Communications: electrical – Aircraft alarm or indicating systems
Reexamination Certificate
1999-09-24
2001-04-10
Anderson, Bruce C. (Department: 2881)
Communications: electrical
Aircraft alarm or indicating systems
C340S947000, C250S50400H, C250S494100, C250S495100, C250S493100
Reexamination Certificate
active
06215416
ABSTRACT:
FIELD OF THE INVENTION
The present invention relates generally to a thermal signaling system. More particularly, the present invention relates to method and apparatus well-suited for signaling to aircraft from the ground.
BACKGROUND OF THE INVENTION
Often times it is necessary to signal to an aircraft from the ground. For example, in military tactical operations, ground troops signal aircraft such as helicopters to identify landing sites, targets, and the like. In that such aircraft often fly night missions, they normally are equipped with heat sensors, such as infrared sensors, by which the aircraft can be flown. For instance, the AH-64 (Apache) helicopter is equipped with forward looking infrared (FLIR) that senses light in the 6-12 micron range.
Despite being so equipped, helicopters normally are landed in night tactical environments without the use of heat sensing systems such as FLIR. In the case of the AH-64 helicopter, a copilot gunner positioned in the front seat of the helicopter images light signals sent from personnel on the ground and, from these light signals, provides verbal instructions to the pilot-in-command seated in the back seat to aide him in landing the aircraft. Such verbal instructions from the copilot gunner generally are necessary in such situations because the pilot-in-command cannot see the immediate foreground of the helicopter. The light signals sent to the helicopter occupants normally are made with a plurality of individual light sources such as light sticks. To aid the copilot gunner in viewing the light signal, the copilot normally uses night vision goggles which amplify the light signals emitted by the light sources.
The signaling procedure described above is lacking for several reasons. First, the pilot-in-command must land the helicopter “blind” in that the light sources used to form the light signal do not emit enough heat so as to be detectable with heat sensing systems such as FLIR. Therefore, the pilot-in-command must rely solely on the verbal instructions given by the copilot gunner seated in the front seat in landing the aircraft. Although the verbal instructions provided by the copilot gunner normally are adequate so as to facilitate proper landing of the helicopter, such a procedure is inferior to a procedure in which the pilot-in-command can also see the signals provided by the ground personnel. Moreover, since the copilot gunner must concentrate on the light signals and on providing precise verbal instructions to the pilot-in-command, the copilot cannot focus on ensuring that the aircraft is clear of all obstructions that could interfere with the aircraft during landing. Therefore, the landing procedure described above provides a substantial risk of crash landings and personnel injuries. In addition to the craft landing disadvantages of conventional signaling systems, use of such systems further invites enemy attack, in that conventional light sources emit light in the visible spectrum. These light signals directed toward friendly aircraft can similarly be seen by enemy troops. Therefore, when such signaling systems are used, the aircraft occupants, as well as ground personnel, are vulnerable to enemy attack.
In an attempt to overcome some of the drawbacks of the aforementioned signaling systems, alternative field solutions have been tried. In one such solution, metal cans, such as coffee cans, have been filled with sand soaked in jet fuel and then ignited so as to burn the jet fuel. Once the fuel had burned for a period of time adequate to heat the metal cans and sand, the flames were extinguished and the cans arranged in an inverted “Y” configuration such that the heat signature of the cans would create a thermal “Y” signal that could be detected by the helicopter heat sensing system. Although providing enough heat so that the heat sensing system could be utilized, this signaling system also is disadvantageous for several reasons. First, jet fuel is highly flammable. For this reason, its use creates unacceptable safety risks to ground personnel and aircraft occupants alike. Secondly, the heated cans provide non-directional heat signals that can be detected by enemy forces as well as the aircraft pilots. Therefore, the use of such heat signaling devices again risks enemy attacks.
From the above, it can be appreciated that it would be advantageous to have a thermal signaling system that is detectable by a heat sensing systems such as FLIR which further is generally safe to use and which is not easily detectable to enemy troops.
SUMMARY OF THE INVENTION
The present invention relates to a thermal signaling device, comprising a container including a thermal emitting surface and an interior space, and at least one heat source disposed within the interior space of the container. In operation, the heat source is activatable to heat the thermal emitting surface such that the thermal emitting surface can be detected by a thermal sensing system.
In a preferred embodiment, the container includes a container body which forms the interior space, and a container lid that forms the thermal emitting surface. Furthermore, the device preferably comprises a retractable support mechanism with which the container can be supported in a reclined orientation.
In addition, the present invention relates to a method for signaling to an aircraft, comprising activating at least one non-electrical, non-volatile heat source, positioning at least one signaling container on the ground in a desired pattern, each signaling container including a thermal emitting surface, and placing at least one heat source in each of the containers such that the heat source will heat the thermal emitting surface so that aircraft can detect the thermal emitting surface with a heat sensing system.
The features and advantages of this invention will become apparent upon reading the following specification, when taken in conjunction with the accompanying drawings. It is intended that all such additional features and advantages be included therein with the scope of the present invention, as defined by the claims.
REFERENCES:
patent: 4945248 (1990-07-01), Farr
patent: 5567950 (1996-10-01), Meeker et al.
patent: 5736744 (1998-04-01), Johannsen et al.
Anderson Bruce C.
Thomas Kayden Horstemeyer & Risley
Wells Nikita
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