JPS62137298A - Vertical injection jet 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 (Technical Field of the Invention) The present invention relates to the generation of ultra-high speeds by eliminating air resistance on the main wing by lifting the aircraft vertically with a single vertical jet or Okerato engine. .

(Technical background and problems) In conventional airplanes, during flight, all of the body's mm is applied to the main wings, and this causes air resistance to be applied to the main Dff.
I can't get enough speed. Also, in the stratosphere, the air pressure is low and the flight altitude is limited, so Narushima 1, which has no air rLE resistance! ! In the air above 1, it is not possible to provide a 11 upper blade to the main wing and propeller of a helicopter. In the present invention, this drawback is eliminated, and by using a vertically rising rocket and a Noel engine, it is possible to fly at both low and high altitudes. Can be doubled.

Especially SeiFil! In the space above If where there is no air resistance, the acceleration can be increased without waste, and since the air resistance applied to the main wing is small, the output of the l1il advancement engine 3 can be small, and therefore the air resistance can be increased. By mounting the main wing horizontally, it is possible to eliminate air resistance, which makes it possible to increase speed.For these reasons, conventional airplanes had to have a strong main wing, and the overall width of the main wing was huge. As a result, the engine output has to be increased, and the overall I of the airplane decreases.
nm becomes large. (of the invention)
Purpose) The present invention was made in consideration of the above circumstances, and uses a vertical rocket and a jet engine to attach a floating blade,
By eliminating air resistance on the main wing, ultra-high-speed flight is possible, and ultra-high windows and structures! It is possible to fly even above the i-zone, and this makes ultra-high speed flight possible.
The weight of the main wings can be reduced, making the aircraft lighter and reducing the engine's power output. It is also capable of flying at any low or high altitude, and its purpose is to fly at super speed.

(Summary of the Invention) In order to achieve the above-mentioned object, the present invention has several rocket or jet engines installed vertically on the fuselage, which vertically rises to provide milky blades. By reducing the air resistance, the output of the engine 3 for forward movement can be reduced, and it is possible to move smoothly.
Similarly, in the case of a jet helicopter (FIG. 1B), it is possible to fly with a very high window, and there is no air resistance, and the speed in the sky is accelerated.

(Embodiment of the Invention) Figures 1A, 2, and 3 show the first embodiment, in which the vertical engine l is mounted vertically on the center of gravity of the aircraft, and fuel is injected directly below. Bring the aircraft to the surface. As a result, it climbs at a rate of 1 Off 1 per second, and there are climbing methods 19 and 30 in East 3, but in the case of I9, the air pressure is small at the top, so you can increase the speed to the horizontal. This means that the higher the air pressure, the higher the air pressure. This is because the air resistance is so high that high speed horizontal flight is dangerous.

In addition, a horizontal forward engine 3 is connected to the main wing 8, a horizontal rudder 7/29 is built in on both sides of the rear of the fuselage, and a horizontal stabilizer 5 is connected horizontally to the fuselage. Dorsal fin 6
, and the lower fin 7 are connected in a straight line above the center of gravity 34 of the fuselage, and the fuel ignition point 2 of the vertical engine 1 must be located above the center of gravity 33 when viewed from the side.

The horizontal rudder jet engine 29 is used in locations above the stratosphere where there is no air resistance, where the vertical and vertical rudders 31 and 32 cannot be used. 2/G/3 for horizontal advancement has no air resistance on the main wing, so the energy needed to move forward is small, so 2/Non output is small and capable of ultra-high speed. The dorsal fin 6 and lower fin 7 function well in conjunction with the tail. In addition, in the case of 19 in Figure 3, the method of ascent of this aircraft is as follows: If it climbs at IQm per second, it will take 50-5000 seconds = 83 minutes to reach the upper atmosphere of the stratosphere.From this, it will go into horizontal flight and the acceleration will be 5m per second. Then, to reach the same speed as one artificial satellite.

