Patent Description:
<CIT> discloses a seal ring having rounded-corner rectangular shape in cross-section is mounted in a recessed groove formed in ring configuration in a pressure-contact surface of a seal jig such that major axis of the seal ring is oriented perpendicular to the pressure-contact surface and the seal ring is projected out the pressure-contact surface by about <NUM>-<NUM>% of length of the major axis to be compressively deformable in the direction of the major axis, and stoppers formed of low thermal conductivity resin are disposed on the pressure-contact surface, the peripheral portion of the opening of an article being tested is brought into pressure-contact with the seal ring in a manner such that the stoppers are interposed therebetween and that the compressively deformed seal ring provides an adequate sealing effect to seal the opening, whereby testing may be conducted without bringing the article being tested into contact with the seal jig.

<CIT> describes a joint structure comprising: two joint members; a drive mechanism that drives the two joint members to rotate about a predetermined axis relative to each other; two sealing members that form a seal between the two joint members at positions that double the outside of a lubricant storage part in the drive mechanism surround; and a pressure applying means that makes the air pressure in a space between the two sealing elements higher than the pressure of the outside air, the sealing element being formed on the outside from an elastic material and having a cutting area at at least one circumferential position, the cutting area being inclined with respect to the radial direction, and wherein the outer sealing element is attached to a fixed part of the drive mechanism by tightening a fastener.

In a first aspect, the present disclosure provides a separable component assembly comprising: a first component having a first interface portion; a second component coupled to the first component, the second component having a second interface portion; and a seal disposed between the first and second interface portions, the seal having a first interface surface associated with the first interface portion, a second interface surface in contact with the second interface portion, and a peel initiator defining a discontinuity in a portion of the second interface surface, wherein, upon separation of the first and second components from one another, the discontinuity creates a stress concentration in the second interface surface that initiates peeling of the second interface surface away from the second interface portion.

In a second aspect, the present disclosure provides a method for facilitating separation of two components from one another, the method comprising: obtaining a first component having a first interface portion; obtaining a second component coupleable to the first component, the second component having a second interface portion; disposing a seal between the first and second interface portions, the seal having a first interface surface associated with the first interface portion, and a second interface surface in contact with the second interface portion; and facilitating separation of the second interface surface from the second interface portion upon separation of the first and second components from one another, wherein a discontinuity in a portion of the second interface surface creates a stress concentration in the second interface.

surface that initiates peeling of the second interface surface away from the second interface portion.

An initial overview of the inventive concepts are provided below and then specific examples are described in further detail later. This initial summary is intended to aid readers in understanding the examples more quickly, but is not intended to identify key features or essential features of the examples, nor is it intended to limit the scope of the claimed subject matter.

As noted above, some existing component couplings (e.g., first and second rocket stages) may remain static or motionless for long periods of time (e.g., years or decades). Compressive stress over time can cause existing seals, gaskets, or O-rings to form a "bond" with one or more of the coupled components. When separation of the coupling is required, often rapidly or instantaneously, the "bond" or stiction resists or retards this separation of coupled components, which can be problematic in meeting requirements such as the coupled components separating within a specified time period or with a specified minimum separation speed.

Accordingly, a separable component assembly is disclosed that reduces the force required to overcome such bonding or stiction between a seal and mating component. The separable component assembly can include a first component having a first interface portion. The separable component assembly can also include a second component coupled to the first component. The second component can have a second interface portion. In addition, the separable component assembly can include a seal disposed between the first and second interface portions. The seal can have a first interface surface associated with the first interface portion. The seal can also have a second interface surface in contact with the second interface portion. Additionally, the seal can have at least one peel initiator defining one or more discontinuities in a portion of the second interface surfaces so as to facilitate the reduction in the amount of stiction or the stiction phenomenon between the first and second components. Upon separation of the first and second components from one another, the discontinuity can create a stress concentration in the second interface surface that initiates peeling of the second interface surface away from the second interface portion. Advantageously, the seal with the peel initiators defining one or more discontinuities can facilitate the first and second coupled components separating within a specified time period or with a specified minimum separation speed.

