Solid-propellant rocket engine nozzle |
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IPC classes for russian patent Solid-propellant rocket engine nozzle (RU 2440506):
 Solid-propellant rocket engine with turning control nozzle (versions) / 2428579
Solid-propellant rocket engine includes combustion chamber and hidden turning control nozzle with thermal-protective coating, which is attached to it. Charge consists of two parts separated with partition; at that, larger part of the charge, which is located between front bottom and partition, is made from high-temperature propellant, and smaller charge part, which is located above hidden part of the nozzle, is made from low-temperature slow-burning propellant. Smaller charge part has shaped surface providing the flow of combustion products, which is close to constant flow. As per one of the versions of rocket engine the partition is made in the form of disc with flanging along central hole in it. Inner surface of flanging encloses the front point of nozzle so that annular gap the value of which remains constant during turning of the nozzle is provided. As per another version, between partition and nozzle, on inlet part of nozzle, on ribs there installed is the ring the inner surface of which encloses the front point of nozzle with the gap the size of which remains constant during nozzle turning. Outer surface of ring has spherical shape with the centre coinciding with centre of rotation of the turning nozzle and forms a spherical hinge together with partition.
 Rocket engine rotary nozzle / 2403427
Proposed nozzle comprises stationary part, rotary part arranged on the engine elastic support hinge, baffle made on stationary part with gap in rotary part and heat protecting element. The latter represents an elastic ring formed by spiral coils of heatproof material, for example wound on rubber cord to roll in recesses made in the baffle and nozzle rotary part.
 Control method of thrust vector of liquid propellant engine / 2391546
Control method of thrust vector of liquid propellant engine consists in installation of control engines of smaller thrust together with fixed chamber of the main propulsion engine with possibility of movement in mutually perpendicular planes and with further movement of control engines in mutually perpendicular planes during the flight. Control engine is placed axisymmetrically with possibility of movement in mutually perpendicular planes inside the cooled cover of the chamber of the main propulsion engine so that the flow of its combustion products flows simultaneously with flow of combustion products of the main propulsion engine, thus providing deflection of vector of flow velocity of combustion products of control engine owing to movement of its chamber in gimbal mounting.
 Rocket engine rotating nozzle / 2309281
Proposed nozzle contains movable diffuser 20 and fixed part 16 rigidly attached to rear wall of engine combustion chamber 12. Cardan joint couples movable diffuser of nozzle with fixed part. Movable diffuser and fixed part contact through corresponding spherical surfaces 24a, 16a, and drive device acts onto movable diffuser to change direction of engine thrust vector by changing orientation of nozzle at sliding of spherical surfaces one along the other. Flexible return devices 62, 64 arranged between movable diffuser 20 of nozzle and fixed part 16 acting onto movable diffuser and pressing it to fixed part to preserver relative contact between spherical surfaces 24a, 16a at any required orientation of nozzle.
 Nozzle with thrust vectoring / 2168047
The invention relates to the field of turbojet aircraft engines used on supersonic combat aircraft
 Adjustable nozzle for aircraft engines with thrust vectoring / 2142571
The invention relates to the field of aircraft engines, in particular to adjustable supersonic nozzles for turbojet engines
 Swivel hanger for installation of reactive camera on an aircraft / 2090773
The invention relates to the field of jet engines, and more specifically to a device articulated suspensions (GSR), enabling rotation of the jet chamber (RC) relative to the aircraft (LA) for flight control
Rocket engine rotating nozzle / 2309281
Proposed nozzle contains movable diffuser 20 and fixed part 16 rigidly attached to rear wall of engine combustion chamber 12. Cardan joint couples movable diffuser of nozzle with fixed part. Movable diffuser and fixed part contact through corresponding spherical surfaces 24a, 16a, and drive device acts onto movable diffuser to change direction of engine thrust vector by changing orientation of nozzle at sliding of spherical surfaces one along the other. Flexible return devices 62, 64 arranged between movable diffuser 20 of nozzle and fixed part 16 acting onto movable diffuser and pressing it to fixed part to preserver relative contact between spherical surfaces 24a, 16a at any required orientation of nozzle.
Control method of thrust vector of liquid propellant engine / 2391546
Control method of thrust vector of liquid propellant engine consists in installation of control engines of smaller thrust together with fixed chamber of the main propulsion engine with possibility of movement in mutually perpendicular planes and with further movement of control engines in mutually perpendicular planes during the flight. Control engine is placed axisymmetrically with possibility of movement in mutually perpendicular planes inside the cooled cover of the chamber of the main propulsion engine so that the flow of its combustion products flows simultaneously with flow of combustion products of the main propulsion engine, thus providing deflection of vector of flow velocity of combustion products of control engine owing to movement of its chamber in gimbal mounting.
