RU2649115C2 - Launcher - Google Patents

Abstract

FIELD: weapon.

SUBSTANCE: launcher includes a collar, with bases, with supporting trusses hinged to them with stops, counterweights and sectors, wherein the sectors are provided with thrust elements and four bearing arrows with four hinged to the bases, interacting with the support elements of the rocket and hinged to the sectors of the supporting trusses, as well as hydraulic actuators interacting with supporting trusses and hingedly mounted on the inner surface of the collar by guiding devices with grippers and lower cable masts. Launcher is equipped with hydraulic jacks - brakes, that allow, depending on the type of launch vehicle, to displace and fix the guiding devices to the corners α≤18°30' and on β up to 40° and more between the vertical axis of the launcher and the working combined positions. Guiding devices have adapters with grippers, stop blockers, sockets for fixing the lower cable masts for various configurations of the launcher.

EFFECT: launcher has the ability to transform and provide launches of launch vehicles of light, medium and heavy classes.

1 cl, 4 dwg

Description

The invention relates to ground launch facilities of launch vehicles installed in a vertical position at launch. The proposed installation contains a support ring on which four bases are mounted with support trusses pivotally mounted on them. Farms have stops, balances and sectors, and the sectors are equipped with persistent elements. Supporting booms with heads inserted into reciprocal support elements of the launch vehicle are pivotally mounted on the bases. Four guiding devices, having grips for connection with the lower part of the launch vehicle (PH), are pivotally mounted on the support ring. Hydraulic actuators interacting with supporting trusses and guiding devices and other auxiliary devices are provided. In this case, the launcher provides launches of launch vehicles with different locations of attachment points in the vertical and horizontal planes, i.e. the launcher has the ability to transform under each class of launcher (heavy, medium, light) and has three configurations.

Configuration A. The launcher in configuration A provides operation with a heavy class LV, for this purpose the guiding devices 9 of FIG. 1 are connected by hydraulic jacks-brakes 8 at an angle α ~ 18 ° 30 'and the grips of the guiding devices are connected to the brackets of the PH side blocks (photo of Fig. 4).

Configuration B. The launcher in configuration B provides operation with a medium-class LV. For a medium-class launch vehicle, the attachment points on the side blocks are closer to the launch vehicle axis than for a heavy-duty vehicle. Therefore, to ensure the interaction of the grippers of the guiding devices with the brackets of the side blocks of the PH, adapters are installed between the grippers and the guiding devices.

Configuration B. The launcher in configuration B enables operation with a light class LV. The light class launch vehicle does not have side blocks, and the attachment points are located on the “central unit” and differ significantly from the mount points of the launch vehicle with side blocks, in the vertical and horizontal planes. Therefore, the guiding devices 9 of FIG. 1, equipped with adapters 10, are supplied by hydraulic jacks-brakes 8 at an angle β ~ 40 °. In this case, the launcher has the following features:

- The guiding devices are equipped with limiters 12, eliminating damage to the design of the LV light class.

- The lower cable masts are locked in position using the sockets pos. eleven.

- The springs in the hydraulic jacks-brakes are installed in the position for working with LV of a light class and provide the removal of the rods of the hydraulic jacks-brakes to the pre-shock position before starting the LV

The invention is aimed at simplifying the means for implementing the operational functions of the installation, at increasing its reliability and reducing cost, and ensuring launches of LV of all classes.

The invention relates to devices for installing and securing a launch vehicle (LV) in a vertical position on a launch pad or platform and their launch.

Known launchers containing a launcher with mounted on it folding support-gripping devices, which are supported and held by the launcher on the launcher, for specially designed elements of the launcher located in its lower part. Launch of the launch vehicle is carried out from these supporting-gripping devices after starting the main propulsion systems (ODE) and the opening of the grippers holding the launch vehicle on the launch pad [1, p. 309, 311, 383 and 384].

The advantages of these devices include the following:

1. Relatively small overall dimensions.

2. The ability to keep the launch vehicle on the launch pad until a complete set of traction ODE, which increases the reliability of launch of the launch vehicle.

However, these devices have significant disadvantages, which include the following:

1. The complexity and high cost of support and gripping devices.

2. Increased requirements for the synchronization of the opening of the grippers of the support-gripping devices and the reliability of their operation after the ODE reaches the specified traction mode.

