US2006515A - Aerial vehicle control - Google Patents

Aerial vehicle control Download PDF

Info

Publication number
US2006515A
US2006515A US466498A US46649830A US2006515A US 2006515 A US2006515 A US 2006515A US 466498 A US466498 A US 466498A US 46649830 A US46649830 A US 46649830A US 2006515 A US2006515 A US 2006515A
Authority
US
United States
Prior art keywords
rudder
brakes
water
brake
control means
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.)
Expired - Lifetime
Application number
US466498A
Inventor
Harry H Semmes
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.)
Bendix Aviation Corp
Original Assignee
Bendix Aviation Corp
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 Bendix Aviation Corp filed Critical Bendix Aviation Corp
Priority to US466498A priority Critical patent/US2006515A/en
Application granted granted Critical
Publication of US2006515A publication Critical patent/US2006515A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C35/00Flying-boats; Seaplanes

Definitions

  • This invention relates to aerial vehicles and w more particularly to steering and arresting means therefor.
  • the invention is shown as applied'to a seaplane and is particularly advantageous when applied thereto although it, is not limited thereto.
  • The, seaplanes and flying boats now in common use have the, inherent disadvantage that they are difllcult to maneuver while on thesurface of the water.
  • no mechanism has been provided which will allow readysteering and at the same time retardation of the plane.
  • An object of the present'invention isto generally improve the steering of aerial vehicles.
  • Another object is to provide brakes cooperating with the rudder for vsteering and retardation.
  • a further object is to provide novel means for actuating the steering means in unison.
  • Figure l is a side elevation of a seaplane in which the improvement is embodied, v
  • Figure 2 is a perspective view of the cooperating mechanism
  • FIG. 3 is an enlarged view taken along line 3-4 of Figure 2, t
  • Figure 4 is a view taken along line H of Figure 3,.
  • Figure 5 is a cross section view along line 8-4 of Figure 4,
  • Figure 6 is a view showing the yoke connection for the water brakes, and V 7 and an air rudder shown the pontoons are vgitudimtl members H and I2.
  • Figure! is a viewtaken along line ure 6.
  • FIG. 1 there I tional seaplane having the usual elements of structure including the fuselage I, sustenation surfaces empennage l, propelling mechanism 4, I.
  • the twin floats or pontoons 8 of any suitable structure, preferably of a light weight alloy of low corrodability and high tensile strength, such 1 for example, as alloy dural.
  • the pontoons I are preferably of the hollow V-bow type to present good freeboard and a good, cruising bow.v
  • step a is equipped with one step a, but, of course, ,it is to be understood that any 1 number of steps. may be employed.
  • the pontoon! may be attached to the 1-'-'I of Figis shown a convens I fuselage of the seaplane directly or, when the invention is applied to a biplane, through the intermediacy of sustaining or lifting surfaces.
  • the Z0 may comprise the, conventional pontoon struts I, 8 and 9, although it is to be understood that any type of attachment may be employed to suitably insure against hogging and sagging effects.
  • Interfloat struts may 2 alsobe'used to minimize rwkinz' effects.
  • each pontoon when twin pontoons are employed, is provided 3 with a waterbrake I0.
  • the water brake is slidably mounted in a suitable housing formed by .the longitudinal members Ii and I2 suitably attached to lateral framing members or ribs l3, ll, II, and it, within the pontoon i.
  • the members H and if, as shown in Figure .1, are so constructed within the float so as to take'up or distribute the thrusts incident to the retarding operation.
  • the member H does not, however, extend the entire longitudinal distance of the float 45 butis so constructed, as shown in Figure 1, as to receive the bell. crank lever attached to the waten brake, the purposeof which will more fully hereinafter appear.
  • the water brake It is capable. of vertical movementin the housing or well formed by the ion-
  • the element is so adapted ,as to be in an inoperative position and out of contact with the water,'or to be lowered into the water to present a relatively large con- -tact area and to thereby increase the resistance