The speed of the artificial satellite is 7400 m/s ÷ acceleration S m −
It will reach the same speed as an artificial satellite in 24 minutes at 1480 seconds. At lower altitudes, air resistance increases, acceleration is not applied, and fuel consumption increases; therefore, it is effective to climb as high as possible and maintain level flight. FIG. 3C illustrates an example of landing in the first and third east figures, which is an example of flying above the stratosphere. An airplane traveling at a high speed must be decelerated by reducing the power of the vertical engine 35 in the tail and raising the nose to reduce the forward speed and the landing path as shown in Figure 3B, 27. You have to fly and land in the same way. In addition, since the main wings 8 do not carry the weight of the aircraft and have no air resistance, they must be connected parallel to the center of gravity 33 when viewed from the side.This allows the airflow to flow against the fuselage more easily than in conventional airplanes and prevent damage to the fuselage. It becomes possible to avoid super high speed. Vertical, vertical, direction a+, 32 has the same function as a conventional airplane.

IO of Figure 1 B, Figure 3 C Figure 4 A, B, C, Figure 5 A
, B indicate the second embodiment, and parts that have the same functions as those in the first embodiment are given the same numbers and detailed explanations will be omitted.

In FIG. 4A, the Noet helicopter engine 11 is vertically connected to the main body of the Noenot helicopter, and the jet helicopter engine 11. 11 connections 1
2 to connect the fuel chamber 28, and connect the passenger compartment 14 below it.It is also possible to connect the fuel chamber below. 6 6 f 4 pieces 0''' and 0 buters 17 and 11 are connected. There are 3 C's. Next, takeoff will be explained.Next 5
[It rises vertically in the IA and moves forward in the same manner as a conventional helicopter, and uses the output of the Noeft Helibutter engine 11 in the rear direction to the engine 11 in the front direction. If it is made larger, the forward speed will be accelerated, and when landing, the opposite method will be used to decelerate and descend.Also, similar to the first embodiment, it will be possible to fly at any altitude, such as low altitude or ultra-high window. Since flying at low altitudes and high speeds is dangerous, it is necessary to fly as high as possible. This makes it possible to accelerate, and it is advantageous that it becomes super-accelerated and does not consume fuel. At high altitudes, once a high speed is reached, the engine can be stopped and the aircraft can continue flying until it reaches its destination. In either case, it is possible to increase the size. The engine mentioned above refers to both a rocket engine and a jet engine, and in the thin air above, a rocket engine must be used.

Vertical engine in Figure 2! , 35, and the number, output, mounting location, etc. of the forward engine 3 can be changed as necessary.

(Effects of the Invention) The present invention connects or incorporates a jet or rocket engine into an airplane, and uses this to lift the airplane vertically, thereby increasing the buoyancy of the airplane. By eliminating the main wing 8, by connecting the main wing 8 horizontally with the fuselage, air resistance is eliminated and super high speed is achieved.The vertical jet engine 1.35. The aim is to achieve ultra-high speed and low fuel consumption by preventing air turbulence and doubling acceleration, and to prevent aircraft noise at airports.

Also, the Boeing 747 has an 11rffi372) fuselage, but can only carry 500 people and about 30 tons of ffIf&. Also, four jet engines produce 5 aooo horsepower, which means that the power to raise 75 and 9 by 1 meter is 1 horsepower, which is 88,000 + 4,900-17, which means that the aircraft can ascend with 1/17 of the total power. In the 41st EIA, the center of gravity of the entire jet helicopter must be located below the left and right sides of the connecting body 12, even if the output is small, since there is no air resistance in the output of the horizontal advance engine 3. This is to have stability. Also, by increasing the distance between the ground 17 and the vertical jet engine ratio, the vertical jet engine ratio relative to the ground 11 can be increased. It is possible to reduce the impact of the injection.

[Brief explanation of drawings]

