JP6027939B2 - airplane - Google Patents

Description

  The present invention relates to an airplane capable of safely performing low-speed flight.

  The present inventor previously provided a canard type airplane that can fly stably even at low speed (see Patent Document 1). The present invention is an improvement of this type of airplane.

JP 2010-76670 A

Conventional airplanes stall and become unstable when flying at low speeds. Also, it is vulnerable to crosswinds and taking off and landing under strong winds is dangerous. In order to solve the above problems, an object of the present invention is to provide the following airplane.
(1) Use small wings necessary for cruise flight and enable low-speed flight.
(2) Not affected by crosswinds even at low speeds.

  The following configurations are means for solving the above-described problems.

<Configuration 1>
An airplane that includes the following components:
(A) The sub-body is arranged in parallel on both sides of the main body.
(B) A front wing and a tail wing having a center fixed to the main body and both ends fixed to the sub-body are provided.
(C) A main wing having a central portion fixed to the main body and an intermediate portion fixed to the sub-body is provided.
(D) Said wing | blade has an area which generate | occur | produces the lift according to the wing | blade surface load in cruise speed.
(E) A total of two pairs of propellers with the rotation axis in the longitudinal direction of the wing are provided at the front end and the rear end of the above-mentioned sub fuselages, and the wings are penetrated at both ends of the front wing and the tail wing. A total of two pairs of propellers with rotating shafts are provided.
(F) A control device is provided for rotating and propagating each propeller as described above for direction change and attitude control during flight.
(G) A pair of rotor blades having a rotation axis directed in a direction perpendicular to both the auxiliary bodies and the blades are provided at the center of the two auxiliary bodies .
(H) The two wings or a pair of the propellers having a rotation axis directed in the direction penetrating the wings and the wings assist the lift of the wings that are insufficient when sliding and taking off and landing. Generate vertical lift.

<Configuration 2>
The configuration 1 is characterized in that a control device is provided for controlling the aircraft to turn in the target traveling direction by independently rotating and driving the total of four pairs of the direction changing and attitude control propellers. airplane.

<Configuration 3>
A tilt sensor for detecting the tilt of the fuselage is provided, and a control device for controlling the tilt of the fuselage by correcting the tilt of the fuselage by independently driving a total of four pairs of the direction changing and attitude control propellers. The airplane according to Configuration 1 or 2, which is characterized.

<Configuration 4>
Airplane according to the diverting and together with attitude control propellers, their respective one of configurations 1 to 3, characterized in that a compressed air jet port oriented in the direction of the rotating shaft.

<Effect of Configuration 1>
(1) Since a vertical levitation propeller is used, the wings can be made smaller overall, and air resistance can be reduced during flight at cruising speed. Therefore, high speed flight is possible. In addition, a wing structure suitable for low-speed flight can be adopted by connecting the front wing and the tail wing with the sub fuselage.
(2) The attitude control propeller can take off and land without being affected by crosswinds even during low-speed flight.
(3) Take off and landing with a short run distance by the vertical levitation propeller.
<Effect of Configuration 2>
It makes vertical flying easier.
<Effect of Configuration 3>
The course of the airplane can be corrected by the compressed air.
<Effect of Configuration 4>
The propeller for attitude control can be rotated to control the traveling direction of the aircraft, and the aircraft can go straight or change direction.
<Effect of Configuration 5>
By rotating the vertical levitation propeller, the inclination of the aircraft can be corrected and the aircraft can fly stably.

FIG. 1 is a perspective view showing an airplane according to the first embodiment. (A) is a top view of an airplane, (b) is a side view, (c) is a front view. It is a block diagram which shows the relationship between a propeller and a control apparatus.

  Hereinafter, embodiments of the present invention will be described in detail for each example.

FIG. 1 is a perspective view showing an airplane according to the first embodiment, FIG. 2A is a plan view of the airplane, FIG. 1B is a side view, and FIG. FIG. 3 is a block diagram showing the relationship between the propeller and the control device.
As shown in the figure, sub-body 12 is arranged in parallel on both sides of main body 11. A front wing 13 and a tail wing 15 having a center fixed to the main body 11 and both ends fixed to the sub-body 12 are provided. A main wing 14 having a center fixed to the main body 11 and an intermediate portion fixed to the sub-body 12 is provided. Two pairs of attitude control propellers 18 are provided at the front end portion 20 and the rear end portion 22 of both sub-bodies 12 with the rotation axis directed in the longitudinal direction of the blade. At both ends of the front wing 13 and the tail wing 15, a total of two pairs of vertical levitation propellers 16 with the rotation axes directed in the direction penetrating the wing are provided.

