SEPARATING DEVICE

Abstract: A separating device for quick mutual separation of objects and vehicles, especially air and space vehicles, comprises attaching elements, attached to the vehicle and the object, respectively, and arranged to interact separably in holding together the vehicle and the object. According to the invention, such a separating device is characterized primarily in that the first attaching element (1) comprises a casing with an internal first cylindric portion (2). In it a first piston (3) is arranged movable, with slide fitting, so that the portion is separated into a first (4) and a second chamber (5). The first attaching element (1) shows a preferably conically generated first grip part (6). A second attaching element (8) has a second grip part (7) which can be separably attached to the first grip part (6) with a shrinking fit for frictional connection. A connecting channel (11, 12) connects the second chamber (5) with the surfaces (9, 10) of the grip parts. A source of pressure (14, 28) is arranged to increase essentially instantaneously the fluid pressure in the first chamber (4) so that the piston (3) will cause a liquid to separate the surfaces (9, 10) via the connecting channel (11, 12), releasing the grip parts (6, 7) from each other, for the separation of the object and the vehicle.

Description: SEPARATING DEVICE The present invention relates to a separating device for quick mutual separation of objects and vehicles, especially air and space vehicles, comprising attaching elements attached to the air vehicle and the object, arranged to interact separably in holding together the vehicle and the object. Ihe concepts of "vehicle" and "object" have in this connection a relatively wide meaning. By vehicle it is meant every movable carrier of one or more objects. The carrier may e.g. be provided with its own driving device, such as a jet motor or a rocket engine or other driving device. However, the carrier may also consist of a ballistic projectile or the like. The object may in turn consist of a missile, bomb or satellite that is to be sepa¬ rated from a carrier rocket, or may be some other arbitrary object. It is evident from the examples named above that separating devices of the above-mentioned type can have numerous applica¬ tions. In all cases, the aim is to achieve a precisely control¬ lable separation. Hitherto existing separating devices of this type have in many cases been complicated and expensive, and also they have often shown inadequate precision in use. The object of the present invention is therefore to provide a separating device of the introductorily-mentioned type which has a relatively simple construction and is therefore relatively inexpensive and which admits a precisely controllable separation. According to the invention such a separating device is charac- terized primarily in that the first attaching element comprises a casing with an internal first cylindric portion in which a first piston is arranged movable in the axial direction of the portion, sliding essentially liquidtightly along the wall of the portion, separating the portion into a first and a second chamber, the first attaching element comprising a preferably conically generated first grip part, whereas the second attach¬ ing element is formed with a second grip part that is separ¬ ably attachable to the first grip part with a shrinking fit, so that, the surfaces of the grip parts are in fractional con- nection, the arrangement being that al least one connecting channel is arranged to connect the said second chamber with the said surfaces, a source of pressure being arranged to increase principally instantaneously the fluid pressure in the first chamber so that the piston will .cause a liquid to separate the surfaces via the connecting channel, whereby the grip parts are released from each other, for the separation of the object and the vehicle. The first attaching element can be attached either to the vehicle or the object, and this applies also to the second attaching element. The first and second grip parts, both of which are preferably provided with conically generated external and internal surfaces, may also optionally be included in the first and the second attaching element, respectively. Said connecting channel may also be arranged either in the first or the second attaching element. In a preferred embodiment of the separating device according to the invention, the connecting channel comprises a second cyliπd- ric portion having its axis parallel to the axis of the first cylindric portion, in which second cylindric portion a second piston rigidly connected with the first piston is arranged axial- ly movable with essentially liquidtight fitting against the wall of the second cylindric portion, the second piston showing a smaller pressure cross section than the first piston. The above-described embodiment is particularly advantageous when the liquid, i.e. usually an oil, is included in a liquidtight, perforatable container that is placed in the second cylindric portion. A perforating means is then arranged so that when the second piston exerts pressure on the container the perforating means will connect the liquid to said surfaces. The perforating means may e.g. be formed as a cannula point projecting upwards from the bottom of the second cylindric portion. Other embodiments are of course possible. The container is suitably made of a metal foil. The source of pressure can be of different types and can be placed in different places in different embodiments of the separating device according to the invention. It can for instance consist of an electrically detonatable blasting charge. The source of pressure can also be placed outside the first chamber. In the cases when the first attaching element is separably attached in a vehicle-fixed launcher, for instance in a recess in the launcher, which is a suitable embodiment of the separating device according to the invention, the source of pressure is suitably arranged in the launcher, connected to the first chamber with a pressure pipe. The separating device according to the invention will now be described in more detail with reference to the accompanying figures of which: Figure 1 shows a longitudinal section through a separating device; Figure 2 a shows schematically, partly in longitudinal section, a missile with a separating device; Figure 2 b shows the same as Figure 2 a from the front; Figure 3 a shows schematically, partly in longitudinal section, a missile fastened by means of a separating device at a launcher; Figure 3 b shows the same as Figure 3 a from the front; Figure 4 shows a longitudinal section of a portion of a missile and the launcher in Figure 3. In figure 1, 1 designates generally a first attaching element in the form of a casing with a first cylindric portion 2, in which a first piston 3 is arranged axially movable with slide fitting at the wall of the cylindric portion. This first piston 3 separates the first cylindric portion into a first chamber 4 and a second chamber 5. The first attaching element is formed with a first grip part 6 with an internally conically generated wall (i.e. a frustum of a cone). In this first grip part there is fitted with a shrinking fit a second grip part 7 representing a part of a second attaching element 8, which is not shown in detail in this figure. The second grip part 7 is formed as an externally (frustum) conical dowel. The two grip parts are thus in fricioπal connection with their respective surfaces 9, 10. The second grip part 7 is provided with a second cylindric portion 11 with its axis in this case coaxial with the axis of the first cylindric portion. This second cylindric portion 11 is a part of a connecting channel between the second chamber 5 and said surfaces 9, 10. The upper portion of this connecting channel is designated by 12 in the figure. The first piston 3 is rigidly connected with a second piston 13, which is fitted with liquidtight fitting in the second cylindric portion 11 with axial mobility. The connecting channel is filled with oil. In the first chamber 4 there is placed an electrically detonatable blasting charge 14. The first chamber is closed in its upper end by a cap 16. The separating device works so that when a separation of the attaching elements from each other is desired, the blasting charge 14 is caused to detonate, whereupon the developed gas acts with its pressure on the first piston in the first chamber 4. The second piston 13, which shows a smaller pressure cross section than the first piston, is then caused by the first piston 3 to press the liguid in the connecting channels 11, 12 with an in¬ creased pressure relative to the pressure in the first chamber, in order to separate the surfaces 9, 10 from each other, so that the grip parts 6, 7 come loose from each other and the attaching elements are separated, releasing the vehicle and the object from each other. The axial movement of the second piston contribute also to the separation of the grip parts from each other. In figure 2 a, a missile is designated by 17, a first attaching element by 18 and a second attaching element by 19. In this case the first attaching element 18 is thus provided with a first grip part 20, with an external (truncated) conical surface and the second attaching element, attached to the missile with an in¬ ternal (truncated) conical surface in the second grip part. An embodiment comprising a vehicle-fixed launcher 21 with a re- cess 22 is shown in figure 3 a. In this recess there is a first attaching element 24 attached with a cotter 23. Two cylinder/ piston elements 25 are also fastened in the launcher 21. In figure 4, this construction is shown more in detail. The first chamber 26 of the first attaching element 24 is connected with a pressure tube 27 to a source of pressure 28 which can contain a detonatable blasting charge or be of other kind. This source of pressure is also connected to the cylinder/piston elements 25 via pressure tubes 29, 30. Thus, the source of pressure 28 acts simultaneously on the first piston 32 in the first attaching element 24 and the pistons in the piston/cylinder elements 25. In the first case the first piston 32 presses down the second piston 33 which presses out liquid to separate the grip parts 34, 35 so that these are released from each other. In the second case the pistons are pressed out in order to work ejectingly on the missile from the launcher, so that the missile is released in the right direction.

