RU2726340C1 - Device for docking of spacecrafts - Google Patents

Abstract

FIELD: space equipment.

SUBSTANCE: invention relates to space engineering, particularly, to spacecrafts and their parts docking and decoupling systems. Device for docking spacecrafts for two-stage docking process consists of extended docking assembly. Docking assembly represents structure with fixing elements on outer side. It is made with possibility of extension from carrier device by means of controlled pneumatic elements. Elements consist of a corrugated sleeve with a cable rope passing inside. Cable-rope is fixed by one end on the pneumatic element base on the docking assembly, and by another one on the servo drive in the pneumatic element body adjusting its length.

EFFECT: enabling higher reliability.

4 cl, 3 dwg

Description

Description of the invention a device for docking spacecraft.

Application area.

The spacecraft docking device belongs to the field of spaceships and their equipment, systems of docking and undocking of spaceships or their parts.

State of the art.

Docking of spaceships and their parts in outer space is the most difficult and dangerous process at the stage of the flight operating phase. Rapprochement, contact, capture, retraction. There are many complexities involved in each of these stages. The approach is carried out according to the laws of ballistics with constant correction by attitude motors with intensive expenditure of the working fluid.

The final stage is especially difficult, when it is necessary to get into the docking device, which has small dimensions, due to the fact that the unit with the docking device after docking enters the ship, opening the opening of the entrance hatch.

Contact is a very dangerous phase, since the mass of abutting objects reaches significant values and it is extremely difficult to extinguish the inertia of large masses, especially on modern multi-link objects. Capturing and tightening operations due to the design features of the used docking devices are performed using a central (pin) element that carries the entire load and does not have duplicate parts.

Known as analogues:

Docking device patent US 4722753 B 64G1 / 64 1987

The complex, containing a docking unit, the cone of which is located on one ship, and the pin on the other, includes a gripper with a cable and a throwing unit attached to one apparatus.

Inflatable gripper device RF patent 2503593 B64G 1/64 10.01.2014

It consists of an inflatable body of a conical shape inflated around the entrance-exit gateway, in order to direct the movement of a space object to or from the gateway.

The method of docking spacecraft RF patent 2521082 B64 G1 / 64 06/27/2014.

Including the use of a homing tug for the delivery of a cable, equipped with a docking station for subsequent rendezvous using the retraction method.

The closest analogue, according to the applicant, is the method of docking of spacecraft RF patent 2521082 B64G1 / 64 06/27/2014.

The purpose of the invention:

The purpose of the invention - a device for docking spacecraft is to search for design principles that make it possible to approach the solution of problems arising during the processes of docking of spacecraft.

Main goals:

Dividing the docking process into two main stages of rendezvous, contact, capture - the first stage occurring at a certain distance of the vehicles, the second stage is contraction, to minimize the negative consequences of the collision of significant masses with a moment of inertia, and due to the design, ensure duplication of the main working functions.

A device for docking spacecraft, consisting of a docking unit, including a flexible connection with the carrier vehicle differs in that the docking unit 1 of Fig. 1 has an annular conical shape, a large diameter, fixation mechanisms 2 of Fig. 1, located on the outer perimeter of the unit and the middle part free of docking mechanisms, facilitating access to the entrance and exit hatches. The docking unit is intended for intermediate docking and is movably fixed on the apparatus carrier 3 of Fig. 1 with the help of 4, 6, 8 pneumatic modules, consisting of corrugated inflatable sleeves 4 Fig. 1, 4 Fig. 2 with the sleeves passing inside cable-rope 5 Fig. 1, 5 Fig. 2 fixed at one end on the base of the sleeve in the docking unit 1 in Fig. 1, 1 in Fig. 2, and with the other to the servo winch 6 in Fig. 2, which is equipped with each pneumatic module.

Pneumatic modules with corrugated sleeves 4 Fig. 1, 4 Fig. 2 cable-ropes 5 Fig. 2 and servo drives 6 Fig. 2 are located circumferentially around the entrance-exit hatch 7 Fig. 1 in the wells of the docking compartment of the spacecraft carrier 3 Fig. 1.

By supplying the working fluid (air or inert gas) to the pneumatic modules, the docking station can be extended to a predetermined distance from the spacecraft, the position of the docking station can be controlled by changing the pressure and length of the cable-tether.

At intermediate docking of the spacecraft 8 of FIG. 1 with the docking unit 1 of FIG. 1, the residual inertial moments are damped by a controllably-amortized structure of corrugated sleeves. Adjustment of the pressure in the sleeves can be carried out by moving the working fluid into reserve containers, according to the principles of operation of pneumatic shock absorbers, or, if necessary, by releasing pressure through the jet nozzles 9 of Fig. 1 according to the principle of a muzzle brake.

The devices are pulled together by winding the cable with a servo drive and controlled by the back pressure of the pneumatic element. In this way, the pulling speed can be controlled very precisely.

To ensure the reliability of the device for docking spacecraft, the pneumatic modules 10 of Fig. 3 should be made easily replaceable. Replacement of pneumatic modules can occur when the devices are docked, or the docking unit 1 of Fig. 3 is in the transport position and the shafts of the pneumatic modules 10 of Fig. 3 are closed and sealed by the annular body of the docking unit 1 of Fig. 3

When the cover 11 of Fig. 3 of the shaft is opened, the pneumatic modules are replaced by spare ones located in the docking compartment. The fastening of the module base to the body of the docking station and the shaft body is carried out by the latch-latch 11 of FIG. 2 by turning the body of the pneumatic module. After connecting the power supply terminals and the pneumatic drive route, the shaft cover is closed and the module is ready for operation.

Claims (4)

1. A device for docking spacecraft for a two-stage docking process, consisting of a retractable docking unit, characterized in that the docking unit is a structure with locking elements on the outer side, is made with the possibility of extension from the carrier spacecraft using controlled pneumatic elements consisting of a corrugated sleeves with a cable-cable running inside, fixed at one end on the base of the pneumatic element at the docking unit, and at the other on a servo-drive in the body of the pneumatic element, which regulates its length. 2. The device according to claim 1, characterized in that the working fluid is fed into the corrugated hoses of pneumatic elements, the docking unit is designed to be extended to a predetermined distance, controlled by the cable-ropes, the pressure and length of the cable-ropes have the ability to regulate and control the position of the docking unit ... 3. The device according to claim 1, characterized in that during intermediate docking of the spacecraft with the extendable docking unit, the residual inertial moments of the masses moving towards each other can be damped by pneumatic elements according to the shock absorber principle, by moving the working fluid, or by releasing reactive braking streams. 4. The device according to claim 1, characterized in that the pneumatic elements are independent, autonomous, interchangeable units and can be replaced with spare ones when the pneumatic element shafts are sealed with the docking unit body.

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