Drone with folding wings

Abstract

Title of the invention: UAV with folding wings - Technical field: Aerospace, mechanics - Technical problem: All aircraft have safety, technical and environmental deficiencies for the development of the urban air transportation network as follows: 1- Fixed-wing aircraft require a lot of space for deployment, landing and take-off 2- Fixed-wing aircraft are unable to fly at a standstill and have maneuverability 3- Fixed-wing aircraft have a short flight time 4- Aircraft rely on a guidance and guidance system Providing a solution to solve existing problems: This hybrid invention, which consists of a fixed wing and a rotary wing, folds its fixed wings into the smallest possible space in terms of length and width in order to be able to deploy, land, and take off in a dense terrestrial environment. In order to maintain its maneuverability at every moment of the flight, it folds its fixed wings as quickly as possible during flight, in about two to three seconds. - How to work: At the highest part of the inventive device, two axes are located next to each other in the longitudinal direction of the device, and the fixed wings are connected to these axes for closing in the +z axis direction and for opening in the +y direction. At the tip of each fixed wing and the lower edge of each airfoil, a brushless motor with a propeller is arranged in such a way that the chord line of the propeller of the brushless motors is parallel to the chord line of the fixed wing airfoils, and the wings are moved using the thrust of the propeller electric motor installed on the wings and using the lever law resulting from the distance that the electric motor is from the wing axis. It spreads its wings as quickly as possible.

