WO1999031455A1 - Separation system - Google Patents
Separation system Download PDFInfo
- Publication number
- WO1999031455A1 WO1999031455A1 PCT/US1998/025159 US9825159W WO9931455A1 WO 1999031455 A1 WO1999031455 A1 WO 1999031455A1 US 9825159 W US9825159 W US 9825159W WO 9931455 A1 WO9931455 A1 WO 9931455A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- structural members
- separation system
- slide
- explosive
- sections
- Prior art date
Links
- 238000000926 separation method Methods 0.000 title claims abstract description 159
- 239000002360 explosive Substances 0.000 claims abstract description 100
- 230000003416 augmentation Effects 0.000 claims description 28
- 238000010304 firing Methods 0.000 claims description 24
- 230000000452 restraining effect Effects 0.000 claims description 3
- 238000005474 detonation Methods 0.000 description 21
- 238000005452 bending Methods 0.000 description 13
- 230000002411 adverse Effects 0.000 description 12
- 230000000750 progressive effect Effects 0.000 description 9
- 229910052751 metal Inorganic materials 0.000 description 7
- 239000002184 metal Substances 0.000 description 7
- 230000002708 enhancing effect Effects 0.000 description 5
- 230000035939 shock Effects 0.000 description 5
- 230000002401 inhibitory effect Effects 0.000 description 4
- 230000009977 dual effect Effects 0.000 description 3
- 229920001971 elastomer Polymers 0.000 description 3
- 239000000806 elastomer Substances 0.000 description 3
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000011109 contamination Methods 0.000 description 2
- 239000000314 lubricant Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000002783 friction material Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- CWQXQMHSOZUFJS-UHFFFAOYSA-N molybdenum disulfide Chemical compound S=[Mo]=S CWQXQMHSOZUFJS-UHFFFAOYSA-N 0.000 description 1
- 229910052982 molybdenum disulfide Inorganic materials 0.000 description 1
- 230000002829 reductive effect Effects 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
- F42B15/38—Ring-shaped explosive elements for the separation of rocket parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/56—Turn-sensitive devices using vibrating masses, e.g. vibratory angular rate sensors based on Coriolis forces
- G01C19/5607—Turn-sensitive devices using vibrating masses, e.g. vibratory angular rate sensors based on Coriolis forces using vibrating tuning forks
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P21/00—Testing or calibrating of apparatus or devices covered by the preceding groups
- G01P21/02—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers
-
- 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
Definitions
- the present invention generally relates to separation systems, and in particular, relates to a separation system for separating a first section from a second section.
- the separation system includes first and second structural members (e.g., doublers or doubler plates) which at least initially interconnect the first and second structures, the first structural member being displaced from the second structural member, first and second notches or grooves positioned on the first and second structural members, and an explosive, contained between the first and second structural members, for breaking the first and second structural members at first and second break planes defined by the first and second notches on the first and second structural members, respectively.
- first and second structural members e.g., doublers or doubler plates
- an explosive contained between the first and second structural members, for breaking the first and second structural members at first and second break planes defined by the first and second notches on the first and second structural members, respectively.
- first and second notches are displaced or staggered relative to one another (e.g., nonplanar), such that the first and second break planes of the first and second structural members, respectively, are offset or displaced relative to each other (e.g., nonplanar) to avoid undesireable contact therebetween.
- first and second notches are positionable on the explosive-facing and/or non-explosive facing sides of the first and second structural members, depending upon the particular structural member on which the groove is positioned.
- the first notch on the first structural member is positionable along a first tangential plane defined by the explosive means
- the second notch on the second structural member is positionable such that the second notch is aligned with at least a portion of the explosive means.
- the second notch on the second structural member may be aligned with a center portion of the explosive core of the explosive means, such that the second structural member will fracture or break as the explosive means expands to a circular configuration upon firing.
- the staggered first and second notches on the first and second structural members, respectively are both positionable along tangential planes defined by the explosive means.
- Such tangential planes may be defined by first and second portions of the explosive means (e.g., end portions of explosive means in an unexploded state).
- the first and second displaced break planes defined by the first and second displaced notches on the first and second structural members, respectively may be substantially coincident with the first and second tangential planes defined by the explosive means.
- the first and second structural members or doublers upon firing of the explosive means, are fracturable or severable at the weak points of the first and second structural members (e.g., at the first and second displaced or staggered notches). Due to the displaced or staggered positioning of the first and second notches, a relatively damage-free separation of the first and second sections or structures is facilitated upon such firing of the explosive means since adverse contact between the severed portions of the first and second structural members is minimized.
- the present invention allows the first structure to separate relative to the second structure without the severed portions of the first and second structural members adversely colliding with each other or with the explosive means in an exploded state or otherwise damaging each other after the explosive means is fired to cause severance in the first and second structural members.
- a vehicle having a first structure e.g., payload fairing, door, window, canopy, spacecraft, etc.
- a second structure e.g., core launch vehicle, land-based vehicle, air-based vehicle or sea-based vehicle
- first direction e.g., along a longitudinal axis of the vehicle or the direction of movement of the vehicle
- separation in at least a second direction e.g., at least laterally, relative to the longitudinal axis of the vehicle or at least orthogonally relative to the direction of the vehicle
- separation system of the present invention without adversely contacting the second structure, such that the first structure is free to separate (e.g., be ejected) from the second structure.
