RU2240264C2 - Rocket acceleration block (variants) - Google Patents

Abstract

FIELD: spacecraft engineering.

SUBSTANCE: in first variant, device has oxidizer tank, fuel tank, inter-tank section, march engine, middle adapter, lower adapter, device section and two engine plants for means for providing for launch. These engine plants for means for providing for launch are mounted on tank by fixed connection. This allows to decrease load moment on fuel tank cover and mass of tank and whole block is decreased as a result. In second variant, device has oxidizer block, fuel tank, inter-tank section, march engine, middle adapter, lower adapter, device section and one engine plant for means for providing for launch and nozzle block of this engine plant for means for providing for launch. Engine plant for means for providing for launch and nozzle block are connected by pipelines, as a result mass of block is decreased.

EFFECT: decreased mass of block.

2 cl, 2 dwg

Description

The invention relates to rocket and space technology, and in particular to the design of rocket booster blocks that are part of space rockets intended for launching from the reference orbit to the working energy orbits of various space objects-payloads.

Known rocket unit (block D) for the lunar space complex, containing a hull, main engine, fuel and oxidizer tanks, two propulsion systems of launch support equipment (Filin V.M. et al. “From the first satellite to“ Energy ”-“ Burana ” and “World”, RKK “Energy”, M., 1994, p. 69). The propulsion system of launch support facilities (DOS POPs), consisting of two autonomous units installed at a maximum distance from the center of mass of this unit, was designed to launch the lunar complex with a mass of at least 95 tons into the orbit of the satellite and deliver the lunar ship to the moon, while the DU POPs had a fuel reserve for launching a rocket block up to 7 times (see the RSC Energia publication, section “N1-L3 Rocket and Space Complex”, pp. 252, 254, 255).

Known rocket block according to patent RU 2165379, B64 G1 / 00.1 / 06.1 / 40, containing a payload interface farm, an oxidizer tank, a fuel tank, an inter-tank compartment, a marching engine, a launch vehicle interface farm and two POPs remote control .

The closest analogue is the rocket block according to patent RU 2153447, B 64 G 1/40, 1/00, 1/16, which is taken as a prototype.

This missile unit includes an oxidizer tank, a fuel tank, an inter-tank compartment, a mid-flight engine, a middle adapter, a lower adapter, an instrument compartment and two POPs remote control, borrowed from a previously developed missile unit for the lunar complex, which, using reset mechanisms, separate them from block after the last run.

The missile unit was designed to remove payloads on GSOs weighing up to 4,500 kg and launching the unit up to 2 times, which is significantly less than the mass of the lunar complex and the number of unit launches, while the triggering of the reset mechanisms of the remote control system of POPs was blocked (see the RSC Energia , section “Multipurpose unified missile blocks D and DM, engines and fuels for them” p. 252-255).

The disadvantage of the prototype is that the missile unit has an excess mass of the fuel tank, on the lower bottom of which the remote control POPs of excess weight are cantilevered, as well as the mechanisms for resetting the remote control of POPs are stored and blocked from being triggered.

The objective of the proposed rocket block in the first embodiment is to reduce the mass of the block by reducing the moment acting on the bottom of the fuel tank.

This task is achieved by the fact that in the first embodiment, in a rocket block containing an oxidizer tank, a fuel tank, an inter-tank compartment, a marching engine, a middle adapter, a lower adapter, an instrument compartment and two POPs remote control, two POPs fixedly mounted on the fuel tank are used.

The objective of the proposed missile block in the second embodiment is to reduce the mass of the block.

This task is achieved by the fact that in the second embodiment, in the missile unit containing the oxidizer tank, fuel tank, inter-tank compartment, the main engine, the middle adapter, the lower adapter, the instrument compartment and two POPs remote control, one POP remote control and nozzle block from the same engine are used installation, while the remote control system of the POPs and the nozzle block are connected by pipelines.

Figure 1 and 2 shows the design of rocket blocks, where:

1 - oxidizer tank;

2 - fuel tank;

3 - marching engine;

4 - inter-tank compartment;

5 - middle adapter;

6 - lower adapter;

7 - propulsion installation of launch support facilities (remote control system for POPs);

8 - nozzle block;

9 - instrument compartment;

10 - fixed mount;

11 - pipelines.

