JPS61501766A - Combined aircraft with helicopter and airplane - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention] helico brain ■、Technical field The present invention has the flight performance of a helicopter or jet aircraft while reducing engine power. Concerning crushed flying objects.

2. Background technology Fluid mechanics theories, formulas, and relationships are used in the present invention, and the Magnus phenomenon is It is clearly used. Among the many books on this subject are John Riley (J. ohn Wilay) & Sons Incoho Red is New York The book titled ``Basic Mechanics of Fluids'' edited by Hunter House C in 1953 Hunter House) and F, Dabriny, No\Uni (F.

There is a book called -3Hωduck). -kai book catalog card number 53-651111 ).

3. Prior art 3.1. Helicopter prior art, horizontal main propeller in a helicopter (axial flow holLzontal + aain helice ) facilitates balance but inhibits high altitude and high climb limit capabilities.

3.2. Aircraft prior technology. High front pressure and resulting drag (air resistance) ) is propeller thrust (helic air) or jet thrust (jet fuel gas) is overcome by the downstream driving force. But super slow Propulsion for degrees requires a large power engine and large fuel burns. aircraft lift generally rely on wings, so vertical takeoffs and landings are not possible in such aircraft. Land is not viable.

Several types of aircraft have temporary lift capabilities by tilting their exhaust pipes or propellers. The aircraft had reduced supersonic speeds and use climb limits.

4.Disclosure of the invention 4.1. principles of flight The present invention corrects the drawbacks mentioned in the previous paragraph and aims to reduce the pressure at the front of the aircraft downstream of the airflow separation zone. We aim to provide a completely new flight principle of flying with the pressure reduced to less than purpose. Kichi, instead of receiving resistance, this helicobrane is pushed forward by the atmosphere. It is something that is pushed by Due to the Magnus phenomenon, this decrease in front pressure reduces the front airflow This was made possible by adding rotational speed using the rotating ring (8). this The rotating ring (8) is conventionally used for vertical take-off and landing as well as for initial horizontal movement. Combined with a horizontal blower aυ to replace the horizontal propeller (helice).

To obtain substantial speed, this helicobrane also incorporates a horizontal blower. It is combined with the power aircraft (1, 2).

This horizontal blower uses its blades to provide vertical motion to the helicopter. Its external rotating surface also provides horizontal motion.

4.2. Helicobran body The fuselage is circular because it incorporates a horizontal blower horizontally. Aimed at low drag In order to and a flat lower cover (3), both of which have a tangential and eddy-free air flow. must be allowed to flow.

For this purpose, the upper cover has the following relationship.

Here, R is the maximum radius in the horizontal direction, r and 2 are the coordinates of an arbitrary surface point, and b is If the value of b is greater than -0,7810,87120,9665, it means that other semi-elliptical The same applies to surfaces. On the other hand, the curved upper cover and flat lower cover are horizontal Provides additional lift during movement.

4.36 Flap To balance the frontal torque and provide maneuverability, the aircraft uses the following flaps: Be equipped.

0.22R” front lower flap (4).

0.15R" 17111 part upper side 7 y y f) 15) * 0, 1SR" f) 41k B lower side 75-/F (6).

2X0. IQ2R” two central lower flaps (7).

The front three flaps are used to balance the front torque of the aircraft as well as maintain a stable straight line. Required to ensure flight.

Flight stability conditions are described in the “Helicobrane Flight Theory” attached to this specification as Appendix ■. Paragraph 4.6.1 of the

All flaps can provide additional lift if needed during gliding flight or landing. can.

Also, those flaps can generate sudden lift when the field accelerates. 2 two central lower flaps (η is the side of the front rotational flow brought about by the rotating ring) Keep the partial torque balanced. These flaps produce a rapid lateral rotation of 90” in 0.6 seconds. It can also cause a turnaround.

4.40 rotation ring The outer surface of the rotating ring adds rotational speed to the front airflow causing the Magnus effect.

Its outer surface, except for the front section, is arranged symmetrically with respect to the downstream airflow separation zone. covered by a cover.

This cover consists of the lower part of the upper cover.The rotating surface of the 0-rotation ring is as follows. As shown in the formula, it has the same surface relationship as the aircraft.

Here, R1-0,96R (R: maximum radius of the aircraft).

