CN110723283A

CN110723283A - Aircraft with airfoil

Info

Publication number: CN110723283A
Application number: CN201911092534.0A
Authority: CN
Inventors: 叶茂胜
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-11-11
Filing date: 2019-11-11
Publication date: 2020-01-24

Abstract

The invention is characterized in that a set of kite-like wing surfaces capable of being folded and unfolded is arranged on an aircraft, so that the wing surfaces can be unfolded or stored according to the requirements in flight, the air flow can be better utilized for flying, and the thrust direction of a rotor wing (propeller) component can be controlled through a rotor wing steering engine.

Description

Aircraft with airfoil

Technical Field

The invention relates to an aircraft, in particular to an aircraft with an airfoil.

Background

In order to keep the helicopter such as a multi-rotor unmanned aerial vehicle flying in the air, the lift force can be provided only by driving the rotor to rotate, the energy consumption is very high, and if the helicopter can utilize the airflow lift force like a kite in the air, the helicopter can be kept to be suspended in the air only by consuming little energy. The invention is to install a set of kite-like wing surfaces capable of being folded and unfolded on an aircraft, so that the wing surfaces can be unfolded when needed in flight, air flow can be better utilized, the endurance time is prolonged, the energy consumption is saved, and the risk of crash can be reduced.

Disclosure of Invention

The invention relates to a manned or unmanned aircraft with an airfoil.

The technical scheme adopted by the invention comprises the following components: a multi-rotor (prop) craft or helicopter body; winged or kite-like airfoils (hereinafter referred to as airfoils); an airfoil deployment and stow or fold assembly; a mechanism (hereinafter referred to as a rotor steering engine) which can rotate the rotor (propeller) assembly by a certain angle to change the thrust direction.

The scheme is mainly characterized in that:

1. the aircraft is provided with wing surfaces which can be made of any appropriate material and shape, so that the aircraft can take off and land vertically, can fly like a common parachute-wing aircraft or a fixed-wing aircraft and can also take off and land in a sliding mode.

2. According to the demand, can select to adopt the airfoil to accomodate, expand or folding assembly, steerable airfoil is accomodate or expand when needs, can reduce the windage when accomodating, promotes the anti-wind ability, increases hover stability to improve vertical take-off and landing speed, and the airfoil can utilize the air current to provide lift for the aircraft when expanding, can realize the landing of leaping, improves the speed of flat flight, the energy can be saved, this receive and release process even can also realize at the flight in-process.

3. According to the demand, the rotor steering engine can be selected, the angle formed by the rotor (propeller) component and the fuselage is controlled through the rotor steering engine, the fuselage is supposed to be parallel to the ground, the rotor steering engine is controlled to enable the rotor (propeller) component to be vertical to the fuselage upwards, and the rotor (propeller) component can also be forward in the same direction as the fuselage or rotate to other required angles, so that the thrust direction is changed.

4. According to the requirements, the folding and unfolding components of the airfoil surface and the airfoil surface can be designed to be detachable, so that the aircraft can fly even if the folding and unfolding components of the airfoil surface and the airfoil surface are not installed.

In view of the above-mentioned features, some design examples will be shown in the following, but the scope of the present invention is not limited to the following examples, and the same numbered parts in all examples have substantially similar functions even though they may be different in shape and form.

Design example one:

fig. 1 is a left-right layout double-reel airfoil aircraft, which is composed of an aircraft body 1, a rotor arm 2, a rotor steering engine 3 located at the end of the outer side of the rotor arm, a rotor (propeller) component 4, a wheel type undercarriage 5, a left airfoil 11, a right airfoil 11, double reels 12 capable of controlling the storage and unfolding of the airfoils, reel synchronizing gears 13, a wing traction belt 14, a belt wheel carrier 15 located at the outer end of the rotor arm, and a motor 16 for providing power for the double reels. The airfoil is shown in the deployed position with the rotor (propeller) assembly oriented vertically up the fuselage and thrust down. The double-reel is responsible for the expansion and the storage of the left and right wing surfaces, and the axis of the reel is the same as the front and back direction of the machine body. Wherein the double-reel and the reel synchronizing gear are coaxial and rotate together, the two reels can be restrained by the mutually meshed synchronizing gears to rotate in the mirror image direction, the rotation of the reels can drive the belt to rotate around the reels and the belt pulley together, and the belt is connected with the airfoil, so that the airfoil is also dragged to be wound and unwound around the reels. The rotor steering engine 3 can control the rotor (propeller) component 4 to rotate a certain angle. The wheeled landing gear facilitates vertical or jump take-off and landing of the aircraft.

