RU154855U1 - TRANSMISSION COMPARTMENT OF THE HEAD OF THE ROCKET - THE CARRIER - Google Patents

Abstract

1. The transition compartment of the head of the launch vehicle, comprising a housing made in the form of a truncated cone and provided with a casing, upper and lower end frames and a longitudinal power kit, an internal end frame located inside the body and made with a change in cross section, and means for providing a rigid the connection of the housing with the inner end frame, while the upper end frame of the housing is made with the possibility of connection with the head fairing, the lower end frame with the last a single stage of the launch vehicle, and the inner end frame - with the possibility of connecting with the payload, characterized in that the means for rigidly connecting the body to the inner end frame is made in the form of trusses, each of which contains two braces, two power rods and a support unit made in the form of a glass, on the side wall of which the first ends of the trusses of the truss are rigidly fixed and the first ends of the power rods of the truss are pivotally fixed, while the second ends of the rods are fixed on the upper end frame of the body sa, and the second ends of the braces are on the lower end frame of the housing, the internal end frame is made up of sections rigidly connected to each other by power brackets, each of which includes upper and lower supporting platforms connected by an inclined wall and located on opposite sides of the inclined wall, wherein the base of the aforementioned support unit of each of the trusses is removably fixed to the lower support area of one of the power brackets, and the upper support area is made to enable soy

Description

The utility model relates to rocket and space technology and can be used in the design of space transport systems for delivering payloads to the orbits of artificial Earth satellites (OIZZ) as part of the space head part of launch vehicles.

From the patent for the invention of the Russian Federation No. 2478533 (IPC B64G 1/22, F42B 15/00, publ. 04/10/2013) a technical solution is known for the transition compartment - the intermediate compartment of the space head part. In accordance with this decision, the transition compartment of the head part - the intermediate compartment, includes a cylindrical shell, upper and lower end frames. The transverse overall dimension of the transition compartment — the diameter of the cylindrical shell — is equal to the transverse overall dimension — the diameter of the last stage of the launch vehicle. The lower end frame is configured to be connected to the last stage of the launch vehicle. The upper end frame of the transition compartment is made with a profile in the form of a channel-shaped form with a wall developed in the transverse direction, due to which the payload, the spacecraft and the head fairing, is secured to the upper frame. In this case, the end frames of the head fairing and the spacecraft are connected to the wall of the upper end frame of the transition compartment.

In addition to these elements, the transition compartment of the head part contains a longitudinal power set - reinforcing elements connected to the cylindrical shell of the transition compartment and the upper end frame from the side of the shell of the transition compartment, and additional transverse frames placed between the end frames of the transition compartment.

The technical solution of the transition compartment considered above solves the problem of increasing the useful volume of the space head part of the launch vehicle by placing part of the payload inside the transition compartment in combination with improving the mass characteristics of the space head part by attaching the head fairing frames and the payload directly to the end frame wall. This solution can be effectively used in deriving payloads, the layout of which includes a block located below the butt frame of the spacecraft, the longitudinal dimension of which is quite significant, and the transverse dimension is smaller than the transverse dimension of the butt frame of the payload. This payload block is located in the internal volume of the transition compartment. However, in the case of using the considered solution of the transition compartment in the space head part, including, for example, booster blocks or spacecraft, in the arrangement of which there are no units or blocks of significant dimensions located below the docking frame, the considered technical solution becomes ineffective, since the transition compartment must to perceive longitudinal and transverse loads both from the head fairing and from the spacecraft and transfer them to the power elements of the last her stage of the carrier rocket. It is problematic to use this technical solution in space warheads, including conical shells adjacent to the junction with the transition compartment, since this increases the mass of the upper end frame, which is additionally loaded with compressive loads.

The closest analogue of the proposed transition compartment of the head of the launch vehicle is the solution according to the patent of the Russian Federation No. 2521078 (MCP B64G 1/22, publ. 06/27/2014). In accordance with this decision, the transition compartment of the head of the launch vehicle comprises a housing, an internal end frame and means for providing a rigid connection of the body with the internal end frame.

The housing of the transition compartment of this solution is made in the form of a conical shell and, in addition to the casing, is equipped with upper and lower end frames. The lower end frame of the housing is made in the form of a profile in the form of a corner, the walls of which are deployed relative to each other at an obtuse angle. The lower end frame of the housing is made with the possibility of connection with the last stage of the launch vehicle. The upper end frame of the housing is made with the possibility of connection with the head fairing.

