RU2318705C1 - Method of and device for mating launcher with missiles of different classes of multistage missile family - Google Patents

Abstract

FIELD: rocketry and space engineering.

SUBSTANCE: invention relates to ground equipment and operations carried out on such equipment. Proposed device contains switching supports engaging with rods of grips of holding mechanism. Said mechanism is installed on bracket in launcher where drive with telescopic link is also installed. Final member of link is made in form of articulated translator mechanism of parallel bars-connecting rods accommodating beams. Beams can be reciprocated by hydraulic cylinders. Grips are arranged on lower sides of beams and are provided with crank levers installed on said swinging supports. Said levers act through hydraulic cylinders onto rods of grips. Upper sides of beams are furnished with alignment devices with guide strips mechanically coupled with swinging supports. According to proposed method, prior to mating, components of articulated translator are set to suit layout of missile installed on launch mount. Axle of telescopic link is adjusted to distance and height required for missile of definite type. Then axes of bars-connecting rods and beams are aligned with axes of hinge supports of missile. Beams are extended to touch surfaces of hinge supports of missile by guide strips and missile is gripped and held.

EFFECT: provision of easy and reliability mating of launcher and missiles of different classes, operation of mechanisms at minimum efforts at sufficient strength and rigidity for holding the missile, enlarged operating capabilities, possibility of automation of mating process.

3 cl, 2 dwg

Description

The invention relates to rocket and space technology, and in particular to methods of docking a rocket with a launcher, its wind holding and tracking during launch, as well as devices for their implementation.

There is a method of docking and holding a rocket on a launcher with a launch tube, implemented by a device using a latch released by the energy of a gas stream (US patent 4132150, F41F 3/04, 01/02/1979).

A device is known for holding a rocket on a launcher by means of fixed supports in the form of spherical hemispheres interacting with convex hemispherical rods of an additional support of a launching structure (RU, patent 2101218 B64G 1/40, 03/14/1996).

However, none of them can be used for docking, holding and escorting missiles of various layout schemes (tandem, packet, combined).

The closest of the known technical solutions is the rocket retainer selected at the launcher as a prototype, comprising a hinged support mounted on the rocket that interacts with the rod of the containment mechanism mounted on the bracket of the ground structure. The method of docking the device consists in combining the axes and stringing the hinge support of the rocket onto the launcher bracket rod during the placement of the rocket on the launch pad, by manually turning the elements of the retention mechanism and moving the rocket. (RU, patent 2226170 7 В64G 5/00, 03/27/2004).

However, it is impossible to dock the launcher with space rockets with large dimensions and mass by the considered method and device; it does not provide for automation or remote control, use for a family of multi-stage rockets made according to various layout schemes, optimization of the parameters of the disturbing effect upon rocket descent with guides.

The required technical result is achieved by the fact that, before docking the launcher with missiles of various classes of the multi-stage missile family, that after installing the launcher bracket in the working position and docking it with the rocket’s hinged supports with the retention mechanism, the arrangement of the articulated translator elements is given a configuration corresponding to the layout installed on the launch pad missiles, while combining the axis of the telescopic rod of the retention mechanism by means of a drive mounted on the bracket, reflecting their marks on the rocket and laser roulettes on the telescopic drive rod with the axis of the rocket and place its end at the distance and height necessary for each type of rocket;

- combine by means of reflective marks mounted on the surfaces of the hinged supports facing the launcher, laser roulettes mounted on the ends of the beam of the rod-connecting rods and the mechanism of the hinged translator axis of the rod-connecting rods and beams with the axes of the hinged rocket supports;

- extend the beams from the line-rods until the guiding strips touch the centering devices of the outer surfaces of the hinged supports;

- produce capture, hold the rocket on the inner surface of the articulated supports by the rods of the capture device and the removal of the guide bars of the centering devices.

The device for implementing the method includes articulated bearings mounted on the rocket, interacting with the rods of the gripper of the rocket holding mechanism on the launcher bracket, equipped with a telescopic rod drive, the final link of which is an integral part of the articulated translator mechanism for parallel connecting rods in which the beams with the possibility by means of hydraulic cylinders to make reciprocating movements, while the gripping devices are located on the lower sides of the beams and equipped with cranked levers mounted on swinging supports with the possibility of impact, by means of hydraulic cylinders on the rods of the gripping devices, and the upper sides of the beams are equipped with centering devices equipped with guide rails mounted on the support arms, kinematically connected by leashes with swinging supports of the gripping devices.

The authors of the invention are not aware of similar technical solutions, and therefore, according to the authors, the claimed combination of features meets the criteria of the invention "significant differences" and the criterion of "novelty."

The device implementing the proposed method is illustrated by drawings.

On figa, b and c depicts a top view of the unitary interacting with the rocket easy-a, medium-b and heavy-in class unitary capture hold and tracking, located on the bracket launcher.

In Fig.2 - view A in Fig.1.

A device for docking a launcher with missiles of various classes consists of a drive 2 mounted on an arm 1 of a launcher 2 with a telescopic rod (Fig. 1), on the final link of which there is a hinged translator mechanism for parallel rulers-rods 3, which is configured to make circular translational the movements of the rods-rods, through the hydraulic cylinders 4, interacting with the lever-rocker arms 5 of the translator.

Rulers-rods 3 are made of box-shaped rectangular closed profile and are guides for beams 6 with devices for centering, gripping, holding and tracking the rocket 7 and are connected with them by hydraulic cylinders 8.

Missile capture-hold and tracking devices consist of hydraulic cylinders 9, cranked levers 10 suspended on oscillating bearings 11 and rods 12 interacting with articulated rocket supports 13.

