RU2068379C1 - Method of launching rocket (versions) and transportation system for its realization - Google Patents

Abstract

FIELD: rocketry and space engineering. SUBSTANCE: several rockets are launched simultaneously with payloads into a single transportation system. Rockets may be accelerated on active leg of trajectory by single boost stage which is just stage of more powerful rocket. Engines of rockets may be first shut down and may be cut in only after separation of rockets from boost stage or may be cut in immediately when they are supplied from boost stage tank and after separation they are fed with their own propellant. After separation from boost stage, rockets continue flight over their own trajectory injecting payloads into different orbits. EFFECT: enhanced efficiency of transportation systems due to simultaneous injection of several payloads into different orbits and wide employment of rockets disarmed for conversion. 4 cl, 5 dwg

Description

 A known transport system and method of launching missiles (see US patent N 4724738, CL 64 G 1/40, 1988).

 The space transport system contains an accelerating first stage, accelerators of the second stage, rockets with payloads connected to the accelerating stage, and a payload under the cowl.

 After the first stage and the second stage accelerators are triggered, the payload is put into its orbit, and each rocket with the payload is put into its orbit along its own trajectory.

 The objective of the invention is to create an efficient transport system and method of its launch by ensuring the launch into different orbits of different payloads. In this case, it is possible to use ballistic missiles that are being withdrawn from service.

 The problem is solved in that in the method of launching rockets, based on their joint movement on the active section of the trajectory using a common accelerating block with the rocket engines turned off, separating the rockets from the common block and their further movement along their own paths, the rocket engines are turned on either immediately before the separation , or immediately after separation of the missiles from the general upper stage.

 The problem is also solved by the fact that in the method of launching rockets, based on their joint movement on the active section of the trajectory using a common booster block, separation of the rockets from the general booster block and their further movement along their own trajectories, the movement of the rockets on the active section of the trajectory is carried out with the engines turned on missiles for which fuel is supplied from the tanks of the upper stage, and after separation of the missiles from their own rocket tanks.

 The problem is also solved by the fact that the transport system, comprising an accelerating unit with its own tanks and engines, rockets with tanks and engines, solid fuel boosters, a control system and separation devices, is equipped with upper and lower discharge fairings, and the fuel tanks of the upper stage are connected by oxidizer supply lines and fuel through check valves and tear-off hydraulic connectors with rocket engines.

 The invention is illustrated by drawings, where figure 1 shows a General view of the transport system with the rocket engines off; in Fig.2 the same, with the rocket engines turned on, operating from the tank of the upper stage; figure 3 is the same; figure 4 is a hydraulic diagram of the transport system shown in figure 1; in FIG. 5 is a hydraulic diagram of the transport system shown in FIG. 2; in FIG. 6 is a hydraulic diagram of the transport system shown in FIG. 3; in FIG. 7 separation of missiles from the upper stage; on Fig - kinematic diagram of the mounting of the rocket to the upper stage; Fig.9 is the same; figure 10 is the same; in FIG. 11 is the same; 12 is the same; in FIG. 13 the same; on Fig scheme of the trajectories of missiles; Fig. 15 is the same.

 The transport system includes an acceleration unit 1, rockets 2, upper 3 and lower 4 fairings, payload 5. Rockets 2 contain payload 5, docked to their last stages through separation systems. Missiles 2 are connected to the booster block 1 by means of clamps 6 and dilution systems.

 The transport system can be performed in three versions of the "passive" (figure 1, 4 89), "joint" (figure 2, 5, 10 and 11) and "active" (figure 3, 6, 12 and 13). The “passive” option provides for the use of liquid-propellant and solid-propellant engines as boosters of block 1 and rockets 2. Two other options include the use of liquid engines.

 In the “passive” version, the rockets 2 are attached to the booster block 1 by means of clamps 6 and are supported by the bottom parts on the brackets 7 of the block 1. The booster block 1 contains hinged rods 8 and 9 with springs (elastic elements) 10 and 11, connected with the response stops of the rockets 2 , and represent a breeding system. To improve aerodynamics, the accelerating block 1 is equipped with fairings 3 and 4, which can be made sectional and associated pyro-mounts with block 1.

