TWM507291U - Positioning system for landing of propeller flying vehicle - Google Patents

Description

Propeller aircraft landing positioning system

The present invention relates to an aircraft landing positioning system, and more particularly to a propeller aircraft landing positioning system with fixed-point guided landing and immediate charging operation.

According to the aircraft, the remote control flight activity is a modern and emerging leisure entertainment. There are many groups and alliances that love this activity. There are also related performances and competitions. The aircraft remote control flight can be used in conjunction with photography and photographic equipment. The effect of the survey. The traditional remote-controlled aircraft uses a helicopter as the main body of the structure. Its forward and backward movements are controlled by the inclination (tilt) of the main propeller, while the newer multi-axis aircraft relies on multiple propellers to achieve the required lift and The rotation speed of each propeller (such as the difference in rotational speed) is used for direction control, and its flight is stable, and the control mechanism that needs to set the inclination angle of each propeller as in the case of the traditional helicopter to move in a spiral tilt angle can be dispensed with, and the economic upgrade economy is not greatly increased. Cost.

Conventional Multi-Axis (Multi-Propeller) Aircraft Structure and Control Architecture As shown in Figures 1 and 2, the multi-axis (multi-propeller) aircraft 90 is a four-axis aircraft comprising a main frame base 91 and the main frame mount 91 extends from the four frame 92, the frame 92 is provided with a motor 93 (such as a brushless motor) and a propeller 94 driven by the motor 93. The main frame holder 91 is provided with a battery 95 and a flight controller. 96 and an electronic transmission 98 (refer to the electronic transmission 98 shown in FIG. 2), and a stand 97 for landing is provided below the main frame base 91. The battery 95 is provided with the power of the flight controller 96 and the motor 93, and the voltage is matched with the voltage range input by the electronic transmission 98; the flight controller 96 is electrically connected (or built) with a remote controller receiver 99. (navigation system) and gyroscope (not shown), the flight controller 96 is configured to receive GPS navigation (by setting a trajectory flight) or a remote control signal (user operation) to determine the current state of the aircraft 90 and transmit Control signal to the electronic transmission 98, following The electronic transmission 98 amplifies the control signal to drive the corresponding voltage current of the motor 93 to achieve the flight request action of the control aircraft 90; the electronic transmission 98 receives the signal input to the battery 95 and the flight controller 96. It is used to output the three-phase control of the motor 93 to control its rotational speed.

Although the aforementioned conventional aircraft 90 can reach its flight and landing operations by the flight controller 96 according to instructions from the user or GPS navigation, there are still some missing, for example, the aircraft 90 is mainly powered by power. The flight operation is performed, so the charging operation of the aircraft 90 is a continuous operation. The conventional aircraft 90 cannot be automatically charged immediately after landing, and it is quite cumbersome and time-consuming to wait for the manpower to be moved to the charging device for charging. And it will reduce its flight use time. Because the aircraft 90 can not reach the immediate charging of the landing and is limited by the charging operation, it is also difficult to cope with the emergency mission or the specific work demand requiring a large flight time, which is not ideal design; Although the conventional aircraft 90 can be fixedly landed by navigation or remote control operation, the actual landing point still has a considerable ground range, so that the aircraft 90 cannot be properly protected and protected when landing. The result is that the angle of the landing is biased or that encountering a special ground may damage the stand 97, affecting its use and increasing maintenance. Use, it is necessary also to be improved together. Therefore, how to improve such missing problems of such aircraft is a further problem that the industry should strive to solve and overcome.

Therefore, the creator of this creator has developed a solution based on the lack of charging of the aircraft system architecture and the unsatisfactory design of its structure design, hoping to develop a more charge immediate, The efficiency and convenience of the operation of the propeller aircraft landing positioning system to serve the public and promote the development of this industry, through the long-term concept of the creation of this creation.

