o10- 2568679 they contain. Another advantage is that such deep-drawn sockets, due to the absence of seals over their entire extent, have the same resistance everywhere, which allows very good reproducibility of the operation of rockets. Finally, these sockets can be easily manufactured with constant internal and external diameters.

  The socket - filled with the ignition / burst charge -

  of the ignition / burst unit is of course adjusted so as to ensure a tight seal in the bottom of the effective charging container, or in

  the fixing plate, and connected in a similar manner to the composition of

  delay lighting. This is preferably obtained by providing a crimped edge on the open end - in conjunction with the delayed ignition composition - of the socket of the ignition / burst unit, by which the socket is screwed at the bottom and in a gas-tight manner in the effective loading container and in the fixing plate, or in the reinforced bottom serving as fixing plate for this container. The open end of the sleeve is advantageously connected by crimping to a cover disc and screwed in a gas-tight manner from below, by this disc and by means of a perforated screw combined with an annular seal, in the effective load container and the mounting plate, or the reinforced bottom of the container. The desired gas tight connection is obtained by an annular seal which, when assembled by screwing, is pressed against the three elements which are the fixing plate or

  the reinforced bottom of the container, the cover disc and the sleeve.

  The hole formed in the cover disc is advantageously closed in a gas-tight manner by a glued spangle, preferably a tin spangle.

  A rocket with an effective load container

  internally read as described above is particularly suitable for filling with an effective charge consisting of thin combustible sheets or else of a single piece molded by compression of reactive material, in particular of a piece obtained by molding pellets of a

  smoke composition based on red phosphorus and a granule of a compound

  smoke emission based on red phosphorus.

  According to a particularly preferred embodiment,

  a combination of thin combus sheets is used as an effective filler

  and a single molded part, so that a specific part of the effective load container is filled with combustible sheets and

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  the rest of this container is filled with a single molded part, preferably

of the type indicated above.

  The thin combustible or pyrotechnic sheets used to fill part or all of the effective loading container are preferably sheets in the form of a sector of a circle, in particular of a sector of approximately 120. Especially the use of

  this latter form ensures, after the sheets have been lit and ejected

  tion of the container, a cloud of material with a very uniform density and a low and steady rate of descent. Such sheets can also be loaded cleanly into cylindrical box-shaped containers. The sector-shaped sheets, only because of their particular shape, are arranged radially around the ignition / burst unit in the effective charging container. Each sheet comprises a layer of suitable support material, on one side of which at least, but preferably both, is applied a

  a slowly burning combustible layer made of an incendiary paste.

  The support material used to make the thin combustible sheets may be paper, for example, a metallic foil, such as aluminum foil, a plastic sheet or film, or a plastic sheet or film bearing a metallic coating. The weight per unit area of these support materials can reach approximately 60 g / m2. The use of plain paper as a support material for making combustible sheets is currently preferred since this material can easily be coated with the combustible layer of incendiary pulp and of the other materials which may be necessary, can be treated well and is finally

  cheap too. Paper 30 to 35 g / m2 is preferred.

  The combustible layer of incendiary paste applied on the thin sheets, that is to say on the support material itself, must, as a rule, be able to be ignited quite easily, which is produced by the ignition unit. / burst placed in the center of the effective charging container, but it must not burn too quickly, in order to emit the desired infrared radiation for a significant period. As coating materials to be applied to thin sheets of carrier material as a combustible layer. incendiary dough are suitable for almost all flammable and combustible doughs that meet

on these conditions.

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  The Applicant has found that, above all, red phosphorus

  and in particular boron are suitable for the formation of combustion layers-

  tarts in incendiary paste. However, since phosphorus and boron behave differently in terms of their flammability and the way they burn, due to their differences in activity, phosphorus being known to be more active than boron, these two materials require different measures in their use for the formation of the combustible layer, measures which

are shown below.

  Sheets bearing a phosphorous-based combustible layer The combustible layer of incendiary pulp of these sheets

  preferably consists of red phosphorus and a plastic

  with a weight ratio between 70:30 and 85:15. Due to the activity

  relatively high speed of such a combustible layer, to prevent its combustion from progressing too quickly on the surface of the sheet, there is

  instead of partially covering it with at least a moderate surface layer

  ratrix or passivation. This layer is also best composed of red phosphorus and a plastic, but this time in a weight ratio of between 5:95 and 30:70. The most favorable plastic material is essentially polyvinyl chloride in both cases

  The combustible layer and the moderating layer therefore differ

  by the mere proportions of their constituents.

  The phosphorous-based incendiary paste used to form the combustible coating (layer) is generally made of a combination of a plastic paste, preferably a paste of polyvinyl chloride convertible into a paste, a plasticizer for polyvinyl chloride, preferably dioctyl phthalate and / or diphenyl and octyl phosphate, of a suitable dispersant, preferably of

  the test essence of a boiling range from 147 to 180 C, and of the combustion-

  target itself, preferably red phosphorus and in particular boron. It is also possible to use, in addition, light metal powder, such as powder of magnesium, aluminum or a light metal alloy. The combustibility of such incendiary pastes can optionally be further improved by the addition of oxidants, such as inorganic nitrates or metal oxides or also easily flammable metal powders, such as manganese, zirconium, cerium or other powder. boron alloy. In order to obtain an incandescent combustion which progresses slowly, which is desirable, it is however necessary to

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  determined relationship between the plastic dough, the combustible

  specifically and the oxidant or other substances. Masses which can be spread out and which contain 15 to 30% of plastic paste, 60 to

  % of fuel proper and 0 to 40% of oxidants are preferred.

  The major part of a coating mass suitable for producing the combustible layer of incendiary paste on the sheets is therefore formed

by the fuel itself.

  For phosphorous-based pyrotechnic sheets, the coating mass used for the moderating layer may, as already indicated, have the same constituents as the coating mass for the formation of the combustible layer, but it contains much less fuel proper , the latter being preferably red phosphorus again. For the moderating layer, it is therefore also preferable to use a coating mass, the plastic material of which is essentially polyvinyl chloride and the fuel proper is based on red phosphorus. The moderating layer is therefore preferably composed of red phosphorus and a plastic, in particular polyvinyl chloride, their weight ratio being

  preferably between 5:95 and 30:70.

  A preferred coating mass for forming the

  combustible layer of incendiary paste based on red phosphorus, in particular

  base on paper as support material, can be prepared, by

example, as shown below.

  25 parts of a plasticizer for polyvinyl chloride a based on dioctyl phthalate and 25 parts of a plasticizer for polyvinyl chloride based on diphenyl phosphate and octyl in a suitable container and the whole is mixed with using an intense action stirrer for approximately 0.25 h with 100 parts of a polyvinyl chloride convertible into paste, the heat of reaction developed during

  the agitation being dissipated by adequate cooling.