  • the device described is adapted to subserve a to movement of the pontoon through the water. number of useful functions especially when ap- Associated with the water brake is is a suitplied to seaplanes.
  • twin float types able mechanism for operating the air rudder 5 of planes are more diillcult to maneuver than the 6 in unison, if desired with the water brakes l0, single hull type and also single screw flying 6 or operating the water brakes independently of boats or seaplanes generally turn easier in one he a r ud e A8 51mm, 8 d l I1 s Amb y direction than in the other due to the slip stream attached to a rudder rock shaft ll. Positioned eifects.
  • the present invention provides a suppleon the rudder rock shaft II is a crank ll supmentary method of steering the plane on the 10 port ng a lov 2
  • the 6 mounted sleeve can also be utilized to compensate for the slug- 22a of this p dal is provided with an aperture 23 i h turning in one direction of a single screw p d to n a a i e D 1 0! the rock ship.
  • the present invention also provides for them 25 of the brakes simultaneously, to efl'ectively re- Connected to the lower pert of the Pedal I! tard the speed of the plane through the water by s a l vis i y ti k to i "l '3" merely actuating the lever SI.
  • Actuation of the shaft by suitable l Inch 38 I lever 39 in this instance does not affect the steer-
  • the cable 25 is provided with a slip connection m mechanism gomprlsing t cooperating water so 21 adapted to entr st a i l b P brakes and the rudder in view of t e slip connecon themnk "a which is etteched to the voter tion :1, which allows the bolts or suitable probrake shaft It slip whnettieh P e in ections 21a on the cranks 20a to slide into the h cable 25 ll P mi ,m groovingll provided in the slip connection.
  • a rudder laterally 45 it is applied, is attached to the bell crank and mead brakes operable independently of rigidly fastened m the hm 1 other.
  • control means operable about an axis reby the member m m Imam mote from the rudder axis and for controlling between the not m m m therudder, other means operable aboutadiii'erent rudder min] Mm axis for controlling, the brakes, and means for to type mechmm when!
  • a rigid is tuned the being adjacent one another and remote from said shaft 2! through suitable cranks II.
  • the two rudder and bra I no legs 31 of the yoke ll are provided each'with a suitable slip connection "to allow bolts, or any projection "a on the cranks 80, to be freely of supporting member" a mo! hm pedal associated witheach supportlns member, a pair fiii st'lffs t fs'iimm*iim M 1mm
  • the yoke 18 connected m a by We tothe rudder, a second pair of pedalspivoted inlinkage, such as a cable a, and a mitigates ILwhich dependently of d fi s nam d pedals.
  • a rudder laterally spaced brakes operable independently of each other, control means operable about an axis remote from the rudder axis for controlling the rudder, other control means operable about a different axis for controlling the brakes, means for operating said rudder control means, separate means for operating said brake control means independently, and separate means for operating said rudder control means and said brake control means conjointly, both of said control means, operating means and both of said separate means being adjacent one another and remote from said rudder and brakes.
  • a rudder laterally spaced brakes operable independently of each other, control means operable about an axis remote from the rudder axis for controlling the rudder, other control means operable about a different axis for controlling the brakes, foot pedal means for operating said rudder control means, separate means for operating said brake control means independently, and separate foot pedal means for operating said rudder control means and said brake control means conjointly both of said control means, said operable means, both foot pedal means and separate means being adjacent one another and remote from said rudder and brakes.
  • a rudder operable independently of each other, cross shafts for controlling the rudder, additional cross shafts for controlling the brakes, foot pedal means for operating said rudder cross shafts, a lever for operating said brake cross shafts independently of said rudder cross shafts, and foot pedals for operating said rudder cross shafts and said brake cross shafts conjointly.

