Ammunition and explosives – Igniting devices and systems – Arming devices
Reexamination Certificate
2000-01-24
2001-12-25
Poon, Peter M. (Department: 3643)
Ammunition and explosives
Igniting devices and systems
Arming devices
C102S215000
Reexamination Certificate
active
06332400
ABSTRACT:
FIELD OF THE INVENTION
The field of the invention is that associated with the provision of a replacement electromagnetic device used to initiate an action. Specifically a preferred embodiment of the present invention is an electromagnetic device that provides the necessary signal to initiate a sustainer motor on a small rocket or missile in which the warhead, with integral circuitry that is connected to a sustainer motor initiator, has been replaced by a telemetry package.
BACKGROUND
Despite the lack of test instrumentation specifically designed to fit in small volumes, there is continued pressure on the defense complex to deliver smaller, high performance weapon systems with quantifiable performance characteristics. Of course, it is expected that these be procured at a cost comparable to presently available weapon systems.
Currently there are no commercially available integrated secure telemetry systems suitable for use on small airframes, e.g., missiles or rockets. There are systems for recording data on board and later recovering the airframe and recorder as evidenced by those built by the U.S. Air Force at Eglin Air Force Base (AFB), Florida. These systems typically enjoy a 50% recovery rate, effectively doubling test requirements. Raytheon Corp. sells a system for use with the STINGER missile, however, it has no encryption capability nor does it have an IMU. The Navy at NAWC, China Lake, Calif. has built systems for use with small airframes but, these are not capable of encryption, have a limited number of channels for data capture and, do not have a fully capable IMU. Refer to U.S. Statutory Invention Registration H1288
, Control and Digital Telemetry Arrangement for an Aerial Missile
, issued to Kenneth P. Lusk.
In addition to the problem of squeezing a high performance telemetry package into a missile or rocket in place of its warhead, the necessary circuitry to insure reliable firing of the rocket or missile's sustainer motor must be provided in the same telemetry package in order to replace that firing circuitry packaged with the original warhead. Previous versions of the firing circuit used with the telemetry package used latching relays, a mechanical G-switch and, analog timing circuits. These components were bulky and, would have been difficult to integrate into a high performance telemetry package for use in a small volume. A new design, employing size and energy efficient solid state components, including digital timers, was needed.
SUMMARY OF THE INVENTION
A preferred embodiment of the present invention is a system interface designed to safely and reliably insure the firing of a sustainer motor about 250 milliseconds (ms) after launch of a rocket or missile. The sequence is:
a longitudinal accelerometer, part of an inertial measurement unit (IMU) associated with a telemetry system, is sensed and upon reaching a pre-determined state, initiates timers within a programmable logic device (PLD);
the PLD uses internal power from the missile or rocket, e.g., the “fuze power,” to enable an initiator, typically a squib;
by removing an electrical short, i.e., a path to electrical ground, across the squib's input an supplying suitable energy to the squib, the squib is energized, firing the sustainer motor.
In the missile's dormant state, the sustainer squib is shorted to ground in order to enhance safety in handling the missile or rocket prior to launch. The electrical short is removed only when the following sequence occurs:
power up of the telemetry (TM) system and initiation of the missile's fuze battery occurring at launch, and
reaching and maintaining an acceleration force of 25 G, or more, for 20 ms in a 40 ms window.
Occurrence of this sequence then enables an energizing signal to be delivered to the squib's input, resulting in the firing of the missile's sustainer motor at about 250 ms after actual launch.
This interface is designed to work in conjunction with a telemetry package having a power distribution board and fitted into a housing designed to replace the warhead in the current 2.75″ family of small missiles and rockets. This integrated capability has not been able to be packaged for use in such small platforms heretofore.
Advantages of the solid state replacement firing circuit representing a preferred embodiment of the present invention are:
compact configuration suitable for installation in small volumes
capable of interfacing to both foreign and domestic systems
low cost
compatible with existing instrumentation
easily upgraded with removable boards
simple to maintain
easy to program
ruggedized
easy interface to existing and planned systems
reliable
low power consumption
With this replacement circuit designed to interface to an integrated telemetry system, test engineers and range instrumentation personnel will no longer have to provide work-arounds or, otherwise estimate performance of small weapons systems such as 2.75″ missiles or rockets. A rocket or missile will fly as if it had the actual warhead installed, enabling the vehicle's sustainer motor at the correct time after actual launch. Test data will be taken onboard, processed and, transmitted over a secure link to locations at which it can be properly analyzed, in near real time, for input to formal evaluations of the weapon system as it flies an actual test mission.
REFERENCES:
patent: H1288 (1994-02-01), Lusk
patent: 4375192 (1983-03-01), Yates et al.
patent: 4739705 (1988-04-01), Hudson et al.
patent: 5245926 (1993-09-01), Hunter
patent: 5520115 (1996-05-01), Braun
patent: 5936188 (1999-08-01), Atkinson
patent: 6185488 (2001-02-01), Nomoto
patent: 410278730-A (1998-10-01), None
Baugher, Jr. Earl
Copier Floris C.
Kalmbaugh David
Poon Peter M.
Serventi Anthony J.
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