Method of aircraft start (versions)

FIELD: aircraft engineering.

SUBSTANCE: aircraft (AC) is placed in the Launcher, or in a Launcher transport and starting barrel, or partially in Launcher TSB with an external arrangement of the jet nozzles, or a transport and starting container (TSC), or TSC of Shaft Launcher, the starting propulsion system (SPS) is fixed in AC front part, AC is partially moved forward, SPS is started, the traction is formed by two jet nozzles located on a lateral surface of SDU at an angle to a longitudinal axis of AC, the front part of LA is protected during acceleration by the fairing fixed on SPS, SPS is separated by means of draft force.

EFFECT: invention allows to decrease the weight of an aircraft structure, launcher start load and simplify a launcher design.

7 cl, 4 dwg

 

The invention relates to reactive managed projectiles, in particular for the aircraft (LA), mostly unmanned, and devices for their start-up.

The known method of launch unmanned LA "Yakhont" ("Weapons and technology of Russia. Encyclopedia. XXI century", volume III, edited by S. Ivanova, publishing house "Arms and technologies", Moscow, 2001, pp. 103-109, and O. A. Artemov "Ramjet engines," publishing "Company Sputnik+", Moscow, 2007, pp. 278, 279), which consists in placing the aircraft in the transport and launch container (glass), which in various embodiments is placed on a car the launcher, the launcher rack, hardpoints of the aircraft carrier, in a shaft below deck the launcher vehicle. The start of the famous LA can be provided with its location directly on the launcher, without transport and launch Cup (TPN). The starting powder of startovie (starting of the propulsion unit, SDU) is performed after ejection (bailout from LA TPN) is a special device that develops the considerable efforts of ejection, with the opening of the lid transport and launch Cup and the subsequent acceleration of the aircraft under the action of the thrust generated by the jet nozzle of the CDS. SDU is placed in the channel ramjet engine Compartment SDU is performed by the air pressure after clicking principle of its attachment to the body and burning out its fuel. When starting from LA silo launchers before starting SDU open the lid of the mine.

The essential features of the prototype, coinciding with the essential features of the first variant of the proposed method are as follows: method start the aircraft, which consists in placing in the launcher, and run it to start the propulsion system with the subsequent acceleration under the action of thrust of its jet, and separating the starting of the propulsion system after overclocking.

The essential features of the prototype, coinciding with the essential features of the second and third variants of the proposed method are as follows: method start the aircraft, which consists in placing in transport-launch Cup, accommodation, transport and launch of glass in the launcher, start the starting of the propulsion system of the aircraft to open the lid of the transport and launch Cup and the subsequent acceleration under the action of thrust of its jet, and separating the starting of the propulsion system after overclocking.

In known embodiments, during acceleration LA, on the portions of the cladding (walls) of the housing attached to the casing of the power frame with the rear (direction of flight) side thrust force starting of the propulsion system, with front and side - force initsiirovannykh in the housing units, strength of structural elements, fuel flighted propulsion, wherein portions of the cladding loaded compressive stress. Since the thin-walled shell under the action of compressive stresses tend to lose resilience (can kopyatsya, crinkle), have to increase their thickness and (or) the number and mass of structural elements (frames, stringers) that reinforce the shell, which increases the mass of the structural elements LA, therefore, it is necessary to increase the mass of fuel and construction starting of the propulsion system, providing acceleration LA. For the release of LA from TPN requires a special device that develops the considerable efforts of the bailout.

The technical result, which directed the invention is to reduce the weight of the design AIRCRAFT, reducing the starting load on the launcher and simplifying the design of the launcher.

To achieve the mentioned technical result in the first embodiment of the method of starting the aircraft, which consists in placing in the launcher, and run it to start the propulsion system with the subsequent acceleration under the action of thrust of its jet, and separating the starting of the propulsion system after overclocking, starting the propulsion system is fixed in the nose of the aircraft up�Arata, and cravings form at least two jet nozzles mounted on its side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, in the process of dispersal protects the front of the aircraft for starting the propulsion system for the fairing mounted on starting the propulsion system, and the starting of the propulsion system provide under the influence of its traction.