  Further, in this embodiment, a rotary blade 17 having a rotation axis directed in a direction perpendicular to both the sub fuselage 12 and the blades is provided at the center of both the sub fuselages 12. In addition, you may provide the compressed air jet nozzle 26 in the front-end part 20 or the rear-end part 22 of both the subbody 12. The rotor blade 17 is a rectangular propeller and is preferably a thin one so as not to increase air resistance during flight. Further, the front wing 13 and the tail wing 15 have the same wing thickness as a whole, and are thin, so the thickness is not shown in the drawing.

  The airplane of the present invention enables safe low speed flight. When flying at low speed, the conventional model will stall and become unstable. The form of the airplane of the present invention is provided with the sub fuselage 12 on both sides of the main fuselage 11 and provided with the front wing 13, the main wing 14 and the tail wing 15 like a canard type. The tail 15 has a role as a stabilizer. These three wings are fixed to the main body 11 and the sub-body 12. This increases the overall rigidity. The propeller (fan) 16 directed to the horizontal direction and the vertical direction provided on the front end portion 20 and the rear end portion 22 of the sub-body 12 is driven. If air flows downward during take-off and landing, lift is generated, and the burden on the wing is reduced accordingly, allowing low-speed flight.

  Moreover, the propeller 18 attached perpendicularly is turned with respect to the crosswind to respond to the crosswind. In order to ensure safety at low speeds, for example, a tilt sensor 30 is provided in the airframe. When tilted to one side, this is detected by the sensor, and the control device 28 can drive one of the propellers 16 to return to the original posture and measure the stability. Also, if the propeller 18 mounted vertically is driven by the control device 28 during the flight, the direction can be changed while maintaining the horizontal flight without losing the altitude without operating the auxiliary wing.

  Further, in the case of crosswind landing, if the control device 28 drives the front and rear propellers 18 to blow out the wind in the lateral direction, the landing can be made without departing from the landing course. Further, if the pair of propellers 18 installed vertically at the front end and the pair of vertical propellers 18 installed at the rear end are operated in opposite directions, the direction of the airframe can be changed at a steep angle while keeping the horizontal state.

  In addition to the method of increasing the lift force and changing the direction by the propeller (fan) 18, there is a method of using compressed air. Compressed air is ejected from the front end or the rear end of the sub-body 12 and the direction change effect similar to that of the propeller can be obtained by utilizing the action of the reaction.

  When the lift by the propeller 16 mounted horizontally at the four corners is small, the load of the fixed blade is reduced by the lift of the rotary blade 17 by adding the lift by the left and right rotary blades 17 provided on the sub-body 12. , Can make low speed flight possible. The vertical levitation propeller 16 and the rotor blade 17 are not capable of vertical takeoff and landing. When it is used for vertical takeoff and landing, the size and output are large, and the fuel consumption is large, which is uneconomical. An auxiliary device that generates lift in the vertical direction may be used. Simply generating lift in the vertical direction during takeoff and landing has the remarkable effect of shortening the running distance.

  An airplane with a secondary fuselage 12 like this model uses the secondary fuselage 12 as the main fuel tank, and if the main fuselage 11 is not loaded with fuel, in the unlikely event that it does not catch fire from the fuselage, safety Can be increased.

  Since the cylindrical sub-body 12 can be used as a pressure-resistant fuel tank, liquefied gas (such as propane gas) can also be used, and fuel options can be increased.

  If the speed of the airplane increases as it is now, if the area of the wing is determined according to the cruise speed, the wing will be too small at the time of takeoff and landing, and the lift will be insufficient. Increasing the takeoff and landing speed to increase lift increases the danger and makes it unusable.

  On the other hand, if the wing area is adjusted to a safe speed at take-off and landing, the wing is too large during cruise flight, resulting in increased air resistance and economical operation. Therefore, a wing high lift device is generally used. This is a method of operating at a safe speed by using a flow of air to generate high lift using the air flow. This method is very effective and is currently widely used.

  However, today's airplane refusal has become very long and expensive. Therefore, this aircraft was developed to obtain a safe flight speed during take-off and landing with a small wing with a high wing surface load that matches the cruise speed.

  As shown in FIG. 2, the airplane of the present invention is characterized in that a front wing 13, a main wing 14, and a tail wing 15 are fixed and integrated with a main fuselage 11 and two sub-fusels 12. Propellers (fans) 16 are attached to both ends of the front wing 13 and the tail wing 15 and are operated by a motor. The four motors are independently driven and controlled to control the attitude of the airplane.

  Normally, it can be controlled at a fixed number of revolutions to obtain buoyancy without breaking the left / right / front / rear balance, thus ensuring stable flight. In addition, when the attitude of the fuselage collapses aerodynamically due to some force, the tilt sensor 30 detects this and adjusts the driving force of each motor to keep the fuselage horizontal and perform stable safe operation. I can do it.