In paragraph 5.2 of Appendix I "Helicobrane Flight Theory" The speed of the lane is independent of the air density of the atmosphere and is twice the circumferential speed of the rotating ring. It has been found that the above. In the same appendix l, paragraph 8.6: Even at low altitudes, the helicobrane's ultra-low speed can be realized with the engine power of 174 engines of the same weight aircraft. It turns out that it is possible. This is rather true for the Magnus phenomenon. Because the thin air layer results in an average side velocity of only 8% of the helicobrane velocity , of course.

4.5. vertical wing In order to balance the horizontal torque and achieve maneuverability, the aircraft has the following vertical wings. We are prepared.

0.17SR”Rear side of total area 11191°0.06R1rrr Bottom center of total area of side wing α.

They both balance the side thrust due to the pressure of the uncovered rotating ring. necessary to maintain. The rear wing (9) also receives the torque of this lateral thrust about the vertical axis Z. balance the balance. Center lower wing 0 [is the sharp side with acceleration of % at low altitude, if necessary. It can cause partial movements.

4.6. Helicobran horizontal blower (Fig. JF19) The horizontal blower is horizontal. , is a mixed flow type. The impeller of a horizontal blower has two walls and an inner The wall on the other side is truncated. The outer wall is truncated on the inner side, and the outer circumference It has a rotating ring (8) which is curved inward. There are multiple blades between these two walls. is fixed. These blades have a surface angular velocity equal to the horizontal blower flow rate (h elic flow) is inclined so that the angular velocity is approximately 7 times.

The impeller is connected via a support member (bearing) (21) and/or a magnetic field. The cabin rotates around the fuselage. Further, a rotation transmission ring (22) is provided. There is. Above and below the impeller are annular openings through which vertical air flows. There are mouths (12, 13).

These two openings control the airflow and the horizontal blower flow torque and its In order to balance the rubbing torque, vanes, which will be described later, are provided. Figure 8 shows the horizontal block. Fig. 9 shows a cross section of the impeller of the power supply, and Fig. 9 is taken from the upper αC and the lower part (5), respectively. The horizontal blower impeller is shown.

As a result, this horizontal blower allows two movements. i.e. on that blade This allows for vertical movement and a slow initial horizontal movement. Horizontal motion at supersonic speeds is caused by the outer surface reducing front pressure.

4.7, Horizontal blower blades In order to tilt the helicobrane in any direction, the upper opening (2) has a tilting A slanted blade (23) is provided, and the slanted blade (23) partially closes this opening. The horizontal blower moves in such a way that the horizontal blower I can do it. To improve the initial horizontal velocity of the helicobrane, impulse vanes (24 ) is used. This impulse blade is located at the rear part of the rear lower flap (6). , by pressing the lower part of the opening (2), the rear airflow of the horizontal blower is directed horizontally downstream. tilt to.

5. Drawing wA light FIG. 1 is a side view of the helicobrane. 1 is the fuselage, 2 is the upper cover, 3 is the lower side Cover, 4, 5. 6. 7 is a flap, 8 is a rotating ring, 9.10 is a vertical wing It is.

FIG. 2 is a sectional view in the direction of movement. ] to 10 is the same as above, and 1 1 is a horizontal blower, 23 and 24 are inclined blades and impulse blades.

Figure IJ3 is a front view of the helicobrane.

FIG. 4 is a cross-sectional view normal to the direction of movement. Horizontal 1 to 10 are the same as above. Yes, 12゜13 is above and below the blower to adjust the flow rate of the horizontal blower. It is an annular opening provided in the

Driving vanes for controlling air flow rate are attached to each of these openings.

FIG. 5 is a drawing of the helicobran seen from above.

FIG. 6 is a half horizontal cross-sectional view of the helicobrane. 1 to 13 are the same as above It is.

16 is a biloft seat. 17 is a seat for guests or troops. 1B is en space for engine, various mechanisms and fuel tank. 19 is the luggage space . The cabin accommodation facility is equivalent to half a 5m helicobane.

FIG. 7 is a drawing of the helicobran seen from below. l to 19 are the same as mentioned above It is.

Additionally, there is a shock-absorbing strut for the lower carriage.

FIG. 8 is a sectional view of the impeller of the horizontal blower. 1 and addition are the same as mentioned above. be.

21 is a support member (bearing), and n is a rotation transmission ring.

