Casing shell of aircraft

FIELD: aviation.

SUBSTANCE: for a shell with a long generatrix L and a smooth bearing wall of thickness δ of casing of cylindrical, conical or biconical form - in the wall of the shell from one or two ends axisymmetrically blind holes of diameter d and length l1, l2 are made in the way that δ=d+2(0.5-4.0) mm, L=(l1+l2)+(2-20) mm. A heat accumulating inserts or a balancing mass is installed in one or more cavities of a blind hole. The heat-accumulating insert is made of a material with a phase transition at the temperature not lower than +70°C. In open part of the blind hole, a groove with a diameter D and a depth h is made in a way that D=ƒ+(0.1-0.8) mm, h=S+(0.1-2.0) mm, where ƒ is diameter of the edge of heat-accumulating insert cork, S is thickness of the cork edge.

EFFECT: improvement of the criterion of efficiency - cost - time of creation and development.

4 cl, 5 dwg

 



 

Same patents:

FIELD: aircraft engineering.

SUBSTANCE: proposed system comprises composites with ceramic matrix reinforced by heat-resistant fibers and including sublimable solid substance. Said solid sublimable substance comprises stabilised pre-ceramic organosilicon polymers containing atoms C, Si and H as well as germanium heteroatoms. Heat-resistant layer as a ceramic matrix comprises carbides or borides of refractory metals or their mixes. Besides, sublimable solid substance can include refractory metal germanates.

EFFECT: efficient heat protection.

10 cl, 5 ex

FIELD: physics.

SUBSTANCE: method involves mounting an angle reflector in the nose of a missile, preliminary transmission of radiation incident on the angle reflector through an electro-optic laser radiation polarisation-modulating medium, selecting the modulating electric signal, selecting a mean-square value and establishing the spectrum of noise voltage. The modulating electric signal used is a mixture of constant bias voltage and noise voltage. The selected mean-square value of the noise voltage is comparable with the constant bias voltage. The constant bias voltage set such that radiation of a potential enemy which is received by the coherent laser radar and reflected from the angle reflector and passing twice through the electro-optic modulating medium has polarisation which is orthogonal to the polarisation of the probing radiation. The spectrum of the noise voltage is comparable with the band of the modulating laser radiation.

EFFECT: high efficiency of counteracting missiles with coherent laser radar.

8 dwg

FIELD: ballistics; protection of structural components in rocketry and space engineering with the aid of special-purpose coats.

SUBSTANCE: proposed active heat-protective coat is made from dissimilar materials applied in layers. Outer layer is made from material of low heat conductivity in form of insulating body forming many cells filled with heat absorbing fluid ensuring endothermic reaction in presence of catalyst finely divided and smoothly distributed in porous insulating body. Intermediate layer is made from paraffin at low melting point; this layer is reinforced with screen made from material of high heat conductivity. Inner layer is made in form of cellular structure from copper foil filled with expansible flameproof composition which seals up holes at high temperature and mechanical damage of heat-protective coat. Proposed coat ensures heat and impact protection of object and self-sealing in case of damage of coat under action of highly intensive fluxes of energy, high-velocity kinetic strikers and extreme atmospheric conditions.

EFFECT: enhanced efficiency and reliability.

1 dwg

Supersonic rocket // 2237858
The invention relates to the field of rocket technology, in particular to the protection devices of the rocket body from heat

The invention relates to protection against laser weapons aerospace systems and storage of hydrocarbon fuel

Guided projectile // 2177139
The invention relates to rocket technology and can be used in small-sized missile shots, and artillery

Guided projectile // 2176069
The invention relates to the field of weapons and can be used in small rockets and artillery shells

FIELD: aviation.

SUBSTANCE: invention relates to the multilayered screen and vacuum isolation (SVI) with microstructural elements for spacecrafts. Each layer of SVI is implemented as a substrate on which the heat reflecting elements designed as massif of rectangular microplates are fixed. Each microplate is fixed on a substrate with a gap 10…20 mcm. On the substrate side facing towards the spacecraft the flutes with rectangular or trapezoidal section, and also longitudinal depressions with semicircular cross-section are implemented. The second and the subsequent layers of SVI are attached to the previous layers through the spherical spacers installed between plates. The diameter of spacers is no less than the size of the named gap. In the places of installation of spacers the layers of silicon dioxide with the thickness 0.5…1 are applied. The aluminium coating with the thickness 0.1…0.3 microns with the reflection factor 0.7-0.9 is applied on external surface of microplates and open surfaces of the substrate. Microplates can be bimorph. Microplates are manufactured with conducting buses on the surface of the silicon substrate.