Rocket engine rotary nozzle / 2403427
Proposed nozzle comprises stationary part, rotary part arranged on the engine elastic support hinge, baffle made on stationary part with gap in rotary part and heat protecting element. The latter represents an elastic ring formed by spiral coils of heatproof material, for example wound on rubber cord to roll in recesses made in the baffle and nozzle rotary part.
Solid-propellant rocket engine with turning control nozzle (versions) / 2428579
Solid-propellant rocket engine includes combustion chamber and hidden turning control nozzle with thermal-protective coating, which is attached to it. Charge consists of two parts separated with partition; at that, larger part of the charge, which is located between front bottom and partition, is made from high-temperature propellant, and smaller charge part, which is located above hidden part of the nozzle, is made from low-temperature slow-burning propellant. Smaller charge part has shaped surface providing the flow of combustion products, which is close to constant flow. As per one of the versions of rocket engine the partition is made in the form of disc with flanging along central hole in it. Inner surface of flanging encloses the front point of nozzle so that annular gap the value of which remains constant during turning of the nozzle is provided. As per another version, between partition and nozzle, on inlet part of nozzle, on ribs there installed is the ring the inner surface of which encloses the front point of nozzle with the gap the size of which remains constant during nozzle turning. Outer surface of ring has spherical shape with the centre coinciding with centre of rotation of the turning nozzle and forms a spherical hinge together with partition.
 Solid-propellant rocket engine nozzle / 2440506
Solid-propellant rocket engine nozzle includes fixed and swinging parts with break of profile in subsonic area of flow path and suspension assembly of swinging part. At that, outlet hole of fixed part of nozzle is made in the form of an ellipse the minor axis of which is located in the plane perpendicular to axis of oscillation.
 Liquid propellant rocket engine with controlled nozzle, and unit of bank nozzles / 2441170
Proposed engine comprises structural frame, combustion chamber with head, cylindrical section and controlled nozzle with extending tip, suspension assembly to allow driven swinging in to planes, drives secured to power ring arranged on combustion chamber, gas generator and turbo pump assembly including, in its turn, turbine, oxidiser pump, fuel pump, and gas duct communicating turbine outlet with combustion chamber head via suspension assembly. In compliance with this invention, is differs from known designs in that bank nozzles are grouped into pairs and fitted on lower power ring mounted on nozzle lower section and connected with nozzle edge. Gas generator gas fee pipelines are connected via gas and fuel three-way valves to bank nozzles. Opposite ends of gas generator are connected by gas bleed pipeline and fuel pipelines. Note here that bank nozzle units are secured on lower power ring attached to extending tip. Bank nozzle unit comprises two bank nozzles integrated in one unit. Note here that said unit includes three-way gas and fuel valves fitted between said nozzles and provided with common drive. All nozzles are equipped with ignition device.
 Solid-propellant rocket engine / 2474720
Proposed engine comprises housing and hinged nozzle, part of nozzle outer surface forms the ball that stays in contact with spherical seat made in aforesaid housing. Solid propellant features combustion product temperature nor exceeding 1500°C. Hinged nozzle and part of housing that forms spherical seat are made from metal. Branch pipe is arranged around spherical seat with sleeve screwed therein to get in contact with hinged nozzle ball part. Cylindrical section with thread is made on outer surface of hinged nozzle edge, said thread being used for kinematic element to be screwed thereon.
 Assembly method of nozzle with elastic support hinge / 2478815
At nozzle assembly, the nozzle is set to vertical position with a mating flange on a rigid base, an elastic support hinge is compressed with the specified force and moving part of the nozzle is attached to fixed part by means of locking devices. At fixation of the nozzle parts, the value of axial compression of elastic support hinge is measured, and then, a gauge with a test disc is installed inside the moving part, as per the position of which relative to the mating flange there determined is a deflection angle and radial offset value of axis of moving part relative to the axis of fixed part. Then, adjustment is performed by means of locking devices of axis position of moving part of the nozzle relative to fixed part so that the axial compression value of elastic support hinge is maintained.
 Device to suppress transverse forces by separation of reactive jet acting at jet engine nozzle, and jet engine nozzle / 2493413
Device to suppress transverse forces includes orientation devices installed on a jet engine nozzle and comprising the first unit forming a traction rod, the second unit forming a fixation link, and a driving unit. The first end of the traction rod is hingedly fixed on the nozzle. The first end of the fixation link is hingedly fixed on the combustion chamber, and the second end is hingedly fixed to the second end of the traction rod. The first end of the driving unit is hingedly fixed on the fixed structure of an aircraft, and the second end is hingedly fixed to the second end of the fixation link. Each traction rod comprises a rigid element fixed to both ends of the traction rod, an element, which is longitudinally deformed under action of compression or extension force, and facilities to disconnect the rigid element from the traction rod ends. The longitudinally deformed element is rigidly connected to two ends of the traction rod and comprises a tube stretching in the longitudinal direction of the traction rod and equipped with multiple circumferential slots. The other invention of the group relates to a jet engine nozzle, comprising the above device for suppression of transverse forces.