- the first structure may separate at least in a second direction (e.g., at least laterally) relative to the second structure moving in at least the first direction (e.g., along the vehicle's longitudinal axis) without the severed portions of the first and second structural members adversely colliding with or otherwise getting hung up on each other or with the expanded explosive container.
- the present invention thus not only provides for separation of the first and second structures by breaking the first and second structural members upon firing of the explosive means, but also reduces the likelihood of undesireable contact by providing at least the displaced or staggered first and second notches, which facilitate severance of the first and second structural members at first and second break planes, the first break plane being offset or displaced from the second break plane.
- the first groove is positionable on one of first and second surfaces (e.g., explosive-facing and nonexplosive-facing sides) of the first structural member, on a first portion of the first structural member to define a line of fracture through the first structural member
- the second groove is positionable on one of the first and second surfaces (e.g., explosive- facing and nonexplosive-facing sides) of the second structural member, on a second portion of the second structural member to define a second line of fracture through the second structural member.
- the first portion of the first structural member is offset or displaced along the first direction from the second portion of the second structural member.
- a relatively damage-free separation at least in the second direction of the first structure relative to the second structure is thus facilitated as the first and second staggered grooves are positionable in the first and second portions of the first and second structural members, respectively.
- the first and second structural members may be configured or affected to bend about or hinge in a selected area.
- bending of the first and second structural members upon firing of the explosive means may be enhanced and controlled, to a certain degree, by providing bend augmentation means.
- the bend augmentation means comprises a reinforced portion on at least one of the first and second structural members or doublers to facilitate bending of the first and second structural members about selected portions thereof while facilitating the fracture of the first and second structural members at, for example, the first and second staggered notches, respectively.
- such reinforced portions of the first and/or second structural members have a thickness greater than the thickness of the first and/or second structural members at the first and second staggered grooves.
- Such reinforced portions may comprise a thickened portion of the doubler and/or a separate doubler plate or stiffening member interconnected to the first and/or second structural member.
- the bend augmentation means comprises at least a first bend augmentation relief portion on at least one of the first and second structural members.
- Such bend augmentation relief portion facilitates bending or hinging of one of the first and second structural members, about or in the relief portion, when the explosive means is fired to fracture at least one of the first and second structural members at a portion thereof displaced from the bend augmentation relief portion.
- the relief portion(s) define(s) a thickness in the first and/or second structural members which is less than that of the first and/or second structural members in other portions.
- Such relief portions may be positioned in upper or lower portions of the structural members, on nonexplosive-facing surfaces of the structural members to further facilitate bending of the structural members away from the explosive means upon firing of the explosive means.
- the first and/or second structural members have weakened sections or grooves to facilitate severance of the first and/or second structural members along lines of fracture defined by such grooves and also include one or more relief portions to facilitate bending of the first and/or second structural members upon detonation of the explosive means
- the thickness of the structural members at the relief portions is greater than the thickness of the structural members at the grooves.
- the separation system further includes a slide plane means interconnected to at least the first structural member.
- the slide plane means functions to at least initially guide one of the first and second sections away from and relative to the other of the first and second sections after at least the first structural member has been severed by firing of the explosive means.
- the slide plane means facilitates a relatively collision-free separation of the first section relative to the second section as the slide plane means guides one of the first and second sections away from the other of the first and second sections along a predetermined plane or path defined by the slide plane means.
- the slide plane means includes at least a first slide member interconnectable to one of the first and second sections.
- the slide plane means is alignable or coplanar with one of the first and second staggered grooves.
- the first slide member is orientable between about 1 ° and about 90° relative to at least one of the first and second structural members.
- first section e.g., payload fairing, payload, door, window, canopy, spacecraft, etc.
- second section e.g., core launch vehicle, land-based vehicle, air- based vehicle or sea-based vehicle
- first direction e.g., along a longitudinal axis of the vehicle
- separation in at least a second direction e.g., at least laterally, relative to the longitudinal axis of the vehicle
- first slide member of the separation system of the present invention without substantially damaging the first or second sections.
- a first slide member angled between about 1 ° and about 90° relative to the first direction at least initially guides the first section away from the second section, at least partially in a second direction, to inhibit undesireable contact between the severed portions of the first and second structural members.
- the present invention thus not only provides for separation of the first and second structures, but also reduces the likelihood of substantial damage from collisions by providing at least the first slide member to guide the first section away from the second section.
- the slide plane means includes first and second opposing slide members or pads for guiding the first section away from the second section after severance of the first and second structural members by firing of the explosive means.
- the first and second slide members define a slide plane which is alignable or substantially coplanar with the first groove on the first structural member, which is coplanar with a first tangential plane defined by a first end portion of the explosive means in an unexploded state.
- the first and second pads are interconnectable to the first and second sections, respectively, and are capable of slidably engaging one another.
- the first and second pads function to at least initially guide the first section away from the second section along at least a first separation plane defined by the first and second pads.
- the first and second pads may be oriented between about 1 ° and about 90° relative to at least one of the first and second sections or relative to at least one of the first and second structural members.
- the first and second pads are oriented about 90° relative to at least one of the first and second structural members to facilitate movement of the first section away from the second section, in a direction, at least initially, perpendicular to at least one of the first and second structural members.
- a low friction coating may be applied to at least one of the first and second pads.
