RU2478532C1 - Spacecraft head and method of its assembly - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering, particularly, to spaceship head and method of its assembly. Spaceship head comprises, nose cone and transfer module for docking to carrier rocket. Nose cone docking diameter exceeds that of the carrier rocket final stage. Transfer module has outer and inner power edges to transfer power load from nose cone and spaceship to carrier rocket body. Outer power edge represents a conical case with nose cone fitted on top frame by means of end face detachable connector. Inner power edge represents a cylindrical case with bottom frame connected with conical case bottom frame. Cylindrical case top frame is jointed with spaceship by end face detachable connector. Top frames of conical and cylindrical cases of transfer module are coupled with power rods. Method of assembling spaceship head comprises jointing nose cone flaps together. Spaceship in vertical position is jointed with top frame of transfer module cylindrical case. Two temporary semi-rings are secured at transfer module conical case top frame. End faces of nose cone flaps are fitted at temporary semi-ring node cone guide pins to joint said flaps in lengthwise edges. Nose cone is detached from temporary semi-rings by detaching guide pins to dismantle said rings. Nose cone is jointed to transfer module conical case top frame.

EFFECT: increased useful volume of nose cone, simplified design.

2 cl, 5 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 -carriers - 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 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 reverse truncated cone.

Space head parts, 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.

A known method of assembling a space head part according to patent RU 2378167 is a prototype.

The prototype assembly method consists in first undocking the cylindrical part of the fairing from the conical, and then after installing the spacecraft, the cylindrical part of the fairing is docked to the conical, which increases the assembly cycle.

In addition to increasing the assembly cycle, the disadvantage of the prototype is that for large diameters of the cylindrical part of the fairing (due to lower stiffness compared to the stiffness of the conical part of the fairing) in the horizontal position under the own weight of the head fairing, its elastic deformation occurs, resulting in an end frame can take the form of an oval, which leads to difficulties when docking with the counterpart of the space rocket system.

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 fairing and the total length of the space-rocket system without increasing the cycle assembly and deformation of the head fairing in the process of docking with the launch rocket due to the installation of the head fairing flaps in a vertical position and.

The objective is achieved by the fact that in the space head part containing the spacecraft and the head fairing, a transition compartment is introduced that provides docking with the launch vehicle, and the docking diameter of the head fairing is greater than the joint diameter of the last stage of the launch vehicle, while the transition compartment has an outer and internal power circuits for transmitting power load from the head fairing and the spacecraft to the launcher body, respectively. The external power circuit of the transition compartment is made in the form of a conical body, on the upper frame of which, with the help of an end split, shared in flight, the head fairing is installed, and 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 using an end split, shared in flight, connection with the spacecraft. The upper frames of the conical and cylindrical cases of the transition compartment are interconnected by power rods.

The task is achieved by the fact that in the method of assembling the space head part, including connecting the head fairing flaps to each other, in a vertical position the spacecraft is joined with the upper frame of the cylindrical body of the transition compartment, then two technological half rings are fixed on the upper frame of the conical body of the transition compartment, then the head flaps the fairings with their ends are installed on the guide pins of the technological half rings and the flaps of the head fairing are connected along the longitudinal joints, then undock the head fairing from the technological half rings, removing it from the guide pins of the technological half rings, and dismantle the technological half rings, after which the head fairing is joined with the upper frame of the tapered case of the transition compartment.

Figure 1 shows the space head part, figure 2 shows the installation of technological half rings between the head fairing and the transition compartment, figure 3 and 4 schematically shows the sequence of actions when installing the spacecraft, technological half rings, flaps of the head fairing, undocking the head fairing, the dismantling of technological half rings and the docking of the head fairing, Fig. 5 schematically shows the docking of the space head part with the launch vehicle, where:

1. booster;

2. spacecraft;

3. head fairing;

4. transition compartment;

5. the last step;

6. conical body;

7. cylindrical body;

8. power rods;

9. sash;

10. reversal nodes;

11. technological half ring;

12. guide pin;

13. assembly and docking trolleys;

14. the upper frame of the conical body;

15. the lower part of the cylindrical body;

16. the lower part of the conical body;

17. the upper frame of the cylindrical body;

18. lower frame of the transition compartment.

