RU2175398C2 - Launch vehicle - Google Patents

Abstract

FIELD: manufacture of rockets; creation (modification) of launch vehicles. SUBSTANCE: launch vehicle has cruising single-chamber engines at first and second stages; thrust of each engine is equal to thrust of l-st stage control engine; third stage is provided with cruising four-chamber engine whose thrust is equal to that of l-st stage control engine; chambers of cruising four-chamber 3-rd stage engine are provided with high-altitude nozzle attachments forming angularity of nozzle contour. Launch vehicle has cruising single-chamber engines at first and second stages; thrust of each engine is equal to that of l-st stage control engine; third stage is provided with cruising four-chamber engine whose thrust is equal to that of 1st stage control engine; chamber of 1st and 2nd stage cruising engines are provided with short nozzles and chambers of cruising 3rd stage engine are provided with common nozzle attachments. EFFECT: enhanced efficiency of unification of cruising and control engines of three stages of launch vehicle; reduced mass; enhanced reliability; low cost. 3 cl, 9 dwg

Description

 The invention relates to the field of rocket science and can be used to create (modernize) a launch vehicle (LV) containing liquid-propellant rocket propulsion systems (LRE) of three stages.

 The Proton rocket equipped with a stage III rocket engine containing the RD-0212 engine, consisting of the marching single-chamber RD-0213 engine and the four-chamber steering engine RD-0214 (The Arms of Russia catalog, Volume VI, 3AO Military Parade, Russia, is known Moscow, 1996-1997; p. 611-analogue).

 The known satellite "Sputnik", "Moon", "Vostok", "Voskhod", "Lightning", "Soyuz" with stage I and II rocket engines containing marching four-chamber engines RD-107 and RD-108 with two and four steering chambers.

 The Soyuz launch vehicle with the 3rd stage rocket engine containing the four-chamber marching engine RD-0110 with four steering nozzles is known (Arms of Russia catalog, volume VI, 3AO Military Parade, Russia-Moscow, 1996-1997; pp. 542-544 , p. 607 - prototype).

 The specified launcher, selected as a prototype, is equipped with multi-chamber engines of different thrusts, which, compared with marching single-chamber engines, have a significantly shorter length, and therefore the dimensions of the entire rocket are reduced, which ultimately leads to a noticeable gain in mass.

At the same time, the design of a multi-chamber engine has the following disadvantages:
does not allow to unify marching and steering engines (units) of the three stages of the launch vehicle;
does not allow the maximum use of the midship rocket;
does not allow for the height of the flight of the rocket to adjust the geometric degree of expansion of the nozzle;
expanding nozzle parts and engine protection have a large mass;
when the engines of the I and II stage, starting to work from the Earth, there is a large unstable bottom resistance.

 The task of the invention is to remedy these disadvantages: ensuring the unification of marching and steering engines (units) of the three stages of the launch vehicle, reducing the weight of the launch vehicle, increasing the geometric degree of expansion of the nozzles, improving the operational characteristics of the launch vehicle.

 The task is achieved by the fact that in the launch vehicle, which contains marching and steering four-chamber engines at the I, II and III stages, marching single-chamber engines are installed at the I and II stages, the thrust of each of which is equal to the thrust of the four-chamber steering engine of the I stage, and at the III stage marching four-chamber engine with a thrust equal to the thrust of the four-chamber steering engine of the 1st stage, while the chambers of the marching four-chamber engine of the III stage are equipped with high-altitude nozzle nozzles forming a kink in the nozzle contour.

In FIG. 1 shows the structural layout of the pH, in FIG. 2 is a view A, in FIG. 3 - section BB, in FIG. 4 - section bb, where:
1 - LRE of the first stage of the launch vehicle;
2 - LRE of the II stage of the launch vehicle;
3 - LRE III stage launcher;
4 - mid-flight single-chamber engine of the first stage;
5 - mid-flight single-chamber engine of the II stage;
6 - steering two-chamber engine of the first stage;
7 - steering four-chamber engine of the II stage;
8 - mid-flight four-chamber engine of the III stage;
9 - chamber marching four-chamber engine of the III stage;
10 - high-altitude nozzle nozzles of the chamber of the marching four-chamber engine of the III stage.

 The first stage of the launch vehicle (see Fig. 2) consists of four side rocket engines 1, each of which contains four mid-flight single-chamber engines 4 and one steering two-chamber engine 6.

 The second stage of the launch vehicle consists of a central rocket engine 2, starting to work from the Earth, which contains four mid-flight single-chamber engines 5 and one steering four-chamber engine 7.

 LRE 3 (see Fig. 3) of the III stage of the LV consists of one marching four-chamber engine 8, the chambers of which contain chambers with an earth nozzle 9 (see Fig. 4) and high-altitude nozzle nozzles 10, forming a contour fracture with earth nozzles. A nozzle with a kink in the earth’s contour and its transition to a high-altitude one has ~ 10% less mass than a high-pressure nozzle without a kink in the contour.

 Currently, work is underway to modernize the Soyuz launch vehicle, which has been in operation for 35 years.

 TsSKB believes that at all three steps it is advisable to replace the engines used with new ones.

