RU2263062C1 - Container - Google Patents

Abstract

FIELD: packing equipment, particularly large containers.

SUBSTANCE: container has base with support device for container fastening to spaceship, lid installed on the base, electrical connectors to provide communication with the spaceship and connected to support device and linked with land-based testing equipment secured to base through electric connectors. Leverage is installed on the base and pivotally connected with support device. Support device includes docking adapter and frame pivotally connected one to another and provided with relative position fixers. Units for spaceship connection and electrical connectors to establish communication with it are installed on docking adapter. Leverage includes lower and upper rods connected in series through hinges. Upper rods are pivotally connected with frame of support device, lower rods are pivotally attached to the base. Rotary units are installed on the base so that rotary units pay cooperate with fixing sockets formed in lower rods. Lower rods are provided with fixers, which may cooperate with fixing sockets of upper rods. Rotation limiters are secured to the base and arranged between lower rods so that rotation limiters may cooperate with lower rods installed in vertical positions. Docking adapter of support device is connected to the base by releasable fixers.

EFFECT: extended range of technical capabilities and increased operational performance of the container.

3 cl, 8 dwg

Description

The present invention relates to containers for accommodating products of special equipment, and more specifically for accommodating spacecraft during transportation, storage and ground preparation.

Known container for accommodating the adapter of spacecraft, containing a base with a support device for mounting the adapter and a cover (see, for example, 17S18K.9401-000SB, Design Bureau "Flight", 2001).

A container for a spacecraft is also known, containing a base with a supporting device for mounting the spacecraft and a lid mounted on it, electrical connectors for communicating with the spacecraft, mounted on a supporting device and connected by a cable with transitional electrical connectors for communication with ground-based testing equipment, mounted on the base ( see, for example, the Small Spacecraft Sterkh of the Nadezhda-M space system, conceptual design, book 3, p. 190, Design Bureau Flight, 1999).

This container has several disadvantages, namely:

- when the spacecraft is in the container, it is impossible to carry out the full cycle of its autonomous preparation, namely tilting the spacecraft, testing the mechanical systems of the spacecraft installed in the lower part of the latter for disclosure;

- difficult access for maintenance personnel to the elements located in the lower part of the spacecraft installed on the basis of the container;

- when installing the container base directly on the floor of the structure, in addition to the inconvenience of servicing the lower part of the spacecraft, pollution of the latter is also possible.

The objective (goal) of the present invention is to expand the functionality (the ability to tilt the spacecraft, test the mechanical systems of the spacecraft installed in its lower part, to open when the spacecraft is in the container, which leads to a reduction in the range of used ground processing equipment and, accordingly to reduce the time of its deployment) and increase operational performance (providing convenient access to the element Am of the spacecraft in the lower part of the latter when the spacecraft is in the container, etc.) of the container.

The task (goal) is achieved in that a lever mechanism is installed on the container base, connected to the supporting device by means of hinges, and the cable is wound on a spring-loaded receiving drum fixed on the base. The supporting device is made up of a docking adapter and a frame, interconnected by hinges and provided with clamps of their relative position. On the docking adapter, nodes for mounting the spacecraft and electrical connectors for communication with the latter are installed. The lever mechanism is made up of lower and upper rods connected by hinges. The upper rods are articulated to the support device, and the lower rods are articulated to the base. On the basis of the rotary stops are installed with the possibility of their interaction with the locking sockets of the lower rods. On the lower rods, latches are installed with the possibility of their interaction with the locking sockets of the upper rods. On the basis of fixed rotation limiters located between the lower rods with the possibility of interaction with the lower rods with the vertical position of the latter. The docking adapter of the support device is attached to the base by means of detachable latches. On the base, horizontal guide rods are fixed, onto which balancing weights connected with the base are mounted with the possibility of movement by means of latches of their relative position.

The proposed device is illustrated in figures 1-8.

Figure 1 presents a General view of the container in transport position.

Figure 2 shows a General view of the container (without lid) with the spacecraft with the lever mechanism lowered.

Figure 3 shows a General view of the container (without lid) with the lever raised when the spacecraft is in a vertical position.

Figure 4 presents a General view of the container (without lid) with the lever raised when the spacecraft is in a horizontal position.

Figure 5 shows a General view of the container in transport position without a spacecraft.

Figure 6 shows a section aa according to figure 4.

Figure 7 presents a section bB according to figure 4.

On Fig shows a section bb according to figure 3.

