Fixed-wing aircraft capable of vertically taking off and landing

Abstract

The invention relates to the technical field of aircrafts, and particularly discloses a fixed wing aircraft capable of vertically taking off and landing, which comprises a fixed wing, a storage box fixedly connected to the bottom of the fixed wing, a plurality of supporting legs connected to the outer wall of the storage box, and a rotating mechanism used for changing the flight direction of the aircraft, the rotating mechanism is positioned on the fixed wing; the lubricating mechanism is used for lubricating the rotating mechanism, and the lubricating mechanism is located on the rotating mechanism; through the action of the rotating mechanism and the action of controlling the rotor motors to work by using the attitude sensors, the connecting plates can be driven to rotate according to the lift force difference generated by the rotor motors, so that the aircraft can fly in a horizontal or vertical state, and the aircraft can be changed in multiple directions in the air; and the flight modes of the aircraft are increased, so that the flight use effect of the aircraft is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a fixed-wing aircraft capable of vertical take-off and landing. Background Art

[0002] Fixed-wing aircraft, also known as fixed-wing airplanes, are heavier-than-air aircraft that fly in the atmosphere with wings fixed to the fuselage and generate lift through fixed wings. Fixed-wing aircraft use a power unit to generate forward thrust or pull, and the fixed wings of the fuselage generate lift. Its airframe structure usually consists of wings, fuselage, tail wing and landing gear. The engine nacelle of some aircraft is also part of the airframe structure. Fixed-wing aircraft can be divided into jet aircraft and propeller aircraft according to the type of engine.

[0003] Its main features are: fixed-wing aircraft have a faster flight speed, especially jet airliners, which can cruise at a speed of about 900 kilometers per hour; flight is not blocked by mountains, rivers, deserts, and oceans, and flight routes and flights can be adjusted at any time according to demand; they can carry large amounts of cargo or passengers for long-distance flights; at the same distance, fixed-wing aircraft are usually the fastest and most energy-efficient models.

[0004] Its application areas are: as the main air transport tool, it is used to carry passengers and cargo for long-distance, fast and convenient transportation; it is used for various military tasks such as reconnaissance, patrol, bombing, transportation, etc. For example, variable-sweep wing aircraft can meet the contradiction between high and low-speed performance requirements by changing the wing sweep angle, and is often used in multi-purpose fighters, fighter-bombers and strategic bombers; fixed-wing UAVs can be used for farmland plant protection operations, such as spraying pesticides and spreading fertilizers; it can be used for air quality monitoring, water quality monitoring, forest fire monitoring, etc.; it provides unique perspectives and materials for the media, and enhances the richness and viewing of news reports.

[0005] In a Chinese patent with publication number CN114771823A, a fixed-wing vertical take-off and landing aircraft is mentioned, including a fuselage, wings and doors, with a wing disposed on each side of the fuselage, and also including four sets of rotor modules and mounting frames, each of which includes a power column and a propeller; the mounting frame is fixed to the tail of the fuselage, including four tail wings, each of which is provided with a set of rotor modules; two tail wings extend toward the upper side of the fuselage, and the tail wings are opened upward in a V-shape; the other two rotor modules extend toward the lower side of the fuselage, and the tail wings are opened downward in a V-shape; the tail wings opened upward and the tail wings opened downward are symmetrically distributed on the upper and lower sides of the fuselage. The present invention forms a fuselage layout that is symmetrical along the upper and lower sides of the fuselage through four rotor modules, without the need for a runway, and the control system is adjusted after being in the air to achieve the change of flight attitude until it reaches a level flight state, and it has a simple structure, high reliability and good safety;

[0006] Compared with the above-mentioned documents, in the above-mentioned documents, although the fuselage layout is symmetrical along the upper and lower sides of the fuselage through four rotor modules, no runway is required, and the control system is adjusted after being in the air to realize the change of flight attitude until it reaches a level flight state. Its structure is simple, reliable and safe, but the above-mentioned aircraft cannot change the direction of multiple sets of rotors in the air, which makes the flight mode of the aircraft relatively single and reduces the flight effect of the aircraft. For this reason, a fixed-wing aircraft that can take off and land vertically is proposed. Summary of the invention

[0007] The purpose of the present invention is to provide a fixed-wing aircraft capable of vertical take-off and landing to solve the problems raised in the above-mentioned background technology.