To achieve the mentioned technical result in the second embodiment of the method of starting the aircraft, which consists in placing the aircraft in a transport-launch Cup, accommodation, transport and launch of glass in the launcher, start the starting of the propulsion system of the aircraft to open the lid of the transport and launch Cup and the subsequent acceleration under the action of thrust of its jet, and separating the starting of the propulsion system after overclocking, starting the propulsion system is fixed in the bow of the aircraft, and thrust form the at least two jet nozzles, located on its side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, before starting starting the propulsion system provide a partial extension of the aircraft, the apparatus�the exit nozzle block from the cavity of the transport and launch Cup, in the process of dispersal protects the front of the aircraft for starting the propulsion system for the fairing mounted on starting the propulsion system, and the starting of the propulsion system provide under the influence of its traction.

To achieve the mentioned technical result in the third embodiment of the method of starting the aircraft, which consists in placing in transport-launch Cup, accommodation, transport and launch of glass in the launcher, start the starting of the propulsion system of the aircraft to open the lid of the transport and launch Cup and the subsequent acceleration under the action of thrust of its jet, and separating the starting of the propulsion system after overclocking, starting the propulsion system is fixed in the bow of the aircraft, and thrust form the at least two jet nozzles, located on its side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, ensure the partial placement of the aircraft in the transport and launch glass with external location of the jet nozzle, in the process of dispersal protects the front of the aircraft for starting the propulsion system for the fairing mounted on the starting motor installation, OTDELENIE starting the propulsion system provide under the influence of its traction. To reduce thermal impact of jets on aircraft when using silo launchers use the mine launcher with opening the lid of the mine, before starting starting the propulsion system provide a partial extension transport-launch cups from the cavity of the mine with the jet nozzle exit to the outside.

Additionally, in each variant of the proposed method to improve the safety of the launch pad or the mother ship vertical launch LA tilt the jet nozzle at various angles form the lateral component of the thrust.

Distinctive features of the first proposed variant of the method of LA start is that the starter motor mounting clips in the nose of the aircraft, and thrust form the at least two jet nozzles mounted on its side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, in the process of dispersal protects the front of the aircraft for starting the propulsion system for the fairing mounted on starting the propulsion system, and the starting of the propulsion system provide under the influence of its traction.

Distinctive features of the second proposed method �tart LA, what starter motor mounting clips in the nose of the aircraft, and thrust form the at least two jet nozzles mounted on its side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, before starting starting the propulsion system provide a partial extension of the aircraft with an exit nozzle block from the cavity of the transport and launch Cup, in the process of dispersal protects the front of the aircraft for starting the propulsion system for the fairing mounted on starting the propulsion system, and the starting of the propulsion system provide under the influence of its traction.

Distinctive features of the proposed third version of the method of LA start is that the starter motor mounting clips in the nose of the aircraft, and thrust form the at least two jet nozzles mounted on its side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, ensure the partial placement of the aircraft in the transport and launch glass with external location of the jet nozzle, in the process of dispersal protects the front of the aircraft for starting the propulsion system obte�the Atelier, secured to starting the propulsion system, and the starting of the propulsion system provide under the influence of her power; use the mine launcher with opening the lid of the mine, before starting starting the propulsion system provide a partial extension transport-launch cups from the cavity of the mine with the jet nozzle exit to the outside.

Furthermore, additional distinctive features for each proposed variant of the method the start of the LA is that the tilt of the jet nozzle at various angles form the lateral component of the resultant force of the thrust.

Thanks to the presence of these distinctive features in conjunction with the known is achieved by the following technical result: the total mass of LA reduced the mass and volume of the structural elements that ensure its strength, it will increase the safety of the launch pad or the mother ship vertical launch LA, the reliability of the launch, reduced weight and requirements to the launcher, eliminating the effects of recoil forces on the launcher at startup.

The proposed technical solution can be used in space and defense technology to reduce aircraft mass, enhance security and reliability of start, LA, expansion of environmental parameters, Ogre�MICIVIH for the start.