FIG. 9 is a drawing of the impeller of the horizontal blower. 14 is a drawing seen from above. be. 15 is a drawing seen from below.

6. Details of the invention and examples Attached appendix ■ "Helicobrane flight theory" includes the theory of helicobrane and 0 types of each relationship. The calculations for each flight case are described. Appendix ■ is the thrust of the helicobrane (hel Regarding ice), the same matters as above are described. The main features are as follows. Ru.

6.1. About a helicobran in the case of a total wing load of 100 kg/n.

In use '11MAl1 22700m+.

Climb limit rise time: 3 minutes Maximum climbing speed limit 28g577ha Maximum low airspeed 2.58 maha Minimum low airspeed.

Vertical climbing speed 15m/3 Sudden vertical when 8G is required Directional or lateral motion acceleration 78 m/s Intense rotation time o, Looping radius 10.5 km6.2. In the case of radius R-3, 5, 7, ton with full wing load 100 kg# Total weight of helicobran 2830 7850 15400 31400kg medal of honor Display 2350 5900 10900 17400 Required for HP increase limit 95 2a5 435 693 HP required on the ground 138 tll 3470 6430 1Q42011P fuel tank weight Main tank 160 380 710 1150 and auxiliary tank 100 230 430　700kgops flight range at low altitude Main tank equipped 750 750 750 750km Auxiliary tank equipped 1240 1240 1240 1240km ascent limit 8970 8600 875 0.87som7, Economic exploitation of inventions The present invention is advantageous in all respects and is inexpensive compared to existing aircraft. Therefore, it can be used economically.

The main benefits compared to the aircraft in use are:

7.1. For all aircraft Manufacturing cost excluding electronic TSM system 5% Maintenance cost excluding electronic @ grid 5% Unlimited practical range Vertical takeoff and landing The total cost of flying a helicobrane is less than a percent of that of a traditional commercial aircraft; The depreciation of the lane cannot be more than % of the aircraft.

Therefore, even if the initial capital depreciation has not been completed, converting a conventional aircraft into a helicobane There is a strong economic incentive to replace it.

7.2. Regarding commercial aircraft The number of helicobrans required is % of that of conventional transport aircraft.

The crew required is 1/3.

Fuel consumption is 3%.

Takeoff and landing within urban areas.

7.34 Regarding military aircraft Fuel consumption is 3%.

Its maximum climb speed is 20% faster than conventional aircraft.

Low airspeed is much faster, more than twice as fast.

The sudden movement normal to the flight has an acceleration of 8G and a somersault radius of 10.5km. Ru.

High dispersion from the airfield (dissipation - from a forward position or more than 3ooot) Can be operated from the vessel below also 8, flight movement Flight of the helicobrane includes the following aspects.

8.1. Vertical take-off from an altitude of 400m to 20m can be achieved in 4 seconds.

8.2. The inclination of the helicobran with respect to the front direction is achieved by using the inclined vanes (23). As a result, horizontal movement begins.

8.3. Increasing horizontal speed is achieved by tilting the vertical airflow downstream of the blower. more achieved. This is carried out by impulse vanes (24). This aspect is the most 8 seconds at final horizontal speed 21a/s, horizontal speed 21n/s to 407+a/s The acceleration increase mode only takes one minute. The increase in acceleration is due to the Magnus phenomenon of the rotating ring. , the final acceleration is 34 m/sec''.

8.5. The acceleration reduction mode from 407o+/s to 904m/s is the final acceleration 2. 2+w/see” and takes 2 minutes.

8.6. At the start of 904+a/s, the steady speed is 24 or more at low altitude. It takes about 42 minutes, and about 5 hours at the E ascent limit altitude.