The purpose of this creation is to provide a propeller aircraft landing positioning system that enables the aircraft to be properly placed after landing at a fixed point, thereby ensuring the safety of its landing and increasing the time and life of its use.

A further object of the present invention is to provide a propeller aircraft landing positioning system System, which enables the aircraft to automatically perform charging operations immediately after landing at a fixed point, achieving excellent efficiency, convenience and speed up the flight operation time of the charging operation.

The technical means for achieving the above object includes an aircraft having a mainframe base, the mainframe mount being provided with at least one frame, the frame being provided with a motor and driven by the motor The propeller is provided with a downwardly extending chassis, and the chassis is formed by a wide or narrow tapered or arcuate body.

In the above configuration, the bottom end of the chassis is provided with a charging base, and the charging base is provided with at least one charging contact.

In the above configuration, the main frame holder is provided with at least one accommodating space, and the frame extends into the accommodating space.

In the above configuration, the mainframe mount is electrically connected to a battery, a flight controller and an electronic transmission, and the battery electrically connects the charging contact.

The foregoing structure further includes a landing device, the landing device includes a positioning landing socket, and the positioning landing socket is formed by a wide or narrow tapered or arc-shaped conical disk body to form the landing socket. a tapered or arc-conical receiving surface; the landing seat is provided with a charging seat at a central position of the bottom end of the tapered or arc-conical receiving surface, and the charging base is provided with at least one charging contact.

The technical means of the present invention further includes a positioning landing device, the positioning landing device comprising a landing socket, the landing bracket being a wide or narrow tapered or arc-shaped conical disc body, such that the landing bracket A tapered or arcuate bearing surface is formed therein, and the landing seat is provided with a charging seat at a central position of the bottom end of the tapered or arc tapered receiving surface.

In the above configuration, the positioning and landing device includes a base for receiving the landing socket, and the charging base is provided with at least one charging contact.

The foregoing structure further includes an aircraft having a mainframe base, the mainframe mount being provided with at least one frame, the frame being provided with a motor and a propeller driven by the motor, the mainframe mount There is a downwardly extending chassis which is formed by a wide or narrow tapered or arcuate body.

In the above configuration, the bottom end of the tapered or arc-conical chassis is provided with a charging base, and the charging base is provided with at least one charging contact.

In the above configuration, the main frame holder is provided with at least one accommodating space, and the frame extends into the accommodating space, and the main frame holder is electrically connected with a battery, a flight controller and an electronic transmission. The battery is electrically connected to the charging contact.

In order to give your reviewers a better understanding and understanding of the technical features of the creation and the efficacies achieved, please refer to the preferred embodiment diagram and the detailed description to illustrate the following:

10‧‧‧Aircraft

10A‧‧‧Aircraft

11‧‧‧ mainframe base

12‧‧‧ accommodating space

13‧‧‧Rack

14‧‧‧Motor

15‧‧‧propeller

16‧‧‧Battery

17‧‧‧ Flight controller

18‧‧‧ Chassis

18A‧‧‧ Chassis

19‧‧‧Charging stand

191‧‧‧Charging contacts

30‧‧‧ Positioning landing gear

30A‧‧‧ Positioning landing gear

31‧‧‧ Landing Seating

311‧‧‧Conical bearing surface

311A‧‧‧Conical bearing surface

32‧‧‧Base

33‧‧‧Charging stand

331‧‧‧Charging contacts

40‧‧‧Power cord

Figure 1 is a schematic view of the structure of a conventional propeller aircraft.

Figure 2 is a schematic diagram of a conventional propeller aircraft control architecture.

Figure 3 is a perspective exploded view of the first embodiment of the present creation.

Fig. 4 is a perspective exploded perspective view showing the bottom view of the first embodiment of the present invention.

Figure 5 is a schematic perspective view of the landing of the first embodiment of the present invention.

Figure 6 is a schematic perspective view of the landing of the first embodiment of the present invention.

