RU2451816C1 - Propellant charge for rocket engine - Google Patents

Abstract

FIELD: power engineering.

SUBSTANCE: propellant charge for a rocket engine is made in the form of a solid propellant grain with a central through channel and a partially armoured side surface. The total area of armoured coating corresponds to the ratio protected by this invention. The armoured coating of the side surface is arranged as "point" with the area of a separate "point" armoured coating on the external surface of the charge equal to 0.5…3.0 mm². The armour points are installed on the side surface of the charge arbitrarily with provision of the distance between them of at least 3.0 mm.

EFFECT: invention makes it possible to reduce maximum pressure in a combustion chamber of a solid propellant rocket engine, to reduce maximum dimensions of armoured particles ejected during its operation.

2 cl, 3 dwg

Description

The invention relates to the field of rocket technology and can be used in the design and manufacture of plug-in charges of solid rocket fuel (TRT), mainly for rocket engines of solid fuel (solid propellant rocket propulsion) of aircraft missiles.

There are known designs of charges for rocket engines of solid fuel (solid propellant rocket engines) of aircraft missiles according to patents: RU 2178092, RU 2221159, RU 2211352, RU 2298109.

It is also known that the launch of rockets with solid propellant rocket engines from under the fuselage of the carrier aircraft carries a number of risks, the main of which are:

1. The probability of stalling the aircraft engine due to the "suction" of the solid propellant rocket of the launch rockets in the air intake of the aircraft engine (HELL).

2. The probability of penetration into the air intake of aircraft engines of solid particles of the TRT charge of a rocket engine, namely particles of armor-plating charge.

To a certain extent, these problems are solved in US Pat. RU 2178092, RU 2221159, RU 2211352, RU 2298109.

The invention according to US Pat. RU 2355906, IPC F02K 9/10, application of October 4, 2007, publ. 05/20/2009, the authors accepted for the prototype.

The disadvantages of the design of the prototype are:

- the presence in the products of combustion (PS) of “normalized” charge particles weighing no more than 1.5 g, the effect of which on the blades of the AD compressor, although it ensures the safety of launching rockets and a carrier aircraft, nevertheless significantly reduces the working life of the AD:

- limited capabilities of the prototype design to provide the required dependences S (e), P (τ), R (τ) for solid propellant rocket motors (S is the current combustion surface of the TRT charge, e is the burning arch, P is the pressure in the solid propellant combustion chamber, R is the thrust RTTT, τ is the time).

An object of the invention is the creation of a solid propellant charge for a rocket engine, for example an aircraft rocket, ensuring high efficiency of the rocket RD, increased safety of the combat use of the rocket for the carrier aircraft, providing an increased working life of the aircraft carrier’s blood pressure due to the minimum emission of TRT charge armor particles no more than 0.02 g

The technical result of the invention is to create a solid rocket fuel charge (Fig. 1) for a rocket engine, while the charge is made in the form of solid rocket checkers with a central through channel and a partially reserved side surface, while the total area of the armor coating corresponds to the ratio

S _bp > S _o -χ _pore · F _cb , where

S _bp - the total area of armor;

S _o - surface area of the combustion of the charge;

χ _pore is the threshold value of the parameter of Professor Yu.A. Pobedonostsev for solid rocket fuel;

F _St - the area of free passage of gases at the nozzle end of the charge, while the armor coating is made "point" with the area of a separate "point" armor coating on the outer surface of the charge of 0.5 ... 3 mm ² and the minimum overall distance (L) between the individual "point" armor coatings not less than 3 mm.

Patented charge design allows you to realize the optimal, depending on the purpose of the solid propellant rocket and rocket, the dependence (Figure 2) S (e) and, accordingly, the dependence "pressure - time" P (τ), "thrust - time" R (τ) for solid propellant only for aircraft missiles, but also for missiles of other classes.

The invention is illustrated in graphic materials.

Figure 1 - patented design of the solid-state channel charge with "point" reservation on the side surface, ensuring close to neutral dependence S (e).

1 - checker TRT

2 - channel

3 - a separate "point" armor plating (the dimensions of the "point" armor plating in Fig. 1 are conventionally increased).

Figure 2 - dependence of P (τ) for the patented design and prototype with a neutral dependence of P (τ).

P _max1 - maximum pressure in the solid propellant rocket charge without a "point" armor coating.

P _max2 - maximum pressure in the solid propellant rocket _motor for the patented design.

Figure 3 - the nature of the burnout TPT charge near the "point armor coating".

1 - checker TRT

2 - channel

3 - separate "point" armor plating (in Fig. 3, the dimensions of the "point" armor plating are conventionally increased)

4 - equidistant surfaces.