8.7. Losing altitude phase is a slip It can be carried out by the sky.

8.80 Landing is carried out with the desired butt or by taxiing on the airfield runway. It is something.

Un#S mouth Grass mouth Atsushi 1 item international search report

Claims (7)

[Claims] 1. Helicobran flight principle The high frontal pressure and resulting drag when conventional aircraft fly be overcome by the downstream propulsion force, if there is either thrust or jet combustible gas. However, the present invention reduces the forward pressure of the aircraft below the pressure downstream of the airflow separation zone. so that the aircraft is pushed forward by the atmosphere instead of being resisted. According to the Magnus phenomenon, the front airflow is requested to reduce the front pressure. By adding the rotational speed of the rotating ring (8) claimed in claim 4, In order to do this and obtain substantial speed, the flight principle is as claimed in claim 1. The low-drag airframe (1, 2) claimed in item 2 is provided, and the rotating ring (8) is vertically separated. Claim 6 provided for land and landing and initial horizontal movement and a horizontal blower (11), which is further assembled into the aircraft. be included. 2. helicoplane body Aircraft secure lift with their wings, but helicoplanes have a lens-shaped upper cover. (1, 2) and a flat lower cover (3), and this lens-shaped upper cover is ▲Contains mathematical formulas, chemical formulas, tables, etc.▼ , where R is the maximum radius in the horizontal direction, and r and Z are the coordinates of any surface point. ▲There are mathematical formulas, chemical formulas, tables, etc.▼ , such a surface has the same drag ratio with tangential airflow and eddyless airflow as the aircraft. allows for substantial lift up to and thus makes gliding flight for landing viable. , as well as semi-ellipses ▲ There are mathematical formulas, chemical formulas, tables, etc. ▼ which is almost the same as above. It may be a surface relationship, such as ▲here are mathematical formulas, chemical formulas, tables, etc.▼. 3. helicoplane flaps The helicoplane flaps correspond to claims directed to the helicoplane fuselage. The flaps included in the dependent claim include the front lower side (4), the rear upper side (5), These are the flaps on the lower rear side (6) and the lower center side (7), and the front three flaps are In order to balance the front torque of the aircraft and ensure stable straight flight. All flaps increase lift when needed, or 8G A sudden lift of acceleration can be caused, while the two central lower flaps (7 ) refers to the front rotational flow caused by the rotating ring claimed in claim 4. Balance the side torques and prevent them from causing sudden rotations about the direction of motion. I can do it. 4. helicoplane rotating ring The high frontal pressure of a flying aircraft and the drag it creates can cause propeller thrust or If any of the jet thrust is overcome by the downstream thrust, this thrust requires a large power engine and high fuel consumption, especially at supersonic speeds; By adding rotational speed to the front airflow, the front pressure is reduced and the Magnus phenomenon is induced. It is much more economical to use the This is carried out by means of a rotating ring (8) located inside the lower part of the cover, but the rear separation The upper cover, which is placed symmetrically in the zone, does not cover the front part, so it is difficult to rotate. The surface of the ring (8) has the same surface relationship as the fuselage, i.e., there are ▲ mathematical formulas, chemical formulas, tables, etc. S▼ Or ▲There are mathematical formulas, chemical formulas, tables, etc.▼ Here, R1=0.96R (R: maximum radius of the aircraft). 5. vertical wing of helicoplane The wings provided are a rear wing (9) and a lower central wing (10), both vertical wings. is necessary to balance the side thrust of the rotating ring pressure not covered by the The rear wing (9) also balances the torque of this side thrust around the vertical axis. The entire scope of this claim is dependent on claim 4 for the rotating ring. are doing. 6. helicoplane horizontal blower Helicopter propeller located above the fuselage makes it easier to balance the helicopter but inhibits the possibility of high speed. To correct this shortcoming, helicoplay The mixed flow type horizontal blower (11) installed in the aircraft is compatible with the helicoplane body. It is incorporated between the lower upper cover of the aircraft and functions simply as a flight cover. The propeller impeller is supported by the aircraft support member (22) and/or by the magnetic field. Above and below the impeller, there is an upper There are upper and lower openings (12, 13), these openings are for the drive vanes, i.e. for tilting. Equipped with oblique blades and impulse blades. 7. Helicoplane Horizontal Prower VanesHelicoplane Horizontal Prower Vanes is used to drive the blower airflow vertically and to rotate the blower airflow horizontally. In order to balance the torques caused by the rotation and friction of the supporting members, horizontal These are drive vanes installed in the two openings (12, 13) of the winder, which partially reduce the lift force. at any part of the opening (12) to tilt the helicoplane in the desired direction. slanted vanes (23) to reduce the vertical airflow and further increase the horizontal velocity. The horizontal blower airflow at the rear of the helicobrane is tilted horizontally and downstream. All these blades are used for helicopter flight. The invention is claimed as a dependent claim of claim 6 for a horizontal blower of a plane.