EFFECT: decrease of weight and overall dimensions of EVI and spacecrafts.

7 cl, 7 dwg

Protective coating // 2542795

FIELD: aircraft engineering.

SUBSTANCE: this coating is composed by aluminium foil covering spacecraft components. Foil outer side has aluminium oxide ply, at least 30 mcm thick, applied by micro-arc oxidation thereon. Said aluminium foil is either mechanically secured to protected components or glued thereto. Tests and calculations show that said coating ensures active life of spacecraft for over 15 years.

EFFECT: longer life under effects of spacecraft engine plasma effects.

3 tbl

FIELD: chemistry.

SUBSTANCE: multilayered coating contains three successive layers with an even thickness: a lower mirror metal radio-reflecting skin-layer of pure aluminium, an intermediate protective thermoregulatory dielectric layer of zirconium dioxide and an upper protective wear-resistant highly strong diamond-like carbon layer.

EFFECT: provision of the operation in extreme conditions of open space due to the application of a thin substrate-envelope from a polymer composite material.

3 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed attachment comprises rib with yoke and four extra threaded bosses with threaded ears, arc with four extra threaded bosses with threaded ears and lugs, braces, bosses, fasteners, lock nuts and clamp. Thrust plate with bolt is secured at said yoke. Threaded bush for mounting extra braces is fitted at lug threaded section and cotter-pinned thereat.

EFFECT: higher stiffness of attachment.

4 cl, 14 dwg

FIELD: transport.

SUBSTANCE: invention relates to space engineering and concerns creation of a temperature-regulating material for applying to a space object (SO) surface. The temperature-regulating material contains a substrate in the form of an optically transparent glass, a highly-reflective layer of silver, a protective layer. The highly-reflective layer of silver has a width of 0.10÷0.15 micron. For the protective layer stainless steel with thickness of 0.10÷0.20 micron is used. On the protective layer an epoxy varnish with thickness of 20÷30 micron is applied. Prior to covering the substrate with the highly-reflective silver layer, the substrate chemical cleaning is performed with simultaneous ultrasound treating for 3 minutes. Then the substrate is removed from the solution, rinsed successively with warm, cold and distilled water, each time for 1-1.5 min, and dried in the air. The surface is treated with glow discharge for additional purification and activation of the substrate surface. Then, the highly-reflective layer and the protective layer is successively applied in a vacuum chamber by magnetron sputtering without the vacuum chamber unsealing in one technological cycle successively positioning the substrate under the sources with a silver target and a stainless steel target. On the substrate with the highly-reflective layer and protective layer, the epoxy varnish layer of 20÷30 micron in thickness is applied for additional protection against atmospheric corrosion and for better adhesion of the coated substrate to adhesive composition. During temperature-regulating material attachment, material bonding using an adhesive composition with an electroconductive filler is performed with the help of weights. As the electroconductive filler, aluminium or silver powder is used in a quantity of 20±5% and 10±5% respectively. This powder provides required electroconductive properties of the temperature-regulating material surface.

EFFECT: better radiant heat characteristics of material, higher processability of coating, higher adhesion values of the coated substrate to the SO body surface.

3 cl, 2 dwg

FIELD: chemistry.

SUBSTANCE: invention relates to temperature-control materials used in space equipment, particularly as a blanket outer layer on outer surfaces of spacecraft with electrical grounding on the body of the spacecraft or as a temperature-control coating of the "solar reflector" category when deposited using an adhesive electroconductive layer on outer surfaces of spacecraft. The multifunctional composite material consists of sheets of transparent dielectric substrate material with an electroconductive coating on the outer surface and a reflecting layer at the back of the substrate. The electroconductive reflecting layer is in form of a metal film with high reflecting power in the wavelength range of 0.3-2.4 mcm. The electroconductive coating is transparent in the wavelength range higher than 0.7-1 mcm, with a reflection coefficient in the wavelength range below 0.6 mcm and surface resistivity of the electroconductive coating in the range from 5 kohm/cm2 to 5×105 kohm/cm2. The electroconductive coating comprises at least three layers, one of which is an electroconductive light-reflecting layer, the second is an additional electroconductive layer which provides the required electroconductivity of the coating, and a protective layer. The protective layer is on the back of the substrate. All layers of the material are radiation-resistant.

EFFECT: high efficiency, reliability, resistance to external action and longer working life of the material.

5 cl, 1 dwg, 1 tbl

FIELD: aircraft engineering.

