Transition device from missile nose cone ceramic jacket to missile case
 Multipath reflector antenna / 2336615Invention concerns radiotechnics, particularly antenna devices generating multipath beam of directional patterns. Multipath reflector antenna includes parabolic reflector in the form of parallel conductive plates, and focus-offset irradiators. Plate edges form reflector surface. Distance between plates varies according to a linear rule depending on a value in a range from not more than λsh/2 to λl/2, where λsh and λl are respectively minimal and maximal wavelength of operating frequency band. Irradiators feature linear dependency of beamwidth on wavelength, and beamwidth of lower operating band frequency corresponding to its aperture size over λl. |
 Method of radio communication antenna extension and reverse folding / 2336610Invention concerns radioelectronics and can be applied in design of flexible antennas for radio receiving and transmitting devices. According to the claimed method, antenna is manufactured to produce an effect of paper "Chinese finger" operation in the form of flexible radio receiving and transmitting rod encased in a housing of ductile non-stretchable material. Ductile non-stretchable housing encasing the rod is hollow. Housing base and top are rigidly connected to the rod ends. Lower antenna base is equipped with excessive/low pressure source driven by an electronic circuit, which pumps working agent and creates excessive/low pressure inside the housing to improve receiving and transmission properties of radio relay promptly due to antenna rod spreading to necessary length. |
 Developable specular reflector / 2336544Invention is related to machine building, in particular, to developable specular reflectors (DSR), which are used for research of space beams and carried into orbit in folded condition in limited volume of carrier-rocket fairing. Substance of invention consists on developable specular reflector, which contains reflecting surface made of cells, mechanisms of development, hinges and fixators, in contrast to available one, every cell is made of focusing surface in the form of Fresnel surface, and flat installation surface, at that focusing surfaces create concentric circumferences with single focus, at that cells are equipped with adjustment mechanisms of Fresnel surface, which are made of regulation part fixed on Fresnel surface and connected to installation part of calibration mechanism by means of hinge fixed on installation surface. |
 Twin reflector rhombic antenna / 2334318Twin reflector rhombic antenna containing conductors arranged along the rhomb sides and forming a long line connected to resistance equal to its wave impedance on one side, and, on other side, connected to the supply lines, is furnished with two flat conducting screens (reflectors). The first reflector is arranged at a certain angle to the rhomb plane and at a certain distance from it. The second reflector is identical to the first one and is arranged in symmetry about it relative to the rhomb plane. Note that the line of intersection of the reflectors' planes is perpendicular to the rhomb lengthwise diagonal. |
 Method of reduction of frequency dependence of abatement at passing of electromagnetic wave through dielectric envelope simultaneously for parallel and perpendicular polarisation and facility for its implementation (vectorial blister) / 2334315Introduced Vector blister is intended for protection of linear-polarized antenna, particularly - for fissural phased-array. Method of reduction of frequency dependence of abatement at passing of electromagnetic wave through the dielectric envelope simultaneously for parallel and perpendicular polarisation is achieved by formation form dielectric envelope space figure, which allows in one plane in cross section zigzag shape in increments of preliminary equal to half of wavelength, corresponding to range medium at that envelope is oriented in space thereby, that vector E of electromagnetic wave parallel to surface, where envelope cross section is of zigzag shape. Honeycomb structure allows vectorial properties and functions as polarising filter which efficiently inhibit. Layer which provides blister strength and allows of most high value of dielectric conductivity, is implemented as envelope with superficial instability, which is of zigzag shape in cross-section in increments of preliminary equal to half of wavelength, corresponding to range medium, at that outside current layer is covered by thin-shell protective envelope, providing blister erosion protection and inside - is covered by thin-shell processing envelope, which excludes possibility of blister body particles hit into internal space. Space between outside and inside envelopes is filled by dielectric of low dielectric conductivity and high strength property, e.g. honeycomb structure. Vector blister is oriented in space relative to antenna in such a way that vector E of electromagnetic wave is parallel to plane, where cross-section of envelope is of zigzag shape. Vector blister can be used in the capacity of airplane blister for protection of linear-polarised antenna. |