The essence of the proposed solution is illustrated by drawings, Fig.1-4.

Fig.1 shows the construction of LA placed on the launcher.

Fig.2 shows the structure of LA, placed in transport-launch beaker, provided with a device partially ejected from LA, with an exit nozzle block from its cavity and placed mine in the launcher.

Fig.3 shows the structure of the LA shown in Fig.2 in position partially extended from LA cavity transport-launch cups.

Fig.4 shows the structure of LA, partially placed in transport-launch Cup with the location of the nozzle block starting of the propulsion system over cap transport-launch of glass, which is thus placed mine in the launcher, equipped with a device of its partial extension.

The drawings show an unmanned AIRCRAFT, comprising a housing 1 with power trim 2 attached to the shell plating 1 power frames 3 and 4, and fixed on the power frame 3 starting the propulsion system 5 by means of fastening devices 6, made with the possibility of clicking principle, and a control system 7 which communicates with the fixing device 6. Starting the engine unit 5 is placed in the front part of the housing 1 and is provided with deploym block 8, containing at least two �aktivnih nozzles 9 and 10, located on its side surface with an inclination to the longitudinal axis of each jet nozzle at the angle of 10-30° to the longitudinal axis of the housing 1. The longitudinal axis of the jet nozzles 9 and 10 are inclined to the longitudinal axis of the housing 1 at different angles, in the range of 10-30°. Weekend sections 11 and 12, respectively, the jet nozzles 9 and 10 are beveled at the outer side of the side under an angle of 10 to 75° to a plane perpendicular to the longitudinal axis of each nozzle. As a variant, Fig.1, LA placed in the launcher 13 and provided with a protective cowling 14 of the front part of the housing 1 for starting the propulsion system 5 is made of heat-resistant material. Fairings attached to the starter motor 5 under her jet nozzles 9 and 10 of the nozzle block 8. The protective cowling 14 is applied to the heat-shielding cover 15. Starting the engine unit 5 is equipped with a starting device 16. Launcher 13 is provided with 17 remote control which communicates with the control system 7 and starting device 16. Power the covering 2 of the housing 1 is provided with reinforcing power elements 18. The power frame 4 is fixed sustainer propulsion system 19 with a starting device 20 which communicates with the control system 7. As a variant, Fig.2, LA placed in transport-launch Cup (TPN) 21 with an opening lid 22. TPN 21 is provided with a device 23 for the nomination with LA in�swing nozzle block 8 from its cavity. The device 23 LA nomination contains the actuator 24 and the yoke 25 on which is mounted the housing 1. TPN 21 posted mine in the launcher 26, is provided with a cover 27, device opening 28 and 29 remote control. As a variant, Fig.4, the protective cowling 14 may be a cover SCC 21, while the shaft 26 is provided with installation device 30 partial extension LA of the hollow shaft 26, which is provided with a drive 31 which communicates with the remote controller 29 controls.