3. The need to withdraw support-gripping devices from the zone of their possible collision with LV or ODE elements, which are always located below the LV power support elements and are in close proximity to them, which significantly increases the requirements for the speed of their removal.

4. The need to protect the support-gripping devices and mechanisms that control them from the gas-dynamic effects of the ODE.

5. The need for reliable operation of the protective devices after the removal of the support-gripping devices in time, eliminating the possibility of their collision with the elements of the launch vehicle.

A launcher is known that contains a launcher with rigid supports fixed to it with wind grips, on which the LV is held in place by the wind grips, and after refueling with fuel components, the stability of the LV, when exposed to wind, is provided by the recovery moment from the weight of the LV. In this case, the wind captures are opened and diverted to places protected from the gas-dynamic effects of the ODE before the launch of the ODE [1, p.309, 311, 383 and 384].

The advantages of this launcher include the following.

1. Reliable and controlled before the launch of the ODE, the opening of the wind grips holding the LV on the launch pad.

2. Reliable protection of wind captures and their mechanisms from the gas-dynamic effects of ODE.

However, these devices have significant disadvantages, which include the following:

1. The need to increase the stiffness, and therefore the weight of the power support ring of the LV due to errors when installing the LV on the rigid supports or a significant complication of the design of the rigid supports, which should provide the necessary flexibility of the rigid supports when installing the LV on them.

2. The possibility of shock impacts of the launch vehicle against rigid supports at the time of equalizing the total thrust of the ODE with the mass of the launch vehicle.

Further analysis of patents and technical literature [1, 2, 3, 4] showed that the device closest in technical essence and achieved effect is [1, p. 309, 311, 383 and 384], containing a support ring on which there are four bases, with support trusses pivotally mounted on them with stops, counterweights and sectors equipped with stop elements, four pivotally mounted on the base of the supporting boom with heads interacting with the support LV elements and pivotally connected to sectors of the supporting trusses, as well as hydraulic actuators interacting with the stops of the supporting trusses, and four guiding devices pivotally mounted on the supporting ring and interacting with the tail part ew pH.

This device is selected as a prototype.

The advantages of this device include the following:

1. The possibility of suspension of the LV for the average power belt, which is due to the batch design of the LV.

2. Removal of support elements from under the end of the launch vehicle, which allows to increase the time for their removal to a safe distance from the zone of possible collision with elements of the starting launch vehicle and from the zone of intense gas-dynamic effect of the ODE jets on the heads of the bearing arrows.

3. The absence of locking and retaining launch vehicles on the launch pad elements at the launch of the launch vehicle.

4. Retraction of the supporting elements of the launcher to a safe distance from the launch vehicle under the influence of absolutely reliable and constantly acting gravitational forces.

The disadvantage of the prototype is the lack of the ability to launch LV light and heavy classes.

The objective of the invention is to simplify the device, increase its reliability and reduce its cost, ensuring launches of LV heavy, medium and light classes.

The stated technical problem is solved in that the device containing the support ring, on which there are four bases, with support trusses pivotally mounted on them with stops, counterweights and sectors equipped with stop elements, and four support arms with heads that are pivotally mounted on the bases, interacting with supporting elements of the launch vehicle and articulated to sectors of the supporting trusses, as well as hydraulic actuators and four guiding devices interacting with the tail of the launch vehicle of Tell, provided with a brake-hydraulic jacks allowing to move the guide device to the angle α≤18 ° 30 'and at an angle β to 40 ° or more (depending on the type of ROP), with retraction rod in position pretonic .; guiding devices with adapters installed on them with grippers connected to the lower part of the launch vehicle, equipped with travel limiters and sockets for attaching lower cable masts with various launcher configurations.

Similar technical solutions of the present invention to the author are not known, and therefore the claimed combination of features meets the criteria of the invention "significant differences".

The invention is illustrated by drawings, where in FIG. 1 is a general view of the proposed launch device designed by the author for the Vostochny spaceport; in FIG. 2 shows an embodiment of a launching device with adapters 11 in the form of welded trusses (designed by the author for the Plesetsk cosmodrome), which are installed on guiding devices when operating with a LV without side blocks; in FIG. 3 is a photograph of an embodiment of a starting device; in FIG. 4 is a photograph of a PH lateral block with a gripping guide device attached to its bracket.

