WO2001002248A1 - Method and device for the separation of a satellite from a carrier rocket - Google Patents

Method and device for the separation of a satellite from a carrier rocket Download PDF

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Publication number
WO2001002248A1
WO2001002248A1 PCT/SE2000/001292 SE0001292W WO0102248A1 WO 2001002248 A1 WO2001002248 A1 WO 2001002248A1 SE 0001292 W SE0001292 W SE 0001292W WO 0102248 A1 WO0102248 A1 WO 0102248A1
Authority
WO
WIPO (PCT)
Prior art keywords
bolt
housing
designed
piston
tension
Prior art date
Application number
PCT/SE2000/001292
Other languages
French (fr)
Inventor
Torbjörn Andersson
Jörgen REMMELG
Örjan ARULF
Göran Månsson
Hans Grunditz
Original Assignee
Saab Ericsson Space Ab
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from SE9902555A external-priority patent/SE9902555L/en
Application filed by Saab Ericsson Space Ab filed Critical Saab Ericsson Space Ab
Publication of WO2001002248A1 publication Critical patent/WO2001002248A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/645—Separators

Definitions

  • the present invention relates to a method according to the pre-characterising part of claim 1.
  • the invention also relates to a device according to the pre-characterising part of claim 5.
  • a known mechanical element for separably connecting a satellite to a carrier rocket is a so-called clamping band.
  • This comprises a circular band with heels.
  • the band may either be a flexible band or may be composed of rigid, circularly curved parts, articulated to one another, which together form a circle.
  • the said heels bear against cylindrical structural parts of the satellite and the adapter of the carrier rocket.
  • the band is tensioned, the heels exerting compressive forces on the parts.
  • the tensioning means that tensile energy is stored in the band and in adjoining structural parts, which is released when the satellite separates from the carrier rocket.
  • the band has an opening mechanism, which in the known case opens the band instantaneously. This releases the tensile energy, which is converted into kinetic energy in the form of vibrations, translational movements primarily as movements of the band ends. In the process, energy losses occur.
  • the conversion of energy from tensile to kinetic energy gives rise to vibrations, which may damage sensitive equipment in the satellite, and to band movements, which may interfere with the satellite.
  • the opening mechanism usually works with a pyrotechnically operated separation device, and this carries with it a risk of scattering small particles, splinters and the like.
  • One object of the present invention in the clamping band separation of satellites from a carrier rocket or other separation in space using the said separation system, is to achieve a method, which will help to improve the performance of the separation system by eliminating or at least reducing the above-mentioned disadvantages. This is achieved, in the method described in the introduction, by the characteristic features of claim 1.
  • the invention has the further object of producing an improved device of the type specified in the pre-characterising part of claim 5. This is achieved by the features specified in the characterising part of claim 5.
  • figure 1 shows a diagrammatic side view of a clamping band with a band opening mechanism.
  • Figure 2 in a longitudinal section, shows an example of a release mechanism, which produces a continuous opening process in the clamping band.
  • Figures 3a and 3b in side outline views forming a 90° angle with one another, illustrate a release mechanism that produces a discontinuous opening process, figures 3c and 3d illustrating different stages of the said process.
  • Figure 4 shows an alternative embodiment of a release mechanism.
  • Figures 5a and 5b show yet a further alternative embodiment of a release mechanism, before and after release.
  • 1 generally denotes a clamping band with a band 2 and heels 3.
  • the two ends of the band, which are arranged in loops 4, are held together by a band opening mechanism 5.
  • the latter in the known case comprises a pyrotechnically operated cutter designed, for example, to cut off a bolt holding the ends of the band together.
  • the band opening mechanism is designed to produce such a precisely timed process that the disadvantages occurring with known opening mechanisms are essentially eliminated.
  • the band opening mechanism is designed to produce a separation process, which gives a continuous or discontinuous retardation of the release of the band ends from one another. Examples of such mechanisms will be described below with reference to figures 2, 3a-3d and figure 4.
  • 6 denotes a housing with a cylindrical bore 6a, in which a piston 7 is axially moveable
  • a piston rod 7a, connected to the piston 7, is supported in a bore 6b coaxial with the bore 6a
  • the piston 7 and the housing 6 define an annular chamber 8, the size of which is dependent upon the axial position of the piston 7 in the bore 6a
  • a cap 9, which with the piston 7 defines a chamber 10 is screwed on to that end of the piston 7 remote from the piston rod 7a