The first variant of the method according to claims.1-2 formula is implemented as follows. To start with LA console 17, Fig.1, the control is operated starting device 16, allowing the starter motor mounting 5. Under the action of the total thrust (Rsee Fig.1) jet nozzles 9 and 10 starting the engine unit 5 together with the housing 1 moves with an acceleration determined by the ratio Rto the weight of LA, at the exit of the housing 1 from launcher 13, and in free flight LA. When starting the acceleration of the housing 1 on the upper part of the region covering 2 power between frames 3 and 4 through the frame 3 is transmitted to the power of Rthrust, and the lower part of the leg covering 2 via the frame 4 is transmitted to the power of RAndthe inertia of the primary propulsion unit 19 mounted on the frame 4 and is equal to the product of the mass of the primary propulsion unit 19 by the amount of the starting acceleration of the housing 1. Power Rand RAnd stretch (straighten) region covering between 2 frames 3 and 4, which, unlike the prototype, where the forces of thrust and inertia act towards each other, compressing the same area of skin. Thanks to the stretched condition of the region covering between 2 frames 3 and 4 increases dynamic stability (critical stress fracture) plating 2 under elastic oscillations of the housing 1 in flight LA, therefore, the required number and weight of load-bearing elements 22 and / or the thickness of the shell can be reduced. Similarly for the other compartments of the housing 1 (fuel, instrument, commercial, not shown). By reducing the total mass of the structure 1 can: when you save the weight of the starting of the propulsion unit 5 to reduce the acceleration of the housing 1 or to increase the weight of the fuel flighted propulsion unit 23 and range of LA; while saving time acceleration of the body 1 to reduce the weight of the starting of the propulsion unit 5. When the angles of inclination of the longitudinal axes of the jet nozzles 9 and 10, less 10° emerging from a stream of high temperature gases is too close to the housing 1, which can lead to overheating of the cladding 2, and at these angles greater than 25°, the value of the longitudinal component of the thrust Raccelerating the housing 1, will be less than 90% of the total thrust of the jet nozzles 9 and 10. Thanks to various� the angles of inclination of the longitudinal nozzles 9 and 10 is formed by the difference of the horizontal projection R9"andR10"forces R9and R10thrust nozzles 9 and 10, deflecting the resultant force Rthrust at the angle β from the vertical, see Fig.1. The body 1 is accelerated in the direction of RTΣ,is shifted in a lateral direction from the start, so when starting a martial propulsion unit 23 the fall of LA will not cause damage to the mother ship or ground launch complex. Execution of output sections 11 and 12, respectively, the jet nozzles 9 and 10, the cut in the outer side of the side under an angle of 10 to 75° to the plane perpendicular to the axis of the corresponding nozzle, reduces the length of the length of each of the nozzles 9 and 10 with an outer side and provides earlier expansion of the jet from the side of the housing 1 side, additionally, the jet is moved at a greater distance from the shell 2 and lower heats. When bevel angles less than 10° deviation of the jet is insignificant, and at angles greater than 75° significantly increases the mass of the jet nozzles 9 and 10. Fairing 14 made of heat-resistant material, protects from overheating the front part of the housing 1, where is the system 7 control system and guidance� LA (not shown). Thermal cover 15 reduces the temperature of the fairing 14 and further reduces the temperature of heating the front of the housing 1 and the control system 7. In the event of disturbance on the housing 1 launcher 13, due to the dynamic of their interaction at the exit of the housing 1 or gust of wind, which led to the rotation of the housing 1 in free flight LA around the center of gravity (CG, see Fig.1) at the angle α, the projection ofRg"gravity gravity Rgon the axis that is perpendicular to the new position of the longitudinal axis of the housing 1, creates a torque about the point of application of total thrust power of Rjet nozzles 9 and 10, which returns the body 1 in a position close to vertical. Unlike the prototype, which in the rotation of the housing 1 by the angle α around the center of gravity projectionRg"creates a moment about the tail part of the housing 1, which increases the angle of rotation α. Thus, the proposed device provides stabilization of the housing 1 when the starting acceleration, which increases the reliability of the start and reduces the requirement for rigidity launcher 17, therefore, provides the possibility�spine simplify the design and reduce its weight. Fuel capacity starting of the propulsion unit 5 is chosen such that the required acceleration of the body 1 was provided until complete burnout of the fuel, the control system 7 LA will use the unfixing occurs in the device for 6 mounts and under the influence of thrust Rprovides quick removal starter motor installation 5 from the housing 1. Due to the fact that the jet nozzle of the jet 9 and 10 do not affect the transport and launch the glass 13, eliminating the effects of recoil forces on the pad 17 at the start.

The second variant of the method according to claims.3-4 formulas, Fig.2 and 3, is implemented similarly to the first embodiment. The difference lies in the fact that directly to the operations of start, LA is in TPS 21 with no contact with the environment at all stages of operation, including storage, loading, transportation, finding on the launcher, for example, a shaft 26, which reduces the likelihood of accidental damage to LA and increases its service life. Cover 22 TPN 21 can be made releasable, hinged, breakthrough or destroyed by nomination from LA TPN. To perform the start, additionally, the remote control 29 is activated, the device 28, providing the opening of the cover 27, further activating the actuator device 24 23 partial extension LA, providing a yield of jet nozzles 9 and 10 of the nozzle block 8 and� cavity SCC 21, see Fig.3, which prevents overheating of the housing 1 high-temperature gas jets from the jet nozzle 9 and 10 until the release of LA from TPS 21. When placing SCC in mine launcher 26, the device 23 is partially ejected from the LA cavity SCC 21 also provides for the nomination of jet nozzles 9 and 10 to the outside of silo launchers 26, which provides the ability to increase its lifetime.