 Plane antenna / 2334314Antenna is implemented in the shape of rectangular metal plate (1) or plate of clad dielectric material with slotted L-shaped groove (2), is mounted perpendicularly to conducting screen (3) and connected to it galvanically. Width of groove section (2), which is parallel to conducting screen (3), two times less then width of groove section (2), perpendicularly to conducting screen (3), and length of groove section (2) is equal to 1/3 of wavelength. In plate (1) of dimension 1/3-1/5 of wavelength are implemented at both sides of L- shaped groove (2) rectangular holes (4, 5), at that distance from holes edges (4, 5) till adjoin it plate edges (1) or groove edges (2) is 2-3 of groove section width (2) which is perpendicularly to conducting screen (3) and perpendicular edges of plate (1) are connected to appropriate holes edges (4, 5) by slot lines (6, 7) of width 0.5-1.5 mm. Coaxial cable armature is connected to conducting screen (3), and internal thread is connected to groove section (2) which is parallel to conducting screen from the groove end (2) at a distance 1/4-1/3 of groove length (2). |
 Spacecraft and section of phased antenna array / 2333139Spacecraft includes the phased antenna array (PHAA) representing flat rectangular sections, each of them the structures furnished with a front covering fitted on the carcass. The spacecraft onboard equipment is fixed on the rear sides of the flat hardware platforms arranged at the PHAA sections rear. In placing the spacecraft into orbit, the PHAA sections are folded with their faces parallel to each other, with solar batteries panels being inserted there between. Transceiver units are arranged on the front covering rear with their radiator on the covering face. Thermal pipes are arranged inside the front covering and connected with the device of heat withdrawal into space. The suggested PHAA section contains a carcass, the a front skin, a transceiver units and radiators. The section carcass is made up of rectangular closed section channels furnished with an extra internal strip. The front covering made up of three-layer panels is attached to the said strip. A screen-vacuum heat-insulation layer is arranged between the aforesaid panels. The outer panel is made from carbon-based plastic material, the inner panel is made from aluminum alloy. The inner panel honeycomb structure accommodates heat pipes withdrawing heat from the transceiver units. |
 Horn radiator / 2332759Invention can be used as transceiving antenna in measuring systems of radar matrix of various objects dispersion in selected polarising basis. Horn radiator contains square or round waveguide and horn with gear structured edge. The horn is pyramidal of square cross-section, or conic of round cross-section. Between wave guide and horn throat there is matching pyramidal horn of square cross-section or conic one of round cross-section. The length of matching horn generator is equal to quarter of average length of propagating wave. Square side size of matching horn or throat cross-section diameter is equal to wave guide cross-section size. Teeth of gear structure are made in the form of rectangles, their height, width and distance between them being equal to odd number of quarters of wave length in free space. |
 Combined irradiator / 2332758Combined irradiator contains low-frequency round wave guide in which the polariser is mounted, and high-frequency round wave guide attached to low-frequency wave guide, high-frequency wave guide axis being perpendicular to low-frequency wave guide axes. The polariser is designed as selective screen inclined in wave guide and consisting of thin dielectric plate with dense lattice made of resonant dipole elements with frequency tuned to high-frequency range. The polariser contour is ellipse-shaped. Polariser dipoles are oriented perpendicular to low-frequency wave guide axes and at an angle of 45 degrees to electric field vector plane of a low-frequency wave. Electric field vector of high-frequency wave is parallel to dipoles. The irradiator generates low-frequency waves of circular polarisation and high-frequency waves of linear polarisation. High-frequency wave travels down on gradient junction formed by the polariser and low-frequency wave guide wall. |
 Flexible carcass / 2331994Invention relates to the production of various-purpose structures with varying shape, for example, spacecrafts or parabolic antenna reflectors. The flexible carcass consists of a rigid frame and forming modules made as branches consisting of cylinder working surface elements running one over another and coupled by flexible links laid along their edges. One ends of the flexible links are fastened on the branch ends, while the other ones pass through the frame and are coupled with the control system by flexible links. |