To further describe the present technology, examples are now provided with reference to the figures. With reference to <FIG>, one example of a separable component assembly <NUM> is illustrated. A detailed cross-sectional view of the separable component assembly <NUM> is shown in <FIG>. The separable component assembly <NUM> can include a first component <NUM>. The separable component assembly <NUM> can also include a second component <NUM> coupled to the first component <NUM>. The first and second components <NUM>, <NUM> may be hollow and cylindrical but are not limited to this configuration. In one specific example, the first component <NUM> can be a first rocket stage and the second component <NUM> can be a second rocket stage. However, this is not intended to be limiting in any way, as the first and second components can comprise other structural members designed and configured to be joined or otherwise coupled together.

The first component <NUM> can have a first interface portion <NUM>, and the second component <NUM> can have a second interface portion <NUM>. The separable component assembly <NUM> can include a seal <NUM> disposed between the first and second interface portions <NUM>, <NUM>. In one aspect, as shown in the figures, the seal <NUM> can have similar geometry and profile as the first and second components <NUM>, <NUM>, however the seal <NUM> can have any suitable geometry or configuration for a given application. In some examples, the seal <NUM> can be a gasket, an O-ring, or any other suitable type or configuration of a seal between the first and second components <NUM>, <NUM>. The seal <NUM> can be constructed of any suitable material, such as an elastomeric material. The seal <NUM> can have a first interface surface <NUM> associated with the first interface portion <NUM> of the first component <NUM>. The seal <NUM> can also have a second interface surface <NUM> in contact with the second interface portion <NUM> of the second component <NUM>. In some examples, the seal <NUM> may be bonded (e.g., with an adhesive <NUM>) to the first component <NUM> to prevent the seal <NUM> from dislocating when the first and second components <NUM>, <NUM> separate.

In addition, the seal <NUM> can have one or more peel initiators 133a, 133b, as shown in the cross-sectional view of <FIG> and the top view of the seal <NUM> in <FIG>. In one aspect, one or both of the peel initiators 133a, 133b can extend through a thickness <NUM> (<FIG>) of the seal <NUM> (i.e., the seal thickness configured to be oriented axially between the first and second components <NUM>, <NUM>). The seal <NUM> can have any suitable cross-section, such as a polygon shape (e.g., a rectangle, a trapezoid, a triangle, pentagon, a hexagon, an octagon, etc.), a curved shape (e.g., a circle, an oval, an ellipse, etc.), a curvilinear shape, etc. Thus, a thickness of the seal can comprise a thickness of any suitable cross-sectional shape. In one aspect, a thickness of the seal comprises at least one of a rectangular cross-section (<FIG>) or a circular cross-section (<FIG>).

As illustrated in a representative peel initiator <NUM> shown in <FIG>, the peel initiator <NUM> can define a discontinuity <NUM> in a portion of the second interface surface <NUM>. The discontinuity <NUM> can be a recess, a cut, a notch, etc. formed in the profile of the second interface surface <NUM> that creates a discontinuous surface or profile. In other words, the discontinuity <NUM> can break or interrupt an otherwise uniform surface <NUM> and therefore disrupt the static friction present between the uniform surface <NUM> and either of the first and second components <NUM>, <NUM>. Upon separation of the first and second components <NUM>, <NUM> from one another in directions 102a, 102b (<FIG>), the discontinuity <NUM> can create a stress concentration (e.g., at singularities or "corners" 136a-c of the discontinuity <NUM>) in the second interface surface <NUM> that initiates peeling of the second interface surface <NUM> away from the second interface portion <NUM>.

The peel initiator <NUM> can include any shape or geometry that can introduce a stress concentration. In one example, the discontinuity <NUM> can comprise a profile defined at least partially by two lines 135a, 135b intersecting at a point 136a that creates the stress concentration. The two lines 135a, 135b can be at any suitable angle <NUM> relative to one another. In one aspect, the angle <NUM> can be greater than or equal to about <NUM> degrees and less than or equal to about <NUM> degrees. In another aspect, a depth <NUM> of the discontinuity <NUM> can be greater than or equal to about <NUM>% of a width <NUM> of the second interface surface <NUM> and less than or equal to about <NUM>% of the width <NUM> of the second interface surface <NUM>. A discontinuity can be of any suitable shape, geometry, or configuration. In one aspect, the discontinuity <NUM> can comprise at least one of a V-shape (<FIG>), a U-shape (<FIG>), or a W-shape (e.g., a sawtooth profile) (<FIG>) (i.e., any one of these or any combination of these).