Fig. 7 is a schematic view showing the charging operation of the first embodiment of the present invention.

Figure 8 is a perspective exploded view of the second embodiment of the present creation.

Figure 9 is a perspective exploded perspective view of the bottom view of the second embodiment of the present invention.

Figure 10 is a schematic perspective view of the landing of the second embodiment of the present invention.

Figure 11 is a perspective view of the second embodiment of the second embodiment of the present invention.

Fig. 12 is a schematic view showing the charging operation of the second embodiment of the present invention.

Please refer to Figures 3 and 4, which is a first embodiment of the present propeller aircraft positioning landing system. The propeller aircraft landing positioning system includes an aircraft 10 and a positioning landing device 30; the aircraft 10 is a four-axis (or multi-axis) The aircraft is described as an implementation. The aircraft 10 includes a main frame base 11 , and the main frame base 11 is provided with four (or plural) accommodating spaces 12 . The frame 11 extends to a frame 13 that enters the accommodating space 12, that is, the main frame base 11 has four accommodating spaces 12 and four frames 13. The frame 13 is provided with a motor 14 (such as a brushless a motor 14 and a propeller 15 for driving the propeller 15 to rotate; the main frame base 11 is provided with a battery 16, a flight controller 17, and an electronic transmission (ESC/not shown), and the battery 16 provides the The flight controller 17 and the motor 14 are powered, and the voltage thereof is in accordance with the voltage range of the electronic transmission input. The flight controller 17 is electrically connected (or built) with a remote controller receiver (navigation system) and a gyroscope (not shown). The flight controller 17 is configured to receive GPS navigation (by a set trajectory flight) or a remote control signal (user operation) to determine the current state of the aircraft 10 and transmit a control signal to the electronic transmission, followed by The electronic transmission amplifies the control signal into a corresponding voltage and current that can drive the motor 14 to achieve the flight request action of the control aircraft 10. The electronic transmission receives the signal input to the battery 16 and the flight controller 17 for outputting the signal. Motor 1 4 three-phase control to control its rotational speed, the control structure of the present invention can be as shown in FIG. 2; further, the main frame base 11 is provided with a downwardly extending chassis 18, in this embodiment, The bottom frame 18 is formed by a plurality of tubular bodies (or a rod body, a plate body or other members) integrally formed as a wide and narrow tapered body. The bottom end of the bottom frame 18 is provided with a charging seat 19, and the charging base is provided. The central portion of the 19 is provided with a charging contact 191. The charging contact 191 (the charging stand 19) electrically connects the battery 16. In a suitable embodiment, the charging contact 191 (charging stand 19) and the battery The electrical guiding of 16 is formed by the communication arrangement between the chassis 18 and the main frame base 11.

The positioning and landing device 30 includes a base 32 and a landing socket 31 disposed on the base 32. The landing bracket 31 is a conical disk having a width and a narrow upper and lower sides, so that a recessed socket 31 is formed therein. The charging base 33 is provided with a charging seat 33 at a central portion of the bottom end of the tapered receiving surface 311. A charging contact 331 is disposed at a central portion of the charging base 33.

The chassis 18 of the main frame base 11 has a configuration corresponding to or conforms to the configuration of the landing socket 31 (the tapered receiving surface 311), and the charging base 19 (charging contact 191) of the chassis 18 is When the charging stand 33 (charging contact 331) of the landing connector 31 is docked (or correspondingly disposed), the charging operation can be performed, and the docking charging mode can be contact electrode charging, inductive charging or other charging mode.

