Abstract:
A Fluidynamic Lift Combined Array, Technology for flying, and/or land, and/or other motor vehicles comprises: a. an aerodynamic structure of chord-telescopic smooth-united multisegment lifting wings; and/or b. a set of hydrodynamic circuits including closed loop waved tunnels each with placed inside pump impelling operative liquid and having curved elbows with lifting winglets; and c. a method of generating high lift forces in combined fluidynamic, self-boosting, accumulative, and energy integrating and conservative technology. This proposal can provide: Short, safe, convenient for people, and appropriate for planes takeoffs and landings at speeds about 20 miles per hour. Sure overcoming any difficulties connected with heavy load for land and other vehicles. High general efficiency and profound reliability in upkeeping and thrifty technology with substantial energy conservation by additional lift generated in any tense situations.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS  
       [0001]     This application claims the benefit of PPA No. 60/714,895 filed Sep. 8, 2005 by present inventor. 
     
    
     FEDERALLY SPONSORED RESEARCH  
       [0002]     Not applicable.  
       SEQUENCE LISTING OR PROGRAM  
       [0003]     Not applicable.  
       BACKGROUND OF THE INVENTION  
       [0004]     This proposal relates to the aerodynamic wing-lifting structures and closed hydrodynamic circuits with lifting winglets. This proposal deals with chord-telescopic wing-design for open systems of flying vehicles, and closed self-boosting circuits for any kind of motor vehicles. The subject matter is a combined upkeeping technology consisting of aerodynamic and hydrodynamic systems with wing-lifting structures for overcoming various tense situations.  
         [0005]     Some specific problems involved in conventional motor vehicles: 
        a) Various regular airfoils of flying vehicles contain so-called high-lift devices with multiple flaps, slats, slots, other separate elements. Said mechanical interrupters cause interactions among air circulations, wing-upwashes, wing-downwashes, and, in many cases, motor&#39;s incoming airflows and high-speed powerful exhaust-jets. Said interactions lead to various deformations and disturbings of wing-airflows and force high and unsafe speeds for takeoffs and landings needed to compensate said energy losses of airflows around lifting wings.     b) Any vehicles need substantial reducing of their sum-general loads, especially in hard portions of operations such as takeoffs and landings for flying means and various road-difficulties for land and other vehicles.     c) No motor vehicles use the remarkable high energy ratio which well known closed fluidynamic testing tunnels demonstrate.        
 
         [0009]     The real knowledge of the Fluidynamic lift nature is not complete even now. For example, two high-experienced specialists D. Anderson and S. Eberhardt, in their book “Understanding Flight” [629.13An2336u; 2001] describe some important miscomprehended problems.  
         [0010]     In other words, the theory of Fluidynamic lift is not perfect. That is why aircrafts can fly but mostly cannot take off and land at appropriate speeds about 20 miles per hour with comfort for people and high reliability for the planes, all their systems and interconnections in multiple high-dynamic operations.  
         [0011]     My proposal solves some of said above problems and presents a combined technology and means for any kind of motor vehicles to be more effective. The actual combined reducing of sum-general loads is substantial, about 50%. It is done by additional lift forces generated in energy preservating and accumulating technology. This technology provides to all parts of all the flows around wings in aerodynamic structures and around winglets in self-boosting hydrodynamic circuits appropriate zones free from any disturbings and energy losses.  
         [0012]     Any prior arts connected with developed in present proposal chord-telescopic curve-tilting smooth-united multisegment lifting aerodynamic wings and their combined and/or independent usage with also developed in present proposal closed loop waved hydrodynamic winglet-circuits providing integrated lift forces were not found.  
       BRIEF SUMMARY OF THE INVENTION  
       [0013]     It is the object of this proposal to provide: 
        a. Various, combined and cooperative fluidynamic lift forces for motor vehicles and statis means in order to facilitate their total-sum loading.     b. High vehicles&#39; efficiency in developed upkeeping thrifty aerodynamic and self-boosting accumulative hydrodynamic technologies with substantial energy savings.     c. Easy, safe and sure overcoming tense situations, connected with heavy load, for any motor vehicles.     d. Short, safe, sure take-offs and landings at speeds about 20 miles per hour, more convenient for people, and appropriate for aircraft&#39;s&#39; systems and their connections keeping and preserving their reliability.        
 