  Separately from this preparation of the base paste of polyvinyl chloride, 12 parts of test essence having a boiling range of 147 to 180 ° C. are introduced into another container and they are mixed, portion by portion, continuing mix carefully, with 37.5 parts of red phosphorus. It is essential to ensure that it does not

  does not form lumps or lumps of red wet phosphorus.

14 zt6f

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  The base paste of poly- chloride is then mixed.

  vinyl and phosphorus slurry, the mixing ratio used for this being a function of the desired concentration of red phosphorus in

the finished dough.

  The coating mass thus obtained is then applied - for the formation of the combustible layer of incendiary pulp on the thin sheets - on strips of paper of 30 to 35 g / m2 using a scraper and then the gel is allowed to gel. layer formed at a maximum temperature of C. To obtain material coated on both sides with a combustible layer, pass the coated paper on one side again

  by the scraper for the application of the second layer.

  A moderating layer can then be applied in an analogous manner to the material coated on one side or on both sides of a

combustible layer.

  The indications given above apply to

parts by weight.

  So that the thin sheets, with the combustion layer-

  relatively active target of incendiary phosphorus-based paste and the moderating layer applied over the combustible layer to limit

  the propagation speed of the combustion, let it ignite corrected

  quickly and as desired, it is useful if not necessary for the sheets in a circular sector, carrying a combustible layer and a

  moderating layer on one side or on both sides, have a strip of

  light without moderating layer on their curved inner edge adjacent to the ignition / burst unit or on one of their straight edges. It is however preferable that each sheet in a circle sector has an ignition strip devoid of a moderating layer at the same time on its curved inner edge, delimiting the recess in a sector of a circle for the reception of the ignition / burst unit. , and on at least one of its

straight edges.

  The ignition strips thus formed ensure that the sheets, when ejected from the effective charge container, can

  be switched on fairly quickly and simply by the ignition / flash unit

  The sheets then burn more slowly, as desired, due to the moderating layer - or any other layer less active than the ignition strips - covering most of the surface of the sheets.

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  The ready-to-use sheets, that is to say the sheets provided with a combustible layer of incendiary paste and, optionally, a moderating layer, advantageously have a weight per unit area which does not exceed 400 g / m2 approx. This weight is preferably between 135 and 400 g / m2 in the case of sheets made of paper such as

  support material. For sheets using aluminum as a material

  support line, the weight per unit area in the ready-to-use state is preferably also between 135 and 400 g / m 2. Ready-to-use sheets comprising a plastic material whether or not coated with metal

  as a support material - for example in the form of poly-

  imide, possibly metallized by spraying - preferably weigh

from 130 to 200 g / m2.

  Sheets carrying a combustible layer based on boron The combustible layer of incendiary paste of these sheets preferably comprises boron and / or a boron alloy containing at least 90% by weight of boron and of a plastic material, according to a report

  which is also between 70:30 and 85:15. The plas-

  The preferred tick here is also essentially polyvinyl chloride.

  In addition to the constituents which have just been mentioned, the incendiary paste may also contain additives, for example up to 40% by weight of

  oxidizer and / or active metal powder and / or metal alloy powder-

  active list. Lead dioxide is particularly suitable as an oxidizer,

  while the powders of manganese, zirconium, cerium and / or al-

  boron bonding comes first as metal powder

  active and / or active metal alloy powder.

  However, since boron-based combustible layers are normally less active than phosphorus-based layers, a moderating layer is generally not required on the sheets as boron-based combustible layers. However, unlike a phosphorus-based combustible layer, those based on boron are not

  not ignite without special measures by an ignition / burst unit.

  For this reason, the sheets bearing a boron-based combustible layer must also be provided with ignition strips but which cannot be formed from the combustible layer proper - as is the case.

  case with sheets whose combustible layer is based on phosphorus -

  that is to say the boron-based layer, the ignition strips in front in

* this case be formed by a special ignition layer, applied by-

  above the boron-based layer at the places provided for the light strips

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  mage, which is easily ignited and continues to burn until it has transmitted its ignition energy to the underlying boron-based combustible layer. Any mass which satisfies the conditions described above is therefore suitable for the formation of ignition strips on sheets in a sector of a circle carrying a combustible layer of incendiary bud formed from boron and / or boron alloys and a material plastic. It is however preferable that these ignition strips are formed with the same incendiary paste as that used for the

  combustible layers based on phosphorus, so by application, by-

  above the boron-based combustible layer, on the edges intended to serve as ignition strips for sector-shaped sheets, of an incendiary paste composed of red phosphorus and of a plastic material, according to

  a weight ratio between 70:30 and 85:15.

  The coating pastes necessary for the formation of the boron-based layers on the sheets can be produced as already

  described for buddies based on phosphorus.

  The support materials used to make the sheets bearing a boron-based combustible layer and the other characteristics, such as the weights per unit area of the sheets ready for use, correspond to what has been indicated in this regard for

  sheets having a phosphorus-based combustible layer.

  Apart from filling according to the invention with the interior of the first embodiment mentioned above of the effective charging container according to the invention with thin pyrotechnic sheets

  as an effective charge, the latter can also be formed of a

  conch known filler, of a conventional smoke composition for example, either in powder form or in a more or less form

  compacted. These smoke-producing compositions also include

  so-called "pyrotechnic" smoke-producing areas, to which also smoke-containing compositions based on red phosphorus. Reference is made in particular to such compositions in "Technik und Versorgung" 1970, pages 63 to 68, in particular pages 66 and 67. The use of agglomerated (trapezoidal) bodies of smoke and flame-producing masses is already mentioned in

German patent 19 13 790.

  The conventional forms under which the composi-

  However, the disadvantage is that they burn either too quickly, so that the desired curtain of smoke or fog does not stay long, or too slowly, so

17 2568679

  that the curtain does not have the required density, or that they form a point focus, without or with insufficient dispersion, with the result that no dense curtain is formed at all or that its formation

lasts too long.

  Consequently, the invention also aims to eliminate the drawbacks specific to known smoke compositions used in rockets and to create a smoke rocket which, in the space of a few seconds after its launch, forms a dense smoke curtain which is

  fed from the ground by a multitude of smoke particles.

  According to the invention, this result is obtained, in the case of the first embodiment mentioned above of the effective load container of the rocket, by the fact that the effective load is a single molded part, filling the interior of the container with partially or fully effective filler produced by compression of pellets of a red phosphorus smoke composition and a

  granule of a smoke composition based on red phosphorus, the

  sion being carried out so that the integrity of the pellets is sensi-

  well preserved and the granule forms a porous structure which

  closes the lozenges individually.