The composition of the space head part containing the spacecraft 2 and the head fairing 3, introduced the transition compartment 4, which provides docking with the launch vehicle 1, and the connecting diameter of the head fairing 3 is greater than the connecting diameter of the last stage of the launch vehicle 1, while the transition compartment 4 has external and internal power circuits for transmitting a power load from the head fairing 3 and the spacecraft 2 to the body of the launch vehicle 1, respectively. The external power circuit of the transition compartment 4 is made in the form of a conical body 6, the head fairing 3 is installed on the upper frame of the conical body 14 using a split end, shared in flight, and the internal power circuit is made in the form of a cylindrical body 7, the lower part of the cylindrical body 15 connected to the lower part of the conical body 16, forming the lower frame of the transition compartment 18. The upper frame of the cylindrical body 17 is docked using an end split, shared in flight, with unity with the spacecraft 2.

The upper frames of the conical and cylindrical bodies 14 and 17 of the transition compartment 4 are interconnected by power rods 8.

In the method for assembling the space head part, including connecting the cams 9 of the head fairing 3 to each other, in a vertical position, the spacecraft 2 is joined with the upper frame of the cylindrical body 17 of the transition compartment 4, then two technological half rings 11 are fixed on the upper frame of the conical body 14 of the transition compartment 4, Further, the flaps 9 of the head fairing 3 are installed with their ends on the guide pins 12 of the technological half rings 11 and the flaps 9 of the head fairing 3 are connected along the longitudinal joints, for thereby undocking the head fairing 3 from the technological half rings 11, removing it from the guide pins 12 of the technological half rings 11, and dismantling the technological half rings 11, after which the head fairing 3 is joined with the upper frame of the conical housing 14 of the transition compartment 4.

Next, they turn over the assembled space head part to a horizontal position, and using assembly and docking carts 13 dock it with the last stage 5 of the launch vehicle 1.

The use of guide pins 12 for docking the flaps 9 of the head fairing 3 with the technological half rings 11 in the vertical position allows you to fix the nominal position of the flaps 9 of the head fairing and join them together, and after the head fairing 3 is assembled, it acquires the necessary rigidity and is not upright loses its shape.

Having transitional compartments 4 of several standard sizes available, the carrier rockets 1 are docked (with the last-stage docking frame 5 of the launch vehicle 1 having a smaller diameter than the head fairing 3 docking frame) with 3 different sizes of the docking frame in operation head fairings. 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 longitudinally divided into two wings 9, the head fairing 3 is separated at the junction with the conical body 6 of the transition compartment 4, then the wings 9 diverge to the sides with respect to the turning units 10, after which the wings 9 of the fairing 3 are separated from the launch vehicle 1.

After entering a given orbit, the spacecraft 2 is separated at the junction with the cylindrical body 7 of the transition compartment 4.

The implementation of this proposal allows you to:

- Using the transition compartment 4, use launch vehicles 1 together with various sizes of head fairings 3 without the lower conical part of the head fairing 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 design and to improve the manufacturability of the fairing 3;

- The shape of the docking frame of the head fairing 3 is preserved during its docking with the transition compartment 4.

Claims (2)

1. A space head part comprising a spacecraft and a head fairing, characterized in that a transition compartment is inserted into it that provides docking with a launch vehicle, wherein the connecting diameter of the head fairing is larger than the joint diameter of the last stage of the launch vehicle, wherein the transition compartment has external and internal power circuits for transmitting power load from the head fairing and the spacecraft to the launcher body, respectively; the external power circuit of the transition compartment is made in the form of a conical body, on the upper frame of which, with the help of an end split, divided in flight, the head fairing is installed, and 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 using an end split, shared in flight, connection with the spacecraft; the upper frames of the conical and cylindrical cases of the transition compartment are interconnected by power rods. 2. A method of assembling a space head part, including connecting the head fairing cusks to each other, characterized in that in a vertical position the spacecraft is joined with the upper frame of the cylindrical body of the transition compartment, then two technological half rings are fixed on the upper frame of the conical body of the transition compartment, then the head flaps the fairings with their ends are installed on the guide pins of the technological half rings and the flaps of the fairing are connected along the longitudinal joints Then, the head fairing is undocked from the technological half rings, removed from the guide studs of the technological half rings, and the technological half rings are dismantled, after which the head fairing is joined with the upper frame of the conical case of the transition compartment.

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