RU2471684C1 - System for separating payload from space vehicle board - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to space engineering, namely to devices for docking payload to main spacecraft and payload separating after insertion to design orbit. System for separating payload includes disengageable adapter installed between structures of aircraft and payload and containing mechanical locks with retaining and fixing elements, mechanical locks fixation device. The system has pushers for payload separation. The mechanical locks fixation device is made as equal-arm rocker with unlimited number of arms corresponding to number of mechanical locks. The rocker is installed on rotation axis fixed in adapter housing Through adapter via-windows, the equal-arm rocker is pivotally interacting by means of tie-rods with fixing elements of mechanical locks the spring-loaded rods of which have recess for retaining rotating double-arm lever by other end interacting with fixing element of lock. One of arms of the equal-arm rocker is pivotally interacting via tie-rod with spring pusher, the other arm - with explosive pin which are rigidly fixed on the outside of adapter housing. On a payload, arresting devices are made which interact with spring-loaded rods of mechanical locks.

EFFECT: higher reliability of docking and separating system operation.

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Description

The invention relates to the field of space technology, in particular to means for docking to the main spacecraft (SC) of simultaneously-launched small-sized spacecraft (MCAs) and separating the latter from the SC after putting them into the calculated orbit.

In order to minimize the impact of the joint operation of the spacecraft and the spacecraft on the reliability and other characteristics of the spacecraft, the ICA separation system (IC MC) is subject to increased requirements in terms of its reliability, minimizing weight and dimensions, reducing shock loads when the separation system is activated (CO ), ease of installation and operation of MCA, etc.

In rocket and space technology, known payload SOs consisting of shared transitional devices (adapters, transitional frames) on which the means of fastening, separation and repulsion of spacecraft (SC) are installed.

So, according to the description of Patent RU No. 2268208, IPC8 B64G 1/64 dated 02.06.2003, the CO contains a payload holding device (MO) on the supporting structure of the launch vehicle (PH) using mechanical locks, a lock fixing device in the holding position (fastening ) PN with the help of a cable system equipped with a fixing sprocket connected with a pyromedicine and a device for repelling LV and PN after breaking the connection between them.

The disadvantages of such a system of separation of the payload (CO PN) is the presence of a cable system in the device for fixing mechanical locks, which creates a risk of collision of the cables with the protruding elements of the lower part of the PN. In addition, adjustment of the cable system tension is required.

In the description of the patent RU No. 2293694, IPC8 B64G 1/64, B64D 1/02, F42B 15/36 of 06/14/2005, the possibility of increasing the area of placement of the PN by expanding the installation plane of the multi-beam locking sprocket below the plane of installation of the locks expands. However, the cable system itself is becoming more complicated, and therefore, the need to adjust it remains.

In addition, in the above variants of CO, after its operation, a protruding lock shaft with a tooth remains on this part of the ST, which creates a risk of grazing it with movable ST construction elements (antennas, covers).

The disadvantage is that each lock after unlocking is opened by a separate spring drive, which reduces the reliability of the system.

The closest known technical solutions is, selected as a prototype, SB PN according to patent RU No. 2396191, IPC8 B64G 1/64 dated 03/18/2009.

CO contains a disconnectable transition device, which is fixed on one rocket (or spacecraft) by one side, and the other interacts with the following elements mounted on it:

- device for mounting monitors with mechanical locks;

- a device for fixing mechanical locks in the position of holding (fastening) PN;

- a device for pushing PN with spacecraft.

The disadvantages of the known SO MON are:

- the complicated design of the device for fixing mechanical locks, incorporating a significant number of actuating elements (cam clutch, thunder rods with single-stage and double-degree hinges, spring drive of sprocket rotation using tension springs). Failure of each of these elements leads to a decrease in reliability or even to failure of the fixation device;

- all structural elements of the device for fixing mechanical locks are located inside the transition device, which leads to a decrease in the area of the PN located below the plane of the junction of the PN with the transition device;

- the need for the location of the rotary sprocket in the center of the circle along which the locks should be discretely located, the number of which should be at least three. The design of the LV located below the plane of its junction with the adapter does not always allow these requirements to be fulfilled, which reduces the capabilities of the known SO MON.