  Further, since the lift is increased by operating the two rotor blades 17 on the auxiliary body 12, low-speed flight is possible, and the take-off and landing distance can be shortened. Further, the propeller 18 vertically attached to the front and rear of the sub fuselage 12 of the airplane can cope with direction change and crosswind.

  For example, the direction of flight can be changed by driving the propeller 18 mounted either vertically on the front or rear in the same direction without using an auxiliary wing or rudder. In the case of crosswind landing, if the vertical propellers 18 at four locations are driven toward the wind, landing can be performed without being swept sideways.

  As mentioned above, the structure and system of this aircraft can make a low-speed flight safely by generating lift using propellers and rotor blades 17 when the airplane becomes slow and flight cannot be maintained only by wing lift. it can.

The advantages of the above plane can be summarized as follows.
1. If lift is generated by operating four propellers 16 mounted horizontally and a rotary wing 17 attached to the sub-body 12, the burden on the wings is reduced, so that low-speed flight is possible and safety is increased.
2. The direction can be changed without using the auxiliary wings by operating the propeller 18 installed in the four front and rear wings mounted vertically.
3 Propellers 16 and 18 mounted near both ends of the front wing 13 and the tail wing 15 are each independently driven to rotate by a driving device that receives the output signal of the attitude sensor of the aircraft, and holds the aircraft horizontally. Therefore, stability and safety during low-speed flight can be measured.
4 Propellers 18 installed vertically at four front and rear positions can prevent the aircraft from being swept away by crosswinds during takeoff and landing.
5 Strength and rigidity can be increased by connecting the main body 11 and the sub-body 12 to each wing.
6 If the sub-body 12 is formed in a cylindrical shape, a pressure-resistant structure can be obtained, so that liquefied gas (for example, propane gas) or the like can be used, and options for fuel can be increased. Also, less carbon dioxide is generated.
7 If the auxiliary fuselage 12 is used as a fuel tank and no fuel is loaded on the fuselage and the fuselage, the fuselage will not burn in the unlikely event that the aircraft will be highly safe.
8 If the rotor 17 of the sub fuselage 12 is operated, the take-off and landing distance can be shortened, so that the airplane can be operated even in a small airport.
9 Since this aircraft can take off and land at a steep angle and at a low speed, it can fly near the airport at high altitude and approach and land at a steep angle, so the noise area around the airport can be reduced.
10 This machine is low speed and has a short running distance, so tire consumption can be reduced.
In the event that 110,000 accidentally arrives, the fuel tank will be cut off immediately and away from the body on which the person is riding to increase safety.

DESCRIPTION OF SYMBOLS 11 Main fuselage 12 Sub fuselage 13 Front wing 14 Main wing 15 Tail wing 16 Vertical levitation propeller 17 Rotary wing 18 Attitude control propeller 20 Front end 22 Rear end 24 Engine 26 Compressed air outlet 28 Control device 30 Inclination sensor

Claims (4)

An airplane that includes the following components:
(A) The sub-body is arranged in parallel on both sides of the main body.
(B) A front wing and a tail wing having a center fixed to the main body and both ends fixed to the sub-body are provided.
(C) A main wing having a central portion fixed to the main body and an intermediate portion fixed to the sub-body is provided.
(D) Said wing | blade has an area which generate | occur | produces the lift according to the wing | blade surface load in cruise speed.
(E) A total of two pairs of propellers with the rotation axis in the longitudinal direction of the wing are provided at the front end and the rear end of the above-mentioned sub fuselages, and the wings are penetrated at both ends of the front wing and the tail wing. A total of two pairs of propellers with rotating shafts are provided.
(F) A control device is provided for rotating and propagating each propeller as described above for direction change and attitude control during flight.
(G) A pair of rotor blades having a rotation axis directed in a direction perpendicular to both the auxiliary bodies and the blades are provided at the center of the two auxiliary bodies .
(H) The two wings or a pair of the propellers having a rotation axis directed in the direction penetrating the wings and the wings assist the lift of the wings that are insufficient when sliding and taking off and landing. Generate vertical lift. 2. The control device according to claim 1, further comprising: a control device that controls the direction change and posture control propellers to rotate independently of each other so as to direct the aircraft in a target traveling direction. Airplane. A tilt sensor for detecting the tilt of the fuselage is provided, and a control device for controlling the tilt of the fuselage by correcting the tilt of the fuselage by independently driving a total of four pairs of the direction changing and attitude control propellers. The airplane according to claim 1 or 2, characterized by the above-mentioned. Airplane according to the diverting and together with attitude control propellers, their respective any one of claims 1 to 3, characterized in that a compressed air jet port oriented in the direction of the rotating shaft.

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