Fig. 2 shows the state in which the airfoil 11 of the aircraft is stowed by the reel 12.

FIG. 3 shows the aircraft with the entire spool airfoil receiving assembly removed and still flying under the control of 4 rotors.

Fig. 4 is a detail of the belt wheel frame 15 at the outer end of the rotor arm 2, the belt 14 is combined with the wing surface 11, and the wing surface can be driven to retract by the rotation of the belt around the belt wheel frame.

Fig. 5 shows that the rotor (propeller) assembly 4 is turned to the same angle as the forward direction of the fuselage under the control of the rotor steering engine 3, and the view angle shown in the figure is the left side of the fuselage. At the moment, the thrust generated by the rotor wing (propeller) assembly faces backwards, and the rotor wing can fly horizontally by virtue of the lift force of the wing surface. The rotor (or propeller) assembly may be steered either perpendicularly to the fuselage as shown in fig. 1 or at other angles.

Design example two:

FIG. 6 is an aircraft using a single spool to deploy airfoils in a fore-aft direction, which is less balanced than example one, but at a lower cost.

Design example three:

fig. 7 shows an aircraft with two transverse reels and front and rear elongated airfoils, which is different from the first embodiment in that the two transverse reels are provided with 4 belt wheel carriers 15 respectively installed on the front and rear sides of the rotor arms and elongated forward and rearward to increase the front and rear distances of the pulleys, thereby increasing the lengths of the front and rear airfoils and the area of the entire airfoil, and the rest of the present embodiment is substantially the same as the first embodiment.

Design example four:

fig. 8 shows a foldable double-reel delta wing aircraft, the double reel 12 is connected with a synchronous gear 13 at the front end and fixed on the front arm 17 of the aircraft, the double reel pulls the delta wing 11 to unfold when being unfolded, and the wing is collected when being folded, the lower part of the reel is provided with a slide rail 121, the unfolding and folding of the reel are driven by the sliding of a slide block on a belt 14 in the slide rail, which will be detailed in fig. 12.

Figure 9 shows the two-spool embodiment folded with the delta wing stowed and the belt 14 and belt pulley 151 at the outer end of the rotor arm visible.

Figure 10 shows rotor (propeller) assembly 4 turning to the front of the aircraft under the control of rotor steering engine 3, so that the thrust is backward and the rotor steering engine can also control the rotor (propeller) assembly to turn to other angles, and the thrust direction changes accordingly.

Fig. 11 is an enlarged view showing the synchronizing gears 13 at the front ends of the two reels, which are engaged with each other to restrain the two reels from being opened and folded at both sides at the same angle. It should be noted that the synchronizing gear 13 in this example is different from the synchronizing gear 13 in the first three examples, in which the scrolling that restricts the two reels is synchronized, and in this example, the angle at which the two reels are restricted to open and close is the same.

Fig. 12 shows the pulley set and the block 141 for folding the reel, seen from above, after the reel and the wing are hidden, the belt driving wheel 161 drives the belt 14 which passes around the belt pulley 151 at the other end of the rotor arm 2 to rotate, and the block 141 is fixed on the belt, the belt rotating around the two wheels drives the block to move along the belt, and the block also slides in the slide rail 121 below the reel shown in fig. 8, and the belt drives the block to slide in the slide rail to push the reel to open and fold.

Claims

1. An aircraft with an airfoil, characterized in that: the aircraft comprises an aircraft body, a wing surface retraction assembly and a mechanism for controlling and changing the thrust direction of a rotor wing (propeller) assembly.

2. An aircraft with an airfoil according to claim 1 wherein: the wing surface can be stored, folded or unfolded through the wing surface folding and unfolding assembly, and the folding and unfolding process can be realized even in the flying process.

3. An aircraft with an airfoil according to claim 1 wherein: the wing surface and the wing surface retraction assembly can be detached, and the aircraft can still fly even if the wing surface and the wing surface retraction assembly are detached.

4. An aircraft with an airfoil according to claim 1 wherein: the mechanism with steerable rotor (screw) subassembly thrust direction can change the angle of rotor (screw) subassembly and fuselage, and then the thrust direction of adjustment rotor (screw) subassembly.