Rolling cruise missile
FIELD: weapons and ammunition.
SUBSTANCE: two-stage rolling cruise missile (CM) with five degrees of freedom of spatial movement includes a housing stabilised as to the sixth degree of freedom by rotation in the form of a rotation figure with wings, rudders and an active aerodynamic nozzle, a single-duct control system, a steering gear, a detachable launching accelerator with an axial turbo-jet engine with a gas-dynamic nozzle, a cruise stage with an n duct system of formation of lift capacity in a rotation mode and a small-size disposable turbo-jet engine with a folded air intake, and a self-guidance head.
EFFECT: simpler control and stabilisation of a cruise missile, lower weight and dimensions of the cruise missile.
The present invention relates to the field of precision weapons and simultaneously applies cruise missiles (CU) and rotating missiles (BP).
The concept of reference for modern and future wars based on the extensive use of IT. WE call these types of weapons that do not beat around the areas and strike directly in the case of the goal, or in her most vulnerable places. Primarily it is expected to inflict irreparable damage on unmanned delivery vehicles THAT run from the middle and far distances even before direct contact of the army, manned aviation and the Navy.
By the mid 80-ies in the USSR were developed and adopted to the other two very important and effective. The first was the defeat of all types of air targets, the functioning of which occurs at altitudes of up to 4 km, and this view was wearable rotating anti-aircraft guided missile (VSWR) with passive optical homing head (AFO), effective at all angles of purpose, on any cloud backgrounds and organized by the optical counter (PLO) from air targets. This complex, known as the "Needle" has been extensively field tested in many military conflicts and combat effectiveness was superior to all foreign similar complexes. However, the technical�wise AFO "Needle" was given without purchasing a license, cheaply abroad the administration of the company LOMO. Moreover, the complex was first sold, and then hastily declassified.
Thus, the U.S. and NATO have received information about our possibilities of the destruction of their aircraft. The conclusion was USA made and reflected in the development of type CU Tomahawk and others whose radiation is small and does not allow to use the "Needle" to defeat missiles and aircraft of this type.
The second type concerns systems using for the functioning of the goals reflected from the laser beam. These systems are designed to engage maloznachaschih terrestrial, marine and other purposes, where the use of passive AFO inefficient. Was developed by rotating a guided artillery projectile (WUAS) fired from 150-mm howitzers and enable the defeat of maloznachaschih purposes, provided their illumination operator manual station backlight that weakened the effectiveness of the use of vulnerability operator of the backlight. This VOIS was also declassified and license its production was sold to China. Through the efforts of the U.S. was eliminated dependence on podsvetchik by arranging the illumination desired goals from space. Against this system of use in the form of CU and laser illumination from space there is no resistance and we are virtually defenseless, and showed that the events in Iraq (2 times) and yugosla�AI. For Yugoslavia, with the connivance of Russia NATO released 22000 bombs and missiles, 70% of which was the FACT, including more than 500 CU Tomahawk were amazed about 450 stationary objects and moving targets more than 900.
Subject to the foregoing, that is, high efficiency VSWR, WUAS and CU, it is proposed to consider the technical solution (TR) of new varieties of CU as a hybrid of the conventional CU and BP in the form of a rotating cruise missiles (WRC).
There are two ways of ensuring the sustainability of both unguided ballistic and controlled motion of rockets and shells: stabilization wings and the stabilization of the rotation. The handling and stability of the non-rotating rockets and shells with 6 degrees of freedom of movement by the first method is more complex principles of construction and operation of control systems and stabilization schemes external aerodynamic and internal layout, and the on-Board instruments autopilot and manual piloting needs to generate a large number of teams, and Executive bodies of a large number of control forces and moments, as required to stabilize the angular positions of the rocket around the three axes, roll, heading, and pitch, and the office for 6 degrees of freedom. In the second method there is no need to have an onboard stabilization system, as the rocket prio�Retal sufficient stability margin naturally due to gyrostabilizers momentum of the rotating body. In this case, the control components of the vector governing force (FF) is also greatly simplified and implemented on one channel, so BP has received the name of a single channel. In addition, the giving of rotation increases the aerodynamic and hydrodynamic symmetry, as it eliminates the effect of inaccuracies of symmetry of the body and installed aerodynamic elements and is offset by the eccentricity of the thrust of the engine arising from the uneven burning of fuel(1, 2, 3, 4).
