RU2349512C1 - Space rocket system - Google Patents

Abstract

FIELD: space engineering.

SUBSTANCE: invention relates to space rocket systems, particularly to the equipment designed to boost spacecrafts into preset orbits. The space rocket system comprises carrier rocket and space vehicle with nose fairing. The proposed system additionally incorporates a base module fitted on the terminal stage vehicle, to dock carrier rocket to nose fairing that features docking diameter exceeding that of the carrier rocket docking diameter. The aforesaid base module features outer and inner primary structures made up of load-bearing elements arranged along the generating lines of the tapered and cylindrical surfaces to transfer power load from the nose fairing and space vehicle over to the carrier rocker casing. The base module cross section represents a right-angled triangle with its smaller leg located in the plane of carrier rocker docking to hose fairing. Hypothenuse is located on the base module tapered surface generating line, while the larger leg represents a continuation of the rocker terminal stage casing cylindrical surface generating line. Note that the base module has also a face releasable joint with the nose fairing to be released in flight, a joint with the frame of coupling with the space vehicle and the joint with the carrier rocket terminal stage casing.

EFFECT: increased payload.

2 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, consisting of a launch vehicle and a spacecraft with a head fairing.

The sea-based rocket and space system was adopted as the prototype (see pp. 522-524 edition of the SPKorolev Rocket and Space Corporation Energia, MENONSOVPOLIGRAF publishing house).

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

Rocket and space systems, incorporating head fairings with a lower part made in the form of an inverse 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 space-rocket systems in which the docking of various sizes of head fairings is provided with launch vehicles having, at the last stage, a smaller docking diameter with a head fairing, an increase in the useful volume of the head fairing and preservation of the total length of the space-rocket system.

The objective is achieved in that a support compartment is installed in the rocket-space system, mounted on the last stage of the launch vehicle, which ensures docking of the launch vehicle with a head fairing having a docking diameter greater than the docking diameter of the last stage of the launch vehicle; wherein the support compartment has external and internal power circuits, consisting of power elements located respectively on the generatrix of the conical and cylindrical surfaces, for transmitting the power load from the head fairing and the spacecraft to the body of the launch vehicle; in cross section, the support compartment is a rectangular power triangle, the small leg of which is located in the plane of the junction of the launch vehicle with the head fairing, the hypotenuse is located on the generatrix of the conical surface of the support compartment, and the large leg is a continuation of the generatrix of the cylindrical surface of the hull of the last stage of the launch vehicle; the support compartment also has an end detachable connection with the head fairing, shared in flight, connection with the coupling farm with the spacecraft and connection with the hull of the last stage of the launch vehicle.

Figure 1 and 2 shows the space rocket system, where:

1 - head fairing;

2 - spacecraft;

3 - reference compartment;

4 - the last step;

5 - booster;

6 - fairing flaps;

7 - nodes of a turn;

8 - external power circuit;

9 - internal power circuit;

10 - detachable connection;

11 - connection;

12 - pairing farm.

A space-rocket system is proposed, consisting of a launch vehicle 5, a spacecraft 2 with a head fairing 1, which includes a support compartment 3 installed on the last stage 4 of the launch vehicle 5, which provides docking of the launch vehicle 5 with the head fairing 1 having a docking diameter greater than the docking diameter of the last stage 4 of the launch vehicle 5; the supporting compartment 3 has an external power circuit 8 and an internal power circuit 9, consisting of power elements, for example beams, stringers, placed respectively along the generatrices of the conical and cylindrical surfaces, for transferring the load from the head fairing 1 and the spacecraft 2 to the body of the launch vehicle 5 ; the support compartment 3 also has an end detachable connection 10 with the head fairing 1, shared in flight, connection 11 with the coupling farm 12 with the spacecraft 2 and connection 11 with the body of the last stage 4 of the launch vehicle 5.

The reference compartment 3 is installed between the housing of the last stage 4 of the launch vehicle 5 and the head fairing 1, while the housing of the last stage 4 of the launch vehicle 5 is made shortened to keep the total length of the launch vehicle 5 unchanged.

In the cross section, the support compartment 3 is a power right triangle, the small leg of which is located in the plane of the junction of the launch vehicle 5 with the head fairing 1, the hypotenuse is placed on the generatrix of the conical surface of the support compartment 3, and the large leg is a continuation of the generatrix of the cylindrical surface of the housing of the last stage 4 launch vehicles 5.

The lateral surface of the support compartment 3 is conical, providing a transition from the docking diameter of the head fairing 1 to the docking diameter of the last stage 4 of the launch vehicle 5, while the support compartment 3 is attached with its lower part to the housing of the last stage 4 of the launch vehicle 5.

Having support compartments 3 of several sizes, docking of the operational launch vehicles 5 (with the diameter of the docking frame of the last stage 4 of the launch vehicle 5 smaller than the diameter of the docking frame of the head fairing 1) is ensured with the operating fairings 1 of various sizes of the docking frame. In addition, in the head fairing 1, the conical lower part is replaced by a cylindrical (i.e., the cylindrical part is extended by an amount equal to the length of the conical part). This allows you to increase the useful volume of the head fairing 1.

The proposed space rocket system operates as follows.

During the operation of the space-rocket system, the head fairing 1, until it is separated from the launch vehicle 5, transfers the load at the junction of the head fairing 1 with the reference compartment 3 and then through the external power circuit 8 of the reference compartment 3 to the housing of the last stage 4 of the launch vehicle 5.

After passing through the space system of the dense atmospheric layers, the head fairing 1 is divided in the longitudinal direction into two wings 6, the head fairing 1 is separated at the junction with the support compartment 3, then the wings 6 diverge to the sides relative to the turning units 7, after which the wings 6 of the head fairing 1 are separated from the launch vehicle 5.

The implementation of this proposal in the space rocket system allows you to:

- using the reference compartment 3, use launch vehicles 5 with a shortened body of the last stage 4 of the launch vehicle 5 together with various sizes of head fairings 1 without increasing the total length of the space rocket system;

- increase the useful volume of the head fairing 1 by replacing the conical lower part of the fairing 1 with a cylindrical one to accommodate a larger spacecraft 1;

- to simplify the design of the head fairing 1 by replacing the conical lower part with a cylindrical one, thereby eliminating the power transition of the cylinder to the cone in the design of the fairing 1, which leads to an increase in the reliability of the structure and an improvement in the manufacturability of the fairing 1.

Claims (1)

A space-rocket system comprising a launch vehicle and a spacecraft with a head fairing, characterized in that a support compartment is installed that is mounted on the last stage of the launch vehicle, which provides docking of the launch vehicle with a head fairing having a docking diameter greater than the docking diameter of the last stage launch vehicles; wherein the support compartment has external and internal power circuits, consisting of power elements arranged respectively along the generatrices of the conical and cylindrical surfaces, for transmitting a power load from the head fairing and the spacecraft to the launcher body; in cross section, the support compartment is a rectangular power triangle, the small leg of which is located in the plane of the junction of the launch vehicle with the head fairing, the hypotenuse is located on the generatrix of the conical surface of the support compartment, and the large leg is a continuation of the generatrix of the cylindrical surface of the hull of the last stage of the launch vehicle; the support compartment also has an end detachable connection with the head fairing, shared in flight, connection with the coupling farm with the spacecraft and connection with the hull of the last stage of the launch vehicle.

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