WO2010134101A1 - Système anti-collision pour aéronef - Google Patents

Système anti-collision pour aéronef Download PDF

Info

Publication number
WO2010134101A1
WO2010134101A1 PCT/IT2009/000220 IT2009000220W WO2010134101A1 WO 2010134101 A1 WO2010134101 A1 WO 2010134101A1 IT 2009000220 W IT2009000220 W IT 2009000220W WO 2010134101 A1 WO2010134101 A1 WO 2010134101A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
crash system
control device
thrust unit
quantities
Prior art date
Application number
PCT/IT2009/000220
Other languages
English (en)
Inventor
Antonio Americo Cannata
Original Assignee
Vitolazzo, Giuseppe
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Vitolazzo, Giuseppe filed Critical Vitolazzo, Giuseppe
Priority to PCT/IT2009/000220 priority Critical patent/WO2010134101A1/fr
Publication of WO2010134101A1 publication Critical patent/WO2010134101A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/14—Attitude, flight direction, or altitude control by jet reaction the jets being other than main propulsion jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for

Definitions

  • said emergency system calculates the right time in which it will switch on the auxiliary engine for restore the longitudinal and/or transversal and/or axial equilibrium drastically decreasing the gravity acceleration reached by the aircraft during is descent step.
  • the auxiliary engine intervention is limited to a short time period. For this reason the emergency system, while keeping monitoring the flight conditions of the aircraft, identifies the intervention period of the auxiliary engines so as to manage at its best power and efficiency thereof.
  • the auxiliary thrust power is not discharged by the mechanical members constantly, but it is managed by a control member in order to restore — in case it is no more present — an horizontal attitude having a controlled deceleration needed for landing.
  • the emergency system communicates in real time the GPS aircraft coordinates to the closest control centre, in case in which the failure is even related to the communication systems between aircraft and ground centre.
  • Fig. 1 is a scheme of the layout within an aircraft of the devices comprised in the anti-crash system according to the present invention
  • Fig. 2 is a scheme of the orientation of the auxiliary engines provided by the system in fig. 1, and
  • Fig. 3 is a scheme of the forces acting on an aircraft provided by the anti-crash system according to the present invention.
  • the aircraft anti-crash system according to a preferred embodiment of the present invention provides the presence of: a monitoring device A, typically placed within cockpit or pilot compartment; a control device B, placed instead onto the fuselage (at rear area thereof within the preferred embodiment described); a dxrust unit C the arrangement of which will be hereinafter better described.
  • Said monitoring device A comprises an electronic board (not shown) arranged and programmed in order to sense continuously during time die aircraft attitude, particularly its longitudinal, transversal and vertical equilibrium, its altitude, as well as its speed changes.
  • said electronic board In order to allow said electronic board for performing the aforementioned monitoring functions, it is provided with devices, known on the market, as accelerometers, gyroscopes for measuring the dynamic quantities useful in checking the attitude of said aircraft, an independent transmission device which can be interfaced with the on-board devices transmitting the measured quantities, a micro-controller for addressing measured and/or calculated data, and finally a data interface for downloading of data stored by the device and loading of the desired operating configuration.
  • devices known on the market, as accelerometers, gyroscopes for measuring the dynamic quantities useful in checking the attitude of said aircraft, an independent transmission device which can be interfaced with the on-board devices transmitting the measured quantities, a micro-controller for addressing measured and/or calculated data, and finally a data interface for downloading of data stored by the device and loading of the desired operating configuration.
  • the system of the present invention is able to sense a failure from an altitude loss or an attitude dangerous for the aircraft.
  • the system measures aircraft sudden accelerations and/or decelerations which can be, for example, caused by malfunctions of the control electromechanical members just provided on said aircraft or the thrust members or by heavy meteors.
  • the measuring instruments embedded in said electronic board of the monitoring device A measure values of the angle of roll, pitch, yaw of the aircraft falling outside the previously set ranges considered safe for these angles.
  • the system of the present invention senses a emergency status by measuring instruments (such as said accelerometers and gyroscopes) values of which communicated to said micro-controller are over thresholds provided for a right status of the aircraft, and thus said micro-controller through an independent transmission device ELT (Emergency Locator Transmitter tuned on emergency frequency or the like) interfacing, if desired, devices just provided onboard for transmitting the position both to the closest control centre by sending the aircraft GPS coordinates and, at the same time, and the control device B.
  • ELT Electronicgency Locator Transmitter tuned on emergency frequency or the like

