RU51969U1 - PROTECTIVE DEVICE FOR ORBITAL SPACE VEHICLE PLACED IN MARINE BASING MISSILE POSITION - Google Patents

Abstract

The utility model relates to rocket and space technology and can be used to protect orbital spacecraft (OKA) when launched by sea-launched combat missiles. The technical task of the utility model is to protect the complex configuration of the OKA, placed on the ground of warheads in a sea-based missile, from the following operational influences: gas-dynamic and fragmentation when separating missile stages, thermal and acoustic when operating engines of the third stage, a sharp pressure drop after separation of the second and third stages - in this case, the design of the protective device should not lead to the conversion of a military missile. The protective device for the OKA contains a casing, which is an enclosure open from the large and small ends, supported by frames, a plate for attaching the spacecraft, and a platform for attaching the casing with the plate to the rocket. The shell of the housing is made, for example, in the form of an elliptical stepped cone of composite material, for example, fiberglass. The casing frame along the small end is made of metal and, due to the sealing with a rubber ring, is hermetically sealed with a plug fixed by a threaded sleeve screwed into the frame by thread. The frame of the shell at the large end is formed by increasing its thickness in the required place. The shell of the housing from the outside is protected by a heat-shielding coating, for example, TTP-FS of a given thickness, which in addition to its main function reduces acoustic loads.

Description

The utility model relates to rocket and space technology and can be used to protect orbital spacecraft (OKA) when launched by sea-launched combat missiles.

As the devices protecting the OKA from external influences on the atmospheric portion of the trajectory in space rockets and on converted ground-based combat missiles, head fairings are known (see Japanese patents: No. 58-2120 published January 14, 1983, No. 59-26520 published June 28, 1984 No. 62-56840 published November 27, 1987). The main disadvantage that does not allow their use in sea-based missiles is the need to re-equip missiles, entailing a significant increase in their dimensions.

A protective device is known for accommodating an OKA (see patent RU 2072954 C1), comprising a head fairing made in the form of a shell closed from one end, an adapter for attaching an OKA, a mount to a rocket. In addition to protection on the atmospheric portion of the trajectory, the OKA is also protected from gas exchange during autonomous ground operation by sealing the cavity to accommodate the OKA, while the head fairing and the adapter are interconnected by means of a mount to the rocket. The specified protective device, as the closest analogue, can be adopted as a prototype. The prototype is not without the drawback described above in similar devices that requires the conversion of a sea-based missile for its use, and hence its cost.

One of the tasks in putting the OKA into low Earth orbit is to reduce the cost of costs, which can be solved by using

launch of OKA of non-converted sea-based missiles, while the cost-effectiveness is much higher if the launch is made from a submarine, combining it either with the training launch of missiles, or with the disposal of missiles with an expiring warranty period by the method of their launch. To carry out such a launch, only the replacement of combat equipment (warheads) with OKA is necessary. In addition, a submarine can launch a rocket from virtually any latitude of the globe.

The technical task of the utility model, based on the design features of three-stage combat missiles of the RSM-54 type, used to put the OKA into low Earth orbit (see under the general editorship of Russian Marshal Igor Sergeyev “Russia's Arms and Technologies” - Encyclopedia XXI Century, Volume 1 “Strategic Nuclear Force "- the publishing house" Arms and Technologies ", Moscow 2000, p.203-204), is to protect the complex configuration of the OKA, placed on the ground of warheads in a sea-based missile from:

- gas-dynamic and fragmentation effects of the separation system of its second and third stages;

- thermal and acoustic effects during the operation of engines of the third stage;

- a sharp pressure drop after the separation of the second and third stages;

- from undesirable impurities during gas exchange OKA with the environment, starting from the stage of ground operation.

The technical problem posed in the application is solved in that the protective device for an orbiting spacecraft placed in a sea-based combat missile contains a housing that is a shell that is not closed from the big and small ends, supported by frames, a plate for fastening the spacecraft and a platform for mounting the hull to the rocket. The shell of the housing is made, for example, in the form of an elliptical stepped cone

from composite material, for example, fiberglass, which, due to its manufacturability, allows in various ways to obtain a shell of such a complex configuration, dictated by the place of its placement in the rocket (in the combat compartment). The casing frame along the small end is made of metal and, due to the sealing with a rubber ring, is hermetically sealed with a plug fixed by a threaded sleeve screwed into the frame by thread. The frame of the shell at the large end is formed by increasing its thickness in the required place. The shell of the housing from the outside is protected by a heat-shielding coating, for example, TTP-FS of a given thickness, which in addition to its main function reduces acoustic loads.

The body of the protective device is connected to the plate for fastening the spacecraft using pyrozamas mounted on the plate, the bolts of which form a threaded connection with the frame bushings of the large end of the shell, while the joint of the body with the plate is made through pin supports installed in the frame and fixing the plate at a specified end distance. Between the end and the plate there is a low-elastic dust and moisture protection gasket, the necessary working deformation of which determines the specified distance between the end and the plate.