Currently known CU only with 6 degrees of freedom, stabilized by the first method (5), but they are analogues of prescription-only. Close to the destination CU (5) contain an elongated cylindrical or other form of housing, on which there are folding wings, empennage and other aerodynamic parts inside the housing or outside on consoles installed small-sized disposable turbojet engine (OTRD), CU also supplied onboard systems automatic piloting and navigation, such as Autonomous inertial system and/or satellite, navigation, terrain, etc. Close to the destination CU are essential somewhere between medium and long range, and with the massive use of they may well be classified as strategic, also CU may be different �of aerovane, land, air, sea, including submarines. They are characterized by a high probability of hitting the wide range of goals, and start CU virtually no modern means of fixed missile warning. Massive use of the CD even with conventional non-nuclear warhead (BC) on the results of the striking action is comparable to the use of nuclear weapons with the difference that it affects only the specified military and other objectives with a minimum of civilian casualties. The disadvantages of similar designation CU are the increased complexity of systems stability and control, as they have 6 degrees of freedom, and consequently high costs technical resources, which, in turn, increases the cost, its own weight and dimensions of both the missiles and launchers).
Known close to the technical nature of VSWR (1, 6) and VWS (6), which contain elongated cylindrical body with 5 degrees of freedom is stabilized by the 6th rotation around the roll axis and is provided with a compact folding beveled tail stabilizers, solid-fuel rocket engine, equipped with basic traction nozzle and concentrically located microplane, the oblique angle of 5-20 relative to the longitudinal axis of the missile, AFO, which determines the CCW�dinate goals the direction and angular velocity of rotation to the line of sight "rocket-target and generating a control signal, informative characteristics and parameters which carry information about it, the output is connected to the control system in rotation mode, the output of which is connected to the steering actuator aerodynamic rudders.
VSWR have significant advantages over rockets, stable plumage, including families, by appointment CU. For example, the sustainability movement VSWR is achieved naturally without the cost of technical equipment due to the gyroscopic effect, control of the vector components of the administering power (US) easier and is implemented on a single channel. Due to the twist of the casing VSWR except for the natural stability of angular positions and movements become more Aero - and gas-dynamic symmetry, a simpler scheme aerodynamic and interior layout. Listed distinctive features enable you to design and produce more compact, including wearable systems, dramatically reduce its own weight and dimensions as missiles and launchers (PU).
Similar in essence WUAS have almost identical with VSWR functional composition. The only difference is that if VSWR contains a jet engine, for WUAS using an external motion�tel - gun.
However VSWR and WUAS have a narrow purpose and scope only as anti-aircraft missiles to intercept low-flying air targets (VSWR) and as a homing projectile to defeat close slaboizluchayuschimi ground targets (WUAS).
The closest in technical essence of the technical solution (TR) it is declared TR aircraft vertical takeoff and landing (LAWP) (7 patent RF №2378156). Specified LAVIT contains made in the form of flat figures of rotation of the housing provided with wings and rudders and stable rotation around the axis of the course, single-channel control system in rotation mode, the output is connected to the steering actuator, one axial turbojet engine (TRD), the nozzle which is installed multi-start spiral gas-dynamic nozzle (PAU), and the upper half-plane of the device equipped with an active spiral aerodynamic nozzle (adni) and the lower - device for starting twist. The described apparatus uses for takeoff, landing and flight aerodynamic lift force of the rotating blades, so that in contrast to BP, you can use much more fuel efficient engines with thrust coefficient (CT) is less than unity and vertically take off and land, long hang and fly long distance�AI. Thus imparting rotation provides apparatus high stability in unfavorable for conventional aircraft GDP takeoff, landing and flight at low speeds in the presence of adverse weather conditions and other external disturbances. However, the apparatus has a large size and weight, is much smaller compared to the CU and the more VSWR cruising speed flight and a great time pre-launch, as at the start of the device need to unwind and to gain the required speed of rotation providing a lifting force, a more take-off weight.