Description

Description of the invention Invention title [Drone with folding wings] Invention of technical field [This invention is related to fixed-wing and rotary-wing hybrid flight equipment whose fixed wings have the ability to retract during flight. Among the prominent features of this inventive device are "the ability to instantly change the angle of its fixed wings towards the +z and +-y axes in the direction of closing and opening simultaneously with the change of horizontal to vertical flight mode and vice versa, so that the entire process of closing the wings in the +z direction and opening the wings in the +-y direction in the fastest possible time takes two to three seconds during flight." and "the unique structure of the fixed wings is that it can be retracted in the smallest possible space in terms of length and width before landing. Features that make this hybrid inventive device find a structure compatible with the dense urban environment and facilitate the formation of an air transportation network.] Technical problem and statement of the objectives of the invention [Environmental pollutants, time wasted in traffic, road accidents, 88% of which are caused by human error and roads, are issues that drive humans towards air transportation in a comprehensive manner. However, all human innovations in this field, if mass-produced and faced with extensive air traffic, will reveal their safety, technical and environmental shortcomings, as fixed-wing and rotary-wing flight equipment are not designed to be compatible with the dense air transportation network. Among the technical problems of the aforementioned flight equipment are the following. Fixed-wing flight equipment 1. The dense urban fabric does not create the capacity to accommodate today's private aircraft, which require unconventional space for deployment, landing, and takeoff. 2. Modern aircraft have a flight environment that is tailored to their flight style. The stability of this aircraft is conditioned by forward motion at high speed, a flight style that conflicts with the expected performance, such as the expectation of stopping and changing direction within the minimum safe operating space in the face of aerial obstacles. 3. Aerial equipment that requires a wide airfield to change direction, which is incompatible with flying in dense environmental conditions with air traffic. 4. The performance weakness resulting from the specific flight style makes it difficult to utilize the autopilot flight system and artificial intelligence in the dense air transport network, which forms the basis for safe flight in this type of network. 5. The potential risk of an air accident resulting from reliance on a set of navigation and guidance devices that have no alternative for flight stability in the event of a technical failure in any of the components. Rotary wing flight equipment 1. Short flight time due to high energy consumption 2. Relatively low speed compared to airplanes 3. The potential risk of an air accident resulting from reliance on a set of navigation and guidance devices that have no alternative for flight stability in the event of a technical failure in any of the components. Therefore, it is not possible to imagine a day when air transportation, like land transportation, will be expanded to the general public with today's flight equipment and current conditions; therefore, the purpose of this invention is to form a systematic, coherent, and evolved structure whose fixed wings, in accordance with the dense urban environment, occupy the least space in terms of length and width before landing, and at the same time, by instantly changing the horizontal to vertical flight mode and vice versa, in the fastest possible time, in about 2 to 3 seconds, it changes the angle of its fixed wings according to the flight conditions, and opens or closes them. A structure that provides the necessary conditions for the formation of an air transportation network.] Description of the state of prior knowledge and history of developments related to the invention of air taxis 1. [One of the first known commercial examples in this field is the conventional helicopter. The conventional helicopter has one or more very large blades compared to other types of vertical flight, which allows for vertical landing and takeoff. In the case of horizontal flight, changing the angle of its main axis plate creates horizontal and forward force, making cruise flight possible. The cruise speed of this type of aircraft is much lower compared to the airplane type. This is the reason why helicopters are not generally popular for air taxi use. 2. Hexacopter or Octacopter, which will have the ability to land and take off vertically. In the case of horizontal movement, due to the absence of a blade mounting plate (similar to what is common in a conventional helicopter), the entire aircraft changes angle and enables forward movement. Due to the distribution of power by a larger number of blades compared to a helicopter (four, six or more), the diameter of the blades of this type of aircraft is much smaller than that of a similar helicopter. It should be noted that vertical flight is much more energy-efficient than horizontal flight, which has led to doubts about the use of quadcopters or similar devices in air taxi applications. Therefore, despite their apparent attractiveness, these types of aircraft have not conquered the air transportation market. And because this type of aircraft does not have wings or a horizontal propulsion system and always uses a flight structure, there is no replacement designed for them in the event of a technical failure and they are unable to maintain flight stability, which increases the likelihood of air accidents.While my invention has its own flight structure in each of the horizontal and vertical flight modes, and in the event of a technical failure, it is able to change its flight mode from horizontal to vertical and vice versa, maintaining its flight stability, and is more energy efficient. 