The inner end frame is connected to the payload. The inner end frame of the solution in question is made in the transverse plane of variable section. This is achieved by changing its linear size in the transverse direction, due to which in this technical solution it is possible to fasten the payload with an offset relative to the longitudinal axis of the launch vehicle.

Means for providing a rigid connection of the housing with the inner end frame in this technical solution is made in the form of an inner conical shell provided with a lower end frame. The lower end frame of the inner conical shell is fixed to the wall of the lower end frame of the housing - the outer conical shell of the transition compartment of this technical solution. In the upper part, the inner conical shell is connected to the inner end frame. In addition, in the considered solution, the inner end frame is connected to the upper end frame of the housing by power rods made in this solution of adjustable length.

In addition to this, the means of providing a rigid connection to the housing of the transition compartment (inner conical shell) in this solution is equipped with an intermediate frame. To ensure rigidity and load-bearing capacity, the means for ensuring a rigid connection of the inner end frame with the body is the inner conical shell, reinforced by longitudinal scarves located between the intermediate frame and the inner end frame. To ensure the rigidity of the installation of the payload locks, the inner conical shell is provided with longitudinal beams of variable cross-section.

The indicated technical solution of the transition compartment allows us to expand the operational capabilities and efficiency of using the transition compartment for launching a large payload with a displaced center of mass relative to the longitudinal axis of the launch vehicle at the SIZZ, while maintaining the stability and controllability of the launch vehicle in flight. However, the use of this technical solution, which provides for the use of a conical shell for transferring forces from the payload to the launch vehicle, is justified only if the load perceived by the conical shell is distributed, for example, when a multi-bolt connection is used in conjunction with the launch vehicle. In common structural designs of space-head warheads, which are characterized by a point-wise connection of the payload and the last stage of the launch vehicle with the transition compartment, the internal conical shell of the transition compartment, even supported by the power set, has a significant mass at a higher voltage level, so as significant pieces of the conical shell adjacent to the joints are excluded from the perception of loads.

The technical problem solved by the claimed utility model is to reduce the mass of the transition compartment, which receives concentrated (point) forces from the payload and transfers these loads to the last stage of the launch vehicle in the presence of a point junction between the launch vehicle and the transition compartment and between the payload and the transition compartment .

The technical problem is solved as follows.

The known transition compartment of the head of the launch vehicle comprises a housing, an internal end frame and means for providing a rigid connection of the body with the internal end frame. The body of the known solution is made in the form of a truncated cone and is equipped with a casing, upper and lower end frames and a longitudinal power set. The inner end frame is located inside the housing and is made in a known solution with a change in cross section. In this case, the upper end frame of the housing is made possible to connect to the head fairing, the lower end frame to the last stage of the launch vehicle, and the inner end frame to connect to the payload.

In the claimed decision of the transition compartment of the head of the launch vehicle, the new means is that the means for rigidly connecting the outer casing to the inner end frame are made in the form of trusses, each of which contains two braces, two power rods and a support unit made in the form of a cup on the side the wall of which the first ends of the truss braces are rigidly fixed and the first ends of the power rods of the truss are pivotally fixed. In addition, in accordance with the claimed solution, the lower and upper end frames of the body on its large parts are made in the form of profiles with a cross-section in the shape of a channel. On the belts of the end frames of the casing the casing is fixed, and on the walls of the end frames the second ends of the rods and braces of the truss are fixed: on the wall of the upper end frame are fixed the second ends of the rods, and on the wall of the lower end frame - the second ends of the braces, and in the places of fastening the braces of the wall end frame is made with increased thickness.

In addition, in accordance with the claimed solution, the inner end frame is made up of sections rigidly connected to each other by power brackets, each of which includes upper and lower supporting platforms connected by an inclined wall and located on different sides of the inclined wall. The base of the aforementioned support unit of each truss by a detachable connection is fixed on the lower support area of one of the power brackets, and the upper support platform is made to provide connectivity to the payload.

The implementation of the inner end frame of the sections rigidly connected to each other by power brackets, each of which includes upper and lower supporting platforms connected by an inclined wall and located on different sides of the inclined wall allows optimally taking point loads from the payload in the optimal way at all stages of ground operation and removal of the payload on the OIZZ.