[0008] To achieve the above object, the present invention provides the following technical solutions:

[0009] A fixed-wing aircraft capable of vertical take-off and landing comprises a fixed wing, a storage box is fixedly connected to the bottom of the fixed wing, a plurality of supporting legs are connected to the outer wall of the storage box, and further comprises:

[0010] A rotating mechanism, used to change the flight direction of the aircraft, wherein the rotating mechanism is located on the fixed wing;

[0011] The lubricating mechanism is used for lubricating the rotating mechanism, and the lubricating mechanism is located on the rotating mechanism.

[0012] Preferably, the rotating mechanism includes an attitude sensor arranged on the top of the fixed wing, and two mounting grooves are provided on the fixed wing, and a rotating shaft is rotatably connected between the two mounting grooves, and the outer wall of the rotating shaft is located inside the mounting groove and is fixedly connected with a rotating plate, and the top and bottom of the rotating plate both extend to the outside of the mounting groove, and the top and bottom of the rotating plate are fixedly connected with a connecting plate, and the end of the connecting plate away from the rotating plate is fixedly connected to a rotor motor, and the output end of the rotor motor is fixedly connected to a rotor blade, and a connecting rod is connected between the two connecting plates.

[0013] By setting the above technical solution, the attitude sensor is turned on, and the rotor motor drives the rotor blade above it to rotate, and the lift difference generated on both sides drives the rotating plate to rotate, and the attitude of the rotating plate and the fuselage is transmitted to the control system through the attitude sensor. The control system calculates and issues a control command to stabilize the fuselage state when the rotating plate rotates. When the control system calculates that the rotation angle is equal to degrees through the attitude sensor, the control system issues an instruction to limit and fix the rotating shaft and enter the level flight mode, and vice versa. It should be noted that: the attitude sensor controls the rotor motor to work, which is a prior art, and its working principle is not described in detail. Through the setting of this structure, the attitude sensor is used to control the rotor motor to work, and the connecting plate can be driven to rotate according to the lift difference generated by the rotor motor, so that the aircraft can fly in a horizontal or vertical state, and the aircraft can change multiple directions in the air, increasing the flight mode of the aircraft, thereby improving the flight use effect of the aircraft, and through the cooperation between the rotating plate and the connecting plate, the upper and lower sets of rotor motors are arranged as a whole, which increases the use intensity of the aircraft, reduces the overall structure of the aircraft, and facilitates the use of the aircraft.

[0014] Preferably, a rotation groove is formed on the inner wall of the installation groove, and the rotation shaft is rotatably connected to the installation groove via the rotation groove.

[0015] Preferably, the extension directions of the end connections of the rotating plate are arranged in opposite directions.

[0016] Preferably, the lubrication mechanism includes a plurality of storage chambers, a discharge port is opened at the bottom of the inner wall of the storage chamber, tension springs are fixedly connected to the bottom of the inner wall of the storage chamber on both sides of the discharge port, a sliding rod is fixedly connected between the two tension springs, a fitting magnetic plate is fixedly connected to the end of the sliding rod, an atomizing mesh plate is fixedly connected to the interior of the discharge port below the fitting magnetic plate, and a plurality of inlaid magnetic blocks are fixedly connected to the outer wall of the rotating shaft.