         [0018]     The nature and substance of Fluidynamic Lift combined Array, Technology are two fluidynamically similar but independent and combined lifting systems: 
        built-in hydrodynamic sets for any of motor vehicles and/or static means including aircrafts, trucks, cars, ships, trains, helicopters, elevators, heavy containers, others;     outer aerodynamic structures for various flying vehicles like planes, and others.        
 
         [0021]     Proposed self-boosting accumulative technology of closed loop waved circuit-tunnels with hydrodynamic lifting winglets and curved elbows, and upkeeping thrifty technology with chord-telescopic curve-tilting wings in aerodynamic structures, provide separate and/or combined fluidynamic lift forces for a high effective common load-reducing result. 
     
    
     DRAWING FIGURES  
       [0022]     In the drawings closely related elements have the same numbers but different alphabetic suffixes, numbers of views, and sections according to numbers of figures where they are shown.  
         [0023]      FIG. 1  shows a plan view of a exemplary flying aircraft designed by “Fluidynamic Lift Combined Array, Technology” with: 
        an aerodynamic structure of multi-segment chord-telescopic wings, and     a set of four built-in hydrodynamic closed-loop circuits.          
         [0026]      FIG. 2  is a schematic, turned horizontal, part-section  2 - 2  taken in  FIG. 1 .  
         [0027]      FIG. 3  illustrates a side view-section  3 - 3  taken in  FIG. 1 , and shows the general design and aerodynamic interactions; simplified contours of hydrodynamic circuits and resulting lifting forces are also shown.  
         [0028]      FIG. 4  shows a plan view  4  from  FIG. 3  and illustrates one of said wings in drawn-in state for high cruise speed with minimum drag.  
         [0029]      FIG. 5  shows the same plan view of the same wing of  FIG. 4  but in extended state for low speed takeoff or landing with maximum lift.  
         [0030]      FIGS. 6 and 7  show the schematic cross-sections  6 - 6  and  7 - 7  taken in  FIGS. 5 and 4 , respectively, illustrating chord-telescopic interactions with curve-tilting displacements of movable smooth-united segments of said wings relatively its static carcass-frame. The coaxial sets of force cylinders, hinges, springs, section chords, angles of attack are also shown.  
         [0031]      FIG. 8  shows the side view-schematic section of the waved hydrodynamic circuit and illustrating its general design lifting winglets, hydrolic pump, closed loop tunnel, cavitation control, bypass, air cooler-set.  
         [0032]      FIG. 9  shows the plan view  9  taken in  FIG. 8 .  
         [0033]      FIG. 10  illustrates a cross section  10 - 10  taken in  FIG. 8  and shows a preferable design of the closed loop tunnel.  
         [0034]      FIG. 11  shows a schematic side view of an exemplary bus with five built-in hydrodynamic closed loop circuits and their integrated lift forces.  
         [0035]      FIG. 12  is a cross section  12 - 12  in  FIG. 11 .  
         [0036]      FIG. 13  is a fragment  13  of  FIG. 11 , it shows a partial side section of lifting winglet in upper zone of said circuit&#39;s tunnel and general hydrodynamic interactions around said winglet including hydrodynamic and centrifugal lift forces. 
     
    
     REFERENCE NUMERALS AND SYMBOLS IN DRAWINGS  
       [0000]    
       