  • a duct 1 1 passing through the piston 7 and opening out into the chamber 10 at the centre thereof provides a connection between the chambers 8 and 10
  • valve needle 12 which is axially fixed between the cap 9 and said opening of the duct 1 1 into the chamber 10
  • the tension in the clamping band in figure 1 acts between the piston rod 7a and a surface 6c on the housing 6, that is to say it endeavours to reduce the volume of the chamber 8
  • the chamber 8 is filled with a viscous material such as lead, for example, which is prevented by the valve needle 12 from flowing into the chamber 10 by way of the duct 1 1
  • the release device 13 In order to separate the satellite from the earner rocket the release device 13 is acted upon, the pin 13a thereof laterally displacing the needle 12, so that the opening of the duct 11 is exposed and the lead can be forced out of the annular chamber 8 and by way of the duct 1 1 into the chamber 10 At this, the piston rod 7a moves relative to the housing 6 according to a continuous process, which lasts for a predetermined length of time, du ⁇ ng which the shock t ⁇ ggered by the tensile energy released in the separation is allowed to act
  • the device according to figures 3a, 3b comp ⁇ ses a cylindrical housing 14, between the ends 14a, 14b of which there is a fairly thin cylindrical wall 14c, which is reinforced with a steel band 15, the width of which is somewhat less than the distance between the ends 14a, 14b
  • the steel band which is resilient, is wound around the wall a predetermined number of times, and in order to prevent it unwinding, the steel band is held together by a evlar thread 16
  • a bolt 17 which at the end 14a is screwed into a nut 18.
  • a thrust washer is arranged between the nut 18 and the head 17a of the bolt 17. The tensioning of the clamping band is intended to be taken up between the outside 14bl of the end 14b and the bolt 17.
  • the device according to figures 3a, 3b is designed to produce a discontinuously decreasing tension in the clamping band 1.
  • a filament 1 designed to burn off the Kevlar thread 1 , which holds the coiled steel band 15 together. Without the support of the Kevlar thread 16 this is coiled up and the supporting function of the band coil ceases.
  • the band coil no longer absorbs the forces acting between the ends 14a, 14b, the wall 14c is not able to do this without collapsing, as is shown in figure 3d.
  • two housings with associated parts such as steel band, Kevlar thread and support thread can be arranged on a longer bolt 17 than that shown in the embodiment in figure 3a. Release at two successive times means that the tension in the clamping band 1 is released in two discontinuous stages.
  • the alternative embodiment, shown in figure 4, of a device designed to produce a discontinuously decreasing tension in the clamping band 1 comprises a housing 22 with two cylindrical ends 22a, 22b and walls 22c, 22d telescopically displaceable in one another.
  • a vertical bolt 23 with head 23a, which is designed to bear against the end 22a, runs through the housing 22.
  • a toroidal body 24 of toughened glass enclosing the bolt 23 is arranged in the housing 22. The said body defines a certain distance between the ends 22a, 22b.
  • the tension of the clamping band 1 is designed to be taken up between the bolt 23 and the outer surface 22b 1 of the end 22b.
  • a needle 25 Arranged in the wall 22d is a needle 25, which is directed radially towards the body 24 and can preferably be actuated pyrotechnically, and the function of which is to pierce the body 24 when the tension in the clamping band 1 is to be released. The said body is then smashed instantaneously and its function as support element between the ends 22a, 22b ceases.
  • 26 and 27 denote two rotationally symmetrically housing halves, which are also mirror-symmetrical with one another and which each have a cavity 28, 29 with bottom 28a, 29a and side wall 28b, 29b, which together describe a truncated cone.
  • a bolt 30a and 31 is slidably supported, one end 30, 31a of which is designed to be operatively connected to the respective end of the clamping band 2.
  • the other end of each bolt 30 and 31 has a head 30b, 31b located in the respective cavity 28, 29, the surface of which head 30b 1, 3 lb 1 facing the bolt has the shape of the outer surface of a truncated cone.
  • the cavities 28, 29 together form a space in which, in addition to the two bolt heads 30b, 31b, there is a locking body 32 holding the bolt heads 30b, 31b together.
  • the said body is rotationally symmetrical and divided radially into at least two, preferably three appropriately identical segmental sections.
  • the locking body 32 has an outer surface 32a, which is complementary to the side walls 28b, 29b of the cavities 28, 29 and an inner surface 32b, which is complementary to boundary surfaces of the bolt heads when these are assembled as shown in figure 5a.
  • a locking element 34 that can be opened by a pyrotechnic release mechanism 33, for example, is to hold the housing halves 26, 27 together against the action of the forces originating from the tension of the clamping band 1 and acting on the housing halves 26, 27 by way of the surfaces 28b, 29b, 32a, 32b and 30bl, 31bl .

