RU201366U1 - Parabolic transformable torus reflector - Google Patents

Abstract

The utility model relates to the field of space technology, in particular to the design of transformable reflectors. The technical result of the utility model is the creation of a reflector design with a low specific gravity and simple execution of a mechanical opening device, increased reliability and rigidity of the structure. The problem is solved due to the fact that the proposed folding method design provides increased reliability (absence of a large number of rim segments), required overall dimensions in the folded position, ease of installation of the reflector on the spacecraft and smooth transfer of the reflector to the transport position without additional loads from the synchronization system.

Description

The utility model relates to the field of space technology, in particular, to the design of transformable reflectors. A patent is known for a parabolic unfolding antenna (US 2015/0352022 A1), the transformable structure of which includes a mesh cloth attached to folding spokes, an irradiator and a counter-reflector. The counterreflector was installed according to the Cassegrand scheme. The main disadvantages of this device are the presence of a shipping container, which increases the mass of the launched satellite, the deployment of the webbing occurs by opening the spokes after they are withdrawn from the transport container, which increases the likelihood of the network webbing catching on the antenna elements.

Also known is the patent for a deployable large-sized space reflector (RU 2442249 C1, IPC H01Q 15/16, B64G 1/22). The deployable large-sized space reflector contains a central unit, a force ring formed by horizontal folding load-bearing power rod elements and vertical load-bearing power struts connected to the support petals and intermediate flexible support lobes, a cable-block deployment system interacting with an opening (folding) drive, a power ring and a central a node, a radio-reflecting surface made of a set-cloth, fixed on the supporting petals on the rod elements that set the profile of the working surface of the reflector.

The disadvantages of this device include: a high specific gravity of the structure for use on small satellites, the complexity of the mechanical device for opening the reflector, an increased probability of mesh mesh of the reflector, an increased probability of reducing the accuracy of the reflective surface of the reflector due to the use of flexible elements.

As the closest analogue - a prototype, a transformable parabolic antenna for space purposes was chosen (Z.A. Kazantsev. The design of a transformable parabolic antenna for space purposes // Bulletin of the Siberian State Aerospace University named after academician MF Reshetnev. 2016. V. 17, No. 3. P . 691-701.).

The design of a transformable parabolic antenna for space purposes consists of a transformable torus rim of the reflector, a reflective cloth fixed to the rim, a mechanism for disclosing the reflector (hinge units with spring drives), an electromechanical drive for regulating the speed of disclosing the rim of the reflector, a system for tensioning the reflecting cloth, and a system for synchronizing the sectors of the rim.

The main disadvantages of the prototype are: low reliability of the reflector design due to the introduction of a large number of moving mechanical elements (hinge nodes), which increases the likelihood of failure of the opening mechanism. This method of folding the antenna also leads to a decrease in the reliability of the antenna design.

The technical problem of the utility model is the elimination of the above disadvantages of the prototype.

For the developed design of the reflector and for the closest prototype of a transformable parabolic antenna for space purposes, the main common essential features have been identified, such as: a transformable torus rim of a reflector, a reflective cloth fixed on the rim, a mechanism for disclosing the reflector (hinged nodes with spring drives), an electromechanical drive for speed control disclosure of the reflector rim, the system of tension of the reflective cloth.

The indicated technical problem is solved due to the following design of the reflector power structure.

The reflector contains the following features that distinguish it from the prototype: the transformable hollow rim of the reflector is a hollow torus with an elliptical or circular cross-section, consisting of two segments, a mechanical device for opening and closing the reflector rim (hinged joints containing torsion springs, with which the reflector is transferred to the working position ). The opening is carried out by spring drives, which are part of the hinge units, while the opening speed is regulated by an electromechanical drive. There is no synchronization system, since the spring drives ensure the simultaneous opening of the indicated number of rim segments.

In addition, the proposed method of folding the structure provides the required overall dimensions in the folded position, ease of installation of the reflector on the spacecraft and smooth transfer of the reflector to the transport position without additional loads from the synchronization system. In order to avoid shock loads and damage to the reflecting part during the transfer of the reflector from the transport position to the working position, an electromechanical drive (EMF) is used, which operates in the containment mode.