Please refer to Figures 5 and 6 together. When the propeller aircraft positioning and landing system is applied, the aircraft 10 is assisted by GPS navigation, base station, remote control, etc. (such as WiFi, 4G, Bluetooth, infrared, ultrasonic, etc. wireless transmission positioning, so that when the aircraft 10 (chassis 18) flies to the upwardly extending range of the tapered receiving surface 311 of the positioning and landing device 30, the aircraft 10 can be stopped Lowering on the landing joint 31, and assisting the base frame 18 of the aircraft 10 to descend on the charging base 33 at the bottom of the landing socket 31 by gravity, so that the chassis 18 is just received and placed on the landing socket 31. . As shown in FIG. 7, the positioning and landing device 30 is connected to a power cord 40, and the power cable 40 electrically connects the charging base 33 (the charging contact 331); at this time, the charging stand 19 of the chassis 18 And the charging seat 33 of the landing socket 31 is in a state of being engaged (or corresponding), and the charging seat 19, the charging base 33 (the charging contact 191, the charging contact 331) are mutually coupled or sensed for immediate use. Charging operation.

Referring to Figures 8 to 12, a second embodiment of the propeller aircraft positioning landing system of the present invention is based on the structure of the first embodiment. The difference is that the chassis 18A of the aircraft 10A is The upper and lower narrow arc-shaped cones are formed, and the tapered receiving surface 311A of the positioning and lowering device 30A is also formed by a corresponding upper and lower narrow arc-conical (disc) joint surface, so that when the aircraft 10A (bottom) When the frame 18A) is flying onto the tapered receiving surface 311A of the positioning and landing device 30A and assisting to slide down on the charging base 33 by gravity, it has a stable state of corresponding smooth sliding and joint placement, and facilitates subsequent charging operations. As shown in Figure 12.

According to the foregoing configuration, the propeller aircraft landing positioning system can guide the aircraft to fall behind and automatically locate and park, so that the aircraft can get a proper connection after landing, thereby ensuring the safety of the landing; Immediately and automatically perform the charging operation to achieve excellent efficiency and convenience of the charging operation. The advantages of the propeller aircraft landing positioning system can make the aircraft have a cost-effective landing mechanism, but still maintain the purpose of accurate fixed-point landing. In addition, this creation can also be used in the Internet of Things disaster prevention system, monitoring equipment aircraft aerial camera The guide is used for landing.

In summary, this creation has indeed met the requirements of the new patent, and filed a patent application in accordance with the law. However, the above description is only for the preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Therefore, the shape, structure, characteristics and spirit described in the scope of the patent application are equally changed and modified. , should be included in the scope of the patent application of this creation.

10‧‧‧Aircraft

11‧‧‧ mainframe base

12‧‧‧ accommodating space

13‧‧‧Rack

14‧‧‧Motor

15‧‧‧propeller

18‧‧‧ Chassis

19‧‧‧Charging stand

191‧‧‧Charging contacts

30‧‧‧ Positioning landing gear

31‧‧‧ Landing Seating

311‧‧‧Conical bearing surface

32‧‧‧Base

33‧‧‧Charging stand

331‧‧‧Charging contacts

Claims (5)

A propeller aircraft landing positioning system includes an aircraft having a mainframe base, the mainframe mount being provided with at least one frame, the frame being provided with a motor and a propeller driven by the motor, the host The pedestal is provided with a downwardly extending chassis which is formed by a wide or narrow tapered or arcuate body. The propeller aircraft landing positioning system of claim 1, wherein the bottom end of the chassis is provided with a charging base, and the charging base is provided with at least one charging contact. The propeller aircraft landing positioning system of claim 1, wherein the mainframe mount is provided with at least one accommodating space, and the rack extends into the accommodating space. The propeller aircraft landing positioning system according to claim 2, wherein the mainframe mount is electrically connected to a battery, a flight controller and an electronic transmission, and the battery electrically connects the charging contact . The propeller aircraft landing positioning system of claim 4, further comprising a positioning landing device, the positioning landing device comprising a landing bracket, the landing bracket having a width and a narrow width or The arc-conical disk body defines a tapered or arc-conical receiving surface in the landing socket; the landing seat is provided with a charging seat at a central position of the bottom end of the tapered or arc-conical receiving surface, The charging base is provided with at least one charging contact.