The aim of the invention is the change of destination (in comparison with the prototype to the technical nature) and the expansion of applications. When compared with the prototype designation, achieved by simplifying management and stabilization, reduced own weight and size.
This object is achieved in that the proposed WRC, as the closest in technical essence LAVIT, contains made in the form of a figure of rotation of the casing with 5 degrees of freedom, stable 6-th degree of freedom of rotation on which you installed the aerodynamic elements of the wings to form the lifting force, rudders for the formation of the administering power and the active spiral adni, also contains a single-channel control system, the output is connected khruleva drive,
Turbojet nozzle which is installed DDT, and is characterized in that the housing is in the form of an elongated cylinder with a pointed head part, not stable rotation around the axis of the course, and around the axis of the roll, the tail portion is lined with small OTRD, and the body of the rocket is equipped with a folding intake and his tail is set on Pirozhenko detachable startup accelerator, the nozzle of which is also installed DDT, and in the head part of the 1st the primary stage of the rocket installed a passive or semi-active, or active homing head, along the longitudinal axis of the missile installed on discrete n pairs of spiral compact folding wings switchable synchronous in frequency and phase of rotation of the rocket is the sign of the angle of attack at some angle to 20 relative to the longitudinal axis of the missile with a step angle of heel
Thus, the novelty and the main distinguishing PR�sign declared TR is introducing previously unknown or TR analogues on purpose, neither in the field TR analogs and prototypes to the technical nature of the n-channel formation of aerodynamic lift in the mode of rotation around the roll axis (TR prototype wings do not alter the sign of the angle of attack, as the device is stabilized by rotation around the axis of course). In close TR VSWR wings are absent, as the missile moves along its trajectory, thrust solid-propellant rocket motor, CT which is much greater than unity, and the component of the aerodynamic lifting force is insignificant and has the second order of smallness (1). Introduction marked feature makes it possible to combine the advantages of missiles and rotating apparatus with the advantages of conventional non-rotating CU, and attach the advantage of reduction of head resistance due to the excited vorticity incoming airflow. The thrust force is known CU expended to overcome the inertial forces on the formation of aerodynamic lift, and some irrevocably to overcome the frontal resistance of the air environment. Declared TR energy costs OTRD to overcome this resistance decrease. Consistent relative positions of the wings, rudders and active ADN excites the vorticity of the flow, the energy of the excited vortex soliton accumulates and forms around cancer�s "cavern" reduced pressure and the resistance of the air environment is reduced. Thus, the proposed combination installed on the rocket gas and aerodynamic elements and their consistent interposition allows you to get additional positive effect and increase the utilization factor of thrust OTRD. The expected reduction of its own weight and dimensions WRC compared to the known CU will provide additional useful effect is the possibility of creating a compact PU or systems of volley fire WRC individual guidance, since in this area we also lag behind.
Fig.figure 1 shows the claimed WRC, Fig.2 - simplified block functional diagram of the WRC for explaining the principle of operation of rockets and more particularly the principle of forming a lifting force in the rotation mode. Fig.1 marked: startup accelerator with 1 PAU 2, building 3, small ATRD 4, DDT 5, folding the air inlet 6, three pairs of folding of the wings 7, 8, 9, rudders 10, 11 adni. Fig.2 are indicated: unit 1 navigation, autopilot (AP) 2, switch 3, the seeker 4, gyroscope 5 roll, combined with sensors quadrature reference signals and the three-phase reference signals, the multiplexer 6, the wings 7, 8, 9, rudders 10 (for convenience, the numbering of the wings and rudders in Fig.1 and Fig.2 matches), power amplifiers 11, 12, 13, drives the wings 14, 15, 16 and the steering actuator 17.