- FIG. 1 illustrates a perspective view of lateral separation of tri-sector payload fairings from a launch vehicle utilizing the separation system of the present invention
- Figs. 2A-2C illustrate cross-sectional progressive views of one embodiment of the separation system of the present invention
- Figs. 3A-3C illustrate cross-sectional progressive views of another embodiment of the separation system of the present invention
- FIGS. 4A-4D illustrate cross-sectional progressive views of still another embodiment of the separation system of the present invention
- Figs. 5A-5C illustrate cross-sectional progressive views of still another embodiment of the separation system of the present invention
- Fig. 6 illustrates a cross-sectional view of another embodiment of the separation system of the present invention for use, for example, in at least longitudinally separating a first section relative to a second section, which can be moving and/or oriented laterally;
- Figs. 7A-7C illustrate cross-sectional progressive views of another embodiment of the separation system of the present invention
- Figs. 8 A-8C illustrate cross-sectional progressive views of another embodiment of the separation system of the present invention.
- Figs. 9A-9C illustrate cross-sectional progressive views of another embodiment of the separation system of the present invention.
- Figs. 10A- 1 OC illustrate cross-sectional progressive views of another embodiment of the separation system of the present invention.
- Figs. 11 A-l 1 C illustrate cross-sectional progressive views of another embodiment of the separation system of the present invention.
- Figs. 1-11 illustrate various features of the separation system of the present invention.
- the separation system of the present invention may be used to at least initially interconnect first and second structures or sections, and thereafter to separate the first structure from the second structure.
- Such separation allows other devices, such as conventional ordnance devices, thrusters, or spring-like devices, to be used to forcibly eject the first structure relative to the second structure.
- the separation system of the present invention may be used in a variety of applications, including, but not limited to, at least lateral separation of tri-sector payload fairings 10a, 10b, 10c from the longitudinally extending core launch vehicle 12, the core launch vehicle traveling along its longitudinal axis 11, as illustrated in Fig. 1.
- the separation system of the present invention can also be used to at least laterally separate bi-sector payload fairings from a core launch vehicle (not shown).
- a core launch vehicle not shown
- the separation systems disclosed herein may be utilized for at least longitudinally separating structures which are at least laterally oriented.
- the separation system 20 includes first and second structural members or doublers 26, 30, an expanding tube explosive charge system having an explosive 36 contained between the first and second doublers 26, 30, and first and second grooves 40, 44 positioned on the first and second doublers 26, 30, respectively.
- the first and second doublers 26, 30 are interconnected to first and second sections or structures 48, 52, which may correspond to, for example, a payload fairing and the core of a launch vehicle, respectively.
- the separation system 20 at least initially interconnects the first and second sections 48, 52, and then functions to separate the first section 48 relative to the second section 52 by breaking or fracturing the first and second doublers 26, 30, as will be described in more detail hereinbelow.
- first and second sections 48, 52 to be separated are at least initially interconnected to each other by the separation system 20 of the present invention.
- first and second doublers 26, 30 of the present invention extend between and are interconnected to the first and second sections 48, 52 to be separated.
- Such interconnection may be accomplished via mechanical fasteners, such as bolts 56a, 56b, which extend through bores in the first and second doublers 26, 30 and through bores in the first and second sections 48, 52 respectively.
- End portions 49, 53 of the first and second sections 48, 52 and inner walls 27, 31, of the first and second doublers 26, 30 define a cavity or space therebetween for containing an explosive charge 36.
- Such explosive 36 may be contained within an elastomer 37, both of which are contained in an expandable metal tube 38.
- the expandable tube 38 which is interconnected to the second section 52 via a restraining strap 55 provides a contamination free separation of the first section 48 relative to the second section 52 when the explosive 36 is fired or detonated by containing the products of such detonation.
- detonation of the explosive 36 results in inflation and expansion of the tube 38 to a generally circular configuration.
- Such expansion of the tube 38 breaks or fractures the first and second doubles 26, 30 which are in shear and/or tension at the first and second grooves or notches 40, 44, as will be explained in more detail hereinbelow.
- a shock absorbing tape 35 fabricated, for example, from silicon rubber, may be interposed between the end portions 39a, 39b of the tube 38 and the end portions 49, 53 of the first and second sections 48, 52.
- first and second grooves 40, 44 are positioned on outer walls 28, 32 of the first and second doublers 26, 30, respectively.
- the first and second grooves 40, 44 provide weak points in the first and second doublers 26, 30, to thereby define break or fracture planes along which the first and second doublers 40, 44 will fracture upon detonation of the explosive 36.
- first and second grooves 40, 44 are positioned on outer walls 28, 32 of the first and second doublers 26, 30, respectively.
- the first and second grooves 40, 44 provide weak points in the first and second doublers 26, 30, to thereby define break or fracture planes along which the first and second doublers 40, 44 will fracture upon detonation of the explosive 36.
- the first groove 40 on the first doubler 26 is staggered relative to the second groove 44 on the second doubler 30.
- the first and second grooves 40, 44 are not coplanar with each other (e.g., offset). Rather, in this embodiment, the first and second grooves or notches 40, 44 are positioned on the first and second doublers 26, 30 respectively, along tangential planes defined by end portions 39a, 39b of the unexpanded tube 38 containing the explosive 36.
- the first groove 40 on the first doubler 26 is aligned with the tangential plane defined by a first end portion 39a of the unexpanded tube 38 while the second groove 44 is aligned with a second end portion 39b of the tube 38.
- FIG. 2B shows the separation system 20 of Fig. 2 A after the explosive 36 has been detonated. Firing of the explosive 36 causes the tube 38 to expand to a substantially circular cross-section as a result of expanding gaseous detonation products.