As shown in <FIG> and <FIG>, a seal can include any suitable number of peel initiators as described herein. In the context of the <FIG> example (but also applicable to the <FIG> example), the peel initiator 133a is located on one side 132a of the second interface surface <NUM> and the peel initiator 133b is located on another side 132b of the second interface surface <NUM> opposite the first side 132a. In other words, the peel initiators 133a, 133b can be formed along an edge of the seal <NUM>. In one aspect, the seal <NUM> can comprise a ring configuration, and the side 132a is proximate an inner diameter of the ring configuration and the side 132b is proximate an outer diameter of the ring configuration. Thus, peel initiators can be configured and arranged about a seal to achieve a desired stiction reducing or releasing effect from an interfacing component.

In a specific example, a seal can be disposed between two adjacent components (e.g., first and second stages) of a rocket or missile that are intended to separate from one another. In this configuration, the seal is under compressive stress in the direction of the central axis of the rocket. During flight, the two adjacent components (e.g., first and second stages) are designed to separate. The seal may be bonded (e.g., with an adhesive) to one of the two components to prevent it from dislocating when the two adjacent rocket components separate. Typically, the separation must be accomplished very quickly to ensure proper operation and flight of the rocket. Separation of the seal from the mating rocket component that is it not bonded to the seal may be retarded or prevented due to stiction of the seal to this rocket component. The magnitude of stiction may be reduced by one or more discontinuities as described herein. These discontinuities function to initiate peeling of the seal from the interfacing component and can therefore reduce the force necessary to separate the seal from the interfacing rocket component. Thus, the discontinuities can reduce the amount of force required to separate the first and second stages, which can ensure proper separation and operation of the rocket.

In accordance with one embodiment of the present invention, a method is disclosed for facilitating separation of two components from one another. The method can comprise obtaining a first component having a first interface portion. The method can also comprise obtaining a second component coupleable to the first component, the second component having a second interface portion. The method can further comprise disposing a seal between the first and second interface portions, the seal having a first interface surface associated with the first interface portion, and a second interface surface in contact with the second interface portion. Additionally, the method can comprise facilitating separation of the second interface surface from the second interface portion upon separation of the first and second components from one another, wherein a discontinuity in a portion of the second interface surface creates a stress concentration in the second interface surface that initiates peeling of the second interface surface away from the second interface portion. it is noted that no specific order is required in this method, though generally in one embodiment, these method steps can be carried out sequentially.

In one aspect of the method, the discontinuity comprises a profile defined at least partially by two lines intersecting at a point that creates the stress concentration. In a specific aspect of the method, an angle between the two lines is greater than or equal to about <NUM> degrees and less than or equal to about <NUM> degrees. In one aspect of the method, the discontinuity comprises at least one of a V-shape, a U-shape, or a W-shape.

Reference was made to the examples illustrated in the drawings and specific language was used herein to describe the same. It will nevertheless be understood that no limitation of the scope of the technology is thereby intended. Alterations and further modifications of the features illustrated herein and additional applications of the examples as illustrated herein are to be considered within the scope of the description.

Although the disclosure may not expressly disclose that some embodiments or features described herein may be combined with other embodiments or features described herein, this disclosure should be read to describe any such combinations that would be practicable by one of ordinary skill in the art. The user of "or" in this disclosure should be understood to mean non-exclusive or, i.e., "and/or," unless otherwise indicated herein.

Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more examples. In the preceding description, numerous specific details were provided, such as examples of various configurations to provide a thorough understanding of examples of the described technology. It will be recognized, however, that the technology may be practiced without one or more of the specific details, or with other methods, components, devices, etc. In other instances, well-known structures or operations are not shown or described in detail to avoid obscuring aspects of the technology.

Claim 1:
A separable component assembly (<NUM>) comprising:
a first component (<NUM>) having a first interface portion (<NUM>);
a second component (<NUM>) coupled to the first component, the second component having a second interface portion (<NUM>); and
a seal (<NUM>) disposed between the first and second interface portions, the seal having a first interface surface (<NUM>) associated with the first interface portion, a second interface surface (<NUM>) in contact with the second interface portion,
characterised by a peel initiator (133a, 133b) defining a discontinuity (<NUM>) in a portion of the second interface surface,
wherein, upon separation of the first and second components from one another, the discontinuity creates a stress concentration in the second interface surface that initiates peeling of the second interface surface away from the second interface portion.