Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F42—AMMUNITION; BLASTING
  • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
  • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
  • F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements
• • 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
  • F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material

Definitions

• the invention relates to missiles with a bow tip, fixed fins or movable rudders [fins], thrusters, thrusters and nozzle head inserts 5, combustion chamber linings 6, tail cone, grille wings, fluidic elements and radomes or partial components made of these, these components consisting of ceramic material.
• the nose tip, fixed fins or movable rudders or fins, thrusters, thrusters and nozzle neck inserts, combustion chamber linings, tail cone, grille wings, fluidic elements and the radome consist of various metals and metal alloys. These missile components are the most thermally and mechanically loaded
• the invention has for its object ceramic bow tips, fixed fins or movable rudders [fins], jet rudders, thrusters and nozzle head inserts, chamber linings, stern cone, grille wings, fluidic elements and radomes or partial components made of these for missiles with high temperature, pressure and abrasion resistance, Erosion resistance, low density or low weight, high thermal conductivity, low thermal expansion with an almost unlimited variety of geometries and shapes.
• the bow tip, fixed fins or movable rudders [fins], jet rudders, thrusters or jet nozzle inserts, combustion chamber linings, stern cone, grille wings, fluidic elements and the radome or partial components of these of the type mentioned at the outset are characterized according to the invention in that the bow tip 1, fixed fins 2 or movable rudder [fins]
• Bow tip 1 fixed fins 2 or movable rudders [fins] 3, jet rudders 4, thrusters or nozzle head inserts 5, combustion chamber linings 6, tail cone 7, grille wings 8, fluidic elements 9 and rado e 10 or partial components made of these consist of a fiber-reinforced ceramic or of combinations various fiber-reinforced ceramics and form a monolithic structure after infiltration. Overall, the temperature resistance increases while the weight of these missile components is reduced.
• C / SiC and C / C and SiC / SiC with continuous fiber reinforcement and short fiber reinforced C / SiC and C / C and SiC / SiC.
• the first-mentioned material made of C / SiC or C / C or SiC / SiC, which can be laminated, pressed or wound, is characterized by particularly high strength and particularly low density. Surface sealing can be used to increase the resistance to oxidation.
• Protective layers made of silicon carbide and / or silicon dioxide and / or molybdenum disilicide are preferably applied to the component surfaces for this purpose. The latter is superfluous with short fiber reinforced C / SiC because the material is particularly resistant to oxidation and corrosion.
• This construction is particularly suitable for C / SiC or C / C or SiC / SiC with short fiber reinforcement, whereby the individual segments are mechanically processed before they are combined or infiltrated.
• Such a missile component 1-10 can also easily be used with fastening elements such as Screws or bolts or flanges, preferably made of C / SiC and / or C / C and / or SiC / SiC, are connected.
• the missile components 1-10 by mechanical processing in the green state
• Cooling channels and / or recesses with a round, rectangular or slot-shaped cross section can be introduced.
• the method according to the invention also provides for the missile components 1-10 to be designed in hybrid and segment construction.
• the missile components 1-10 By mechanical processing of raw bodies and subsegments, which preferably consists of C / SiC and / or C / C and / or SiC / SiC or from suitable combinations with continuous fiber reinforcement and / or short fiber reinforcement and by the subsequent infiltration with silicon and / or silicon carbide and / or carbon this single segments are designed to form monolithic missile components in hybrid construction.
• the inner wall of the missiles or the thermally highly stressed locations of the missiles are suitably coated with C / SiC or
• the insulation materials can also be connected with the missile components 1-10 made of C / SiC and / or C / C with the interposition of spacers, preferably made of C / SiC or C / C or SiC / SiC, in order to produce the desired monolithic structure .
• the density and porosity of the C / SiC and / or the C / C and / or SiC / SiC material during infiltration or siliconization can be adjusted by adding silicon, carbon or silicon carbide, so that the C / SiC and / or C / C and / or SiC / SiC with high density and low porosity as a thermomechanical support structure and / or lining and the C / SiC and / or C / C and / or SiC / SiC with low density or high porosity as thermal insulation can be used. Density and porosity gradients can also be set over the wall thickness of the missile components 1-10.
• open cooling channels can also be incorporated into the metallic missile structure, which occur when the C / SiC and / or C / C parts and / or SiC are inserted / SiC parts are closed.