The implementation of the means of rigidly connecting the outer casing with the inner end frame in the form of trusses, each of which contains two braces connected to the lower end frame, two power rods, and a support unit made in the form of a glass, on the side wall of which the first ends of the truss braces are rigidly fixed and the first ends of the power rods of the truss are pivotally fixed, it allows to reduce the mass of the transition compartment, since truss structures can operate at a higher voltage level in comparison with the reinforced shell point.

In addition, the power rods of the trusses provide the necessary rigidity of the construction of the transition compartment during its assembly and testing, and the hinged fastening of the first ends of the power rods of the trusses to the supporting nodes of the trusses simplifies the assembly of the transition compartment.

The technical result from the use of these techniques is to reduce the mass of the transition compartment of the head of the launch vehicle.

The execution of the end frames of the casing on its large parts in the form of profiles with a cross-section in the form of a channel, on the belts of which are fixed the casing of the casing with a longitudinal power set, and on the walls of the end frames the second ends of the rods and braces of the trusses are fixed, which allows transferring to the lower end the load frame from the head fairing and trusses and further reduce the weight of the transition compartment structure.

In addition, in the transitional compartment of the head of the launch vehicle, the sections of the inner end frame are most preferably made in the form of a L-shaped profile, which is effective in terms of weight of the structure, and the execution of parts adjacent to the junction of the sections of the inner end frame with power brackets with the transition from the L-shaped profile to the Z-shaped profile allows you to reduce the stress concentration, further reducing the weight of the transition compartment structure.

Among other things, it is advisable to reinforce the support pads of the power brackets with side walls connected to the inclined walls of the brackets, which can further reduce the mass of the structure when farms perceive concentrated efforts from the payload.

The claimed technical solution is illustrated by the following materials:

FIG. 1 is a General view of the transition compartment in a perspective view,

FIG. 2 - a common transition compartment from below (view A from Fig. 1),

FIG. 3 - connection nodes of the upper and lower end frames of the housing with the sheathing of the transition compartment (section FJ with Fig. 2),

FIG. 4 is a General view of the inner end frame in a perspective view,

FIG. 5 is a profile of the inner end frame on most of its sections (section 3-3 of Fig. 12),

FIG. 6 is a profile of the inner end frame on the parts adjacent to its joints with a power bracket (section II with Fig. 12),

FIG. 7, 8 - power bracket of the inner end frame in a perspective view (view from the inside and outside of the inner end frame),

FIG. 9 - the reference node of the farm in a perspective view,

FIG. 10 is a General view of the farm in the assembly with frames and cladding in a perspective view,

FIG. 11 is a General view of the farm in the Assembly with frames and casing (view B from Fig. 2),

FIG. 12 - farm in the assembly with frames, bottom view (view In from Fig. 11),

FIG. 13 - nodes connecting the brace of the farm with the support node of the farm and with the lower end frame (section EE with Fig. 12),

FIG. 14 - farm in the assembly with frames, the braces of the farm conditionally not shown (view In from 11),

FIG. 15 - nodes connecting the power rod with the supporting node of the farm and with the upper end frame (section DD from Fig. 14).

The inventive transition compartment of the head of the launch vehicle is arranged as follows.

The transition compartment of the head of the launch vehicle contains a housing that is made in the form of a truncated cone (see Fig. 1, 2, 3). The housing is equipped with a casing 1, upper 2 and lower 3 end frames and a longitudinal power set 4. In addition, the transition compartment is equipped with an internal end frame 5 and means for providing a rigid connection of the body with the inner end frame 5.

The transition compartment of the launch vehicle as part of the spacecraft head part using fastening and separation means (locks, pushers and other elements) not shown in the drawings, known from the prior art, is connected to the last stage of the launch vehicle, to the head fairing and to the payload

The upper 2 and lower 3 end frames in accordance with the claimed solution on its large parts are made in the form of profiles with a cross-section in the shape of a channel (see Fig. 3), the belts of which are made of different heights. The casing 1 of the housing is equipped with hatches to provide access for servicing the head of the internal elements of the adapter compartment at a technical position and is fixed on the outer belts of the upper and lower end frames. The upper 2 end frame of the housing is made possible to connect to the head fairing of the launch vehicle (not shown in the drawings), while on the wall of the upper end frame 2 there are mounting points for the transition compartment with the head fairing, made in the form of pins 6 of small height. The lower end frame is configured to be connected to the last stage of the launch vehicle, while the wall of the lower end frame is provided with holes 7 for accommodating docking elements with the last stage of the launch vehicle.