WRC operates �next.
In the initial state, the missile is armed, mounted in the transport and launch container or in PU volley fire and passed preflight training. On the command "start" triggered lifting charge, the missile exits the launch tube, then run startup accelerator 1, accelerates the missile to the primary speed and simultaneously twists it around the roll axis due to the action on the jet DDT 2. After running out of fuel in the accelerator trigger pirozhki (figure not shown) and the accelerator 1 is separated from the rocket. At the same time served starting command ATRD 4 and unlocking the folding of the air inlet 6, the wings 7, 8, 9 and rudders 10, grooves which extend from and are fixed in position. In accordance with the stored missiles flight instructions of the navigation unit 1 generates the control signal for the adjustment of the trajectory of a given route of approach to the goal which is sent to AP 2. AP 2 forms a standard single-channel control signal, which is supplied to the steering actuator 17, the axis of which are mounted wheels 10, which are beginning to switch the sign of the angle of attack. When the deviation of the trajectory of the rocket rudders 10 form a governing force, which returns a rocket on a given tectorius. Sensors oparah signals, combined with gyro 5 roll, synchronous in frequency and phase rotation cancer�you form a quadrature reference signals sinωt,
cosωt, where ω is the angular frequency of rotation of the missile, and t is time. These signals are transferred in AP 2, they are necessary for the formation of a single SU. Devices and methods for forming single-channel SU-known from theory and practice of designing VSWR and therefore the application will not be considered. The second gyro sensor 5 converts the roll angle in three-phase "meanders" sign(sinωt),
Stated WRC along with the famous CU can be used for striking the 1st and 2nd wave at crowds of terrestrial, marine, stationary and moving targets at medium and long distances. The essence of the declared TR in the further development of such promising areas, as CU and VSWR by creating a hybrid BP and CU, combining the beneficial properties and advantages of the 1st and 2nd kind. The prospect of further development of such media is to create the CD and WRC small caliber, weight and dimensions for systems of volley fire cruise missiles individual guidance.
Above shows that the declared TR entered previously unknown characteristic of the system of forming the lifting force in the rotation mode and characterized� unknown new set of features, providing far from obvious and original creation of hybrid vehicles, having dissimilar ways to stabilize and control that does not follow a clear path from the current level of missile technology. The claimed solution can be implemented using known materials, fuel, OTRD, and the drives of the wings can be used proven practice development VSWR and WUAS steering actuators. Thus, the inventive TR meets all the criteria of inventive step.
The LIST of references
1. Krasovskii, A. A., et al., "fundamentals of theory and design of rotating single-channel controlled missiles," Zhukovsky Academy. Zhukovsky, 1963.
2. Arkhangelsk A. A. et al., "Design of anti-aircraft guided missiles, M., MAI, 1999.
3. Kazakov, I. E. et al., "control Systems and dynamics missile guidance", Zhukovsky Academy. Zhukovsky, 1973.
4. Product specifications A and complex KM, Barongis, 1970.
5. "Rocket science", "Operating system" Air BASE NEW-factoria, a Large aviation encyclopedia "Corner of the sky", Air.war.ru "Science" - "American CU sea-based; R. Radomiro - Description CU "SCALP-EG (France); AGM-84; SLAM-EAT; AGM-AM; BGM-109ACM; BGM-109 "Tomahawk"; JASSM-BZ (USA); KEPD-150TAURUS (Germany-Sweden) - analogues by appointment.
6. The US patent No. 4309393; RF Patents №№2101742, 2093850; Analogues of the technical nature.p> 7. RF patent №2378156 "Aircraft vertical takeoff and landing" - a prototype.