 The second (joint) version of the transport system involves the use of liquid rocket engines on rockets and the upper stage and hydraulic communication between them. The fuel and oxidizer lines of the rockets 4 contain normally closed pyromembranes 12 above the tanks and are connected to the similar lines of block 1 by means of tear-off hydraulic sockets 13 and check valves. The power circuit of this option also provides for the bracket 7, similar to the previous version, as well as the upper stops 14, pushing springs 15 (figure 10) and latches 6 included in the breeding system. Missiles 2 are provided with protrusions for stops 14.

 The third (active) option involves the use as a unit 1 of a fuel tank with fuel and oxidizer, connected by hydraulic lines (Fig. 6) to missiles 2, similarly to the second option, while missiles 2 also have liquid engines, and a power circuit (Fig. 12) contains articulated rods 8 and 9, similar to the first embodiment, back stops and latches 6, forming together the breeding system.

 The transport system contains a single control system, which can be located on the accelerating block 1 and is connected with the engines of the block 1 and missiles 2 by the clamps 6, pyro-mounts of the fairings 3, 4, pyromembranes 12.

 In the initial position, the transport system is assembled as a whole, the tanks of the upper stage 1 and the rockets 2 are filled with fuel, the rockets 2 are fixed with clamps 6 to the block 1 taking into account the alignment, the flight program is entered into the control system, the transport system is located on the launch device.

 When starting the transport system, they include jet engines of either acceleration unit 1 only (passive version), or only missiles 2 (active version), or both at the same time (joint version). The transport system rises up the active part of the trajectory.

 If the specified inclinations of the orbits of the payloads 5 are close, then in addition to the vertical component of the velocity vector, the transport system also gains a horizontal component, moving along the arc OA (Fig. 14) in azimuth within the angles of inclination of the orbits. If the payload 5 should be put into different orbits, then the transport system rises vertically (Fig. 15).

 In the OA section (Fig. 14), with the passive version, the engine of block 1 operates, and the engines of rockets 2 are turned off, with the joint and active versions, the engines of rockets 2 are turned on and consume fuel only from the tanks of block 1, preserving their fuel. After the fuel is consumed from the tanks of block 1, rockets 2 are separated (point A in Figs. 14, 15).

 The separation of missiles 2 is as follows. In the passive version, the engines of the rockets 2 are turned on, the latch 6 opens and the fairings 3, 4 are reset (Fig. 7). Due to the increased thrust of the rocket 2 begin to overtake the block 1 (Fig.9), and the rods 8, 9 are rotated in hinges under the action of the springs 10, 11 and push the rocket 2 to a safe distance.

 In the joint embodiment (FIG. 2), after the engine of the block 1 is turned off, the latch 6 also opens and the springs 15 push the rockets 2 away from the block 1, dropping them from the brackets 7 and the stops 14 (FIG. 11). The connectors 13 are opened, and the check valves ensure the integrity of the missile hydraulic lines 2.

 After separation from missile unit 1, rockets 2 continue to accelerate payloads 5 using their engines in the AB section (Figs. 14, 15), telling them a speed sufficient to put them into orbits with the required parameters.

 When using the invention it is possible to provide the allocation of several spacecraft simultaneously into orbits with different parameters; to use ballistic missiles removed from armament and, thereby, save money and resources spent both on the creation of launch vehicles and on the destruction of military missiles as part of the conversion. YYY13 YYY14

Claims (3)

 1. The method of launching rockets, based on their joint movement on the active section of the trajectory using a common booster block with the rocket engines turned off, separation of the rockets from the common block and their further movement along their own trajectories, characterized in that the rocket engines are turned on either directly in front of the compartment, or immediately after separation of the missiles from the general upper stage.  2. The method of launching rockets, based on their joint movement on the active section of the trajectory using a common booster block, separation of the rockets from the general booster block and their further movement along their own trajectories, characterized in that the movement of the rockets on the active section of the trajectory is carried out with the rocket engines turned on , the fuel for which is supplied from the tanks of the upper stage, and after the separation of the rockets from their own rocket tanks.  3. A transport system for launching missiles, comprising an accelerating unit with fuel tanks and engines, rockets with tanks and engines, solid fuel boosters, a control system and separation devices, characterized in that it is equipped with upper and lower discharge fairings, and the fuel tanks of the upper stage are connected oxidizer and fuel supply lines through check valves and tear-off hydraulic sockets with rocket engines.

Images