Description

y 1935- H. H. SEMMES AERIAL VEHICLE CONTROL Filed July 8, 1930 2 Sheets-Sheet l R- \L! R v is U m 9 r HQ y 1935' H. H. SEMMES AERIAL VEHICLE CONTROL Filed July 8, 1930 2 Sheets-Sheet 2 Patented July 2, 1935 V UNITED STATE Amman viinrctu Contact.
' Harry H..Se1nmes,
-- to Bendix Aviation Ind, a corporation of Chevy Chase; Md.,-
Corporation, South ware assignor Bend,
Application July a, me, No. 400,498
'iciaims.
This invention relates to aerial vehicles and w more particularly to steering and arresting means therefor. The invention is shown as applied'to a seaplane and is particularly advantageous when applied thereto although it, is not limited thereto. The, seaplanes and flying boats now in common use have the, inherent disadvantage that they are difllcult to maneuver while on thesurface of the water. Heretofore, no mechanism has been provided which will allow readysteering and at the same time retardation of the plane.
An object of the present'invention isto generally improve the steering of aerial vehicles.
Another object is to provide brakes cooperating with the rudder for vsteering and retardation..
A further object is to provide novel means for actuating the steering means in unison.
with these and other objects in view, which maybe incident'to my improvements, the invention consists in the parts and combination to be hereinafter set forth and claimed, with the understanding that the several necessary elements comprising my inventionjmay be varied in construction, proportions and arrangement without departing from the spirit and scope of the appended claims. I
In accordance with the present invention there is provided means adapted to coact directly in unison with the rudder of an airship having a watersustaining member for greatly facilitating the steering of aseaplane on the surface of the water together with retarding the speed of the plane with respect to the water. It is to be understood, of course, that this invention is applicable to both the seaplane and flying boat types of airships. Inorder to make my invention more clearly understood, I have shown in the accompanying drawings, means for carrying the same into practical effect'without. limiting the improvements in their useful applications to the particular constructions which, for the purpose of explanation. have been made thesubject of illustration.
Figure l is a side elevation of a seaplane in which the improvement is embodied, v
Figure 2 is a perspective view of the cooperating mechanism,
Figure 3 is an enlarged view taken along line 3-4 of Figure 2, t
Figure 4 is a view taken along line H of Figure 3,.
Figure 5 is a cross section view along line 8-4 of Figure 4,
Figure 6 is a view showing the yoke connection for the water brakes, and V 7 and an air rudder shown the pontoons are vgitudimtl members H and I2.
Figure! is a viewtaken along line ure 6. a Y
Referring to Figure 1 there I tional seaplane having the usual elements of structure including the fuselage I, sustenation surfaces empennage l, propelling mechanism 4, I. Associated with the plane are the twin floats or pontoons 8, of any suitable structure, preferably of a light weight alloy of low corrodability and high tensile strength, such 1 for example, as alloy dural. The pontoons I, are preferably of the hollow V-bow type to present good freeboard and a good, cruising bow.v As
equipped with one step a, but, of course, ,it is to be understood that any 1 number of steps. may be employed.
The pontoon! may be attached to the 1-'-'I of Figis shown a convens I fuselage of the seaplane directly or, when the invention is applied to a biplane, through the intermediacy of sustaining or lifting surfaces. As shown the Z0 may comprise the, conventional pontoon struts I, 8 and 9, although it is to be understood that any type of attachment may be employed to suitably insure against hogging and sagging effects. Interfloat struts may 2 alsobe'used to minimize rwkinz' effects. As will hereinafter appear, in steering a seaplane by the present invention on the water torsional stresses are set up when the water brake is applied on one side only of the longitudinal axis of the plane and it is therefore preferable to provide addimnal bracing between the fuselage and the ponns. a 1 When practicing the invention each pontoon, when twin pontoons are employed, is provided 3 with a waterbrake I0. The water brake is slidably mounted in a suitable housing formed by .the longitudinal members Ii and I2 suitably attached to lateral framing members or ribs l3, ll, II, and it, within the pontoon i. The members H and if, as shown in Figure .1, are so constructed within the float so as to take'up or distribute the thrusts incident to the retarding operation. The member H does not, however, extend the entire longitudinal distance of the float 45 butis so constructed, as shown in Figure 1, as to receive the bell. crank lever attached to the waten brake, the purposeof which will more fully hereinafter appear.
The water brake It is capable. of vertical movementin the housing or well formed by the ion- The element is so adapted ,as to be in an inoperative position and out of contact with the water,'or to be lowered into the water to present a relatively large con- -tact area and to thereby increase the resistance The device described is adapted to subserve a to movement of the pontoon through the water. number of useful functions especially when ap- Associated with the water brake is is a suitplied to seaplanes. As is known, twin float types able mechanism for operating the air rudder 5 of planes are more diillcult to maneuver than the 6 in unison, if desired with the water brakes l0, single hull type and also single screw flying 6 or operating the water brakes independently of boats or seaplanes generally turn easier in one he a r ud e A8 51mm, 8 d l I1 s uitab y direction than in the other due to the slip stream attached to a rudder rock shaft ll. Positioned eifects. The present invention provides a suppleon the rudder rock shaft II is a crank ll supmentary method of steering the plane on the 10 port ng a lov 2|- Sllltable linkage or a cable water which is used in a cooperative relationship 10 2| connects the rudder I, as at Imwith the loot with the rudder. It will be appreciated that if pedal I f r opernt ns he dd r w le th plane one only of the water brakes to is operated to is in flight. engage the water and the rudder is rotated in Loosely m unted on the rudder rock shaft is, unison therewith, the plane will turn on that and adjacent'the rudder control is another pedal to as an i 15 1 f r actuating both the Water brake! and the Such usage of one of the brakes and the rudder udde in u ls The 6 mounted sleeve can also be utilized to compensate for the slug- 22a of this p dal is provided with an aperture 23 i h turning in one direction of a single screw p d to n a a i e D 1 0!! the rock ship. Using one of the brakes and the rudder shaft ll. This arrangementperml 01m 6011- in this manner for steering sets up torsional 20 train! the ru d r m h nism w l the lane is stresses due to the di'irerent relative speeds of in "flight, and also by suitably constructing the th pontoons and, to compensate for this, it is p r e 23. allows the cooperative' beratton of preierableto provide suitable additional bracing brake between the pontoons and the fuselage.