 Radio-absorbing cover / 2243899Cover is formed in form of layer on basis of fiber, placed between outer and inner layers of dielectric materials. Fiber layer along thickness is formed of several cloths of textile material of synthetic filaments with carbon cover with specific electrical, in which adjacent cloths are interconnected by inserts of given thickness on basis of dielectric connecting substance. Outer layer is made of rubber. Inner layer is made of dielectric connecting substance, containing granulated material, weakening reflection of electro-magnetic waves, in amount of 5-25% of total. |
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Composite material for shielding electromagnetic emission and a method for manufacture thereof / 2243980 Invention discloses a method for manufacturing composite material for shielding-mediated protection against electromagnetic emission and can be used in electronics, in radio engineering, and also in a series of special-destination articles. In addition, material may be used for anechoic boxes and in various assemblies of technical devices and radio apparatuses. Method comprises mixing modified graphite-containing conducting filler and polymeric binder at weight ratio (50-80):(20-50). Once ingredients combined, mixture is additionally subjected to thermal expansion in thermal shock mode at 250-310оС and then molded. Polymeric binder is selected from polyolefins, polystyrene, fluoroplastic, polyvinylchloride paste and modified graphite is product obtained by modifying graphite with concentrated sulfuric and nitric acids. Material is characterized by that, in wavelength band from 2 to 5 cm at thickness of material up to 0.1 mm, transmission coefficient is decreased from -40 to -85 dB. |
 Helicopter with radar antenna / 2245820Radar antenna is located under fuselage and is provided with mechanisms for rotating it relative to vertical axis and turning it relative to horizontal axis. Rotation mechanism has body consisting of two parts; one part is secured in fuselage and other part is rotatable relative to first one. Radar antenna is secured on frame through strip on which charge for emergency jettisoning is mounted; said frame is connected with movable part of body by means of supports; one end of each support is connected with movable part of body and other end is connected with frame by means of axle. Rotation mechanism of radar antenna is mounted on movable part of body and is made in form of rod performing reciprocating motion by means of drive; its one end is connected with frame by means of axle and bracket. Mounted on fixed part of body is drive of mechanism turning the radar antenna relative to vertical and horizontal axes. |
 Composition for absorption of electromagnetic emission and a method for preparation thereof / 2247759Invention relates to a method of preparation and to composition of magneto-dielectric materials absorbing electromagnetic emission. Composition is prepared by combining binder with superdispersed magneto-dielectric filler, in particular composite product obtained through caking at 1150-1250°C followed by disaggregation of cake composed of magnetic particles of ferrite material (61.5-86.7 vol %) obtained by chemical precipitation of ferrite phase from aqueous solutions, the rest being layers of dielectric oxides precipitated onto surface of magnetic particles by way of nanomolecular layering from gas medium. Invention further discloses composition including 65-75 vol % of superdispersed magneto-dielectric filler along with binder prepared by above-indicated method. |
 Composition for absorption of electromagnetic emission and a method for preparation thereof / 2247760Invention relates to a method of preparation and to composition of materials absorbing electromagnetic emission. Composition is prepared by combining binder with ferrite, the latter containing 60-90% of ferrite material obtained according to high-temperature ceramic technology and ground to microparticle size and 10-40% of particles belonging to ferrite phase obtained by chemical precipitation from aqueous solutions onto surface of ferrite material microparticles. Ferrite is calcined in the form of isolated precipitate at 500-600°C and then disaggregated. Invention further discloses ferrite-based composition containing 9-13% binder obtained by above-indicated method. |
 Transceiving antenna / 2249280Proposed superbroad-band antenna characterized in passband extended to six octaves with fixed low-pass transmission windows is disposed in plane perpendicular to screen and has radiators made in the form of three monopoles that form funnel-shaped directivity pattern in elevation plane and omnidirectional pattern in azimuth plane. Electric length of radiators and distances between axes of central radiator and side ones are stipulated. In addition radiators and matching device or matching device only are disposed in space filled with insulating material having dielectric constant not over 2.0. This space may be shaped as elliptical cylinder or elliptical truncated cone. Other dimensions of antenna are specified. Cone may be interpolated by polyhedron with minimum four apexes whose pointed edges are rounder off at radius of minimum 0.01λm. |