- Such expansion of the tube 38 deforms portions of the first and second doublers 26, 40, as illustrated in Fig. 2B, and fractures or ruptures the weakened sections of the first and second doublers 26, 30 at the first and second grooves 40, 44. Since the elastomer 37 absorbs much of the shock from the explosive 36, the principle force causing expansion of the tube 38 is the high pressure forces generated within the tube 38 by the gaseous products of the explosion. Detonation or firing of the explosive 36 may be accomplished electrically via control circuitry (not shown).
- the first and second sections 48, 52 are separable after firing of the explosive 36.
- the first section 48 is movable relative to the second section 52.
- the separation system 20 of a present invention is particularly useful in avoiding undesireable contact between the first and second sections 48, 52 and/or adverse contact between the sections 48, 52 and the expanded tube 38, especially in instances where at least lateral separation of the first section 48 relative to a longitudinally moving second section 52 is desired.
- the selected positions of first and second grooves 40, 44 on the first and second doublers 26, 30, respectively, facilitate such separation as the resulting fractured end portions of
- first and second doublers 26, 30, respectively are not likely to adversely collide with each other or with the expanded metal tube 38, which remains interconnected to the second section 52 after detonation of the explosive 36 via the restraining strap 55.
- the first section 48 is free to at least laterally separate from and relative to the second section 52, as illustrated in Fig. 2C. Such lateral separation may be accomplished by an ejection means (not shown), which functions to push or force the first section 48 laterally away from and relative to the second section 52.
- the first and second grooves 140, 144 are staggered (nonplanar) relative to each other and are further positionable on the explosive- facing and nonexplosive-facing sides 127, 132 of the first and second structural members 126, 130, respectively.
- the second groove 144 is positionable proximate a center portion of the expandable tube 138 and/or the explosive 136, as opposed to along a tangential plane defined by an end portion of the explosive means.
- the second structural member 130 will fracture substantially in tension due to bending when the tube 138 expands upon firing of the explosive 136 to a circular cross-section, as illustrated in Fig. 3B.
- the first groove 140 is positionable on the first structural member 126 along a tangential plane defined by an end portion 139a of the expandable tube 138 containing the explosive 136 (in an unexploded state) .
- Such positioning of the staggered grooves 140, 144 also enhances the fracturability of the first and second structural members 126, 130 and reduces shock since less force is required to break the doublers 126, 130.
- locating the second groove 144 on the nonexplosive-facing side 132 of the second structural member 130 proximate a center portion of the explosive system shifts the stress concentration to the area of tension load due to bending to facilitate fracturing of the second structural member 130.
- the second doubler 130 will break or fracture in tension upon firing of the explosive 136 and the resulting expansion of the tube 138.
- locating the first groove 140 along a tangential plane defined by the unexpanded tube 138 provides for the fracture of the first doubler 126 along a break plane above the expanded tube 138 (e.g., after firing of explosive 136), which facilitates a relatively damage-free separation of the first and second sections 148, 152.
- the first section 148 is substantially free to separate relative to the second section 152, as illustrated in Figs. 3B-3C.
- this staggered arrangement of the grooves 140, 144 reduces the likelihood of application of undesireable forces between the severed sections 129a, 129b, and 133a, 133b of the first and second structural members 126, 130 with each other and/or with the expanded tube 138.
- Figs. 3B-3C this staggered arrangement of the grooves 140, 144 reduces the likelihood of application of undesireable forces between the severed sections 129a, 129b, and 133a, 133b of the first and second structural members 126, 130 with each other and/or with the expanded tube 138.
- the separation system 220 of the present invention includes first and second structural members or doublers 226, 230 interconnecting first and second sections 248, 252 to be separated, first and second grooves 240, 244 positioned on explosive-facing and nonexplosive-facing surfaces 227, 232 of the first and second doublers 226, 230, respectively, a single explosive charge 236 contained within an expandable tube 238 which is positioned between the first and second doublers 226, 230 and between the first and second sections to be separated 248, 252, and a slide plane means defined by first and second slide members 260, 264 interconnectable to the first and second sections 248, 252 for facilitating a relatively collision-free separation of the first section 248 relative to the second section 252.
- the first and second grooves 240, 244 are positioned on the inner and outer walls 227, 232 of the first and second doublers 226, 230, respectively. Positioning of the first and second grooves 240,
- first and second grooves 240, 244 are staggered.
- the first notch or groove 240 is positioned in substantial alignment with a tangential plane defined by end portion 239a of the expandable tube 238 enclosing the unexploded charge 136.
- the second notch or groove 244 is positioned proximate a central portion of the expandable tube 238, in a center portion of the doubler 230, such that the second doubler 230 will break in a central section of the second doubler 230, when the tube 238 expands to a circular configuration upon firing of the explosive 236.
- first and second grooves 240, 244 are displaced or staggered relative to one another to facilitate fracture or severance of the first and second doublers 226, 230 at the first and second grooves 240, 244, as the first and second grooves 240, 244 define weakened areas of the first and second doublers 226, 230, respectively.
- firing or detonation of the explosive charge 236 causes the tube 238 to expand to bend and break the first and second doublers 226, 230, such that the first section 248 is movable laterally over the tube 238, which is restrained in a conventional manner to the second section 252, as illustrated in Fig. 4B.
- Severance or fracture of the first and second doublers 226, 230 at the first and second grooves 240, 244 allows a substantially collision-free separation of the first section 248 relative to the second section 252 as the fractured ends 229a, 229b of the first doubler 226 and the fractured portions 233a, 233b of the second doubler 230 can clear each other.
