US2876585A - Flying devices - Google Patents

Flying devices Download PDF

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Publication number
US2876585A
US2876585A US523576A US52357655A US2876585A US 2876585 A US2876585 A US 2876585A US 523576 A US523576 A US 523576A US 52357655 A US52357655 A US 52357655A US 2876585 A US2876585 A US 2876585A
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Prior art keywords
speed
plane
control
wing
vane
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US523576A
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English (en)
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Zaic Frank
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Individual
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Individual
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Priority to US523576A priority Critical patent/US2876585A/en
Priority to GB16987/56A priority patent/GB813184A/en
Priority to DEZ5641A priority patent/DE1064405B/de
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    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H27/00—Toy aircraft; Other flying toys

Definitions

  • This invention relates to the control of flying devicesparticularly, although not exclusively, to control means for model airplanes.
  • the invention is especially directed to flying devices that are launched or propelled initially at high speeds, and which must descend or glide downwardly at relatively lower speeds after the initial propelling force has been dissipated.
  • the aerodynamical balance of the device is so fixed with relation to the center of gravity that the airplane assumes a high-lift condition under all conditions of flight or speed.
  • a highlift aerodynamical balance is detrimental during the initial period when the device is operating under the launching force, which is several times greater than that required merely to overcome the force of gravity. It is because of the drag incident to such set high-lift conditions that conventional devices are unable to achieve the heights that would be possible if there were no such retarding force.
  • the lift generated at launching speedswith the balance set for highlift is of such a magnitude as to cause looping or spiralling.
  • the aerodynamical balance about the center of gravity of an airplane is usually obtained by having the center of the wings lifting force positioned behind the center of gravity; but inasmuch as, in this position, the wings lift tends to produce a diving tendency, the stabilizer is negatively angled, so that the downward force resulting from the airflow reaction on the upper surface of the stabilizer will offset the diving tendency.
  • the control of my invention will provide highlift conditions; and at high speed or launching condi-. tions it will provide zero lift, so that the device, when launched, is enabled to follow a straight line or arrow flight trajectory. In this manner, the said disadvantage of unpredictability of conventional devices is eliminated.
  • Fig. 1 is a perspective view of a form of my invention, showing the control components at low speed positions.
  • Fig. 2 is a frgamentary perspective of the rear portion of the device of Fig. 1, showing the control components at high speed position.
  • Fig. 3 is a fragmentary plan view of the rear part of the device of Fig. l. i
  • Fig. 4 is a plan view of Fig. 2.
  • Fig. 5 is a rear view of Fig. 1.
  • Fig. 6 is a rear view of Fig. 2.
  • Fig. 7 is a somewhat enlarged longitudinal section of the rear portion of the device when at its low speed position, the section being taken substantially along line 7-7 of Fig. 8.
  • Fig. 8 is a side view of the device of Fig. 1 showing the forces acting thereupon at low speed.
  • Fig. 9 is a side view of said device showing the forces acting thereupon at high speed.
  • Fig. 10 is a perspective view of the rear portion of a somewhat modified form of the device of Fig. 1, showing the control vane in spaced relation to the rudder, the device being shown in low speed position.
  • Fig. 11 is a plan view of Fig. 10, the dot-dash lines showing the control vane and associated flexible member at high speed position.
  • Fig. 12 is a perspective view of a unitary control device according to my invention, adapted for attachment to the stabilizer and rudder portion of a plane shown by.d o t dash lines.
  • Fig. 13 is a plan view of the wing portion of the flying wing form of my invention when the device is at low speed position.
  • Fig. 14 is a rear view of the device of Fig. 13 looking in the direction of arrows 27-27.
  • Fig. 15 is a section of an airplane embodying the structure of Fig. 13, the section being taken substantially along line 28-28 thereof, the view showing the forces acting.
  • Fig. 16 is a view like Fig. 15, but showing the forces acting thereupon at high speed conditions.
  • Fig. 17 is a fragmentary perspective of the rear portion of Fig. 13.
  • a control vane is employed for operating the plane-elevating component, whether it be a stabilizer, a movable trailing edge'flap, or the entire wing itself.
  • the said control vane is movable between a predetermined high speed position and low speed positions.
  • said control vane is hinged, is disposed in a plane substantially at right angles to the plane-elevating component, and in most forms it is yie'ldably urged into its low speed limiting position.
  • the yieldable means normally urging said control vane into its said low speed position is an elastic band or equivalent member.
  • said resiliently operated control vane is at times referred to herein as a spring loaded member.
