Stage separation system and method

Details Stage separation system and method Stage separation system and method

1999-03-05

2001-09-18

Nelson, Peter A. (Department: 3641)

Ammunition and explosives

Having reaction motor

Having separation means

C102S378000

Reexamination Certificate

active

06289818

ABSTRACT:

TECHNICAL FIELD OF THE INVENTION
The present invention relates to aerospace vehicles and, in particular, to a stage separation system and method.
BACKGROUND OF THE INVENTION
Multistage aerospace vehicles are widely used to carry payloads into orbit and propel space vehicles into outer space. One or more booster stages accelerate an orbital stage, or vehicle, toward space. Depleted booster stages are generally dropped in order to reduce the weight of the aerospace vehicle. After each booster stage has served its purpose in attaining a certain velocity, it separates from the next stage and falls back to earth.
Timely and proper separation of stages in an aerospace vehicle often requires intricate planning and design, and typically involves high-cost, sensitive hardware and instrumentation. Separation is often accomplished by detonating pyrotechnic devices in a predetermined sequence which in turn disengage the mechanical connection between stages.
Pyrotechnic devices, however, are hazardous explosives, and inherently expensive to manufacture, deliver and handle. Therefore, the number of pyrotechnic devices employed in a given system has significant cost implications. Furthermore, the shock and debris of pyrotechnic devices may have a deleterious effect on other system components including the booster stage(s) and orbital vehicle because they cause structural damage above and beyond that required for separation. This collateral damage increases with the number of devices utilized and impacts the ability to reuse system components for subsequent launches.
SUMMARY OF THE INVENTION
An object of the present invention is to reduce the cost of placing aerospace vehicles or payloads in earth orbits and space, and in particular, to provide a multistage separation system which employs a limited number of pyrotechnic devices. Another object is to enhance the efficiency of separation of multistage aerospace vehicles. Yet another object is to minimize damage to aerospace vehicles caused by pyrotechnic devices. Still another object is to provide a safe, reliable, cost-effective separation system for multistage aerospace vehicles.
The foregoing objects are attained in accordance with the present invention by employing a separation system which requires a limited number of pyrotechnic devices. In a particular embodiment, a first stage and a second stage are provided with a plurality of separation assemblies coupling the first stage to the second stage. At least one container charged with pressurized gas in fluid communication with the separation assemblies may also be provided. The container provides pressurized gas to the separation assemblies to cause separation of the first stage and the second stage.
In another embodiment of the present invention, a first stage and a second stage may be coupled to define a cavity between the first stage and the second stage. An orifice operable to provide fluid communication between the cavity and external ambient may also be provided.
In yet another embodiment, a separation system for use on a multistage aerospace vehicle includes a manifold and a plurality of containers filled with pressurized gas, in fluid communication with the manifold. A plurality of separation nut assemblies in fluid communication with the manifold are also provided. A plurality of valves are disposed between the manifold and the containers. The valves, upon actuation, release the pressurized gas for delivery to the separation nut assemblies.
A technical advantage of the present invention includes the limited number of pyrotechnic devices required to effectuate the safe and efficient separation of the stages. By limiting the number of pyrotechnic devices, collateral damage to the structural components of the aerospace vehicle is minimized, as well as the amount of flying debris generated. This allows the operator to refurbish and reuse the aerospace vehicle during subsequent launches.
Another technical advantage includes separation of the stages using trapped air to prevent unwanted side velocities, uneven separation, and structural damage. The trapped air may be controllably released to establish predetermined separation forces.
Other technical advantages are readily apparent to one skilled in the art from the following figures, description, and claims.


REFERENCES:
patent: 5218165 (1993-06-01), Cornelius et al.
patent: 5227579 (1993-07-01), Gibson et al.
patent: 5318255 (1994-06-01), Facciano et al.
patent: 5671650 (1997-09-01), Aubret

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