- a relatively damage-free lateral separation of the first section 248 relative to the second section 252 is further facilitated by the slidable engagement of the first slide member 260 relative to the second slide member 264, the first and second slide members 260, 264 being interconnected to the first and second sections 248, 252 to be separated and defining a slide plane 270 along which, at least initially, the first section 248 may move relative to the second section 252.
- the first section 248 may be moved (e.g., ejected) relative to the second section 252.
- the first and second slide members 260, 264 and specifically, the surfaces 261, 265 of the first and second slide members 260, 264 are oriented at least laterally (e.g., 90°) relative to the longitudinally extending first and second doublers 226, 230.
- these first and second slide members 260, 264 facilitate a substantially damage-free separation by at least initially inhibiting downward longitudinal movement of the first section 248 relative to the second section 252, at least until the first section 248 has cleared the second section 252, as illustrated in Figs. 4B- 4C.
- first and second slide members 260, 264 at least initially inhibit undesireable contact of the first section 248 with the exploded metal tube 238 and the second section 252, as illustrated in Fig. 4C. Once at least laterally cleared from the second section 252, the first section is free to move longitudinally downwardly relative to the longitudinally extending and moving second section 252, as illustrated in Fig. 4D.
- first and second surfaces 261, 265 of the first and second slide members 260, 264 are load bearing surfaces which are slidably engagable with each other, at least initially, to enable the first section 248 to laterally slide relative to and away from the second section 252.
- first and second slide members 260, 264 are oriented substantially perpendicular to the longitudinally extending first and second doublers 226, 230 and relative to the first and second sections 248, 252 to be separated relative to each other.
- the slide plane 270 defined by the first and second slide members 260, 264 is substantially aligned or coplanar with the first groove 240 on the first doubler 226, which defines a break plane for the first doubler 226.
- Such alignment of the slide plane 270 with the first groove 240 enhances separation and ejection of the first section 248 relative to the second section 252 by substantially inhibiting undesireable contact between the severed portions 229a, 229b of the first doubler 226.
- the slide plane may be defined by first and second slide members on the opposite (e.g., outboard) side of the first and second doublers and may be aligned with the second groove 244.
- collision-free lateral separation and ejection of the first section 248 relative to the second section 252 is possible, even in instances where the second section 252 continues to move in a direction parallel to a longitudinal axis of the second section 252, since the separation system 220 facilitates separation and ejection of the first section 248 in a direction at least orthogonal to the direction of movement of the second section 252.
- the separation system 220 of the present invention is especially useful for laterally separating a first section 248 relative to a second section 252, even in instances where the second section 252 (e.g., core launch vehicle) is moving in a direction parallel to a longitudinal axis of the second section 252 to thus facilitate a collision-free separation of first section 248 relative to the second section 252.
- the second section 252 e.g., core launch vehicle
- at least one of the load bearing surfaces 261, 265 of the slide members 260, 264, respectively can be coated with a low friction material.
- the surface 265 of the first slide member 264 includes a lubricant or low friction coating 262, such as a dry film, molybdenum disulfide lubricant.
- orientation and length of the first and second slide members 260, 264 may be varied, depending upon, for example, the orientation of the first and second doublers 226, 230 relative to the desired direction of separation (e.g., orthogonally) of the first section 248 from the second section 252, and the predicted or intended break planes of the doublers 226, 230.
- the slide plane 270 may be substantially coplanar with at least one of the fracture or break planes in the first and second doublers 226, 230, to guide the first section 248 away from the second section 252, which thereby inhibits undesireable contact between the separated structures, as illustrated in Fig. 4B-4C. More specifically, the slide plane 270 defined by the first and second slide plane members 260, 264 may be positioned in substantial alignment with at least one of the break planes of the first and second doublers 226, 230 to at least initially inhibit downward longitudinal movement of the first section 248 relative to the second section 252 and specifically, to inhibit damaging contact between severed end portions 229a, 229b, 233a, 233b with each other and with the expanded tube 238.
- the positioning of the staggered grooves 240, 244 and the slide plane means function to inhibit adverse contact between the severed portions of the first and second doublers 226, 230 with each other and with the expanded tube 238.
- the first and second grooves on the first and second structural members or doublers may be staggered relative to each other to avoid undesireable contact between the separated portions.
- such separation systems may further include a slide plane means to further inhibit adverse contact between the separated sections.
- a separation system which achieves a substantially damage-free separation while utilizing coplanar grooves on the first and second structural members is disclosed. In this embodiment, illustrated in Figs.
- the separation system includes a slide plane means which is coplanar with first and second opposing grooves on the first and second doublers, respectively.
- the slide members which define the slide plane can be positioned and sized to at least initially inhibit collisions upon severance of the first and second doublers.
- the system 320 includes first and second doublers 326, 330 for interconnecting, at least initially, first and second sections 348, 352 to be separated, an explosive charge 336 contained therebetween, coplanar first and second grooves 340, 344 positioned on the first and second doublers 326, 330 and first and second slide members 360, 364, which are aligned with the coplanar first and second grooves 340, 344 on first and second doublers 326, 330.
- the first and second grooves 340, 344 are positioned proximate a tangential plane defined by a first end portion 339a of the expandable tube 338 in an unexploded state.
- the first and second grooves 340, 344 are positionable on explosive facing surfaces 327, 331 of the first and second doublers 326, 330.