Figure 1 is a perspective view of the overall view of the first embodiment.B is a perspective view of the entire fuselage of the second embodiment.Figure 2A is a cross-sectional view of the first embodiment, and B is an aerial view of the same. Front view, C is a construction drawing of the first embodiment seen from the front, Figure 3A is a drawing showing the takeoff and ascent of the first embodiment, C1 is a flight above the stratosphere of the first and second embodiments. A drawing showing the route. FIG. 4A is a cross-sectional view of a helicopter-jet aircraft according to a second embodiment. B, Front view seen from Cji same as above, Figure 5A
B is a drawing showing the take-off route of the second embodiment, and B is a drawing showing the landing route. 5 Explanation of symbols 1 Vertical two on the nose side 24 Stratosphere 2
Ignition point 25 Noet helicopter 3 in landing position Horizontal forward engine 26
Flight path 4 while ascending Vertical stabilizer
27 Landing path 5 Vertical tail
28. Fuel chamber 6, dorsal fin
29. Horizontal rudder jet engine 7 lower fin
30. Inclined ascending route 8 Main +
31. Vertical rudder 9 Jet aircraft body 32. Tarumi rudder 10, jet helicopter 33, center of gravity line I1 seen from the side. jet helicopter engine 34
Connection of center of gravity line 12 and II seen from above
351 Vertical engine on tail side 13 people 14 cabin 158 Spring +6. Wheels +7. Ground level 18, jet helicopter ascending +9. Vertical, ascending path 20, jet airplane in deceleration attitude. ,'
-42z man 1, display of incident Showa era) 2nd license nth'
771fo No. 2, name of invention? L'"-1zu'rT
Temporary Entity 3 Relationship with the case of the person making the amendment Patent originator/button 4, Agent address (residence) Name $ 5, Date of amendment order (shipment date) 6, Request for amendment) ] Association JP Hirohito t'pQ Details Book 1 Name of the invention Vertical injection flying vehicle 2 Claims Jet engine for flying vehicles such as airplanes and helicopters.
A vertical injection flying vehicle characterized by being equipped with a vertical injection propulsion device such as a rocket. 3. Detailed Description of the Invention [Technical Field of the Invention] The present invention relates to a vertical jet aircraft such as a jet airplane, a helicopter, or a model airplane. [Prior art and its problems] Conventionally, for example, jet airplanes fly by obtaining thrust with a jet engine and lift with the main wings. In other words, it is the lift force acting on the wings that supports the weight of the airplane in the air. When an airplane moves through the air at a certain speed, wind equal to that speed hits its wings. This wind (air flow) increases in velocity when passing over the highly curved upper surface, and decreases in flow velocity when it passes through the less curved lower surface. According to Bernoulli's theorem, when the flow velocity increases, the pressure decreases, and when the flow velocity decreases, the pressure increases. This creates negative pressure on the upper surface of the wing, sucking it up, and positive pressure on the lower surface, pushing the wing upward, and both effects work together to produce upward lift. When an airplane is flying horizontally at a constant speed,
The lift of the wings is equally balanced by the weight of the aircraft. In order for the wings to generate lift, an airplane must move forward through the air at a certain speed. The amount of lift on a given wing is proportional to the square of its speed, and as the angle of attack of the wing relative to the airflow increases, the lift increases approximately proportionally. Airplanes fly horizontally with lift force equal to weight, so when flying fast the angle of attack is reduced, and when flying slowly the angle of attack is increased. In this way, when the angle of attack is increased, the lift increases approximately proportionally, but when the angle of attack exceeds a certain limit, the air flow on the upper surface of the wing separates from the surface and the air flow behind it becomes turbulent. If the angle of attack is exceeded, even if the angle of attack is increased further, the lift will actually decrease, and the turbulence will become more intense, making the wing's function worse. Even if the angle of attack is increased beyond the stall point, lift will not increase, so
At a speed below the stall angle of attack, that is, below the stall speed, it is no longer possible to generate enough lift to support the weight of the aircraft. In other words, stall speed is the minimum speed at which the aircraft can fly horizontally. In general, vehicles can run at any speed, but airplanes cannot fly below a minimum speed. Since the lift force is generated by the wings having an angle of attack, the main wings generate a relatively large air resistance. This air resistance limits the speed of conventional jet airplanes. Furthermore, although the air resistance is reduced in the stratosphere, it cannot be made extremely small, so there is a limit to speed even in the stratosphere. For this purpose, the power of jet engines has been increased to increase thrust, but this increase in power comes at the cost of a significant increase in the weight of the airplane. Furthermore, a helicopter that generates lift by its rotor cannot fly in the stratosphere, where the air is thin, because the lift becomes small. As described above, conventional flying vehicles have problems such as speed limitations due to air resistance and inability to fly in the stratosphere. Procedural amendment (procedural amendment) Paragraph 2 et al. Showa Me/2, February 23-3 To the Commissioner of the Patent Office, by JEE 6162'”2□-7,