The longitudinal power set 4 of the transition compartment housing can be made in the form of longitudinal beams.

The inner end frame 5 is located inside the housing and is configured to connect the transition compartment with the payload. The inner end frame (see Fig. 4) is composed of sections 8, rigidly connected to each other by power brackets 9.

Sections 8 of the inner end frame 5 are made with a change in the cross section (see Figs. 4, 5, 6, 10, 12, 13): along their large parts, the sections of the inner end frame are made in the form of a L-shaped profile, as shown in FIG. 5, the walls of which are located at an obtuse angle to each other. The parts of the sections of the inner end frame adjacent to the joints with the brackets 9 are made with the transition from the L-shaped profile to the Z-shaped profile (see Fig. 6, 12, 14), the belts of which are located at obtuse angles to the wall.

The power brackets 9 (see Figs. 7, 8) are made of the lower 10 and upper 11 walls and the inclined wall 12. The lower 10 and upper 11 walls are located on opposite sides of the inclined wall 12 and connected to it at obtuse angles. Each of the brackets 9 includes a lower 13 and upper 14 bearing pads located on the lower 10 and upper 11 walls of the power bracket 9. The lower 13 and upper 14 bearing pads of the power brackets are made with increased thickness, reinforced by side ribs 15 and provided with holes for mounting fasteners trusses of the transition compartment and payload, as shown in FIG. 7, 8.

The means for rigidly connecting the body to the internal end frame in accordance with the claimed solution of the utility model are made in the form of trusses 16 (see Fig. 1, 2), evenly spaced along the circumference of the body and connected to the upper 2 and lower 3 end frames of the body and to the internal end frame 5 transition compartment.

Each of the farms 16 (see Fig. 10-15) contains two braces 17, two power rods 18 and a support node 19.

The braces 17 and the power rods 18 are made of pipes, the ends of which are equipped with fastening means to the end frames of the housing and the support nodes of the trusses: the first ends of the power rods are made in the form of a “plug” connecting element, the second ends of the power rods and the ends of the braces are made in the form of fittings equipped with supporting platforms with holes for placement of elements of detachable connections.

The support node 19 of each of the trusses is made in the form of a glass (see Fig. 9), on the side wall of which two fittings 20 are rigidly located, equipped with an “ear” fastening element, and the base is equipped with an opening for accommodating a detachable connection fastening element.

In accordance with the claimed solution, the first ends of the braces 17 of the trusses are rigidly, and the first power rods 18 are pivotally mounted on the side wall of the support node 19 of the truss. In this case, the first ends of the braces 17 of the trusses can be welded with the ends of the fittings 20 (see Fig. 8), and the power rods are fixed to the support node by the ear-plug connection using the articulated bearing 22 (see Fig. 15).

In accordance with the claimed solution, the second ends of the rods 18 are mounted on the lower side of the wall of the upper end frame 2 (see Fig. 14, 13) using two screws 24. The second ends of the braces 17 are fixed on the upper surface of the wall of the lower end frame 3 using detachable connections (see Fig. 8).

As the main means of securing the second ends of the truss braces to the lower end frame of the housing (see Fig. 13), it is most preferable to use a detachable connection 2, for example, a bolted connection passed through holes 7 and connecting the power element 26 of the last stage of the launch vehicle into one package, the lower end frame 3 of the housing and the second end of the truss 17. To ensure additional rigidity of the transition compartment and the head part as a whole, it is advisable to provide the specified connection with additional elements of cre 23, for which two screws and a pin can be used.

As mentioned above, the upper 2 and lower 3 end frames on their large parts are made in the form of profiles with a cross-section in the shape of a channel, however, at the joints of the upper and lower end frames of the body with the elements of the truss, the frame wall is made with increased thickness and the frame belts are cut.

In accordance with the claimed solution, the base of the support unit 19 of each truss is detachable by a fastening to the lower support platform 13 of one of the power brackets, which can be done using studs. In this case, the upper bearing pads 14 of the power brackets are made with the possibility of connection with the payload.