In FIG. 1 shows LVs without side blocks and LVs with side blocks and two positions of the guiding devices 9 for them. The launcher comprises a support ring 7 and four bases 6 fixed thereon, on which support trusses 2 with weights 4 and sectors 1 are pivotally fixed, at the edges of which the stop elements are fixed. In addition, on the bases 6, support arrows 3 are pivotally fixed with heads that are pivotally connected to sectors 1 of the support trusses 2. When the sectors of support trusses are closed, the thrust elements of adjacent sectors of the support trusses abut against each other and form the upper power support ring, on the heads of the bearing arms which is mounted and on which the LV is held, while the guiding devices 9, interacting with the tail of the LV, form the lower power belt holding it in a vertical position. With the guiding devices, the lower cable masts 14 of FIG. 2, serving to bring the communications to the board. The hydraulic actuator cylinders, the rods of which interact with the stops of the supporting trusses, are fixed in the bases 6 of FIG. 1 and are intended for the drive of supporting trusses 2 both in the working (reduced) and initial (divorced) positions. Hydraulic jacks-brakes 8, the rods of which interact with the stops of the guiding devices 9, are fixed in the support ring 7 and are designed to drive the guiding devices 9 both in the working (reduced) and initial (divorced) positions. In this case, before starting the launch vehicle, the rods of the hydraulic actuator power cylinders are in the initial (retracted) position from the stops. After transferring the weight of the LV to the heads of the carrier arms 3 and the connection of the guiding devices 9 with the tail of the LV, it is held on the starting device, after which the rods of the hydraulic actuator power cylinders are retracted, which makes it possible to retract the supporting trusses 2 with the carrier arms 3 under the action of loads 4 , retracting the guiding devices 9 and retracting the lower cable masts 14 of FIG. 2 by gravity. At start-up, after the start of the launch of the launch vehicle, the ends of the supporting arrows 3 of FIG. 1 under the influence of loads 4 disengage from the LV, and the supporting trusses 2 with supporting arrows 3, the guiding devices 9 and the lower cable masts are withdrawn from the zone of their possible collision with the rising LV at a safe distance.

Thus, from the above justifications of the essential features of the claimed invention it follows that the proposed combination of features set forth in the claims, allows to obtain a significant positive effect, namely: to ensure launches of LV light, medium and heavy classes. This invention can be used both in the retrofitting of existing launch complexes, and to create new ones.

SOURCES OF PATENT AND TECHNICAL INFORMATION

1. COSMONAUTICS: Encyclopedia. - M.: Soviet Encyclopedia, 1985, p. 309, 311, 383, 384.

2. Volsky A.P. Cosmodrome. - M .: Military Publishing House, 1977.

3. N.M. Korneev, V.N. Neustroev. General Designer Academician Vladimir Pavlovich Barmin. The main stages of life and activity. Moscow, 1999, with. 82, 84, 85, 103, 104, 105.

4. On the earth and in space. FSUE KBOM them. Barmina, Moscow, 2001, p. 82, 84, 94.

Claims (2)

1. A launcher containing a support ring, with bases, with support trusses pivotally mounted on them with stops, counterweights and sectors, the sectors being provided with stop elements, and four support arms with heads articulated to the rockets and interacting with the support elements of the rocket and pivotally associated with sectors of the supporting trusses, as well as hydraulic actuators interacting with the supporting trusses and guiding devices with grips pivotally mounted on the inner surface of the supporting ring and lower cable masts, characterized in that it is equipped with hydraulic jacks - brakes, which, depending on the type of launch vehicle, can move and fix guiding devices at angles α≤18 ° 30 'and β up to 40 ° or more between the vertical axis of the launcher and reduced working positions, and the guiding devices have adapters with grips, travel stops, sockets for fixing the lower cable masts with various configurations of the launcher. 2. The launcher according to claim 1, characterized in that it is equipped with hydraulic jacks - brakes, which allow to move transformable guiding devices with grips, buffers to absorb shock loads and braking guiding devices when they are removed from the launch vehicle during start up.

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