           20 —Chord-telescopic curve-tilting wing [CTW] 
           20 A—CTW carcass-frame  
           20 B—CTW head-segment  
           20 C—CTW middle for-segment  
           20 D—CTW tail-segment  
           20 E—CTW middle aft-segment  
           20 F—Force cylinder  
           20 P—Cylinders&#39; power set  
           21 —CTW—horizontal stabilizer  
           22 —Fuselage  
           23 —Vertical stabilizer  
           24 —Aileron.  
           25 —Rudder  
           26 —Thrust Motor  
           27 —Hinge  
           28 —Spring  
           29 —Elevator  
           30 —Hydrodynamic circuit  
           30 A—Closed-loop waved tunnel  
           30 B—Controlled bypass  
           30 C—Air cooler  
           30 D—Bottom bend.  
           30 E—Comb elbow  
           30 F—Cooling fins  
           30 L—Operative liquid  
           30 P—Static pressure piston-valve  
           31 —Tunnel frame structure  
           32 A,B,C,D,E—Hydrodynamic lifting winglets  
           33 A,B—Guide-grids  
           33 P—Pocket  
           33 S—Flow straightener  
           34 C—Wiglet control  
           34 G—Guide-grid control  
           35 —Axial-flow propeller pump  
           35 D—Pump drive  
           35 M—Pump motor  
           36 —Visualization  
           37 —Meters, control  
           38 —Bus engine  
       
     
         [0076]     Reference numerals  20 F,  20 P,  22 ,  23 ,  24 ,  25 ,  26 ,  27 ,  28 ,  30 B,  30 C,  30 F,  31 ,  35 D,  35 M,  36 ,  37 ,  38  are conventional units, elements, and structures used in present new combined Fluidynamic lift-technology. Control of regular elements is not shown.  
         [0077]     Aerodynamic Symbols: 
             —Wing upwash              —Wing bending airflow              —Tip vortex              —Wing downwash-jet     C H,Lmax —Extended wing section chord of the wing  20      C H,Dmin —Drawn-in wing section chord of the wing  20                 T,L —Angle of attack for takeoff and landing.                c,f —Angle of attack for cruise flight              —Force cylinders&#39; set common axis              —Aerodynamic lift force    
 
         [0088]     Hydrodynamic and Other Symbols: 
              Winglet upwash               Winglet bending flow               Winglet downwash-jet               Circuit operative liquid flow               Motor incoming airflow               Motor thrust jet               Winglet hydrodynamic lift force               Operative liquid resulting centrifugal lift force               Circuit integrated lift force    
 
       DETAILED DESCRIPTION OF THE INVENTION  
       [0098]     The Fluidynamic Lift Combined Array, Technology for motor vehicles includes two systems: 
        an aerodynamic structure of chord-telescopic multisegment smooth-united lifting wings  20 ,  21  for flying vehicles, and     a set of hydrodynamic circuits  30  comprising closed loop waved tunnels  30 A with lifting winglets  32  and operative liquid  30 L inside said tunnels, for any kind of vehicles and some static means. 
 
 Both said systems can work together cooperating each with other in common motor vehicle or separately and independently. 
       
 
         [0101]     FIGS.  1 , 2 , 3  illustrate how said systems can be designed and arranged into an exemplary aircraft. There are shown: 
        an arrangement of lifting wings  20 ,  21  with fuselage  22 , thrust motors  26  in order to provide for all acting aerodynamic flows needed clear zones without any interactions and interdisturbings;     built in placement of circuits  30  connected with vertical walls of fuselage  22 ;     outer aerodynamic lift forces AL, created by wings  20 ,  21 ,     inner integrated hydrodynamic lift forces HL generated in circuits  30 ;     clear cooperations of general flows with said aerodynamic structure;     vertical stabilizers  23 , ailerons  24 , rudders  25 , elevators  29  are also shown.        
 
         [0108]      FIGS. 1,3  show the general acting flows with circled symbols UW, BA, DW, V, MA, TJ. The clear nondisturbing cooperative interactions among the all said flows at all their directions and zones are illustrated: 
        The wings  20 ,  21 , and aircraft thrust motors  26  are arranged in the aerodynamic structure in vertically declined order, so     Any upper adjacent wing is placed back in airflows direction, and     Any lower adjacent wing is placed forward in flight direction. 
 
 Therefore, Interaffections and mutual disturbings of airflows bending wings, upwashes, downwashes, vortices and thrust-motor-flows near the flying vehicle are prevented. 
         
