 Device for guiding a missile |
| The above object is achieved according to the present invention by a device for guiding a missile ... |
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| Vehicle guidance system for guided missiles having adaptive trajectory bias |
| What is claimed is: 1. In a guided missile system of the type including a seeker for providing ... |
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| Static vent units |
| According in one aspect this invention provides a static vent unit for use on a vehicle and which ... |
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| Differential GPS ground station system |
| An object of the present invention is to provide a differential GPS ground station having enhanced ... |
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| Communication system employing space-based and terrestrial telecommunications equipment |
| To meet the above and other objectives, the present invention provides for a communications system ... |
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| Ins alignment method using a doppler sensor and a GPS/HVINS |
| The following description of the preferred embodiments of the invention shown in the FIG. 1 and FIG... |
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| Method and device for displaying animated navigation information |
| The present invention satisfies the above described need and other needs by providing a GPS ... |
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| Bobbin transfer tail retainer |
| What is claimed is: 1. A yarn bobbin having a transfer tail retainer comprising a cylindrical tube ... |
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| Yarn carrier |
| An object of the present invention is to provide an improved yarn carrier. Another object of the ... |
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| Textile yarn carrier |
| This invention relates to tubular carriers of textile yarn packages particularly used with winding ... |
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Sonotube compatible unmanned aerial vehicle and system
| Details |
Inventors: Woodland, Richard L. K.;
Assignee:
Primary Examiner: Poon; Peter M.
Assistant Examiner: Ducker, Jr.; Charles R
Attorney, Agent or Firm: Bullock; Roddy M.
The present invention is generally comprised of a sonotube-compatible unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV. The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section. The modular sections are attached to adjacent sections by uniform lock sealing rings and related components. The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming. A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight. Man-portable operation is accomplished by the use of a launch canister apparatus. The launch canister comprises retractable launch stabilizing legs, turbine engine exhaust orifices, and various antennas. The launch canister apparatus alternatively comprises a modified type "A", "B", or "C" sonotube launch canister. The system of the invention also comprises a portable Command, Control, Communications, Computer, and Intelligence (C4I) control and sensing analysis console. The console is preferably ruggedized, waterproof, shockproof, and comprises necessary control and analysis computers, input/output devices, antennas, and related hardware and software for vehicle and mission control. A C4I console and/or launch canisters may be transported by means of a backpack adapted for man portability. |
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DETAILED DESCRIPTION The present invention is generally comprised of a sonotube-compatible, micro-miniature, unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV.
The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section.
The modular sections are attached to adjacent sections by uniform lock sealing rings and related components.
The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming.
A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight.
The nose section of the UAV can accommodate either fixed forward, down, side or upward mounted sensors, optionally mounted on a gimbaled turret.
The nose section typically houses a control module comprised of a system computer, transceiver and telemetry means, and navigation electronics.
The payload section is comprised of an airframe casing housing a rotary payload launcher or gravity payload release mechanism with sequential release doors for payload packages.
In particular, payload rotary launcher is designed for full length, half length, or quarter length size payloads.
The payload section may also comprise a fixed sensor or photographic payload which is not jettisoned from the UAV.
The wing and fuel tank section is comprised of an airframe casing housing means for fuel storage and delivery, and a pair of retracted two sequence, or single sequence, spring-actuated wing assemblies.
Wing assemblies are typically equipped with aileron control surfaces and spring loaded winglets on the outboard wing sections.
The wings are modular and can be field replaced or repositioned with other types of wings for higher, or lower speed aeronautical, or payload weight and balance considerations
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Telecommunications 