The third variant of the method according to claims.5-7 formulas, Fig.4, is implemented similarly to the second embodiment. The difference lies in the fact that due to the fact that the protective cowling 14 is the cover SCC 21, at the start of LA high-temperature gases from the jet nozzle 9 and 10 do not fall into the cavity SCC 21, so there is no need to provide each SCC 21 the extension device 23. At the start of automotive rack or launcher, not shown, TPN 21 is stationary, and to ensure the start from LA mine launcher 26 is activated, the actuator 31 and the device 30 provides a partial extension transport-launch cups from the cavity of the mine to the outside of the jet nozzles 9 and 10.

1. Method start the aircraft, which consists in placing in the launcher, run it to start the propulsion system with the subsequent acceleration under the action of the rods� her jet unit and the starting of the propulsion system after overclocking, characterized in that the starting motor mounting clips in the nose of the aircraft, and thrust form the at least two jet nozzles mounted on its side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, in the process of dispersal protects the front of the aircraft for starting the propulsion system for the fairing mounted on starting the propulsion system, and the starting of the propulsion system provide under the influence of its traction.

2. Method of starting an aircraft according to claim 1, characterized in that the inclination of the jet nozzle at various angles form the lateral component of the thrust.

3. Method start the aircraft, which consists in placing in transport-launch Cup, accommodation, transport and launch of glass in the launcher, start the starting of the propulsion system of the aircraft to open the lid of the transport and launch Cup and the subsequent acceleration under the action of thrust of its jet, and separating the starting of the propulsion system after overclocking, characterized in that the starting motor mounting clips in the nose of the aircraft, and thrust form the at least two jet nozzles mounted onits side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, before you start starting the propulsion system provide a partial extension of the aircraft with the jet nozzle exit from the cavity of the transport and launch Cup, in the process of dispersal protects the front of the aircraft for starting the propulsion system for the fairing mounted on starting the propulsion system, and the starting of the propulsion system provide under the influence of its traction.

4. Method of starting according to claim 3, characterized in that the inclination of the jet nozzle at various angles form the lateral component of the thrust.

5. Method start the aircraft, which consists in placing in transport-launch Cup, accommodation, transport and launch of glass in the launcher, start the starting of the propulsion system of the aircraft to open the lid of the transport and launch Cup and the subsequent acceleration under the action of thrust of its jet, and separating the starting of the propulsion system after overclocking, characterized in that the starting motor mounting clips in the nose of the aircraft, and thrust form the at least two jet nozzles mounted on its side surface with an inclination of their axes at an angle of 10-30° to the longitudinal axis of the aircraft, provide partial placement� aircraft in a transport-launch Cup with the external location of the jet nozzle, in the process of dispersal protects the front of the aircraft for starting the propulsion system for the fairing mounted on starting the propulsion system, and the starting of the propulsion system provide under the influence of its traction.

6. Method of starting according to claim 5, characterized in that the inclination of the jet nozzle at various angles form the lateral component of the resultant force of the thrust.

7. Method of starting according to claim 5 or 6, characterized in that use the mine launcher with opening the lid of the mine, before starting starting the propulsion system provide a partial extension transport-launch cups from the cavity of the mine to the outside of the jet nozzles.



 

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11 cl, 17 dwg

FIELD: weapons and ammunition.