SUBSTANCE: proposed system comprises composites with ceramic matrix reinforced by heat-resistant fibers and including sublimable solid substance. Said solid sublimable substance comprises stabilised pre-ceramic organosilicon polymers containing atoms C, Si and H as well as germanium heteroatoms. Heat-resistant layer as a ceramic matrix comprises carbides or borides of refractory metals or their mixes. Besides, sublimable solid substance can include refractory metal germanates.

EFFECT: efficient heat protection.

10 cl, 5 ex

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. In compliance with first version, fuselage comprises area with floor including one or several floor panels Floor panels exhibit anti-burning-through properties with respect to flame acting at outside of aircraft fuselage towards said area for at least four minutes Aircraft fuselage area above said floor does not includes anti-burning insulation In compliance with second version, fuselage comprises area with floor and wing/fuselage cowling Floor panels exhibit anti-burning-through properties with respect to flame acting at outside of aircraft fuselage towards said area for at least four minutes Area under said cowling does not include anti-burning-through insulation

EFFECT: decreased weight of aircraft.

8 cl, 6 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft and aerospace engineering, particularly, to hypersonic craft thermal protection. Hypersonic craft wing comprises heat emission layer 2 arranged at its surface connected via onboard electric power using circuit 7 with electrically conducting element 3. Electrically conducting element 3 is thermally connected via insulating layer 4 with channels 6 communicated with onboard thermal control system cooling line. Aforesaid heat emission layer 2 is arranged at wing outer surface nearby leading edge. Electric conductor 3 is arranged at insulating layer 6 nearby wing trailing edge.

EFFECT: reduced temperature of heating, higher reliability and lower drag.

2 cl, 1 dwg

FIELD: transport.

SUBSTANCE: invention relates to passive thermal protection of, in particular, spacecraft instrumentation and equipment. Thermostatic material comprises outer and reinforcing layers and thermostatic layer arranged there between. Outer layer is composed of polyimide film metalised on inner side that features thickness equal to or smaller than 12 mcm. Reinforcing layer consists of aramide thread with surface density of < 25 g/m2. Thermostatic layer is based on polyimides, or polyether imides, or polysulfones and introduced between said outer layer and reinforcing layer by welding.

EFFECT: stable optical parameters, higher breaking point and decreased weight.

1 dwg

FIELD: chemistry.

SUBSTANCE: invention relates to composite materials and deals with a device for the protection of composite materials against electromagnetic influence. A hardening flexible resistant to electromagnetic influence laminate includes a layer of an electroconductive metal material and a thermoresponsive polymer, in which the outer surface of the laminate includes a detachable sheet of a substrate in contact with the polymer, and the laminate additionally includes a practically non-transformable sheet of a solid material.

EFFECT: invention provides the creation of the laminate, resistant to an electromagnetic influence, which does not stretch and transform under high loadings, produced by an automatic device for the tape placement.

17 cl, 13 dwg, 1 tbl, 6 ex

FIELD: transport.

SUBSTANCE: invention relates to connection of aircraft fuselage section with adjacent section. Fuselage element contains the first section. The section includes plating and connecting devices made with possibility of connecting the first section with adjacent second section. The section goes along fuselage longitudinal axis. Fuselage element also contains stiffening elements (stringers) passing along longitudinal axis. Herewith, end of longitudinal stiffening element goes out of free edge of the first section plating for predetermined length.

EFFECT: simplification of fuselage sections assembling, force transfer between sections, lower mass.

14 cl, 4 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to assembly of aircraft cabin and building it in aircraft airframe. Proposed device comprises mounting frame intended for preassembly of aircraft cabin section and drive system for attachment of preassembled cabin part to said mounting frame and for sliding it therefrom to aircraft airframe open section. Said drive system is composed of the guide system including the guide and several retainers for attachment of preassembled aircraft cabin section to mounting frame.

EFFECT: accelerated assembly of aircraft airframe and cabin.

11 cl, 9 dwg

Honeycomb // 2507113

FIELD: transport.

SUBSTANCE: invention relates to honeycomb sandwiches. Sandwich panel honeycomb is composed by 3D structure of composite regular hollow hexagon prisms having common face with every adjacent face. Sandwich panel honeycomb is composed by of composite regular hollow triangular or tetrahedral or hexagon prisms with walls reinforced by unidirectional fibres and composed by crossed bards. In compliance with second version, sandwich panel honeycomb is composed by 3D structure of composite regular hollow hexagon prisms having common face with every adjacent face. Walls of hexagon prisms are made of bars each directed at preset angle to its base, with one bar crossing horizontally the prism face centre.

EFFECT: decreased weight, better performances, longer life.

3 cl, 12 dwg

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