In the first embodiment, a rocket booster block is proposed, which contains an oxidizer tank 1, a fuel tank 2, an inter-tank compartment 4, a main engine 3, a middle adapter 5, a lower adapter 6, an instrument compartment 9, and two POPs 7 remote control systems, which can be made in a small-sized version. These remote control POPs 7 are installed on the tank 2 using a fixed mount 10, as a result of which the loading moment of the shell of the fuel tank 2 decreases and, accordingly, the mass of the tank and the unit as a whole decreases.

In the second embodiment, a rocket booster block is proposed, comprising an oxidizer tank 1, a fuel tank 2, an inter-tank compartment 4, a marching engine 3, a middle adapter 5, a lower adapter 6, an instrument compartment 9 and one remote control pop-up unit 7 and a nozzle block 8 from the same remote control pop-up unit 7, while the remote control unit POPs 7 and the nozzle block 8 are interconnected by pipelines 11, as a result of which the mass of the upper stage is reduced.

In the first embodiment, the proposed rocket booster block operates as follows.

After the launch vehicle is complete, the booster unit is separated at the junction of the middle adapter 5 and the lower adapter 6. Immediately after the unit is separated from the carrier, the middle adapter 5 is reset, after which the main engine 3 is started. In most cases, the support is formed as a result of the first start beaten off, then a software turn is made to the position necessary for the second start of the mid-flight engine 3, as a result of which the block with the payload is displayed in the target orbit.

Remote control pop-ups 7, after separating the block from the launch vehicle, provide longitudinal overload to the block to start the mid-flight engine 3. After the block enters the reference orbit by remote control pop-ups 7, a software turn is made to the position necessary for the second turn-on of the mid-flight engine 3, after which the remote control pop-up 7 provides maintaining the orientation of the block. After completing the flight program, the remote control of the POPs 7 provides the unit to turn to the withdrawal position and the block is transferred to the storage orbit where fuel is produced from the remote control of the POPs 7.

Remote control POPs 7, located on the bottom of the fuel tank 2, load the tank with its mass during transportation and flight of the unit.

The possibility of using two remote control POPs 7 of smaller mass and dimensions, which are refueled with a smaller mass of fuel necessary for the execution of the flight program of the unit, makes it possible to reduce the loading of the fuel tank 2, install the remote control of POPs 7 on the fuel tank 2 using a fixed mount 10 that does not allow for the reset of the remote control POPs 7, and, at lower mass costs for the accelerating unit ~ 1.5%, to ensure that the tasks of launching the mid-flight engine 3, orientation of the unit and its transfer to storage orbit are fulfilled.

In addition, the use of remote control POPs 7 of lower mass and dimensions can significantly improve the performance of the upper stage by increasing the shelf life of the unit with refueling remote control POPs.

In the second embodiment, the proposed rocket booster block operates as follows.

After the launch vehicle is completed, the booster unit is separated at the junction of the middle adapter 5 and the lower adapter 6. Immediately after the unit is separated from the carrier, the middle adapter 5 is reset, after which the main engine 3 is started. In most cases, as a result of the first start, the support beaten off, then a software turn is made to the position necessary for the second start of the mid-flight engine 3, as a result of which the block with the payload is displayed in the target orbit.

Remote control pop-ups 7 and nozzle block 8, interconnected by pipelines 11 through which fuel is supplied, after separating the block from the launch vehicle, provide longitudinal overload to the block to start the main engine 3, and with the help of remote control pop-ups 7 and nozzle block 8, after the block exits to the reference orbit, the program turns the block into the position necessary for the second turning on of the marching engine 3, after which the remote control pop-up 7 and the block of nozzles 8 ensure the orientation of the block. After the flight program is completed, the remote control unit POPs 7 and the nozzle block 8 provide the unit to turn to the withdrawal position and the unit is transferred to storage orbit where fuel is produced from the remote control unit POPs 7.

The use of one remote control unit for POPs 7 and a nozzle block 8, interconnected by pipelines 11, allows, at lower mass costs for the accelerating block ~ 1.5%, to ensure the fulfillment of the tasks of starting the main engine 3, orienting the block and moving it into orbit of storage.

Claims (2)

1. The rocket booster block containing the oxidizer tank, the fuel tank, the inter-tank compartment, the main engine, the middle adapter, the lower adapter, the instrument compartment and the propulsion systems of the launcher, characterized in that the propulsion systems of the launcher are mounted on the fuel tank using a fixed fastenings. 2. The rocket booster block containing the oxidizer tank, fuel tank, inter-tank compartment, main engine, middle adapter, lower adapter, instrument compartment, characterized in that on the lower bottom of the fuel tank there is one propulsion system for starting means and a nozzle block from the same propulsion system, which are interconnected by pipelines.

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