- the first and second slide members 360, 364 can be positioned in substantial alignment with the first and second grooves
- the first section 348 is movable relative to the second section 353 along the slide plane 370 defined by the first and second slide members 360, 364, which substantially coincides with the line of fracture through the first and second doublers 326, 330.
- the slide plane members 360, 364 function to at least initially inhibit downward movement of the first section 348 relative to the second section 352 to avoid damaging contact between the severed end portions 329a, 329b, 333a, 333b with each other and with the expanded tube 338.
- first and second slide members 360, 364 can be sized (e.g., in length) to be slidably engagable with one another to at least initially inhibit downward movement of the first section 348 relative to the second section 352, at least until an ejection system (not shown) operates to forcibly eject the separated first section 348 away from the second section 352.
- Fig. 6 illustrates another embodiment and application of the separation system of the present invention.
- the separation system 420 is used to at least longitudinally separate a first section (e.g., door) 448 from a second section (e.g., at least laterally moving vehicle) 452.
- the separation system may be used to separate the payload 13 illustrated in Fig. 1 from the longitudinally extending and moving core launch vehicle 12. Referring to Fig.
- the separation system 420 includes first and second doublers 426, 430 for at least initially interconnecting the first and second sections 448, 452, a dual cord explosive system having two explosive charges 436a, 436b enclosed in an inflatable tube 438 for severing or breaking the first and second doublers 426, 430 upon detonation, and staggered, non-coplanar first and second grooves 426, 430 positioned on the first and second doublers 426, 430.
- the first and second grooves 440, 444 may be aligned with tangential planes of the tube 438 containing the explosive charge 436 to facilitate a collision-free separation and ejection of the first section 448 relative to the second section 452.
- first and second grooves 440, 444 on the first and second laterally extending doublers 426, 430, respectively, are staggered (e.g., not coplanar relative to one another).
- the first and second grooves 440, 444 define weak areas (e.g., break planes) of the first and second doublers 426, 430, which will thus break along break planes defined by the grooves 440, 444 when the explosive 436 is detonated.
- the separation system 420 also includes a slide plane 470 defined by first and second slide members 460, 464, along which the first section 448 may be slidably moved longitudinally relative to the second section 452 in a collision-free manner during ejection of the first section 448.
- the slide members 460, 464 inhibit lateral movement of the first section 448 relative the second section 452 during ejection of the first section 448.
- a single cord explosive may be utilized instead of the dual cord explosive illustrated in Fig. 6.
- a separation system for separating a first section from a second section is provided.
- the separation system 520 includes first and second doublers 526, 530 extending between and interconnecting the first and second sections 548, 552.
- the system 520 further includes an explosive 536 enclosed within an elastomer 537, both of which are contained within an expandable (e.g., inflatable) metal tube 538.
- the explosive 536, the elastometer 537 and expandable metal tube 538 are positioned within a cavity defined by the inner (e.g., explosive-facing) walls 527, 531 of the first and second doublers 526, 530, respectively, the tube 538 being interconnected to the second section 552 via a stainless steel strap 555 wrapped therearound.
- the separation system 520 further includes a slide plane means having first and second slide members 560, 564, which define a slide plane.
- the first and second slide members 560, 564 are interconnectable to the first and second sections 548, 552, respectively.
- first and second slide members 560, 564 are slidably engagable with one another during separation and ejection of the first section 548 relative to the second section 552 to substantially inhibit significant downward longitudinal movement of the first section 548 relative to the second section 552, which is especially beneficial in instances where the second section 552 continues to move longitudinally upward.
- collision of the first section 548 and the second section 552 upon severance of the first and second doublers 526, 530 may be inhibited.
- the separation system may further include bend augmentation means associated with (e.g., interconnectable to, integrally formed in or on) first and second structural members 526, 530, respectively, for facilitating bending or hinging of the first and second structural members 526, 530, as illustrated in Figs. 7A-7C.
- bend augmentation means associated with (e.g., interconnectable to, integrally formed in or on) first and second structural members 526, 530, respectively, for facilitating bending or hinging of the first and second structural members 526, 530, as illustrated in Figs. 7A-7C.
- bend augmentation means define reinforced or stiffened portions 580, 582 which enhance bending or hinging of the first and second structural members 526, 530 in selected portions, such that upon firing of the explosive 536, the expanding tube 538 will cause the first and second structural members 526, 530 to rotate about or proximate the reinforced portions 580, 582, respectively, and break at first and second staggered notches 540, 544 on the first and second structural members 526, 530, respectively, displaced from the augmentation means 580, 582.
- the bend augmentation means or reinforced portions can be a separate piece 580 (e.g., doubler plate, slide plane components, etc.) of stiffening material (e.g., metal, such as titanium, aluminum, stainless steel, or combinations and/or composites thereof) interconnected to the first structural member 526, as illustrated in Fig. 7A.
- the bend augmentation means or reinforced portion can be a thickened portion of the structural member or doubler.
- the reinforced portion comprises a thickened portion 582 of the second structural member 530, the thickened portion 582 being integrally formed with the second structural member 530 to provide one or more thickened, less fracturable portions of the second structural member 530, as illustrated in Fig. 7A.
- Such thickened portion 582 has a thickness greater than that of the doublers 526, 530 themselves, and greater than thickness of the doublers 526, 530 at the first and second grooves 540, 544, respectively.
- the doublers 526, 530 will fracture or sever at the first and second grooves 540, 544, respectively, and bend proximate the reinforced areas 580, 582.
- Figs. 8A-8C illustrate another embodiment of the separation system of the present invention.