• the missile component 1-10 is manufactured from C / SiC and / or C / C and / or SiC / SiC individual segments, which then form a monolithic structure with carbon and / or silicon and / or silicon carbide are infiltrated and / or put together or the missile components 1-10 are manufactured in one piece, preferably by mechanical processing of a C / SiC and / or C / C and / or SiC / SiC blank.
• These C / SiC and / or C / C parts and / or SiC / SiC parts can also provide the cooling channels (if necessary) or recesses in order to remove the heat.
• the C / SiC and / or C / C body and / or SiC / SiC body 1-10 and the metallic missile structure are with suitable connecting elements such as bolt, screw or flange connections, preferably made of C / SiC and / or C / C and / or SiC / SiC to connect with each other. Options for this are shown in Figures 2 to 9.
• Figure 2 shows a nose tip 1 and a radome 10 of a missile.
• the bow tip is particularly stressed by high pressures and high temperatures.
• the weight of the nose tip can be reduced by at least 1 kg compared to a metallic nose tip.
• Radomes are exposed to high pressures and high temperatures.
• increased radar permeability and surface accuracy (e.g. through grindability) and the construction of different wall thicknesses are required for radomes.
• Figure 3 shows the stabilizing films or fixed fins 2 and the tail cone 7 of a missile.
• FIG. 4 shows movable rudders or fins 3 and lattice wings 8.
• the movable rudders or fins 3 are subject to stresses caused by high longitudinal and lateral acceleration forces and high temperatures. They serve as an aerodynamic steering aid. Stresses due to high longitudinal and lateral acceleration forces and high temperatures also occur on the lattice wings 8. They serve both as an aerodynamic steering aid and to maintain the stability of the missile.
• the grille wing looks like a narrow doormat attached to the tail of the missile, the openings of which are in the direction of flight and can be rotated about the longitudinal axis.
• Fig. 5 the thrusters 4 according to the invention are shown.
• a stress caused by high transverse forces, temperatures and abrasion by exhaust gases and solid particles (eg Al 2 0 3 particles) must be taken into account when designing thrusters.
• the use of thrusters in the exhaust jet serves as an additional steering aid during the propulsion phase of the missile. Thruster in the rear
• FIG. 6 shows a thrust nozzle 5 and the typical embodiment of the combustion chamber lining 6 according to the invention.
• the thruster is subjected to extremely high pressures and temperatures.
• the missile engines often have several and different numbers of thrusters for the individual thrust phases (ejection, acceleration and marching phases).
• Figure 7 shows typical fluidic elements 9 that are used as transverse thrust controls.
• the method according to the invention provides that the thrust nozzle and / or the nozzle neck and / or the combustion chamber are lined with C / SiC and / or C / C segments and / or SiC / SiC segments.
• the inside walls of the missiles are out
• the C / SiC and / or C / C and / or SiC / SiC individual segments are to be designed in such a way that the dividing slots, the gases under high pressure and high temperature, are not let through to the metallic missile structure.
• the C / SiC and / or C / C parts and / or SiC / SiC parts can be adapted to the inner contour of the missile engine and thus enable a geometrical simplification of the missile structure.
• a process variant also provides that the C / SiC and / or C / C and / or SiC / SiC individual segments for the missile components (1-10) made of C / SiC and / or
• the cooling can optionally be carried out by introducing cooling channels or recesses in the C / SiC and / or C / C and / or SiC / SiC structure or the isolation with carbon felts or graphite foil or C / SiC or C / C or SiC / SiC or combinations of these.
• the cooling with cooling channels can be carried out in the missile structure at the transition from metal to C / SiC and / or C / C and / or SiC / SiC or in C / SiC and / or C / C and / or SiC / SiC -Take part yourself. A combination of both parts is also provided.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• General Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Physics & Mathematics (AREA)
• Thermal Sciences (AREA)
• Ceramic Products (AREA)
• Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
• Details Of Aerials (AREA)

Applications Claiming Priority (3)

Publications (2)

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ID=7802697

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• 1996
  • 1996-08-16 DE DE19632893A patent/DE19632893C2/de not_active Revoked
• 1997
  • 1997-08-04 US US09/242,372 patent/US6460807B1/en not_active Expired - Fee Related
  • 1997-08-04 WO PCT/EP1997/004235 patent/WO1998008044A1/fr not_active Ceased
  • 1997-08-04 AT AT97935567T patent/ATE193942T1/de not_active IP Right Cessation
  • 1997-08-04 DE DE59701892T patent/DE59701892D1/de not_active Expired - Fee Related
  • 1997-08-04 EP EP97935567A patent/EP0918976B1/fr not_active Expired - Lifetime

Non-Patent Citations (1)

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