  Such a molded part preferably fills all the information.

  inside of the efficient loading container. Its shape therefore corresponds practi-

  only to that of the interior volume defined by this container, including its cover and its bottom, with only a recess in the center for the reception of the ignition / bursting unit in the form of a bar, this

  recess being formed during the molding of the part.

  Another embodiment which may be advantageous

  in certain circumstances such a rocket includes an effective charge

  cace which consists of a molded part filling only part of the interior of the effective loading container and thin sheets of the type described in the foregoing which fill the remaining part of the interior of this container. Such a rocket makes it possible to obtain, for example, the combined effects of a molded part based on phosphorus and pyrotechnic sheets.

  The pellets contained in the molded part according to the

  vention preferably have a diameter of about 11 mm, a thickness of 6 mm and a weight of about 1 g. The tablets are usually composed of red phosphorus, copper oxide powder, magnesium powder and a

18 2568679

  binder. The granule contained in the molded part will also usually consist of red phosphorus, copper oxide powder, magnesium powder and a binder. The pellets contained in the molded part normally have a higher content of binder than the granule of the part, since the granule must in this case be more plastic than the

  pellets, to facilitate its compression molding with them.

  The pellets contained in the molded part are preferably composed of approximately 65 to 75% by weight of red phosphorus, approximately 5 to 20% by weight of copper oxide powder, approximately 3 to 5%

  by weight of magnesium powder and about 3 to 10% by weight of binder.

  The granule contained in the molded part preferably consists of approximately 60 to 70% by weight of red phosphorus, approximately 5 to% by weight of copper oxide powder, approximately 3 to 8% by weight of magnesium powder and approximately 5 15% by weight of binder. The best is

  to use an elastomer as a binder in both cases.

  The weight ratio between the pellets and the granule in the molded part used as an effective filler is preferably

between 8: 2 and 7: 3.

  The essential and predominant constituent of the smoke-producing compositions used to produce the pellets and the granule is the

  red phosphorus. When red phosphorus burns,

  times phosphoric acid, a small part of which is already precipitated as condensate on the surface of phosphorus which has not yet burned. This precipitation limits the access of oxygen from the air and can lead to the extinction of the smoke composition. It is therefore necessary to add sufficient quantities of oxidizers to the red phosphorus, most often in the form of metal oxides or metal powders, entering into an exothermic reaction with the red phosphorus, so that the desired reaction is maintained. Copper oxide, manganese dioxide or nitrates are preferably used as oxidizers and the powder of

  magnesium is preferably used as a metallic powder. The ingredients

  smoke-producing positions usable within the framework of the invention can consequently consist essentially of phosphorus and magnesium powder and / or copper oxide only, a certain content of binder

being of course essential.

  As binder, an elastomer is used, both during the production of the pellets and for that of the granule.

chlorinated rubber base.

19 25 686'79

  The binder content of the smoke composition used to produce the pellet is generally greater than the content

  by binding smoke composition used to produce the pellets.

  It is essential that the binder ensures a high solidity and at the same time a good elasticity of the pellets, so that they are deformable up to a certain limit, without breaking, when they are

molded with the granulate.

  In the second embodiment - briefly man-

  mentioned in the foregoing and reported as being particularly pre-

  fairy - for a rocket from the invention, an expelling charge chamber

  sion is placed in or on the fixing plate located at the bottom of the effective load container, or in or on the reinforced bottom of this container, the load contained in this chamber being intended to

  expel an effective load contained in said container with tear off

  ment of the cover provided at the head of the container, this expulsion charge being of course also in connection with the delayed ignition composition. By suitable construction measures, it is ensured, in this embodiment, that the expelling charge chamber is practically not in direct contact with the adjacent parts of the wall of the effective charging container, so that the force produced upon ignition of the expelling charge acts essentially as a push towards the lid of the effective load container, so that the effective load, contained in the container and disposed

  on an appropriate plate, either expelled with this plate from the outside

  head mate at the front of the efficient load container.

  For this purpose, the expulsion charge chamber is preferably arranged in the upper side of the fixing plate, or of the reinforced bottom serving as a fixing plate for the effective load container, so that it is open from the side directed towards inside this container. The upper side of the fixing plate or the reinforced bottom can therefore be produced simply with a recess, in the manner of a flat piston. The edge of the piston thus formed ensures that the forces produced

  after ignition of the expulsion charge cannot attack directly

  the wall of the efficient load container.

  In this second embodiment of a rocket according to the invention, the effective load is placed on an effective load support, formed of at least one plate, which is placed above the

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  expulsion charge chamber and is guided in the efficient charging container in such a way that it can practically not be crooked and blocked. The plate and the fixing plate or the reinforced bottom of the effective load container are preferably shaped so that the expulsion charge chamber, as already indicated, does not have direct contact with the surrounding wall of the container. Guiding without risk of jamming of the effective load support, therefore also of the plate, in the efficient load container and the arrangement of

  different elements avoiding direct contact with the ex-charge chamber

  drive with the surrounding wall of the container can be obtained by different measures or by a combination of such measures. The plate is preferably provided for this purpose, at its outer edge, with at least one annular seal applied against the wall of the effective load container and ensuring a gas-tight closure, the plate being in particular provided of two of these sealing rings. These sealing rings can also be made of nitrile rubber. The effective load plate or support therefore preferably affects the shape of a flat piston open on the bottom side of the effective load container, the outer edge at the bottom of the plate preferably fitting into the outer edge at the top fixing plate or reinforced bottom serving

  effective load container mounting plate. Thanks to this combination

  Due to measurements, a suitable isolation of the expulsion charge chamber is obtained with respect to the surrounding wall of the effective charge container. The sealing rings provided in the outer edge of the plate ensure a gas-tight separation between the load chamber and the space containing the effective load of the container, allow guiding without risk of jamming of the plate in the container effective load and also compensate for dimensional tolerances between the plate and the container wall. Without these measures, the effective load container could burst laterally after

  ignition of the charge of expulsion, which would prevent the expulsion cor-

  desired recte of the effective load by the head end of the container.

  In addition to the trim, the effective load carrier of the preferred rocket embodiment discussed here

  includes a central column placed on the plate and extending practically

  only up to the lid of the efficient load container, as well as a cover plate adapted to the internal diameter of the load container

21 2568679

  efficient and located at the upper end of the central column.

  The cover plate of the effective load support preferably has, in the region of its outer edge, a peripheral ring of orifices which, during the flight of this support with its load, provides the required stabilization and at the same time produces the effect that the effective load is, so to speak, blown out of the support, which ensures

its proper distribution.

