A dispensing system for releasing a number of spacecraft from a launch vehicle. The dispensing system includes a base support structure securely fastened to a launch vehicle and a number of stacked frame assemblies. Each frame assembly includes a number of substantially parallel load bearing elongated post elements and a shear load transferring structure. The post elements are so arranged and spaced so as to define a geometry having a centerline. Each post element has a first end portion and a second end portion. Each first end portion is connected to either another frame assembly or the base support structure of the launch vehicle. The post elements support a number of spacecraft. The spacecraft are supported between adjacent post elements. The shear load transferring structure is connected to the post elements for transferring shear loads between the post elements. The dispensing system also includes a plurality of longitudinally spaced stabilizers connected to desired locations on the post elements to increase the buckling capability of the dispensing system. The provision of a plurality of stacked frame assemblies provides a modular structure which does not require attachment to external supports other than via the base support structure.

Spacecraft dispensing system

An airborne spin dispensing apparatus (100,101) and method of dispensing a plurality of sub-units (60) such that the ground plane impact pattern of the plurality of sub-units substantially corresponds to a particular geometric ground target. An onboard microprocessor (24) which receives flight data (26) and a selected target data (28) also has a program store of sub-unit ejection sequences each of which corresponds to a particular target impact geometry. The microprocessor (24) selects an appropriate sub-unit ejection sequence in accordance with the flight and selected target data and effects a release of the sub-units (60) from the spinning apparatus such that their ground impact pattern substantially matches the geometry of the ground target.

Spin dispensing method and apparatus

A method and system for extracting and targeting multiple submunitions from a delivery vehicle. Each submunition may be self-extracting, recoil-less extracting, self-spin initiating, and/or sensor fuzed.

Self extracting submunition

A dispenser is disclosed for ejecting space vehicles from a launch vehicle. The dispenser includes an inverted outer truncated cone and an upright inner truncated cone positioned within the outer cone and connected thereto at lower end portions thereof. The cones are mounted on the launch vehicle. The dispenser also includes a mounting platform secured to the outer cone and inner cone at upper end portions thereof. Hinges detachably pivotally mount the space vehicles on the mounting platform, and separation nuts and bolts releasably secure the vehicles to the platform. Spring actuators mounted in the platform provide pivoting of all or any individual vehicle relative to the mounting platform resulting in separation and ejection of the vehicles from the launch vehicle.

Space vehicle dispenser

A cantilever, bi-level platform satellite dispenser for supporting a plurality of independently deployable satellites in a dual platform arrangement. The dispenser includes a lower platform assembly having a center post extending therefrom. An upper platform assembly is secured to an opposite end of the center post, thus spacing the upper platform assembly elevationally from the lower platform assembly. Each of the upper and lower platform assemblies include a platform member upon which a plurality of satellites may be disposed and supported solely along bottom portions thereof. On the lower platform assembly the satellites are supported exteriorly of the center post, which enables access to the satellites on this platform even after same are secured thereto. The dispenser is lighter in weight than previously developed dispensers and eliminates the need for any external support structure to be carried by the dispenser or attached to the fairing. This enables the full fairing of the launch vehicle to be jettisoned at the appropriate time during ascent of the launch vehicle, thus significantly increasing the payload weight that may be carried into low earth orbit.

Cantilever, bi-level platform satellite dispenser

The system includes an elongated support structure positioned substantially central of the carrier missile, wherein the support structure includes a gas-actuated piston-like device which moves between a start position and an extended position. A series of elongated launch tubes, in which submissiles are positioned, are arranged around, and parallel to, the support structure. The forward end of each launch tube is pivotally connected to the central support structure. The other end of each launch tube is connected to the piston-like device through levers which are hinged at both ends, so that as the piston-like device moves, the rear end of the launch tubes move radially relative to the support structure, so that the launch tubes are at an angle relative to the carrier missile. In this position, the submissiles in the launch tubes may be ejected rearwardly of the carrier missile by an explosive charge or similar means.

Dispensing system for use on a carrier missile for rearward ejection of submissiles

A missile container for storing a missile therein and having an extraction mechanism for extracting the missile from the container and placing the missile in the proper launch attitude.

Missile container and extraction mechanism

A shock suppressing device adapted to be attached to the aft end of a shoulder-fired rocket launcher. The device comprises a cylindrical housing defining a substantially enclosed expansion chamber having a diameter and cross-sectional area greater than that of the exhaust end of the launch tube. A plurality of annular baffles extend radially inwardly from the cylindrical housing and define aligned through openings through which a plug from a rocket being launched can be emitted rearwardly from the launch tube. The initial shock which follows the expulsion of the plug from the rocket is spread outwardly into the expansion chamber to engage the baffles therein. The baffles suppress the shock by absorbing a substantial portion of the energy of the shock wave, and also partially reflecting the shock wave in an upstream direction toward the launch tube. In the preferred form, the housing is made of several members which telescope together for storage, and are pulled out to an expanded position for use.

Alex B. Hunter

Papers

Dispensing system for use on a carrier missile for rearward ejection of submissiles

Missile container and extraction mechanism

Shock suppressing apparatus and method for a rocket launcher