Solid-propellant dual-mode rocket engine

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket engine production and can be used in designing flying vehicles incorporating dual-mode engines. The dual-mode solid-propellant engine comprises a front cover, a housing, primary and secondary mode charges arranged consecutively therein, initiation devices, an intermediate bottom made up of an elastic membrane and sleeve, and a nozzle. In the second mode charge, the said sleeve and elastic membrane contain 3 to 6 uniformly distributed strips made from high-strength elastic material. The sleeve strips are attached to the front cover, while those of the membrane are attached to the housing to hold the sleeve and elastic membrane during operation of the second mode charge.

EFFECT: higher reliability of second-mode charge and rocket engine due to ruling out release of sleeve and elastic membrane.

3 dwg

 

The invention relates to rocket technology and can be used to create aircraft that contains a dual-mode engine.

A known design of rocket engines solid fuel, in which the charge separation of the first and second modes are used dividing the bottom of the patents of the Russian Federation NN 2131053 from 05.08.96, IPC F02 9/12, 2197707 from 26.11.01, IPC F42 15/00).

The disadvantage of analogue Pat. 2131053 is a fixed time between the end of charge of the first mode and begin charging the second mode. Increase this time interval can be achieved by increasing the thickness of the intermediate plate, which increases the passive weight of the engine.

The disadvantage of analogue Pat. 2197707 is a great passive weight of the engine due to the massive intermediate bottom plugs.

Also known structure rocket engine RF patent 2272927, IPC F02 9/28 taken by the authors for the prototype, in which the bottom between the charges of the first and second modes is made in the form of an elastic membrane, bonded with programmirovanie destructible connection with elastic sleeve, housed in the channel of the second charge mode. On the other hand, the sleeve is fixed from the front engine cover. The disadvantage of the prototype is the ability of the isolation sleeve and the overlapping critical sections soplao time charge in the second mode, that will cause unplanned sudden rise of pressure in the combustion chamber. A similar process is possible with an elastic membrane. A possible variant of simultaneous separation and sleeves and elastic membrane. The changing nature of the curve of pressure can lead to the deviation of the engine, and strength to the structural failure of the engine.

It is known that under otherwise equal conditions, the pressure in the combustion chamber of the solid rocket motor is inversely proportional to the square of the critical section of the nozzle:

where ν - the exponent in the law of the speed of burning of the solid fuel.

For example, when the level indicator ν in the range of 0.3 to 0.5 overlap only half of the area of the critical section of the nozzle increases the pressure in the combustion chamber of 1.78-2.25 times. To avoid departure sleeves, elastic membrane or them together through the critical section of the nozzle during operation charge of the second mode, it is necessary to ensure reliable fastening sleeve and the elastic membrane to the design of the engine.

The technical task of the present invention is to increase the reliability of the charge of the second mode and the rocket engine by eliminating the departure of the membrane and sleeves.

The technical result is achieved due to the fact that in dual mode rocket engine solid fuel, soda the containing casing, successively installed in it charges the first and second modes, the front cover, the node initiating the nozzle, the intermediate bottom, consisting of elastic membranes and sleeve, the diaphragm and the sleeve inside the entire length contain from 3 to 6 evenly spaced sling made of high-strength elastic material, slings, sleeves mounted on the engine front cover, sling elastic membrane attached to the solid rocket motor case and hold the sleeve and the elastic membrane in the process of charge of the second mode.

Figure 1 shows the design of dual-mode rocket engine solid fuel.

Figure 2 is a view As in figure 1.

Figure 3 - a view B figure 1.

1 - body;

2 - the charge of the first mode;

3 - charge second mode;

4 - front cover;

5 - the site of initiation of the first mode;

6 - host initiation of the second mode;

7, an elastic membrane;

8 - sleeve;

9 - nozzle;

10 - slings;

The presence of a sling inside the sleeve and elastic membrane eliminates the possibility of unexpected abnormal rise of the pressure in the combustion chamber due to secure the sleeve and membrane in the design of the engine after they are programmed unfastening during operation charge of the second mode.

Dual mode rocket engine works as follows. After activation of the node mandatory UN paid the simulation 5 in the process of combustion of the charge of the first-mode elastic membrane 7 and the sleeve 8 to provide thermal protection and devoplment charge of the second mode. After completing the charge of the first mode upon command from the control system of the missile unit is triggered initiation of the second mode 6. The combustion products of the initiator into the cavity between the second charge mode 3 and the sleeve 8 and the membrane 7, is the ignition of the charge of the second mode 3. Under the action of the resulting pressure is scheduled disconnection membrane 7, the sleeve 8. When the charge of the second mode elastic membrane prokladyvaetsya in the direction of the expiration of combustion products using the sling 10 is firmly held in place by bonding with the housing 1 and is gradually being destroyed, swept through the nozzle 5. The sleeve also using the sling 10 is held on the front cover 4, protocolised and gradually being destroyed, swept through the nozzle 5 during operation of the second charge mode 3. The lines 10 are protected from exposure to combustion products when the charges first 2 and second 3 modes of material of the membrane 7 and the sleeve 8.

Thus, this invention improves the reliability and integrity of the second charge mode in all phases of its operation, as well as to improve the reliability of ignition him at a specified time.

Dual mode rocket engine solid fuel containing the front cover, housing, successively installed in it charges first vtorogo modes, the sites of initiation, intermediate plate, consisting of an elastic membrane and the sleeve and nozzle, characterized in that the second charge mode sleeve and elastic membrane contains from 3 to 6 evenly spaced sling made of high-strength elastic material, slings, sleeves mounted on the front cover and sling elastic membrane fixed to the body and hold the sleeve and the elastic membrane in the process of charge of the second mode.



 

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