  In the second preferred embodiment of a rocket according to the invention, the effective load preferably consists of

  antiradar filaments arranged parallel to the longitudinal axis of the

  effective load pient on the effective load support. The best

  solution is to place several bundles of filaments together

  above the others on the effective load support, the different packages

  being separated from each other by perpendicular intermediate discs

  to the central axis of the efficient load container and alternating with

  the bundles of filaments in the stack of bundles and inter-discs

  calaires. Separation between the packets can also be ensured by disc segments which each time form a complete disc, instead of the one-piece spacer discs. These discs can be

  of cardboard, for example, or of another suitable material.

  The different bundles of filaments are in the form of circular disks whose outside diameter corresponds to the inside diameter of the effective loading container. In the center of these packages is placed a cardboard or aluminum sleeve, so that all of the load-forming packages can easily and conveniently be threaded onto the central column of the effective load support. The bundles of filaments will usually be wrapped in film, which will be cut in at least three places uniformly distributed around the periphery when placing the different bundles in the effective loading container, to ensure that this envelope easily detaches when the filaments are expelled.

  A rocket according to the invention operates as indicated below. The ignition of the propellant or ejection charge contained in the contact head via the contact rings and the ignition bead causes the rocket to be ejected from the launching pot and, at the same time, ignition of the delayed ignition composition. To the

22 2568679

  At the end of the required delay time, the delay ignition composition ignites the ignition / burst charge or the expulsion charge contained in the effective charge container. This results in either the bursting of the effective charge container by the ignition / burst charge and at the same time the ignition of the effective charge, or the expulsion, by the head end of the container, of the effective charge. contained in this

  container on a support, tearing off the lid of said container.

  In both cases, a suitable and uniform distribution of

  the effective load on the desired extent and at the desired height.

  Other characteristics and advantages of the invention

  will emerge more clearly from the description which follows from several

  nonlimiting exemplary embodiments, as well as appended drawings in which: - Figure 1 is a vertical axial section of a rocket

  according to the invention, without special conformation of the interior volume of the container

  effective load monitor; - Figure 2 is a vertical axial section of a rocket according to the invention like that of Figure 1, the section being however taken at 90 relative to that of Figure 1 and the interior volume of the effective load container containing thin sheets in a circle sector constituting the effective charge, as well as an ignition / burst unit .; - Figure 3 is a plan view of a sheet in a circle sector with an angle of 120 corresponding to those used in the rocket of Figure 2; - Figure 4 is a section taken along a rope of the sheet of Figure 3; - Figure 5 is a vertical axial section of a rocket according to the invention, the effective load container of which contains thin sheets in a circle sector plus a part

  molded formed of pellets and a granule based on a smoky composition

  conventional gene, the sheets and the molding together forming the effective charge of the rocket; and - Figure 6 is a vertical axial section of a rocket according to the invention corresponding to that of Figure 1, the section being however taken at an angle of 90 relative to the section of Figure 1 and the interior volume of the efficient load container being further configured to receive an expulsion charge chamber and a

23 2568679

  effective load support formed by a plate, a central column and a cover plate provided with orifices, support in which are

  arranged, between intermediate discs, bundles of anti-filaments

  radar. As is already apparent from this enumeration of the figures, the constitution of the rocket according to Figures 1, 2, 5 and 6 is always the same as regards its essential parts, namely the container of

  effective charge and the contact head which is connected to it with inter-

  position of an elastic sealing ring.

  FIG. 1 represents a contact head 1 having a charging chamber 13 which contains, in the ready-to-use state, a charge

  propellant or ejection 15, in which is embedded an ignition bead 17.

  The charging chamber 13 is closed in the bottom part 19 of the contact head 1 by a screwed cover 21. The edge 47 of the cover 21 has for this purpose a thread 49. The bottom of the cover 21 has rupture zones in in the form of windows 57. The cover 21 also has a

  roughly diametrical rib which forms a support 51 for a piece of space

  cement 53 of a launch pot 55. On the edge 47 of the cover 21 is arranged an annular seal 105 for this cover. In the upper part 27 of the contact head 1 is placed a delay ignition composition 31 which forms a connection between the charging chamber 13

  and the interior of an efficient loading container 3. The composition of

  delay mage 31 is screwed by a threaded sleeve 107 in the upper part 27 of the contact head 1. In the side wall 61 of the charging chamber 13 are provided bushings 23 which connect the ignition bead 17 by wires link 67 - sealed in the bushings by a sealing means 25 - and by connection pins 63 arranged in a rib 5, located in an interior volume 59 between the side wall 61 of the load chamber 13 and a wall lateral lateral 7 of the contact head 1, to contact rings 9 arranged in the external lateral wall 7 of the contact head 1. The connection pins 63 therefore form with the connecting wires 67 firing lines 11 between the contact rings 9 and the ignition bead 17. The contact head 1

  and the screwed cover 21 are injection molded parts made of poly-

  styrene, their various parts mentioned above having come from molding.

24 2568679

  Between the upper part 27 and the bottom 29 of the container 3 is disposed an elastic sealing ring 69 (which is made of nitrile rubber in the example shown). The ring 69 seals between the rocket and the launch pot 55 in which it is arranged. In the bottom 29 of the container 3 is also arranged a fixing plate (not shown in FIG. 1), unless this bottom 29 of the container 3 is reinforced and itself serves as a fixing plate (which n 'is not shown further). The contact head 1 also has holes (not shown) for screws (not shown) used for the

  solid fixing of the contact head 1 on the bottom 29 of the container 3.

  These holes are closed on the bottom part 19 of the contact head 1 by suitable plastic caps (not shown). The elements just mentioned provide the proper connection

  between contact head 1 and container 3.

  On the head 43 of the container 3 is fixed, by appropriate crimping, a cover 5. The rocket and the launching pot 55 are further covered with a common cap 110 which ensures the watertight arrangement

  of the rocket in the launch pot. This hat is of conventional type.

  The effective loading container 3 and the cover 5 of this container, as well as the fixing plate not shown or including the reinforced bottom serving as the fixing plate for this container,

  are made of the preferred material according to the invention, that is to say of aluminum.

  The wall thickness of the container 3 and the thickness of the cover 5 are

  both about 0.25 millimeters.

  Figure 2 shows the same elements as Figure 1, having the same references, but, because it is taken at an angle of 90 relative to the section of Figure 1, it reveals additional elements; in addition, the rocket shown in Figure 2 contains inside the container 3 elements not shown or

  absent in the example in Figure 1.

