Classifications

• • C—CHEMISTRY; METALLURGY
  • C06—EXPLOSIVES; MATCHES
  • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
  • C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/40—Arrangements or adaptations of propulsion systems
  • B64G1/402—Propellant tanks; Feeding propellants
• • C—CHEMISTRY; METALLURGY
  • C06—EXPLOSIVES; MATCHES
  • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
  • C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
  • C06B47/02—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
• • C—CHEMISTRY; METALLURGY
  • C06—EXPLOSIVES; MATCHES
  • C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
  • C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/40—Arrangements or adaptations of propulsion systems
  • B64G1/403—Solid propellant rocket engines

Definitions

• the invention relates to a method for producing (cryogenic) monergolic solid fuels for rocket propulsion systems, in particular from heterogeneous liquid-solid fuels, in which at least one of the reactants contains, as an oxidizer or fuel, a phase which is liquid or gaseous at normal temperature, for example, for producing Emulsions of non-mutually soluble liquid components, suspensions of solid in liquid components or fillings soaked in liquid.
• the invention further relates to a (cryogenic) solid fuel for rocket propulsion cooled to below room temperature, in particular a heterogeneous quasi-monergol fuel-oxidizer combination, in which at least one of the reactants is a liquid or gaseous phase at normal temperature, for example emulsions of liquid components which are not soluble in one another , Suspensions of solid in liquid components or liquid soaked fillings.
• a (cryogenic) solid fuel for rocket propulsion cooled to below room temperature in particular a heterogeneous quasi-monergol fuel-oxidizer combination, in which at least one of the reactants is a liquid or gaseous phase at normal temperature, for example emulsions of liquid components which are not soluble in one another , Suspensions of solid in liquid components or liquid soaked fillings.
• the invention thus aims at the technical field of t
• Fuels for rocket engines and therein for the manufacture and construction of solid propellants are understood to be present in certain geometric shapes. This also includes any built-in or add-ons that, for mechanical reasons, are used for fuels that can be stored without refrigeration
• the components are in the liquid and / or solid state and serve as an oxidizer or as a fuel. Some also have other functions, for example as binders or additives.
• monergols one-component fuels.
• Diergolen distributes the functions to separate components.
• Monergols can be homogeneous or heterogeneous both according to their phase structure and their molecular composition as well as their physical state.
• Examples of homogeneous monergols as liquid fuels are hydrogen peroxide, hydrazine and nitroglycerin.
• Heterogeneous monergols include, for example, emulsions of non-mutually soluble liquid components.
• a whole series of fuels for rocket propulsion are known, in which at least one of the components is a liquid phase at normal temperature (US Pat. Nos. 2,802,332, 3,367,268, 3,398,215, 3,687,746, 3,697,455, 3,697,455 , U.S. 3,703,080).
• the US 2,802,332 discloses a propellant charge of a liquid 'keitsrakete having a structure which is formed from a plurality of cells. There is at least one reactant in these cells.
• the walls of the cell-like structure are made of polyethylene, Teflon or silicone rubber.
• the individual cells are connected to each other by openings.
• the prior art according to US 3,367,268 relates to a hybrid rocket propellant which is constructed from a solid polymeric cell-like rubber substance which forms an intercellular matrix. Powdered solid fuels, for example light metal powders from Groups II and III of the PSE, and reinforcing fibers are embedded in this matrix. The pores contain a liquid oxidizer.
• US Pat. No. 3,398,215 describes a method "for producing a rocket propellant, in which a curable rubber polymer is mixed with powdered metal fuel and hardener and is treated with an organic blowing agent.
• the rubber polymer is selected from the group of rubber-like hydrocarbons and halogenated hydrocarbon rubbers. Powders made of aluminum, boron, titanium, beryllium, magnesium and lithium are used as the metal fuel.
• the organic blowing agent boils at 70 to 200 ° C and is compatible with the polymer and evaporates at a curing temperature of 120 ° C to 205 ° C Composite, with pores or cells in of the matrix.
• the sponge-like matrix contains the metal fuel and forms a coherent phase.
• the matrix is then immersed in an oxidizer liquid so that the pores fill with the oxidizer liquid. All these known solutions have the disadvantage in common that they only achieve a very low level of performance and are complicated in their construction and handling.
• propellant charges in very different geometric shapes. However, they can be roughly divided into two categories, namely internal burners with more radially directed burns and front burners with more axially directed burns.
• monergolic fuels those are known which contain fuel and oxidizer as separate elements in different geometrical arrangements. Examples are radially burning disc stacks or rod-in-matrix head torches (RELO, N. EISENREICH; "Modular and cryogenic solid propellants - a new class of chemical rocket propulsion", German Aerospace Congress, DGLR-JT98-104; Bremen, October 7th. 1998; Yearbook 1998, Volume 2, p. 1231). Such arrangements are known as modular propellants. Modular propellants with large module elements belong to the Diergolen (two-component fuels). The combustion takes place in diffusion flames as so-called boundary layer combustion, in which the transition to uncontrolled explosions or detonations cannot or cannot easily occur.
• RELO rod-in-matrix head torches
• Modular propellants with large module elements belong to the Diergolen (two-component fuels). The combustion takes place in diffusion flames as so-called boundary layer combustion, in which the transition to uncontrolled explosions or det
• Modular fuels can also be distinguished from those with encapsulated components.
• goal of Encapsulation is the mutual separation of reactive liquids and thus an improvement in long-term storage.
• Liquids or very sensitive reactants can be enclosed in the capsules.
• Small capsules are enclosed undirected in binders, macrocapsules are aligned and cast with a binder or hardening solid propellant.
• capsule fuels pass into a subclass of the rod-in-matrix fuels.
• cryogenic solid propellants CSP
• Monergols CSP consist of frozen monergols that are fluid at room temperature.
• Modular CSP are composed of at least one frozen element that is not combustible on its own (US 3 137 127).
• the erosion of modular, non-monoleric fuel elements is fundamentally a diffuse boundary layer erosion and as such is dependent on the influx of reactants. If this is not by a strong current, but only by convection, the reaction is irregular and sluggish, if at all. Therefore, modular propellants need at least a certain size
• the invention has for its object to increase the performance of the cryogenic solid fuels compared to conventional solid drives, hybrid drives or liquid engines, their storage life and To improve cost-effectiveness in a simple manner while avoiding complex liquid management while eliminating permanent ignition of the cryogenic solid fuels.
• the process according to the invention is characterized in particular by the fact that the freezing of the liquid phase in the heterogeneous liquid-solid fuels turns the latter into cryogenic, monergolic solid fuels, as a result of which the permanent ignition can be dispensed with and problems of liquid management which arise with normal liquid-solid - Quasimonergolen occur, bypassed.
• the invention thus covers all quasi-monergolic fuel-oxidizer combinations in which at least one of the components is a frozen liquid.
• the invention leads to significant increases in performance of launchers.
• the invention also leads to significant operating and thus start-up cost savings when selecting suitable fuel candidates such as SOX or SH 2 0 2 in connection with solid hydrocarbons such as PE, PU, HTPB.
• suitable fuel candidates such as SOX or SH 2 0 2 in connection with solid hydrocarbons such as PE, PU, HTPB.
• Fig. 1 shows a section through a polymer sponge
• Fig. 2 shows a section through an aluminum sponge as a solid structure with embedded cryogenic phase
• Fig. 3 shows a section through a poured bed of polyethylene and cryogenic phase.
• a rocket propellant from solid fuel according to the invention is to be produced using the method according to the invention.
• the solid fuel is to consist of a polymer sponge 1, for example of polyethylene, as fuel and a cryogenic oxidizer phase 2, for example of frozen hydrogen peroxide.
• the sponge 1 as a solid phase is first attached to the inner insulation of a combustion chamber wall, not shown, by gluing and then filled with hydrogen peroxide using capillary forces or a pressure gradient and, if necessary, subsequently by hypothermia in the
• FIG. 2 shows an example in which an aluminum sponge 3 is used as the solid phase, the pores of which are filled with frozen oxygen.
• the solid fuel according to the invention is produced as previously described.
• oxidizer 5 which is liquid at room temperature and which has been frozen after filling.
• the table below shows the scope of the present invention, in each of which two components are listed, with one of the components always representing the oxidizer and the other the fuel.
• Each component can also be a homogeneous or heterogeneous mixture of different substances.
• high-energy materials for example representatives of the "High Energy Density Matter” (HEDM)
• HEDM High Energy Density Matter
• components or additives for example disperse atoms or molecules in a stabilizing matrix, tensioned compounds (for example CUBAN), weak covalent compounds (poly nitrogen), excited atoms or molecules (triplet helium) or metallic hydrogen
• tensioned compounds for example CUBAN
• weak covalent compounds poly nitrogen
• excited atoms or molecules triplet helium
• metallic hydrogen metallic hydrogen
• Solid rocket engines all components have the same initial temperature by nature.

