Solid-propellant rocket engine to withdraw rocket jettisonable parts. RU patent 2513052.

IPC classes for russian patent Solid-propellant rocket engine to withdraw rocket jettisonable parts. RU patent 2513052. (RU 2513052):

F02K9/30 - with the propulsion gases exhausting through a plurality of nozzles

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Proposed engine comprises body with solid-propellant multigrain charge arranged between support grates, two gas-communicated nozzles of different diameters of throat and igniters with pyrotechnical compound equipped with exploder. every said igniter is fitted in one of ante-nozzle cavities arranged on every side from charge support grates. Weight of igniter on nozzle side of smaller throat is larger than that of exploder of opposite igniter and/or exploders of igniters feature different energy capacity. Energy capacity of the exploder on smaller throat nozzle side is larger than that on opposite side.

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises body with solid-propellant multigrain charge arranged between support grates, two gas-communicated nozzles of different diameters of throat and igniters with pyrotechnical compound equipped with exploder. every said igniter is fitted in one of ante-nozzle cavities arranged on every side from charge support grates. Weight of igniter on nozzle side of smaller throat is larger than that of exploder of opposite igniter and/or exploders of igniters feature different energy capacity. Energy capacity of the exploder on smaller throat nozzle side is larger than that on opposite side.

EFFECT: decreased disturbances of the rocket end jettisonable structure.

1 dwg

The invention relates to the field of rocket and space technology and can be used in the design of engines of firm fuel.

It is known that in order to ensure the withdrawal of separable parts missiles on guide pins with flight trajectory without collision with a missile requires that the thrust vector of the withdrawal was with the vector of the missile some angle, for example, within approximately 3°10C (see Graceful "Engineering methods for calculating the dynamics of a missile with a solid rocket motor", str. - M: SEC "informtehnika", 1995).

When using gazobetonnyh mnogomernyh engines (number of nozzles from 2 and more) is most simply, it is achieved due to the different sizes of oppositely located in the plane of withdrawal critical sections of nozzles. The thrust vector, implemented in the nozzle with great critical section, at the same pressure in gazolazernoi the combustion chamber is always greater than the thrust vector, implemented in the nozzle with a lower critical-section with the same parameters of the output part of the nozzle. Due to this, the total thrust vector is some angle in respect to the thrust vector of the same size critical sections.

Known engine contains a body with two nozzles, in which solid propellant charge is divided into two parts, between which there are igniter device, fired from one of the actuator (see "special-purpose Motors pulse type of solid fuel. Principles of design, design and the experience of development", the authors Iamgladso, Uperman and others, p.102, RIS. - M: Zoneinformation, 1990).

The disadvantage of this engine when used as an engine of evading object is that at the initial moment due to the mismatch of the thrust vector with vectors appears disturbing moment and led object unevenly separated from the rocket. This creates resentment as a rocket that has to fend off the indignation of the control commands and detachable object that moves along non-nominal trajectory.

Object of the present invention is to provide a solid rocket motor fuel for withdrawal detachable parts missiles, allowing to reduce indignation at the initial moment of movement detachable object due to the fact that, overall thrust vector Department coincides with the vector of movement.

This is achieved by famous rocket engine of solid fuel for the Department of the rocket contains the explosives c pyrotechnic composition and the actuator, and each of the devices installed in one pridniprovya volumes, placed on each side of the support grates charge, if this mass of pyrotechnic composition of igniter ,for example, smoky gun powder (PDA) from the nozzle with a smaller diameter critical section more mass pyrotechnic composition opposite igniter or pyrotechnic compositions of igniters have different energy capacity, and from the nozzle with less critical section energy ability pyrotechnic composition more than the opposite.

Due to such design, the total thrust vector coincides with the vector of movement, as at operation of such devices, at the initial moment in pridniprovya volumes are created different pressures are products of combustion, which, dripping through the critical section, create equality rods R 1 =R 2 . This should satisfy the condition: R 1 ·d KR1 2 =P 2 ·d CR 2 , where d KR1 <d kr , P 1 >R 2 .

