RU2457987C1 - Method of prelaunch preparation and launching of multibank space rockets made up of universal rocket modules, and device to this effect - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: set of inventions relates to aerospace engineering. Proposed method consists in that, after mounting the rocket on launching pad, strut with rocket retainer mechanisms and those of onboard plug-in connector withdrawal is underproped and docked to rocket. Rocket is launched and, at a time, aforesaid strut with aforesaid mechanisms is withdrawn. After jointing the strut to rocket, rocket retaining mechanisms are locked by levers mounted on tower. After rocket fueling, said mechanisms are unlocked. Servicing device is displaced to safe distance without breaking ''ground-board'' connections. Prior to launching, aforesaid mechanism are disconnected from rocket. Proposed device comprises U-like trussed structure with two parallel towers and strut arranged there between to support aforesaid mechanism and mounted on tie-rods of articulated beams mounted on said towers. Towers are mounted on running bogies. Retaining device is made up of click-on chuck with its arms to be fitted on space rocket stage II (III). Towers are equipped with levers to lock click-on chuck arms.

EFFECT: higher reliability.

2 cl, 3 dwg

Description

The invention relates to rocket and space technology, and in particular to methods and means of prelaunch preparation and launch of space rockets (ILV), composed of universal rocket modules (URM).

Known methods of preparation for launch, the composition and design of launch complexes (SC) ILV using mobile service units (MAO), cable refueling towers (KZB) and refueling masts (ZDM).

For example, the Energy-Buran rocket and space system (RCC) SC consists of a launcher (launcher), MAO, withdrawn from the RCC before launch along an arc of a circle, and a stationary ZDM.

IC Proton rocket launcher includes a launcher and a U-shaped MAO mobile and translationally moving along crane tracks, retracted from the rocket launcher 40 minutes before it starts.

Final operations to launch the rocket launcher on these SCs are carried out by mechanisms located in the launch pad (PS) (rocket launcher "Proton") and ZDM (RKS "Energy - Buran").

The use of SS for these purposes is unacceptable for rocket launchers made up of universal missile modules (URM), because final operations for launching ILV for them are also carried out at the moment of ILV separation from the SS. For example, in the Angara rocket launcher, the connection of 2 (3) stages, the upper stage and the space head part with communications of the ground-based equipment complex is also carried out at the time it starts to rise. Inclusion in the structure of SK ZDM (RKS "Energy - Buran") increases the cost of SK and operating costs for its maintenance.

Currently, to reduce the number of units in the SK, stationary KZBs are used that combine the functions of a service unit and a refueling mast (Technological objects of the ground-based infrastructure of rocket and space technology. Book 1. Edited by IV Barmin, M., 2006).

There is a method of preparation for launch and launch of rocket launchers, composed of URM using in the structure of SC KZB. The method of preparation and launch of a multi-block rocket launcher according to the invention (RU No. 2291089, 01/10/2007, B64G 5/00) consists in the fact that after installing the missile at the substation, a mast mounted on the KZB with the mechanisms of the missile holding device (ASD) and retraction airborne detachable connections (BRS) with communications, and docked on a rocket. Next, technological operations are carried out for refueling and for providing land-to-board communications. After completion of the technological operations for servicing the rocket, the work is carried out in the reverse order, and at the initial moment of the rocket's lifting, the BS mechanisms with communications and UUR are undocked and retracted, and the mast returns to its original position. A device for implementing this method contains a U-shaped truss with two parallel towers and a mast located between them with the mechanisms for steering and retraction of the BRS with communications, mounted on the connecting rods of articulated arrows mounted on the towers of the KZB. The mast is mounted with the possibility of reciprocating movements relative to the rocket by means of separate hydraulic actuators with rectilinear lemniscate guiding mechanisms. This method and device provide preparation for launch and launch of the rocket launcher, made up of URM. However, at the same time, the windshield of the RCP and its maintenance have to be carried out from sites installed on long booms mounted on the KZB, covering the distance between the SS and KZB, necessary under the conditions of shockless rocket lift and safe gas-dynamic impact on it of jets of propulsion systems of the first stage of the rocket. According to its functional purpose, technical nature and technical result achieved, the invention according to the patent RU No. 2291089 is the closest and is selected as a prototype to the claimed method and device.