The structural elements of the inventive transition compartment of the head of the launch vehicle can be made of aluminum-based alloys. In the manufacture of the upper and lower end frames of the workpieces, precision-milled channel sections of the channel are made. Separate turned-milled sections of the upper end frame and separate power brackets of the internal end frame, which are connected by welding during the assembly of the internal end frame, are also made of aluminum-based alloy billets. During the assembly of the transition compartment housing, its casing is connected to the end frames and the riveting power set. The pipe blanks of the braces and power rods of the truss are welded together with their tips at their first and second ends. The first ends of the braces are welded to the supporting nodes of the trusses. During the aggregate assembly of the transitional compartment, the trusses are detachable to the case of the transitional compartment and to the internal end frame, while the articulated connection of the power rods with the supporting nodes of the truss simplifies the assembly process. After this, the assembly of the warhead as a whole is carried out.

In the process of launching the launch vehicle, the upper end frame of the housing receives, through the pins 6, the longitudinal and transverse load from the head fairing, which occurs during ground operation and at the stage of launching the launch vehicle under the action of a high-pressure head, and transfers these loads to the case of the transition compartment supported by the power set . The longitudinal and transverse forces from the payload are perceived by the internal end frame and, through the support units, are transmitted to the truss braces.

When carrying out transport operations with the head part at a technical position, the longitudinal and transverse forces from the payload from the truss to the lower end frame are transmitted through detachable joints 23 made in the form of bolts and pins.

In the process of removing the payload by the launch vehicle, the forces from the head fairing are transmitted through the longitudinal power elements of the hull and its casing to the lower end frame of the hull and through the bolts and pins installed in the holes 7 are transferred to the design of the launch vehicle. The longitudinal and transverse forces from the braces of the trusses are transmitted to these same elements.

The power rods connecting the inner end frame with the upper end frame of the housing serve to provide structural rigidity of the transition compartment during assembly and testing.

The considered example of the structural design of the transition compartment (see Fig. 1-15) allows you to perceive the inertial and aerodynamic loads from the head fairing and transfer them through the casing and its power set to the lower end frame. At the same time, with the internal end frame, the concentrated forces from the payload are received by eight power brackets and transmitted through the braces of eight trusses to sixteen points of the lower end frame. Calculations and design studies can reduce the mass of the transition compartment of the head of the launch vehicle by 4 ... 6% in comparison with well-known analogues.

The claimed solution to the transition compartment can be made at the enterprises of the rocket and space industry.

Claims (6)

1. The transition compartment of the head of the launch vehicle, comprising a housing made in the form of a truncated cone and provided with a casing, upper and lower end frames and a longitudinal power kit, an internal end frame located inside the body and made with a change in cross section, and means for providing a rigid the connection of the housing with the inner end frame, while the upper end frame of the housing is made with the possibility of connection with the head fairing, the lower end frame with the last a single stage of the launch vehicle, and the inner end frame - with the possibility of connecting with the payload, characterized in that the means for rigidly connecting the body to the inner end frame is made in the form of trusses, each of which contains two braces, two power rods and a support unit made in the form of a glass, on the side wall of which the first ends of the trusses of the truss are rigidly fixed and the first ends of the power rods of the truss are pivotally fixed, while the second ends of the rods are fixed on the upper end frame of the body sa, and the second ends of the braces are on the lower end frame of the housing, the internal end frame is made up of sections rigidly connected to each other by power brackets, each of which includes upper and lower supporting platforms connected by an inclined wall and located on opposite sides of the inclined wall, wherein the base of the aforementioned support unit of each of the trusses is removably fixed to the lower support area of one of the power brackets, and the upper support area is made to enable soy Inonu payload. 2. The transitional compartment of the head of the launch vehicle. 1, characterized in that the lower and upper end frames of the housing on its large parts are made in the form of profiles with a cross-section in the form of a channel, on the belts of which the casing is fixed. 3. The transition compartment of the head of the launch vehicle according to claim 2, characterized in that the second ends of the rods are fixed to the wall of the upper end frame, and the second ends of the braces are fixed to the wall of the lower end frame. 4. The transition compartment of the head of the launch vehicle according to claim 3, characterized in that at the points of attachment of the braces the wall of the lower end frame is made with an increased thickness. 5. The transition compartment of the head of the launch vehicle according to claim 1, characterized in that the sections of the inner end frame are for the most part made in the form of a L-shaped profile, and on the parts adjacent to the joints with power brackets, the transition from shaped profile to a Z-shaped profile. 6. The transitional compartment of the head of the launch vehicle according to claim 1, characterized in that the supporting platforms of the power brackets are supported by side walls connected to the inclined walls of the brackets.

Images