The LIST of USED ABBREVIATIONS
- Accurate weapon; CU - cruise missile; VR - rotary rocket; WRC - rotating cruise missile; PU - launcher; US - controlling force; SU - control signal; CT is the thrust coefficient; VSWR - rotating anti-aircraft guided missile; VOIS - driven rotating artillery shell; adni - aerodynamic nozzle; PAU - gas-dynamic nozzle; HS - seeker; TR - technical solution; SA activation signal; OOP - organized optical counter; LA aircraft; LAVIT - aircraft vertical takeoff and landing; TS - technical solution.
Rotating cruise missile with five degrees of freedom of the spatial motion containing made in the form of a figure of rotation, the housing provided with wings, rudders and active aerodynamic nozzle, stable six degrees of freedom of rotation, single-channel control system, the output is connected to the steering actuator, axial turbojet engine, the nozzle which is installed on the gas-dynamic nozzle, characterized in that for the purpose of changing the use and expansion of application areas it is made of two steps, starting detachable accelerator, nasolo which is installed on the gas-dynamic nozzle,
and flighted stairs, stable rotation around the axis of the roll and is made in the shape of an elongated cylinder with a pointed head part provided with a homing head, the tail portion of the primary stage is set small disposable turbojet engine equipped folding intake, and the sustainer stage is provided with n-channel forming system of the lift force in the rotation mode, the outputs of which are connected to the n pairs of actuators compact folding and switched the sign of the angle of attack of the wings, which are mounted along the longitudinal axis of the missile symmetrical about the center of mass of the discrete spiral with a pitch angle roll
FIELD: weapons and ammunition.
SUBSTANCE: guided missile is made based on canard configuration. The missile with a single-channel control system and rotating in roll direction. The missile contains a main propulsion system, a steering wheel in one plane and a stabiliser with the location of fixed bearing surfaces by X-shaped pattern relating to the plane of the steering wheel console. At the head part of the housing of the guided missile in a plane perpendicular to the plane of the steering wheel console, the pylons are mounted. The fixed consoles of the pylons in a transverse plane are located at an angle of 45-60 degrees relative the consoles of the stabiliser. The consoles of the pylon on the geometric shape in the plan are made like consoles of the steering wheel with the ratio of areas of the pylon and the steering wheel as 0.5-1.0. The ratio of areas of the console of the pylon and the console of the stabiliser are made as 0.05-0.1.
EFFECT: improved control efficiency, improved ballistic and dynamic properties of the missile.
FIELD: weapons and ammunition.
SUBSTANCE: guided missile (GM) comprises compartments of cylindrical thin-walled shells, a main propulsion system, an armament section, connected in series telescopically by radial screws with nuts and conical heads. The conical head has a cylindrical surface which interacts with the cylindrical opening of one compartment, and a conical part interacting with the conical opening of the second compartment. The axis of the conical opening of the first compartment is located eccentrically from the axis of the cylindrical opening of the second compartment.
EFFECT: invention enables to improve the efficiency of the guided missile.
3 cl, 4 dwg
FIELD: weapons and ammunition.
SUBSTANCE: unit of control system of rocket projectile comprises a housing with ogive part, aerodynamic controllers folding-out in flight with actuators and a control unit, mounted on the ogive part. Each controller is equipped with abutment. The abutment is located in front of the front edge of the controller coaxially with the axis of folding-out. The profile of the front part of the abutment is congruent to the profile of the ogive part of the housing. The diameter of the maximum circumscribed circle of the abutments of all the controllers does not exceed the unit gauge. Folding-out axes of the controllers are biased to the axis of the unit relative to its gauge by an amount at least 0.5 of the maximum thickness of the controller at the root chord of its folding-out part.
EFFECT: improvement of accuracy of projectile shooting.