The container contains a base 1 (Fig. 1) with a supporting device 2 (Fig. 2) for fastening the spacecraft 3 and a cover 4 (Fig. 1) mounted on the base 1, electrical connectors 5 (Fig. 2) for communication with the spacecraft 3, fixed on the supporting device 2 and connected by a cable 6 with transitional electrical connectors 7 for communication with ground-based test equipment (not shown in FIG. certainly), fixed on the base 1. On the base 1, a lever mechanism 8 (FIG. 2) is connected to the supporting device 2 by means of hinges 9. Cable 6 is wound on a spring a receiving drum 10 (FIG. 2), mounted on the base 1. The supporting device 2 consists of a docking adapter 11 (FIG. 3) and a frame 12 interconnected by hinges 13 and provided with latches of their relative position 14 (FIG. 3) and 15 (Fig. 4). On the docking adapter 11 installed nodes 16 (figure 2) for mounting the spacecraft 3 and electrical connectors 5 for communication with him. The lever mechanism 8 consists of (four) lower 17 (Fig. 3) and (four) upper 18 rods connected in series by hinges 19. The upper rods 18 are connected to the frame 12 of the supporting device 2 by means of hinges 9. The lower rods 17 are connected to the base 1 by means of hinges 20 (FIG. 3). On the basis of 1 mounted rotary stops 21 (Fig.3, 6) with the possibility of their interaction with the locking sockets 22 (Fig.6) of the lower rods 17. On the lower rods 17 mounted latches 23 (Fig.3, 8) with the possibility of their interaction with the fixing sockets 24 (Fig. 8) of the upper rods 18. The docking adapter 11 of the supporting device 2 is fixed to the base 1 by means of detachable latches 25 (Figs. 2, 5). On the base 1, horizontal guide rods 26 are fixed (FIG. 1), on which the balancing weights 28 are connected with slots 27 (FIG. 7), connected with the base 1 by means of the latches of their relative positions 29 (FIG. 1) and 30 (FIG. .4). Also on the basis of 1 between the lower rods 17 fixed rotation limiters 31 (figure 3) with the possibility of interaction of the latter with the lower rods 17.

The proposed device operates as follows.

At the factory, the spacecraft 3 by a crane (not shown conventionally in Fig.) Is mounted (Fig. 2) onto the docking adapter 11 of the supporting device 2 and fixed to it by means of nodes 16. When the spacecraft 3 is installed by moving (moving) the latter, the electrical connectors are docked 32 (FIG. 2) of the spacecraft 3 with electrical connectors 5 mounted on the docking adapter 11 of the supporting device 2. Then, with a crane (not shown conventionally in FIG.), A cover 4 is mounted on the base 1 and attached to the base 1 (elements of the Lenia FIG. conditionally not shown). Thus, the container is prepared (Fig. 1) for loading onto a vehicle and subsequent transportation to the spaceport.

After the container arrives at the spaceport, the container with a crane (not shown conditionally in Fig. 1) is installed (Fig. 1) in the assembly and test building at the site of the autonomous preparation of the spacecraft 3. Then, the lid 4 is unfastened (the fastening elements in Fig. Are not shown conventionally) from the base 1 and is dismantled from the base 1 using a crane (not shown conventionally in FIG.).

After that, the docking adapter 11 of the support device 2 is detached from the base 1 (detachable latches 25 are removed). The spacecraft 3 by a crane (Fig. Conditionally not shown) moves up (Fig.3). In this case, together with the spacecraft 3, the supporting device 2 rises and pulls the lever mechanism 8. The lower 17 and upper 18 rods of the lever mechanism 8 tend to occupy a vertical position. At the same time, the cable 6, docked with electrical connectors 5 for communication with the spacecraft 3, is unwound from the spring-loaded receiving drum 10, mounted on the base 1. After verticalization of the lower 17 and upper 18 rods of the lever mechanism 8, the rotary stops 21 are installed (Fig. 6) into the fixing the nests 22 of the lower rods 17. Then, the latches 23 mounted on the lower rods 17 are inserted (Fig. 8) into the fixing sockets 24 of the upper rods 18. The crane (not shown conditionally in Fig.) is detached from the spacecraft 3. Thus, the lever mechanism 8 with the spacecraft 3 mounted on the docking adapter 11 of the support device 2, it is moved to the upper position and locked (Fig. 3) in this position. After that, the transitional electrical connectors 7, mounted on the base 1, are docked with ground test equipment (not shown conditionally in Fig.).

In this position, by lifting the spacecraft 3 from the floor of the structure to a height of about 1-1.5 m, convenient access for maintenance personnel to the bottom of the spacecraft 3 is ensured, the likelihood of pollution of the spacecraft 3 is reduced (the main amount of polluting particles is deposited on the floor of the structure) and its mechanical damage, and it also becomes possible to test mechanical systems (not shown conditionally in FIG.) located at the bottom of the spacecraft for disclosure.

If necessary, the tilting of the spacecraft 3 for testing its mechanical systems (not shown in FIG. Of course) to open or supply the spacecraft 3 to dock with the launch vehicle (not shown conventionally in FIG.), The latches 14 of the relative position of the docking adapter 11 are dismantled and frame 12 of the supporting device 2. Using a crane (not shown conventionally in FIG.), the spacecraft 3 is moved to a horizontal position (FIG. 4). In this case, the docking adapter 11 of the support device 2 is rotated on hinges 13 and is locked (Fig. 4) by the latches 15.

