RU2329390C1 - Solid-propellant launching rocket engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: solid-propellant launching rocket engine incorporates an annular combustion chamber with a nozzle unit, an igniter and multi-grain charge made up of all-round burning grains representing equal-diameter channel cylinders buried one into another, the grains axes being arranged on circular arc. The distance between the channel cylinder axes and circular arc diameter the said grain axes are located on, are defined by ratios protected by this invention. Cavities between the grains adjoining the outer and/or inner annular chamber outline accommodate additional small caliber grains. The said small-caliber grains are made in the form of channel and/or channelless cylinders of all-round burning, or in the form of channel cylinders armoured over the outer surface.

EFFECT: higher efficiency of launching engine thanks to optimum filling of its combustion chamber with fuel.

3 cl, 9 dwg, 1 tbl

Description

The invention relates to the field of rocketry and can be used in the design, development and manufacture of plug-in charges and rocket engines of solid fuel.

-го) профиля (в виде утопленных друг в друга канальных цилиндров).When developing aviation and tactical missiles with inseparable marching and launching stages, the layout of the propulsion system is used (Figure 1) with the tandem arrangement of the marching and launching engine, while the gas duct of the marching engine passes through the combustion chamber (KS) of the starting engine (ST). In this case, the COP is formed in the form of an annular chamber formed by the outer shell of the rocket body and the gas duct (Figure 2). For DM use, as a rule, channel round checkers of solid rocket fuel (TRT) of comprehensive combustion, providing high thrust-to-weight ratio of the rocket engine during the launch period (Figure 2). Also known are more optimal designs of TRT charges for diabetes (Figure 3, Figure 4) providing increased longitudinal stability of the checkers and traction ratio of diabetes (US Pat. RU 2272167) due to the developed figure-eight (

-th) profile (in the form of channel cylinders recessed into each other).

Charge design according to US Pat. RU 2272167 of 03.20.2006 was adopted by the authors as a prototype.

An object of the invention is to increase the efficiency of a rocket engine with an annular combustion chamber, which ensures, due to the optimal filling of fuel cells with a fuel, increasing the thrust-weight ratio and reliability of a rocket engine.

-го профиля, расстояние между осями которых (L) составляет:The technical result of the invention consists in the execution of a starting engine containing an annular combustion chamber with a nozzle block, an igniter and a multi-rocket charge of solid rocket fuel from comprehensive combustion checkers. In this case, the TRT charge is multi-shell in the form of channel circular cylinders of equal diameter recessed into each other, i.e. as

profile, the distance between the axes of which (L) is:

2e <L <2e + d,

where e is the thickness of the burning arch, d is the diameter of the channel (Figure 4)

Moreover, the axis of the centers of the cylinders are located on an arc of a circle with a diameter of (D ₁ + D ₂ ) / 2, where D ₁ is the inner diameter of the CS along the outer contour, D ₂ is the inner diameter of the CS along the inner contour, and between the peripheral sections of the profile of the charge checkers facing external and / or internal circuit KS SD, placed additional small-caliber checkers. In this case, additional checkers can be made in the form of channel and / or channelless cylinders of all-round combustion or in the form of channel cylinders, armored on the outer surface.

-го профиля, преимущественно у внешнего контура кольцевой КС, образуются весьма значительные "пустоты". С учетом параметра заряжания æ=S/F_св проф. Ю.А.Победоносцева (Я.М.Шапиро и др. "Теория ракетного двигателя на твердом топливе", М., 1966 г., стр.109) часть площади указанных "пустот" может быть заполнена топливом при допустимых газодинамических параметрах двигателя в целом (æ~100...120). При этом одним из эффективных вариантов заполнения пустот является размещение в последних канальных и/или бесканальных малокалиберных шашек всестороннего горения (Фиг.6, Фиг.7, Фиг.9). В зависимости от конкретных особенностей СД может быть полезна конструкция с заполнением "пустот" канальными бронированными по наружной поверхности малокалиберными шашками (Фиг.8).The essence of the invention lies in the optimal filling of the cross section of the COP with fuel. When laying checkers

profile, mainly at the outer contour of the annular CS, very significant “voids” are formed. Given the charging parameter æ = S / F _St. prof. Yu.A. Pobedonostseva (Ya. M. Shapiro et al. "The theory of solid propellant rocket engine", Moscow, 1966, p. 109) a part of the area of the indicated "voids" can be filled with fuel for admissible gas-dynamic engine parameters in whole (æ ~ 100 ... 120). In this case, one of the effective options for filling the voids is the placement in the last channel and / or channelless small-caliber checkers comprehensive combustion (Fig.6, Fig.7, Fig.9). Depending on the specific features of the DM, a design with filling the "voids" with small-caliber checkers armored on the outer surface can be useful (Fig. 8).

The introduction of small-caliber drafts into the charge structure increases the total momentum of the LED. Comparative data on the parameter æ and the value of the total thrust impulse (I _Σ ) of the charge are given in comparison with the prototype in the table.

Considering that, due to the short duration of operation of the LEDs (as a rule, for the missiles under consideration no more than 1 s), the CSs are not equipped with thermal protection, which contributes to a significant increase in heat losses in the CS wall. Equipping the charge with additional small-caliber checkers allows, fully or partially, to compensate for these heat losses.

As can be seen from the table, equipping the charge with small-caliber checkers according to the patented technical solution does not increase the mass of degressive fuel residues, but at the same time provides an increase in I _Σ SD compared to the prototype by 2.8 ... 5%.

The invention is illustrated by drawings.

Figure 1. Propulsion system diagram

1 - marching stage (marching engine);

2 - starting stage (starting engine);

3 - gas duct.