  • a wing component extends transversely from opposite sides of the fuselage 11, a fixed rudder 12 being disposed at the rear of the fuselage.
  • the stabilizer referred to generally by the reference numeral 13, contains a forwardly disposed'fixed portion 14 and a rear movable portion 15, equivalent to an elevator.
  • said movable portion 15 will, where convenient, be re ferred to herein as the stabilizer.
  • the said movable stabilizer portion 15 is attached by hinge means 16, to the stationary portion 14, whereby the former is movable between upper and lower limiting positions.
  • the upper limiting position is defined bybottom surface 17 of said rudder 12, stabilizer portion 15 being lift position; and under these conditions, the plane will follow a substantially arrow-like path.
  • the length of flexible member 28 is such that, as the control vane 21 moves outwardly under the action of resilient member 24, it (flexible member 28) will apply an upward pull to the stabilizer 15 tothc position shown in Figs. 1 and 5the upper limit being, as aforesaid, the plane of contact of the stabilizer 15 with the bottom edge 17 of the rudder 12. In this position the airplane is caused to fly with its wing at a high angle of attack, the action of said resilient member 24 being such as to hold it in such position. This results in the maintenance of low speed conditions for descent and landing.
  • the gravitational pull G at the center of gravity 31 is disposed forwardly of the wing lift W, the stabilizer 11ft being indicated by the arrow S.
  • the angle of attack is identified by the reference letter A
  • the flight path being indicated by the arrow B
  • the a flight path is indicated by the arrow C.
  • the stop bar 18 Positioned below the stabilizer is the stop bar 18 which is substantially in the plane of rudder 12 and, because of its vertical disposition, may be regarded as coacting with said rudder.
  • Said stop bar 18 contains the recessed portion 19, the base 20 of which is positioned and proportioned to receive the said hinged stabilizer 15 when it reaches its lowermost position.
  • said stabilizer portion 15 is movable between the aforesaid surfaces 17 and 20.
  • control vane of this form of my invention is identified by the reference numeral 21, said vane having at the leading edge thereof a front hinge 22 attached to one side of rudder 12, the hinge member containing a plate 22a which carries thereon a book 23.
  • the resilient member or elastic band 24 Mounted over said hook 23 is the resilient member or elastic band 24, the rear portion thereof being anchored to book 25 at the rear of surface 26 of said control vane 21.
  • the control vane 21 is urged outwardly away from the rudder by said resilient member 24, the outer limiting position being determined by the length of flexible member 28.
  • the area of said vane 21, the length of flexible member 28 and the length and elastic properties of resilient member 24 can be predetermined to meet predetermined conditions. In other words, the area of the control vane can be calculated, in known manner, so that for given speeds the force directed thereagainst will be sufficient to overcome the tension of the resilient member 24 under specific or predetermined conditions.
  • the neutralizing force which overcomes the force of the resilient member 24 has been caused by aerodynamic means, whereby complete control has been effected of the stabilizers operative movement. Since the neutralizing force is applied against the control vane 21 which is disposed in a plane from the plane of the wing, the said aerodynamic neutralizing force will have no effect on the longitudinal balance of the plane.
  • the vertically disposed control vane 21 has a negligible directional effect during high speed flying.
  • a circular descent is elfectedwhich is generally considered desirable in a model airplane so as to bring it close to the launching site. If, however, a circular descent is not desired, it is possible with my invention to obviate this effect, in a manner to be hereinafter set forth.
  • control vane 21a, resilient member 241: and flexible member 28a are substantially similar to the corresponding parts of the form of my invention first above described, the hinge member 32, however, having a plate attached to the stationary stabilizer portion 140.
  • the arrangement is hence such that the control vane 21a is in spaced relation to the rudder 12a.
  • the said control embodiment of Fig. 1. -However, since the .rudder .1212
  • the rudder will tend to keep the airplane along the flight path with relatively littleturning eflect under the influence ,of the control vane 21a.
  • Fig. 12 illustrates a unitary device 45 whichis .adapted for attachment to conventional model airplanes adapted to receive at the rear of the stationary stabilizer 14d a movable stabilizer portion 15d.
  • Device 45 comprises a forwardly extending bracket portion 46 comprising abottom plate 47 and a top plate 48, both plates being adapted to embrace the rear portion of said stationary member 14d.
  • Plate 48' has an upwardly extending flange 4 9 which carries the hinge member 56 upon which -,is pivotal-1y mounted the control vane 21d.
  • the hinge member 50 is operatively associated with a hook 51 for flexible member 28d, .it will operate substantially in the manner of the device of Fig. 1.
  • Figs. 13-17 show the applicability of my invention to a flying device known as a flying wing.
  • the main wing member 57 contains two laterally opposite fins S8 and 59, both recessed at 60 to accommodate therein the trail- .ing edge flap 61 hingedly mounted at 62 to' the rear of said main wing 57.
  • a control vane 21:: is hingedly mounted at 22c along fuselage 63 above the wing.
