A biocompatible monomer composition includes: (A) at least one monomer, which forms a medically acceptable polymer; (B) at least one plasticizing agent present in the composition in an amount of from 0.5 wt.% to 15 wt.% of the composition; and (C) at least one acidic stabilizing agent having a pKa ionization constant of from about 1 to about 7. The composition can be applied to a variety of materials and is particularly suitable as in vivo tissue adhesive. A method of joining together in vivo two surfaces, e.g., body tissues, includes (a) holding damaged tissue edges together to form abutted tissue surfaces; (b) applying to the abutted tissue surfaces an excessive amount of a composition containing 1) at least one monomer, which forms a medically acceptable biodegradable polymer, 2) at least one plasticizing agent; and 3) at least one acidic stabilizing agent; and (c) maintaining the surfaces in contact until the composition polymerizes to form a thick film of polymerized composition bridging the abutted tissue surfaces.

Monomeric compositions effective as wound closure devices

A nozzle having an undulating surface for enhancing the mixing of a primary flow with a secondary flow or ambient air, without requiring an ejector. The nozzle includes a nozzle structure and design for introducing counter-rotating vorticity into the primary flow either through (i) internal surface corrugations where an axisymmetric line through each corrugation is coincident with an axisymmetric line through the center of the flow passageway or (ii) through one or more sets of alternating convexities and cavities in the internal surface of the nozzle where an axisymmetric line through each convexity and cavity is coincident with an axisymmetric line through the center of the flow passageway, and where the convexities contract from the entrance end towards the exit end. Exit area mixing is also enhanced by one or more chevrons attached to the exit edge of the nozzle. The nozzle is ideally suited for application as a jet engine nozzle. When used as a jet engine nozzle, noise suppression with simultaneous thrust augmentation/minimal thrust loss is achieved.

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Undulated nozzle for enhanced exit area mixing

A thrust directing mechanism (430) to vector thrust and control discharge throat area is disclosed. Mechanism (430) includes a number of vanes (460a-460h) mounted across passage (418) of thrust vectoring nozzle (440). Mechanism (430) includes control linkage (486) pivotally coupled to each of vanes (460a-460h). The control linkage (486) is selectively movable to correspondingly pivot vanes (460a-460h) and has a link with at least two degrees of freedom corresponding to a two-coordinate position. A desired orientation of vanes (460a-460h) may be determined as a function of the two-coordinate position. The discharge exit area is contracted by adjusting convergence of vanes (460a-460h). During convergence, vanes (460a-460h) are pivoted to various pivot angles selected to optimize thrust efficiency when contracting the discharge throat area.

Thrust vectoring techniques

A thrust vectoring mechanism (30) to vector thrust and control discharge throat area includes four or more vanes (40) mounted across the outlet of a nozzle (28) in a cascade arrangement. The mechanism further includes a rod (50) to control pivoting of each of the vanes that may be selectively rotated with one or more actuators. The rod includes threading (58). The vanes each include a drive member (54) that is either toothed to engage the rod threading or defines a camming relationship with a coupling member threaded on the rod. The rod threading, drive members, and coupling members may be arranged to define different pivoting schedules for each of the vanes so that a generally constant throat area may be maintained over a given vector directional range of the vanes. The outlet (34) may be generally rectangular in cross-section and a strut (48) may be mounted across the outlet perpendicular to the pivot axes of the vanes to house the rod, drive members, and/or coupling members.

Thrust vectoring mechanism

A dispenser comprising a valved aerosol container (22) and a unitary flexible barrier member (10) having an outer wall segment (12) terminating in a sealing flange (16). The sealing flange (16) is joined to the container (22) between top and sidewall portions (27, 25), and an inner wall segment (14) is joined to the outer wall segment (12) through a fold (15). A central piston region (20) emerges from the terminus of the inner wall segment (14) distal to the fold (15). The barrier (10) is sufficiently thick and rigid to be free-standing before incorporation into a pressurized container (22). The outer and inner wall segments (12, 14) are oppositely-directed frustoconical shapes forming an acute angle with each other when the barrier (10) is initially inserted into the container (22). The outer wall segment (12) is thicker and more rigid than the inner wall segment (14). The barrier (10) is nestable with like barriers (10).

Flexible barrier member useful in aerosol dispensers

A diaphragm adapted for use in a positive expulsion tank is subjected to a pre-rolling operation prior to installation within a tank in order to provide for improved diaphragm rolling characteristics during a subsequent expulsion operation.

Method of fabricating an expulsion tank diaphragm

There is disclosed an improved upper-stage rocket engine thrust nozzle assembly of the type which comprises in combination with a basic engine rigid nozzle 12 one or more telescopically nestable-extendible truncated cone-shaped collars 22, 30 of rigid structural forms, and a further deployable perimetrically attached skirt 35 formed of sheet metal or the like which is pleat-folded inwardly from an initial truncated cone-shaped configuration into a generally planar configuration. The assembly when inoperative is stowed within the basic engine-nozzle profile, but in association with engine firing the extendible components thereof are progressively deployed in accord with an improved technique to provide the desired extended length and plume exiting diameter/are nozzle effect.

Extending rocket engine exhaust nozzle assembly

A skirt-like device attached to the exit end of a rocket engine nozzle is fabricated of thin sheet heat resistant metal; which when extended in operative condition is in frustoconical form, but which prior to engine firing is pleat-folded inwardly into a stowed position relative to the exit end of the rocket engine nozzle. Thus, prior to engine firing the device adds little or nothing to the engine/nozzle occupancy space; but incident to engine firing the device deploys to provide an effective engine nozzle/skirt combination of increased length and exit diameter/area; such combination having an inner surface of constant slope.

Extendible/expandable nozzle for rocket engines and the like and method of making same

A skirt-like device attached to the exit end of a rocket engine nozzle is fabricated of thin sheet heat resistant metal; which when extended in operative condition is in frustoconical form, but which prior to engine firing is pleat-folded inwardly into a stowed position relative to the exit end of the rocket engine nozzle. Thus, prior to engine firing the device adds little or nothing to the engine/nozzle occupancy space; but incident to engine firing the device deploys to provide an effective engine nozzle/skirt combination of increased length and exit diameter/area; said combination having an inner surface of constant slope.

Method of making an extendible/expandable nozzle for rocket engines

A skirt-like device attached to the exit end of a rocket engine nozzle is fabricated of thin sheet heat resistant metal; which when extended in operative condition is in frusto-conical form, but which prior to engine firing is pleat-folded inwardly into a stowed position relative to the exit end of the rocket engine nozzle. Thus, prior to engine firing the device adds little or nothing to the engine/nozzle occupancy space; but incident to engine firing the device deploys to provide an effective engine nozzle/skirt combination of increased length and exit diameter/area; the combination having an inner surface of constant slope.

Lee F. Carey

Papers

Method of fabricating an expulsion tank diaphragm

Extending rocket engine exhaust nozzle assembly

Extendible/expandable nozzle for rocket engines and the like and method of making same

Method of making an extendible/expandable nozzle for rocket engines

Extendible/expandable nozzle for rocket engines and the like