RU2478531C1 - Spaceship head - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering, particularly, to means for placing spaceships in orbit. Spaceship head comprises spaceship, nose cone and transfer module. Transfer module, spaceship and nose cone ensure docking to carrier rocket. Nose cone docking diameter exceeds that of the carrier rocket final stage. Transfer module consists of top and bottom truncated cones jointed together in their larger diameters. Bottom case lower frame is jointed to final stage case. Cylindrical case top frame is jointed with spaceship by end face detachable connector. Bottom case top frame is jointed with nose cone by means of end face detachable connector.

EFFECT: enlarged free space under nose cone, higher reliability.

1 dwg

Description

The invention relates to rocket and space technology, and in particular to means for launching spacecraft into predetermined orbits.

Known rocket and space systems "Proton", "Soyuz-2", a sea-based rocket and space system, each of them contains a spacecraft with a head fairing, which are connected to the launch vehicle by a transition system.

Space rocket systems are known according to patents RU 2349512 and RU 2351510, each of them contains a space head part consisting of a spacecraft and a head fairing, which are connected to the launch vehicle using the support or removable compartments, respectively, located on the last stage of the rocket -carrier - analogues.

The disadvantage of analogues is the need to refine the power frame of the last stage of the launch vehicle.

The sea-based rocket and space system (see pages 522-524 of the SP Korolev Rocket and Space Corporation Energia publishing house, MENONSOVPOLIGRAF publishing house), which contains the payload block (space warhead), was adopted as a prototype. consisting of a spacecraft, a head fairing and transition compartments, with the help of which the payload block is connected to the launch vehicle.

Recently, the use of large-volume spacecraft in rocket and space systems has required the development of head fairings of larger diameter, in connection with which the transition of the head fairing to the last stage of launch vehicles having a smaller docking diameter is carried out using the lower part of the head fairing, made in the form reverse truncated cone.

Rocket and space systems, incorporating head fairings with a lower part made in the form of a reverse truncated cone, have the following disadvantages:

- an additional transition from the cylindrical part of the fairing to the inverse cone in its lower part reduces the reliability of the design and affects the manufacturability of the manufacture of the fairing;

- due to the implementation of the lower part of the fairing in the form of an inverse cone, the useful volume of the head fairing is reduced.

The objective of the proposed invention is the creation of a space head part, with the help of which the head fairing is docked with a launch vehicle having, at the last stage, a smaller docking diameter than the diameter of the head fairing, an increase in the useful volume of the head fairing and the total length of the space rocket system is maintained.

The objective is achieved by the fact that a transition compartment is introduced into the space head part containing the spacecraft and the head fairing, which, together with the spacecraft and the head fairing, provides docking with the launch vehicle, and the docking diameter of the head fairing is larger than the joint diameter of the last stage of the launch vehicle, wherein the transition compartment consists of the lower and upper truncated conical bodies, joined to each other over a larger diameter, and the lower frame of the lower case is joined van with the hull of the last stage of the launch vehicle, the upper frame of the upper hull is docked using an end split, shared in flight, connection with the spacecraft. The head fairing is docked to the upper frame of the lower body with the help of an end split, shared in flight.

Figure 1 shows the space rocket system, where:

1 - booster;

2 - spacecraft;

3 - head fairing;

4 - transition compartment;

5 - the last step;

6 - lower case;

7 - upper case;

8 - sash;

9 - nodes of a turn;

10 - the upper frame of the lower body;

11 - lower frame of the upper body;

12 - lower frame of the lower body;

13 - the upper frame of the upper body.

A transition compartment 4 is introduced into the space head part containing the spacecraft 2 and the head fairing 3, which, together with the spacecraft 2 and the head fairing 3, provides docking with the launch vehicle 1, and the docking diameter of the head fairing 3 is larger than the joint diameter of the last stage 5 of the rocket -carrier 1, while the transition compartment 4 consists of an upper and lower truncated conical bodies 6 and 7, joined to each other over a larger diameter, and the lower frame of the lower case 12 is docked with the body Ohm of the last stage 5 of the launch vehicle 1, the upper frame of the upper body 13 is docked using a split end, shared in flight, connected to the spacecraft 2. To the upper frame of the lower case 10 is docked using a split end, shared in flight, the head fairing 3 .

Having transitional compartments 4 of several sizes available, the carrier rockets 1 are docked (with the diameter of the last-stage docking frame 5 of the carrier rocket 1 smaller than the diameter of the head fairing docking frame 3) with the operated fairings 3 of various sizes of the docking frame. In addition, in the head fairing 3, the conical lower part becomes cylindrical. This allows you to increase the useful volume of the head fairing 3.

The space warhead functions as follows.

After passing through the space system of the dense atmospheric layers, the head fairing 3 is divided in the longitudinal direction into two wings 8, the head cowl 3 is separated at the junction with the lower case 6 of the transition compartment 4, then the wings 8 diverge to the sides relative to the turning points 9, after which the wings 8 of the fairing 3 are separated from the launch vehicle 1.

After reaching a predetermined orbit, the spacecraft 2 is separated at the junction with the upper case 7 of the transition compartment 4.

The implementation of this proposal allows you to:

- using the transition compartment 4 to use launch vehicles 1 in conjunction with the head fairings 3 of various sizes by eliminating the lower conical part of the head fairing 3 and without increasing the total length of the space rocket system;

- increase the useful volume of the head fairing 3 by eliminating the conical lower part of the fairing;

to simplify the design of the head fairing 3, eliminating the power transition of the cylinder to the truncated cone in the design of the fairing 3, which leads to an increase in the reliability of the structure and to improve the manufacturability of the fairing 3.

Claims (1)

A space head part comprising a spacecraft and a head fairing, characterized in that a transition compartment is introduced into it, which, together with the spacecraft and the head fairing, provides a docking with a launch vehicle, and the docking diameter of the head fairing is larger than the joint diameter of the last stage of the launch vehicle, wherein the transition compartment consists of the lower and upper truncated conical bodies, joined to each other over a larger diameter, and the lower frame of the lower joint of the joint n with the hull of the last stage of the launch vehicle, the upper frame of the upper body is docked with a split end joint, shared in flight, the spacecraft is docked to the upper frame of the lower body with a split end joint, shared in flight, the head fairing.