25 t rins nd ins h P While v the The present invention also provides for them 25 of the brakes simultaneously, to efl'ectively re- Connected to the lower pert of the Pedal I! tard the speed of the plane through the water by s a l vis i y ti k to i "l '3" merely actuating the lever SI. Actuation of the shaft by suitable l Inch 38 I lever 39 in this instance does not affect the steer- The cable 25 is provided with a slip connection m mechanism gomprlsing t cooperating water so 21 adapted to entr st a i l b P brakes and the rudder in view of t e slip connecon themnk "a which is etteched to the voter tion :1, which allows the bolts or suitable probrake shaft It slip whnettieh P e in ections 21a on the cranks 20a to slide into the h cable 25 ll P mi ,m groovingll provided in the slip connection.
the M min! e mech- While I have shown and described the pre- 35 the rudder h P lerred embodiment of my invention, I wish it to which"!!! "been be understood that I do not confine myseli to The Crank 3 i8 8111M}! M the the precise details of construction herein set brake shaft II and supports a clevis II. Suitable f rth by way of m m-w as t is apparent that -8 such a! a mum many changes and variations may be made there- 40 the in, by those skilled in the art without departing brake by a from the spirit of the invention, or exceeding on a bell crank lever SI, suitably attachedto the the scope of the appended clamm water brake II. A spring 84 forexertim the nec- I claim;
e838" tendon in an M m 1. In an aerial vehicle. a rudder, laterally 45 it is applied, is attached to the bell crank and mead brakes operable independently of rigidly fastened m the hm 1 other. control means operable about an axis reby the member m m Imam mote from the rudder axis and for controlling between the not m m m therudder, other means operable aboutadiii'erent rudder min] Mm axis for controlling, the brakes, and means for to type mechmm when! the m operating said rudder control means independentbe actuated alone in the air or cooperatively with of the brake control means separate mm g g fig the on me mm for operating the said brake control means indedently of said rudder'control means, and sepin mm mt'bh mm :r a te means for operating both of said control is "Provided applying the W means coniointly, said control. means, operable ousiy without cooperatingwith the air rudder mum'opemm mem and both m mean,
A rigid is tuned the being adjacent one another and remote from said shaft 2! through suitable cranks II. The two rudder and bra I no legs 31 of the yoke ll are provided each'with a suitable slip connection "to allow bolts, or any projection "a on the cranks 80, to be freely of supporting member" a mo! hm pedal associated witheach supportlns member, a pair fiii st'lffs t fs'iimm*iim M 1mm The yoke 18 connected m a by We tothe rudder, a second pair of pedalspivoted inlinkage, such as a cable a, and a elevis ILwhich dependently of d fi s nam d pedals. connecarrangement permits the water brakes to b tions from each of said last named pedals to one actuated independently of the air rudder I. of the brakes, and means operated by actuation Figure 1, shows the water brake I. positioned of each of said last named pedals about its pivot substantially to the rear of the center as gravity for operating said rudder connections. 70 oi the plane which is, of course, prelerable toob- '3. The combination set forth in claim 2 in viate the dangers of nosing over when the brakes which the first named pedals are ineifeotive to are applied. Positioning the water brakes so, adds operate the brakes. the further advantage or causing the ship to seta. The combination set forth in claim 2 in 76 tle at the stern n h k s reapplied. which the aerial vehicle is provided with means for operating both of said brakes conjointly comprising a hand lever connected thereto.
5. In an aerial vehicle, a rudder, laterally spaced brakes operable independently of each other, control means operable about an axis remote from the rudder axis for controlling the rudder, other control means operable about a different axis for controlling the brakes, means for operating said rudder control means, separate means for operating said brake control means independently, and separate means for operating said rudder control means and said brake control means conjointly, both of said control means, operating means and both of said separate means being adjacent one another and remote from said rudder and brakes.
6. In an aerial vehicle, a rudder, laterally spaced brakes operable independently of each other, control means operable about an axis remote from the rudder axis for controlling the rudder, other control means operable about a different axis for controlling the brakes, foot pedal means for operating said rudder control means, separate means for operating said brake control means independently, and separate foot pedal means for operating said rudder control means and said brake control means conjointly both of said control means, said operable means, both foot pedal means and separate means being adjacent one another and remote from said rudder and brakes.
7. In an aerial vehicle, a rudder, laterally spaced brakes operable independently of each other, cross shafts for controlling the rudder, additional cross shafts for controlling the brakes, foot pedal means for operating said rudder cross shafts, a lever for operating said brake cross shafts independently of said rudder cross shafts, and foot pedals for operating said rudder cross shafts and said brake cross shafts conjointly.
. HARRY H. SEMMES.
US466498A 1930-07-08 1930-07-08 Aerial vehicle control Expired - Lifetime US2006515A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US466498A US2006515A (en) 1930-07-08 1930-07-08 Aerial vehicle control

