RU2362724C2 - Cross bar for docking of large space vehicle with carrier rocket equipped with supercaliber payload fairing - Google Patents

Abstract

FIELD: transportation, shipment of goods.

SUBSTANCE: said utility invention relates to lifting and transfer equipment for mounting and docking operations with a large space vehicle docked with a carrier rocket equipped with a supercaliber payload fairing. A cross bar comprising a bearing beam with a lug and a shank pivotally attached to the bearing beam and equipped with a stop located so that it can interact with the fixing socket on the bearing beam. Slings with hoist fittings are installed in balanced sockets of the carrier beam. The hoist fittings are installed on a transition frame coupled with the slings, and made as the front and rear adjustable brackets pivotally coupled with the transition frame. The rear adjustable brackets are located at the side of docking of the large space vehicle with the carrier rocket, and installed so that their angular positions can be fixed. The slings are located between the hoist fittings for the attachment of the large space vehicle. The rear adjustable brackets are located between the horizontal axis of symmetry of the large space vehicle and the internal boundary of the supercaliber payload fairing.

EFFECT: enhanced functionality and performance.

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Description

The present invention relates to lifting and handling equipment, and more particularly to rigging equipment used in reloading, assembling, tilting spacecraft and docking with an adapter or launch vehicle.

Known pulling device ER 140-14.0-30, containing slings installed on the earring with fixed rigging units for fastening the spacecraft (see Product 17F118. Instructions for assembly (disassembly). 17F118. IE14, Design Bureau "Flight", 1985, l.29).

A traverse 153.9521-000 is known, which contains a carrier beam with an earring mounted on it, consisting of an eye and a shank pivotally connected to the carrier beam, as well as with slings fixed to the balancing sockets of the carrier beam with rigging units for fastening the spacecraft on them (see Block KA 17С18 K. Instructions for docking (undocking). 17С18К. IE15, Design Bureau "Flight", 2002, l.44).

A traverse is also known according to the patent of the Russian Federation No. 2263065 dated 10.27.2005 for carrying out reloading operations with the spacecraft, containing a supporting beam with an earring mounted on it, consisting of an eye and a shank pivotally mounted on the supporting beam and equipped with a stopper arranged to interact with a fixing socket made on the carrier beam, slings installed in the balancing sockets of the carrier beam with rigging attachment points of the spacecraft made on them.

The disadvantage of this traverse is the impossibility of its use when carrying out crane docking of a large spacecraft with a launch vehicle equipped with a head-mounted fairing. This is due to the fact that in most cases the design and power circuit of the spacecraft dictates the need to place (rear) rigging elements used during assembly, docking and lifting and handling operations on the end docking frame (power belt) of the spacecraft. At the same time, for launching a launch vehicle of large-sized spacecraft, over-caliber (expanded) head fairings are used, the diameter of which exceeds the transverse midship of the launch vehicle. To ensure the docking of the over-caliber head fairing with the launch vehicle, which displays the large spacecraft, and to realize the possibility of docking the large-sized spacecraft and the launch vehicle, equipped with the head-mounted fairing, the latter is detachable (sectional) consisting of the front (nose) and rear parts (sections), and has an additional (intermediate) transverse joint. At the same time, the rear part (section) of the over-caliber head fairing is connected to the launch vehicle, having a conical adapter on the over-caliber (expanded) part of the head fairing, after which the large-sized spacecraft is docked to the launch vehicle, and then to the rear part (section) of the over-head head fairing the fairing is joined by the front (nose) part (section) along an additional transverse joint. In practice, the angle of inclination of the generatrix of the conical adapter to the horizontal axis is not more than 30-35 ° (the use of conical adapters with large angles of inclination leads to a deterioration in the aerodynamic stability of the launch vehicle and, as a result, to the installation of large aerodynamic stabilizers, which reduces energy capabilities launch vehicles). The presence of a conical adapter in the launch vehicle during docking with it does not allow the use of a traverse according to RF patent No. 2263065 for carrying out the indicated crane docking because the (rear) traverse lines must have a guaranteed angle of inclination to the horizontal less than the angle the inclination of the generatrix of the conical adapter nadkalibernogo head fairing to the horizontal axis. At such angles of inclination of the rear lines, the points of their attachment to the carrier beam will be (in the overwhelming majority of alignments) between the points of attachment of the front lines to the carrier beam and the center of mass of the system to be lifted, which will lead to the warping of the "traverse - large spacecraft" system and, as a result the impossibility of docking with a booster. Possible compensation for the warping of the elevated system by installing on the traverse (or on a large spacecraft) large mass balances (up to 40-50% of the lifted mass) is irrational, as this leads to additional loading of the traverse structure.

It should be noted that the mass-centering characteristics of the manufactured large-sized spacecraft (as well as the traverse structure) differ from the corresponding characteristics obtained by calculation, due to errors in the mass values of the component parts (devices, equipment, etc.) and mass power structure, as well as due to errors in their spatial arrangement on a really made structure (large spacecraft and traverse).

