RU199885U1 - FIXING UNIT OF STRUCTURAL ELEMENTS AND EQUIPMENT OF THE SPACE VEHICLE - Google Patents

Abstract

The utility model relates to the space industry and is intended for fastening structural elements and equipment of a spacecraft (SC) to a power mesh structure (SSC) made of polymer composite materials. The tasks to be solved by the claimed technical solution are to improve the design of the attachment point in terms of increasing reliability the work of the attachment point, as well as the expansion of functionality. The problem is solved by the fact that the attachment point of the spacecraft structure elements and equipment consists of connected trapezoidal fastening and support pads and installed symmetrically on both sides on the SSK elements, installed without support on the annular and longitudinal elements SSK, while the configuration of the overlays provides positioning and fixation with an emphasis on the spiral elements of the SSK. In addition, a landing hole is made on the inner side of the support plate, which forms a fixation point for the spacecraft structure and equipment, and the fixing plate is made with a lug in the form of a trapezoidal prism, repeating the geometric parameters of the SCS spiral elements, providing the installation plane and the fixation point of the spacecraft structure and equipment ... It is recommended to use pads made of metal, fastened to each other with glue and metal fasteners. The technical results of the claimed utility model are: - the ability to install a fastening unit for spacecraft structural elements and equipment without relying on circular and spiral elements of the SSK; - high reliability of the unit fastening; - the possibility of installing the attachment point for the spacecraft structure elements and equipment on the SCS of any configuration with spiral elements.

Description

The utility model relates to the space industry and is intended for fastening structural elements and equipment of a spacecraft (SC) to a power mesh structure (SSC) made of polymer composite materials (PCM).

A device and a method of asymmetric fastening of parts made of carbon and metal with strips (patent RU No. 2352497 C1) is known from the existing state of the art, in which the strip and a counter strip provide strong fastening of structural elements placed between the strip and a counter strip, while the counter strip has less than pad number of attachment points. The disadvantages of the known design are:

- low degree of manufacturability;

- low reliability of fasteners;

- fastening of structural elements is possible only on flat surfaces.

Also known is a unit for securing equipment to a power mesh structure made of polymer composite materials (patent RU No. 2535780 C2), in which the unit for securing equipment consists of fastening and support pads fastened to the elements of the SSK. The overlays are made with the angle of inclination of the guiding faces, which coincides with the angle of inclination of the spiral elements of the SSK. The support plate rests against the crosshairs of the CCK elements and serves to fasten the fastening plate, which, in turn, creates a plane and a fixation point for installing the equipment. The disadvantages of the known design are:

- limiting the installation of the fixing unit only on two spiral and one annular SSK element;

- machining of the clamping unit can be performed only radially;

- low reliability of fasteners;

- low reliability of the unit for loaded elements.

The closest to the claimed technical solution in terms of purpose and a set of essential features is the attachment point for the spacecraft structure elements (patent RU No. 190988 U1), in which the attachment point for the spacecraft structure elements consists of connected fastening and support pads and installed symmetrically on both sides on the SSK elements in this case, the mounting plate is made with a plane and a fixation point for the spacecraft structure elements. On the mating surfaces of the mounting and support pads, grooves are made with the geometric parameters of the SSC elements at the installation sites, in addition, a boss with chamfers and a landing hole is located on the mounting pad, forming a plane and a fixation point for the spacecraft structure elements. This technical solution was taken as a prototype of a utility model. The disadvantages of the known design are:

- limiting the installation of the fixing unit only in the zone of the simultaneous location of the spiral, annular and a pair of longitudinal elements of the SSC;

- limiting the installation of the fixing unit only in the SSK with annular and longitudinal elements;

- low reliability of fasteners;

- low reliability of the unit for loaded elements.

The tasks to be solved by the claimed technical solution are to improve the design of the fastening unit in terms of increasing the reliability of the fastening unit, as well as expanding the functionality.

The task is solved by the fact that the attachment point of the spacecraft structure elements and equipment consists of connected trapezoidal fastening and support pads and mounted symmetrically on both sides on the SSC elements, installed without support on the circular and longitudinal SSC elements, while the configuration of the pads provides positioning and fixation with emphasis on the spiral elements of the SSK. In addition, a landing hole is made on the inner side of the support plate, which forms a fixation point for the spacecraft structure and equipment, and the fixing plate is made with a lug in the form of a trapezoidal prism, repeating the geometric parameters of the SCS spiral elements, providing the installation plane and the fixation point of the spacecraft structure and equipment ... It is recommended to use pads made of metal, fastened together with glue and metal fasteners.

The technical results of the claimed utility model are:

- the possibility of installing the attachment point for spacecraft structure elements and equipment without support on the circular and spiral elements of the SCS;

- high reliability of the fastening unit;

- Possibility to install the attachment point for spacecraft structure elements and equipment on the SCS of any configuration with spiral elements.

The essence of the utility model is illustrated by the drawings shown in FIG. 1-9:

- fig. 1 - general view of the SSC with the attachment point for the spacecraft structural elements and equipment;

- fig. 2, 5, 6, 7 - options for installing the attachment point for spacecraft structural elements and equipment;

- fig. 3 - sec. A-A shown in FIG. 2;

- fig. 4 - sec. B-B shown in FIG. 2;

- fig. 9 - sec. D-D shown in FIG. 7;

- fig. 8 - sec. B-B shown in FIG. 7.

