RU2581274C2 - Modular spacecraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering. Module spacecraft comprises the service system module, the first and second payload modules. The first payload module is arranged at the second one for it to take up the load transferred thereto from the first payload module. Spacecraft comprises the interfaces for power supply, data transfer and other signals and has the sufficient space for accommodation of the larger components: solar battery panels and antennas.

EFFECT: decreased weight, accelerated fabrication and ground experimental finishing.

3 cl, 4 dwg

Description

The invention relates to space technology and can be used to create spacecraft (SC) for various purposes.

A spacecraft typically consists of a service system module and a payload module. Service systems module (MSS) and payload module (MPN) are usually structurally different assemblies on which mounted components are located: antennas, solar panels, etc.

Currently, the development trends of space technology impose a number of requirements for the design of spacecraft. A constant increase in the number of target functions leads to an increase in the equipment that must be placed on the spacecraft.

Known KA, including the casing and antennas according to US patent US 20030057328 A1 dated 03/27/2003, in which the casing has a non-uniform cross section along the main axis of the apparatus. The heterogeneity of the spacecraft hull allows you to maximize the use of available volumes of the launch vehicle. However, MPN is a single design, which does not allow to produce and experience various payloads at the same time.

Closest to the claimed technical solution in terms of technical nature and the technical result achieved is a spacecraft (adopted as a prototype of the invention) protected by patent EP 19970121935, which includes many functionally independent modules assembled around a central structure, interfaces for power supply, interfaces for data transmission and other signals having enough space for laying large components.

The disadvantage of the prototype is that the use of a Central bearing structure increases the total mass of the spacecraft and reduces the possible size and volume of the zone of placement of the payload.

The objective of the invention is the introduction of a new architecture for the construction of the spacecraft, the use of which will contribute to the creation of lighter and more compact spacecraft, and will also reduce the time of production of the spacecraft, reduce the cost of manufacturing and ground experimental testing of the spacecraft.

The problem is solved due to the fact that the spacecraft containing modules of the spacecraft (SC), interfaces for providing power, interfaces for transmitting data and other signals, which has enough space for laying large components, additionally consists of a module of service systems, the first module useful load and the second module of the payload, and the second MPN is installed on the first MPN so that the starting load of the second MPN is transmitted to the first MPN and is perceived by it, thereby eliminating the need Axle use by the central structure.

The design of the MPN in the form of two or more structural assemblies allows you to simultaneously work with assemblies at the stages of ground-based satellite operation, which reduces the spacecraft fabrication time and the time it takes for the ground experimental spacecraft to be tested.

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. 1 shows an example of a spacecraft designed according to the proposed solution, in axonometric projection;

- in FIG. 2 shows a structural division of a spacecraft in accordance with the principles of the present invention;

- in FIG. 3 shows an embodiment of a spacecraft designed according to the proposed solution in axonometric projection;

- in FIG. 4 shows a structural division of a spacecraft in accordance with the principles of the present invention.

In FIG. 1, 2, a block-modular spacecraft is shown. The SC includes a service system module 1, a first payload module 2 and a second payload module 3. It should be noted that although in FIG. 1, 2, a spacecraft with two payload modules is shown, however, the present invention contemplates three or more payload modules.

Regardless of the number of payload modules 2, 3 used in the spacecraft layout, the payload modules can be placed in a vertical, longitudinal “tandem” configuration, as shown in FIG. 1. The term "tandem" used in this document means the orientation of the installed payload modules 2, 3 relative to the SC, when the SC is oriented in a vertical position relative to the Earth, while the modules of the payload 2, 3 are located along or coincide with the central longitudinal axis of the SC and are arranged one after another so that the payload module 3 rests on the payload module 2. Also, the spacecraft includes large-sized components: BS 4 panels and antennas 5.

In another embodiment, regardless of the number of payload modules 2, 3, 6 used in the spacecraft layout, the payload modules can be placed in a vertical, longitudinal “packet” configuration, as shown in FIG. 3, 4. The term “packet” used in this document means the orientation of the installed payload modules 3, 6 relative to the SC, when the SC is oriented in a vertical position relative to the Earth, while the modules of the payload 3, 6 are located along or coincide with the central longitudinal the axis of the spacecraft and are arranged in parallel so that the payload module 3 and the payload module 6 are based on the payload module 2. The spacecraft also includes large-sized components: BS 4 panels and antennas 5.

The proposed constructive solution is used as follows.

Ensuring the effective implementation of the target functions of the spacecraft is the goal of designing a new spacecraft. This goal can be achieved by solving design problems. The solution to these problems is carried out in the process of assembling the spacecraft. Traditionally, each spacecraft is considered unique with its purpose or mission. In general, a spacecraft can fulfill several targets, and various manufacturers can produce equipment for performing targets. In this case, it is advantageous to make several MPN in the form of independent structural assemblies and build the spacecraft according to the architecture proposed in the present invention.

Since the modules 1, 2, 3 of the spacecraft are separate structural assemblies, the work (assembly manufacturing, equipment installation, some testing) can be carried out in parallel, which reduces the overall production time of the spacecraft.

In this invention, it is assumed that the starting loads from the second MPN are perceived by the first MPN, which allows us to abandon the central power structure and thereby reduce the size of the spacecraft, due to the possibility of placing the equipment in place of the central bearing structure. The exclusion of the supporting structure will reduce the spacecraft mass or reserve it for the payload.

The technical result achieved is to reduce the mass of the spacecraft by eliminating the central structure. Reducing the time of manufacturing and conducting ground experimental testing is achieved by placing the target equipment in several modules of the payload and the implementation of these modules in the form of separate structural assemblies.

Thus, the claimed spacecraft construction architecture makes it possible to produce lighter and more compact spacecraft and reduce the spacecraft manufacturing time.

A spacecraft made in this way allows independent assembly and testing of spacecraft modules.

This will allow, while retaining the advantages of the prototype, to achieve a reduction in the spacecraft manufacturing time, lower costs for the production and ground operation of the spacecraft.

Claims (3)

1. A block-modular spacecraft containing modules of the spacecraft (SC), interfaces for supplying power, interfaces for transmitting data and other signals, having enough space for laying large components, characterized in that the SC includes a service system module, the first payload module and the second payload module (MPN), the second MPN being installed on the first MPN so that the starting load of the second MPN is transmitted to the first MPN and perceived by it. 2. The spacecraft according to claim 1, characterized in that the spacecraft can contain many payload modules. 3. The spacecraft according to claim 1 and 2, characterized in that in the presence of three or more MPNs, the second and subsequent MPNs can be installed in “packages”.

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