Detachable object without distortions at the initial moment the movement is separated from the rocket trajectory, coinciding with the trajectory of the rocket. As pridniprovye engine volumes associated gas connection - a common combustion chamber, the pressure in pridniprovya volumes after a while levelling R 1 =R 2 ), in each nozzle is implemented its thrust vector (R 2 >R 1 ) and their total thrust vector gets the calculated angle between the vector of movement and leads detachable object with the flight path of the missile.

The same effect is achieved due to the fact that the explosives contained pyrotechnic composition of various power capacities. For example, smoky gun powder (ANC) in the igniter on the part of smaller diameter critical section of the nozzle

( d to R 1 )

and coarse-grained black powder (CSDP) in the opposite igniter PDA when ignited burns faster than CSDP, creating pridniprovya volumes in a fixed moment of time is different is the pressure of combustion products. The same effect is reached at simultaneous use of these principles.

In addition, the placement of explosives in pridniprovya volumes compared with explosives in the middle part can increase the reliability of lighting mnogoserijnogo charge due to the fact that the products of combustion from each igniter first move towards each other, and then in the opposite direction, that is, more time interacting with the surface of checkers charge.

The design of the engine of withdrawal is illustrated by a drawing, which shows a General view of the engine (Fig. 1). The engine consists of a body in the form of a cylinder (1), enclosed on two sides solovyi lids (2)containing a nozzle (3) with different values of the diameters of critical sections

( d to R 1 < d to R 2 )

. The building is located mnogochastichnye solid propellant charge (4).

In nozzle cover (2) niduses (5) to install cutter (6) and mounting perforated derjati (7), as well as enshrined support grid (8)restricting the movement of charge (4).

Inside holder are cases igniter containing pyrotechnic composition (9). The cavity of the actuator and of the igniter is connected afterburner channel (10). The mass or energy ability pyrotechnic composition (9) from the nozzle (3)having a lower value of the diameter of the critical-section (d WP1 ), more than the mass or energy ability pyrotechnic composition from the opposite nozzle that have a higher value of the diameter of the critical section

( d to R 2 ) .

The engine works as follows.

When submitting commands to the operation of engine fire cutters (6), force their combustion products, dripping through afterburner channels (10), destroy case of ignition and light pyrotechnic mixtures (9)contained in them. Products of combustion of explosives through the perforated holder (7) expire in pridniprovye volumes and further to the surface mnogoserijnogo charge of solid fuels (4). Due to the different mass or energy abilities of pyrotechnic composition of explosives in pridniprovya volumes created different meanings pressure of products of combustion, which, dripping through nozzles produce the same thrust of each nozzle. Pyrotechnic composition ensures condition:

P 1 x d to R 1 2 = P 2 x d to R 2 2

. Detachable object without distortions at the initial moment the movement is separated from the rocket.

As pridniprovye volumes of associated gas connection - a common combustion chamber, the pressure of combustion products at some time in pridniprovya volumes aligned (P 1 =P 2 ) and expire through nozzles with different diameters of a critical section realize their vectors thrust (R 2 >R 1 ). Total thrust vector gets the calculated angle between the vector of movement and leads detachable object with the flight path of the missile.

The engine of this construction is planned to be used when pulling a missile unit of the emergency rescue of astronauts at the launch of the latest rocket.

Rocket solid fuel engine for withdrawal separated parts of a rocket with a frame containing a solid mnogochastny charge, located between basic lattices and two gatewayname nozzles with different diameters critical sections (d kr ), characterized in that it contains the explosives with pyrotechnic composition, supplied with a cutter, and each of the devices installed in one pridniprovya volumes, placed on each side of the support grates charge, the mass of pyrotechnic composition of the igniter with the nozzle with a smaller diameter critical section more mass pyrotechnic composition opposite igniter and/or pyrotechnic compositions of igniters have different energy capacity, and from the nozzle with less critical section energy ability pyrotechnic composition more than the opposite.