The objective of the proposed group of inventions is to create a method for preparing and launching a multi-unit RCP and a maintenance device (UO) for its implementation, providing a technical result consisting in increasing the reliability of the operation of technological equipment, reducing the cost of building launch complexes, providing flexibility in circuit designs for servicing RCP.

The optimal design of a service device for multi-block rocket launchers made up of a workstation for the implementation of the method must meet the following requirements:

- to carry out retention, maintenance and refueling of the rocket launcher, being in the immediate vicinity of the rocket standing on the launcher;

- move away from the launcher with the missile to a distance that provides shock-free lifting and the unit is safe from the gas-dynamic effect of the jets of the first stage rocket engines, after refueling the rocket with the removal of wind retention and maintaining the operability of communications connecting the 2 (3) stage of the rocket, the upper stage and the space head with ground equipment;

- launch the rocket with the withdrawal of communications at the initial moment of its rise.

The required technical result is achieved by the fact that after the installation of the RCP on the substation, a rack located on the UO is brought to it with UUR mechanisms and BRS withdrawal with communications and docked on a rocket. Next, they carry out technological operations for refueling, servicing the rocket, and after they are completed, they launch it with simultaneous withdrawal of the rack with the mechanisms of the UUR and removal of the BRS with communications. According to the invention, after docking the rack with the missile, the missile retention device is blocked, which ensures reliable ILV retention in a given position, and after the refueling and maintenance operations are completed, the lock is removed. Then, without breaking the ground-to-board communications, using the platform with the bogies, the service device is withdrawn to a safe distance, and before launch, the UUR mechanisms are disconnected from the rocket. The service device for implementing the method includes a U-shaped truss with two parallel towers and a rack located between them with mechanisms for holding the rocket and retracting airborne detachable connections with communications, mounted on rods of articulated arrows mounted on the towers. According to the invention, the towers are placed on a platform with running trolleys, and the rocket retention device is made in the form of a tick grip with the possibility of imposing its shoulders on the II (III) stage of the rocket launcher, while the towers are equipped with levers made with the ability to lock the tick grip shoulders.

The authors of the proposed inventions are not aware of similar technical solutions, and therefore, according to the authors, the claimed combination of features meets the criteria of the invention "inventive step" and the criterion of "novelty."

The device implementing the proposed method is illustrated by drawings.

On figa, 1B shows the position of the device during maintenance (1A) and before starting the rocket launcher (1b).

Figure 2 is a view And on the rack mechanisms for the removal of cattle and tick-borne capture.

Figure 3 is a view of B on the rack mechanisms for the removal of BRS and tick capture.

The device for prelaunch preparation and launch of the rocket launcher, made up of the URM, consists of a U-shaped truss 1 (Fig. 1) with two parallel towers 2 (Fig. 2) with horizontal service platforms 3 (Fig. 1) and levers 4 (Fig. .2) installed on the platform 5 (Fig. 1) with running trolleys 6 (Fig. 1), and located between the towers of the rack 7 (Fig. 1) with retraction mechanisms 8 (Figs. 1, 3) of communications 9 (Fig. 1). 1), mounted on the connecting rods 10 (Fig. 1, 3) of articulated arrows 11 (Fig. 1) with hydropneumatic actuators 12 (Fig. 1), on which the UUR is fixed in the form of a tick grip 13 (FIGS. 1, 3) with hydraulic actuators 14 (FIG. 2) with the possibility of imposing its shoulders 15 (FIG. 2) on the II (III) stage of a space rocket made up of URM 16 (FIG. 1), standing on the PS 17 (figure 1).

We will consider the implementation of the proposed method and device using the example of prelaunch preparation and launch of a space rocket installed at a substation.

After installing the rocket launcher 16 (Fig. 1) on the PS 17 (Fig. 1), hydraulic actuators 14 (Fig. 2) of the arms 15 (Fig. 2) of the opened tong grip 13 (Figs. 1, 3) mounted on the rack 7 (Fig. 1) .1), mounted on the connecting rods 10 (Fig. 1, 3) of the articulated arrows 11 (Fig. 1) of the device, the arms 15 (Fig. 1) of the tongs 13 (Fig. 1) are mounted on the II (III) stage ILV 16 (figure 1), after which the levers 4 (figure 2) of the towers 2 (figure 2) of the device are superimposed on the shoulders 15 (figure 2) of the tongs 13 (figure 1, 3), making the wind "dry" "ILV 16 (figure 1) for the tower 2 (figure 2). Next, the communications are docked, refueling and serviced. After their completion, the levers 4 (figure 2) of the towers 2 (figure 2) are removed from the shoulders 15 (figure 2) of the tongs 13 (figure 1, 3), and the device is diverted from the rocket launcher 16 (figure 1) by means of the chassis carts 6 (figure 1) at a safe distance.