[0017] By setting the above technical solution, when the rotating shaft rotates, according to the effect that the discharge port extends to the outer wall of the rotating shaft, when the rotating shaft rotates, the embedded magnetic block on its outer wall can be driven to rotate. When the embedded magnetic block rotates to the position where the magnetic plate is fitted, according to the effect that the same poles of the two repel each other, the fitted magnetic plate slides toward the inside of the discharge port, so that the discharge port is opened, and the lubricating oil inside the storage chamber flows to the inside of the rotating groove through the atomizing mesh plate inside the discharge port to lubricate the outer wall of the rotating shaft. By setting this structure, when the rotating shaft rotates, the lubricating oil can automatically flow to the outer wall of the rotating groove to rotate and lubricate the outer wall of the rotating shaft, which correspondingly improves the rotation effect of the above-mentioned rotating mechanism, thereby further improving the user's change of direction of the aircraft and the effect of flight use;

[0018] By utilizing the effect of the atomizing screen, the amount of lubricating oil liquid flowing out is reduced, so that the lubricating oil flows into the inside of the rotating groove in the form of water droplets, effectively lubricating the outer wall of the rotating shaft, avoiding the accumulation of lubricating oil inside the rotating groove, thereby improving the lubricating effect of the lubricating oil on the outer wall of the rotating shaft.

[0019] Preferably, the bottom of the dosage outlet extends to the inside of the rotating groove and corresponds to the outer wall of the rotating shaft.

[0020] Preferably, the plurality of storage cavities are all opened on the inner wall of the mounting groove.

[0021] Preferably, the outer wall of the fitted magnetic plate and the inner wall of the discharge port are arranged to be slidingly fitted, and the fitted magnetic plate and the embedded magnetic block are arranged to have corresponding like poles that repel each other.

[0022] Preferably, both the fixing plate above the fixing wing and the connecting block below the fixing wing are provided with feed holes, and the feed holes extend to the interior of the agent storage cavity.

[0023] Preferably, the outer wall of the storage box is connected to a plurality of supporting legs.

[0024] A method for using a fixed-wing aircraft capable of vertical take-off and landing:

[0025] Step 1: Turn on the attitude sensor, and the rotor motor drives the rotor blade above it to rotate, and the lift difference generated on both sides drives the rotating plate to rotate, and transmits the attitude of the rotating plate and the fuselage to the control system through the attitude sensor. The control system calculates and issues control instructions to stabilize the fuselage state when the rotating plate rotates;

[0026] Step 2: When the rotating shaft rotates, the dosage outlet extends to the outer wall of the rotating shaft. When the rotating shaft rotates, the embedded magnetic blocks on its outer wall can be driven to rotate. When the embedded magnetic blocks rotate to the position of the fitted magnetic plate, the like poles of the two repel each other, so that the fitted magnetic plate slides toward the inside of the dosage outlet, thereby opening the dosage outlet.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] Through the action of the rotating mechanism and the use of the attitude sensor to control the operation of the rotor motor, the connecting plate can be driven to rotate according to the lift difference generated by the rotor motor, so that the aircraft can fly in a horizontal or vertical state, and the aircraft can make multiple direction changes in the air, which increases the flight modes of the aircraft and improves the flight effect of the aircraft. In addition, through the cooperation between the rotating plate and the connecting plate, the upper and lower sets of rotor motors are arranged as an integral whole, which increases the use intensity of the aircraft, reduces the overall structure of the aircraft, and facilitates the use of the aircraft.

[0029] Through the action of the lubricating mechanism, when the rotating shaft rotates, the lubricating oil can automatically flow to the outer wall of the rotating groove, and lubricate the outer wall of the rotating shaft, which correspondingly improves the rotation effect of the above-mentioned rotating mechanism, thereby further improving the user's direction change of the aircraft and the flight effect;

[0030] By utilizing the effect of the atomizing screen, the amount of lubricating oil liquid flowing out is reduced, so that the lubricating oil flows into the inside of the rotating groove in the form of water droplets, effectively lubricating the outer wall of the rotating shaft, avoiding the accumulation of lubricating oil inside the rotating groove, thereby improving the lubricating effect of the lubricating oil on the outer wall of the rotating shaft. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a structural diagram of the present invention;

[0032] Figure 2 It is a top view of the structure of the present invention;

[0033] Figure 3 It is a side structural diagram of the present invention;

[0034] Figure 4 It is a cross-sectional structural diagram of the mounting groove of the present invention;

[0035] Figure 5 For the present invention Figure 4 Enlarged structural diagram at location A.

