DE3930854A1 - Stalling speed danger warning appts. for pilot - has electronic unit evaluating dynamic air pressures picked-up from two positions on aircraft - Google Patents

Stalling speed danger warning appts. for pilot - has electronic unit evaluating dynamic air pressures picked-up from two positions on aircraft

Info

Publication number
DE3930854A1
DE3930854A1 DE19893930854 DE3930854A DE3930854A1 DE 3930854 A1 DE3930854 A1 DE 3930854A1 DE 19893930854 DE19893930854 DE 19893930854 DE 3930854 A DE3930854 A DE 3930854A DE 3930854 A1 DE3930854 A1 DE 3930854A1
Authority
DE
Germany
Prior art keywords
aircraft
pilot
instrument
electronic unit
appts
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
DE19893930854
Other languages
German (de)
Inventor
Cestmir Sebesta
January Roman
Piotr Lamers
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to DE19893930854 priority Critical patent/DE3930854A1/en
Publication of DE3930854A1 publication Critical patent/DE3930854A1/en
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • B64D43/00—Arrangements or adaptations of instruments
    • B64D43/02—Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P1/00—Details of instruments
    • G01P1/07—Indicating devices, e.g. for remote indication
    • G01P1/08—Arrangements of scales, pointers, lamps or acoustic indicators, e.g. in automobile speedometers
    • G01P1/10—Arrangements of scales, pointers, lamps or acoustic indicators, e.g. in automobile speedometers for indicating predetermined speeds
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
    • G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Measuring Fluid Pressure (AREA)

Abstract

When a corresp. difference of the dynamic pressure values taken from two different points on the aircraft indicates failure to attain a min. flight speed, an optical and/or acoustic alarm signal is released. Two tubes of i.d. 4 to 5mm are laminated in holes and bonded to the skin of the aircraft. The lower hole (2) lies at a tangent of 47 deg. plus or minus 2 deg. w.r.t. the upper hole (1) at a sufficient distance from the propeller air stream. The instrument (3), powered by a 12 volt supply, is mounted on the control panel or other obvious position in the cockpit. The instrument has a buzzer, a siren or LED. Two hoses connect the tubes to the instrument. ADVANTAGE - Favourable cost, easy to mount, works without inferference; suitable for all types of aircraft; can be retrofitted. Functions under all flying conditions, weather and at all heights.

Description

Die Erfindung betrifft ein Gerät zur Warnung des Piloten vor Unterschreitung der Mindestfluggeschwindigkeit des Flug­ zeuges.The invention relates to a device for warning the pilot before falling below the minimum flight speed of the flight stuff.

Bei Annäherung an die vorgegebene Mindestfluggeschwindig­ keit eines Flugzeuges soll der Pilot vor Unterschreitung derselben rechtzeitig gewarnt werden. Dies soll in allen Höhen, bei allen symmetrischen und asymmetrischen Flug­ zuständen, Wetterlagen, Beladungsverhältnissen oder bei Veränderung der Oberflächengüte der Flügel durch Schmutz, Insekten oder Eisansatz gewährleistet sein. Bei Rückenflug­ lage wird dies durch den Einbau eines zweiten Gerätes mög­ lich.When approaching the specified minimum flight speed The pilot should be below an aircraft be warned in good time. This is supposed to be in everyone Heights, with all symmetrical and asymmetrical flight conditions, weather conditions, loading conditions or at Change in the surface quality of the wing due to dirt, Insects or ice buildup can be guaranteed. In inverted flight This is made possible by installing a second device Lich.

"Stall warning" - Überziehwarngeräte oder -hilfsmittel sind schon seit langer Zeit in Gebrauch. Verwendet werden einfa­ che Vorrichtungen mit einer einen Mikroschalter betätigen­ den Klappe, die an der "Nase" des Flugzeuges montiert werden, bis hin zu komplizierten elektronischen Geräten der Groß­ raum- oder Militärflugzeuge."Stall warning" - stall warning devices or aids are in use for a long time. Simple are used Actuate devices with a microswitch the flap that is attached to the "nose" of the aircraft, to complicated electronic devices the big space or military aircraft.

