RU2422335C1 - Spacehead - Google Patents

Abstract

FIELD: transport. ^ SUBSTANCE: invention relates aerospace engineering, namely, to design of spacehead. The spacehead consists of head fairing, missile upper stage with instrumental framework, adapter representing tapered cone and spacecraft. The intersection line of the plane passing through longitudinal axis of spacehead and the plane formed by two axes of adjacent rods of upper stage instrumental framework where the point of intersection of these axes is located at the place of adapter connection to the mentioned framework is the extension of adapter generatrix. ^ EFFECT: better mass parameters of spacehead and increase of payload zone in underfairing area of spacehead. ^ 1 dwg

Description

The invention relates to rocket and space technology, and in particular to the construction of the space head part, which is part of space rockets intended for launching various space objects — payloads — into working energy orbits.

In 2002, the international project “Land Launch” was created, which provided for the modernization of the launch complex existing at the Baikonur Cosmodrome for launching the Zenit-3 SLB space rocket, consisting of the Zenit-2SB launch vehicle and the space warhead ( see Magazine "Cosmonautics News" No. 10, 2005, p. 66).

Known space head part, consisting of a rocket booster block with an instrument rod farm, a transition system consisting of an adapter and a transition compartment and mounted on the instrument bar truss of a rocket booster block, a spacecraft mounted on a transition system and a head fairing mounted on a rocket booster block (Magazine "Cosmonautics News" No. 10, 2005, p. 66) - analogue.

The analogue transition system consists of two power housings docked together: the spacecraft adapter and the transition compartment, made in the form of truncated cones, and the angles of inclination of their generators with respect to the longitudinal axis of the space head part are different. In addition, these angles differ from the same angle of inclination of the axes of the rods of the instrument rod truss of the rocket booster block.

A disadvantage of the analogue is the use of a transition system in the space head part, the inclination angles of the constituent parts of which, together with the angle of each plane of the instrument bar truss of the rocket booster block formed by the axial lines of two adjacent rods, are different from each other with respect to the longitudinal axis of the space head part , as a result of which the load from the spacecraft during the flight of the space rocket is not optimally distributed, which leads to the need for rochnyat transitional system and elements of communicating with her, as a result of mass characteristics of the transitional system and the space head part of the overall surplus obtained. In addition, the use of such a transition system in the composition of the space head part leads to a decrease in the zone of placement of the payload in the runoff space of the space head part.

A known spacecraft and a method for assembling a spacecraft consisting of a launch vehicle and a payload using an adapter between a launch vehicle and a payload, the adapter consisting of two parts interconnected (see patent US 2005109878 (A1) - Spacecraft and the method of manufacturing such a spacecraft and adapter that will be used in such a spacecraft) is a prototype. Thus, the space head in the said patent is presented in the form of an assembly consisting of two adapters, each of which is presented in the form of a truncated cone, and a payload.

The aforementioned patent does not describe the angles of inclination of the forming adapters. Any mismatch in the angle of inclination of the generatrix of one adapter with respect to the other adapter leads to additional spacer forces at the junction of these adapters and, consequently, to compensation of these forces due to the investment in the design of additional mass, which is a disadvantage of the prototype.

The objective of the invention is to improve the mass characteristics of the space head part.

The task is achieved due to the fact that in the space head part, consisting of a head fairing, a rocket booster block with an instrument rod truss, an adapter made in the form of a truncated cone, and a spacecraft, the line of intersection of the plane passing through the longitudinal axis of the space head part and perpendicular a plane formed by two axes of adjacent rods of the instrument bar truss of the rocket booster block, at which the intersection point of these axes is located at the junction of the adapter and the aforementioned Hermas, is a continuation of the adapter.

The drawing shows a space head part, where:

1. rocket booster;

2. spacecraft;

3. head fairing;

4. adapter;

5. instrument core farm;

6. rods;

7. longitudinal axis.

In the space head part, consisting of the head fairing 3, the rocket booster block 1 with the instrument rod farm 5, the adapter 4, made in the form of a truncated cone, and the spacecraft 2, the line of intersection of the plane passing through the longitudinal axis 7 of the space head part and perpendicular to the plane formed by two axes of adjacent rods 6 of the instrument rod truss 5 of the rocket booster block 1, at which the intersection point of these axes is located at the junction of the adapter 4 and said truss 5, is longer iem the adapter 4.

The space warhead functions as follows. After the space rocket leaves the dense atmosphere, the head fairing 3 is discharged. Then, after the launch rocket is completed, the head orbital block consisting of the spacecraft 2, adapter 4 and the rocket booster block 1 is separated from the launch rocket.

The rocket booster block 1 completes the launch of the spacecraft 2 into the calculated orbit, after which the rocket booster block 1 is separated together with the adapter 4 from the spacecraft 2.

Due to the fact that the intersection line of the plane passing through the longitudinal axis 7 of the space head part and the perpendicular plane formed by two axes of adjacent rods 6 of the instrument rod truss 5 of the rocket booster block 1, in which the intersection point of these axes is located at the junction of the adapter 4 and the truss 5, lie on one straight line, a decrease in the mass of the space head by ~ 0.6% is achieved.

Claims (1)

The space head part, consisting of a head fairing, a rocket booster block with an instrument rod truss, an adapter made in the form of a truncated cone, and a spacecraft, characterized in that the line of intersection of the plane passing through the longitudinal axis of the space head part and the perpendicular plane formed the two axes of adjacent rods of the instrument bar truss of the rocket booster block, at which the intersection point of these axes is at the junction of the adapter and the truss rodolzheniem the adapter.