  FIG. 2 shows that the contact head 1 contains screws 45, the receiving holes of which are closed by caps 111 which are flush with the bottom part 19 of the contact head 1. The screws 45 are screwed in a fixing plate 71 arranged in the bottom 29 of the container 3 and thus ensure the solid fixing of the container 3 on the contact head 1. The fixing plate 71 is arranged in a sealed manner

  in the bottom 29 of the container 3 by an O-ring 113.

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  Inside the effective charge container 3 is an ignition / burst unit 33 which is mounted in the mounting plate 71. The unit 33 includes a socket 75 which contains an ignition / burst charge 35 and has , at its end being inside the fixing plate 71, an edge 77 which is folded inwards and in which a covering disc 79 is maintained, by means of which the sleeve 75 is fixed in sealed manner, using a hole screw 81 and an annular seal 115, in the fixing plate 71 on the bottom 29 of the container 3. The orifice in the covering disc 79 is closed by a glued glitter 119, preferably a tin flake, which therefore isolates the ignition / burst unit 33 from the delay ignition composition 31. The interior of the container 3 contains, between the socket 75 of the ignition / burst unit 33 and the side wall 41 of the container 3, an effective charge 73 which is constituted e in this example of pyrotechnic sheets 83 in the form of a sector of a circle with an angle of 120. The sheets. 83 are arranged inside the container 3, around the sleeve 75 therefore, in superimposed layers. The socket 75 of the ignition / burst unit 33 of the embodiment shown in Figure 2, the container 3 and its cover 3, as well as its fixing plate 71 are made of the preferred material for these elements, c is aluminum. Socket 75,

  the container 3 and the cover 5 each have a wall thickness of

  about 0.25 millimeter. Figure 2 therefore shows one of the preferred embodiments of the rocket according to the invention, namely a rocket whose effective charge consists of thin pyrotechnic sheets, especially suitable for the formation of a decoy cloud with infrared radiation

  for homing missiles sensitive to infrared radiation.

  FIG. 3 represents a sheet 83 which has the shape of a

  circle sector with an angle of 120. This sheet has al-

  lights designated by 87, which have a combustible layer 85 of incendiary paste. The combustible layer 85 extends over the entire surface of the

  sheet 83. It is covered, except in the area of the light strips.

  mage 87, of a moderating or passivation layer 86.

  Figure 4 is a section taken along a cord of the sheet 83 of Figure 3; this section shows that the support material 88 of the sheet is coated on each of its two faces with a combustible layer 85 partially covered with a moderating layer 86. FIG. 3 clearly shows that an ignition strip 87 is formed on a

26 2568679

  straight edge of the sheet 83 and a second ignition strip 87 is formed on a curved inner edge delimiting a cutout which is also

shaped like a circle sector.

  The combustible layer 85 of the sheet 83 of FIGS. 3 and 4 is preferably based on phosphorus and the same applies to the layer

  moderator 86 which is generally necessary in practice to limit

  ter the rate of propagation of the combustion of the sheet. The ignition strips 87 of this example are therefore formed automatically by the

  combustible layer 85 proper based on phosphorus which is sufficient

  healthily active, thanks to the non-covering of this layer by the layer

moderator 86.

  The sheets in a circle sector, the combustion layer of which

  target 85 in incendiary paste is based on another material, in particular boron-based, differ from the sheet shown in FIGS. 3 and 4 by the different nature of the combustible layer 85, the absence of the moderating layer 86 and by the fact that their ignition strips 87 are formed by a special combustible layer (ignition layer) which is applied over the combustible layer 85 of incendiary boron-based paste and which is capable of igniting the latter , the composition of this special combustible layer preferably being exactly the same

  than that of the combustible layer of incendiary phosphorus-based paste.

  The rocket shown in Figure 5 corresponds to that of Figure 2, except for the possible additional presence of a disc known as distance compensation between the elastic sealing ring on the contact head and the effective load container , different filling of the interior volume of this container, constituted in FIG. 5 of leaves in a sector of a circle which fill only part of this volume and the essential filling in the form of a molded part according to the invention and composed of pellets and a granule, each

  of these components being made of a smoke-based phos-

  red phore, as well as the presence of a domed cover, whose shape

  is adapted to that of the hat - shown in addition in Figure 5 -

  common to the rocket and to the launch pot, the latter not being shown more in FIG. 2 but corresponding to the pot represented in FIG. 1. FIG. 5 uses the same references as FIG. 2 for

  analogous or identical elements.

  Between the bottom 29 of the effective charging container 3 and the elastic sealing ring 69 (also made of nitrile rubber in this example) on the upper part 27 of the contact head 1 is

  arranged in addition, compared to Figures 1 and 2, a compensating disc

  massive distance station 121, the outside diameter of which is smaller than the outside diameter of the elastic sealing ring 69 but nevertheless large enough to prevent folding of the ring

  elastic seal 69 in the annular slot between the side wall

  line 41 of container 3 and the interior surface of the launching pot 55.

  In combination with the solid disc 121, the elastic ring 69 ensures the sealed arrangement of the rocket in the launch pot 55. On the head 43 of the container 3 is again fixed, also by crimping, a cover 5, which is here curved, which allows better use

  of the space available inside the volume closed by the cap 111.

  The space included in the container 3 between the socket 75 of the dval- unit

  light / burst 33 and the side wall of the container 3 contains, in

  its lower part, an effective charge which is formed of thin sheets

  pyrotechnic lets 83, preferably having a shape in a sector of a circle

at an angle of about 120.

  The interior of the container 3 of the example in FIG. 5 also contains, as an essential part of the effective charge, a molded piece 23 obtained by compression of pellets 125 made of a smoke composition based on red phosphorus, as well as d 'a granule 127 which is also made of a smoke composition based on red phosphorus; the compression molding of these two components to obtain the piece 123 is carried out so that the integrity of the pellets 125 is substantially preserved and that the granule 127 forms a structure

  porous which contains the pellets individually.

  The essential characteristic of this variant of the first embodiment of a rocket according to the invention therefore resides in the particular constitution of the molded piece 123 formed of the pellets 125 and of the granule 127. At the time of the firing of the rocket, the ignition / burst unit 33 not only ensures ignition and distribution

  pyrotechnic sheets 83 contained in the rocket, but also al-

  lighting and fractionation of the molded piece 123, as well as, simultaneously

  nement, the fractionation of the wall 41 of the effective load container 3.

  When the molded piece 123 is split, the granule is pulverized.

  laughed and immediately ignited. The lightning thus produced guarantees, with a slight time lag, the lighting of the pellets. At the same time, a very dense cloud of smoke forms above the object to be protected,

  cloud that subtracts the object from the sight of a possible enemy in the sky.