SUBSTANCE: housing is provided with profile power layer (5) located between its outer (3) and inner (4) power layers and is attached to them. Profile power layer is made as a set of mated and fastened to each other longitudinal multiwalled profiles (7) with inner hollow and filled cavities. Longitudinal slot (2) is designed mainly through, it is oriented by housing radius and formed by unit (6) of rigid fixation of the slot form. Unit of rigid fixation is formed by corrugations made on the slot location and to the length of the slot. Corrugations include slot fixing corrugation (14) of inner power layer and corrugation (17) of higher rigidity of profile power layer. Corrugation of higher rigidity is made on one or two adjacent profiles and is reinforced from outside by longitudinal stiffener (19). Profiles cavities adjacent to the corrugation with its stiffener are filled with heat-insulation material. By the second version housing has longitudinal rectangular slot in guiding profile element provided with base, slot-forming and support surfaces. Guiding profile element is located in fixation unit embracing its support surface by slot-fixing corrugation.

EFFECT: improving maintenance reliability with required housing geometry being unchanged.

29 cl, 12 dwg

FIELD: transport.

SUBSTANCE: invention relates to ship loading devices and may be used for loading carrier-launcher into ship multi-seat pit launcher. Proposed set comprises bearing assembly with bearing rod, loading beam with guides, safety and feed devices, locking devices and carriage with wedge-type safety device. Carrier-launcher is secured at loading beam carriage. Multi-purpose crane is used to displace carrier-launcher toward launching pod. Loading beam is mounted at ship deck bearing assembly to down carrier-launcher into launching pod. Finally, carrier-launcher if manually fitted on launching pod bearing assembly.

EFFECT: reduced overloads at carrier-launcher in loading on ship, devices unified for different-length carrier-launcher, higher reliability and safety.

7 cl, 6 dwg

FIELD: weapons and ammunition.

SUBSTANCE: container complex of missiles comprises container with launcher. Said container comprises stiff side and end walls, roof of two jointed panels and independent attachment panel. The main panel is rigidly jointed with the launcher while additional panel is equipped with a drive and arranged behind the main panel to turn about horizontal axis.

EFFECT: lower impact loads at carrier at rocket launching.

4 cl, 4 dwg

FIELD: weapons and ammunition.

SUBSTANCE: weapon comprises a barrel, with a gas-port hole on a side wall, with a gas cylinder and a gas piston, where the barrel is made of two split parts, connected to each other with a threaded head, a bracket for fixation of barrel parts, a ratchet wrench with a fixator for screwing and unscrewing of barrel parts, a handle, a pusher, a pusher's stem, a "П"-shaped bracket for clamping of a service projectile, an electric current battery for creation of an ignition spark, a cock, a muffler. The muffler comprises a body, a sleeve tightly built into the barrel hole, a valve switch, a cylinder, which holds a piston, a stem and a return spring, an accumulator battery with an electric drive and an optical sight. The projectile for firearms is a cartridge, where a fire-resistant plastic bullet is placed, made with a figured slot and a lead hemisphere, electric contacts for ignition of powder and a mini rocket. The mini rocket comprises a body, which consists of a tail part with a chamber for powder and a pressure indicator, a starter casing, a perforated partition for fire transfer, and a front part with propellant.

EFFECT: increased firing range.

2 cl, 1 dwg

FIELD: armament, in particular, recoilless grenade launchers.

SUBSTANCE: the engine body is made integral with the barrel, with centering outer ring bands. An annular shoulder is made on the inner side on the boundary of separation of the engine body and barrel. The pre-combustion chamber is made in the form of a thin-walled metal tube with an inner annular stop on the end face at the annular shoulder and gas conducting openings, and installed in the front bottom of the engine up to the stop against the annular shoulder. The tensioner is centered by a perforated diaphragm in the unconfined space of the grenade rear section and installed inside the pre-combustion chamber on the annular stop of the thin-walled tube. The tensioner represents a screw with a cylindrical head, on which gas conducting grooves are made in the same plane with the gas conducting openings. An additional powder charge is covered with a lattice. An adapter in the form of a short tube with a blind bottom that divides the adapter into two planes - one with a perforated surface and the other - with throttle openings and an initiator is installed between the pre-combustion chamber and the engine nozzle block, the igniter is fastened around them on the outer side.

EFFECT: enhanced reliability of operation of the grenade launcher.

4 dwg

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