RU2324130C1 - Air missile launch system - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: system comprises aircraft with elevation-alignment mechanisms for missiles and a ramp. The ramp hosts launch platform, which is connected to aircraft control console via cables, and guides used to move launch platform. The aircraft is done as an encasement, filled with light gas, and connected to the ramp with absorbing stands. The launch platform is connected to the ramp using withdrawable absorbing devices. Each elevation-alignment mechanism is equipped with power plant for missile launching. The system is also equipped with a guide, which is fastened to the ramp. The guide is equipped with inner fan-outs, to ends of which lockout devices are fastened.

EFFECT: missile launching from any point; full payloading of the aircraft.

2 cl, 5 dwg

Description

The proposed invention relates to rocket technology and can be used to launch rockets from the air.

A known complex chosen as the closest analogue for launching missiles from the water area, comprising an aircraft with lifting and mounting devices for missiles and a platform on which a detachable launch platform is fixed, connected to the vessel with cables and cable lines for launch control of the missile, guides for moving placed on the vessel launch platform outside the vessel and vice versa (RF patent No. 2151995, class IPC F41F 3/04, publ. 06/27/2000. Bull. No. 18).

The disadvantage of this device is the inability to launch missiles from the most advantageous point and insufficient loading of the aircraft.

The technical task of the proposed invention is the implementation of the launch of missiles from anywhere and the full loading of the aircraft with a payload.

The task is achieved in that in a complex for launching missiles from the air, containing an aircraft with lifting and mounting devices for missiles and a platform on which a detachable launch platform is located, connected to the aircraft control panel with cable lines for launching missiles, placed on the aircraft guides for moving the launch platform, the aircraft is made in the form of a shell filled with volatile gas and connected to the platform with shock absorbing struts, while retractable shock absorbing devices connecting the launch platform to the platform and the power plant for launching the rocket located in each lifting and installing device are used, while the lifting and mounting devices are connected to the control panel for the cable launch line control of the rocket, and a closed guide fixed to the platform is introduced a circuit having internal branches located on the guide movable drives with flexible cables, at the ends of which grippers are attached.

The proposed invention is illustrated using the schemes shown in figures 1, 2, 3, 4, 5.

Figure 1 shows the complex for launching rockets from the air in preparation for the launch of the rocket, figure 2 shows the complex for launching rockets from the air before the launch of the rocket, figure 3 shows the complex for launching rockets from the air at the time of the launch of the rocket, .4 shows an embodiment of the guide; FIG. 5 shows a drive with a gripper on the guide.

In figure 1, 2, 3, 4, 5, the following notation:

- aircraft 1,

- a shell 2 filled with volatile gas,

- platform 3,

- launch platform 4,

- guides 5,

- shock absorber struts 6,

- sliding shock absorbing devices 7,

- lifting installation device 8,

- rocket 9,

- remote control 10,

- cable lines 11 control the launch of the rocket 9,

- rocket 12,

- a device for capturing 13 on a rocket 12,

- gripping device 14,

- flexible cable 15,

- drive 16,

- guide 17.

Complex for launching missiles from the air works as follows. At a given starting altitude (starting altitude for various types of missiles and their launch purposes can range from 50 to 15,000 meters, if necessary, it can exceed 15,000 meters), an aircraft 1 is arranged in the form of a shell 2 filled with volatile gas, for example , like the shell of a balloon or stratospheric balloon, tie the air harbor 1 to a certain point due to the operation of internal combustion engines. A pad 3 is fastened to the shell 2 filled with volatile gas by means of shock absorbing racks 6. On the pad 3, rails 5 are fixed, on which the launch platform 4 is located, which can be moved along the rails 5 using the drive (not shown in the diagrams) of the launch platform 4. Along the perimeter of the site 3, a closed loop guide 17 is rigidly fixed from the ground (rail, tee and other profiles can be used as guide 17), on which movable drives 16 with flexible cables 15 and grippers properties 14. In addition, the guide 17 can be branched inside a closed loop (figure 4), the branching is carried out using arrows. Branching is performed for a more compact placement of missiles 12. A gripping device 14 is made, for example, in the form of a hook, and a device for gripping 13, for example, in the form of a bracket, is made on the rocket 12. On the launch platform 4, a lifting and mounting device 8 is provided with a rotary device and a power unit (not shown in the diagrams) for launching the rocket 9. In addition, the lifting and mounting device 8 is connected to the cable line control panel 10 of the rocket launch control 9.

