SE518171C2 - Bandage on a spacecraft - Google Patents

Abstract

The invention concerns a coupling 4 for a space vessel 1 for holding together a vessel part 2 and a protective envelope 3 that is separable from the vessel part 2. The coupling comprises a first outer flange 5 that is arranged on the vessel part 2, and a second outer flange 6 that is arranged on the protective envelope. The coupling further comprises a number of clamps 7, which are distributed along the periphery of the flanges 5, 6 to transfer radial forces from a tension element that surrounds the clamps 5, 6. The outer flanges are joined by the combination of clamps and tension elements. The coupling further comprises a radially inwardly oriented second inner flange 11, which is arranged on the vessel part 2. The first inner flange 9 is integrally realized with at least one surrounding element 10, which surrounds the second inner flange 11 at least partly.

Description

Ilva »10 l5 20 25 30 51 a 171 The connecting devices must be designed so that until the time of separation they hold the vehicle part and the protective cover together with such force that mutual movement between these two parts is minimized. Today's technology uses a pyrotechnic linear charge around the perimeter to cut off the structural element. These charges must be oversized in order to achieve satisfactory reliability. This leads to a great shock effect when the connection is dissolved, which can lead to damage to sensitive electronics in the satellites.

For the separation of satellites, a technology with straps is used today. This technology today does not work satisfactorily for attaching a protective cover to a vehicle part.

This is mainly due to the large circumference of the spacecraft, which means that extremely high tension would be required in the strap for secure mounting of the casing.

DESCRIPTION OF THE INVENTION The object of the invention is to solve one or more of the above problems.

This is achieved with a device according to claim 1.

A vehicle part and a protective cover separable from the vehicle part are held together by a joint, which comprises a first outer end arranged for the vehicle part, a second outer end arranged for the protective cover, a number of stirrups and a clamping member surrounding the stirrups. The vehicle part further comprises a radially inwardly directed first inner end. This is integrally formed with one or more enclosing members, which at least partially surround a radially inwardly directed second inner flange on the protective housing.

In an embodiment of the invention, the enclosing member extends uninterrupted along a periphery of the vessel part and engages the first inner end along the entire extent of the flange.

In an advantageous embodiment of the invention, the enclosing member engages the first inner end at a number of different areas distributed along the periphery of the ends. ~ |; |; In a further embodiment of the invention, said enclosing means comprises a plurality of clamping lips. When the clamping means is fitted around the stirrups, the clamping lips are pressed against the corresponding upper abutment surfaces on the other inner end of the protective cover. The enclosing member with the clamping lips helps to fix the interior of the housing in both the radial direction and in the longitudinal direction.

In an advantageous embodiment of the invention, the protective cover may surround one or more of the satellites, which are held together with the vehicle part.

The unit's task is to absorb different forces between the vehicle part and the protective cover during the launch of the spacecraft and during maneuvers in a path up to the moment of separation. By designing inner ends with an integrated enclosing member, a joint is obtained where cohesion and separation can be obtained without too much tension in the surrounding tensioning member. Due to the design of the enclosing body, the inner ends form a new supporting and load-bearing part of the joint.

DESCRIPTION OF THE DRAWINGS The invention will be described in more detail in exemplary embodiments, with reference to fi g. 1, showing a partial cross-section of the inventive dressing.

DESCRIPTION OF EMBODIMENTS A spacecraft is generally designated in the drawing by 1. The craft comprises a protective cover 3 separable from a craft part 2, which is arranged to surround satellite equipment arranged at the craft part. A dressing 4 is arranged to hold the two parts 2, 3 together for the part of the time that the dressing is used.

The joint 4 has a first outer end 5 at an upper part of the vehicle part 2 and a second outer end 6 at a lower part of the protective cover 3. These ends are radially outward relative to a center line through the spacecraft. Furthermore, the joint has one or more stirrups 7 distributed around the periphery of the grooves 5, 6. A clamping member 8 runs around or through the stirrups 7 and pushes them radially inwards against the bridges 5, 6. 1:14, 10 15 20 25 30 '1 The stirrups 7 are arranged to join the outer ridges 5, 6 when the stirrups are inserted over the bridges. By applying a force to the tensioning belt 8, the stirrups are pressed radially inwards against the outer fl ends 5, 6. The radial force is transmitted from the tensioning belt 8 to a clamping force, which clamps the fl ends 5, 6 against each other. According to the prior art, the radially acting force is transmitted by the inner surfaces of the stirrups having outwardly sloping release angles. To avoid the risk of self-locking due to friction, the outer surfaces of the braces should be slightly sloping so that they fit in shape with the inner surfaces of the jumpers.