The technical essence and principle of operation of the proposed device are illustrated by drawings, which show:

in fig. 1 is a general view of a parabolic transformable torus reflector in working position;

in fig. 2 is a general view of the rim of the parabolic transformable torus reflector in the transport position;

in fig. 3 is a top view of the rim of the parabolic transformable torus reflector in the transport position;

in fig. 4 is a general view of a parabolic transformable torus reflector in a folded position;

in fig. 5 is a general view of the articulated connection of the reflector rim in the folded position;

in fig. 6 is a general view of the reflective web tensioning system.

The above figures show the design of the proposed reflector using the following elements: 1 - radio-reflecting parabolic surface (reflecting cloth); 2 - transformable rim; 3 - a mechanical device for opening and closing the reflector rim, which is a hinge joint having a rotational degree of freedom relative to 4 - the axis of rotation of the hinge assembly, into which 5 - an electromechanical drive is installed to control the speed of opening the rim; 6 - three-layer honeycomb spacers, on which the locks are located in 6.1 - mounting locations of the locking locks in the working position; the system of tension of the reflective canvas, including: 7 - cables of the system of tension of the reflective canvas; 8 - rollers of the tensioning system of the reflective cloth.

The proposed device for the construction of a parabolic transformable torus reflector, shown in the figures, consists of the following elements:

- direct focus radio-reflecting parabolic surface (reflecting cloth) 1, formed by a paraboloid cut, which is fixed on the transformable rim (Fig. 1);

- a transformable hollow torus rim of the reflector 2, for example, made of composite carbon fiber, the shape of which is determined by the requirements for geometry

reflective surface and dimensions when folded. At the ends of the segments of the torus rim, three-layer torus spacers 6 are installed;

- a mechanical device for opening and closing the reflector rim, which is a hinge joint 3, having a rotational degree of freedom relative to their axes of rotation 4 and connecting adjacent torus segments. The reflector is transferred from the transport position to the working position due to the action of the springs located in the control box. The reflector is brought to the working position by rotating one or both segments at the same time relative to the rotation axes of the hinge nodes. The locking of the reflector in the working position is carried out with the help of locking locks installed in the seats 6.1 on three-layer honeycomb spacers 6;

- an electromechanical drive operating in a restraining mode and providing a smooth opening of the reflector.

- the system of tension of the reflective web, consisting of cables 7, which in the working position of the reflector with the help of their own tension create a tension force of the web in the radial direction, and rollers 8.

The above-described construction of a parabolic transformable torus reflector is transferred from the starting position to the working one as follows:

After launching the target satellite into orbit, the reflector is released from being fixed in the transport position, power is supplied to the electromechanical drive, the reflector is transferred from the transport position to the working position by means of torsion springs installed in the control box. The instantaneous deployment of the reflector with shock loads is prevented by the operation of the EMF operating in containment mode. The radio-reflecting parabolic surface (reflective canvas) 1 is stretched using a system of tensioning the reflective canvas (cables 7 with rollers 8). In the transport position, the structure is held by means of locks located on three-layer honeycomb spacers 6. The locks connect the three-layer honeycomb spacers of opposite segments, ensuring the rigidity of the structure. The number of locks is chosen in such a way as to limit the movement of three-layer honeycomb spacers along all degrees of freedom.

Thus, the problem of low reliability is solved by applying a new method of folding the structure of a parabolic transformable torus reflector, a relatively simple mechanical device for opening and closing

(reduction of the number of power segments of the rim) of the reflector rim.

The technical result of the utility model is the creation of a reflector design with increased reliability.

Claims (1)

A parabolic transformable torus reflector, consisting of a transformable torus rim of the reflector, a reflective cloth fixed on the rim, a mechanism for opening the reflector, an electromechanical drive for regulating the speed of opening the rim of the reflector, a system for tensioning the reflector cloth, characterized in that the transformable rim of the reflector is a hollow torus consisting of of two segments, made with the possibility of bringing the reflector to the working position and with the possibility of turning one or both segments at the same time relative to the axes of rotation of the hinge assemblies, and the spring drives are made with the possibility of simultaneously opening the indicated number of rim segments.

Images