  The hot pellets which fall on the ground continue to burn and thus form a curtain of smoke which they feed from the ground by the continuation of their combustion. The special composition of the molded piece 123 of pellets 125 and of granule 127 consequently ensures the formation of a dense smoke curtain immediately after the launch of the rocket, and the maintenance of this curtain for an extended period thanks

  to the slow burning of the pellets.

  The use of a compression molded part such as that just described is of course not limited to a special rocket like those described here. On the contrary, such a part can be used everywhere where appropriate measures ensure its fractionation.

  adequate and, at the same time, the ignition of its components.

  To produce a molded part like the one shown

  in FIG. 5, one can proceed, for example, as described below.

  To produce the pellets, 69.8% by weight of red phosphorus, 19.4% by weight of copper oxide, 4.8% by weight of magnesium powder and 6% by weight of a binder are mixed. elastomer based

  chlorinated rubber and transformed into paste in a solvent, until the

  tion of a homogeneous mixture, which is then transformed by compression and in a conventional manner into pellets of about 1 g which have a

  11 mm diameter and 6 mm thickness.

  To produce the necessary granule, 65.7% by weight of red phosphorus, 18.2% by weight of copper oxide, 4.5% are used.

  by weight of magnesium powder and 11.6% by weight of an elasto binder

  mother made from chlorinated rubber and transformed into paste in a solvent, which is conventionally transformed into a granule of a size

  average grain of the order of 0.5 to 2 mm.

  420 parts by weight of the pellets obtained and 160 parts of the granule produced are then mixed, then the mixture is loaded into a mold whose imprint corresponds exactly to the shape of the interior of the effective loading container, the imprint in which the mixture is transformed. in a molded part under pressure which does not destroy the integrity of the pellets and gives a molded part in which the pellets are embedded in a porous matrix formed of the composition

  smoke smoke used in the production of the granule.

29 2568679

  FIG. 6 represents the second preferred embodiment of a rocket according to the invention, represented by a rocket which

  particularly suitable for the distribution of antiradar filaments.

  The references again have the same meanings as in FIGS. 1 and 2. Like FIG. 2, FIG. 6 is also a section taken at right angles to that of FIG. 1. The plan

  of section 6 therefore corresponds to that of Figure 2.

  The contact head of Figure 6 corresponding exactly to that visible in Figures 1 and 2, it is not necessary to describe it again. The same applies to the effective loading container 3 and to the cover 5 of this container. The only change compared to Figures 1 and 2 lies in a different conformation of the fixing plate 71 in the bottom 29 of the container 3. In addition, of course, the very content of the container 3 also differs from that of the rocket shown on the

  Figure 2 because the function of the rocket in Figure -6 is different.

  The fixing plate 71 located in the bottom 29 of the container 3 shown in FIG. 6 simultaneously forms a chamber 37 for expelling charge which is open towards the inside of the container 3 on the upper side of the plate. attachment 71 and in which there is, when the rocket is ready for use, an expulsion charge 39. On the side directed towards the interior of the container 3, the attachment plate 71 consequently takes the shape of a piston open dish. The expulsion charge 39 placed in the chamber 37 is in connection with the ignition composition to

  delay 31. The outer edge - facing the side wall 41 of the recess

  pient 3 - of the fixing plate 71 has an annular groove 117. at the top. The container 3 of this embodiment contains an effective load support 89 which is placed above the expulsion load chamber 37 formed by the fixing plate 71. The support 89 comprises a plate 91 which is guided in the container 3 by annular seals 93. These seals are preferably also made of nitrile rubber. Plate 91 is connected via a

  central column 95 to a cover plate 97 which has a

  gives holes 99. The support 89 for effective charging therefore consists

  essentially, in the embodiment shown, of the three elements

  ment mentioned above that are the plate 91, the central column 95 and the cover plate 97. The central column 95 of the support 89 is surrounded by intermediate discs 103 which extend over the entire cross section of the container 3 and which separate the different packages of

  filaments 101. In each of the spaces delimited by the inter-

  103, the filaments 101 are arranged in a bundle and parallel-

  ment to the longitudinal axis of the rocket, therefore also to the central column 95.

  The filaments can be in the form of metallized wires or filaments made of plastic or glass, or in the form of wires or

metallic filaments.

  Upon ignition of the expulsion charge 39 located in the chamber 37 via the ignition composition to

  delay 31, the support 89 filled with filaments is expelled, with

  ment of the cover 5 at the head 43 of the container 3, outside of this container, the cover plate 97 provided on the support 89 then ensuring,

  in combination with the orifices 99 provided on it, good stabilization

  tion and correct distribution of the filaments contained in the support.

  The filament layers on the interlayer discs 103

  thereby spread laterally from the support 89.

  The preferred constituent material for the effective load container 3 of the device shown in Figure 6 is again aluminum. The same goes for the cover 5 of the container 3 and for the fixing plate 71. The wall thickness of the container 3 and of the cover 5 of this container is again about 0.25 millimeter. The essential elements of the support for effective charging are preferably

also in aluminum.

  The rockets shown in Figure 2 (with Figures 3 and 4), Figure 5 and Figure 6 are particularly suitable, as already indicated, for firing and distributing thin pyrotechnic sheets (flora), incendiary masses, materials or compositions and / or smoke-based

  of red phosphorus, possibly in combination with pyro-

  techniques, or filaments, in particular antiradar filaments. However, it is also perfectly possible to fill the rockets according to the invention with other effective charges; in this case, one can use, for example, the rocket whose basic design is shown in Figure 1,

  with adaptation of the internal conformation of the effective load container

  specific to the intended application. Such an implementation of the invention makes it possible to obtain as good results as with the rockets shown in the following figures. It is also possible to replace, also in the preferred embodiments shown, the contact head with a contact head of another type or conformation, which amounts to saying that an effective charging container according to the invention, including its interior equipment and effective load, can also be

  combined with conventional contact heads.