The joint further has a first inner 9 9 arranged at the vehicle part and a second inner 11 arranged at the protective cover. These fl extends in a radial direction towards an imaginary center line through the spacecraft. An enclosing member 10 is integrally formed with the first inner flange 9 and comprises a clamping lip 10a, which at least partially abuts against an upper abutment surface 11a of the second inner flange 11.

By the combination of the first inner end 9 and enclosing means 10, the second inner end 11 is surrounded on each side.

The first inner flange 9 in the embodiment shown extends substantially in the same plane as the first outer flange 5. Thereby a support surface is formed on the upper side of the first outer flange and on the first inner flange. A lower abutment surface 11b on the second inner end 11 rests against the part of the support surface formed on the first inner end.

The clamping lip 10a is essential for fixing the second inner end in both the radial direction and the longitudinal direction. The clamping lip may abut against the upper abutment surface of the other inner end. Both the surface of the clamping lip 10a directed towards the second inner end 11 and the upper abutment surface 11a are given in the embodiment shown the angle ß in relation to the normal plane. This should exceed 0 ° to avoid the risk of self-locking due to friction. The angle ß can be varied, provided that measures are taken to eliminate the risk of self-locking when mounted. The two surfaces can also have different angles in relation to the normal plane. e u - v. va ...

When the stirrups 7 are released by cutting the prestressed belt 8, the separation of the different parts begins. The stirrups 7 surrounding the outer flanges 5, 6 are pressed radially outwards and removed. The protective cover 3 can be divided into at least two separable parts along a longitudinal direction of the protective cover 3. When the tensioning strap 8 is released, the separation of these protective cover parts begins. Because the protective cover 3 can be separated into at least two separate parts, this movement is possible. The vehicle part 2 continues along the planned path at the same time as the released protective cover 3 in at least two separate parts falls down towards the atmosphere. 5.8 17, é COMPILATION OF REFERENCE DESIGNATIONS Mouthpiece 1 Vessel part 2 Protective housing 3 5 Joints 4 First outer flange 5 Second outer flange 6 Jumper 7 Clamping means 8 10 First inner flange 9 Enclosing ear 10 Clamping lip 10a Second inner surface 15a Second inner surface llb angle ß now.

Claims (6)

1.: apan 10 15 20 25 2. I ~ H n a. w. . . . : '_' z z 0: o! o I u. c v; vc t o u om u s n ß a p '' ''17 n u u u u - o 4 o n u o n. i' 3. CLAIMS 1. A connection (4) to a spacecraft (1) for holding together a vehicle part (2) and a protective cover (3) separable from the vehicle part (2), along longitudinal section divisible into at least two protective cover parts (3a, 3b), which connection (4) comprises a first outer flange (2) arranged for the vehicle part (2) 5.), a second outer ((6) and a number of stirrups (7) arranged for the protective casing, arranged to be distributed according to the (of the ((5, 6.) circumferentially transmitting radial forces from a clamping means (8) surrounding the stirrups (5, 6), whereby the outer ends (5, 6) are arranged to be connected, characterized in that the connection (4) further comprises a to the vehicle part (2) ) arranged radially inwardly directed first inner end (9) and a radially inwardly directed second inner end (11) arranged to the protective housing (3), the first inner end (9) being integrally formed with at least one enclosing member (10), which surrounds the second inner flange (11) at least partially. Bandage (4) according to claim 1, characterized in that the enclosing member (10) is arranged to engage with the second inner end (11) along the entire extent of the end. A dressing according to claim 1, characterized in that the enclosing member (10) is arranged to engage the second inner end (11) at spaced apart areas distributed along the periphery of the ends. A dressing according to claim 2, characterized in that the enclosing member (10) comprises a clamping lip (10a), which is arranged to abut against an upper abutment surface (11a) on the second inner end. A dressing according to claim 3, characterized in that the enclosing member comprises a plurality of clamping lips (10a), which are arranged to abut against an upper abutment surface (11a) on the second inner end (11). Bandage according to Claim 1, characterized in that the protective cover (3) surrounds at least one satellite which is attached to the vehicle part (2).