HELICOPTER-AIRPLANE COMPOUND AIRCRAFT

Abstract: The invention relates to a new flight motion concept. It consists of a decrease of the front pressure of helicoplanes to lower than the downstream separation zone pressure. So helicoplanes are pushed forward by atmospheric air instead of being dragged as conventional aircraft are. This decrease of front pressure, according to the Magnus phenomenon, is effected by adding to the front air flow a rotational velocity. That is done by the external surface (8) of a horizontal mixed-flow blower (11). So the blower provides vertical take-­ off, vertical landing and initial low speed horizontal motion by its blades, and by its external surface, there is provided a supersonic speed in horizontal motion. The blower is incorporated in a low drag semilens-­ shaped hull (1-3), being uncovered only in a front segment. Helicoplanes can accomplish low level speed of 2,5 MACH, a ceiling range which is pratically unlimited, glide capability, manoeuverability acceleration 8g, and time to ceiling 3 min.

Description: HELICOPLANE I, TECHNICAL FIELD 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. 2. BACKGROUND ART The mechanics theory of fluids, its formulas and relationships are used in the present invent ion, and the Magnus phenomenon is exploited in it. One of the many books concerning this field is the Hunter House and F.W. Howe entitled "Basic Mechanics of Fluids" edited in 1953 in New York by John Wilay and Sons, Inc. (Library of Congress Catalog Card Number 53-6518). 3. PRIOR ART 3.1, HELICOPER PRIOR ART. The axial flow horizontal main helice over its hull facilitates the balance but prevents any potential for high speeds and high ceiling. 3.2. AIRCRAFT PRIOR ART. The high front pressure and the resulting drag are overcome by downstream impulse, provided either by helic air or jet combustion gas. This impulse, for supersonic speed, requires a large power engine and large fuel combustion. Because the aircraft lift is generally based on the wings, vertical take-off and landing are unfeasible for such aircraft. Some aircraft types, having a temporary lift capability by tilting their exhaust pipe or their helice, have reduced subsonic speed and service ceiling. 4. DISCLOSURE OF THE INVENTION AS CLAIMED. 4.1. CONCEPT OF FLIGHT 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 decreasing the front pressure below the downstream pressure of the air flow separation zone. Thus, the helicoplane will be pushed forward by the atmospheric air instead of being dragged. According to the Magnus phenomenon, 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. For substantial speed, the concept of motion is combined with a low drag hull (1,2) which incorporates the horizontal blower. This horizontal blower provides vertical motion by its blades and by its external rotating surface it provides the horizontal motion of the helicoplane. 4.2. HELICOPLANE HULL Because the hull incorporates the blower horizontally, it is circular. For purposes of low drag, the helicoplane 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. For this purpose, the upside boundary is characterized by the relationship: EMI3.1 where R is the horizontal maximum radius, t and z are the coordinates of any surface point and 2 has the following values: EMI3.2 Other surfaces almost similar to the semiellipsoidal are acceptable. The curved upside boundary and the flat downside boundary provide an additional lift during horizontal motion. 4.3. FLAPS To balance the front torque, and for manoeuvering capability, the hull is provided with the following flaps. The front downside flap (4) of 0,22 R2 2 The rear upside flap (5) of 0,15 R The rear downside flap (6) of 0,15 R2 The two center downside flaps (7) 2 X 0,102 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 paragraph 4.6.1 of the"Flight 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 rotating ring. They can also cause an abrupt side rotation of 90O in 0,6 seconds. 4.4. ROTATING RING The external surface of the rotating ring adds rotational 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 helicoplane boundary. The ring rotating surface is characterized by having the same surface relationship as the hull. EMI4.1 where R1 =0,96 R of the hull maximum radius. In paragraph 5.2 of the attached appendix 1, "Heli- coplane Flight Theory", it has been found out that the helicoplane speed is independent of the atmospheric altitude density and more than twice the ring perimeter speed. In paragraph 8.6 of the same appendix, it has been found that helicoplane supersonic speed, even at low altitude is feasible with engine power onefourth of the same weight aircraft engine power. That is natural, because in Magnus phenomena, a rather thin air layer get a mean side speed which is only 8% of the helicoplane speed. 