RU2196712C2 - Device for separation of spacecraft members - Google Patents

Abstract

FIELD: space engineering; holding developable structures of spacecraft (antennae, booms) in folded position. SUBSTANCE: device has body where explosive charges, membrane, rod and sleeve with tail-piece for securing the separable member are arranged. Sleeve is made in form of two interconnected parts with spherical inner surfaces which are engageable with spherical insert connected with body by means of retainer. Body has two holes for articulation with spacecraft. Proposed device ensures curvilinear trajectory of separable member. EFFECT: enhanced reliability. 2 cl, 2 dwg

Description

 The invention relates to the field of space technology and can be used to hold in the folded position antennas, rods with devices mounted on the spacecraft (SC) body and separating them for program disclosure.

 Known pyrotechnic mechanism comprising a housing in which a piston is located that carries a rod connected by a shear pin to a sleeve connected by a ball retainer to the housing. When applying pressure to the piston, he pushes the rod and opens the ball lock [1].

 The disadvantages of this design include the fact that during the separation process local shock pulses arise, which negatively affect the equipment located in the immediate vicinity of the shared spacecraft elements.

 The closest in technical essence is a device for separating spacecraft elements, comprising a housing in which a chamber with pyro cartridge is installed, a membrane, a rod, a sleeve with a shank for attaching a detachable part [2].

 When the squibs are triggered under gas pressure, the membrane deforms, the rod moves and the constituent elements of the sleeve are pulled together and are pulled together.

 The disadvantage of this device is that, if necessary, to have a trajectory of the detachable part, different from the rectilinear, it is possible jamming of the sleeve in the device body and non-disclosure of the junction of the shared spacecraft elements.

 The technical problem solved by this invention is to ensure the disclosure of the junction of the shared elements of the spacecraft with the trajectory of the detachable part other than straightforward.

 This problem is solved due to the fact that in the known device for separating spacecraft elements, consisting of a housing in which a chamber with pyrocartridges is installed, a membrane, a rod, a sleeve with a shank for attaching a detachable element, the sleeve is made in the form of two parts interconnected and having spherical inner surfaces interacting with a spherical liner connected to the body by means of a latch, in addition, two holes for swiveling with the spacecraft are made in the body.

Figure 1 presents a General view of the device in a docked state;
figure 2 - the position of the elements of the device after disconnecting the connection between the elements.

 A device for connecting spacecraft elements shared in flight consists of a housing 1 pivotally mounted, for example, on a spacecraft housing 2, with half shafts 3. A chamber 4 has a chamber 4 with squibs 5, a membrane 6, a rod 7 with a trapezoidal groove 8, a sleeve 9 with a shank 10 for fastening the detachable element 11, the spherical insert 12, the latch 13. The membrane 6 is installed inside the housing 1 and rigidly clamped by the chamber 4 through the sealing element 14 installed in the lock between the chamber 4, the membrane 6 and the housing 1.

 In the housing 1 from the side of the membrane 6, a spherical surface 15 is made, which is the limiting support during the deformation of the membrane 6. The shank of the membrane 6 is rigidly connected to the rod 7.

 The sleeve is made in the form of two parts 17 and 18, interconnected and having spherical surfaces 19 and 20, interacting with a spherical liner 12 connected by a ball retainer 13 with the housing 1.

 When a signal is applied to separate the connection between the elements to be separated, the squibs 5 are triggered. Under the gas pressure, the membrane 6 is deformed, moving the rod 7, releasing the spherical liner 12 of the sleeve 9. Under the action, for example, pushers (not shown), the necessary elements are given the necessary separation speed by programmatic opening .

 As a result of the fact that the device is pivotally mounted on the spacecraft’s axles 3, and the sleeve 9, consisting of parts 17, 18, has degrees of freedom of movement on the spherical liner 12 along the spherical surfaces 19, 20, a trajectory is provided for the detachable part 11, excellent from straightforward, and increases the reliability of the separation of the elements of the spacecraft.

 The operation of the device is confirmed by the results of tests conducted on prototypes.

Sources of information
1. Copyright certificate 576443, cl. F 16 B 2/16, 1973.

 2. Patent RU 2144892 C1, cl. B 64 G 1/64, F 16 B 2/16, 2000.

Claims (1)

 A device for separating elements of a spacecraft, comprising a housing in which a chamber with pyrocartridges is installed, a membrane, a rod, a sleeve with a shank for attaching a detachable element, characterized in that the sleeve is made in the form of two parts interconnected and having spherical internal surfaces interacting with a spherical liner connected to the casing by means of a latch, in addition, two openings are made in the casing for articulating with the spacecraft.

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