Figure 2. Cross section of annular CS SD (analogue)

4 - outer shell DU;

3 - gas duct;

5 - checkers charge TRT.

Figure 3. The cross section of the annular KS SD with the profile of the TPT charge checkers according to patent RU 2272167 (prototype).

Figure 4. Profile of charge checkers (for prototype)

6 - equidistant surfaces;

7 - degressive residue;

d is the diameter of the channel.

Figure 5. Patented SD design

8 - KS case with nozzle block;

9 - igniter;

10 - small-caliber checkers.

6. Cross section of patented design of diabetes and dependence S (e).

S is the combustion surface of the charge,

e - burning (current) arch,

10 - small-caliber checkers,

11 - S (e) for the prototype,

12 S (e) - for patentable solution.

7. Variant of the profile of small-caliber charge checkers TPT and the dependence S (e) according to the patented invention with channelless small-caliber additional checkers (single placement of additional checkers)

Dependencies S (e):

11 - for the prototype;

12 for a patentable invention.

Fig. 8. Variant of the profile of small-caliber charge checkers TPT and the dependence S (e) according to the patented invention with channel small-caliber additional checkers, armored on the outer surface.

Dependencies S (e):

11 - for the prototype;

12 for a patentable invention.

Fig.9. Variant of the profile of small-caliber charge checkers TRT and the dependence S (e) according to the patented invention with channelless small-caliber additional checkers (group placement of additional checkers).

Dependencies S (e):

11 - for the prototype;

12 for a patentable invention.

-го профиля.An essential distinguishing feature of the patented SD from the prototype is the introduction of additional small-caliber checkers placed in the voids between the checkers into the design of the SD

profile.

Patented LED (Figure 5, Figure 6) includes a COP (8) with a nozzle block, an igniter (9), a charge of TPT from channel pieces (5) of a shaped profile and small-caliber pieces (10).

SD works as follows:

When a pulse is supplied to the igniter (9), the latter fires and ignites the drafts (5), (10) of the TPT charge on the outer surfaces and channels. The high-temperature gases formed during the burning of the drafts flow out through the KS nozzle block (8), creating a jet thrust.

Patented DM is experimentally tested at the prototype level, including:

- annular CS with dimensions:

D ₁ = 110 mm;

D ₂ = 50 mm;

length - 150 mm;

-го профиля и 5 дополнительных малокалиберных канальных шашек, размещенных вблизи внешнего диаметра кольцевой КС.- TRT charge - 5 pieces of ballistic TPT 140 mm long

profile and 5 additional small-caliber channel blocks placed near the outer diameter of the annular CS.

- igniter - 7 g of smoky gunpowder in a shell of polyethylene.

A positive effect of the invention is an increase in the efficiency of LED missiles, in terms of increasing the total thrust impulse, ensuring a steady exit of LEDs to the operating mode, and the reliability of the operation of LEDs in general.

Charge characteristics Section Profile Option Geometrical dimensions, mm S cm ² F _St. cm ² well ΔI _Σ ,% "round" (without extra charges) 1385.9 21.80 63.6 -

-й профиль (без доп. зарядов) - прототипThe main one is

profile (without additional charges) - prototype Main:
D = 32
d = 6
L ₁ - 140 1318.3 16.8 78.7 + 6.5% relative to round profile option The main one is

-th profile ("eight") + add. charge 6 Basic + add. charge: D ¹ = 10
d ¹ = 0
L ₁ - 140
5 checkers 1544.2 14.8 104.5 + 3.8% compared to the "eight" The main one is

profile + add. charge 7 Basic + add. charge: D ¹ = 8
d ¹ = 4
L ₁ - 140
5 checkers 1616.3 15.4 106.0 + 2.8% compared to the "eight" The main one is

profile + add. charge of Fig. 8 Basic + add. charge: D ¹ = 10
d ¹ = 4
L ₁ - 140
5 checkers 1457.5 14.0 104.0 + 5.0% compared to the "eight" The main one is

profile + add. charge of Fig. 9 Basic + add. charge: D ¹ = 4
d ¹ = 0
L ₁ -140
15 checkers 1639.6 15.4 105.0 + 3.0% relative to the figure eight The table indicates: D is the outer diameter of the charges

profile
d is the diameter of the channel of charges

profile
D ¹ - the outer diameter of the additional small-caliber charges,
d ¹ - channel diameter of additional small-caliber charges,
L ₁ - the length of the charges (checkers)

profile and additional small-caliber charges
S is the total combustion surface of the charge,
æ - charging parameter prof. Yu.A. Pobedonostseva,
ΔI _Σ - "increase" of the total impulse of traction SD,
F _St. - the area of free passage of gases in the channel section of the COP.

Claims (3)

1. A solid rocket starting rocket engine containing an annular combustion chamber with a nozzle block, an igniter and a multi-catter charge from comprehensive combustion checkers in the form of channel circular cylinders of equal diameter "recessed" into each other, the distance between the axes of which (L) is 2e <L <2e + d, where e is the thickness of the burning arch, d is the diameter of the checker channel, characterized in that the axis of the centers of the cylinders are located on a circular arc of diameter (D) D = (D ₁ + D ₂₎ / 2, wherein D ₁ - inner diameter of the annular combustion chamber outer loop, D ₂ - inner diameter of the annular combustion chamber of the inner contour, while in the cavities between checkers adjacent to the outer and / or inner contour of the annular combustion chamber has additional checkers caliber. 2. The solid rocket starting rocket engine according to claim 1, characterized in that the small-caliber checkers are made in the form of channel and / or channelless cylinders of all-round combustion. 3. The solid rocket starting rocket engine according to claim 1, characterized in that the small-caliber checkers are made in the form of channel cylinders, armored on the outer surface.

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