[0036] In the figure: 1. Fixed wing; 2. Storage box; 3. Support leg; 4. Attitude sensor; 401. Mounting slot; 402. Rotating shaft; 403. Rotating plate; 404. Connecting plate; 405. Rotor motor; 406. Rotor blade; 5. Agent storage chamber; 501. Tension spring; 502. Sliding rod; 503. Agent outlet; 504. Fitting magnetic plate; 505. Atomizing mesh plate; 506. Inlaid magnetic block; 6. Connecting rod. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] Embodiment 1

[0039] like Figure 1-5As shown, a fixed-wing aircraft capable of vertical take-off and landing comprises a fixed wing 1, a storage box 2 is fixedly connected to the bottom of the fixed wing 1, a plurality of supporting legs 3 are connected to the outer wall of the storage box 2, and also comprises: a rotating mechanism for changing the flight direction of the aircraft, the rotating mechanism is located on the fixed wing 1, the rotating mechanism comprises an attitude sensor 4 arranged on the top of the fixed wing 1, two mounting grooves 401 are provided on the fixed wing 1, a rotating shaft 402 is rotatably connected between the two mounting grooves 401, the outer side wall of the rotating shaft 402 is located inside the mounting groove 401 and is fixedly connected to a rotating plate 403, and the top and bottom of the rotating plate 403 both extend to the outside of the mounting groove 401, the top and bottom of the rotating plate 403 are fixedly connected to a connecting plate 404, the end of the connecting plate 404 away from the rotating plate 403 is fixedly connected to a rotor motor 405, the output end of the rotor motor 405 is fixedly connected to a rotor blade 406, and a connecting rod 6 is connected between the two connecting plates 404;

[0040] The present invention further specifically describes that the inner wall of the installation groove 401 is provided with a rotation groove, the rotation shaft 402 is rotatably connected to the installation groove 401 through the rotation groove, and the extension direction of the connecting plate 404 at the end of the rotation plate 403 is opposite to that of the rotation plate 403;

[0041] As can be seen from the above, when the attitude sensor 4 is turned on, the rotor motor 405 drives the rotor blade 406 above it to rotate, and the lift difference generated on both sides drives the rotating plate 403 to rotate, and the rotating plate 403 and the fuselage attitude are transmitted to the control system through the attitude sensor 4, and the control system calculates and issues control instructions to stabilize the fuselage state when the rotating plate 403 rotates. When the control system calculates that the rotation angle is equal to 90 degrees through the attitude sensor 4, the control system issues an instruction to limit and fix the rotating shaft 402 and enter the level flight mode, and vice versa. It should be noted that: the attitude sensor 4 controls the rotor motor 405 to work, which is a prior art. The working principle is not described in detail. Through the setting of this structure, the attitude sensor 4 is used to control the operation of the rotor motor 405. The connecting plate 404 can be driven to rotate according to the lift difference generated by the rotor motor 405, so that the aircraft can fly in a horizontal or vertical state, and the aircraft can make multiple direction changes in the air, which increases the flight mode of the aircraft and improves the flight effect of the aircraft. Through the cooperation between the rotating plate 403 and the connecting plate 404, the upper and lower sets of rotor motors 405 are arranged as a whole, which increases the use intensity of the aircraft, reduces the overall structure of the aircraft, and facilitates the use of the aircraft.