An example implementation of a patentable design.

A prototype of the patented charge design is made of ballistic quick-burning TPT with charge sizes:

- length - 1200 mm

- outer diameter - 120 mm

- channel diameter - 40 mm

- "point reservation" of the lateral surface was carried out in the form of sites bonded to the lateral surface of the charge with sizes of 0.5 ... 3.0 mm ² , randomly located on the lateral surface of the charge.

The essence of the invention (Figure 3) consists in targeted accounting for the effect of short-term degeneration of "pointwise" armored charge surfaces and their influence on the resulting combustion surface S ₀ (e), and their minimal effect, for example, on the distortion of the neutral dependence S (e) [R (τ)]. In fact, the patented design allows, in addition to the neutral dependence S (e), R (τ), to ensure a significant decrease in the value of P _max (Figure 2) when the solid propellant rocket motor reaches the operating mode with both neutral and other programmed dependence R (τ).

"Point" booking in the example was carried out by brushing a solution of polymethylmethacrylate and colloxylin in acetone using a template (US Pat. RU 2355906 from 05.20.2009).

The positive effect of the invention is the creation of highly efficient designs of TRT charges with minimal economic costs in manufacturing.

The essence and distinguishing features of the patented invention are:

1. In the implementation of the "point" (local) reservation of the surface of the charge.

отдельного "точечного" бронепокрытия в пределах

- 0,5…3,0 мм².2. In the implementation of the area

separate "point" armor plating within

- 0.5 ... 3.0 mm ² .

высока вероятность срыва (смыва, вымыва) "точечного бронепокрытия", с поверхности заряда газовым потоком от срабатывания воспламенителя и дополнительным газопритоком от горящих поверхностей заряда ТРТ, за счет малой площади скрепления "точечного" бронепокрытия с поверхностью тела шашки заряда ТРТ, т.е. эффект "точечного" бронирования может не сработать в полном объеме. При площади отдельного "точечного"

снижается, уменьшается сам эффект "точечного" бронирования, как такового, - характер "развития" поверхности S(e) под бронированным "точечным" участком (Фиг.3) заряда затрудняет осуществление программированной зависимости Р(τ), R(τ) в требуемом объеме.Moreover, with the area of a separate "point" armor coating

there is a high probability of disruption (flushing, washing out) of "point armor plating" from the surface of the charge by the gas stream from the ignition and additional gas influx from the burning surfaces of the TPT charge, due to the small area of bonding of the "point" armor coating to the surface of the body of the TRT charge plate, i.e. the effect of a "point" reservation may not work in full. With the area of a separate "spot"

decreases, the effect of the "point" booking itself decreases, as such - the nature of the "development" of the surface S (e) under the armored "point" section (Figure 3) of the charge makes it difficult to implement the programmed dependence P (τ), R (τ) in the required volume.

3. In ensuring the overall distance between individual "point" armored coatings of at least 3 mm, which is due to the need to ensure strict geometric combustion along the equidistant charge surfaces of the TRT, taking into account permissible technological tolerances for manufacturing charges in production conditions.

The essence of the “point” reservation with respect to the TPT plug-in charge designs is to use the effect of “fast” degeneration of the burning charge surfaces under the “armor coating points” due to the main sign of TPT combustion, namely burning along equidistant surfaces.

The patented TPT charge design works as follows: under the action of an igniter (initiator), the unarmored surface of the charge ignites. Charge burning occurs on equidistant surfaces, which allows us to realize the required dependences S (e), R (τ).

The positive effect of the invention is to increase the efficiency, reliability and safety when launching aircraft missiles from under the fuselage of a carrier aircraft, increasing the working life of blood pressure.

The actual maximum dimensions of the ejected armored particles from the solid propellant rocket engine with the charge structure according to the patented solution did not exceed 0.02 g.

Claims (2)

1. A solid propellant charge for a rocket engine, made in the form of a solid rocket fuel checker with a central through channel and a partially reserved side surface, while the total area of armor plating corresponds to the ratio:
S _br > S _o -χ _pore · F _St ,
where S _br - the total area of armor;
S _o - surface area of the combustion of the charge;
χ _pore is the threshold value of the parameter of Professor Yu.A. Pobedonostsev for solid rocket fuel;
F _St - the area of free passage of gases at the nozzle end face of the charge, characterized in that the armor coating is made "point" with the area of a separate "point" armor coating on the outer surface of the charge of 0.5 ... 3.0 mm ² , with booking points located on the side surface charge arbitrarily with a dimensional distance (L) between them of at least 3.0 mm. 2. A solid fuel charge for a rocket engine according to claim 1, characterized in that the armor coating is made directly on the side surface of the charge, for example, using a template.

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