 Ship / 2249535Ship has metal hull and superstructure which is made from multi-layer polymer composite material. Ratio of superstructure area to hull area shall be no less than 0.54; metal members built in superstructure are coated with radio-absorbing external layer. Open cavities in hull and in superstructure are provided with detachable shields made from material reflecting the radio waves. Provision is made for forming false radar targets for receiving enemy missiles and effective protection of personnel against radiation of own radar facilities. |
 Horn antenna / 2250542Proposed horn antenna 1 (Fig. 1) that can be used in metrology, in communication systems, in solving problems of electromagnetic compatibility and is characterized in low level of cross-polarization component of field and linear phase-frequency characteristic has rectangular horn 2 whose butt-end is closed with metal plug 6 that mounts coaxial connector, as well as first, second and third metal ridges 3, 4, and 17, respectively; two first opposing faces 8 and 9 of rectangular horn 2 are made of metal in the form of equilateral trapezium and other two faces 11 and 12, in the form of a number of contact members 13 whose leads are electrically connected to respective metal faces 8 and 9. First metal ridge 3 is mounted in center of metal face 8, second and third metal faces 4 and 17 are mounted on metal face 9 symmetrically relative to first metal ridge 3 either side of the latter; first metal ridge 3 is connected on metal plug 6 to central conductor of coaxial connector; second and third metal ridges 4 and 17 are connected on metal plug 6 to ground conductor of coaxial connector. Relevant equations describing shape of metal ridges are given in description of invention. |
 Antenna assembly / 2251767Novelty is that separating screen is newly inserted in antennaassemly metal reflector in the form of cylindrical surface with part of (O.6 - 1.4)λ width cut along generating line, where λ is wavelength; this screen is disposed in symmetry axis within reflector to create two in-phase excited apertures and functions to narrow directivity pattern in H-plane. In this way proposed antenna incorporates provision for two-fold narrowing of directivity pattern in H-plane (to 30 - 60 deg.) while maintaining narrow (about 20 deg.) directivity pattern in E-plane. |
 Circular-polarization microstrip antenna / 2251768Proposed antenna that can be used in production of various receiving, transmitting, and transceiving antenna assemblies including phased antenna arrays has microstrip line with exciting structure on one end and ground conductor, on other that has slots functioning as radiators; these relatively perpendicular slots are disposed on adjacent sides of square radiator each of whose sides equals half-wavelength; radiator is coupled with slots through first and second insulating layers; dielectric constant of second insulating layer is twice as high as that of first insulating layer; slots are series-excited by means of one section of microstrip line. |
FIELD: weapons.
SUBSTANCE: transition device from missile nose cone ceramic jacket to missile case contains an adapter, connected to the jacket with an elastic compound, made from material, which is similar to the jacket material in linear expansion temperature coefficient in the given temperature range, annular fastening ledge. The device is additionally equipped with a course, made from viscoelastic material and located in the void, constituted by jacket surfaces, adjacent to the course, surface of adapter, support element and external delimiter of course movement. At that, support element and external delimiter of course movement are either made as a whole, or fixed to each other. Besides, they are a constituent part of adapter in the shape of ring with a bore in front butt end or in both butt ends. Supplementary course from viscoelastic material can be installed between rear butt end of the support element and the adapter.
EFFECT: increase of construction durability and manufacturability and decrease of weight.
2 cl, 1 dwg
The invention relates to the field of aviation and rocket technology, primarily to the device to transition from the ceramic lining of the fairing to the metal body of the rocket.
Ensuring reliable connections ceramic shell metal body of the rocket is challenging experimental and theoretical character.
Known vehicle according to patent EP 0828312, IPC 6 01Q 1/42, 1/28, 1997, including ceramic membrane made of porous alumina ceramics and attached face to the metal body of the rocket using solid solder through the metal adapter, consistent temperature coefficient of linear expansion (TCLE) ceramics having a low radial stiffness due to its low thickness.
The main disadvantages of this design are the complexity of the Assembly and the impossibility of its application for heavy duty fairings with a shell of silica ceramic, glass-ceramic, glass-ceramic whose thermal expansion and tensile strength significantly lower than that of alumina ceramics.
