RU2401408C1 - Aircraft rocket launcher for launching of spaceworthy ballistic missiles - Google Patents

Abstract

FIELD: defense technology.

SUBSTANCE: aircraft rocket launcher for launching of ballistic missiles comprises missile launching canister (MLC) with bottom and open end oriented towards aircraft tail, installed on cargo deck of carrier aircraft. For rocket ejection from missile launching canister, there is a power device installed on its bottom. Missile direction in process of motion is done by support-drive belts fixed on its body. MLC canister is equipped with two cradle supports with side horizontal platforms. Each of platforms is hingedly connected to two pairs of carriages installed on rail guides fixed on cargo deck of carrier aircraft. Some rail guides are arranged as light-weight and detachable. Guides under carriages are fixed permanently on cargo deck of carrier aircraft and have power side walls, where devices of carriages fixation are mounted in longitudinal and transverse directions.

EFFECT: reduced effect of cargo deck deformations at missile and level of body loading in process of landing operation.

3 cl, 5 dwg

Description

The invention relates to aerospace engineering and can be used to land ballistic missiles from an aircraft primarily for space purposes.

A device is known according to US patent No. 5279199, IPC F41F 3/06, B64D 1/04, published January 18, 1994, by the Hughes Aircraft Company for launching (pushing) a rocket against the direction of flight of an aircraft, containing a launch tube in which the rocket is installed, and a rocket-pushing device in the form of an air bag with a device for boosting it.

The disadvantage of this design of the device is the significant transverse loads (reactions) acting on the rocket’s body when landing from the container (launch tube), when some of the support-leading belts installed on the rocket have already left the container, and on the remaining support-carrying belts in the container all inertial forces acting on the missile are concentrated when it is dropped from the container.

There is also known a device for landing heavy bulky cargo from an airplane (patent No. 2175932, B64D 1/04, F41F 3/06, B64G 1/00) with a priority of 02/07/2001, containing an airborne container with an open end, a device for pneumatically ejecting cargo from container through the open end, a source of high pressure. The airborne cargo is placed inside the container on mounting elements located, for example, in two belts of the airborne cargo. Moreover, one of the installation elements is made in the form of a calibrated support, while the maximum force settings and the permissible lateral movements of these supports are selected from the condition of maintaining a guaranteed gap between the landing container and the landing cargo when evacuating it from the container. To reduce the dynamic loading of the landing cargo, the calibrated supports are equipped with dampers, and the container is mounted on the cargo floor of the carrier aircraft in more than two sections along its length.

The disadvantages of this device are that the container structure, which has more than two mounting supports on the cargo floor of the carrier aircraft, is statically indeterminable, when the aircraft deforms in flight before landing, it deforms and loads the container and rocket with additional transverse loads (support reactions, shear forces and bending moments). At the same time, the load on the rocket and container due to deformations of the cargo floor of the carrier aircraft is 2–3 times greater than that due to flight inertial overloads. The disadvantages of the above device can also be attributed to the lack of sealing of the internal cavity of the container from the external environment, which reduces the reliability of the health of the landing cargo (spacecraft) and its service life.

Despite these shortcomings, the device according to patent No. 2175932 can be adopted as a prototype, as the closest in technical essence.

The problem to which the invention is directed, is to eliminate the above drawbacks and create an aircraft launcher, which reduces the influence of deformations of the cargo floor of the carrier aircraft on the rocket in flight and during landing, reduces the level of loading of the rocket body during landing when it leaves the transport launch container (TPK) supporting-leading belts, as well as sealing the internal cavity of the TPK.

The solution of the technical problem, according to the attached invention, is achieved by the fact that the TPK is equipped with two lodgement supports with lateral horizontal platforms, each of which is pivotally connected to two pairs of carriages mounted on rail guides mounted on the cargo floor of the carrier aircraft and designed to move the TPK with a rocket during its loading (unloading) into the cargo compartment of the carrier aircraft, while to reduce the mass of the launcher, some of the rail guides are made lightweight removable, which dismantled after loading rockets into the cargo compartment of the aircraft carrier. In this case, the guides under the carriages are fixed stationary on the cargo floor of the carrier aircraft and have side walls on which devices for fixing the carriages in the longitudinal and transverse directions are mounted. The fastening of the TPK in two sections along its length makes this design statically determinable, and thus, the deformation and loading of the TPK and missiles become independent of the deformations of the aircraft, and the maximum load values in flight cases of loading are reduced by 2–3 times. However, in order to obtain the required value for reducing the load on the rocket and TPK, TPK supports must be placed in sections that are optimal along the length of the TPK, and at the same time, a console 30–40% of its total length is formed from the side of the TPK open end. When the missile is landing, due to the movement of the reactions of the rocket supports to the open end of the TPK, its cantilever part elastically deforms in the transverse direction, and when each of the rocket supports leaves the support surface of the TPK due to the elastic forces, the console makes a return movement, and the TPK elastic vibrations occur and rockets. These fluctuations worsen the conditions of the unstressed exit of the missile from the TPK and increase the load on the TPK and the rocket during landing.