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US466498A US2006515A (en) 1930-07-08 1930-07-08 Aerial vehicle control

Publications (1)

Publication Number Publication Date
US2006515A true US2006515A (en) 1935-07-02

Family

ID=23851986

Family Applications (1)

Application Number Title Priority Date Filing Date
US466498A Expired - Lifetime US2006515A (en) 1930-07-08 1930-07-08 Aerial vehicle control

Country Status (1)

Country Link
US (1) US2006515A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6983710B1 (en) * 2004-11-05 2006-01-10 The United States Of America As Represented By The Secretary Of The Navy High speed braking of submerged propelled sea craft
US20140318432A1 (en) * 2011-11-10 2014-10-30 Prezip Technology Ab Device for controlling trim and/or steering of a boat

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6983710B1 (en) * 2004-11-05 2006-01-10 The United States Of America As Represented By The Secretary Of The Navy High speed braking of submerged propelled sea craft
US20140318432A1 (en) * 2011-11-10 2014-10-30 Prezip Technology Ab Device for controlling trim and/or steering of a boat
US9415837B2 (en) * 2011-11-10 2016-08-16 Prezip Technology Ab Device for controlling at least one of trim and steering of a boat, ship or vessel
AU2012334037B2 (en) * 2011-11-10 2016-11-03 Prezip Technology Ab Device for controlling trim and/or steering of a boat

Similar Documents

Publication Publication Date Title
US2843337A (en) Composite aircraft system and method of flight
US2510561A (en) Airplane control surface
US1869326A (en) Control system for airplanes and the like
US2006515A (en) Aerial vehicle control
US2390939A (en) Airplane
US3738598A (en) Amphibious apparatus for conventional land aircraft
US1742461A (en) Aircraft
US2770427A (en) Aircraft construction
US1981237A (en) Multimotored airplane
US2580841A (en) Flap aileron for airplanes
US2076398A (en) Aircraft
US1779855A (en) Glider
US1929255A (en) Airplane
US1843678A (en) Aeroplane
US1879547A (en) Seaplane
US1734251A (en) Aero propelling and steering means
US1863944A (en) Seaplane
US1957675A (en) Seaplane
US1866451A (en) Collapsible pontoon for flying machines
US3070334A (en) Flying control system for aircraft
US2392439A (en) Airplane
US3016215A (en) Aerodynamic aircraft control system
US1671865A (en) Aircraft
US2136165A (en) Rotary wing aircraft
US1895458A (en) Aircraft