  • Aresilient member 64 anchored at 65 and attached to-the control member 21.9 at 66, normally urges the control member .21e outwardly fromthe fuselagea fiexiblemember 26a connecting saidvaneZlie to the flap 61.
  • the aerodynamic balance when the wing is angled to the air-flow at the desired angle of attack, is achieved bylocating the center of gravity 67 (Fig. 15) forwardly of the lift center '68 of the said Wing 57. speed conditions (Fig. 15), the downward force F due to the air pressure on flap 61 will counter-balance the wing lift W, as illustrated.
  • the resiliency of the member 64 tends to maintain said control vane in its open position illustrated in Fig. 13; and in such position the flexible member 282 pulls the flap 61.upwardly, as clearly indicated in Figs. 15 and 17.
  • the control vane 21a is forced backin the line of flight, permitting the trailing edge flap 61 to find its neutral position, substantially in the manner above described.
  • the control of the plane is effected through a movable control vane which is connected to a plane-elevating device, such as a stabilizer, trailing edge flap or wing.
  • a plane-elevating device such as a stabilizer, trailing edge flap or wing.
  • a flying'device a wing member, a plane -elevat ing member movable between a predetermined highspeed non-lifting position and a range of low-speed lifting positions, a control vane member movable between a high-speed position substantially in the path of flight and a predeterminedrrange of low-speed positions angu larly disposed with respect to the path of flight, resilient means on one of said members urging it away from its said high-speed position, and actuating means on said device disposed between and adapted for operatively connecting said elevating member and said control member, said actuating means being so proportioned and positioned that the movement of one of said members within a predeterminedportion of its operative pathin a direction away from.
  • a flying device In a flying device, a wing member, a plane elevating .member movable between a predetermined highspeed non-lifting-position and a range of low-speed lifting positions, a control vane member movable between a high-speed position substantially in the path of flight anda predetermined range of low-speed positions angularly disposed with respect to the path of flight, resilient means -onone of said members urging it away from its said high-speed position, and actuating means on said device disposed between and adapted for operatively connecting said elevating.
  • said actuating means being so proportioned and positioned that the movement of one of said members within, a predetermined portion of its operative path in a direction away from its said high-speedposition will "actuate the-other member in a direction away fronrits said high-speed position along a predetermined portion of, its operative path, the said elevating member being free floating in a plane substantially parallel to the plane of said wing member and independently movable relative to said control member in the region of said elevating members non-lifting position outside of said predetermined portion of the latter members operative path, said resilient means being attached to said control vane member and urging it away from its said high speed position.
  • a flying device a wing member, a plane elevating member movable between a predetermined highspeed non-lifting position and a range of low-speed lifting positions, a control vane member movable between a high-speed position substantially in the path, of flight and a predetermined range of low-speed positions angularly disposed with respect to the path of flight, resilient means on one of said members urging it away from its said high-speed position, and actuating means on said devicedisposed between and adapted for operatively connecting said elevating member and said control member, said actuating means being so proportioned and positioned that the movement of one of said members within a predetermined portion of its operative path in a direction away from its said high-speed position will actuate the other member in a direction away from its said high-speed position along a predetermined portion of its operative path, the said elevating member being free floating in-a plane substantially parallel to the plane .of said wing member and independently movable relative-:to'said control member in the region
  • control vane member having a front leading edge a and extending generally rearwardly therefrom, and hinge means connected to said control member in the region of said leading edge.
  • a flying device a wing member, a plane elevat- I ing member movable between two limiting positions, one of said positions being a predetermined extreme highspeed position and the other being a predetermined extreme low-speed position, stop means engageable with said plane elevating member at said two limiting positions, a control vane member movable between a highspeed position substantially in the path of flight and a predetermined range of low-speed positions angularly disposed with respect to the path of flight, resilient means on one of said members urging it away from its said high-speed position, and actuating means on said device disposed between and adapted for operatively connecting said elevating member and said control member, said actuating means being so proportioned and positioned that the movement of one of said members within a predetermined portion of its operative path in a direction away from its said high-speed position will actuate the other member in a direction away from its said highspeed position along a predetermined portion of its operative path, the said elevating member being free floating in a plane
