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Automatic Autopilot Landing System for aircraft.
Automatic Autopilot Landing System for aircraft.We are currently seeking investors and manufacturing companies to license, purchase patent rights or enter into a royalty agreement for this timely invention.
Interested parties can send e-mail to contact listed at the bottom of this page.

Invention description

2 | P a g e 4. DESCRIPTION. Technical field of invention: This invention particularly relates to aeronautical engineering and more particularly provides device and methodology for facilitating landing of aerial vehicles which can further be utilized for enhancing flight capabilities in near earth environment. Prior art: Landing of aircraft in general is the most difficult step in the operation of aircraft. It requires highly-skilled operators, involves non-negligible risk, and can be performed only in favorable flight conditions. In existing technology for landing of VTOL aircraft or Helicopter a predefined helipad or base station is required , apart from that it requires GPRS system ,and a continuous communication with base station . A basic problem presented in landing an aircraft is to guide the aircraft to approach the runway asymptotically to intercept the runway at a small angle thus preventing the aircraft from violently contacting the runway and experiencing considerable impact at touchdown. The necessity for asymptotic approach and the elimination of violent impact is evident when safety factors as well as wear and tear on aircraft components are considered. Ground effect can generally be defined as the reaction on the craft due to the downwash of air from the rotating blades striking the ground and then reflected back from the ground to the craft tending to increase air density and hence rotor lift as the craft enters the ground effect zone. The ground effect zone can be generally defined as a zone or volume having a diameter and height equal to the diameter of the rotor blades. In existing helicopters having automatic radar altitude hold capability, the pilot may select through a conventional mode select panel or through manual override of the altitude hold, an altitude at which it is desirable to hover; for example, during a rescue mission. The autopilot through a servo amplifier drives a parallel trim actuator which is connected to the pilot's collective control stick through a preloaded force feel spring. Included also in the trim servo system is a clutch means, integral with the trim actuator, which allows the actuator control arm to be declutched from the servomotor. Also included is a detent switch operable by force spring and a collective control stick position sensor. 3 | P a g e Currently the RPVs are landed by human operators that either observe it from the land strip or monitor the picture transmitted by a TV camera mounted on board. The guidance commands are radio transmitted to the RPV. Both methods pose considerable difficulties since the pilot is put into unfavorable conditions compared to the operation of ordinary aircraft and receives only incomplete information. In particular, the pilot's perception of the RPV position is limited, he lacks some motion cues, is less percipient of sudden disturbances etc. The ability to land the RPV in adverse conditions such as bad weather, limited visibility, or at night is severely limited. Landing of manned aircrafts on small airstrips such as aircraft carriers present similar difficulties. The landing platform is very small compared to the typical ground landing strip, so that very accurate guidance to the touch down point is required. The pilot lacks a stationary reference like the horizon or some terrain features; strong wind disturbances are often encountered; the landing process is very short and demands very quick response of the pilot to correct the flight path deviations; and in rough seas the landing platform is moving in six degrees of freedom with considerable amplitude. Problems to be solved: From the above mentioned problems prevalent in the existing technology there was a long felt need in the field of art to provide a device and methodology for aircraft landing where the pilot does not requires the help of any GPRS or communication with base station . He can land his helicopter or VTOL aircraft safely without this technologies Pilot does not have any stress of judgment .The possibilities of accidents can be reduced to a great extent . These and other advantages will be more readily understood by referring to the following detailed description disclosed hereinafter with reference to the accompanying drawings and which are generally applicable to other Method and Apparatus for home automation and security systems using cell phone. Object: 1. Primary object of present invention is to provide a system of autopilot landing which enables the pilot to land safely in extreme conditions, when the pilot requires blind landing and finds difficulty in judgment such as in fog conditions, brownouts etc without the help of GPS and communication with base station. 2. Automatic Autopilot Landing System for VTOL aircraft and Helicopter where pilot does not requires the help of any GPRS or Communication with base station. 3. Further object of present invention is to provide a methodology where pilot does not have any stress of judgment. 4. Yet another object of present invention is to drastically reduce the possibilities of accidents. Other objects, features and advantages will become apparent from detail description and appended claims to those skilled in art. STATEMENT: Present invention relates to an automatic landing system comprising of four sensors, which through ADC converter processes data with connected microcontroller like 8051/Arm 7/89C52 etc or with neural network controller, which is further processed at mechanical control unit for controlling like Swash-plate in helicopter or thrust Control in VTOL/STOL aircraft during landing. . The system is based on microcontroller which enables for safe landing of helicopter VTOL, STOL aircraft/ UAV etc in adverse conditions and limited visibility. Hardware model of neural network can also be applied instead of microcontroller for this purpose. This system enables safer landing during degraded environment such as brownout , whiteout , night operations and the like . Microcontroller system using different sensors is used for this purpose. Ultrasonic radar system is used for detection of altitude. In normal conditions when autopilot landing system will start at that time , firstly the altitude is detected . After that when the output of four sensors will be same it will go to controller and the helicopter will come down until 5 seconds and then the helicopter will get stabled for 2 to 3 seconds on that altitude and then again the altitude will be detected by the sensors and again output will get same the helicopter will come down for 5 seconds and when the output of sensors will be zero the engine will stop. When the output of one or two sensors will be different at that time the helicopter will move aside or in forward direction as per the programming of microcontroller or neural network implemented hardware. The scope of present invention is defined by the claims which are incorporated into this section by reference. A more complete understanding of embodiments of the present invention will be afforded to those skilled in the art, as well as a realization of additional advantages thereof, by a consideration of the following detailed description. References will be made to appended sheets of drawings that first be described briefly. 5 | P a g e Detailed description: Aircraft particularly helicopters are very difficult to operate during landing, when the pilot is unable to observe adequately the motion of helicopter with respect to landing area . The proposed system is based on microcontroller like 8051/Arm 7/89C52 etc or neural network controller connected to sensors through ADC converter which carries signals to mechanical control unit for controlling like Swash-plate in helicopter or thrust Control in VTOL/STOL aircraft during landing which 6 | P a g e enables safe landing of helicopter and VTOL aircraft in adverse conditions and limited visibility. In this process ultrasound waves or ultrasonic transmitter are used and signal are received by ultrasonic receiver . This system enables safer landing during degraded environment such as brownout, whiteout, night operations and the like . Microcontroller system using different sensors is used for this purpose. Frequency of all the four sensors will be different so that the receiver should not receive the signal from another transmitter . Hardware model of neural network can also be applied instead of microcontroller. This system enables pilot to land safely during reduced visibility conditions. In one of the preferred embodiment of present invention ultrasonic radar system is used for the detection of altitude. Apart from that we can used laser light technology an RF waves for measurement of altitude. In normal conditions when output of all four sensors will be the same autopilot landing system start’s, at that time firstly the altitude will be detected . After that when the output of four sensors will be same it will go to controller and the helicopter will come down until predefined time and then the helicopter will get stabled for few seconds on that altitude and then again the altitude will be detected by the sensors and again output will get same the helicopter will come down for a predefined timing and when the output of sensors will be zero the engine will stop. Now , when the output of one or two sensors will be different at that time the helicopter will move aside or in forward direction as per the programming of microcontroller or neural network implemented hardware. This system enables safer landing during degraded environment such as brownout , whiteout , night operations and the like . This system helps pilot to land safely during reduced visibility conditions. Best Method / Example of Working of Invention For the purpose of better understanding, illustration is hereafter provided of the working of the invention in provided working condition. But the illustrations shall not be construed as a limiting factor for the process and applicability as it can easily be understood by the person skilled in the art that even further modifications and applications of the inventions are possible by making relevant modifications, amendments and alterations in the design without deferring from the basic conscience of the invention. If a helicopter approaches a landing site in desert , downwash from the rotor typically strips up the sand which greatly reduces visibility . This is very dangerous because the pilot cannot adequately observe landing area to obtain the necessary visual feedback of aircrafts speed and position. By installation of present system In normal conditions when output of all four sensors will be the same autopilot landing system start’s, at that time firstly the altitude will be detected . After that when the output of four sensors will be same it will go to controller and the helicopter will come down until predefined time and then the helicopter will get stabled for few seconds on that altitude and then again the altitude will be detected by the sensors and again output will get same the helicopter will come down for again predefined time and when the output of sensors will be zero the engine will stop. Now , when the output of one or two sensors will be different at that time the helicopter will move aside or in forward direction as per the programming of microcontroller or neural network implemented hardware. Additional advantages and modification will readily occur to those skilled in art. Therefore, the invention in its broader aspect is not limited to specific details and representative embodiments shown and described herein. Accordingly various modifications may be made without departing from the spirit or scope of the general invention concept as defined by the appended claims and their equivalents.