4 cl, 2 dwg
FIELD: weapons and ammunition.
SUBSTANCE: this missile comprises warhead screwed to another compartment and secured thereto by fastener composed by rectangular-section ring with arched hooks with inner cylindrical surface and ledges at end surface. End of connectable compartment comprises arched ledges with OD, sizes and quantity equal to those of fasteners. Arrangement of said hooks in angular direction complies with arrangement of ledges with threaded holes for fastening screws of warhead.
EFFECT: decreased length and weight, higher reliability and combat efficiency.
3 cl, 4 dwg
FIELD: weapons and ammunition.
SUBSTANCE: invention relates to missile engineering and is intended to be used in rockets launched from a launching transporting container. The design of the retention mechanism assembly represents a bracket, on which a limit stop, a turnbuckle and a grip arranged on the rotation axis in the front part of the retention mechanism bracket are mounted. The grip design has an attachment axis of the turnbuckle serving as a fastening element of the grip design with a flag, by means of which the rear face of the rocket is held down to the limit stop of the retention mechanism. The flag design has a rotation axis fixed on the bracket. In the zone of the rotation axis in the flag there is a T-slot for fixation of the turnbuckle; on the opposite side there is a platform with holes for attachment of a fastening plate. The fastening plate attaches flags of two assemblies of the retention mechanism.
EFFECT: achievement of reliable fixation at transportation, and minimum disturbances at start-up at the moment of the plate burnout.
4 cl, 4 dwg
FIELD: weapons and ammunition.
SUBSTANCE: invention relates to missile engineering, namely to controlled missiles. A controlled missile includes a housing with the main control elements symmetrically arranged on it - aerodynamic surfaces and rudders, as well as a wire duct. The latter is arranged along the housing in the incline of rudders. An aerodynamic surface is additionally installed on the housing, on the side opposite to the wire duct.
EFFECT: improvement of aerodynamics of missile flight and improvement of its target guidance accuracy.
2 cl, 1 dwg
FIELD: weapons and ammunition.
SUBSTANCE: guided bullet comprises a balancing weight, stabilising elements, aerodynamic control bodies, the drive unit of control bodies, and the beam control system which comprises a photoreceiver and onboard equipment. The balancing weight is used as the warhead of kinetic action. The warhead is made in the form of armour-piercing rod. The stabilising elements are made in the form of two consoles and are arranged in a plane passing through the longitudinal axis of the guided bullet. The aerodynamic control bodies are made in the form of a pair of all-moving aerodynamic rudders arranged on one axis located behind the stabilising elements in the direction of motion in a plane passing through the longitudinal axis of the guided bullet and perpendicular plane of location of the stabilising elements. In the guided bullet an on-board power source is located, made with the ability to initiate at the time of firing.
EFFECT: increase in the firing range.
10 cl, 7 dwg
FIELD: weapons and ammunition.
SUBSTANCE: coned-bore rocket comprises the solid rocket propulsion. The solid rocket propulsion is a part of the propulsion system, structurally combining it with rocket-ramjet propulsion. The front bottom of the propulsion system is provided with air intake device located in the ring formed by the difference of calibre of the main propulsion stage and the propulsion device. The gas generator of the rocket-ramjet propulsion is placed in the combustion chamber of the rocket propulsion concentrically with its fuel charge. The method of extending the area of applicability of coned-bore rocket in range comprises the rocket acceleration on the ascending branch of the trajectory by the solid rocket propulsion, its subsequent separation and flying of the main propulsion stage by inertia. To increase the range of flight after use of the solid rocket propulsion the rocket-ramjet propulsion is activated. The air intake device is opened, the nozzle of the rocket propulsion is transformed, increasing its critical section, and the rocket propulsion combustion chamber is used as an afterburning chamber of the rocket-ramjet propulsion. After use of the rocket-ramjet propulsion it is separated together with the rocket propulsion. To reduce flight distance after use of the rocket propulsion the rocket-ramjet propulsion is not activated and they are separated with programmable time delay.
