EP2499042A2 - Aircraft - Google Patents

Aircraft

Info

Publication number
EP2499042A2
EP2499042A2 EP10788157A EP10788157A EP2499042A2 EP 2499042 A2 EP2499042 A2 EP 2499042A2 EP 10788157 A EP10788157 A EP 10788157A EP 10788157 A EP10788157 A EP 10788157A EP 2499042 A2 EP2499042 A2 EP 2499042A2
Authority
EP
European Patent Office
Prior art keywords
aircraft
control
axis
balance
control surface
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Withdrawn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
EP10788157A
Other languages
German (de)
English (en)
French (fr)
Inventor
Edward Marganski
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.)
Aeroem Edward Marganski Spolka Komandytowo- Akcyjn
Original Assignee
Marganski Edward
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 Marganski Edward filed Critical Marganski Edward
Publication of EP2499042A2 publication Critical patent/EP2499042A2/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/04—Noseplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/12—Canard-type aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/10—Adjustable control surfaces or members, e.g. rudders one surface adjusted by movement of another, e.g. servo tabs

Definitions

  • the object of the invention is an aircraft provided with a device for creating a constant moment in relation to the axis of rotation of an additional control surface placed at the front of the aircraft at an as large as possible distance from the centre of gravity of the aircraft.
  • the Polish patent specification no. 20191 1 describes a method of control of a flying aircraft of required degree of stability, wherein movable control surfaces placed at the front of the airframe at a large distance forward of the centre of gravity, on which control surfaces a constant aerodynamic force is applied, which force is independent of the angle of attack of the airframe, of the setting angle of the movable control surface and of other configuration parameters of the airframe, are acted upon by means of connections of electrical and/or hydraulic control elements, as the result of which a defined deflection of the control element corresponds to a defined force acting on the movable control surface, wherein the movable control surface is suspended on a transverse axis located forward of the resultant aerodynamic force acting on the movable control surface, and wherein a constant adjustable moment set by the pilot is applied to the transverse axis or wherein the deflection of the movable control surface is changed in order to attain a constant, adjustable by the pilot, pressure difference at selected points of the upper and lower side of the movable control surface.
  • the moment applied caused positioning of the additional control surface under a resultant angle in relation to the undisturbed stream of air, providing thereby generation of a vertical force that was essentially dependant only on the controlled moment.
  • the aircraft according to the invention provided with a control surface that generates controlled vertical force independent of the angle of attack of the aircraft and its configuration, is characterized in that the vertical force is controlled by deflecting control elements mounted pivotably on the rotation axis of the balancing and control surface, which deflection causes tilting of the balancing and control surface mounted rotatably on the axis, whereas the said axis is mounted perpendicularly to the plane of symmetry of the aircraft.
  • Fig. 1 represents a top view of an aircraft provided with movable control elements placed along an axis perpendicular to the plane of symmetry of the aircraft
  • Fig. 2 represents a side view of an aircraft provided with movable control elements placed along an axis perpendicular to the plane of symmetry of the aircraft
  • Fig. 3 represents a top view of an aircraft provided with movable control elements placed along an axis oblique to the plane of symmetry of the aircraft
  • Fig. 1 represents a top view of an aircraft provided with movable control elements placed along an axis perpendicular to the plane of symmetry of the aircraft
  • Fig. 2 represents a side view of an aircraft provided with movable control elements placed along an axis perpendicular to the plane of symmetry of the aircraft
  • Fig. 3 represents a top view of an aircraft provided with movable control elements placed along an axis oblique to the plane of symmetry of the aircraft
  • Fig. 1 represents a top view of an aircraft provided with
  • FIG. 4 represents a side view of an aircraft provided with movable control elements placed along an axis oblique to the plane of symmetry of the aircraft
  • Fig. 5 represents a top view of an aircraft provided with movable control elements placed along an axis parallel to the plane of symmetry of the aircraft
  • Fig. 6 represents a side view of an aircraft provided with movable control elements placed along an axis parallel to the plane of symmetry of the aircraft
  • Fig. 7 represents an example embodiment of the mechanical steering of the balance and control surface.
  • Fig. 1 and Fig. 2 show an example embodiment of the invention, wherein control elements 3 are placed on axis 4 perpendicular to the plane of symmetry 5 of an aircraft 6.
  • the additional balance and control surface 1 is freely suspended on axis 2 and the profile thereof is symmetrical and with the same configuration of control elements 3 deflected on axis 4 locked in position zero, the system practically does not generate any lift, and consequently does not change the balance of the aircraft and its stability in practical application.
  • Deflecting the control elements 3 by a defined angle changes the angle of attack of the balance and control surface1, and generates thereby a constant force independent of the angle of attack of the aircraft 6 and of the configuration thereof.
  • control element 3 In this case the role of the control element 3 is assumed by the cut off external part of the additional control and balance surface 1 itself.
  • This external part of the control and balance surface ⁇ upon deflecting it in relation to the basic part thereof generates a moment equal to the force generated by the control elements 3 multiplied by the arm a equal to the distance between axis of rotation 2 of the control and balance surface ⁇ and the axis of rotation of the control elements 3.
  • All three example embodiments satisfy the basic requirements, and the choice thereof depends on the aerodynamic and structural optimisation for a particular application.
  • control elements 3 in relation to the control and balance surface 1 may be effected by direct mechanical steering and also by means of various types of mechanical, electromechanical, hydraulic or pneumatic servo-mechanisms.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Toys (AREA)
EP10788157A 2009-11-09 2010-11-05 Aircraft Withdrawn EP2499042A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
PL389502A PL389502A1 (pl) 2009-11-09 2009-11-09 Statek powietrzny
PCT/PL2010/000110 WO2011056082A2 (en) 2009-11-09 2010-11-05 Aircraft

Publications (1)

Publication Number Publication Date
EP2499042A2 true EP2499042A2 (en) 2012-09-19

Family

ID=43970605

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10788157A Withdrawn EP2499042A2 (en) 2009-11-09 2010-11-05 Aircraft

Country Status (3)

Country Link
EP (1) EP2499042A2 (pl)
PL (1) PL389502A1 (pl)
WO (1) WO2011056082A2 (pl)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7767121B2 (en) 2008-11-10 2010-08-03 Kryron Global, Llc Solid composition having enhanced physical and electrical properties
PL414124A1 (pl) * 2015-09-23 2017-03-27 Edward Margański Statek powietrzny pionowego startu i lądowania

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR943005A (fr) * 1942-03-27 1949-02-24 Miles Aircraft Ltd Perfectionnements apportés aux avions
US2747816A (en) * 1950-05-11 1956-05-29 Ben O Howard Canard type airplane and controls therefor
PL201911A1 (pl) 1977-11-03 1979-07-02 Wytwornia Sprzetu Komunikacyjn Regulator temperatury powietrza
FR2719548B1 (fr) * 1994-05-03 1996-07-05 Aerospatiale Avion de transport à empennage avant.
CA2444560C (en) * 2002-10-21 2008-09-23 The Boeing Company Method and apparatus for rotatably supporting movable components, including canards

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2011056082A2 *

Also Published As

Publication number Publication date
WO2011056082A3 (en) 2011-08-25
WO2011056082A2 (en) 2011-05-12
PL389502A1 (pl) 2011-05-23

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Owner name: AEROEM EDWARD MARGANSKI SPOLKA KOMANDYTOWO- AKCYJN

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Inventor name: MARGANSKI, EDWARD

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