RU2497726C1 - Spacecraft head part and method of its assembly - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering. Spaceship head comprises craft, nose cone and transfer module for docking to carrier rocket. Main frame is arranged in spacecraft above its centre of gravity whereto transfer module is attached by end split joint detachable in flight. Nose cowl is arranged at said main frame while craft is arranged inside transfer module. Sliding supports are arranged at transfer module inner surface to slide in guide surface of craft in separation of transfer module. Proposed method of assembly comprises attaching said transfer module with craft main frame. Craft is lowered in vertical position into transfer module. Transfer module sliding supports are fitted in craft guide surface. After attachment of craft with transfer module, nose cone is attachment to craft main frame.

EFFECT: decreased weight, simplified assembly.

2 cl, 5 dwg

Description

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

Space rocket systems are known according to patents RU 2349512 and RU 2351510, each of them contains a space warhead. The space head part consists 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 launch vehicle.

Known space warhead according to patent RU 2422335, consisting of a spacecraft, a head fairing and a transition compartment connecting the launch vehicle with the spacecraft.

A known spacecraft and a method of assembling a spacecraft according to patent US 2005109878 (A1), consisting of a launch vehicle and a payload using a transition compartment between a launch rocket and a payload, wherein the transition compartment consists of two parts interconnected.

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

As the transition system, the compartment options can be applied: adapter + transition compartment, transition compartment + transition compartment, reference compartment + transition compartment, etc., which are used to connect the spacecraft to the launch vehicle in a mechanical (shared and non-separated in flight), electrical and pneumohydraulic connections.

The disadvantage of analogues and prototype is that the spacecraft, installed with its lower part on the transition system, is loaded with power and inertial loads. during the flight of the space-rocket complex, while the spacecraft fixed to the transition system with the help of a power element located above the center of mass of the spacecraft is loaded mainly with inertial loads. In the first case, the mass of the cosmic warhead becomes excess.

A known method of assembling a space head part, consisting of a rocket booster block, a transition compartment, a spacecraft and a head fairing, according to the patent RU 2378167 is a prototype.

The prototype assembly method consists in combining the vertical and horizontal assembly of the components of the space head part, namely:

- in a horizontal position, the rocket booster block is joined with the tail of the fairing;

- in a vertical position, the spacecraft is docked with the transition compartment;

- in an upright position, the assembly of the rocket booster + tail section of the head fairing is joined with the assembly of the spacecraft + transition compartment;

- in a horizontal position, the nose of the head fairing is joined with the assembly of the rocket booster + tail section of the head fairing + spacecraft + transition compartment. Such an assembly of the space head part leads to a complication of the assembly process and the manufacture of additional processing equipment that provides all the operational steps of the assembly.

The objective of the proposed invention is the creation of a space head with minimal mass characteristics by reducing the load on the transition system, as well as reducing and simplifying the assembly cycle of the space head by minimizing the operations of its assembly.

The task is achieved by the fact that in the space head part containing the spacecraft, the head fairing and the transition system, which provides the docking of the launch vehicle with the spacecraft, a power frame is introduced into the spacecraft above its center of mass, to which the transition system is docked using the end face detachable, shared in flight connection. The head fairing is mounted on the power frame of the spacecraft, the spacecraft is located in the inner cavity of the transition system, and sliding supports are installed on the inner surface of the transition system, moving along the guide surfaces of the spacecraft when the transition system is separated from it.

The problem is achieved in that in the method of assembling the space head part containing the docking of the transition system with the frame of the spacecraft, in a vertical position the spacecraft is lowered into the internal cavity of the transition system, while the sliding supports of the transition system are introduced into the guiding surfaces of the spacecraft, and after the docking of the space spacecraft with the transition system to the power frame of the spacecraft dock the head fairing.

Figure 1 shows the space head part, figure 2 shows the assembly sequence of the space head part, where:

1 - booster;

2 - spacecraft;

3 - head fairing;

4 - transition system;

5 - power frame;

6 - sliding bearings;

7 - guiding surfaces of the spacecraft;

8 - rollers;

9 - limiters.

In the space head part containing the spacecraft 2, the head fairing 3 and the transition system 4, which provides the docking of the launch vehicle 1 with the spacecraft 2, a power frame 5 is introduced into the composition of the spacecraft 2 above its center of mass 5. A transitional frame is attached to the power frame 5 system 4 with the help of an end split, shared in flight connection. The head fairing 3 is installed on the power frame 5 of the spacecraft 2, and on the inner surface of the transition system 4 there are sliding bearings 6 moving along the guide surfaces of the spacecraft 7 when the transition system 4 is separated from it.

When the transition system 4 is separated from the spacecraft 2, a uniform transition system can be achieved, for example, by introducing rollers 8 into the sliding supports 6. The transition system 4 can be offset from the spacecraft 2 in the tangential direction, for example, by limiters 9, introduced into the guiding surfaces of the spacecraft 7. To reduce the dynamic component, the rollers 8 can be spring loaded or the sliding bearings 6 can be spring-type.

In the method of assembling the space head part, in a vertical position, the spacecraft 2 is lowered into the internal cavity of the transition system 4, while the sliding supports 6 of the transition system 4 are introduced into the guiding surfaces of the spacecraft 7. After this, the transition system 4 is joined with the power frame 5 of the spacecraft 2 Then, the head fairing 3 is joined to the power frame 5 of the spacecraft 2.

In the process of assembling the space head part, the transition system 4 is fixedly mounted with its end face, for example, on a flat floor surface of the assembly and test building, and the spacecraft 2 is suspended in a vertical position and lowered into the internal cavity of the transition system 4, for example, using standard crane equipment. The introduction of the sliding supports 6 into the guide surfaces of the spacecraft 7 due to the standard crane equipment can be provided, for example, manually without the use of any special technological equipment.

The space warhead functions as follows.

After passing the space rocket system of dense layers. atmosphere head fairing 3 is separated at the junction with the power frame 5 of the spacecraft 2.

After entering a given orbit, the spacecraft 2 is separated together with the transition system 4 from the launch vehicle 1, after which the transition system 4 is separated from the spacecraft 2 at the interface with the power frame 5.

The implementation of this proposal allows to reduce the mass of the space head part by reducing the load on the spacecraft 2, and also reduces and simplifies the assembly cycle of the space head part by minimizing the operations of its assembly without the use of special technological equipment.

In addition, the case of the transition system 4 in such an arrangement of the space head part simultaneously plays the role of a fairing in the active section of the flight of the space-rocket complex, while it does not have longitudinal joints shared in flight.

The use of such an arrangement of the space head part is most expedient when launching large-sized space modules, laboratories, stations into orbit of the Earth.

Claims (2)

1. The space warhead containing the spacecraft, the head fairing and the transition system, which provides the docking of the launch vehicle with the spacecraft, characterized in that a spacecraft is inserted into the spacecraft above its center of mass, to which the transition system is docked using the end system detachable, shared in flight connection, with the head fairing mounted on the power frame of the spacecraft, the spacecraft is placed in the inner cavity of the transition system, on the inner surface of the transition system installed sliding supports moving along guide surfaces of the spacecraft when separating it from the transitional system. 2. A method of assembling a space head part containing a docking of the transition system with the frame of the spacecraft, characterized in that in the vertical position the spacecraft is lowered into the internal cavity of the transition system, while sliding bearings of the transition system are introduced into the guiding surfaces of the spacecraft, and after the docking of the space spacecraft with the transition system to the power frame of the spacecraft dock the head fairing.

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