[0042] Embodiment 2

[0043] like Figure 1-5As shown, a lubrication mechanism is additionally provided on the basis of the above-mentioned embodiment 1 for lubricating the rotating mechanism, the lubrication mechanism is located on the rotating mechanism, the lubrication mechanism includes a plurality of storage chambers 5, a discharge port 503 is provided at the bottom of the inner wall of the storage chamber 5, a tension spring 501 is fixedly connected to both sides of the discharge port 503 at the bottom of the inner wall of the storage chamber 5, a sliding rod 502 is fixedly connected between the two tension springs 501, a fitting magnetic plate 504 is fixedly connected to the end of the sliding rod 502, an atomizing mesh plate 505 is fixedly connected to the inside of the discharge port 503 below the fitting magnetic plate 504, and a plurality of inlaid magnetic blocks 506 are fixedly connected to the outer wall of the rotating shaft 402;

[0044] The present invention is further specifically described in detail, the bottom of the agent outlet 503 extends to the inside of the rotating groove and corresponds to the outer wall of the rotating shaft 402, multiple agent storage chambers 5 are opened on the inner wall of the mounting groove 401, the outer wall of the bonding magnetic plate 504 and the inner wall of the agent outlet 503 are slidingly bonded, the bonding magnetic plate 504 and the embedded magnetic block 506 are correspondingly arranged with the same polarity repelling each other, a drug inlet hole is opened on the fixed wing 1, and the drug inlet hole extends to the inside of the agent storage chamber 5, and the outer wall of the storage box 2 is connected to multiple support legs 3;

[0045] As can be seen from the above, when the rotating shaft 402 rotates, according to the effect that the outlet 503 extends to the outer wall of the rotating shaft 402, when the rotating shaft 402 rotates, the embedded magnetic block 506 on its outer wall can be driven to rotate. When the embedded magnetic block 506 rotates to the position of the attached magnetic plate 504, according to the effect of the same poles repelling each other, the attached magnetic plate 504 slides toward the inside of the outlet 503, so that the outlet 503 is opened, and the lubricating oil inside the storage chamber 5 flows to the inside of the rotating groove through the atomizing mesh plate 505 inside the outlet 503 to lubricate the outer wall of the rotating shaft 402. Through the setting of this structure, when the rotating shaft 402 rotates, the lubricating oil can automatically flow to the outer wall of the rotating groove to rotate and lubricate the outer wall of the rotating shaft 402, which correspondingly improves the rotation effect of the above-mentioned rotating mechanism, thereby further improving the user's change of direction of the aircraft and the flight use effect;

[0046] By utilizing the atomizing screen 505, the outflow content of the lubricating oil is reduced, so that the lubricating oil flows into the inside of the rotating groove in the form of water drops, effectively lubricating the outer wall of the rotating shaft 402, avoiding the accumulation of the lubricating oil inside the rotating groove, thereby improving the lubricating effect of the lubricating oil on the outer wall of the rotating shaft 402;

[0047] It should be noted that: through the function of the feed hole, lubricating oil can be added into the interior of the storage chamber 5 for use.

[0048] Furthermore, the present design application is applied to a fixed-wing aircraft. By adjusting the angle of the rotor motor 405 and the rotor blade 406, the aircraft can be flown in a horizontal or vertical state, and the aircraft can be turned in multiple directions in the air, thereby increasing the flight modes of the aircraft and improving the flight performance of the aircraft.

[0049] A method for using a fixed-wing aircraft capable of vertical take-off and landing:

[0050] Step 1: Turn on the attitude sensor 4, and the rotor motor 405 drives the rotor blade 406 above it to rotate, and the lift difference generated on both sides drives the rotating plate 403 to rotate, and the attitude of the rotating plate 403 and the fuselage is transmitted to the control system through the attitude sensor 4, and the control system calculates and issues control instructions to stabilize the fuselage state when the rotating plate 403 rotates;

[0051] Step 2: When the rotating shaft 402 rotates, the discharge port 503 extends to the outer wall of the rotating shaft 402. When the rotating shaft 402 rotates, the embedded magnetic block 506 on its outer wall can be driven to rotate. When the embedded magnetic block 506 rotates to the position of the bonding magnetic plate 504, the bonding magnetic plate 504 slides toward the inside of the discharge port 503 due to the effect of like poles repelling each other, so that the discharge port 503 is opened.