4.5 VERTICAL BLADES To balance horizontal torque and for the purpose of manoeuver capability, the hull is provided with the following blades. R22 The rearside blades (9) of 0,175 R m total area. The central downside blades (10) of 0,06 R2m2 total area. Both of them are required to balance the side thrust of the uncovered rotating ring pressure. 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 required, an abrupt side motion of 8g acceleration at low altitudes. 4.6. HELICOPLANE BLOWER (Fig. 9) 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, and Fig. 9 shows the blower impeller from above (14) and from below (15). Finally, 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. 4.7. BLOWER VANES To tilt the helicoplane toward any direction, 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 subsequent segment of the blower. To improve the initial horizontal speed of the helicoplane, 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 downstream. 5. DESCRIPTION OF FIGURES Fig. 1 is the side view of the helicoplane. Reference no. 1 is the hull, 2 is the flight cover, 3, 4, 5, 6 and 7 the flaps, 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. On these openings are fixed the above and below driver vanes of the air 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 helicoplane radius of 5 m. 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. Fig. 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. 6. DETAILS AND EXAMPLES OF THE INVENTION The attached appendix "Helicoplane Flight Theory" includes the theory, the respective relationships and the computation of diverse flight cases of helicoplane. Appendix 2 includes the same for the helicoplane helice. The following are the main characteristics. 6.1. For any helicoplane with full wingload of 100 kg/m2 Service ceiling 22700 m. Ceiling climb time 3 min. Maximum ceiling speed 2,95 Mach. Maximum low level speed 2,58 Mach. Minimum low level speed 0 Vertical climb speed 15 m/s Abrupt vertical or side motion acceleration if required 8g or 78 mi sec2 900 abrupt rotation time, around motion direction, if required 0,6 sec. Looping radius 10,5 km. 6.2. For helicoplanes full wingloaded with 100 kgim2 and of radius. R = 3 5 7 lOm Total weight 2830 - 7850 - 15400 - 31400 kg Engine power Indicative 2350 5900 10900 17400 HP Required at ceiling 95 235 435 693 HP Required at ground 1380 3470 6430 10420 HP Fuel tank weight Main 160 380 710 1150 kg Auxiliary 100 230 430 700 kg OPS FLIGHT RANGE at low altitude with main tanks 750 750 750 750 km with auxiliary tanks 1240 1240 1240 1240 km at ceiling 8970 8600 8750 8750 km ENDURANCE At ceiling 325 312 317 317 min. 7. EXPLOITATION OF THE INVENTION 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 aircraft are as follows: 7. 1. WITH REGARD TO ALL AIRCRAFT Construction costs without avionics 25% Maintenance costs without avionics 25% Range practically unlimited Vertical take-off and landing 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. Thus, a strong economica motive exists to substitute the conventional aircraft by helicoplane even if the capital amortization of the first is not completed. 7.2. WITH REGARD TO COMMERCIAL AIRCRAFT Number of helicoplanes required is 33% of conventional transport aircraft. Number of crew required is one third. Fuel consumption is 3%. Take-off and landing on downtown fields. 7.3. WITH REGARD TO MILITARY AIRCRAFT Fuel consumption is 3% Ceiling speed 20% greater than with conventional aircraft Low level speed more than two times greater. Abrupt motion normal to flight 8g acceleration 8g Looping radius 10,5 km. Full dispersion and hiding away from airfields. Operation possibility from forward positions or from ships no greater than 3000 t. 8. MOTION The helicoplane flight includes the following phases. 8.1. Vertical take-off up to an altitude of 20 to 2000 m. The 20 m. are accomplished in 4 seconds. 8.2. Tilt of the helicoplane to the front direction is accomplished by using tilt vanes (23) and subsequently, horizontal motion begins. 8.3. 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 mis horizontal speed lasts one minute. The increase of the acceleration is due to the Magnus phenomena of the rotating ring and the final acceler 2 ation is 34 m/sec. . 8.5. The acceleration decreasing phase from 407 mis to 904 m/s lasts two minutes with final acceleration being 2,2 m/sec2. 8.6. At 904 m/s begins the steady speed phase which lasts at low altitudes for 24 to 42 minutes and at the ceiling altitude for about 5 hours. 8.7. Losing altitude phase can be performed by gliding. 8.8. Landing is to be done vertically at any pad or by gliding on an airfield runway.