Landscapes

• Chemical & Material Sciences (AREA)
• Engineering & Computer Science (AREA)
• Organic Chemistry (AREA)
• Combustion & Propulsion (AREA)
• Remote Sensing (AREA)
• Aviation & Aerospace Engineering (AREA)
• Chemical Kinetics & Catalysis (AREA)
• Crystallography & Structural Chemistry (AREA)
• Solid Fuels And Fuel-Associated Substances (AREA)
• Filling Or Discharging Of Gas Storage Vessels (AREA)
• Manufacture Of Porous Articles, And Recovery And Treatment Of Waste Products (AREA)

Priority Applications (4)

Applications Claiming Priority (2)

Publications (1)

Family

ID=28459559

Family Applications (1)

Country Status (8)

Cited By (2)

Families Citing this family (7)

Citations (8)

Family Cites Families (5)

• 2002
  • 2002-04-16 EP EP02090144A patent/EP1354862A1/de not_active Withdrawn
• 2003
  • 2003-04-14 AU AU2003229662A patent/AU2003229662A1/en not_active Abandoned
  • 2003-04-14 WO PCT/EP2003/003860 patent/WO2003087017A1/de not_active Ceased
  • 2003-04-14 JP JP2003583976A patent/JP2005528469A/ja active Pending
  • 2003-04-14 RU RU2004133348/02A patent/RU2312847C2/ru active
  • 2003-04-14 CN CNB038111772A patent/CN100337995C/zh not_active Expired - Fee Related
  • 2003-04-14 US US10/511,865 patent/US8147628B2/en not_active Expired - Fee Related
• 2004
  • 2004-10-13 IL IL16456604A patent/IL164566A0/xx unknown

Patent Citations (8)

Non-Patent Citations (3)

Also Published As

Similar Documents

Legal Events