RU2574103C2 - Method of payload integration and device to this end - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to space engineering and can be used for spacecraft payload integration. Claimed device comprises the spacecraft and is composed of the separable structural tube of isogrid to make the spacecraft load-bearing body. It consists of the parts depending on the height and quantity of spacecraft in the payload, with constant cross-section area within one part and cross-section increasing toward the carrier rocket adapter. Spacecraft are built around appropriate units of separable parts of said detachable load-bearing tube at the Manufacturers' to combine said spacecraft to the integral payload. The spacecraft head is assembled to include the payload and nose cowling. Now, said head is mounted at its prescribed seat at carrier rocket.

EFFECT: compact design, ease of assembly.

5 cl, 2 dwg

Description

The invention relates to space technology, in particular to spacecraft launched into orbit by means of launch vehicles.

A known method of layout of the payload under the head fairing of the Dnepr launch vehicle (http://www.kosmotras.ru/upload/kgc_iul_2013.pdf, p.5-6) using an additional frame installed in the cylindrical part of the head fairing, providing Seats for fixing several spacecraft.

The disadvantages of this method are the limited use of it on different types of launch vehicles, associated with the need to develop a non-standard head fairing for each type, as well as the reduction in the mass of the payload displayed by the launch vehicle due to the mass of the frame and an additional system for separating this frame from the head fairing.

Also known is the space warhead for group launch of satellites (patent RU 2428358 C1, B64G 1/22), which contains a transition compartment for docking with the last stage of the rocket, an adapter for attaching satellites and a head fairing, while the spacecraft are attached to the adapter on the side.

The disadvantage of this technical solution is the presence of an additional adapter for mounting satellites, which reduces the maximum mass of spacecraft docked to it due to its own mass.

A known layout method, the essence of which is disclosed in the materials of patent RU 2156212 C2, B64G 1/10, 1/22, “Device for placing several satellites on a launch vehicle”, containing a central rack mounted on the launch vehicle and having many identical seats , a plurality of identical docking elements, each of which is intended for fixing one of the plurality of satellites at an appropriate seat, a removable fastening means and a fastening-uncoupling means by which any of the satellites can yt fastened with the possibility of separation from the corresponding managed docking element.

The disadvantages of this technical solution are the need to manufacture additional devices (central rack and seats) to ensure the fixation of the payload, which entails a decrease in the mass of the output cargo in proportion to the mass of the proposed transition device, as well as a side way of attaching spacecraft to the central rack, which imposes additional restrictions on the power circuit of the spacecraft, unnecessarily increasing its mass.

The closest in technical essence to the proposed method of layout of the payload and device for its implementation is the "Method of launching artificial satellites as the main and associated payloads in the geostationary orbit and device for its implementation" (RU 2254265 C2, B64G 1/00, 1 / 10), which consists in the fact that the payload consists of two spacecraft, and the spacecraft are sequentially mounted on a launch vehicle, starting from the bottom. In this case, the main payload in the form of one or more spacecraft is installed through the separation device on the body of the specified lower spacecraft. The housing of the latter combines its functions with the functions of the power element of the adapter to set the main payload. This layout method was taken as a prototype.

The disadvantage of this arrangement method is the use as a power element, transferring the load from the upper spacecraft to the adapter (or transition system) of the launch vehicle, the lower spacecraft body, which entails an increase in the mass of the body elements associated with the need to increase its strength and rigidity .

The applicant in the process of information retrieval did not identify analogues that are close to the claimed device in the aggregate of essential features and technical nature.

The objective of the invention is to minimize the mass cost of introducing additional spacecraft into the payload, increase the efficiency of using the volume under the head fairing of the launch vehicle, and reduce the cost of launching spacecraft into orbit.

The problem is solved by the method of layout of the payload, which consists in the fact that the payload is installed on the launch vehicle, which includes at least two spacecraft. For the mutual placement of spacecraft in the payload and securing the payload on the launch vehicle, a device for implementing the method of arranging the payload is included as a power structure of the spacecraft hull. The claimed device is made in the form of a shared power tube, consisting of several parts (according to the number of spacecraft in the payload), each of which performs the functions of the power structure of the hull of the corresponding spacecraft. The spacecraft is assembled around the corresponding parts of the shared power tube at the manufacturer, the spacecraft are integrated into a single payload, the space head part of the integrated payload and the head fairing is assembled, and the space head is set to its regular position on the launch vehicle.

The shared power tube performs the functions of a single transitional device for all spacecraft constituting the payload, providing the relative position of the spacecraft under the head fairing of the launch vehicle and transferring the weight and starting loads from the spacecraft to the adapter (or transition system) of the launch vehicle, and the ability of the power pipe to be divided into several parts (for example, using the built-in separation device) allows you to divide the payload into separate space hardware devices after putting it into orbit. This technical solution allows to reduce the number of structural elements of the spacecraft that accept launch loads, to reduce the weight of the structure of panels for on-board equipment due to a significant mitigation of the stiffness requirements imposed on them, which increases the maximum permissible payload mass, increases the net volume under the head fairing and reduces the cost launching spacecraft into orbit through the use of one rocket to launch several spacecraft.