 The creation of marching engines for the I, II, and III stages of the Soyuz launch vehicle can be carried out on the basis of the RD-0245 four-chamber steering engine (module) modified for oxygen-kerosene fuel, which is in serial production, without which it is impossible to upgrade the launch vehicle. To reduce by four times the number of chambers on the rocket propulsion system of the first and second stage rockets, it is advisable to use the RD-0216 engine chamber, the thrust of which is equal to the thrust of the four-chamber RD-0245 engine. At the same time, the height along the axis of the I and II stage engines is ~ 1200 mm, which is 1700 mm less than the height specified in the technical specifications.

 The thrust vector control of four stage I rocket engines can be provided with two four-chamber RD-0245 engines or four two-chamber RD-0245 engines. The thrust vector control of the second stage rocket engine can be provided with one RD-0245 four-chamber engine.

 In each stage I rocket engine, the number of marching engines can be reduced to three if you use one four-chamber steering engine to control the thrust vector in each engine. The technical requirements of the TsSKB can be fully met by changing the internal propulsion parameters of both mid-flight engines and steering.

 The thrust vector control of the III stage rocket engine can be provided by turning the marching chambers or steering nozzles (chambers).

 In another version of the LV, the goal is achieved by the fact that in it at stage I and II there are marching single-chamber engines, the thrust of each of which is equal to the thrust of the four-chamber engine of the first stage, and at stage III there is a marching four-chamber engine with a thrust equal to the thrust of the four-chamber engine of the I stages, while the chambers of the mid-flight engines of the I and II stages, made with shortened nozzles, and the chambers of the mid-flight engine of the III stage are equipped with common nozzle nozzles.

In FIG. 5 shows the structural layout of the PH (second option), FIG. 6 is a view of D, in FIG. 7 is a cross-section EE, in FIG. 8 is a section DD, in FIG. 9 - section MF, where:
11 - liquid propellant rocket engine with a common nozzle nozzle of the first stage of the launch vehicle;
12 - liquid propellant rocket engine with a common nozzle nozzle of the second stage of the launch vehicle;
13 - liquid propellant rocket engine with a common nozzle nozzle of the III stage of the launch vehicle;
14 - main engine with a common nozzle nozzle I stage;
15 - main engine with a common nozzle nozzle of the II stage;
16 - a chamber with a shortened nozzle of the engine of I and II stages;
17 - common nozzle nozzles of the engine of the I and II stages;
18 - mid-flight four-chamber engine with a common nozzle nozzle of the III stage;
19 - General nozzle nozzles of the engine of the III stage.

 The first stage of the launch vehicle (see Fig. 6) consists of four lateral rocket engines 11, each of which contains four mid-flight single-chamber engines 14 with a common nozzle nozzle and one steering two-chamber engine 6.

 The second stage of the launch vehicle consists of a central rocket engine 12, starting to work from the Earth, which contains four mid-flight single-chamber engines 15 with a common nozzle nozzle and one steering four-chamber engine 7.

 In the liquid propellant rocket engine of the first and second stages of the chamber 16 (see Fig. 7), they are made with shortened nozzles, to which a common nozzle nozzle 17 is connected.

 The liquid propellant rocket engine 13 (see FIG. 8) of the III stage of the launch vehicle consists of one mid-flight four-chamber engine 18, a chamber with an earth nozzle 9 (see FIG. 9) which is connected to a common nozzle nozzle 19.

 Three or four modular single-chamber mid-flight engines with shortened nozzles of the I and II stages and chambers of the mid-flight four-chamber engine of the III stage in the area of the output sections are connected to common nozzle nozzles having a cross section in the direction perpendicular to the axis of the engine with the shape of an epicycloid with three or four branches. The total nozzle nozzles, compared with the full-sized parts of these nozzles, have ~ 34% less mass.

 The use of a common nozzle nozzle allows to increase the specific impulse of thrust (to reduce the height of the engine) due to the maximum use of the missile midship, height adjustment of the geometric degree of expansion of the nozzle (when the nozzle contour and nozzle break) and a decrease in the bottom resistance of the launch vehicle.

 The application of the proposed invention can effectively unify the marching and steering engines of the three stages of the launch vehicle, reduce the mass of the structure, increase its reliability, reduce the cost of creating a launch vehicle.

 The manufacture (modernization) of the proposed launch vehicle does not require special technologies and is implemented by known methods.

Claims (2)

 1. A booster rocket containing marching and steering engines at I and II stages and a marching four-chamber engine with four steering nozzles at the III stage, characterized in that marching single-chamber engines are installed in it at I and II stages, the thrust of each of which is equal to the thrust the steering engine of the first stage, and at the third stage there is a marching four-chamber engine with a thrust equal to the thrust of the steering engine of the first stage, while the cameras of the marching four-chamber engine of the third stage are equipped with high-altitude nozzle nozzles forming a kink nozzle contour.  2. A booster rocket containing marching and steering engines at I and II stages and a marching four-chamber engine with four steering nozzles at the III stage, characterized in that marching single-chamber engines are installed in it at I and II stages, the thrust of each of which is equal to the thrust the steering engine of the first stage, and at the third stage there is a four-chamber mid-flight engine with a thrust equal to the thrust of the first stage steering engine, while the main engine chambers of the first and second stage, made with shortened nozzles, and the main engine chamber of the third stage and equipped with common nozzles.

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