The attachment unit for spacecraft structure elements and equipment is a fastening pad 1, a support pad 2 and fasteners 3 connecting the fastening pad 1 and a support pad 2 to each other. The fastening and support pads 1, 2 are made in the form of plates, are attached symmetrically on both sides to the elements of the CCK 4 and are shaped with the same contour in the form of a trapezoid. On the mating inner surfaces of the fastening pad 1 and the support pad 2 there are grooves, the geometric parameters of which repeat the geometric parameters of the SSK 4 elements, which provides positioning, fixation and additional emphasis on the spiral elements of the SSK 4. In the fastening pad 1 on the outside there are two smooth holes, and in the support plate 2 on the inner side there are two threaded holes necessary for fixing the fastening plate 1 with the support plate 2 to the CCK 4 using fastening elements 3, providing an unambiguous place in space. The fastening pad 1 on the outside has a trapezoidal boss, the edges of which are conjugated with the radius, and the geometric parameters repeat the geometric parameters of the CCK 4 elements, for machining (surface D) both radially and perpendicular to the normal to the CCK 4. In the boss 5 of the fastening strip 1 a smooth hole is made. After that, a coaxial threaded hole is made in the support strip 2 along the guide smooth hole of the fastening pad 1, which provides a fixation point for the structural elements and equipment of the spacecraft. On the inner surfaces of the linings, fasteners and on the CCK 4 elements at the points of contact, glue is applied, which ensures the elimination of gaps and additional fixation. General view of SSK 4 made of PCM with the attachment point for spacecraft structural elements and equipment is shown in Fig. 1.

The attachment point of the spacecraft structure elements and equipment has a universal shape, which allows its installation on the elements of the SSK 4 in various ways, shown in Fig. 2, 5-7, without support on the annular and longitudinal elements of the SSC of any configuration with spiral elements.

The fastening plate 1 is installed with an emphasis on the inner surface along the outer radius R1 CCK 4, the support strip 2 is installed with an emphasis on the inner surface along the inner R2 (Fig. 2, 3, 5), so that the boss 5 is located on the outside of the CCK 4. If the elements the spacecraft structure and equipment must be installed on the inner side of the SSK 4, then the fixing pad 1 is installed with an emphasis on the inner surface along the inner radius R2 of SSK 4, and the support pad 2, respectively, with an emphasis on the inner surface along the outer R1 (Fig. 6-8), and the boss 5 is located on the inner side of the CCK 4.

- Possibility to install the attachment point for spacecraft structure elements and equipment on the SCS of any configuration with spiral elements.

The essence of the utility model is illustrated by the drawings shown in FIG. 1-9:

- fig. 1 - general view of the SSC with the attachment point for the spacecraft structural elements and equipment;

- fig. 2, 5, 6, 7 - options for installing the attachment point for spacecraft structural elements and equipment;

- fig. 3 - sec. A-A shown in FIG. 2;

- fig. 4 - sec. B-B shown in FIG. 2;

- fig. 8 - sec. B-B shown in FIG. 7;

- fig. 9 - sec. D-D shown in FIG. 7.

The attachment unit for spacecraft structure elements and equipment is a fastening pad 1, a support pad 2 and fasteners 3 connecting the fastening pad 1 and a support pad 2 to each other. The fastening and support pads 1, 2 are made in the form of plates, are attached symmetrically on both sides to the elements of the CCK 4 and are shaped with the same contour in the form of a trapezoid. On the mating inner surfaces of the fastening pad 1 and the support pad 2 there are grooves, the geometric parameters of which repeat the geometric parameters of the SSK 4 elements, which provides positioning, fixation and additional emphasis on the spiral elements of the SSK 4. In the fastening pad 1 on the outside there are two smooth holes, and in the support plate 2 on the inner side there are two threaded holes necessary for fixing the fastening plate 1 with the support plate 2 to the CCK 4 using fastening elements 3, providing an unambiguous place in space. The fastening pad 1 on the outside has a trapezoidal boss, the edges of which are conjugated with the radius, and the geometric parameters repeat the geometric parameters of the CCK 4 elements, for machining (surface D) both radially and perpendicular to the normal to the CCK 4. In the boss 5 of the fastening strip 1 a smooth hole is made. After that, a coaxial threaded hole is made in the support strip 2 along the guide smooth hole of the fastening pad 1, which provides a fixation point for the structural elements and equipment of the spacecraft. On the inner surfaces of the linings, fasteners and on the CCK 4 elements at the points of contact, glue is applied, which ensures the elimination of gaps and additional fixation. General view of SSK 4 made of PCM with the attachment point for spacecraft structural elements and equipment is shown in Fig. 1.

Claims (4)

1. Attachment unit for structural elements and equipment of the spacecraft (SC), consisting of connected support and fastening pads and installed symmetrically on both sides on the elements of the power mesh structure (SSK), while grooves with geometric parameters are made on the mating surfaces of the mounting and support pads elements of SSK in the places of installation, in addition, a boss with chamfers and a landing hole is located on the fastening plate, forming a plane and a fixation point of the spacecraft structure elements, characterized in that the plates have a trapezoidal shape and are made with the possibility of installation on the spiral elements of the SSK, while the boss is made in the form of a trapezoidal prism, repeating the geometric parameters of the spiral elements of the SCC, the edges of which are conjugated with the radius. 2. The attachment unit according to claim 1, characterized in that the support plate is made with a fixation point for the spacecraft structural elements and equipment. 3. The attachment unit according to claim 1, characterized in that the mounting of the attachment unit is carried out without support on the circular and longitudinal elements of the SSK, and the configuration of the pads provides positioning and fixation with emphasis on the spiral elements of the SSK. 4. The attachment unit according to claim 1, characterized in that the mounting of the attachment unit can be performed on the SSC of any configuration having spiral elements.

Images