The objectives (goals) of the proposed system for separating payload (GHG) from the spacecraft are:

- improving the reliability of CO;

- increase in the area of GHG deployment.

To achieve the objectives, it is proposed that the GHG from the spacecraft side contains a detachable adapter installed between the KA and GH structures and includes mechanical locks with holding and fixing links, a mechanical lock fixing device, and the system contains spring pushers of the payload compartment, where , according to the invention, the device for fixing mechanical locks is made in the form of an equal-sized rocking chair without limiting the number of shoulders corresponding to the number of mechanical locks and mounted on the axis of rotation, fixed in the housing of the transition device, and the equal-arms swinging through the through windows of the transition device, pivotally interacts via rod rods with the locking links of the mechanical locks, the spring-loaded rods of which have a recess for holding the rotary two-arm lever, the other end interacting with the locking link of the lock, in this case, one of the shoulders of an equal-shouldered rocking chair pivotally interacts through a rod rod with a spring pusher, the other with a pyrochette, which rigidly fixed on the outside of the case of the transition device, and on the payload there are made travel limiters interacting with the spring-loaded rods of mechanical locks.

The claimed technical solution is presented in the drawings:

Figure 1 presents a General view of the GHG from the spacecraft.

In Fig.2 shows a view A in Fig.1 (view of the device in the initial position from the PG).

Figure 3 presents a section bB in figure 2. The lock is in its original (closed) position.

Figure 4 presents the lock in the open position.

SO GHG from the spacecraft side contains a transition device 1 (frame or cylindrical shell) installed between SC 2 and SG 3. PG (MCA) is connected to the transition device 1 by mechanical locks 4, which are connected to the locking device of mechanical locks in the holding position and are made in in the form of equal arms of the rocker 5 of the rod rods 6. The equal-arm rocker 5, the number of shoulders of which is not limited and corresponds to the number of mechanical locks, is mounted with the possibility of rotation around axis 7, fixed in the casing of the transition device m L relative to its center of symmetry. To ensure free movement of equal arms of the rocking chair 5, through the windows 8 are made in the housing of the transition device 1.

In the joints of the rod rods 6 with the fixing links 9 of the mechanical locks 4 and rods with an equal arm rocking chair 5, hinge assemblies 10 are made.

Spring pushers 11 pushing the main spacecraft and the steam generator after opening the mechanical locks 4 are mounted on the transition device 1 and abut against the bottom of the steam generator. Pyrochek 12 and a spring pusher 13 for opening mechanical locks 4 are mounted on brackets 14 and 15, respectively, which are mounted on the outer surface of the transition device 1.

At one end, the equal-armed rocker 5 interacts on the one hand through the rod rod 16 with the pusher 13, and on the other hand through the rod rod 17 with the pyrochette 12.

The mechanical lock 4 has a spring-loaded rod 18, the spring 19 of which is placed outside the cup 20, which is also the stroke limiter of the spring-loaded rod 18 after the mechanical lock is opened 4. The spring-loaded rod 18 itself has a recess 21, which is held by a rotary two-arm lever 22, which is different end interacts with the locking link 9 of the mechanical lock 4.

In the initial position, the transition device 1, attached to the board of the main spacecraft 2, is pulled together with the PG 3 by mechanical locks 4.

The transverse loads at the junction "PG - transition device" are perceived by the pins 23.

The required axial force on the mechanical lock 4 when tightening is created by tightening the nut 24.

The rod 18 of the mechanical lock 4 is held by a rotary two-arm lever 22, the other end of which interacts with the locking link 9 of the mechanical lock 4.

The locking links 9 of all mechanical locks 4 are held in their initial position by a swivel equal-arms rocking chair 5 using rod rods 6, and the equal-arm rocking chair 5, with its end, is connected on one side to pyrochelic 12, and on the other hand, to a cocked spring pusher 13.