Abstract

The invention relates to a method in the separation of a satellite from a carrier rocket. The said rocket and the satellite are connected by means of a clamping band in which, in order to maintain the connection, tensile energy is stored, which is released in the separation. The release of the tensile energy is made to follow a timed process. The invention also relates to a device in a clamping band connecting a satellite to a carrier rocket. In the clamping band there is a tension for maintaining the connection between the satellite and the carrier rocket, which is released in the separation. The ends of the clamping band are joined by a mechanism designed to release the tension according to a timed process.

Description

Method and device for the separation of a satellite from a carrier rocket
The present invention relates to a method according to the pre-characterising part of claim 1. The invention also relates to a device according to the pre-characterising part of claim 5.
A known mechanical element for separably connecting a satellite to a carrier rocket is a so- called clamping band. This comprises a circular band with heels. The band may either be a flexible band or may be composed of rigid, circularly curved parts, articulated to one another, which together form a circle. In the assembled state, the said heels bear against cylindrical structural parts of the satellite and the adapter of the carrier rocket. In order to achieve a solid connection between the said parts the band is tensioned, the heels exerting compressive forces on the parts. The tensioning means that tensile energy is stored in the band and in adjoining structural parts, which is released when the satellite separates from the carrier rocket. For this purpose the band has an opening mechanism, which in the known case opens the band instantaneously. This releases the tensile energy, which is converted into kinetic energy in the form of vibrations, translational movements primarily as movements of the band ends. In the process, energy losses occur.
It is obvious that the greater the payload, that is to say the heavier the satellite, the tighter the clamping band has to be tensioned and the greater the tensile energy that is stored in the band and adjoining structural parts and that will be released in the separation.
The conversion of energy from tensile to kinetic energy gives rise to vibrations, which may damage sensitive equipment in the satellite, and to band movements, which may interfere with the satellite. The opening mechanism usually works with a pyrotechnically operated separation device, and this carries with it a risk of scattering small particles, splinters and the like.
One object of the present invention, in the clamping band separation of satellites from a carrier rocket or other separation in space using the said separation system, is to achieve a method, which will help to improve the performance of the separation system by eliminating or at least reducing the above-mentioned disadvantages. This is achieved, in the method described in the introduction, by the characteristic features of claim 1.
The invention has the further object of producing an improved device of the type specified in the pre-characterising part of claim 5. This is achieved by the features specified in the characterising part of claim 5.
Further features of the invention will be apparent from the dependent claims. The invention will be explained in more detail below with reference to the attached drawing, in which figure 1 shows a diagrammatic side view of a clamping band with a band opening mechanism. Figure 2, in a longitudinal section, shows an example of a release mechanism, which produces a continuous opening process in the clamping band. Figures 3a and 3b, in side outline views forming a 90° angle with one another, illustrate a release mechanism that produces a discontinuous opening process, figures 3c and 3d illustrating different stages of the said process. Figure 4 shows an alternative embodiment of a release mechanism. Figures 5a and 5b show yet a further alternative embodiment of a release mechanism, before and after release.
In figure 1, 1 generally denotes a clamping band with a band 2 and heels 3. The two ends of the band, which are arranged in loops 4, are held together by a band opening mechanism 5. The latter in the known case comprises a pyrotechnically operated cutter designed, for example, to cut off a bolt holding the ends of the band together.