The stability of the container when tilting the spacecraft 3 is provided as follows. Before tilting the spacecraft 3, the latches of the relative position 29 are removed to the horizontal position. The balancing weights 28 along the guide rods 26 are moved in the opposite direction to the tilting of the spacecraft 3 and are locked in this position (Fig. 3) by the latches of the mutual position 30.

It should be noted that with insufficient displacement of the center of mass from the movement of balancing weights 28, the stability of the container with the spacecraft 3 when tilting the latter to a horizontal position can be ensured:

- either by fastening the container to the place of work;

or installation on the basis of 1 rotary platform (not shown conditionally in FIG.), on which a counterweight is installed before tilting the spacecraft 3 (not shown conditionally in FIG.).

After carrying out the necessary operations with the spacecraft 3 in a horizontal position (for example, testing its mechanical systems (not shown conditionally in FIG.) For disclosure), the spacecraft 3 is hung out on a crane (not shown conditionally in FIG.). The spacecraft 3 is undocked from the nodes 16 of the docking adapter 11 of the supporting device 2. By horizontal movement of the crane (not shown conventionally in Fig.), The spacecraft 3 is diverted from the docking adapter 11. In this case, the connectors 32 of the spacecraft 3 come out of the electrical connectors 5 of the docking adapter 11. Space apparatus 3 by a crane (not shown conditionally in FIG.) is transferred to the docking zone with a launch vehicle (not shown conditionally in FIG.).

After that, the latches 15 are dismantled, the docking adapter 11 of the support device 2 is rotated (manually) on hinges 13 and is attached to the frame 12 by means of the latches 14. In this case, the cable 6 is wound on a spring-loaded receiving drum 10.

The docking adapter 11 of the support device 2 is attached (fasteners in Fig. Not shown conventionally) to a crane (not shown in Fig.). The latches 23 mounted on the lower rods 17 are removed from the fixing sockets 24 of the upper rods 18 and are fastened (fasteners are not shown conventionally in FIG.) To the lower rods 17. The pivoting stops 21 are removed from the fixing sockets 22 of the lower rods 17 and are fastened (fastening elements in Fig. conditionally not shown) to the base 1. By moving the crane (in Fig. conditionally not shown) down, the supporting device 2 also moves down until the racks 33 (Fig. 5) of the frame 12 are supported on the base 1. In this case, the lever mechanism 8 is folded. The folding of the upper 18 and lower rods 17 of the lever mechanism 8 inward (towards the spring-loaded receiving drum 10) is thereby eliminated by installing on the base 1 between the lower rods 17 the rotation limiters 31 with the possibility of interaction of the latter with the lower rods 17 in their vertical position.

After that, the crane (conditionally not shown in Fig.) Is detached from the docking adapter 11 of the support device 2, and the docking adapter 11 is attached to the base 1 by means of detachable latches 25 (Fig. 5). Then, the latches of the relative position 30 are dismantled. The balancing weights 28 along the guide rods 26 are moved to the initial position and locked in this position (Fig. 5) by the latches of the mutual position 29. After installing the lid 4 on the base 1, the container is prepared (Fig. 5) for transportation to unladen to the manufacturer.

Thus, the proposed device has significant differences from previously known containers and allows you to expand their functionality and improve their operational characteristics.

Claims (3)

1. A container containing a base with a support device for mounting the spacecraft, a lid mounted on the base, electrical connectors for communicating with the spacecraft, mounted on the support device and connected by a cable and transitional electrical connectors for communication with ground-based testing equipment fixed on the base, characterized in that on the basis of the installed lever mechanism associated with the supporting device by means of hinges, while the supporting device consists of a docking adapter and a frame connected interconnected by hinges and provided with clamps of their relative position, and on the docking adapter mounted nodes for mounting the spacecraft and electrical connectors for communication with it, and the linkage mechanism consists of lower and upper rods sequentially interconnected by hinges, while the upper rods are pivotally connected with the frame of the support device, and the lower rods are pivotally connected to the base, and rotary stops are installed on the base with the possibility of their interaction with the locking sockets of the lower rods, and the lower rods are equipped with latches with the possibility of their interaction with the locking sockets of the upper rods, while on the base there are fixed rotation limiters placed between the lower rods with the possibility of interaction with the lower rods in the vertical position of the latter, and the docking adapter of the supporting device is attached to the base via detachable latches. 2. The container according to claim 1, characterized in that the cable is wound on a spring-loaded receiving drum mounted on the base. 3. The container according to claim 1, characterized in that the horizontal guide rods are fixed on the base, on which balancing weights connected with the base are mounted with the possibility of movement by means of the latches of their relative position.

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