 Rocket engine / 2495274
Rocket engine comprises body and rotary nozzle mounted thereat in coaxially spaced radial bearings with axial bearing fitted there between. Axial bearing is arranged in circular web made in said body. Radial bearing arranged farther from nozzle outlet has its cage thrusting against axially moving sleeve with its end in contact with axial bearing.
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FIELD: engines and pumps. SUBSTANCE: solid-propellant rocket engine nozzle includes fixed and swinging parts with break of profile in subsonic area of flow path and suspension assembly of swinging part. At that, outlet hole of fixed part of nozzle is made in the form of an ellipse the minor axis of which is located in the plane perpendicular to axis of oscillation. EFFECT: invention allows improving the nozzle design reliability owing to providing the integrity of components sealing the gap between its fixed and swinging parts. 2 dwg
The invention relates to rocket technology and can be used in solid fuel engines for thrust vector control. For highly maneuverable missiles the most appropriate use of the 4-nozzle designs engines, in which a control (swing) nozzles allow simultaneously with high efficiency to control the rocket through the channels of the course, pitch and roll. A known design of a swinging nozzle, comprising a fixed and a movable (swing) parts with a gap profile in the subsonic region of the flow path of the nozzle (Design rocket engines solid fuel / under the General editorship Lnerv. - M.: Mashinostroenie, 1993, s, RES; Ikhwanuddin, Aphrodelics. Construction and design of rocket engines solid fuels: a Textbook for engineering universities. - M.: Mashinostroenie, 1987, str, Risa) The deviation of the oscillating part of the nozzle occurs in the plane perpendicular to the axis of suspension. A disadvantage of the known construction of the nozzle is that when approaching during engine operation, the input edge of the swinging part of the nozzle and of a trailing edge of the fixed part is an intensive leaking high temperature combustion products into the cavity of the connector of the two parts of the nozzle. The impact of combustion products on the sealing elements of the connector, the actuator is t to the destruction of the latter, depressurization of the connector with the subsequent burnout design. The technical task of the present invention is to eliminate this drawback and, accordingly, improving the reliability design of the nozzle. The technical result is achieved by the fact that in the nozzle, comprising a fixed and oscillating part with a gap profile in the subsonic region of the flow path, the node charms swinging parts, elements, sealing the hole of the fixed part of the nozzle is made in the form of an ellipse, the minor axis of which is located in the plane perpendicular to the axis of the bearings (suspension). Execution of the outlet of the fixed part of the nozzle in the form of an ellipse is a significant distinguishing feature, as it allows to provide overlapping its edge an edge of the inlet of the oscillating part in the whole range of angles of swing. The result of the overlap is to increase the reliability of the nozzle. The essence of the invention shown in figures 1, 2, where indicated: 1 - fixed part of the nozzle 2, the swinging nozzle section 3 - node pendants 4 - sealing elements 5 - surface duct fixed part 6 - the surface of a flowing path of the swinging part T - the gap between the fixed and swinging parts Ne - edge output slip the practical holes fixed part K - plane swing M - edge inlet of the oscillating part of the Theoretical line............ - flow tract fixed portion of the output edge in the form of a circle NKR - edge of the output of the round hole of the fixed part α - position of the edge of the inlet of the swinging part when the deviation angle α. The advantage of the proposed technical solution follows from a comparison of the relative position of the fixed output and input of the tilting parts of the nozzle when the deviation of the latter at the same angle (with round and elliptical hole in the output parts (Fig.1): - when the round opening gap (point NKR, α); - when an elliptical hole gap is overlapped by the edge of the fixed part (dot Ie). A feature of the nozzle is as follows. When the deviation of the oscillating part in the whole range of working angles, the edge of the elliptical hole of the fixed part overlaps the edge of the inlet of the swinging part, while providing a continuous flow gas flow path of the nozzle. Prevent flowing of the gas flow in the gap between the fixed and swinging parts will preserve the integrity of the sealing elements and, thereby, to increase the reliability of the structure. The nozzle of the rocket engine solid fuel, containing what it stationary and oscillating part with a gap profile in the subsonic region of the flow path, site suspension swinging part, characterized in that in it the hole of the fixed part of the nozzle is made in the form of an ellipse, the minor axis of which lies in a plane perpendicular to the axis of swing.
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