Before launching, the rocket 9 is lifted from the ground onto the aircraft 1 by any known method, for example, using a winch, and it is placed horizontally in the lifting and installation device 8 on the launch platform 4. Before starting the rocket 9 from the control panel 10 through cable lines 11 of the rocket launch control 9 give a command to the drive of the launch platform 4 to the output of the lifting and installation device 8 outside the shell 2. Then, from the control panel 10 through the cable lines 11 of the launch control of the rocket 9, a command is given to the rotary lifting device multi-installation device 8 to bring the rocket 9 into a vertical position, and the drives of sliding shock absorbing devices 7 to their extension. After that, the rocket 9 takes up a vertical position, and the sliding shock absorbing devices 7 are advanced so that the wheels of the launch platform 4 rise above the guides 5. From the control panel 10, through the cable lines 11 of the launch control of the rocket 9, they command the power plant of the lifting and installation device 8 to launch the rocket 9. After the start, with the help of the power plant of the lifting installation device 8, the rocket 9 receives the initial speed and turns on its own engines.

At the time of the launch of the rocket 9, under the influence of the emerging pulse, the launch platform 4 moves towards the platform 3, compressing the sliding shock absorbing devices 7, which, in turn, exert pressure on the platform 3. Under the influence of the pressure transmitted by the launch platform 4, the platform 3 moves down by stretching the struts 6. The shock-absorbing struts 6 and the shock-absorbing devices 7 can be made as telescopic hydraulic or pneumatic shock absorbers. Part of the pressure arising at the start is quenched by compressing the shock absorbing devices 7, and part due to the stretching of the struts 6. Thus, the effect of the pulse at the start of the rocket 9 on the balance of the shell 2 filled with volatile gas is minimized.

Before launching the rocket 12, the gripping device 14 is connected to the gripping device 13 on the rocket 12. Then, the flexible cable 15 is selected using the actuator 16, thereby lifting the rocket 12 up. After the rocket 12 is raised to a predetermined starting height, stop selecting the flexible cable 15 and turn on the engine of the rocket 12, accelerating it. The inclusion of the engines of the rocket 12 can be carried out over the air from the remote control 10 or by any other known method. Simultaneously with the acceleration of the rocket 12, the flexible cable 15 is released from the drive 16. In this case, the drive 16 can move along the guide 17 (both due to its own engine, and due to the tension force of the flexible cable 15) so that the flexible cable 15 will not slow down when tensioned acceleration of the rocket 12. In addition, due to its own engine, the drive 16, moving along the guide 17, can accelerate the rocket 12. After the rocket 12 will move at a safe flight speed, the capture device 14 is undocked from the capture device 13 on the rocket 12.

Thus, due to the fact that in the complex for launching missiles from the air, the aircraft is made in the form of a shell filled with volatile gas and is connected to the platform by shock absorbing racks, as well as by introducing retractable shock absorbing devices connecting the launch platform to the platform and placement missiles on a rail connected to the platform from the ground, expand the functionality of the complex, i.e. it becomes possible to launch missiles from anywhere and the aircraft is fully loaded with payload.

Claims (2)

1. A complex for launching missiles in the air, comprising an aircraft with lifting and mounting devices for missiles and a platform on which a detachable launch platform is located, connected to the aircraft control panel with cable lines for launching the rocket, and guides for moving the launch platform, characterized in that the aircraft is made in the form of a shell filled with light gas and connected to the platform by shock absorbing struts, the launch platform is connected to the platform by sliding shock absorbing they have devices and in each lifting and installing device there is a power plant for launching a rocket, and lifting and mounting devices are connected to a control panel for cable lines for launching a rocket. 2. The complex for launching missiles in the air according to claim 1, characterized in that it is equipped with a closed-loop guide fixed to the site, having internal branches located on the guide, movable drives with flexible cables, at the ends of which gripping devices are attached.

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