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)

Abstract

L'invention concerne un système anti-collision pour un aéronef, comprenant un dispositif de surveillance (A) conçu pour vérifier que des paramètres d'attitude de l'aéronef restent au sein de valeurs seuils prédéfinies, un dispositif de commande (B) en communication sans fil avec le dispositif de surveillance (A) et apte à actionner une unité de poussée (C) dans le but de rétablir les paramètres d'attitude au sein des valeurs seuils.
PCT/IT2009/000220 2009-05-19 2009-05-19 Système anti-collision pour aéronef WO2010134101A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/IT2009/000220 WO2010134101A1 (fr) 2009-05-19 2009-05-19 Système anti-collision pour aéronef

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IT2009/000220 WO2010134101A1 (fr) 2009-05-19 2009-05-19 Système anti-collision pour aéronef

Publications (1)

Publication Number Publication Date
WO2010134101A1 true WO2010134101A1 (fr) 2010-11-25

Family

ID=42200363

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IT2009/000220 WO2010134101A1 (fr) 2009-05-19 2009-05-19 Système anti-collision pour aéronef

Country Status (1)

Country Link
WO (1) WO2010134101A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012022915A1 (de) * 2012-11-02 2014-05-08 Karl Milton Halbow Gegenstand der Erfindung ist das Computerprogramm, welches die Arbeitsweise von Zusatzmotoren bei Großflugzeugen mit Düsenmotoren koordiniert, um durch Drosselung der Fluggeschwindigkeit den Fluglärm zu verringern und die Flugsicherheit zu gewährleisten
US20160176538A1 (en) * 2011-02-08 2016-06-23 Joseph Bekanich Smart avionics system

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB610143A (en) * 1946-03-28 1948-10-12 Roman Brykczynski Improvements in and relating to aircraft
FR1287372A (fr) * 1960-11-17 1962-03-16 équilibreur d'avion automatique à décharge d'air liquide à balancier électrique de contact
GB958548A (en) * 1962-01-31 1964-05-21 Godfrey Alan Merricks Means for retarding the rate of fall of a crash-landing aircraft
US5547149A (en) * 1994-05-16 1996-08-20 Flight Safety Systems Inc. Aircraft airbag protection apparatus and method
CA2273605A1 (fr) * 1999-06-01 2000-12-01 Tuica Gigel Dispositifs pour augmenter la securite de vol dans les transports aeriens
US6315241B1 (en) * 1999-12-23 2001-11-13 Edwin Zenith Gabriel Buoyancy system for avoiding light aircraft crashes
US7104499B1 (en) * 2002-09-25 2006-09-12 Northrop Grumman Corporation Rechargeable compressed air system and method for supplemental aircraft thrust

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB610143A (en) * 1946-03-28 1948-10-12 Roman Brykczynski Improvements in and relating to aircraft
FR1287372A (fr) * 1960-11-17 1962-03-16 équilibreur d'avion automatique à décharge d'air liquide à balancier électrique de contact
GB958548A (en) * 1962-01-31 1964-05-21 Godfrey Alan Merricks Means for retarding the rate of fall of a crash-landing aircraft
US5547149A (en) * 1994-05-16 1996-08-20 Flight Safety Systems Inc. Aircraft airbag protection apparatus and method
CA2273605A1 (fr) * 1999-06-01 2000-12-01 Tuica Gigel Dispositifs pour augmenter la securite de vol dans les transports aeriens
US6315241B1 (en) * 1999-12-23 2001-11-13 Edwin Zenith Gabriel Buoyancy system for avoiding light aircraft crashes
US7104499B1 (en) * 2002-09-25 2006-09-12 Northrop Grumman Corporation Rechargeable compressed air system and method for supplemental aircraft thrust

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160176538A1 (en) * 2011-02-08 2016-06-23 Joseph Bekanich Smart avionics system
US11999504B2 (en) * 2011-02-08 2024-06-04 InFlight Labs, LLC Smart avionics system
DE102012022915A1 (de) * 2012-11-02 2014-05-08 Karl Milton Halbow Gegenstand der Erfindung ist das Computerprogramm, welches die Arbeitsweise von Zusatzmotoren bei Großflugzeugen mit Düsenmotoren koordiniert, um durch Drosselung der Fluggeschwindigkeit den Fluglärm zu verringern und die Flugsicherheit zu gewährleisten

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