3. Another concept proposed under the title of Tilt wing and Tilt rotor type flying devices, this type of flying devices operates in vertical flight and landing and take-off similar to helicopters, and in horizontal flight and cruise relying on the wing, they operate similar to turboprop aircraft. In the Tilt rotor type, the transition process between vertical landing and take-off as well as horizontal flight is carried out by changing the angle of its blades. The mechanism and mechanism created to provide a change in the angle of the rotating blades is very complex and expensive, and in the Tilt wing type, the entire wing undergoes a change in angle during the transition process. The mechanical complexity of this idea is greater than its new type (Tilt rotor). These flying devices are unable to change their flight direction from horizontal to vertical and vice versa when stationary, and they lose their maneuverability to a large extent when changing flight mode.Such a structure, when changing its flight mode, due to its lack of instantaneous maneuverability and consequently its inability to avoid collisions with obstacles, is unable to fly in an environment with a dense flight density and for this purpose it requires a wide and safe airfield. Another obstacle to these flying devices is the wings of these flying devices during landing and takeoff, which do not retract completely and occupy space in terms of length and width. Meanwhile, my invention is made in accordance with such an environment and is able to instantly change its flight mode from horizontal to vertical and vice versa in the least possible space, and in the fastest possible time. And in an environment with limited space, it retracts the wings before landing in a way that occupies the least space. 4. Other examples of vertical take-offs that are vertical to the ground when taking off, landing, and stopping in the air, such as the tail sitter, which cannot change its flight direction from horizontal to vertical and vice versa when stationary, and loses its maneuverability to a large extent when changing flight mode, and requires a wide and safe airfield to change direction. It cannot fly in dense environmental conditions with air traffic, and when changing flight mode from vertical to horizontal and vice versa, its body changes direction by 90 degrees, while the body of my invention remains fixed when changing flight mode from horizontal to vertical and vice versa; a feature that is suitable for the development of the air transport network.] Technical solution for forming an extensive air transport network [The formation of the air transport network is based on a coherent structure that is modeled on the systematic integration of two flight models (fixed wing like airplanes and rotary wing like quadcopters). An integration that, by utilizing the distinctive and distinctive features of the two designs, is able to remove obstacles facing the aviation industry, the descriptive details of which are as follows. 1. The structure of this inventive device is to be able to deploy, land and take off in a flight environment that has high density and does not have sufficient operating space for other fixed-wing aircraft. It is built in such a way that it is able to fold its fixed wings in the smallest possible space in terms of length and width before landing. For this purpose, in the highest part of the body and at the closest distance to the line of symmetry of the inventive device, two axes are located next to each other in the longitudinal direction of the device. Each of these wings, by connecting to these axes and taking advantage of the reversibility property inherent in the wings, is able to change its angle by 90 degrees in the direction of the +z axis and close its wings. In such a way that when the wings are closed, both wings are symmetrical to each other and parallel to each other. (Refer to the drawings) 2. Folding-wing drones are not able to change their flight direction from horizontal to vertical and vice versa in the shortest possible time and in a stationary state, and given that they lose their maneuverability when changing flight mode. For this purpose, they need a safe airfield without flight congestion. While this invented device, using unique equipment, is able to change its flight direction from horizontal to vertical and vice versa in a stationary state without the need for a low-density airfield, and at the same time, with an instant change in flight mode, it changes the angle of its fixed wings in the fastest possible time, about two to three seconds, according to the flight conditions, and opens or closes them.In order for the inventive device to open its wings as quickly as possible, a propeller-driven electric motor is arranged at the tip of each wing and the lower edge of each airfoil in such a way that the chord line of the propeller of the electric motor is parallel when it is aligned with the chord line of the airfoil of the folded wings, and the wings are moved using the thrust of the propeller-driven electric motor installed on the wing and the distance between the electric motor and the wing axis. It uses the law of leverage and moves the wings in the direction of the y-axis as quickly as possible and opens the wings and uses the reversibility property to close the wings.]. Explanation of shapes and maps [Figure 1: The overall structure of the drone, the details of its parts are explained below. 1. A shock absorber that neutralizes the force and vibration caused by the wings hitting each other when the wings are closed. 2. Brushless electric motor that provides the driving force to change the angle of the wing 3. Wing structure bracket 4. Airfoil 5. Wing movable axis 6. Wing central locking 7. Wing reversibility force 8. Protractor 9. Guidance System Processor 2, which consists of aircraft equipment. 10. Guidance system processor 1 (flight control), which consists of the drone equipment. 11. Speed ​​control of brushless motors of the wings 12.Brushless motor bracket, guidance system 1 13. Stabilizer 14. Carbon fiber structure 15. Guidance system propulsion motor 2 16. Body 2 power supply holder 17. Body 1 (cabin) 18. Brushless electric motors, guidance system 1 19. Shock absorber that neutralizes the force and vibration caused by the wings hitting the fuselage when the wings are deployed. 20. The fixed axis of the wings 21. Wing central locking relay 22. Landing pads Map No. 2: The components that make up the wing, the details of which are explained as follows: 1. Connecting the distance sensor 2. Guidance system processor 1, which consists of quadcopter equipment. 3. Wing central locking to stabilize the wing angle 4. The fixed axis of the wings 5. Carbon fiber wing stabilizer 6. Wing bracket and guide rails 7. Wing drive electric motor bracket 8. Speed ​​control of brushless motors 9. Wing pivot 10. Vibration absorber caused by the wings hitting the body when the wings are opened. 