The technical result achieved is to minimize the cost of mass for introducing additional spacecraft into the payload by using a shared power tube, which in assembled form is a single structure for both the main and at least one additional spacecraft; increasing the efficiency of using the volume under the head fairing of the launch vehicle by placing additional spacecraft under the head fairing; reducing the cost of launching spacecraft into orbit through the use of one launch vehicle for the simultaneous launch of several spacecraft.

The invention is illustrated by drawings, which do not cover and, moreover, do not limit the entire scope of the claims of this technical solution, but are only illustrative materials of a particular case of execution:

In FIG. Figure 1 shows the layout of two spacecraft under the head fairing of the launch vehicle using a shared power tube (longitudinal section).

In FIG. 2 shows a diagram of the implementation of the method of assembling the payload: a - assembly of spacecraft around the corresponding parts of the shared power pipe at the manufacturer; b - integration of spacecraft into a single payload; c - assembly of the space head part as part of the integrated payload and head fairing and its installation in a regular place on the launch vehicle.

The method of layout of the payload, which includes one main and at least one additional spacecraft, is as follows. For placement under the head fairing 1, in addition to the main spacecraft 2, at least one additional 3, it is necessary to arrange them coaxially with the launch vehicle and sequentially along the longitudinal axis of the launch vehicle, and also ensure the transfer of weight and launch loads from all spacecraft 2, 3 on the adapter (or transition system) 4 launch vehicles 7. It is proposed for these purposes to use a shared power pipe 5, mounted coaxially with the launch vehicle and serving to build at least one additional spacecraft 3 as part of the payload relative to the main spacecraft, as well as for the perception of loads from spacecraft 2, 3. At the same time, spacecraft 2, 3 are arranged around the power tube 5, as if covering it. Thus, the power tube 5, in addition to the transition device for fixing spacecraft 2, 3 on the adapter (or transition system) 4 of the launch vehicle 7, serves as the basis for the power circuit of each spacecraft.

A device for implementing the method of assembling the payload, made in the form of a shared power tube 5 for simultaneously launching at least two spacecraft 2, 3 with one launch vehicle 7. The power tube 5 is equipped with at least two separation devices 6, known from the prior art, used to separating the payload from the launch vehicle and separating the payload after putting it into orbit. Separation device 6 must be designed in such a way as to ensure guaranteed separation of the payload in orbit, on the one hand, and, on the other hand, to maintain the stiffness and strength characteristics of the shared power pipe 5 at the stage of putting it into orbit.

In order to ensure the manufacturability of spacecraft assembly, it is proposed to divide the shared power tube into parts, according to the number of spacecraft in the payload, and to assemble each spacecraft around its part of the shared power tube.

In this case, the height of each part of the shared power tube can be selected individually, according to the dimensions of the respective spacecraft, in such a way as to ensure the mutual placement of spacecraft as part of the payload, taking into account the reserves to guarantee non-collision of spacecraft.

In order to optimize the mass of the structure, parts of the shared power pipe can be an isogrid mesh structure, for example, described in patent RU 2392122 C1.

To ensure the strength characteristics of the shared power tube, the cross-sectional area of its various parts can vary in accordance with the following regularity: the part of the shared power tube that receives the load from all spacecraft that make up the payload, that is, the part one end of which is attached to the adapter (or transition system) of the launch vehicle, must have a maximum cross-sectional area, and that part of the shared pipe that receives the load from only one space one unit, that is the part that is in the starting position of the payload is the top, may have a minimum cross-sectional area.

The device operates as follows: spacecraft 2, 3 are assembled at the factory each around its part of the shared power pipe 5. The separated power pipe 5 with the spacecraft 2, 3 attached to it is assembled using, for example, the separation device 6 into a single construct in the technical complex at the launch site and assembled is installed on the adapter (or transition system) of the launch vehicle. At the orbital site, the shared power tube receives and transfers the effects from all spacecraft that are part of the payload to the adapter (or transition system) 4 of the launch vehicle 7 via separation devices 6. After the payload is brought to the target orbit, the separation devices provide shockless separation of the spacecraft that make up the payload.

Claims (5)

1. The method of arranging the payload, which consists in the fact that the payload is installed on the launch vehicle, including at least two spacecraft, characterized in that for the mutual placement of spacecraft in the payload and fixing the payload on the launch vehicle in As the power structure of the hull, the spacecraft include a device for implementing the method of assembling the payload, made in the form of a shared power pipe, consisting of several parts (according to payload spacecraft), each of which performs the power structure of the hull of the corresponding spacecraft, assemble spacecraft around the corresponding parts of the shared power tube at the factory, integrate spacecraft into a single payload, assemble the space head part of the integrated payload load and head fairing, set the space head to a regular place on the launch vehicle. 2. A device for implementing the method of layout of the payload, which includes at least two spacecraft, made in the form of a shared power tube, consisting of several parts (according to the number of spacecraft in the payload), each of which performs the functions of the power structure of the corresponding spacecraft apparatus. 3. The device according to claim 2, characterized in that the height of the parts of the shared power tube for each spacecraft is selected individually, according to the height of each spacecraft. 4. The device according to p. 2 or 3, characterized in that the design of the parts of the shared power pipe is an isogrid mesh structure. 5. The device according to p. 2, or 3, or 4, characterized in that the cross-sectional area of the various parts of the shared power pipe is the greater, the closer they are to the adapter (or transition system) of the launch vehicle, while within the same part shared power pipe cross-sectional area constant.

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