Dabei sind allerdings die einfachen Geräte aufgrund ihrer mechanischen Funktionsweise störanfällig und auch bezüglich ihrer Genauigkeit unzulänglich, während die aufwendigen elektrischen Geräte teuer und außerdem wegen ihres hohen Gewichts für Kleinflugzeuge ungeeignet sind. Auch verschlech­ tern sie die Aerodynamik des Flugzeuges.However, the simple devices are due to their mechanical operation prone to failure and also in terms of their accuracy deficient, while the elaborate electrical devices expensive and also because of their high Weight are unsuitable for small aircraft. Too bad the aerodynamics of the aircraft.

Der Erfindung liegt die Aufgabe zugrunde, eine Lösung zu finden, die kostengünstig und leicht zu montieren ist, stö­ rungsfrei arbeitet, für alle Arten von Flugzeugen geeignet ist, ein einfaches Nachrüsten möglich macht und bei allen möglichen Flugzuständen, Wetterlagen und Höhen funktioniert.The invention has for its object a solution find that is inexpensive and easy to assemble, stö works smoothly, suitable for all types of aircraft is, makes easy retrofitting possible and for everyone possible flight conditions, weather conditions and heights works.

Diese Aufgabe wird erfindungsgemäß dadurch gelöst, daß an zwei bestimmten Stellen des Flugzeuges Staudrücke entnommen und durch eine elektronische Einheit ausgewertet werden, so daß bei einer entsprechenden Differenz der Druckwerte ein optisches und/oder akustisches Alarmsignal ausgelöst wird. Je nach Fluglage des Flugzeuges verändern sich die gemesse­ nen Staudrücke. Durch elektronisches Vergleichen dieser Drücke läßt sich rechtzeitig erkennen, wann die Mindestflug­ geschwindigkeit erreicht wird. Das Gerät wird so eingestellt, daß dem Piloten beim Auslösen des optischen und/oder akusti­ schen Signals noch genügend Zeit zur Korrektur der Geschwin­ digkeit bleibt. This object is achieved in that back pressure taken from two specific locations on the aircraft and evaluated by an electronic unit, so that with a corresponding difference in pressure values optical and / or acoustic alarm signal is triggered. Depending on the flight position of the aircraft, the measurements change dynamic pressure. By electronically comparing them Pressures can be recognized in good time when the minimum flight speed is reached. The device is set so that the pilot when triggering the optical and / or acousti signal enough time to correct the speed persistence remains.  

Die mit der Erfindung erzielten Vorteile bestehen insbeson­ dere darin, daß das Gerät genauer als die bisher gebräuch­ lichen Geräte empfangen, unabhängig von Wetter, Flächenbe­ lastung, Flugzustand oder Güte der Flügelfläche. Es ist ko­ stengünstig, von geringem Gewicht, einfach zu montieren und bei allen Flugzeugen verwendbar.The advantages achieved with the invention are in particular the fact that the device used more precisely than previously devices, regardless of the weather, surface area load, flight condition or quality of the wing area. It is knocked out Most affordable, light weight, easy to assemble and usable on all aircraft.

Ein Ausführungsbeispiel der Erfindung ist in der Zeichnung dargestellt und wird im folgenden näher beschrieben.An embodiment of the invention is in the drawing shown and is described in more detail below.

Bei Segelflugzeugen, Düsenflugzeugen, zweimotorigen Flugzeu­ gen oder Flugzeugen mit Druckpropeller wird die Druckentnah­ me direkt an der Nase des Flugzeuges vorgenommen. Bei kon­ ventionellen einmotorigen Flugzeugen wird der Druck in der Flügelnase entnommen, in ausreichender Entfernung vom Pro­ pellerluftstrahl. An der jeweiligen Entnahmestelle wird ein Loch gebohrt 1, ein zweites Loch 2 an der unteren Tan­ gente von 47° ± 2° dazu.In the case of gliders, jet aircraft, twin-engine aircraft or aircraft with a pressure propeller, the pressure is removed directly from the nose of the aircraft. In conventional single-engine aircraft, the pressure in the wing nose is removed at a sufficient distance from the propeller air jet. At the respective extraction point, a hole is drilled 1 , a second hole 2 on the lower tangent of 47 ° ± 2 °.