The body with the plate is connected to the platform by means of pyro-locks fixed on the platform, the bolts of which pass through the plate and form a threaded connection with the large end frame sleeves, additionally reinforcing the body with the plate.

The large-end frame bushings form a threaded connection with plugs that hermetically reinforce their fastening zone with the housing.

The internal cavity of the casing is protected from gas emission from the casing by an aluminum foil glued to it; it is also protected from unwanted impurities during gas exchange with the environment by making the casing and passes through the plate into the internal cavity, for example, for electrical connectors, sealed and making holes in

a plate for relieving internal excess air pressure in the form of a jet protected by a filter.

The dust and moisture protection gasket is made of Isolon material, for example, PPE 3005 and is installed with the necessary deformation, which allows the gasket to equalize the pressure with the environment, in addition to the nozzle, through the gasket surface in contact with the plate with an excess air pressure in the internal cavity. In the absence of a differential pressure, the dust and moisture protection gasket serves as a sealing gasket.

The plate is equipped with spring pushers fixed on it, the pushing elements of which are made in the form of rods passing through holes in the plate and abutting against the large end face of the shell.

The platform is made in the form of a frame structure equipped with pockets for placing pirozamok, holes for attaching to the rocket, protective screens in the form of bent plates that cover laterally the internal space of the platform from fragments of rocket design elements that occur at the time of separation of the steps.

Duplicated spacecraft launching devices are fixed on the plate, the activation buttons of which are in contact with adjustable supports located on the platform

The essence of the proposed technical solution is illustrated by drawings, where in Fig.1 shows a General view of the protective device for the OKA, placed in a sea-launched military missile; figure 2 is a view of B in figure 1; figure 3 shows the remote element A in figure 1 - mounting the housing with a plate; figure 4 is a section bb in figure 1; in Fig.5 is a section NN in Fig.2 - mounting the housing with the platform; figure 6 is a section DD in figure 2 for the placement of the nozzle; in Fig.7 is a section TT in Fig.2 along the spring pusher; on Fig - view C in figure 2 on the relative position of the launch device of the spacecraft and the platform.

A protective device for an orbiting spacecraft placed in a sea-launched combat missile (FIG. 1),

comprises a casing 1, which is an enclosure 4 open from the large 2 and small 3 ends, supported by frames 5, 6, a plate 7 for attaching the spacecraft and a platform 8 for attaching the casing 1 with the plate 7 to the rocket. The shell 4 of the housing 1 is made, for example, in the form of an elliptical stepped cone of composite material, for example, fiberglass. The frame 5 of the shell 4 along the small end 3 is made of metal and due to the sealing with the rubber ring 9 is hermetically sealed with a plug 10 fixed by the threaded sleeve 11 screwed into the frame 5 by thread. The frame 6 of the shell 4 along the large end 2 is formed by increasing its thickness in necessary place. The shell 4 of the housing 1 from the outside is protected by a heat-protective coating 12, for example, TTP-FS of a given thickness.

The housing 1 (Fig. 1) of the protective device is connected to the plate 7 for fastening the spacecraft with the help of the lock pins 13 mounted on the plate, the bolts 14 (Fig. 3) of which form a threaded connection with the sleeves 15 of the frame 6 of the large end face 2 of the shell 4, and the joint the housing 1 with the plate 7 is implemented through the pin supports 16 (Fig. 4) installed in the frame 6 and fixing the plate 7 at a distance 17 specified from the end 2. Between the end 2 and the plate 7 there is a slightly elastic dust and moisture protection gasket 18, the necessary working deformation of which determines given e the distance 17 between the end 2 and the plate 7.

The housing 1 with the plate 7 is connected to the platform 8 (Figs. 2, 5) by means of the lock pins 13 mounted on the platform, the bolts 14 of which pass through the plate 7 and form a threaded connection with the sleeves 15 of the frame 6 of the large end face 2 (Fig. 5), additionally reinforcing body 1 with plate 7.

The sleeve 15 of the frame 6 of the large end 2 form a threaded connection with plugs 19 (Fig.3, 5), which hermetically reinforce the area of their fastening with the housing 1.

The internal cavity of the housing 1 is protected from gas emission of the shell 4 by an aluminum foil 20 glued to it (Fig. 1), it is also protected

from unwanted impurities during gas exchange with the environment due to the execution of the housing 1 and the passages through the plate 7 into the internal cavity, for example, for electrical connectors 21 (Fig. 2), sealed and holes 22 in the plate 7 (Fig. 6) to relieve internal overpressure air in the form of a nozzle 23, protected by a filter 24.

The dust and moisture protection gasket 18 is made of material (Fig. 1) isolon, for example, PPE 3005 and is installed with the necessary deformation, which allows the gasket to equalize the pressure with the environment, in addition to the nozzle 23, through the gasket 18 in contact with stove 7.