According to the present invention the band opening mechanism is designed to produce such a precisely timed process that the disadvantages occurring with known opening mechanisms are essentially eliminated.
To this end, the band opening mechanism is designed to produce a separation process, which gives a continuous or discontinuous retardation of the release of the band ends from one another. Examples of such mechanisms will be described below with reference to figures 2, 3a-3d and figure 4. In figure 2, 6 denotes a housing with a cylindrical bore 6a, in which a piston 7 is axially moveable A piston rod 7a, connected to the piston 7, is supported in a bore 6b coaxial with the bore 6a The piston 7 and the housing 6 define an annular chamber 8, the size of which is dependent upon the axial position of the piston 7 in the bore 6a A cap 9, which with the piston 7 defines a chamber 10, is screwed on to that end of the piston 7 remote from the piston rod 7a A duct 1 1 passing through the piston 7 and opening out into the chamber 10 at the centre thereof provides a connection between the chambers 8 and 10
The said connection is, however, closed by a valve needle 12, which is axially fixed between the cap 9 and said opening of the duct 1 1 into the chamber 10 A release mechanism 13 with a pin 13a, aligned transversely to the valve needle and interacting therewith, is mounted in the wall of the cap 9, the said pin being designed to displace the valve needle laterally so that its tip no longer closes the duct opening
The tension in the clamping band in figure 1 acts between the piston rod 7a and a surface 6c on the housing 6, that is to say it endeavours to reduce the volume of the chamber 8 The chamber 8 is filled with a viscous material such as lead, for example, which is prevented by the valve needle 12 from flowing into the chamber 10 by way of the duct 1 1
In order to separate the satellite from the earner rocket the release device 13 is acted upon, the pin 13a thereof laterally displacing the needle 12, so that the opening of the duct 11 is exposed and the lead can be forced out of the annular chamber 8 and by way of the duct 1 1 into the chamber 10 At this, the piston rod 7a moves relative to the housing 6 according to a continuous process, which lasts for a predetermined length of time, duπng which the shock tπggered by the tensile energy released in the separation is allowed to act
The device according to figures 3a, 3b compπses a cylindrical housing 14, between the ends 14a, 14b of which there is a fairly thin cylindrical wall 14c, which is reinforced with a steel band 15, the width of which is somewhat less than the distance between the ends 14a, 14b The steel band, which is resilient, is wound around the wall a predetermined number of times, and in order to prevent it unwinding, the steel band is held together by a evlar thread 16 At the ends there are central bores for a bolt 17, which at the end 14a is screwed into a nut 18. A thrust washer is arranged between the nut 18 and the head 17a of the bolt 17. The tensioning of the clamping band is intended to be taken up between the outside 14bl of the end 14b and the bolt 17.
The device according to figures 3a, 3b is designed to produce a discontinuously decreasing tension in the clamping band 1. For releasing the device there is a filament 1 designed to burn off the Kevlar thread 1 , which holds the coiled steel band 15 together. Without the support of the Kevlar thread 16 this is coiled up and the supporting function of the band coil ceases. When the band coil no longer absorbs the forces acting between the ends 14a, 14b, the wall 14c is not able to do this without collapsing, as is shown in figure 3d.
In figures 3a, 3b the space between the ends is covered by means of a rubber sleeve 21. Its sole function is to serve as protection and it plays no part in the functioning of the device.
It will be obvious that according to an alternative embodiment two housings with associated parts such as steel band, Kevlar thread and support thread can be arranged on a longer bolt 17 than that shown in the embodiment in figure 3a. Release at two successive times means that the tension in the clamping band 1 is released in two discontinuous stages.
