Classifications

• • G—PHYSICS
  • G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
  • G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
  • G09B19/00—Teaching not covered by other main groups of this subclass
  • G09B19/16—Control of vehicles or other craft
  • G09B19/165—Control of aircraft
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
  • B64F1/00—Ground or aircraft-carrier-deck installations
  • B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
• • G—PHYSICS
  • G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
  • G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
  • G09B9/00—Simulators for teaching or training purposes
  • G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
  • G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
  • G09B9/12—Motion systems for aircraft simulators

Definitions

• the present invention relates to training materials and, in particular, air training devices.
• the present invention aims to overcome the above drawbacks by making it possible to actually fly in the in the air, just like in reality, by piloting a captive but free aircraft on its three axes, both on taxiing and in flight in the air.
• the present invention relates to an apparatus offering, moreover, the possibility of modifying at will the relative mass of the aircraft, with a view to creating, from the same power characteristics of the engine of the aircraft, taxiing, takeoff conditions , flight and landing different for the same aircraft.
• Another object of the invention is to propose an apparatus possessing, in a positive manner, limited flight safety at altitude.
• the apparatus according to the invention is characterized in that it comprises:
• a counterweight provided at its base with a stop and rolling member intended to cooperate with the ground and to limit the amplitude of pivoting of the beam on the horizontal axis in the direction of elevation of the large arm,
• the object of the invention consists essentially of a large rigid beam placed about 1/5 of its length on a supporting pylon, which gives a large arm and a small arm. This large beam is articulated on the top of the supporting pylon around. two horizontal and vertical axes. The end of the large arm can therefore turn in one direction as in the other, go up or down, having as its point of articulation the top of the pylon, the small arms doing the reverse movements. At the end of the small arm hangs the counterweight which can be weighed down or lightened.
• the aircraft can taxi at intervals of a few meters ( depending on the height of the supporting pylon and the sling), which allows the student to learn to taxi.
• the aircraft still experiences an inertia effect similar to the reality of flight takeoff and landing, thanks to the inertia effect proportional to the counterweight.
• the apparatus according to the invention allows aircraft, such as propeller or jet aircraft, helicopter, gyrocopter, to evolve on land and in the air.
• aircraft such as propeller or jet aircraft, helicopter, gyrocopter
• the aircraft are suspended at the end of the sling at their center of gravity.
• helicopter like the gyrocopter, the latter are suspended above the rotor head by a system allowing rotation.
• the apparatus according to the invention can be constructed to have a large arm with a radius of 65 meters, a " height of 10 meters for the supporting pylon, in order to define either a diameter of 130 meters, or a revolution perimeter or track length of around 400 meters.
• the apparatus according to the invention makes it possible to operate an aircraft at an altitude of approximately 30 meters sufficient to learn the take-off and, above all, the landing phase, including that of rounding.
• the present invention therefore relates to an apparatus for training and piloting a captive aircraft inexpensive to build, at a very low cost price in use compared to traditional means and making it possible to devote, for a period of time of equal flight, more time learning the take-off and, above all, landing maneuvers, as well as the conjugation in flight of the three axes, pitch, roll, yaw and this safely by any time.
• FIG. 1 is a side elevation of the aircraft training and piloting apparatus according to the invention.
• Fig. 2 is a plan view of the same device, taken along line II-II of the fig. 1.
• Fig. 3 is a partial elevation, on a larger scale, of the central part of the same device.
• the apparatus comprises a beam composed, in an exemplary embodiment, of a central bracket A extended, on one side, by a large stiffened arm B and, on the other side, by a small stiffened arm C, the arms B and C being supported at various points by cables 1 all starting from the same attachment point 8 of the central bracket.
• a counterweight G is hung by a universal joint H allowing it to articulate in all directions.
• a steerable and self-steering wheel I is fixed with a flexible shock absorber. This wheel I serves as a flexible stop and smoothly with the ground when the beam pivots on a horizontal axis, as described below.
• the central bracket which may be of any composition, will preferably be made up, as shown, of a main tube 15 of the two cross tubes 27 and 28, stiffened by the tubes 26.
• Four tubes 17 hold the tube 15 vertically by the junction point 16.
• the top of the tube 15 is held vertically, from point 8, by cables 2 and 20.
• the tubes 27 are extended by tubes 18 braced, vertically, by tubes 19 and, horizontally, by cables 9.
• the structure D can be a tube fixed to the ground by any means preventing it from moving. It is held vertically by 6-stage cables from the top of the D pylon and moored to stakes (7) firmly fixed to the ground. The number of cables 6 is in sufficient quantity to allow good maintenance of the pylon D.
• the counterweight G is a tank filled with water or sand, but it is preferable to fill it with steel shot to reduce its volume to equal weight.