- the separation system 620 includes first and second doublers 626, 630 for interconnecting, at least initially, first and second sections 648, 652 to be separated, and explosive 636 contained within an expandable metal tube 638, the explosive 636 and tube 638 being contained within a cavity defined by the first and second doublers 626, 630 and first and second sections 648, 652.
- the separation system 620 includes first and second grooves 640, 644 which define lines of fracture in the first and second structural members 626, 630, respectively, the first and second structural members 626, 630 fracturable upon detonation of the explosive 636 and resulting expansion of the tube 638 to a circular cross-section.
- the separation system 620 further includes bend augmentation means.
- the bend augmentation means comprises relief portions 690, 692 on the first and second structural members 626, 630, respectively.
- the bend augmentation means comprises reinforced portions, which are described hereinabove.
- the first and second grooves 640, 644 on the first and second doublers 626, 630 of the separation system 620 are staggered relative to each other.
- the first and second grooves 640, 644 are positioned along first and second tangential planes defined by first and second end portions 639a, 639b of the tube 638 in an unexpanded state.
- the relief portions 690, 692 on the first and second doublers 626, 630, respectively, are displaced from the grooves 640, 644, respectively.
- the relief portions 690, 692 on the first and second doublers 626, 630 are also staggered relative to each other.
- the relief portions 690, 692 are positionable proximate the second and first tangential planes defined by the second and first end portions 639b, 639a, respectively, of the unexpanded tube 638. Furthermore, in order to ensure fracture and severance of the doublers 626, 630 at the grooves 640, 644, respectively and not at the relief portions 690, 692, the relief portions 690, 692 define a thickness through the doublers 626, 630 which is greater than thickness of the first and second doublers 626,
- first and second doubler 626, 630 defined by the first and second grooves 640, 644, respectively.
- first and second doubler 626, 630 fracture at the first and second staggered groove 640, 644 and bend about the relief portions 690, 692 displaced from the first and second grooves 640, 644, as illustrated in Fig. 8B.
- less explosive force is required to fracture and bend the doublers 626, 630.
- the separation system 620 may further a slide plane means having first and second slide members 660, 664 to further facilitate a relatively collision-free lateral separation and ejection of the first section 648 relative to the second section 652.
- first and second slide members 660, 664 are interconnected to the first and second sections 648, 652 and are oriented approximately 90° relative to the longitudinally extending first and second doublers 626, 630.
- slide members 660, 664 inhibit damage- causing collisions between severed portions 629a, 629b, 633a, 633b of the first and second doublers 626, 630 and with the expanded tube 638 by at least initially inhibiting downward longitudinal movement of the first section 648 relative to the second section 652, as illustrated in Fig. 8C.
- the first and second staggered grooves 740, 744 of the separation system 720 cooperate with the bend augmentation means 790, 792 on the first and second doublers 726, 730 to provide a relatively collision-free separation of the first section 748 relative to the second section 752.
- the second groove 744 on the second doubler 730 is positionable proximate a center portion of the explosive means (e.g., proximate the explosive 736 or a center portion of the tube 738), staggered or offset from the first groove 740, which is positionable along a tangential plane defined by the first end portion
- a first bend augmentation means comprising a relief portion 790 is positionable in the first doubler 726 a distance from the first groove 740, proximate (e.g., in alignment with) a second tangential plane defined by a second end portion 739b of the tube 738.
- bend augmentation means comprising relief portions 792, 794 in the second doubler 730 are positionable on either side of the center positioned second groove 744 in the second doubler 730.
- the relief portion 792, 794 on the second doubler are positionable proximate the first and second tangential planes defined by the first and second ends 739a, 739b of the tube 738.
- the severed sections of the doublers 726, 730 are easily bendable about the relief portions 790, 792 and 794, radially outwardly relative to the tube 738.
- the relief portions 790, 792, 794 on the doublers 726, 730 facilitate bending of the first and second doublers 726, 730 upon expansion of the tube 738.
- thicknesses of the first and second doublers 726, 730 defined by the first and second grooves 740, 744 are less than thicknesses of the first and second doublers 726, 730 defined by the relief portions 790, 792, and 794.
- the bend augmentation means utilized in this embodiment comprise reinforced portions, which are described hereinabove.
- a separation system 820 of the present invention includes first and second doublers 826, 830, an expanding tube explosive charge system contained between the first and second doublers 826, 830, and first and second grooves 840, 844 positioned on the first and second doublers 826, 830, respectively.
- the first and second grooves 840, 844 are positioned opposite each other, along a first tangential plane defined by a first end portion 839a of the expandable tube 838 containing the explosive 836.
- the separation system 820 further includes first and second bend augmentation relief portions 890, 892 positioned on the first and second doublers 826, 830, respectively.
- the first and second bend augmentation relief portions 890, 892 are positionable proximate a second tangential plane defined by a second portion 839b of the expandable tube 838.
- the thickness of the first and second doublers 826, 830 at the relief portions 890, 892, respectively is greater than the thicknesses of the first and second doublers 826, 830 at the first and second grooves 840, 844, respectively, in order to fracture the first and second doublers 826, 830 at the first and second grooves 840, 844, respectively and to bend the first and second doublers 826, 830 about the relief portions 890, 892, respectively.
- the separation system 820 may further include a slide plane means comprising first and second slide members 860, 864 to at least initially guide the first section 848 at least orthogonally relative to the second section 852, substantially as described hereinabove in relation to other embodiments.
- Figs. 11 A-l 1 C illustrate yet another embodiment of the present invention wherein coplanar or opposing grooves on doublers are utilized.