11. Airfoil 12. Brushless electric motor that provides the driving force to change the angle of the wing. 13. Airfoil bracket 14. Carbon fiber flight stabilizer in the direction of the pitch axis 15. Guidance System Processor 2, which consists of aircraft equipment. 16. Wing reversibility actuator 17. Guidance tools 18. Servo motor 19. Vibration absorber caused by the wings colliding with each other when the wings are closed. Map No. 3: Coverage of technical defects of guidance system 1 as follows 1.Flight by guidance system 1 consisting of quadcopter equipment 2. Guidance System 2 standby consisting of aircraft equipment to immediately cover the technical failure of Guidance System 1 during flight. Map No. 4: Coverage of the technical defect of guidance system 2 as follows 1.Flight by means of a guidance system 2 consisting of aircraft equipment 2. Guidance System 1 standby consisting of quadcopter equipment to immediately cover the technical failure of Guidance System 2 during flight. Map No. 5: Coverage of technical defects of guided missiles as follows 1. Flight guidance in the direction of the Roll axis by the wing flaps 2. Be ready to drive the motors to change the angle of the wings after the wings are locked to cover the immediate technical failure of the wing struts. Advantages of the invention over previous inventions in the field of drones with folding wings 1. [Unlike other folding-wing drones that are unable to fully close their wings during flight and fly and land and take off in a space-limited environment, the fixed wings of this inventive device are designed to fly and land in a space-limited environment, and are designed to occupy the least amount of space in terms of length and width after being folded during flight. 2. Another advantage of this inventive device over other folding-wing drones that are unable to change their flight direction from horizontal to vertical and vice versa in the shortest possible time and at rest, and require sufficient airspace to change their flight mode while moving forward and in a specific curve. This inventive device is capable of instantly changing the flight direction from horizontal to vertical and vice versa in the smallest possible space, and in the fastest possible time, in about two to three seconds, changing the angle of its fixed wings according to the flight conditions, and opening or closing them. 3. One of the weaknesses of other folding high-wing drones is that they lose their maneuverability when changing flight modes. Considering that the change of flight mode from vertical to horizontal and vice versa occurs during forward movement, it must have a safe maneuverable space without flight congestion for this purpose. While this inventive device maintains its maneuverability in any mode while instantly changing the horizontal to vertical flight mode and vice versa. 4. Unlike other folding wing flight inventions, this invention, due to its two separate flight systems consisting of quadcopter equipment and aircraft equipment in a single set, is able to place the other system in standby mode to cover technical defects while one system is in operational mode. Multi-faceted equipment that complements each other in increasing flight safety and stability. (Refer to map no. 3, 4 and 5) 5. The driving force that other folding-wing drones use to change the angle of the wings is inside the fuselage, which requires high power and potential due to the proximity of the wing angle changing motor to the wing axis, in accordance with the law of leverage. As a result, folding-wing aircraft use large-sized motors to provide sufficient power, which has a significant effect on increasing the weight of the flight equipment. While a drone with folding wings uses the law of leverage to achieve the lowest weight and energy and the highest efficiency and speed while moving the wings. For this purpose, a brushless motor with a propeller is attached to the tip of each wing and the lower edge of each airfoil. Using the thrust of the aforementioned motor and the distance between the brushless motor and the wing axis, it moves the wings in the direction of the y + - axis as quickly as possible and opens the wings. The wings use the reversibility property to close, which closes in the direction of the z + axis. 6. In most folding-wing drones, the drone body changes angle by 90 degrees as the flight mode changes. While the body of a drone with folding wings remains fixed when changing from horizontal to vertical flight mode, a feature that is suitable for the development of the air transport network.] Implementation method for applying the invention [If the invented device is built in large models to be used for air transportation, it should be installed on the roofs of buildings for landing and takeoff, and in order to fly safely and prevent mid-air collisions, all relevant equipment should fly in a coherent network from the beginning to the end of the route, in a curved manner and around an axis, in a specific direction.] Applications of the invention [In business fields] 1. Flying cars 2. Research 3. Mapping 4. Filming In military fields 1. Marine drones can be used on ships, vessels, and oil platforms. 2. Ability to be used in warships 3. Surveillance: By utilizing the multi-modal guidance equipment of this invention, whose guidance systems have contrasting functions in terms of flight continuity and facial vibrations and operate in accordance with the requirements of the environment and location, this structure is capable of navigating long distances and spying on specific points.]

Claims

Complaint [Claim No. 1: What is claimed is the invention of a hybrid flying device consisting of two long folding wings, which are located at the highest part of the body and at the closest distance to the line of symmetry of the inventive device, two axes in the longitudinal direction of the device, side by side, which establish the connection between the roots of the wings and the body, and the wings are closed in the z+ angle direction by connecting to these axes and are opened in the y angle direction in such a way that when the wings are closed, both wings and are parallel to each other and when they are opened, they are in the same direction. And at the tip of each wing and the lower surface of each airfoil, an electric motor with a propeller is placed to create wing torque]

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