The alternative embodiment, shown in figure 4, of a device designed to produce a discontinuously decreasing tension in the clamping band 1 comprises a housing 22 with two cylindrical ends 22a, 22b and walls 22c, 22d telescopically displaceable in one another. A vertical bolt 23 with head 23a, which is designed to bear against the end 22a, runs through the housing 22. A toroidal body 24 of toughened glass enclosing the bolt 23 is arranged in the housing 22. The said body defines a certain distance between the ends 22a, 22b. The tension of the clamping band 1 is designed to be taken up between the bolt 23 and the outer surface 22b 1 of the end 22b. Arranged in the wall 22d is a needle 25, which is directed radially towards the body 24 and can preferably be actuated pyrotechnically, and the function of which is to pierce the body 24 when the tension in the clamping band 1 is to be released. The said body is then smashed instantaneously and its function as support element between the ends 22a, 22b ceases.
The construction and function of another mechanism 5 according to the invention will be explained with reference to figures 5a, 5b. In the figures, 26 and 27 denote two rotationally symmetrically housing halves, which are also mirror-symmetrical with one another and which each have a cavity 28, 29 with bottom 28a, 29a and side wall 28b, 29b, which together describe a truncated cone. At the bottom 28a, 29 of each cavity there is a central bore 26a, 27a, in which a bolt 30a and 31 is slidably supported, one end 30, 31a of which is designed to be operatively connected to the respective end of the clamping band 2. The other end of each bolt 30 and 31 has a head 30b, 31b located in the respective cavity 28, 29, the surface of which head 30b 1, 3 lb 1 facing the bolt has the shape of the outer surface of a truncated cone.
With the housing parts 26, 27 assembled as in figure 5a, the cavities 28, 29 together form a space in which, in addition to the two bolt heads 30b, 31b, there is a locking body 32 holding the bolt heads 30b, 31b together. The said body is rotationally symmetrical and divided radially into at least two, preferably three appropriately identical segmental sections. The locking body 32 has an outer surface 32a, which is complementary to the side walls 28b, 29b of the cavities 28, 29 and an inner surface 32b, which is complementary to boundary surfaces of the bolt heads when these are assembled as shown in figure 5a.
The function of a locking element 34 that can be opened by a pyrotechnic release mechanism 33, for example, is to hold the housing halves 26, 27 together against the action of the forces originating from the tension of the clamping band 1 and acting on the housing halves 26, 27 by way of the surfaces 28b, 29b, 32a, 32b and 30bl, 31bl .
It should be mentioned that it is important for the function of the mechanism 5 that the housing halves 26, 27 are supported so that they can move freely on the bolts 30, 31. For this purpose there are ball bearings 35 in the bore 26a, 27a. When the release mechanism 33 opens the locking element 34, designed, for example, as a shackle, the following happens under the effect of the above-mentioned forces acting on the housing halves 26, 27, the housing halves 26, 27 slide away from one another on the bolts 30, 31 and reach a position in which segments of the locking body 32 are no longer held together by the housing halves, as shown in figure 5b The result of this is that the bolts 30, 31 and hence also the ends of the clamping band can move freely
It must be noted, however, that on opening of the locking element 34 the housing halves 26, 27 are set in motion first, followed by the bolts 30, 31 , and that the speed of the housing halves 26, 27 is thereby considerably greater than the speed of the bolts 30, 31 This means that duπng a timed process the housing halves absorb the greater part of the energy stored in the locking band, from which it follows that the remaining energy is capable of subjecting the ends of the clamping band only to moderate loads It is obviously possible, through seπes connection of two devices according to figure 4, to relieve the load in two stages at an interval from one another
It is also obvious that many retardation mechanisms already known in the art can be used to achieve release of the tension in the clamping band 1 as descπbed in the invention As an example of such a known mechanism, mention will be made here of a retardation mechanism operating on the flywheel principle, known from US-A-5,603,595