  • a flying device the combination according to claim 4, said device having a body portion, a rudder member above the rear of said body portion, and a recessed portion between said rudder member and said body portion, said plane elevating member extending transversely within said recessed portion between said rudder member and body portion and being engageable therewith, whereby said rudder member and body portion constitute said stop means.
  • a flying device the combination according to claim 1, said device having a body portion and a fixed rudder at the rear thereof, said rudder being disposed substantially in a vertical plane, said control vane member being hingedly connected at its leading edge to said body portion and extending generally rearwardly from said leading edge.
  • a flying device the combination according to claim 1, said device having a body portion, a fixed rudder at the rear thereof, and a stabilizer component comprising a stationary support and said plane elevating member, said latter member being hingedly connected to said support.
  • a flying device a wing member, a plane elevating member movable between a predetermined high-speed non-lifting position and a range of low-speed lifting positions, a control vane member movable between a highspeed position substantially in the path of flight and a predetermined range of low-speed positions angularly disposed with respect to the path of flight, resilient means on one of said members urging it away from its said highspeed position, and actuating means on said device disposed between and adapted for operatively connecting said elevating member and said control member, said actuating means being so proportioned and positioned that the movement of one of said members within a predetermined portion of its operative path in a direction away from its said high-speed position will actuate the other member in a direction away from its said high-speed position along a predetermined portion of its operative path, the said elevating member being free floating in a plane substantially parallel to the plane of said wing member and independently movable relative to said control member in the region of said elevating members non-
  • a body portion a body portion, a wing member,
  • a plane elevating member movable between a predetermined high-speed non-lifting position and a range of lowspeed lifting positions
  • a control vane member movable between a high-speed position substantially in the path of flight and a predetermined range of low-speed positions angularly disposed with respect to the path of flight
  • resilient means attached to said body portion and said control member and yieldably urging the latter from its said high-speed position
  • a flexible member attached to said control member and to said elevating member, said flexible member being of a length whereby it is slack when said elevating member and control member are in the regions of their respective high-speed positions and taut when said elevating and control members are in predetermined other positions
  • the said elevating member being free floating in a plane substantially parallel to the plane of said wing member and independently movable relative to said control member in the region of said elevating members non-lifting position when said flexible member is in its said slack condition.
  • a control vane assembly for attachment to a flying device having a Wing member, a fixed support, an elevating member hingedly attached to the rear of said support and movable through a range of predetermined lowspeed positions in angular relation to the plane of said wing and a high-speed position in a plane substantially parallel to the plane of said wing member, comprising a hinge member with a front and rear plate secured together by a hinged connection, said front plate being adapted for attachment to said support and said rear plate being adapted for attachment to said elevating member, a second hinge connection secured to said front plate and at right angles to said first-mentioned hinged connection, a control vane having its front edge mounted on said second hinged connection and disposed in a plane substantially normal to said first-mentioned hinged connection, whereby said vane is movable between a high-speed position substantially in the direction of flight and other positions angular with respect thereto, elastic-band anchoring means on said vane and said second hinged connection, an elastic band anchored to and
  • a body portion a wing component substantially rigid throughout its extent extending laterally from opposite sides of said body portion, two laterally opposite fins on said wing component, a trailing edge elevator hingedly connected at the rear of said wing component, said elevator being movable between a predetermined high-speed non-lifting position and a range of low-speed lifting positions, a control vane member hingedly connected at its front edge to said body portion and movable between a high-speed position substantially in the path of flight and a predetermined range of low-speed positions angularly disposed with respect to the path of flight, resilient means attached to said body portion and said vane member yieldably urging the latter away from its said high-speed position, and a flexible member attached to said vane member and anchored to said movable elevator, said flexible member being of a length whereby it is slack when said control vane member and said elevator are in the regions of their respective high-speed positions and taut when said control vane member and elevator are in predetermined other