Advantages of this invention

8 | P a g e I claim:- 1. Device and methodology for automatic landing of aircraft comprising of sensors, ADC converter, microcontroller or neural network controller and alternatively laser light technology, an RF waves for measurement of altitude which carries data to mechanical controlling unit Swash-plate in helicopter or thrust Control in VTOL/STOL aircraft etc for controlling which enables safe landing of aircrafts even under low visibility conditions or when support from base station is not available. 2. The device as claimed in claim 1 comprises ultrasonic radar for detection of altitude for which ultrasound waves or ultrasonic transmitter are used and signal are received by ultrasonic receiver, but even other technologies like laser light technology an RF waves etc can be used for measurement of altitude. 3. Frequency of all the four sensors used in the device as claimed in claim 2 is kept different so that the receiver shall not receive the signal from another transmitter but the methodology can also be performed by implementing frequency of any range according to the requirement and the working conditions. 4. During the process of landing of the aircraft as claimed in claim 3 when the output of all four sensors is same, autopilot landing system will start at the time of landing means firstly the altitude will be detected and after that when the output of four sensors will be same it will go to controller and the helicopter will come down up till predefined time and then the aircraft will get stabled for some time on that altitude and then again the altitude will be detected by the sensors and again output will get same the aircraft will come down for again predefined time and when the output of sensors will be zero the engine will stop. 5. In the process as claimed in claim 4 when the output of one or two sensors will be different at that time the aircraft will move aside or in forward direction as per the programming of microcontroller or neural network implemented hardware . 6. The microcontroller as claimed in claim 5 is 8051/Arm 7/89C52 but any other microcontroller or neural network controller according to requirement and working conditions can be applied for the said purpose.

Inventor : Anil Hundikar
Contact : manish@patint.co.in

Patent Number : 2821/MUM/2011


For more information about this invention/patent please write us at contact@worldwideinvention.com
Invention Drawings
Automatic Autopilot Landing System for aircraft.Automatic Autopilot Landing System for aircraft.Automatic Autopilot Landing System for aircraft.Automatic Autopilot Landing System for aircraft.
R&D Global Business Ventures LLC
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