The closest analogue of constructive solutions, in which the inner surface of the ceramic shell is connected with an elastic adhesive (resin) with an adapter, it is design patent of the Russian Federation No. 2225664 IPC 6 is 01Q 1/42, 2002, including ceramic shell, glued elastic adhesive with the outer surface of the thin-walled metal adapter from a material approved by TCLE in a predetermined temperature range with the sheath material, and located on the outer surface of the tail portion of the adapter extending beyond the end face of the shell, the retaining ring clamp to connect using wedges with the body of the rocket.
The main disadvantage of constructive solutions for the prototype is that reducing weight by reducing the thickness of the ceramic shell in its end region, the thickness of the adapter, as well as the length of the collar joint portion of the rocket body leads to a decrease in the carrying capacity of the shell (because of the increased likelihood of its destruction in the end part).
The destruction is due to the concentration of the contact stresses in the compression zone of the end part of the membrane from the concentrated end force caused when opening the junction of the end face of the ceramic shell when exposed to an asymmetrical power loads, as well as from changing around the perimeter of the supporting surface pliability in the axial direction of the end portion of the rocket body at the expense of locally evenly spaced therein through-holes (Windows) to install the mounting wedges. This is true for both shells made of quartz ceramics, the AK and shells of glass ceramics.
Poster research tests the nose of the missile of class "air - ground" with the design of the device to transition from the ceramic shell of the ceramic to the metal body of the rocket, similar to the prototype, the authors identified significant importance for the carrying capacity of the shell structure of the butt portion of the rocket body and the structural properties of the structural elements of the transition. Were recorded following the destruction of the shell in the zone of compression of the end portion of one longitudinal crack at a design compression stress
(σcalc -in ceramics, commensurate with the value of its average values of ultimate tensile strength (σin cp); two longitudinal cracks running from the edges of the mounting window of the rocket body in the zone of compression, when the σcalc -commensurate with σin cf.
The use of ceramic for the manufacture of shell fairing gives a definite advantage in weight compared to use for this purpose quartz ceramics at comparable satisfaction radio requirements, but the stricter requirements to the weight of the construction forces to consider the possibility of its reduction and by reducing the thickness of the shell in the area of bonding with the adapter, the thickness of the adapter in the field of scle the key of his shell, the thickness in the axial direction of the fixing clamp of the rocket body while maintaining the carrying capacity of the ceramic shell by reducing stresses in the front part of the shell.
Thus, maintaining the carrying capacity of the membrane by reducing the weight of the transition requires the introduction of new elements that reduce the vulnerability of the front part of the shell in the region of compression, since the destruction of its fixed bench trials, begins with this area.
The technical result of the invention is to increase the carrying capacity of the shell - reducing the likelihood of its destruction in front part from compressive efforts, improving the technological design of the transition from the ceramic shell to the metal body of the rocket, reducing the weight of the structure.
This technical result is achieved by the fact that:
1. The device transition from the ceramic shell nose fairing of the rocket to its case, including an adapter connected to the shell with an elastic compound, made of material approved by TCLE in a predetermined temperature range with the sheath material, and located on the outer surface of the tail portion of the adapter extending beyond the end of the shell mounting ring clamp, characterized in that the end region of the sheath placed both the IKE of the elastic-viscous material in the cavity, formed adjacent to the side surfaces of the shell, adapter, support element and the outer limiting movement of the shell, while supporting element and limiter movements shells made in one piece or rigidly connected between a material of the rocket body or adapter, the edge of the sock outer limiting movement of the shell is displaced toward the nose of the fairing relative to the end face of the ceramic shell, the inner surface of the outer limiter movements shell formed straight or curved generatrix of the body of rotation is made extending to the nose fairing and cowling in this area ravintolana or variable thickness, decreasing to the edge of the sock outer limiter movements shells, besides supporting element and outer limiter movements shells conducted as part of the adapter in the form of a ring with the groove of the front end or both ends associated with the adapter mechanical or klemenhagen connection, or made in one piece with the adapter for homogeneity of their materials.
2. The device transition from the ceramic shell nose fairing of the rocket to its housing according to claim 1, characterized in that between the rear face of the support element and the adapter installed additional shell of elastic-Vaskov the material.