Claims

Claims
1. Method in the separation of a satellite from a carrier rocket, the said rocket and the satellite being connected by means of a clamping band (2) in which, in order to maintain the connection, tensile energy is stored, which is released in the separation, characterised in that the release of the tensile energy is made to follow a timed process.
2. Method according to claim 1, characterised in that the process is continuous
3. Method according to claim 1 , characterised in that the process is discontinuous.
4. Method according to claim 1 , characterised in that the process is a combination of continuous and discontinuous.
5. Device in a clamping band (2) connecting a satellite with a carrier rocket, there being a tension present in the clamping band in order to maintain the connection between the satellite and the carrier rocket, which tension is released in the separation, characterised in that the ends of the clamping band (2) are joined by a mechanism 5 designed to release the tension according to a timed process.
6. Device according to claim 5, characterised in that the mechanism (5) is designed to achieve separation under continuously decreasing tension.
7. Device according to claim 5, characterised in that the mechanism (5) is designed to achieve separation under discontinuously decreasing tension.
8. Device according to claim 5, characterised in that the mechanism (5) is designed to achieve separation under a combination of continuously and discontinuously decreasing tension. Device according to claim 7, characterised in that the mechanism (5) is designed to achieve separation in at least two discontinuous stages at an interval from one another
Device according to claim 5, characterised in that the mechanism (5) compπses a housing (6) with a central bore (6a), in which a piston (2) is moveable, the piston rod of which is supported so that it can slide in the housing (6), the piston (7) and the housing (6) between them defining an annular chamber (8) filled with a viscous mateπal such as lead, for example, that a cap (9) is arranged on the end of the piston (7) remote from the piston rod (7a), which cap with the piston encloses a space (10), that a duct (1 1), the opening (1 la) of which lies at the centre of the piston (7) runs through the piston (7) between the annular chamber (8) and the space ( 10), that the opening (1 la) is displaced by means of the tip (12a) of a valve needle (12), which is fixed between the cap (9) and the piston (7), and that in order to achieve the displacement of the duct (1 1) a release element ( 13) is fitted in the cap (9) with a pin (13a) acting against the needle ( 12) duπng release
Device according to claim 5, characterised in that the mechanism (5) compπses a cyhndπcal housing (14) with ends ( 14a, 14b) and between them a cylindrical wall (14c), a bolt (17), which is fixed in one end (14a) and supported in the other end (14b) so that it can slide, the tension of the clamping band (1) being intended to act between the bolt and an outer surface ( 14b 1 ) on the other end ( 14b), a band ( 15) of a stiffly resilient matenal, such as spnng steel, the width of which is somewhat less than the distance between the ends (14a, 14b), as support for the cylinder wall (14c) being wound around this and held together by means of a thread (16) of fusible matenal, such as Kevlar, for example, and a filament (20) being designed to burn off the thread (16), as a result of which the steel band ( 15) is coiled up so that its support function ceases and the cylinder wall (14c) consequently collapses
Device according to claim 1 1 , characterised in that a gaiter (21) of a rubber-like mateπal engages with the ends (14a, 14b) in order to form a closed space therewith
13. Device according to claim 5, characterised in that the mechanism (5) comprises a housing (22) with two cylindrical ends and walls telescopically displaceable in one another, a bolt (23) passing centrally (23a) through the housing and provided with a head (23), which bolt is supported at the ends (22a, 22b) so that it can slide, a toroidal body (24) arranged in the housing around the bolt and made of a material that is smashed when it is subjected to a pulse, such as toughened glass, which defines a certain interval between the ends (22a, 22b), the tension of the clamping belt being designed to be taken up between the bolt (23) and the outside (22b 1) of the end (22b) furthest from the head (23a) of the bolt, and that a release element with a tip (25) directed radially towards the body (24) and designed to smash the body (24) is arranged in one wall (22d).
14. Device according to claim 5, characterised in that the mechanism (5) comprises two housing halves (26, 27) preferably of mirror-symmetrical and rotationally symmetrical shape, which are each formed with a cavity (28, 29), the bottom (28a, 29a) and walls (28b, 29b) of which describe a truncated cone and in the centre of the bottom (28a, 29a) have a through-bore (26a, 27a) for a bolt (30, 31) connected to each end of the clamping band, the head (30b, 31b) of which bolt has a cone-shaped surface (30bl, 3 lbl ) tapering towards the bolt (30, 31) and a rotationally symmetrical locking body (32), formed with an outer surface (32a), which is complementary to the walls (28a, 29b; 29a, 29b) of the cavities (28, 29) in the housing parts when these are assembled and with an inner surface (28b), which is complementary to the boundary surfaces of the bolt heads (30b, 31b) when these are assembled, which locking body (32) is divided radially into at least two sections and a locking element (34), holding the housing halves (26, 27) together in the pre-release position of the mechanism, and capable of being opened by the release mechanism (33).
15. Device according to claim 14, characterised in that the bolt is supported by ball bearings (35) in the bore.
6. Device according to claim 14 or 15, characterised in that the number of sections is three.
PCT/SE2000/001292 1999-07-02 2000-06-19 Method and device for the separation of a satellite from a carrier rocket WO2001002248A1 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
SE9902555-3 1999-07-02
SE9902555A SE9902555L (en) 1999-07-02 1999-07-02 Method and arrangement of a satellite's separation from a carrier rocket
US56662800A 2000-05-08 2000-05-08
US09/566,628 2000-05-08