32 OOY

32 2568679

Claims (66)

R E V E N D I C A T I 0 N S   1. Rocket or other projectile having a contact head and an effective load receptacle connected to the head and possibly closed   by a cover, the external side wall of the contact head   both contact rings connected by firing lines to an ignition bead arranged inside the contact head in a propellant charge chamber in the form of a boot for receiving a propellant charge or ejection, the propellant charge chamber being closed in a substantially gas-tight manner with respect to the outside by a cover screwed to the bottom part of the contact head and by a sealing means at the bushings for the release lines fire, a delay ignition composition forming a connection between the propellant charge chamber and the effective charge container being arranged gas tight relative to the outside in the upper part of the contact head or in the bottom of the container effective load, the composition   ignition system being linked, either with an ignition / burst unit   tely disposed in the effective charge container and comprising an ignition / burst charge to ignite an effective charge, in particular a pyrotechnic charge, and to split the wall of the effective charge container, either with an expelling charge chamber containing a charge expulsion device for expelling the effective load, with the cover tearing off at the head of the effective load container, the contact head and the effective load container being firmly connected to each other by screws, characterized in that that the propellant charge chamber (13) is arranged in the middle of the contact head (1) and is provided with a screwed cover (21), closing in a gas-tight manner and having a thread (49) on a solid edge (47), which constitutes at the same time, at least in its central part, a massive support (51) intended to cooperate with a spacer (53) provided in a launch pot (55), the cover portions located between the edge (47) and the support ( 51) massive forming rupture zones (57) in the form of windows for the ejection gas outlet.   2. Rocket according to claim 1, characterized in that a delay ignition composition (3Z is arranged in the middle of the part   upper (27 of the contact head (1).   3. Rocket according to claim 1 or 2, characterized in that a fixing plate (7) is arranged in the bottom (29) of the container effective load (3).   4. Rocket according to claim 3, characterized in that the bottom (29) of the effective load container (3) is reinforced and used as a fixing plate (71).   5. Rocket according to any one of claims 1 to 4,   characterized in that the effective loading container (3) is closed by a cover (5) at its head (43).   6. Rocket according to any one of claims 1 to 5,   characterized in that the effective loading container (3) is a boot stamped aluminum (3).   7. Rocket according to claim 6, characterized in that   the aluminum boot (3) is closed by crimping on an aluminum cover minium (5) at its head (43).   8. Rocket according to any one of claims 1 to 7,   characterized in that the effective charge container (3) contains an ignition / burst unit (33) which is in contact with the delay ignition composition (31) and which comprises an ignition / burst charge (35 ) to ignite the effective charge (73) contained in the effective charge container (3) and / or to split the wall (41) of the effective load (3).   9. Rocket according to claim 8, characterized in that the ignition / burst unit (33) comprises a socket (75) filled with an ignition / burst charge (35) and disposed in the middle of the plate. fixing (71) or the bottom (29) serving as a container fixing plate effective load (3).   10. Rocket according to claim 8 or 9, characterized in that the ignition / burst unit (33) extends practically up to   cover (5) of the effective charging container (3).   11. Rocket according to any one of claims 8 to 10,   characterized in that the socket (75 of the ignition / burst unit (33) is made of aluminum.   12. Rocket according to any one of claims 8 to 11,   characterized in that the open end, in connection with the compound   The delayed ignition (31) of the socket (75) of the ignition / burst unit (33) has a crimped edge (77), by which the socket (75) is screwed from below and gas-tight in the effective load container (3) and in the mounting plate (71), or in the bottom   (29) made as a fixing plate for the effective load container (3). 34 2568679   13. Rocket according to claim 12, characterized in that the open end of the sleeve (75) is connected by crimping to a cover disc (79) and is screwed in a gas-tight manner from below, by this disc and by means of a screw (81) combined with an annular seal (115), in the effective load container (3) and the fixing plate (71), or the bottom (29) made as a plate   for fixing the effective load container (3).   14. Rocket according to any one of claims 8 to 13,   characterized in that the effective charge (73) is formed from thin films fuel hoses (83).   15. Rocket according to claim 14, characterized in that   the sheets (83) are in the form of a sector of a circle.   16. Rocket according to claim 15, characterized in that the sheets (83) are in the form of a sector of a circle with an angle of approximately 120.   17. Rocket according to claim 15 or 16a characterized in that the sheets (83) in a sector of a circle are arranged radially around the ignition / burst unit (33) in the load container effective (3).   18. Rocket according to any one of claims 14 to 17,   characterized in that the sheets (83) are made of a support material (88) on which is applied, at least on one side, a layer   fuel (85) made of an incendiary paste and burning slowly.   19. Rocket according to any one of claims 14 to 17,   characterized in that the sheets (83) are formed of a material of   support (88) on both sides of which are applied combustion layers tarts (85) of incendiary paste.   20. Rocket according to any one of claims 14 to 19,   characterized in that the support material (88) of the sheets (83) is paper.   21. Rocket according to any one of claims 14 to 19,   characterized in that the support material (88) of the sheets (83) is   a sheet or film of metal.   22. Rocket according to claim 21, characterized in that the support material (88) of the sheets (83) is an aluminum foil or film.   23. Rocket according to any one of claims 14 to 19,   characterized in that the support material (88) of the sheets (83) is a sheet or film of plastic material whether or not provided with a metallic coating.   24. Rocket according to any one of claims 20 to 23,   characterized in that the support material (88) used for the sheets (83) has a weight per unit area of up to g / m2 approx.   25. Rocket according to any one of claims 14 to 24,   characterized in that the combustible layer (85) of incendiary paste which is on the sheets (83) is composed of red phosphorus and a plastic material in a weight ratio of between 70:30 and 85:15.   26. Rocket according to any one of claims 14 to 25,   characterized in that the combustible layer (85) of incendiary paste which is on the sheets (83) is at least partially covered with a   moderating or passivation surface layer (86).   27. Rocket according to claim 26, characterized in that the moderating layer (86) is composed of red phosphorus and a material   plastic in a weight ratio of 5:95 to 30:70.   28. Rocket according to claim 25 or 27, characterized in   what the plastic is basically polyvinyl chloride.   29. Rocket according to any one of claims 15 to 28,   characterized in that the sheets (83) in the sector of a circle have an ignition strip (87) which is not provided with a moderating layer   (86) on their curved inner edge adjacent to the ignition / burst unit ment (33).   30. Rocket according to any one of claims 15 to 28,   characterized in that the sheets (83) in the sector of a circle have an ignition strip (87) which does not have a moderating layer (86) on one of their straight edges.   31. Rocket according to any one of claims 15 to 28,   characterized in that the sheets (83) in the sector of a circle have an ignition strip (87) which does not have a moderating layer (86)   on their curved inner edge and on one of their straight edges.   32. Rocket according to any one of claims 14 to 31,   characterized in that the ready-to-use sheets (83) have a weight   per unit area up to approximately 400 g / m2. 36 2568679   33. Rocket according to any one of claims 14 to 24,   characterized in that the combustible layer (85) of incendiary paste which is on the sheets (83) is composed of boron and / or boron alloys having a boron content of at least 90% by weight and a plastic material, according to a weight ratio between 70:30 and 85:15. 