The plate 7 is equipped with spring pushers 25 fixed on it (Fig. 7), the pushing elements of which are made in the form of rods 26 passing through holes in the plate and abutting against the large end face 2 of the shell 4.

The platform 8 is made in the form of a frame structure 27 (Fig.1,2), equipped with pockets 28 for accommodating pirozamok 13, holes 29 for attaching to the rocket, protective screens 30 in the form of bent plates.

On the plate 7 are fixed (Fig. 2.8) duplicated launch device 31 of the spacecraft, the activation buttons 32 of which are in contact with adjustable supports 33, placed on the platform 8.

The protective device operates as follows. OKA is transported to a technical position (TP) assembly with a plate 7 inside the housing 1 (Fig. 1), platform 8 is transported separately. On TP, unscrew the bolts 14 (Figs. 1, 3) of the locks 13, mounted on the plate 7, and open access to the OKA by removing the housing 1 from the plate 7. After carrying out routine work with the OKA, the final assembly of the housing 1 is carried out using the locks 13 with the plate 7 and platform 8, thus closing the OKA into a protective device, which together with the OKA is fixed through holes 29 (Fig. 2) on the platform 8 in the combat compartment of the rocket. After the launch of the rocket, the protective device performs its functions of protecting the OKA from:

- gas-dynamic and fragmentation effects of the separation system of its second and third stages;

- thermal and acoustic effects during the operation of engines of the third stage;

- a sharp pressure drop after the separation of the second and third stages;

- from undesirable impurities during gas exchange OKA with the environment.

The separation of the OKA at the end of the active section of the trajectory is as follows. On command from the missile control system, the pyro locks 13 are mounted, fixed on the platform 8, releasing their bolts 14 (Fig. 5), the third stage of the rocket maneuvers with low-thrust engines (orientation nozzles) and the housing 1 together with the plate 8 and the OKA fixed to it is separated from platform 8. At the time of separation from platform 8, the released buttons 32 are triggered (Fig. 8) and the duplicated launch device 31 of the spacecraft are activated, which launch the onboard control complex (BCC) of the OKA. BKU gives the command to operate the pirozamok 13, mounted on the plate 7 (Fig.3), which release the bolts 14, after which the rods 26 of the spring pushers 25 (Fig.7) push the housing 1 of the protective device from the plate 7, freeing OKA for functioning.

Thus, the use of the proposed design of the protective device allows to solve the technical problem posed in the application.

Claims (9)

1. A protective device for an orbiting spacecraft deployed in a sea-based combat missile, comprising a housing that is an enclosure open from the large and small ends, supported by frames, a plate for attaching the spacecraft and a platform for attaching the hull with the plate to the rocket, characterized in that the shell of the housing is made in the form of an elliptical stepped cone of composite material - fiberglass, its frame along the small end is made of metal and due to plotneniya rubber ring sealingly plugged stopper fixed by the threaded sleeve screwed into a threaded frame and the frame of the large end face is formed by increasing the thickness of the shell, wherein the outer shell surface of the thermal barrier coating is applied. 2. The protective device according to claim 1, characterized in that the housing is connected to the plate for fastening the spacecraft using pyro locks mounted on the plate, the bolts of which form a threaded connection with the frame ends of the large end face, while the joint of the body with the plate is made through pin supports, installed in the frame and fixing the plate at a predetermined distance from the end, and between the end and the plate there is a slightly elastic dust and moisture protection gasket fixed to the end with glue. 3. The protective device according to claim 1, characterized in that the housing with the plate is connected to the platform by means of pirozamok mounted on the platform, the bolts of which pass through the plate and form a threaded connection with the frame ends of the large end face. 4. The protective device according to claim 2 or 3, characterized in that the large-end frame bushings form a threaded connection with plugs, hermetically reinforcing the area of their fastening with the housing. 5. The protective device according to claim 1, characterized in that the internal cavity of the housing is made of a sheath protected from gas emission due to the aluminum foil glued to it, made of undesirable impurities during gas exchange with the environment by performing the housing and passes through the plate into the internal cavity tight and due to the hole in the plate to relieve internal excess air pressure in the form of a jet protected by a filter. 6. The protective device according to claim 2, characterized in that the dust and moisture protection gasket is made of isolon material and makes pressure equalization with the environment when the air pressure is excessive in the internal cavity of the housing through the gasket surface in contact with the plate. 7. The protective device according to claim 1, characterized in that the plate is equipped with spring pushers fixed on it, the pushing elements of which are made in the form of rods passing through holes in the plate and abutting against the large end face of the shell. 8. The protective device according to claim 1, characterized in that the platform is made in the form of a frame structure equipped with pockets for accommodating pirozamok, protective screens in the form of bent plates covering the interior of the platform, and holes for mounting on a rocket. 9. The protective device according to claim 1, characterized in that the launch pad of the spacecraft is fixed to the plate, the activation buttons of which are in contact with adjustable supports located on the platform.