• This counterweight G is suspended at the end of the small arm C by a universal joint H thus allowing it to always keep a vertical balance, whatever the horizontal or inclined position of the small arm C.
• This counterweight G always remains vertical, the self-rotating I wheel will always contact the ground in good conditions.
• This self-orienting wheel can be of a current commercial model and be associated with a shock absorber, incorporated or not. the mass to be given to the counterweight must be sufficient for the movable assembly fit, B, C to be balanced, so that the counterweight G tends to descend and, by definition, that the extrem i e- a large arm B tends to go up. All around the contr p ⁇ oids G, the cast iron plates 12 can be hung or unchecked easily.
• each plate 12 does not exceed 20 kg, so that a man of average strength can handle them.
• These plates 12 are provided with a handle to facilitate handling.
• the number of plates 12, to be positioned around the counterweight G, is variable, according to the weight of the aircraft M attached to the end of the sling J and according to the desired lightening of this aircraft M.
• these plates will be made of steel or cast iron.
• the large arm B consists of a plurality of elementary modules 13 comprising each a section of tube 130 provided, at both ends, with two connection flanges 23.
• the tube section 130 is carrying, in its transverse median part, a cable-holder rhombus N connected to the flanges 23 by guying cables 5.
• the diamond N is constituted by radial tubes 21, the ends 24 of which are joined by tubes 22.
• the modules 13 are placed end to end while being joined, on the one hand, by means of flanges 23 and, on the other hand, by means of cables 3 extending between the diamonds. At least some of the elementary modules are, moreover, suspended by the cables 1 at point 8 of the bracket A.
• the elementary module 13 is fixed, by the flange 23, to the corresponding end of the tube 28 of the central bracket.
• the assembly of the large arm thus formed is also held by cables 10 hooked to the ends of the tubes 18. All of this assembly gives a triangulation effect whose purpose is to stiffen the large arm B.
• the small arm C is identical in design to the large arm B, only the cables are shorter.
• the principle for hanging cables 1 and 11 is identical.
• a sling J is attached to the end of the large arm B, by a universal joint K, which allows the sling to articulate in all directions.
• a universal joint fitted with a hook L, makes it possible to suspend the aircraft M by its center of gravity.
• Other lifting systems can be used in place of the sling J, while retaining the universal joints K and L, such as rigid tubes, elastic sling or a combination of several of these solutions.
• Mooring points 35 and 36 are provided under the large arm and under the small arm to allow the ends of the cables of two winches 350 and 360 to be hung. These two winches are fixed to the ground, one under point 35 , the other under point 36. This system makes it possible to maneuver the mobile assembly along the axis E, in order to suspend or unhook the aircraft M and to place or remove the plates 12.
• the aerial training device described and shown without going beyond the ambit of the invention, for example, to the structure of the bracket A with arms B and C, during assembly. articulated in E and F. It is also possible to use other weight systems G and plates 12, as well as another stop method than that of the shock absorber wheel I.
• the pylon D can be replaced by a pylon - self-supporting or by a concrete tower.
• the sling J which is one of the main parts of the invention described, can be in multiple forms and compositions, such as flexible, rigid, elastic.
• the device according to the invention is entirely removable in small, easy-to-handle components made up of tubes, cables, diamonds, counterweights.
• Fig. 1 shows that it can be provided to connect the aircraft M to the large arm B by a second flexible sling J .., intended to limit the elevation of the aircraft M under the effect of centrifugal force.
• This sling J. is attached to the arm B, • near the bracket A and to the center of gravity L of the aircraft and has a length calculated as a function of the desired elevation limit.
• This sling J. also assumes a safety function by making the aircraft doubly captive of the large arm B.
• the sling J. passes through a guide M., adapted at the end of the inner wing of the aircraft M in the case of an airplane. This arrangement makes it possible to preserve the freedom of maneuver on the roll axis.

Landscapes

• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Theoretical Computer Science (AREA)
• Business, Economics & Management (AREA)
• Physics & Mathematics (AREA)
• Educational Administration (AREA)
• Educational Technology (AREA)
• General Physics & Mathematics (AREA)
• Entrepreneurship & Innovation (AREA)
• Mechanical Engineering (AREA)
• Toys (AREA)
• Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
• Jib Cranes (AREA)
• Magnetic Bearings And Hydrostatic Bearings (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=9320951

Family Applications (1)

Country Status (6)

Families Citing this family (8)

Family Cites Families (13)

• 1985
  • 1985-07-02 FR FR8510196A patent/FR2584374A1/fr not_active Withdrawn
• 1986
  • 1986-06-25 ES ES556805A patent/ES8707459A1/es not_active Expired
  • 1986-06-26 EP EP86903447A patent/EP0226606A1/fr not_active Ceased
  • 1986-06-26 JP JP61503491A patent/JPS62503193A/ja active Pending
  • 1986-06-26 WO PCT/FR1986/000225 patent/WO1987000141A1/fr not_active Application Discontinuation
  • 1986-06-26 US US07/018,810 patent/US4790755A/en not_active Expired - Fee Related

Non-Patent Citations (1)

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