Skews and deviations of the longitudinal axis of the large spacecraft from the horizontal axis are possible due to the assembly technology of the traverse and its mutual docking with the large spacecraft due to the inaccuracy of the docking holes of the large spacecraft and the reciprocal rigging nodes of the traverse, as well as when installing the traverse slings in discrete located balancing sockets of the carrier beam.

The objective (goal) of the present invention is to expand the functionality (providing the possibility of crane docking of a large spacecraft with a launch rocket equipped with a head-mounted fairing) and increasing operational characteristics (eliminating distortions and mechanical damage to the large-sized spacecraft and head-mounted head fairing) of the beam.

The task (goal) is achieved by the fact that in the proposed traverse, the rigging attachment units of the large spacecraft are mounted on the transition frame associated with the slings, and are made in the form of front and rear adjustable brackets pivotally connected to the transition frame. The rear adjustable brackets are located on the side of the plane of docking of the large spacecraft with the launch vehicle and are installed with the possibility of fixing their angular position. Slings are placed between the rigging attachment points of a large spacecraft. The rear adjustable brackets are located between the horizontal axis of symmetry of the large spacecraft and the inner contour of the head-mounted fairing. The practice of developing large-sized spacecraft and rigging devices for their lifting has shown that the errors of the actual mass-centering characteristics from the calculated ones are no more than 2 ... 5% of the mass of the system being lifted. Therefore, it is proposed to fix the pins with the balancing weights of small mass and the devices for fixing the latter on the pins on the transition frame from the side of the supporting beam. The rear adjustable brackets are detachable, consisting of longitudinal rods sequentially fixed to each other.

The proposed device is illustrated in figures 1-4.

Figure 1 shows a General view of the proposed crosshead at the docking of a large spacecraft with a launch vehicle equipped with a super-caliber head fairing.

Figure 2 presents a section aa according to figure 1.

Figure 3 shows a section bB according to figure 1.

Figure 4 shows the remote element I according to figure 1.

The proposed crosshead contains a carrier beam 1 (Fig. 1) with an eye 2 and a shank 3, pivotally mounted on a carrier beam 1 and provided with a stopper 4, arranged to interact with a fixing socket (not shown) made on the carrier beam 1, installed in balancing the slots 5 of the load-bearing beam 1 of the sling 6 with the rigging nodes 7 for fastening the large spacecraft 8. The rigging nodes 7 are mounted on the transition frame 9 (Figs. 1, 3) connected with the slings 6 and are made in the form of front 10 and rear 11 (fig. 1) adjustable crowns mattes pivotally connected to the transition frame 9. The rear adjustable brackets 11 are placed on the side of the plane of docking of the large spacecraft 8 with the launch vehicle 12 and are installed with the possibility of fixing their angular position (the latches are not shown conventionally in Fig.). Slings 6 are placed between the rigging attachment nodes 7 of the large spacecraft 8. The rear adjustable brackets 11 are placed between the horizontal axis of symmetry of the large spacecraft 8 and the inner contour 13 of the head-mounted fairing. On the transition frame 9 from the side of the supporting beam 1, pins 14 are installed (FIGS. 1, 2) with balancing weights 15 placed on them and devices for their fixation (not shown). The rear adjustable arms 11 are made detachable, consisting of sequentially fixed (fastening elements in Fig. Not shown conventionally) between each other longitudinal rods 16 (Fig.4).

The proposed device operates as follows.

Before starting work, the slings 6 are installed and fixed in the corresponding balancing sockets 5 of the supporting beam 1 (a specific selection of balancing sockets 5 is carried out according to the passport (settlement) centering of the raised large-sized spacecraft 8). In the initial position, the beam crosses over the hook 17 (Fig. 1) of the crane (not shown). At the same time, for the convenience of capturing by the hook 17 of the eyelet 2, the shank 3 is in the unlocked state (the stopper 4 is removed from the fixing socket (not shown) of the carrier beam 1). After hitching the traverse to the hook 17, the stopper 4 of the shank 3 is inserted into the fixing socket (not shown), made on the carrier beam 1. Then, the traverse is connected to the large spacecraft to be lifted 8 through the rigging units 7. The front 10 and rear 11 adjustable brackets are deployed on hinges 18 and 19 (FIG. 1), respectively, until their receiving sockets (not shown) are combined with the corresponding lifting elements 20 and 21 (FIG. 1) of the large spacecraft 8 and are fixed on them. In this case, the required angular position of the front 10 and rear 11 adjustable brackets on the hinges 18 and 19 is locked by clamps (not shown). After that, the large-sized spacecraft 8 on the traverse is transferred to the area of its docking with the launch vehicle 12. By this time, the rear part (section) 22 (FIG. 2) of the head-mounted fairing having a conical adapter 23 (FIG. .2). In order to avoid mechanical damage, the angle of inclination of the rear adjustable brackets 11 to the horizontal axis should be guaranteed to be less than the angle of inclination to the horizontal axis of the generatrix 24 (Fig. 1) of the conical adapter 23 of the rear part (section) 22 of the head-mounted fairing. Such an angular installation of the rear adjustable brackets 11, as well as the placement of the slings 6 between the front 10 and the rear adjustable 11 brackets (Fig. 1), make it possible to place a large-sized spacecraft (its rear part) 8 into the backflow space 25 (Fig. 1) of the rear part (section) ) 22 nadkalibernogo fairing, thereby ensuring shock-free docking of large spacecraft 8 with a launch vehicle 12 (in this position for docking large spacecraft 8 with a launch vehicle 12 rear brackets 11 will be placed between the horizontal axis of symmetry of the large spacecraft 8 and the inner contour 13 of the head-mounted fairing).