To ensure the smallest level of loading of the hull and improve the conditions for ensuring the rocket’s shock-free appearance when landing, the TPK is equipped with two external lateral extendable supports located in the open end area of the TPK, which interact with the cargo floor of the carrier aircraft only at the time of launch, excluding lateral movements of the console of the TPK relative to the plane. To ensure the microclimate inside the TPK, a sealing membrane is installed on its open end, which is destroyed by the course of the rocket at launch.

The invention is illustrated by drawings, in which Fig. 1 shows a general view of an aircraft launcher, Fig. 2 shows a leader G with a lodgement support, Fig. 3 shows a top view along arrow A, Fig. 4 shows a section B-B along the lodgement supports with carriages, figure 5 shows a cross-section BB in retractable supports.

Aircraft aircraft launcher for launching ballistic missiles contains mounted on the cargo floor 1 of the carrier aircraft 2 TPK 3 with the bottom 4 and the front end 5, oriented in the tail of the aircraft. To eject rocket 6 from TPK 3, an energy device 7 is installed on its bottom 4, while the direction of movement of rocket 6 in TPK 3 is provided by supporting-leading belts 8, mounted on its body and interacting with the inner surface of TPK 3 during loading and landing. The retention of the rocket 6 in the TPK 3 from longitudinal movements is carried out by the holding device 9 (pyro bolts or explosive bolts). The disconnection of the electro-pneumatic hydraulic connections 10 TPK 3 from the rocket 6 is provided by the device for separating them 11. TPK 3 has two lodgement supports 12 with lateral horizontal platforms 13, each of which is pivotally connected to two pairs of carriages 14 mounted on rail rails 15 mounted on the cargo floor 1 carrier aircraft 2, while part of the rail rails 16 is made lightweight and removable, and the rails 15 under the carriages 14 are stationary mounted with ties 17 and have power side walls 18 on which are mounted fixing devices 19 of the carriages 14 in the longitudinal and transverse directions, while one of the lodgement supports 12 is not fixed in the longitudinal direction. TPK 3 is equipped with two lateral sliding supports 20 located in the open end 5 of TPK 3, and a sealing membrane 21 mounted on the open end 5 of TPK 3, which is destroyed by the rocket 6 during launch.

Aircraft launcher operates as follows. Before loading TPK 3 with rocket 6 into the cargo compartment of carrier aircraft 2, lightweight removable guides 16 are mounted on cargo floor 1. After that TPK 3 with rocket 6 is loaded, for example, through the front cargo hatch of carrier aircraft 2 using a loading device moving TPK 3 before placing the carriages 14 in the guides 15, 16 and fix it from longitudinal and lateral movements by devices 19 mounted on the power side walls 18 of the guides 15. Before refueling the rocket with 6 fuel components, the removable guides 16 are removed thereby reducing the flight weight of the launcher.

The launch of the rocket 6 is carried out according to the command supplied to the igniter of the launch of the energy device 7, for example a steam and gas generator (PGG). Under the action of the piston force generated by the gas pressure of the PGG 7, the holding device 9 of the rocket 6 in the TPK 3 is destroyed and the rocket 6 moves in the TPK 3 on the support-leading belts 8, mounted on the rocket 6. At the same time, a command is sent to the lateral sliding supports 20, which pushing all the way to the cargo floor 1 of the carrier aircraft 2, they create additional support, thereby ensuring the smallest loading during landing and the unstressed exit of rocket 6 from the TPK 3.

The undocking of the pneumatic links 10 and the destruction of the membrane 21 is carried out by the course of the rocket 6.

The proposed invention allows:

- reduce the effect of deformations of the cargo floor of the carrier aircraft on the rocket in flight and during landing by securing the TPK on the cargo floor of the aircraft in two sections, which makes the structure statically determinable and independent of the deformation of the aircraft;

- to reduce the level of loading of the rocket body during landing at the moment of the descent of the support-leading belts from the TPK due to the introduction of two external lateral retractable supports that are put forward during start-up to the stop in the cargo floor of the aircraft;

- provide sealing of the internal cavity of the TPK.

Claims (3)

1. Aircraft launcher for launching ballistic missiles for space purposes, including a transport and launch container mounted on the cargo floor of a carrier aircraft with a bottom and an open end oriented to the tail of the aircraft, an energy device for pushing a rocket out of a transport and launch container, support-leading belts, mounted on a rocket, a device for holding the rocket in the container, a device for separating the electro-pneumohydraulic connections of the container from the rocket, characterized in that the transport and launch the steiner is equipped with two lodgement supports with horizontal lateral platforms, each of which is pivotally connected to two pairs of carriages mounted on rail guides mounted on the cargo floor of the carrier aircraft, some of which are lightweight and removable, while under the carriages rail guides on the cargo floor of the aircraft -carriers are fixed stationary and have power side walls on which devices for fixing carriages in the longitudinal and transverse directions are mounted. 2. Aircraft launcher according to claim 1, characterized in that the transport and launch container is equipped with two lateral extendable supports located in the open end area of the container, which interact with the cargo floor of the carrier aircraft only at the time of launch. 3. Aircraft launcher according to claim 1, characterized in that it is equipped with a sealing membrane mounted on the open end of the transport and launch container and destroyed during missile launch.

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