34. Rocket according to claim 33, characterized in that   the plastic material is essentially polyvinyl chloride.   35. Rocket according to claim 33 or 34, characterized in that the incendiary paste composed of boron and / or boron alloys and   of plastic also contains up to 40% by weight of fuel   rant and / or active metal powder and / or active metal alloy powder. 36. Rocket according to claim 35, characterized in that the incendiary paste of boron and of a plastic material contains carbon dioxide. lead as oxidizer.   37. Rocket according to claim 35, characterized in that the incendiary paste of boron and of a plastic material contains manganese, zirconium, cerium and / or boron alloy powder as powder   of active metal and / or as active metal alloy powder.   38. Rocket according to any one of claims 33 to 37,   characterized in that the sheets (83) in a circle sector have an allunm.ge strip (87) on their curved inner edge adjacent to the unit ignition / burst (33).   39. Rocket according to any one of claims 33 to 37,   characterized in that the sheets (83) in the sector of a circle have   an ignition strip (87) on one of their straight edges.   40. Rocket according to any one of claims 33 to 37,   characterized in that the sheets (83) in a circular sector have an ignition strip (87) on their curved inner edge and on one of their straight edges:   41. Rocket according to any one of claims 33 to 40,   characterized in that the ignition strip (87) is formed of a combustible layer of an incendiary paste composed of red phosphorus and of a plastic material, according to a weight ratio between 70:30 and 85:15,   which is applied over the combustible layer (85) according to one conch of claims 33 to 37.   42. Rocket according to claim 41, characterized in that   the plastic material is essentially polyvinyl chloride.   43. Rocket according to any one of claims 8 to 13,   characterized in that the effective charge is a single molded part (123), filling the interior of the effective charge container (3) partially or totally, which is produced by compression of pellets (125) with a smoke-based composition of red phosphorus and a granule (127) of   smoke composition based on red phosphorus, compression being effective   made in such a way that the integrity of the pellets (125) is substantially preserved and that the granule (127) forms a porous structure which contains   the pellets (125) individually.   44. Rocket according to claim 43, characterized in that the effective load is a molded part (123) which fills exactly all   the interior of the effective charging container (3).   45. Rocket according to claim 43, characterized in that the effective charge consists of a molded part (123) which partially fills the interior of the effective charge container (3) and of thin   combustible sheets (83) which fill the remaining part of the interior   of the effective load container (3) according to any of the vendications 14 to 42.   46. Rocket according to any one of claims 43 to 45,   characterized in that the pellets (125) contained in the molded part (123) have a diameter of approximately 11 mm, a thickness of approximately 6 mm and a weight of about 1 g.   47. Rocket according to any one of claims 43 to 46,   characterized in that the pellets (125) contained in the molded part (123) are composed of red phosphorus, copper oxide powder, powder magnesium and a binder.   48. Rocket according to any one of claims 43 to 47,   characterized in that the granule (127) contained in the molded part (123) is composed of red phosphorus, copper oxide powder, magnesium and a binder.   49. Rocket according to any one of claims 43 to 48,   characterized in that the pellets (125 contained in the molded part (123) have a higher content of binder than the granule (127) contained in this piece.   50. Rocket according to claim 49, characterized in that the pellets (125) contained in the molded part (123) are composed of approximately 65 to 75% by weight of red phosphorus, approximately 5 to 20% by weight   copper oxide powder, about 3 to 8% by weight of magnesium powder   sium and about 3 to 10% by weight of binder.   51. Rocket according to any one of claims 43 to 46,   characterized in that the granule (127) contained in the molded part is composed of approximately 60 to 70% by weight of red phosphorus, approximately 5 to 20% by weight of copper oxide powder, approximately 3 to 8% in powder weight   magnesium and about 5 to 15% by weight of binder.   52. Rocket according to any one of claims 43 to 51,   characterized in that the binder is an elastomer.   53. Rocket according to any one of claims 43 to 52,   characterized in that the weight ratio between the pellets (125) and   the granule (127) in the molded part (123) used as effective filler cace is approximately 3: 1 to 2: 1.   54. Rocket according to any one of claims 1 to 7,   characterized in that an expulsion charge chamber (37) is arranged   in or on the fixing plate (71) located at the bottom (29) of the container   effective load point (3), or else in or on the bottom (29) made as a plate for fixing the effective load container (3), the chamber (37) being designed to receive an expulsion charge (39) intended to expel an effective load (73) contained in the effective load container (3) with tearing off the cover (5) provided at the head (43) of the effective load container (3), the expulsion load (39) being in   connection with the delayed ignition composition (31).   55. Rocket according to claim 54, characterized in that the expulsion charge chamber (37) is arranged in the upper side of the fixing plate (71) or in the bottom (29) made as a fixing plate for the container. effective load (3) and is open from the side   directed towards the inside of the effective load container (3).   56. Rocket according to claim 54 or 55, characterized in   that the effective load (73) is arranged on an effective load support   cace (89) which is formed of at least one plate (91) placed above the expulsion charge chamber (37) and guided in the charge container   effective (3) so as not to be able to block in this container.   57. Rocket according to any one of claims 54 to 56,   characterized in that the plate (91) and the fixing plate (71), or   the bottom (29) made as a fixing plate for the effective load container   cace (3), are arranged so that the expulsion charge chamber (37) does not have direct contact with the surrounding wall of the container effective load (3).   58. Rocket according to claim 57, characterized in that   the plate (91) carries, on its outer edge, at least one seal   annular shell (93) applied in a gas-tight manner against the wall (41)   of the effective load container (3).   59. Rocket according to claim 58, characterized in that   the plate (91) carries two annular seals (93).   60. Rocket according to claim 58 or 59, characterized in that the plate (91) takes the form of a flat piston which is open   towards the bottom of the effective load container (3).   61. Rocket according to any one of claims 55 to 60,   characterized in that the outer edge of the lower part of the plate (91) fits into the outer edge of the upper part of the fixing plate (71) or of the bottom (29) made as a plate   fixing the efficient load container (3).   62. Rocket according to any one of claims 55 to 61,   characterized in that the effective load support (89) consists of the plate (91), a central column (95) disposed on the plate - and extending practically to the lid (5) of the container effective load container (3) and a cover plate (97) adapted to the inside diameter of the effective load container (3) and located at the end   upper of the central column (95).   63. Rocket according to claim 62, characterized in that   the cover plate (97) has a peripheral crown of ori- fices (99).   64. Rocket according to any one of claims 54 to 63,   characterized in that antiradar filaments (101) are arranged in parallel   along the longitudinal axis of the effective load container (3) on the effective load support (89).   65. Rocket according to claim 64, characterized in that several bundles of filaments (101) are placed on each other on the effective load support (89). 2 68679   66. Rocket according to claim 65, characterized in that the bundles of filaments (101) are separated from each other by intermediate discs (103) arranged perpendicular to the central axis   of the effective load container (3).