         [0112]     FIGS.  4 , 5 , 6 , and  7  illustrate the general design and chord-telescopic smooth-united operations of said lifting wings  20 ,  21  with displacements of their segments  20 B,  20 C,  20 D,  20 E around static carcass-frames  20 A. Said chord-telescopic displacements, are provided by coaxial sets of force cylinders  20 F driven by power sets  20 P.  
         [0113]     The hinges  27  and springs  28  provide needed mini-turns, support and self-adjusting to the segments of the wings  20 ,  21  for needed aerodynamic positions. This gives the maximum lift when the chord of the wing section is extended to Lmax and the angle of attack is          T, L providing short, slow, and safe takeoffs and landings at small speeds about 20 miles per hour.  
         [0114]     The same said means give needed minimum drag when the chord of the wing section is shorter by drawn-in telescopic segments  20 B, C,D,E the chord becomes equal HDmin and angle of attack is           providing minimum drag for high speed cruise flights.  
         [0115]     The force cylinders  24  are installed and act by their coaxial sets and have their power sets  20 P. The said cylinders can work separately, independently or together, providing needed displacement and self-adjusting of moving segments, correct aerodynamic performances without affecting and disturbing of airflows, upwashes, downwashes, circulations and vortices thus preserving all the energy of air jets for effective aerodynamic lift forces.  
         [0116]     FIGS.  8 , 9 , 10  show the hydrodynamic circuit  30  comprising said tunnel  30 A, hydrolic controlled bypass  30 B, air cooler  30   c  with cooling fins  30 F, visualization  36 , meters, control  37 . A preferably axial-flow propeller pump  35  impels operative liquid  30 L inside said tunnel  30 A by motor  35 M and drive  35 D.  
         [0117]     Said liquid  30 L is a preferably high-density solution like heavy antifreeze, salt water, bromide, other.  
         [0118]     Said tunnel  30 A also includes: 
        Upper and lower waved closed loop contoured rows of smooth-connected tubular upper curved elbows  30 E and lower smooth bends  30 D,     A kit of lifting winglets  32 A,B,C,D,E, placed in said elbows  30 E in series,     A kit of guide-grids  33 A, B and flow-straighteners  33 S placed in said bottom bends  30 D,     A static pressure control valve device  30 P with a springed piston to adjust and limit possible cavitation of operative liquid  30 L,     Winglet controls  34 C, guide-grids controls  34 G.     Some tunnels  30  an include adjustable pockets  33 P for some kinds of waved elbows  30 E winglets  32  and operative liquids in order to provide additional fluid-flow equalization.        
 
         [0125]     Said elbows  30 E have cross section areas and curves&#39; radii smaller than adjacent bends have in order to provide bigger velocity of operating liquid  30 L in elbow-portions of the tunnel  30 A. Said winglets  32  can be various and different including monowinglets, ladder-like, compound with smooth high-lift devices, and/or others in the same tunnel  30 A depending on design.  
         [0126]      FIGS. 11, 12 ,  13  illustrate an exemplary set-arrangement of several hydrodynamic circuits  30  into vertical walls of an exemplary bus.  
         [0127]      FIG. 11  shows also the circuit integrated lift-forces IHL reducing the common bus-load including its own weight with engine  38 .  
         [0128]      FIG. 13  illustrates in fragmentary section view of the tunnel&#39;s elbow  30 E, winglet  32 D, operative liquid  30 L circulating around winglet, visualization  36 , cooling fins  30 F. The hydrodynamic lift force HL generated by winglet  32 D, and result centrifugal lift force CF generated by operative liquid  30 L running in curved elbow  30 E are shown.  
         [0129]     Operation, Effectiveness, Some Conclusions:  
         [0130]     Aerodynamic Structure 
        a) The force cylinders  20 F (or solenoids, or others), driven by their power sets  20 P, move the smooth-united segments  20 B, C, D, E relatively carcass  20   a,  and provide for said chord-telescopic curve-tilting wings  20 ,  21  mini-gap shifts and almost gap-less displacements. These shifts lead to maximum lift AL in extended drawn-off state for short takeoffs and landings at speeds about 20 miles per hour and minimum drag at drawn-in state for high-speed cruise flights.     b) Any possible interactions and interdisturbings among any various flows, jets vortices are effectively minimized. Slow takeoffs and landings, reducing of the general load by all the generated lift forces provide calm conditions to any aircraft system and real high reliability and security.     c) The preservation the energy of downwash-jets and thus the self-protecting and conservation of generated lift forces in diverse flight circumstances provide economic effect, energy savings, stable flights.        
 