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WO2001002248A1 true WO2001002248A1 (en) 2001-01-11

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001085542A1 (en) * 2000-05-10 2001-11-15 Saab Ericsson Space Ab Device and method for connecting two parts of a craft
WO2012090419A1 (en) 2010-12-27 2012-07-05 川崎重工業株式会社 Coupling/uncoupling mechanism and cosmonautic vehicle provided with same
CN110239748A (en) * 2019-07-11 2019-09-17 航天科工火箭技术有限公司 Firer's separator between star

Citations (3)

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Publication number Priority date Publication date Assignee Title
EP0493211A1 (en) * 1990-12-21 1992-07-01 AEROSPATIALE Société Nationale Industrielle Remotely releasable tensioning means
US5197695A (en) * 1991-03-04 1993-03-30 Saab Space Aktiebolag Locking device for a band or the like, subject to a tensile force
EP0905022A1 (en) * 1997-09-26 1999-03-31 Construcciones Aeronauticas, S.A. System for attaching and separating satellites

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0493211A1 (en) * 1990-12-21 1992-07-01 AEROSPATIALE Société Nationale Industrielle Remotely releasable tensioning means
US5197695A (en) * 1991-03-04 1993-03-30 Saab Space Aktiebolag Locking device for a band or the like, subject to a tensile force
EP0905022A1 (en) * 1997-09-26 1999-03-31 Construcciones Aeronauticas, S.A. System for attaching and separating satellites

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001085542A1 (en) * 2000-05-10 2001-11-15 Saab Ericsson Space Ab Device and method for connecting two parts of a craft
US6454214B1 (en) 2000-05-10 2002-09-24 Saab Ericsson Space Ab Device and method for connecting two parts of a craft
WO2012090419A1 (en) 2010-12-27 2012-07-05 川崎重工業株式会社 Coupling/uncoupling mechanism and cosmonautic vehicle provided with same
JP2012136131A (en) * 2010-12-27 2012-07-19 Kawasaki Heavy Ind Ltd Coupling/separating mechanism and space navigation body including the same
US9284072B2 (en) 2010-12-27 2016-03-15 Kawasaki Jukogyo Kabushiki Kaisha Coupling/uncoupling mechanism and cosmonautic vehicle comprising the same
EP3470340A2 (en) 2010-12-27 2019-04-17 Kawasaki Jukogyo Kabushiki Kaisha Coupling/uncoupling mechanism and cosmonautic vehicle comprising the same
CN110239748A (en) * 2019-07-11 2019-09-17 航天科工火箭技术有限公司 Firer's separator between star
CN110239748B (en) * 2019-07-11 2020-11-03 航天科工火箭技术有限公司 Inter-satellite fire separation device

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