The centering device consists of guide rails 14 mounted on the swinging supports-rocker arms 15, which are kinematically connected by a leash 16 with the swinging supports of the gripping-holding and tracking devices.

The hydraulic system of the drives includes hydrogas accumulators, the control system includes laser roulettes, photodiodes and reflective marks.

We will consider the implementation of the proposed method and device using the example of docking a launcher with a rocket installed on the launch pad.

After centering the rocket 7 by the installer from the cable-filling tower, the rocket wind holding bracket 1 with the telescopic rod 2 mounted on it is advanced, the end link of which is an integral part of the articulated translator mechanism, equipped with rocket centering, hold-hold and tracking devices.

Previously, depending on what class the rocket is installed on the launch pad, the location of the connecting rods 3 by means of circular translational movements under the action of hydraulic cylinders 4 and the beams installed in them with centering, hold-hold and tracking devices, by means of reciprocating movements hydraulic cylinder 8, one of the configurations shown in FIG. one.

Then, the drive 2, using the controls manually, remotely or automatically by software, using the reflective marks on the rocket 7, sets the longitudinal axis Y of the telescopic rod in the center of the rocket 7 at the necessary distance relative to the hinge supports of the rocket 13 along the X and Y axes.

Further, by means of hydraulic cylinders 4, rocker arms 5, laser roulettes and photodiodes mounted on the ends of the beams facing the rocket 7 with centering, gripping, holding and tracking devices, as well as reflective marks on the rocket hinged supports 13, the axis of the guiding devices (rulers - connecting rods) 3 with beams 6 are installed coaxially with the axes of the ball bearings of the rocket 13 at the required distance from them, while the pistons of the hydraulic cylinders 4 are fixed with hydraulic locks.

After that, the hydraulic cylinders of the guiding devices 8 push the beams onto the hinge supports of the rocket 13 until the guiding bars 14 touch their outer surfaces, while the X and Y axes of the ball bearings and rods are combined.

The efforts of pressing the guides 14 on the articulated bearings 13 are regulated by a hydraulic safety valve, then the pistons of the hydraulic cylinders 8 are locked with hydraulic locks and the supply of working fluid to the hydraulic cylinders 9 of the gripper-hold and rocket tracking devices 7 is turned on. The hydraulic cylinder rods 9 rotate the crank arms 10 mounted on the swinging supports 11 and push the rods 12 into the inner cavity of the hinge supports 13 of the rocket 7, connecting the bracket 1 of the cable-filling tower with the rocket 7.

At the same time, the swinging supports 11 of the cranked levers 10 connected by leads 16 to the support arms 15 of the guide rails 14 divert the guide bars 14 from the outer surfaces of the hinge supports 13 of the rocket 7, eliminating the possibility of pinching the rods 12 in the hinge supports 13 during start-up.

In this position, the capture device, together with the bracket 1 on which it is installed, performs the function of holding the rocket 7 on the launch pad with the rigidity set by the developers within the range of permissible loads that occur during refueling and wind exposure. To do this, the hydraulic system of the capture device and bracket 1 includes hydrogas accumulators with characteristics that provide the specified parameters, which makes it possible to obtain the minimum values of disturbing effects on the programmed trajectory of its movement when the rocket leaves the guides, after undocking all onboard connectors.

The simplicity of the method of docking the launcher with missiles of various classes and the device for its implementation, the reliability of the kinematics of the mechanisms, the capture of the articulated bearings of the missiles with minimal interaction forces, sufficient to maintain strength and stiffness, providing specified deviation parameters when accompanied, versatility of use, the ability to automate the docking process allows you to use the proposed method and device in promising launchers.

Claims (2)

1. The method of docking the launcher with missiles of various classes of the multi-stage missile family, which consists in the fact that after installing the launcher bracket in the working position, it is docked with the rocket articulated supports by the retention mechanism, characterized in that the retention mechanism is provided with a telescopic rod located on the bracket with a drive, the final link of which is made in the form of a mechanism of a hinged translator of parallel ruler-rods, in which are placed with the possibility of reciprocating progressive movement of the beam, on the lower sides of which the gripping devices are located, and the upper sides of the beams are equipped with centering devices with guide rails, and before joining, the elements of this hinged translator are given a configuration corresponding to the layout of the rocket mounted on the launch pad, while the axis of the telescopic rod is aligned using the specified drive , reflective marks on the rocket and laser roulettes on a telescopic rod with the axis of the rocket and place the end of the rod on the required the distance and height that are acceptable for each type of rocket, after which the axes of the connecting rod and beam axes are combined with the axes of the rocket’s hinge supports and the connecting rod rod beams are extended until the guiding strips touch the centering devices of the outer surfaces of the indicated hinge supports and they grab and hold the inner surfaces of the hinged supports the rods of the gripping devices, with the simultaneous retraction of the guide bars of the centering devices. 2. A device for docking a launcher with missiles of various classes of a multi-stage missile family, comprising swinging supports fixed to the rocket, interacting with the rods of the capture devices of the retention mechanism mounted on the bracket of the launcher, characterized in that it is equipped with a telescopic rod-mounted drive on the bracket, the final link of which is made in the form of a hinged translator mechanism of parallel ruler-rods, in which beams are placed with the possibility of reciprocating the movement by means of hydraulic cylinders, while the gripping devices are located on the lower sides of these beams and are equipped with cranked levers mounted on these swinging supports with the possibility of impact through the specified hydraulic cylinders on the rods of the gripping devices, and the upper sides of these beams are equipped with centering devices with guide rails, mounted on rocker supports kinematically connected by leashes with said swinging supports.

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