The elimination of possible distortions in the longitudinal and transverse planes when lifting a large spacecraft 8 (leveling the longitudinal axis of a large spacecraft 8 before docking it with a launch vehicle 12) is achieved if necessary by appropriate installation and subsequent fastening with the help of fixing devices (not shown) of balancing weights ( low mass) 15, placed (figure 1, 2) on the pins 14 mounted around the perimeter of the transition frame 9 from the side of the supporting beam 1. Specific placement b balancing goods 15, their number on the pins 14 are determined by calculation or experimentally.

After docking the large spacecraft 8 with the launch vehicle 12, the crosshead is undocked from the large spacecraft 8 and moved horizontally from the backflow space 25 of the conical adapter 23 of the rear part (section) 22 of the head-mounted fairing. Then, the front (section) part (not shown) is docked to the rear part (section) 22 of the nadcaliber head fairing.

Depending on the configuration of the large over-caliber head fairing, the following variants of the sequence of shockless removal of the traverse from the large spacecraft 8 after its docking with the launch vehicle 12 are possible:

- detachment of the front 10 and rear 11 adjustable brackets respectively from the rigging elements 20 and 21 of the large spacecraft 8 and the horizontal movement of the beam in the direction from the conical adapter 23 of the rear part (section) 22 of the head-mounted fairing;

- disconnecting the rear adjustable brackets 11 from the transition frame 9, disconnecting the front adjustable brackets 10 from the rigging elements 20 of the large spacecraft 8, horizontal movement of the traverse in the direction from the conical adapter 23 of the rear part (section) 22 of the head-mounted fairing, detaching the rear adjustable brackets 11 from rigging elements 21 of a large spacecraft 8 and removing them (manually) from under the conical adapter 23 of the rear part (section) 22 of the over-caliber head fairing (through the end opening 26 (Figs. 1, 4) or through technological hatches 27 (Figs. 1, 4) on the conical adapter 23 of the rear part (section) 22 of the large head fairing);

- disconnecting the rear adjustable brackets 11 from the transition frame 9, disconnecting the front adjustable brackets 10 from the rigging elements 20 of the large spacecraft 8, horizontal movement of the traverse in the direction from the conical adapter 23 of the rear part (section) 22 of the head-mounted fairing, phased dismantling of individual longitudinal rods 16 adjustable rear brackets 11 and removing them (manually) from under the conical adapter 23 of the rear part (section) 22 of the head-mounted fairing (via a torus Eve opening 26 or through technological hatches 27 on the tapered adapter 23, the rear portion (section) 22 Bulky fairing).

Before removing the traverse from the hook 17, the spring-loaded stop 4 is removed from the fixing socket (not shown) made on the carrier beam 1, thereby removing the rigid attachment of the shank 3 to the carrier beam 1. Then the traverse is lowered to the floor and, with the subsequent movement of the hook 17 down, the latter is withdrawn from the eye 2.

Thus, the proposed device has significant differences from previously known traverses and allows you to expand the functionality (to provide the possibility of crane docking of a large spacecraft with a launch rocket equipped with an over-caliber head fairing) and to increase operational characteristics (to exclude distortions and mechanical damage to the oversized spacecraft and over-caliber head fairing) traverses.

Claims (3)

1. Traverse for docking a large-sized spacecraft with a launch vehicle equipped with a super-caliber head fairing, comprising a carrier beam with an eye and a shank pivotally mounted on a carrier beam and provided with a stopper that is arranged to interact with a fixing socket made on the carrier beam, installed in balancing slots of the load-bearing beam of the sling with rigging attachment points of a large spacecraft, characterized in that the rigging attachment units of large-size spacecraft are mounted on the transition frame associated with the slings, and are made in the form of front and rear adjustable brackets pivotally connected to the transition frame, the rear adjustable brackets placed on the side of the plane of docking of the large spacecraft with the launch rocket and installed with the possibility of fixing them angular position, while the slings are placed between the rigging attachment points of the large spacecraft, and the rear adjustable brackets are placed between the horizontal axis of symmetry of the large-sized spacecraft and the inner contour of the head-mounted fairing. 2. Traverse according to claim 1, characterized in that on the transition frame from the side of the supporting beam, pins are installed with balancing weights placed on them and the devices for fixing the latter on the pins. 3. Traverse according to claim 1 or 2, characterized in that the rear adjustable brackets are detachable, consisting of longitudinal rods sequentially fixed to each other.

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