The drawing shows a structural diagram of the transition from the ceramic shell 1 to shell 2 rocket. The shell is connected with the adapter of the Invar alloy 3 with an elastic compound 4 and the adapter with the body of the rocket - using wedges 5, are installed through the mounting of the window 6 in the forward part of the rocket body. In the area of the end part of the shell is shell 7 made of elastic-viscous material. Shell is located in the cavity between the surfaces of the ceramic shell, adapter, support element 8 and the outer limiting movement of the shell 9.
Installing shell of elastic-viscous material (silicone sealant-type Sealers) in the area of the end part of the casing and the organization of the means of limiting its movement in the radial direction due to the introduction of the external limiting movement of the shell provided with a reliable execution of the specified modes thermal loading of the developed device to transition from the ceramic shell nose fairing of the rocket to its body (bench test design was conducted using full-scale second compartment of the rocket and the exhaust elements of wedges).
The implementation of the support element and the outer limiting movement of the shell in the form of a ring with the groove of the front end face or the both exhibitions of its ends, related adapter mechanical or klemenhagen connection, or made in one piece with the adapter for homogeneity of their materials, allows to implement various modifications of the shapes and sizes of shells depending on the mode of operation of the product, design and technological considerations and depending on experimental and theoretical studies when choosing the material of the shell and its deformability from operational impacts.
The introduction of an additional shell 10 of the elastic-viscous material (silicone sealant-type Sealers) between the rear face of the support element and the adapter (clamp) enhances the positive effect of the shell, located in the region of the front end of the support element, simplifies manufacturing technology design (reduces stiffness tolerances in the manufacture of its components) and the technology of its Assembly.
Execution of the external limiting movement of the shell and the support element for one simplifies the design, and the use of their "getcompanyname" allows you to limit the radial movement of the shell by applying for limiting movement of the shell, for example, materials based on carbon fibers.
The offset edges of the sock outer limiting movement of the shell to the nose of the fairing relative to face the ceramic shell rationally, but due to the convergence of the ends of the shell and the support element in the zone of compression from an unbalanced forces acting on the fairing it might shift the minimum commensurate with the thickness of the power holding the elastic layer of the compound in connection adapter with the inner surface of the ceramic shell.
Performing inner surface of the outer limiter displacements of the shell, extending to nose fairing, due to greater efficiency to prevent leakage of the shell (self-closing "gateway" when unbalanced forces) in the gap between the edge of the sock outer limiting movement of the shell and the surface of the ceramic shell. From technological considerations (simplification of the manufacturing elements of the fairing) shell in this area may be of equal thickness was or variable thickness, decreasing to the edge of the sock limiter her movements.
The proposed solution it is advisable not only for the V-connection adapter with the case, but for other types of connections the rear of the adapter with the butt of the structural elements of the transition from the ceramic shell nose fairing missiles of different classes to her body.
1. The device transition from the ceramic shell nose fairing of the rocket to its design, including a power is nick, connected with the shell elastic compound made of a material approved by the temperature coefficient of linear expansion (TCLE) in a predetermined temperature range with the sheath material, and located on the outer surface of the tail portion of the adapter extending beyond the end face of the shell, the retaining ring clamp, characterized in that the end region of the sheath placed shell of elastic-viscous material in the cavity formed adjacent to the side surfaces of the shell, adapter, support element and the outer limiting movement of the shell, while supporting element and limiter movements shells made in one piece or rigidly linked from housing material missiles or adapter, the edge of the sock outer limiting movement of the shell is displaced toward the nose of the fairing relative to the end face of the ceramic shell, the inner surface of the outer limiter movements shell formed straight or curved generatrix of the body of rotation is made extending to the nose fairing and cowling in this area ravintolana or variable thickness, decreasing to the edge of the sock outer limiting movement of the shell, in addition, the supporting element and the outer limiter movements shells conducted as part of perehodnik the form of a ring with the groove of the front end face or both end faces, related adapter mechanical or adhesive-mechanical connection, or made in one piece with the adapter for homogeneity of their materials.
2. The device transition from the ceramic shell nose fairing of the rocket to its housing according to claim 1, characterized in that between the rear end of the support element and the adapter installed additional shell of elastic-viscous material.