         [0134]     Set of Hydrodynamic Circuits  30  
        d) The preferably, axial-flow propeller pump  35  operates as self-booster impelling the operative liquid  30 L in closed loop tunnel  30 A, working at itself, for itself, for lifting winglets  32 , and for curved elbows  30 E. The high power ratio of the pump motor  35 M is cyclically provided and effective energy preservation is reached. This is the method of my accumulative technology in which the singular pump  35  works actually in series with itself, providing high potential circulative hydrodynamic flow in closed loop tunnel  30 A with multiplied pressure ratio and limited suppressed cavitation.     e) The operative liquid  30 L interacts with lifting winglets  32  and elbows  30 E in the closed loop tunnel  30 A providing integrated lift forces consisting of hydrodynamic portions generated by winglets  32 , and centrifugal portions generated by operative liquid  30 L in upper zones of elbows  30 E due to curve radii, high velocity, and high density of liquid  30 L.        
 
         [0137]      FIGS. 8, 10 ,  13  demonstrate how the phenomenon of an integrated lift force appears in said closed loop tunnel  30 A: 
        The well known hydrodynamic lift HL is mostly provided by preservation of energy of the flow which is circulating and bending the winglets  32  forcing powerful downwash-jets in waved elbows  30 E. The winglets  32  push themselves off from these jets reacting to jets which winglets  32  produced, thus generating hydrodynamic lift forces inside closed loop tunnel  30 E,     The centrifugal forces CF provided by liquid  30 L moving inside curved upper zones of elbows  30 E,     The integrated upwarded lift force I HL is the sum of hydrodynamic lift HL and resulting centrifugal forces CF accounting some downward centrifugal losses in smooth, low-velocity, big radii bends  30 D.          
         [0141]     The guide-grids  33 A, B and flow-straighteners  33 S provide damping to vortices, flow equalization and correct flow directions to the adjacent winglets  32 . The initial static pressure of the operative liquid  30 L is regulated by piston  30 P in order to minimize any cavitation; the controllers  34 C and  34 G adjusting winglets  32  and guide-grids  33 G, pump drive  35 D regulating capacity of the pump  35  and thus the effective velocity of operative liquid  30 L; controlled regulating of bypass  30 B; air cooler  30 C provide needed conditions to the high potential internal flow in said self-boosting hydrodynamic technology.  
         [0142]     A couple of basic formulae and notes. 
        a) Fluidynamic lift force of any aerodynamic wing  20 ,  21 , and/or winglet  32 :  
           L   w     =         C   L     ·     1   2       ⁢     p   ·     u   2     ·   Sw         ,       
 
 where C—lift coefficient, p—fluid density, 
            U velocity of the fluid,     Sw—working area of the wing.    
            b) Centrifugal forces of the operative liquid  30 L in upper winglet-elbows and lower guide-grid bends:  
         CF   =           M   .     ·     U   L   2         G   ·   R       ⁢   γ       ,       
     where 
            {dot over (M)}—instant mass of running liquid  30 L in the curved zone,     U L —velocity of the liquid  30 L in the curved zones,              —damping coefficient,     G—gravity acceleration, R—curve radius.    
            c) Sum—result centrifugal force 
             CF =Σ  CF   E −Σ  CF   B , where     Σ  C F E —vector sum of elbow&#39;s centrifugal forces,     Σ  CF   B —vector sum of bend&#39;s centrifugal forces,    
            d) Integrated circuit lift force is a vector sum 
            I  HL =  HL +  CF , where      HL  is a sum of hydrodynamic winglet-lift forces    
            e) Hydrodynamic circuit  30 ′ power ratio PRc:  
           PR   c     =       Qp   ·   Pa       H   .   P   .   P   .         ,       
     where 
            Qp—capacity of axial flow pump  35 ,     Pa—accumulated pressure of liquid  30 L in stable regime     H.P.P.—power of pump motor  35 M.     PR is about 7.5 depending on design.