RU2564458C1 - Ascent unit - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: ascent unit contains a payload, a payload fairing, a transfer compartment with a lower docking structural ring and an upper docking structural ring with a circular partition in the form of cross walls which are rigidly connected among themselves to fit the demountable end connections, transverse-longitudinal primary structures, a circular transverse frame.

EFFECT: invention allows to simplify design of the upper docking structural ring.

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Description

The invention relates to rocket and space technology, and in particular to the design of the space head part (KGCH), which is part of space rockets (ILV), designed to bring to working energy orbits of various space payloads (PN).

Known KGCH containing a spacecraft (SC), a head fairing (GO) and a transition compartment (PF). The transition compartment along with the spacecraft and civil defense provides docking with a launch vehicle (LV). The connecting diameter of the GO is greater than the connecting diameter of the last stage of the launch vehicle. The transition compartment consists of the lower and upper truncated conical bodies, joined to each other over a larger diameter. The lower frame of the lower body is docked with the body of the last stage of the launch vehicle. The upper frame of the upper body is docked with an end split, shared in flight connection with the spacecraft. The head fairing is docked to the upper frame of the lower casing with the help of an end split, flight joint shared in flight (see RU patent No. 2478531) - analogue.

Known KGCH containing KA, GO and PHO, which provides docking with pH. The connecting diameter of the GO is greater than the connecting diameter of the last stage of the launch vehicle. The transition compartment has external and internal power circuits for transmitting the power load from the civil defense and spacecraft to the launch vehicle, respectively. The external power circuit of the PXO is made in the form of a conical body, on the upper frame of which the GO is installed using the end split, shared in flight connection. The internal power circuit is made in the form of a cylindrical body, the lower frame of which is connected to the lower frame of the conical body. The upper frame of the cylindrical body is docked with an end split, shared in flight connection with the spacecraft. The upper frames of the conical and cylindrical bodies of the PXO are interconnected by power rods, (see patent RU No. 2478532) - analogue.

The disadvantages of analogues include the excessive weight of the structure connecting the housing of the transition compartment.

A device is known (patent RU No. 2478533 - prototype), in which the space warhead, which is part of the ILV, consists of GO and PN. PhC was introduced into the composition of the OGC, which ensures, by means of the compounds shared in flight, the connection between the PN and the LV and GO. The aggregate part of the monopole is located in the internal cavity of the PXO and is outside the limits of the PXO descent zone, which is separated from the PN along with the launch vehicle. In the upper frame of the intermediate compartment, two end detachable joints are combined, separated in flight, connecting this compartment with the civil defense and with the payload, respectively.

In the known technical solution for placing the combined end detachable joints in the upper docking frame, closing niches are made, which leads to a complication of its design.

The objective of the technical solution is to simplify the design of the upper docking frame, which also simplifies the design of the KCH in general.

The tasks are solved by the fact that in the space head part, which is part of the rocket launcher and consisting of a payload, a head fairing and a transition compartment, with lower and upper docking frames, which provide docking with a launch vehicle and connection of end-detachable end connections with the head fairing and payload, on the upper docking frame of the transition compartment secured an annular partition for detachable end connections, which is made in the form of a set of transverse st nock, rigidly interconnected, and the partition on the inner side of the transition compartment is supported by a longitudinal-transverse power set, and the end detachable connection on the side of the payload is shifted within the zone of the internal cavity of the transition compartment and fixed to the partition by means of an annular frame, while the joints of the end split compounds of PN with PXO and GO with PXO are located in the same plane.

The invention is illustrated by drawings:

- in FIG. 1 shows a general view of the space head part;

- in FIG. 2 shows an annular partition (section AA from FIG. 1);

- in FIG. 3 shows the location of the end detachable joints on the annular partition (section BB with Fig. 1), where:

1. payload;

2. head fairing;

3. transition compartment;

4. lower docking frame;

5. upper docking frame;

6. booster;

7. end detachable connection with a head fairing;

8. end plug connection with payload;

9. annular partition;

10. transverse wall;

11. longitudinal-transverse power set;

12. ring frame;

13. junction of the end detachable connection of the payload with the transition compartment

14. The joint of the end detachable connection of the head fairing with the transition compartment.

The space head part consists of the payload 1, the head fairing 2 and the transition compartment 3 with the lower and upper docking frames 4, 5, while the lower docking frame 4 of the transition compartment 3 is attached to the last stage of the launch vehicle 6, and the upper docking frame 5 serves for installing the head fairing 2 and the payload 1 on it. The payload 1 and the head fairing 2 are fastened to the upper frame 5 of the transition compartment 3 by means of an end detachable connection with the head fairing 7 and socket detachably connected to a payload 8 by means of the annular partition 9, which is configured as a set of cross-walls 10 rigidly interconnected.

The end detachable connections with the head fairing and with the payload 7, 8 are spaced by displacing the end detachable connection with the payload 8 within the zone of the internal cavity of the transition compartment 3.

To ensure the specified rigidity and strength of the annular partition 9, it is supported on the inside of the transition compartment 3 by a longitudinally transverse power set 11, which can be made, for example, in the form of fittings, brackets, stringers, beams (not shown in the drawing), which distribute the action on the annular partition 9 of concentrated efforts on the entire body of the transition compartment 3. The payload 1 is fastened to the annular partition 9 by means of the ring frame 12, while the joint of the end split the payload of the connections with the transfer compartment 13 and socket joint fairing releasable connection with the transfer compartment 14 are arranged in one plane.

The use of the claimed technical solution will simplify the design of the upper docking frame by introducing an annular partition that allows to split split end connections without the use of lockable niches.

Claims (1)

The space warhead, which is part of the rocket launcher and consisting of a payload (PN), a head fairing (GO) and a transition compartment (PXO) with lower and upper docking frames, providing docking with a launch rocket and connecting in-flight split end connections with a head fairing and a payload, characterized in that on the upper docking frame of the transition compartment an annular partition is fixed for detachable end connections, which is made in the form of a set of transverse walls, w tightly interconnected, and the partition on the inner side of the transition compartment is supported by a longitudinal-transverse power set, and the end detachable connection on the payload side is displaced within the zone of the internal cavity of the transition compartment and secured to the partition by means of an annular frame, while the joints of the PN end detachable joints with PXO and GO with PXO are located in the same plane.

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