[0052] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electric welding connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0053] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0054] In the drawings of the embodiments disclosed in the present invention, only the structures related to the embodiments disclosed in the present invention are involved, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other.

[0055] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A fixed-wing aircraft capable of vertical take-off and landing, characterized in that: The invention comprises a fixed wing (1), the bottom of which is fixedly connected to a storage box (2), and further comprises: A rotating mechanism, used for changing the flight direction of the aircraft, wherein the rotating mechanism is located on the fixed wing (1); The lubricating mechanism is used for lubricating the rotating mechanism, and the lubricating mechanism is located on the rotating mechanism.

2. A fixed-wing aircraft capable of vertical take-off and landing according to claim 1, characterized in that: The rotating mechanism comprises an attitude sensor (4) arranged at the top of the fixed wing (1); two mounting grooves (401) are provided on the fixed wing (1); a rotating shaft (402) is rotatably connected between the two mounting grooves (401); an outer wall of the rotating shaft (402) is located inside the mounting groove (401) and is fixedly connected with a rotating plate (403); the top and bottom of the rotating plate (403) both extend to the outside of the mounting groove (401); the top and bottom of the rotating plate (403) are fixedly connected with a connecting plate (404); one end of the connecting plate (404) away from the rotating plate (403) is fixedly connected with a rotor motor (405); the output end of the rotor motor (405) is fixedly connected with a rotor blade (406); and a connecting rod (6) is connected between the two connecting plates (404).

3. A fixed-wing aircraft capable of vertical take-off and landing according to claim 2, characterized in that: The inner wall of the installation groove (401) is provided with a rotation groove, and the rotation shaft (402) is rotationally connected to the installation groove (401) via the rotation groove.

4. A fixed-wing aircraft capable of vertical take-off and landing according to claim 2, characterized in that: The extending directions of the connecting plate (404) at the end of the rotating plate (403) are opposite to each other.

5. The fixed-wing aircraft capable of vertical take-off and landing according to claim 3, characterized in that: The lubrication mechanism comprises a plurality of storage chambers (5), a discharge port (503) is provided at the bottom of the inner wall of the storage chamber (5), and a tension spring (501) is fixedly connected to the bottom of the inner wall of the storage chamber (5) on both sides of the discharge port (503), a sliding rod (502) is fixedly connected between the two tension springs (501), and the end of the sliding rod (502) is fixedly connected to a bonding magnetic plate (504), an atomizing mesh plate (505) is fixedly connected to the inside of the discharge port (503) below the bonding magnetic plate (504), and a plurality of inlaid magnetic blocks (506) are fixedly connected to the outer wall of the rotating shaft (402).

6. A fixed-wing aircraft capable of vertical take-off and landing according to claim 5, characterized in that: The bottom of the dosage outlet (503) extends to the inside of the rotating groove and corresponds to the outer wall of the rotating shaft (402).

7. The fixed-wing aircraft capable of vertical take-off and landing according to claim 5, characterized in that: The plurality of agent storage cavities (5) are all opened on the inner wall of the mounting groove (401).

8. The fixed-wing aircraft capable of vertical take-off and landing according to claim 5, characterized in that: The outer wall of the fitted magnetic plate (504) and the inner wall of the drug outlet (503) are arranged to be slidably fitted, and the fitted magnetic plate (504) and the embedded magnetic block (506) are arranged to have corresponding like poles that repel each other.

9. The fixed-wing aircraft capable of vertical take-off and landing according to claim 5, characterized in that: The fixed wing (1) is provided with a feed hole, and the feed hole extends to the interior of the storage chamber (5).

10. The fixed-wing aircraft capable of vertical take-off and landing according to claim 5, characterized in that: The outer wall of the storage box (2) is connected to a plurality of supporting legs (3).

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