Claims: CLAIMS 1. CONCEPT OF HELICOPLANE MOTION The high front pressure of flying conventional aircrafts and the resulting drag are overcome by a downstream impulse provided either by the helice air or by the jet combustion gas, instead the concept of motion of the invention as claimed, consists of decreasing the front pressures to lower than the downstream pressure of the airflow separation zone, and consequently, the flying craft will be pushed forward by the atmospheric air, instead of being dragged, and according to the Magnus phenomenon, this decrease of front pressure is effected by adding to the front airflow a rotational velocity by a rotating ring (8) as claimed in claim 4 and for substantial speed, this concept of motion is combined with a low drag hull (1,2) as claimed in claim 2 and said rotating ring (8) is combined with a horizontal blower (11) as claimed in claim 6 for vertical takeoff and landing, as well as for initial horizontal motion and this blower is incorporated in the hull. 2. HELICOPOLANE HULL The aircrafts secure their lifting by their wings, but the helicoplane has a lens shaped upside (1,2) and a flat downside boundary (3), and this lens shaped upside boundary is characterized by the relationship EMI11.1 where R is the horizontal maximum radius, t and z are the coordinates of any surface point and g has the following values, EMI11.2 this surface permitting tagential and irrotational air flow and a substantial lift to drag ratio similar to that of aircrafts, so that a gliding flight for landing is feasible, but also other relationship surfaces almost similar to the above as the semielipsoidal, EMI12.1 are acceptable, wherein EMI12.2 3. HELICOPLANE FLAPS They are covered by a subclaim to the claim directed to the helicoplane hull, and the provided flaps are the front downside (4), the rear upside (5), the rear downside (6) and the central downside (7) flaps, the three first flaps being required to balance the front torque of the hull, as well as to secure a steady linear flight, and all of them could augment the lift when required, or cause an abrupt lifting of 8 g acceleration, instead the two central downside flaps (7) are balancing the side torque of the front rotating flow, caused by the rotating ring claimed in claim 4 and also they can cause an abrupt rotation around motion direction. 4. HELICOPLANE ROTATING RING The high front pressure of flying aircraft and the resulting drag are overcome by a downstream impulse provided either by the helice air or by the jet combustion gas, and this impulse requires large power engines and fuel consumption especially on supersonic speed, instead it is far more economical to decrease the front pressure by adding a rotational velocity to the front air flow and to exploit the Magnus phenomenon, and this is performed by a rotating ring (8) adjusted to the lower part and inside of the overside boundary of the helicoplane hull, but uncovered at a front segment symmetrical to the rear separation zone, and characterized by having the same surface relationship as the hull, which is EMI13.1 where R1=0,96 R of the hull maximum radius. 5. HELICOPLANE VERTICAL BLADES The provided blades are the rearside (9) and the central downside (10) blades, and both of them are required to balance the side thrust of the uncovered rotating ring pressure, and especially the rearside blades (9) balance also the torque of this side thrust around the vertical axis z and all of this claim is dependent on the claim 4 directed to the rotating ring. 6. HELICOPLANE BLOWER The axial flow helice of helicopters over their hull facilitates the balance of them, but avoids any possibility of high speed, and to remedy this drawback an helicoplane mixed-flow blower (11) is incorporated be- tween the helicoplane hull and the lower overside boundary of it, which functions as flight cover only, and the impeller of the blower is supported by the hull or vice versa by bearings (14) and/or a magnetic field, and above and below the impeller are the above opening (12) and the below opening (13) to allow the blower air flow, and these openings are equipped with driving vanes, tilt vanes and an impulse vane. 7. HELICOPLANE BLOWER VANES The helicoplane blower vanes are the driving vanes fixed on the two openings (12, 13) of the blower for driving vertically its air flow and to balance the torques provided by the rotation of the blower air flow and the bearings friction, and the tilt vane (23) is provided which permits the diminuation of the vertical air flow on a segment of the opening (12) for reducing partly the lift and tilt of the helicoplane in a desired direction, and the impulse vane (24) is provided, which permits the tilt of the blower air flow on the rear of the helicoplane, horizontally and dowstream for increasing the horizontal speed, and all these vanes are claimed in subclaims of claim 6 directed to the helicoplane blower.

Inventors: PAPANDREADIS, ELIAS
Applicants: PAPANDREADIS, ELIAS
Application year: 1984
Main classification: B64C39
IPC codes: B64C39