- the separation system 920 includes first and second grooves 940, 944 positioned on first and second doublers 926, 930, an explosive means positioned between the first and second doublers 926, 930 and a bend augmentation means for facilitating bending of the first and second doublers 926, 930 upon detonation of the explosive 936.
- this embodiment of the present invention is directed to achieving at least initially a longitudinal separation of the first section 948 relative to the second section 952.
- Such longitudinal separation may be accomplished by utilizing an ejection system (not shown).
- the first and second grooves 940, 944 on the first and second doublers 926, 930 are positioned proximate a center portion of the explosive 936 or expandable tube 938 .
- bend augmentation means comprising reinforced portions or relief portions are positionable on the first and second doublers 926, 930, along or proximate first and/or second tangential planes defined by end portions 939a, 939b of the tube 938.
- relief portions 990, 992 are positionable on the first doubler 926 and relief portions 994, 996 are positionable on the second doubler 930, along the first and second tangential planes defined by the end portions 939a, 939b of the tube 938.
- the thickness of the first and second doublers 926, 930 at the first and second grooves 940, 944 is less than the thickness of the first and second doublers 926, 930 at the relief portions 990, 992, 994, 996.
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
- Processing Of Stones Or Stones Resemblance Materials (AREA)
- Laminated Bodies (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP98965375A EP1040312A4 (en) | 1997-12-16 | 1998-11-25 | Separation system |
AU20853/99A AU2085399A (en) | 1997-12-16 | 1998-11-25 | Separation system |
JP2000539312A JP2002508502A (en) | 1997-12-16 | 1998-11-25 | Separation system |
Applications Claiming Priority (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US08/999,573 US5969287A (en) | 1997-12-16 | 1997-12-16 | Separation system |
US08/991,225 | 1997-12-16 | ||
US08/999,573 | 1997-12-16 | ||
US08/991,225 US5992328A (en) | 1997-12-16 | 1997-12-16 | Separation system |
US08/999,572 US5983802A (en) | 1997-12-16 | 1997-12-16 | Separation system |
US08/999,572 | 1997-12-16 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1999031455A1 true WO1999031455A1 (en) | 1999-06-24 |
Family
ID=27420783
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US1998/025159 WO1999031455A1 (en) | 1997-12-16 | 1998-11-25 | Separation system |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP1040312A4 (en) |
JP (1) | JP2002508502A (en) |
CN (1) | CN1090312C (en) |
AU (1) | AU2085399A (en) |
WO (1) | WO1999031455A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2805245A1 (en) * | 2000-02-23 | 2001-08-24 | Centre Nat Etd Spatiales | Method of lauching a number of communication satellites mounted on the same launch platform, includes mounting satellites on bases around a launch platform and launching them simultaneously |
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US7367738B2 (en) * | 2002-09-23 | 2008-05-06 | The Boeing Company | Apparatus and method for releaseably joining elements |
JP5728820B2 (en) * | 2010-04-08 | 2015-06-03 | 株式会社Ihi | rocket |
FR2969748B1 (en) * | 2010-12-22 | 2013-01-25 | Astrium Sas | REVERSIBLE DETONATING PYROTECHNIC RUPTURE PIECE |
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CN103700983B (en) * | 2012-09-27 | 2016-06-22 | 上海宇航***工程研究所 | Air-conditioning adapter |
FR3009284B1 (en) * | 2013-08-01 | 2017-06-09 | Astrium Sas | METHOD AND DEVICE FOR BINDING AND SEPARATING TWO ELEMENTS WITH MIXED BONDING AND SEPARATION MEANS |
FR3040693B1 (en) * | 2015-09-03 | 2018-08-10 | Arianegroup Sas | METHOD FOR LINKING AND LINEAR SEPARATING TWO ELEMENTS |
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CN107585329A (en) * | 2017-08-10 | 2018-01-16 | 大连理工大学 | A kind of carrier rocket wire type bundlees separator |
CN107521723A (en) * | 2017-08-25 | 2017-12-29 | 北京电子工程总体研究所 | A kind of linear firer's separator |
CN108750149B (en) * | 2018-06-15 | 2020-07-28 | 上海卫星工程研究所 | Ring type connecting and separating device based on punching separation technology |
CN110920899B (en) * | 2019-12-05 | 2023-06-09 | 江西洪都航空工业集团有限责任公司 | General cocoon type storage and transportation transmitting box for airborne equipment |
CN113566659B (en) * | 2020-04-29 | 2024-01-16 | 大连理工大学 | Transverse-longitudinal separation integrated interstage line type separation device and application thereof |
CN113834387B (en) * | 2021-09-17 | 2023-06-06 | 北京宇航***工程研究所 | Large-diameter combined high-reliability expansion pipe-groove plate separation device |
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- 1998-11-25 WO PCT/US1998/025159 patent/WO1999031455A1/en not_active Application Discontinuation
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- 1998-11-25 EP EP98965375A patent/EP1040312A4/en not_active Withdrawn
- 1998-11-25 JP JP2000539312A patent/JP2002508502A/en active Pending
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Also Published As
Publication number | Publication date |
---|---|
JP2002508502A (en) | 2002-03-19 |
EP1040312A1 (en) | 2000-10-04 |
EP1040312A4 (en) | 2002-09-04 |
AU2085399A (en) | 1999-07-05 |
CN1282415A (en) | 2001-01-31 |
CN1090312C (en) | 2002-09-04 |
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