Abstract: Payload delivery of a payload compartment containing a delivery device is initiated by a suitable fusing device which ejects the delivery device from a payload section by firing a gas generator in the section base to propel the delivery device forwardly, thereby shearing retaining pins and ejecting the delivery device from the payload section. The fusing device concurrently fires a time-delayed mechanism leading to a second gas generator in the center of the delivery device. The gas generator ignites after the chaff dispenser is clear of the payload section. The ignition reaction pneumatically blows chaff (e.g. metallized dipoles) out of wrapped bundles, leaving the wrapper bonded to the delivery device and disseminating the chaff in a cloud of hot gas and air turbulently mixed in the wind shear occurring in the wake of the delivery device. The delivery device survives the dispensing and dissemination processes without losing structural integrity. Thus, no harmful debris is ejected into the chaff cloud.

Abstract: Each of first and second switches, preferably ganged, have first and second operative relationships. In the first operative relationship, the first switch is connected across a firing device to prevent the firing device from being energized. In the first operative relationship, the second switch is connected across an energy storage device (e.g. capacitor) to prevent the capacitor from being charged. In the second operative relationship of the second switch, the capacitor is charged by an energy supply device (e.g. battery). In the second operative relationship of the first and second switches, the capacitor is connected in a circuit with the first device and a third switch (e.g. transistor). The transistor is normally nonconductive to prevent the capacitor from discharging through the firing device with the first and second switches in the second operative relationships.

Abstract: A motor for impelling a missile or projectile has a housing and a plurality of spaced walls defining progressive compartments in the housing. A nozzle in one of the compartments produces a thrust for the missile or projectile when pressurized gases flow through it. Igniters extending into the individual compartments ignite propellants in such compartments. The igniter in an individual one of the compartments is energized initially and the igniters progressively displaced from such individual compartment are thereafter energized sequentially. Each wall separating an individual pair of adjacent compartments has a normally closed valve. Each valve has a first orifice of relatively great area in the compartment closer to the nozzle and a second orifice of limited area in the compartment further from the nozzle. A membrane between the orifices prevents the valve from being opened by a pressure from the closer compartment until this pressure becomes relatively great (e.g. 6500 psi).

Abstract: First and second ganged switches having first and second operative relationships are normally operative in the first relationship and are actuated by an external mechanism to the second relationship. In the first relationship, the first switch shunts and short circuits a pyrotechnic device and the second switch shunts and short circuits an energy storage member such as a capacitor. In the second operative relationship of the second switch, a battery charges the capacitor and also introduces a starting signal to an electronic timing circuit to institute a timing sequencer by the circuit for a pre-selected period that is selected via a series of inputs to the electronic timer. When the pre-selected time period has been timed out, the timing circuit introduces a signal to a solid state electronic switch which is normally in a non-conductive state to prevent actuation. The signal from the timing circuit causes the electronic switch to provide a low impedance.

Abstract: A solid propellant acts in a chamber to propel a member such as a rocket, the chamber being closed to the atmosphere. The propellant provides high density-impulses and, when combusted, produces end products which do not have any deleterious effects. The propellant includes a binder/reducing agent having hydrocarbyl linkages including --CH.sub.2 -- and a lead compound oxidizer formed from an inorganic lead oxidizer salt. The oxidizer has dense characteristics and stable properties at ambient temperatures and through a range of temperatures above ambient. A second oxidizer made from a metallic salt (not including lead) such as potassium perchlorate may also be included in the propellant. Carbon, preferably in particulate form, may also be included in the mixture as an additional reducing agent. The different materials are included in the propellant in relative amounts by weight to reduce the lead salt in the oxidizer to lead oxide.

Abstract: A self contained, self powered microprocessor controlled aircraft ejection seat escape parachute deployment sequencer which can handle problems caused by high altitudes into the stratosphere and by high speeds above Mach 1, and which will deploy the parachute, based on seat mounted pitot tube and ambient pressure readings plus stored data, when speed and altitude are at human physiologically acceptable levels. Many failsafes to cope with unusual conditions, and additional features are also included.

Abstract: A solid propellant acts in a chamber to propel a member such as a rocket, the chamber being closed to the atmosphere. The propellant provides high density-impulses and, when combusted, produces end products which do not have any deleterious effects. The propellant preferably includes a binder having hydrocarbon linkages and a lead compound oxidizer formed from an inorganic lead oxidizer salt. This oxidizer has dense characteristics and stable properties at ambient temperatures and through a particular range of temperatures above ambient. The propellant also includes a fuel additive, preferably a metal such as aluminum, having properties of being oxidized by the oxidizer and of reducing the lead. The fuel additive has a percentage by weight relative to the lead compound oxidizer to reduce the lead to lead oxide. The fuel additive is preferably included in the propellant in the range to approximately twenty percent (20%) by weight and is preferably in a fragmentary form.

Abstract: A gas generator is capable of being stored in a stable form for long periods of time without deteriorating in quality. The gas generator provides a substantial amount of gases, and particularly oxygen, carbon monoxide or carbon dioxide without producing any harmful or hazardous chemicals. The gas generator includes in some embodiments a minimum of fuel so that a maximum amount of oxygen in the generator is capable of being liberated. The oxygen is liberated by the combustion of a fuel at localized positions in a refractory binder, which has the property of preventing the salt residue from becoming molten and the oxidizer from flowing and thereby preventing the combustion from becoming extinguished.The gas generator includes a suitable clay as a binder, coke as the fuel and a chlorate such as sodium chlorate or potassium chlorate as the oxidizer.