EFFECT: increase in the maximum range of the rocket flight.
4 cl, 9 dwg
FIELD: weapons and ammunition.
SUBSTANCE: shell is made based on the canard configuration. The shell comprises an air-dynamic steering gear in the front section of the shell housing and aerodynamic control elements - steering wheels with pylons mounted in front of them. The air-intake devices of the air-dynamic steering gear are incorporated in the pylons and made in the form of bi-plane U-shaped plates with converting into the monoplane along the rear edge. In the front edge of the pylon the U-shaped hole is made and the hole in the shell housing is made.
EFFECT: increase in efficiency of the shell operation.
2 cl, 6 dwg
FIELD: weapons and ammunition.
SUBSTANCE: this rocket section comprises body with heat insulation and set of fins. Sleeve of elastic material with low ablation temperature fitted in ring groove is arranged ahead of fins some 0.025…0.25 caliper from the butt of body and fins on body and inner surface. At butt between heat insulation and sleeve, said insulation has inner circular ledge abutting on sleeve.
EFFECT: higher reliability of operation due to lower heating of threaded joint between body and fins.
FIELD: armament, in particular, guided missiles.
SUBSTANCE: the guided missile has a body with a warhead and a casing positioned in succession in it, the control equipment units are located in the casing. A flange with a stop in the end face of the warhead and the casing is installed between the warhead and the casing. Annular bosses uniformly distributed in its longitudinal axis and engageable with the inner surface of the body provided with a stop in the bottom section are made on the outer surface of the casing. The warhead is installed in the body with compression the side of the front end face.
EFFECT: enhanced initial velocity and enhanced allowable launching g-loads.
FIELD: armament, in particular, guided missiles.
SUBSTANCE: the guided missile has a control actuator in the nose cone, warhead and a control equipment positioned in the missile body and connected by lines of electric coupling made in the form of bundled conductors with connectors. The control actuator, warhead, control equipment are made in the form of a single unit provided with electric connectors on the outer surface. The lines of electric coupling are located inside the body along the unit outer surface. The missile body is fastened in the rear part of the control surface unit.
EFFECT: improved aerodynamic properties of the missile, simplified construction and manufacturing and assembly methods.
FIELD: space rocketry.
SUBSTANCE: each door of the nose aerodyanmic fairing is made of two sections with a cross joint. The plane of the joint coincides with the rear section of the fuselage fairing closed with cover in the mounted state. The cover is made in the form of a tapered surface integrated with the door section joined to the body of the rocket booster and rigidly connected to it in the point of conjugation.
EFFECT: enhanced operating and technical characteristics of the rocket booster.
FIELD: rocketry, applicable in the construction of two-stage bicaliber rockets provided with a device for separation of the electric lines of the rocket stages.
SUBSTANCE: the assembly of electric connection is fastened at an angle to the rocket longitudinal axis and provided with a rejecting device in the form of a hatch plate door made in the transient fairing, connected to the rejected connector block of the first stage.
EFFECT: enhanced reliability of the rocket.
FIELD: rocket manufacturing.
SUBSTANCE: sealing of the gas system in the points of installation of the functional members is preliminarily performed by simulators of the control actuator functional members. Then the preset value of air pressure in the source of pneumatic supply is set, and air is fed to the control actuator gas system through a service storage vessel, in which the air pressure is measured. The gas system passage flow sections are estimated by comparison of the value of the measured air pressure in the service storage vessel with the maximum allowable value. The device uses a service storage vessel made with inlet, outlet and measurement connections. The service storage vessel communicates with the source of pneumatic supply through the inlet connection, with the specimen under test-through the outlet connection, and with the pressure gauge - through the measurement connection. The inlet and outlet connections are installed on the front and rear walls of the service storage vessel respectively, and the measurement connection is installed on its side surface. The inlet connection is provided with a measuring orifice with a flow section area making up 0.7 to 0.9 of the allowable passages of the control actuator, and the flow section area of the outlet connection exceeds the allowable minimum sections area of the passages of the control actuator gas system at least by 5 times.