Step 1, Display of the incident Showa Zc) Annual maintenance permit n*27?
(f; o No. 2, title of the invention A to color βte 1 year old) π bone body 3 Person making the amendment Relationship to the case Patent issuer 15-4, Agent address (residence) Name (name) $ 5. A passenger compartment 14 is provided, and wheels 16 are provided below the passenger compartment 14 via a spring 15. Furthermore, a connecting body 12 is installed horizontally at a corner of the combustion chamber 28, and jet engines 11 and 118 that inject downward are fixed to the ends of this connecting body 12. Therefore, when taking off from the ground 17, the jet engine 11 is fired to ascend. When the helicopter is to proceed, the output of the jet engine 11 on one side is increased, so that the jet helicopter body 10 can be tilted as shown in FIG. 8 to proceed in the direction n. Furthermore, if the propulsion device is a rocket and the gravitational force of the earth and the centrifugal force of the jet helicopter body 10 are balanced, it can fly like an artificial satellite. On the other hand, when landing, the output of the jet engine 11° 118 is reduced. Is this landing insect repellent? UM can be absorbed by the spring 15. In this second embodiment, the jet engine is 11°118
As shown in FIG. 9(a), jet engines 11 are installed at eight cylinder locations at the corners and intermediate parts of the jet helicopter main body 10, which has a square plane, through connecting bodies 12. As shown in FIG.
Alternatively, as shown in FIG. Further, as shown in Fig. 10, there is a jet helicopter main body 10 having a cylindrical shape with a pointed tip similar to a space shuttle or rocket on the upper and lower sides, and oxygen and hydrogen fuels on the upper and lower sides. In addition to arranging the chambers 28 and 28a,
The passenger compartment 14 is provided in multiple stages through the security space 36 in the middle part of the lower fuel chamber 28° 28a, and the jet helicopter main body 1
Jet engines 11 may be provided on six sides of 0 via connecting bodies 12. Incidentally, reference numeral 37 is a support leg similar to that of a conventional airplane that supports the wheels 16. FIG. 11 shows a seventh embodiment, in which the rocket body 41
A fixed wing 42 is provided at the rear end of the rocket body 41, and jet engines 43, 438 or rocket engines are installed at the front and rear sides of the rocket body 41, and their ignition points 44, 44a are set to moment I? It is located on one side of qII41a. Furthermore, a jet engine 45.45a or a rocket engine for thrusting is provided on both sides of the front of the center of the rocket body 41. Therefore, when taking off from the ground 17, the jet engine 43, 438 or the rocket engine can be fired to ascend, and the propulsion jet engine 45.45a or the rocket can be fired to move forward. Furthermore, the direction of travel is determined by the jet engines 43, 43a, 45, 45a, etc. Further, the jet engines 45, 45a or the rocket engines may be provided on both sides of the rear of the center of the rocket body 41, as shown by the dashed line. It should be noted that the present invention is not limited to the above-mentioned embodiments; for example, a jet airplane equipped with a conventional propulsion jet engine may be provided with a vertical injection rocket and a jet engine 11, or it may be used in a radio-controlled flying vehicle. Various variations of the tube are possible. [Effects of the Invention] The present invention provides vertical injection JI and slave devices such as jet engines and rockets immediately after the first flight of an F1 plane, a helicopter, etc., and enables open speed flight. 4. Brief description of the drawings Figures 1 to 5 show a first embodiment of the present invention, where Figure 1 is an overall perspective view, Figure 2 is a front view, and Figure 34 is a plan view. Fig. 3 (B) is a side view, Fig. 4 (5) is a front view showing the takeoff state, Fig. 4 (13) is a front view showing the landing state, and Fig. 5 is a front view showing the stratospheric flight state. , FIGS. 6 to 8 show a second embodiment of the present invention, in which FIG. 6 is an overall perspective view, FIG. 7 is a front view, and FIG. 8 (A) is a front view showing a takeoff state. Figure 8 is a front view showing the landing condition, Figure 9 is a front view showing the landing condition.
The figures show the third to fifth embodiments, the ninth doujin is a plan view of the third embodiment, FIG. 9(B) is a plan view of the fourth embodiment, and the ninth
Figures (Q is a plan view of the fifth embodiment, Figure 10 is a plan view of the sixth embodiment, Figure 10 is a vertical sectional view, Figure 10 is a plan view, Figure 11 is a plan view of the seventh embodiment). 11(A) is a plan view, and FIG. 11(B) is a front view.

Claims (1)

[Claims] A vertical injection jet airplane characterized in that an airplane or helicopter is equipped with a vertical injection rocket or a jet engine and takes off and lands vertically. Vertical jet or rocket engines that can be used in conventional airplane emergencies.