Spring pushers 11 pushing the PG 3 from the main spacecraft are cocked and abut against the bottom of the PG 3.

On command of the PG 3 compartment, the pyrocheck 12 is triggered and under the action of the force (Pt) of the spring pusher 13, the equal-arm rocker 5 is rotated in the direction of arrow B and, using the rod rods 6, rotates the locking links 9 of all mechanical locks 4 until the levers 22 are unlocked.

After that, all mechanical locks 4 are opened and the PGZ is repelled by spring pushers 11 from the main spacecraft.

Since the rocker 5 is made of equal arms, the peripheral speed of all the hinge assemblies 10 is the same and, thereby, the synchronous opening of all mechanical locks occurs. The length of the rods 6 is selected taking into account the magnitude (L) of the displacement of the center of rotation of the equal arms of the rocking chair 5 relative to the center of symmetry of the transition device 1 or in case of impossibility (due to the design of the bottom part of the steam generator 3) of the discrete arrangement of mechanical locks 4 at the junction of the transition device 1 with the steam generator 3.

Depending on the number of mechanical locks 4, the rocking chair 5 becomes two shoulders with two locks, three shoulders with three, etc.

After the mechanical locks 4 are opened, the spring-loaded rods 18 are moved by the springs 19 all the way into the protrusion of each cup 20, which are the stroke limiters of the spring-loaded rods 18, ensuring the absence of protruding CO elements in the bottom of the SG below the plane of its junction with the adapter 1 after separation.

The proposed design of SO GHG from the spacecraft side allows to exclude from its structure a cam clutch, thunder rods, a spring turn drive using tension springs. The rocker equal-arms drive, made in the form of a single spring pusher, has greater reliability than the drive of a rotary sprocket, consisting of a tension spring, since in the event of failure, the tension spring completely loses its purpose, and the compression spring in the pusher continues the task. The reduced number of actuating elements in the device for fixing mechanical locks increases the reliability of the system for separating the GHG from the spacecraft.

The proposed design of the SG GHG from the spacecraft side allows the actuator elements of the mechanical lock fixing device (pyrocheck, rod rods, pusher) to extend beyond the inner zone of the transition device and, thereby, increase the GHG zone located below the plane of its junction with the adapter.

It seems possible to use the proposed design of SO GHG from the spacecraft side with the number of locks in its composition less than three and the requirements of discrete location of locks at the joint of the GHG with the adapter, as well as the location of the axis of rotation of the equal-arm lever strictly at the symmetry point of the transition device, are excluded. All that is required is a corresponding change in the length of the rod rods. This extends the technical capabilities of CO.

The authors carried out calculations of the parameters of the proposed design of the SO GHG from the spacecraft during its design, manufacture and experimental testing confirmed the effectiveness of the technical solution.

The claimed device GHG from the spacecraft in comparison with the prototype has significant differences and can improve its reliability, increase the area of deployment of GHGs.

Claims (1)

A system for separating payloads from the board of a spacecraft, comprising a releasable transition device installed between the structures of the spacecraft and payloads and including mechanical locks with holding and fixing links, a device for fixing mechanical locks, the system comprising pushers for separating the payload, characterized in that the device for fixing mechanical locks is made in the form of an equal-arm rocking without limiting the number of shoulders corresponding to the number of fur locks mounted on the axis of rotation, mounted in the housing of the transition device, and the equal-arm rocker through the through windows of the transition device pivotally interacts with the rod links with the locking links of the mechanical locks, the spring-loaded rods of which have a recess under the holding rotary two-arm lever, the other end interacting with the locking link lock, while one of the shoulders of an equal-shouldered rocking chair pivotally interacts through a rod link with a spring pusher, the other with pyroece, which are rigidly fixed on the outside of the case of the transition device, and on the payload there are made travel limiters interacting with the spring-loaded rods of mechanical locks.

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