Zwei Röhrchen von 4 bis 5 mm Innendurchmesser werden in die Löcher einlaminiert, außen bündig mit der Flugzeugoberfläche. Das Instrument 3, das mit 12 Volt gespeist wird, wird ent­ weder am Armaturenbrett oder an einer anderen geeigneten Stelle im Cockpit montiert. Das Instrument ist mit einem Summer, einem Piepton oder einer Leuchtdiode ausgestattet. Zwei Schläuche verbinden die beiden Röhrchen mit dem Instru­ ment. (Durch zwei geeignete Luftdruckmeßsonden, die anstelle der Druckentnahmeröhrchen installiert werden, kann dieses System noch aerodynamisch verbessert werden, da dann die zwei offenen Löcher in der Außenhaut des Flugzeuges verschwin­ den.)Two tubes of 4 to 5 mm inside diameter are laminated into the holes, on the outside flush with the aircraft surface. The instrument 3 , which is supplied with 12 volts, is either mounted on the dashboard or at another suitable location in the cockpit. The instrument is equipped with a buzzer, a beep or a light emitting diode. Two tubes connect the two tubes to the instrument. (This system can be aerodynamically improved by two suitable air pressure measuring probes, which are installed instead of the pressure sampling tubes, since the two open holes in the outer skin of the aircraft then disappear.)

Bei einem Flug in ausreichender Höhe mit einer Geschwindig­ keit von V = 1,1 ÷ 1,15 Vmin wird durch Drehen der Ein­ stellschraube das Warnsignal ausgelöst, danach wird die Ein­ stellschraube abgedeckt und nicht wieder verstellt. Das Gerät ist jetzt auf eine Geschwindigkeit, die etwas oberhalb der Mindestfluggeschwindigkeit des jeweiligen Flugzeuges liegt, justiert.When flying at a sufficient altitude with a speed of V = 1.1 ÷ 1.15 V min , the warning signal is triggered by turning the adjusting screw, then the adjusting screw is covered and not readjusted. The device is now adjusted to a speed that is slightly above the minimum flight speed of the respective aircraft.

Claims (1)

Gerät zur Warnung des Piloten vor Unterschreitung der Mindest­ fluggeschwindigkeit des Flugzeuges, dadurch gekennzeichnet, daß an zwei bestimmten Stellen des Flugzeuges Staudrücke entnommen und durch eine elektroni­ sche Einheit ausgewertet werden, so daß bei einer entspre­ chenden Differenz der Druckwerte ein optisches und/oder akustisches Alarmsignal ausgelöst wird.Device for warning the pilot that the minimum airspeed of the aircraft is not reached, characterized in that dynamic pressures are taken from two specific points on the aircraft and evaluated by an electronic unit, so that an optical and / or acoustic alarm signal in the event of a corresponding difference in pressure values is triggered.
DE19893930854 1989-09-15 1989-09-15 Stalling speed danger warning appts. for pilot - has electronic unit evaluating dynamic air pressures picked-up from two positions on aircraft Withdrawn DE3930854A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19893930854 DE3930854A1 (en) 1989-09-15 1989-09-15 Stalling speed danger warning appts. for pilot - has electronic unit evaluating dynamic air pressures picked-up from two positions on aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19893930854 DE3930854A1 (en) 1989-09-15 1989-09-15 Stalling speed danger warning appts. for pilot - has electronic unit evaluating dynamic air pressures picked-up from two positions on aircraft

Publications (1)

Publication Number Publication Date
DE3930854A1 true DE3930854A1 (en) 1991-03-28

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104512544A (en) * 2013-09-26 2015-04-15 空中客车运营简化股份公司 Method of mounting pressure ports in the skin of an aircraft

Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1786841A (en) * 1925-05-28 1930-12-30 Gilbert Walton Air-speed indicator
DE706862C (en) * 1937-12-18 1941-06-07 E H Dr Phil H C Ernst Heinkel Dynamic pressure measuring device for aircraft
DE709519C (en) * 1938-12-21 1941-08-19 Versuchsanstalt Fuer Luftfahrt Arrangement for the display of the approach to the inflated flight condition
US2352955A (en) * 1944-07-04 Angle of attack indicator
DE750978C (en) * 1938-10-06 1945-02-03 Warning device for displaying critical flight conditions
US2503249A (en) * 1945-03-30 1950-04-11 Walter S Diehl Angle of attack indicator
US2538003A (en) * 1946-11-21 1951-01-16 Jennings Ralph Edward Skid indicator
US2660056A (en) * 1949-02-03 1953-11-24 Honeywell Regulator Co Angle of attack sensing device
US3008134A (en) * 1957-05-06 1961-11-07 Specialties Inc Indicating instrument for aircraft or the like
FR1293340A (en) * 1961-06-16 1962-05-11 Westland Aircraft Ltd Improvements to devices for speed measurement
DE2430805A1 (en) * 1974-06-27 1976-01-15 Bodenseewerk Geraetetech DEVICE FOR DETERMINING THE AERODYNAMIC FLOW CONDITION OF A WING AIRPLANE
DE3010172A1 (en) * 1980-03-17 1981-09-24 Josef W. 5100 Aachen Tichy Aircraft glide and lift measuring system - uses momentary direction of air flow relative to fixed line or plane
US4350314A (en) * 1980-07-10 1982-09-21 The Board Of Trustees Of Western Michigan University Wing mounted stall condition detector
DE3417232A1 (en) * 1984-05-10 1985-11-28 Roland Dipl.-Ing. Klotz (FH), 7142 Marbach Method and device for determining the towing speed of sail planes
DE3544144A1 (en) * 1985-12-13 1987-06-25 Eduard Prof Dr Ing Igenbergs METHOD AND DEVICE FOR DETERMINING A FLOW ANGLE ON VEHICLES
EP0262702A1 (en) * 1986-09-30 1988-04-06 The Boeing Company Apparatus and method for warning of a high yaw condition in an aircraft
JPH05320983A (en) * 1992-05-22 1993-12-07 Kobe Steel Ltd Pretreatment for electroplating

Patent Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2352955A (en) * 1944-07-04 Angle of attack indicator
US1786841A (en) * 1925-05-28 1930-12-30 Gilbert Walton Air-speed indicator
DE706862C (en) * 1937-12-18 1941-06-07 E H Dr Phil H C Ernst Heinkel Dynamic pressure measuring device for aircraft
DE750978C (en) * 1938-10-06 1945-02-03 Warning device for displaying critical flight conditions
DE709519C (en) * 1938-12-21 1941-08-19 Versuchsanstalt Fuer Luftfahrt Arrangement for the display of the approach to the inflated flight condition
US2503249A (en) * 1945-03-30 1950-04-11 Walter S Diehl Angle of attack indicator
US2538003A (en) * 1946-11-21 1951-01-16 Jennings Ralph Edward Skid indicator
US2660056A (en) * 1949-02-03 1953-11-24 Honeywell Regulator Co Angle of attack sensing device
US3008134A (en) * 1957-05-06 1961-11-07 Specialties Inc Indicating instrument for aircraft or the like
FR1293340A (en) * 1961-06-16 1962-05-11 Westland Aircraft Ltd Improvements to devices for speed measurement
DE2430805A1 (en) * 1974-06-27 1976-01-15 Bodenseewerk Geraetetech DEVICE FOR DETERMINING THE AERODYNAMIC FLOW CONDITION OF A WING AIRPLANE
DE3010172A1 (en) * 1980-03-17 1981-09-24 Josef W. 5100 Aachen Tichy Aircraft glide and lift measuring system - uses momentary direction of air flow relative to fixed line or plane
US4350314A (en) * 1980-07-10 1982-09-21 The Board Of Trustees Of Western Michigan University Wing mounted stall condition detector
DE3417232A1 (en) * 1984-05-10 1985-11-28 Roland Dipl.-Ing. Klotz (FH), 7142 Marbach Method and device for determining the towing speed of sail planes
DE3544144A1 (en) * 1985-12-13 1987-06-25 Eduard Prof Dr Ing Igenbergs METHOD AND DEVICE FOR DETERMINING A FLOW ANGLE ON VEHICLES
EP0262702A1 (en) * 1986-09-30 1988-04-06 The Boeing Company Apparatus and method for warning of a high yaw condition in an aircraft
JPH05320983A (en) * 1992-05-22 1993-12-07 Kobe Steel Ltd Pretreatment for electroplating

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
GB-Z: Stalling and the Indicator. In: THE AEROPLANE, January 19, 1952 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104512544A (en) * 2013-09-26 2015-04-15 空中客车运营简化股份公司 Method of mounting pressure ports in the skin of an aircraft
CN104512544B (en) * 2013-09-26 2018-06-22 空中客车运营简化股份公司 Method pressure port being mounted in the covering of aircraft

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