EFFECT: enhance accuracy of check and reduced labor content of the test.
2 cl, 2 dwg
SUBSTANCE: the guided missile has a body with a warhead located in it and provided with an explosive charge and destructive components, with an electric cable laid along it. The destructive components are made in the form of sectors touching with radial surfaces and forming rings making up a cylinder with a longitudinal axial duct engageable by the outer surface with the inner surface of the missile body. The electric cable is fastened on the surface of the cylinder axial duct, and the explosive charge is made in the form of a body with a variable section longitudinal duct filled with an explosive, and is positioned in the cylinder axial duct.
EFFECT: enhanced efficiency of action of the warhead, enhanced velocity of the guided missile.
FIELD: armament, in particular, guided missiles and rockets.
SUBSTANCE: the guided missile ballistic cap has a body, separation device with a separation chamber, powder charge placed in a high-pressure chamber communicating with the separation chamber through an opening. Installed in the separation chamber is a partition with exhaust-gas ducts separating the separation chamber into two cavities, with an additional charge of fine-grained powder, mainly pyroxylin one, located in one of them communicating with the high-pressure chamber through an opening. A metal screen is installed between the additional charge and the partition, whose cell dimension is less than the linear dimension of the powder grain of the additional charge. The additional charge of fine-grained powder is installed separately from the powder charge limiting its displacement in the direction of motion of the ballistic cap.
EFFECT: enhanced reliability of separation of the guided missile ballistic cap within a wide temperature range of operation at guided missile flight speeds exceeding 2-3M.
2 cl, 1 dwg
FIELD: rocketry applicable in small-sized rocket complexes.
SUBSTANCE: the rocket has an engine provided with a barrel installation located inside the engine in its longitudinal axis, in which a projectile separated in the trajectory is installed, the projectile caliber is less than the engine caliber, and a propellant charge. The propellant charge is positioned in a cavity made in the projectile rear section. The rear section of the projectile outer surface has a variable section with a reduction to the rear end face. The cavity with the propellant charge communicates through gas vents with the reduced surface of the projectile. The gas vent outlets are positioned symmetrically in the cross section of the projectile body, and the bottom section of the barrel installation communicates with the atmosphere through a passage, whose area is less than the barrel cross-section area.
EFFECT: reduced mass of the rocket and the level of overloads acting on the projectile.
FIELD: armament, in particular, missile complexes.
SUBSTANCE: the method consists in firing of the missile from the launching tube and subsequent starting of the jet engine by thermogasdynamic action by igniter combustion products on the inserted charge of solid fuel. At starting of the engine subjected to the action by combustion products is only the part of the charge end face surface that is limited by the cavity communicating with the engine combustion chamber. Action is effected by means of thermogasdynamic jets directed at an angle to the charge end face, and the time of action is provided according to a definite dependence. The combustion products from the charge end face surface are moved in the charge axis and turned before the inlet to the engine nozzle axis and turned before the inlet to the engine nozzle unit, at the same time they are transferred in the radial and tangential directions. A complex of armament for realization of the given method is also claimed.
EFFECT: enhanced reliability of the armament complex.
3 cl, 2 dwg
FIELD: armament, in particular, artillery, projectiles.
SUBSTANCE: the guided missile has a body with control units and bulges on the outer surface of the body. The outer surface of each bulge is made in the form of a wedge, whose point faces the projectile nose, and the bulge proper is installed before the projecting member of the construction. The wedge base is made to the shape of the front part of the projecting member, and the bulge projection in the plane transverse to the missile plane is larger than the projection of the projecting member in the same plane.
EFFECT: provided protection of the missile construction projecting members against the action of the incoming air flow.