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US523576A 1955-07-21 1955-07-21 Flying devices Expired - Lifetime US2876585A (en)

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Application Number Priority Date Filing Date Title
US523576A US2876585A (en) 1955-07-21 1955-07-21 Flying devices
GB16987/56A GB813184A (en) 1955-07-21 1956-06-01 Improvements in and relating to the control of model aircraft
DEZ5641A DE1064405B (de) 1955-07-21 1956-07-05 Spielflugzeug mit einer Einrichtung zur Regelung des Anstellwinkels des Hoehensteuers

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US523576A US2876585A (en) 1955-07-21 1955-07-21 Flying devices

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US2876585A true US2876585A (en) 1959-03-10

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US523576A Expired - Lifetime US2876585A (en) 1955-07-21 1955-07-21 Flying devices

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DE (1) DE1064405B (de)
GB (1) GB813184A (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1291478B (de) * 1967-01-25 1969-03-27 Kinkead Industries Insbesondere durch Stossen zu betaetigende Teppichspannvorrichtung
US4125960A (en) * 1977-05-31 1978-11-21 Bacca Charles R Toy glider
US4282675A (en) * 1979-07-16 1981-08-11 Stripling Jr Sheldon A Automatic elevator control for model glider
US4708682A (en) * 1986-07-31 1987-11-24 Schentrup Lawrence M Helicopter toy
US5271579A (en) * 1992-07-10 1993-12-21 Luca Nicholas J De Recreational and sport rocket construction
US5423706A (en) * 1994-01-28 1995-06-13 Chase; George W. Toy aircraft glider with rotating and folding wings
US6497600B1 (en) 1999-10-05 2002-12-24 Alejandro Velasco Levy Automatic pilot system for model aircraft
US20060244264A1 (en) * 2003-03-18 2006-11-02 Renewable Devices Swift Turbines Limited Wind turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2647377C1 (ru) * 2017-02-03 2018-03-15 Артем Станиславович Щербаков Кордовая пилотажная модель самолета

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US927815A (en) * 1908-02-01 1909-07-13 Ludwig Ruppin Aerial device.
US1078888A (en) * 1912-10-08 1913-11-18 Theodore Windel Automatic stabilizer for aeroplanes.
US1300564A (en) * 1918-12-23 1919-04-15 George W De Witt Toy aeroplane.
US1821172A (en) * 1930-01-27 1931-09-01 Robert M Baylis Toy airplane
US2007964A (en) * 1933-02-15 1935-07-16 Carl J Crane Airplane stabilizer
US2034143A (en) * 1933-06-06 1936-03-17 James M H Jacobs Toy airplane
US2136067A (en) * 1937-08-16 1938-11-08 Western Coil & Electrical Co Toy airplane
US2147638A (en) * 1932-12-09 1939-02-21 Port Theophile De Means for rigging an airplane
US2210642A (en) * 1938-05-27 1940-08-06 Stephen W Thompson Aircraft
US2597521A (en) * 1946-05-25 1952-05-20 J C Pemberton Toy glider

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE567432C (de) * 1931-10-27 1933-01-02 Jakob Fuerst Spielflugzeug
US2588941A (en) * 1947-09-15 1952-03-11 Stark Edward Adolph Model glider

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US927815A (en) * 1908-02-01 1909-07-13 Ludwig Ruppin Aerial device.
US1078888A (en) * 1912-10-08 1913-11-18 Theodore Windel Automatic stabilizer for aeroplanes.
US1300564A (en) * 1918-12-23 1919-04-15 George W De Witt Toy aeroplane.
US1821172A (en) * 1930-01-27 1931-09-01 Robert M Baylis Toy airplane
US2147638A (en) * 1932-12-09 1939-02-21 Port Theophile De Means for rigging an airplane
US2007964A (en) * 1933-02-15 1935-07-16 Carl J Crane Airplane stabilizer
US2034143A (en) * 1933-06-06 1936-03-17 James M H Jacobs Toy airplane
US2136067A (en) * 1937-08-16 1938-11-08 Western Coil & Electrical Co Toy airplane
US2210642A (en) * 1938-05-27 1940-08-06 Stephen W Thompson Aircraft
US2597521A (en) * 1946-05-25 1952-05-20 J C Pemberton Toy glider

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1291478B (de) * 1967-01-25 1969-03-27 Kinkead Industries Insbesondere durch Stossen zu betaetigende Teppichspannvorrichtung
US4125960A (en) * 1977-05-31 1978-11-21 Bacca Charles R Toy glider
US4282675A (en) * 1979-07-16 1981-08-11 Stripling Jr Sheldon A Automatic elevator control for model glider
US4708682A (en) * 1986-07-31 1987-11-24 Schentrup Lawrence M Helicopter toy
US5271579A (en) * 1992-07-10 1993-12-21 Luca Nicholas J De Recreational and sport rocket construction
US5423706A (en) * 1994-01-28 1995-06-13 Chase; George W. Toy aircraft glider with rotating and folding wings
US6497600B1 (en) 1999-10-05 2002-12-24 Alejandro Velasco Levy Automatic pilot system for model aircraft
US20060244264A1 (en) * 2003-03-18 2006-11-02 Renewable Devices Swift Turbines Limited Wind turbine
US7550864B2 (en) * 2003-03-18 2009-06-23 Renewable Devices Swift Turbines Limited Wind turbine

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Publication number Publication date
GB813184A (en) 1959-05-13
DE1064405B (de) 1959-08-27

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