Claims: Claims 1. A separating device for quick mutual separation of objects and vehicles, especially air and space vehicles, comprising attach¬ ing elements attached to the air vehicle and the object, ar¬ ranged to interact separably in holding together the vehicle and the object , c h a r a c t e r i z e d in that the first attaching element (1) comprises a casing with an internal first cylindric portion (2) in which a first piston (3) is arranged movable in the axial direction of the portion, sliding essen¬ tially liquidtightly along the wall of the portion, separating the portion into a first (4) and a second chamber (5), the first attaching element (1) comprising a preferably conically generated first grip part (6), whereas the second attaching element (8) is formed with a second grip part (7) that is separably attachable to the first grip part (6) with a shrink- ing fit, so that the surfaces (9, 10) of the grip parts are in frictional connection, the arrangement being that at least one connecting channel (11, 12) is arranged to connect the said second chamber (5) with said surfaces (9, 10), a source of pressure (14, 28) being arranged to increase principally instantaneously the fluid pressure in the first chamber (4) so that the piston (3) will cause a liquid to separate the surfaces (9, 10) via the connecting channel (11, 12), whereby the grip parts (6, 7) are released from each other, for the separation of the object and the vehicle. 2. A separating device according to claim 1, c h a r a c t e¬ r i z e d in that the connecting channel comprises a second cylindric portion (11) having its axis parallel to the axis of the first cylindric portion (2), in which second cylindric portion a second piston (13) rigidly connected with the first piston (3) is arranged axially movable with essentially liquid¬ tight fitting against the wall of the second cylindric portion, the second piston (13) showing a smaller pressure cross section than the first piston (3). 3. A separating device according to claim 2, c h a r a c t e¬ r i z e d in that a liquidtight perforatable container is placed in said second cylindric portion (11) containing said liquid, a perforating means being arranged so that when the second piston (13) exerts pressure on the container the per¬ forating means will connect the liquid to said surfaces (9, 10). 4. A separating device according to any one of claims 1 to 3, c h a r a c t e r i z e d in that said source of pressure consists of an electrically detonatable blasting charge (14) arranged in the first chamber. 5. A separating device according to any one of claims 1 to 3, c h a r a c t e r i z e d in that said source of pressure (18) is arranged outside the first chamber (4). 6. A separating device according to claim 5, c h a r a c t e¬ r i z e d in that the first attaching element (11) is separab¬ ly attached to a vehicle-fixed launcher (21), preferably in a recess (22) in the launcher (21). 7. A separating device according to claim 6, c h a r a c t e- r i z e d in that said source of pressure (28) is placed in the launcher (21), connected to the first chamber with a pressure tube (27, 29, 30).

Inventors: NORRVI HANS, NORRVI, HANS
Applicants: SAAB MISSILES AB, SAAB MISSILES AKTIEBOLAG
Application year: 1989
Main classification: F41F3
IPC codes: F16B4, F42B15, F42B25