During the movement, the tick grip 13 (FIGS. 1, 3) continues to hold the ILV 16 (FIG. 1), and the change in the distance between the ILV 16 (FIG. 1) and the device is compensated by an increase in the outreach of the articulated arrows 11 (FIG. 1) that occurs under the influence of hydropneumatic actuators 12 (figure 1), while the efficiency of communications 9 (figure 1) is maintained. The movement of the device and the proportionally synchronous change in the departure of the articulated arrows 11 (Fig. 1) ends when the maximum reach of the articulated arrows 11 (Fig. 1) is reached. Before starting the hydraulic actuators 14 (figure 2) tick-borne capture 13 (figure 1, 3) take the shoulders 15 (figure 2) from the rocket carrier 16 (figure 1). Startup is in progress. In the initial period of the rise of the RCP 16 (Fig. 1), the withdrawal mechanisms 8 (Figs. 2, 3) separate the boards and communications to the rack 7 (Fig. 1), which, in turn, together with the tick-shaped gripper 13 installed on it (Fig. 1) , 3) and retraction mechanisms 8 (FIG. 2, 3) of communications 9 (FIG. 1) are retracted by articulated arrows 11 (FIG. 1) by means of hydropneumatic actuators 12 (FIG. 1).

Implementation of the method of prelaunch preparation and launch of rocket launchers, assembled from an automated missile system, carried out by means of a mobile service device with a full cycle of prelaunch and missile launch operations, equipped with service platforms located directly on the device’s towers and having one lightweight mechanism designed only to divert ground communications to the initial rocket lifting period, instead of a stationary cable-refueling tower (RKS "Energy - Buran"), 13-15 m from the axis of the launcher, Commercially 4 to 6 with the arrows of service platforms weighing over 100 tons each, with an arm of 5-6 m center of gravity, will reduce the weight of the unit towers and improve working conditions for the staff working at high altitudes.

Thus, the set of inextricably interconnected essential features set forth in the claims, allows to obtain a significant technical result. Using the proposed method and device for the preparation and launch of multi-unit rocket launchers, it will be possible to abandon cable-filling towers with platforms and holding devices installed on long and heavy booms, as well as refueling and drainage masts, which will reduce the cost of building launch complexes, in addition, will increase the reliability of technological equipment, provide flexibility circuit design services ILV. The inventions can be used at the launch site of the Baikonur Cosmodrome, and are also considered as an option for the design of the Vostochny Cosmodrome.

Claims (2)

1. The method of preparation and launch of multiblock space rockets, which consists in the fact that after installing the rocket on the launch pad, technological operations are carried out to refuel the rocket, to provide ground-to-air communications by means of a rack mounted on the service device with the mechanisms of the rocket containment device and the airborne retraction detachable connections with communications, which are docked with the rocket, then launch with simultaneous withdrawal of the rack with the mechanisms of the device for holding the rocket and removal of onboard detachable soy of the connections, characterized in that after docking stand with a missile blocking mechanisms missile retention device by means of levers mounted on the tower, and after the operation is completed fueling lock missile is removed, then withdrawn device service at a safe distance, without breaking the bonds "land-board", and Before starting, the mechanisms for holding the rocket from the rocket are disconnected. 2. The service device for implementing the method according to claim 1, containing a U-shaped truss with two parallel towers and a rack located between the towers with mechanisms for holding and retrieving onboard detachable connections with communications mounted on it, mounted on connecting rods of articulated booms, mounted on towers, characterized in that the towers are placed on a platform with running trolleys, and the retention device is made in the form of a tick grab with the possibility of imposing its shoulders on II (III) stupas the space missiles, while the towers are equipped with levers made with the possibility of locking the arms of the tongs.

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