Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C39/00—Aircraft not otherwise provided for
  • B64C39/001—Flying saucers

Definitions

• the present invention relates to a flying craft having the flight performance of a helicopter as well as a jet aircraft, with reduced engine power.
• Some aircraft types having a temporary lift capability by tilting their exhaust pipe or their helice, have reduced subsonic speed and service ceiling.
• the invention as claimed is intended to remedy the drawbacks in the previous paragraph 3 and to provide a total new concept of flight which consists of de ⁇ creasing the front pressure below the downstream pressure of the air flow separation zone.
• the helicoplane will be pushed forward by the atmospheric air instead of being dragged.
• this decrease of front pressure could be affected by adding to the front air flow, a rotational velocity by a rotating ring (8) .
• This rotating ring (8) could be combined with a horizontal blower (11) instead of a horizontal helice for vertical take-off and landing, as well as for initial horizontal motion.
• This horizontal blower provides vertical motion by ts blades and by its external rotating surface it provides the horizontal motion of the helicoplane.
• the helico- plane has to have a lens shaped upside boundary (1,2) and a flat downside boundary (3) and both must permit tagential and irrotational air flow.
• the upside boundary is characterized
• R is the horizontal maximum radius
• r and z are the coordinates of any surface point and b has the following values:
• the hull is provided with the following flaps.
• the three first flaps are required to balance the front torque of the hull as well as to secure the steady linear flight.
• the flight stability condition is mentioned in para ⁇ graph 4.6.1 of the' ⁇ light Theory"attached hereto as appendix I. All flaps could increase the lift if required, as during gliding flight or while landing. Also, they can cause an abrupt lifting by an 8g acceleration.
• the two central downside flaps (7) are balancing the side torque of the front rotating flow, caused by the ro ⁇ tating ring. They can also cause an abrupt side rotation of 90° in 0,6 seconds.
• the external surface of the rotating ring adds ro ⁇ tational speed to the front air flow and provokes the Magnus phenomena. It is covered all around by the flight cover apart from the front segment which is symmetrical to the downstream air flow separation zone. This flight cover is the lower part of the upside 0 helicoplane boundary.
• the ring rotating surface is characterized by having the same surface relationship as the hull.
• the hull is provided with the following blades.
• the rearside blades (9) also balance the torque of this side thrust around the vertical axis z.
• the central downside blades (10) can cause, if re ⁇ quired, an abrupt side motion of 8g acceleration at low altitudes.
• the blower is horizontal and of mixed-flow type.
• the blower impeller is constituted by two surfaces; the inner surface has a frustum shape.
• the outer surface is frustum shaped on its inner side and has the curved rotating ring (8) on its external side. Between these two surfaces are fixed the impeller blades. These blades are tilted in such a way that the surface angular speed is about seven times the blower rate flow angular speed.
• the impeller is rotating around the cabin hull by means of bearings(21) and/or a magnetic field. Also, a rotation transmission ring (22) is provided. Above and below, the impeller there are two circular openings (12 and 13) to allow for the vertical air flow. In these two openings, vanes for driving the air flow and balancing the torque of the blower flow, as well as its friction torque are provided.
• Figure 8 shows the blower impeller in cross section
• Fig. 9 shows the blower impeller from above (14) and from below (15)
• this horizontal blower causes two motions.
• the vertical motion is provided by its blades as well as the initial horizontal motion of low speed.
• the horizontal motion with supersonic speed is caused by its external surface which decreases the front pressure.
• the upward opening (12) is provided with the tilt vanes (23), which can be moved in close this opening partly and consequently reduce the lift force on the subse ⁇ quent segment of the blower.
• the impulse vane (24) is utilized. This vane pushed below the opening (13) at its segment beyond the rear downside flap (6) tilts the rear blower ratio of flow horizontally down ⁇ stream.
• Fig. 1 is the side view of the helicoplane.
• Reference no. 1 is the hull
• 2 is the flight cover
• 8 the rotating ring
• 9 and 10 the vertical blades.
• Fig. 2 is the cross section on the motion direction. Reference no. 1 to 10 are the same as above, 11 is the horizontal blower. 23 and 24 are the tilt and impulse vanes.
• Figure 3 is the front view of the helicoplane.
• Figure 4 is the cross-section, normal to the motion direction.
• Reference no. 1 to 10 are the same as above, 12 and 13 are the circular openings, above and below the blower, for the blower rate of flow.
• Fig. 5 is the view of the helicoplane from above.
• Fig. 6 is half the horizontal cross section of the helicoplane. No. 1 to 13 are the same as above. No,
• 16 is the pilot seat. No. 17 is the passenger or troop seats. 18 is the engine, the mechanisms and the fuel tank space. 19 is the cargo space.
• the cabin accomodation corresponds to a helico- plane radius of 5 .
• Fig. 7 is the view of the helicoplane from below.
• No. 1 to 19 are the same as previously mentioned.
• No. 20 is the under carriage shock absorber struts.
• fcig. 8 is the cross-section of the blower impeller.
• No. 1 to 20 are the same as previously mentioned.
• No. 21 is the bearing rings.
• No. 22 is the ring of movement transmission.
• Fig. 9 is the view of the blower impeller.
• No. 14 is the view from above.
• No. 15 is the view from below.
• Helicoplane Flight Theory includes the theory, the- respective relationships and the computation of diverse flight cases of heli ⁇ coplane.
• Appendix 2 includes the same for the heli ⁇ coplane helice. The following are the main charac ⁇ teristics.
• the invention is exploitable because it is adventageous from all points of view in comparison with existing aircraft, and it is also less costly.
• the main advantage in comparison with utilized air ⁇ craft are as follows:
• Construction costs without avionics 25% Maintenance costs without avionics 25%
• the total flight cost of a helicoplane is less than 20% of a conventional commercial aircraft and the helicoplane amortization is no more than 25% of the aircraft.
• a strong economica motive exists to substitute the conventional aircraft by helicoplane even if the capital amortization of the first is not completed.
• Number of helicoplanes required is 33% of conventional transport aircraft.
• the helicoplane flight includes the following phases.
• Tilt of the helicoplane to the front direction is accomplished by using tilt vanes (23) and subse- quently, horizontal motion begins.
• An increase of horizontal speed is accomplished by tilting the rear vertical blower air flow downstream. This is effected by the impulse vane (24) . This phase lasts 8 seconds with a final horizontal speed of 21 m/s. 8.4.
• the acceleration increase phase from 21 m/s to 407 m/s horizontal speed lasts one minute.
• the in ⁇ crease of the acceleration is due to the Magnus phen ⁇ omena of the rotating ring and the final acceler-
• Losing altitude phase can be performed by gliding.
• Landing is to be done vertically at any pador by gliding on an airfield runway.

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• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Toys (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Measurement Of The Respiration, Hearing Ability, Form, And Blood Characteristics Of Living Organisms (AREA)

Applications Claiming Priority (2)

Publications (1)

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• 1984
  • 1984-06-12 JP JP59502459A patent/JPS61501766A/ja active Granted
  • 1984-06-12 AU AU30676/84A patent/AU3067684A/en not_active Abandoned
  • 1984-06-12 WO PCT/EP1984/000173 patent/WO1985003684A1/en not_active Ceased
  • 1984-06-12 EP EP84902448A patent/EP0172829A1/de not_active Withdrawn
• 1985
  • 1985-05-17 SU SU853956143A patent/SU1496630A3/ru active

Non-Patent Citations (1)

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