TWM610093U - Controller of flying vehicle - Google Patents

Abstract

A control device for a flying vehicle includes at least three actuating units, and the actuating units are arranged on the ground at intervals. Each actuation unit includes a towing member suitable for connecting to the flying vehicle, a retracting mechanism connected to the towing member opposite to one end of the flying vehicle, and a retracting mechanism connected to the retracting mechanism and used to operate the The retractable mechanism retracts and retracts the towing member, thereby controlling the operating member of the flight vehicle. When the flight vehicle deviates from a preset range, at least one of the at least three actuating units can be selected to operate, and the effect of adjusting the flight vehicle is achieved by retracting and retracting the corresponding towing member, so as to maintain the The stability of the flight vehicle within a preset range.

Description

Flight vehicle control device

The new model relates to a control device of a vehicle, in particular to a control device of a flying vehicle.

Referring to FIG. 1, it is an existing inflatable flying vehicle 10. This type of inflatable flying vehicle 10 has the advantages of being easily transported after being deflated, and being able to be lifted into the air almost in a small area. It is often used as shown in FIG. It carries a lighting device 19 to provide lighting for a specific range in the air. In addition, the inflatable flying vehicle 10 can also be lifted off with communication and monitoring equipment to meet the communication or monitoring needs of a specific area.

However, although the inflatable flying vehicle 10 generates buoyancy by filling it with a low specific gravity gas, it can produce unique application advantages. Also, because of its lighter density, it is also susceptible to airflow disturbances or other high altitudes. Environmental conditions interfere, and stability cannot be effectively maintained. When the position, height, and azimuth conditions of the inflatable flying vehicle 10 cannot be maintained stably, it will naturally not be able to perform the expected effects of lighting, communication, monitoring, etc. normally.

Therefore, the purpose of the present invention is to provide a control device for a flight vehicle that can assist the flight vehicle to maintain stability.

Therefore, the control device of the new type of flying vehicle includes at least three actuating units, and the actuating units are arranged on the ground at intervals. Each actuation unit includes a towing member suitable for connecting to the flying vehicle, a retracting mechanism connected to the towing member opposite to one end of the flying vehicle, and a retracting mechanism connected to the retracting mechanism and used to operate the The retractable mechanism retracts and retracts the towing member, thereby controlling the operating member of the flight vehicle.

The effect of the present invention is that when the towing elements of the at least three actuating units are connected to the flying vehicle, the three connection points can be properly allocated to enable the actuating units to be responsible for a certain adjustment range and orientation. It constitutes a control mechanism for maintaining the flight vehicle within a set range. When the flight vehicle is deviated due to airflow or other external environmental conditions, as long as at least one actuation unit is operated, the corresponding traction member can be pulled back or lengthened for the deflection, thereby compensating for the deflection. Move to maintain the flight vehicle at least within the set range.

Before the present invention is described in detail, it should be noted that in the following description, similar elements are represented by the same numbers.

Refer to Fig. 2, which is a first embodiment of a control device for a new type of flying vehicle. The first embodiment includes three actuating units 2. The actuating units 2 are triangular and equidistantly distributed as shown in Fig. 3 They are arranged on the ground at intervals. In the first embodiment, one of the flying vehicles 9 controlled is an inflatable airship with the power to maintain itself at a specific height, which is more conducive to applications that maintain a specific range to provide lighting, communication, etc. In the implementation scenario, but in actual implementation, the controlled flying vehicle 9 can also be a sail, a hot air balloon, etc., which is not limited to this.

Each actuation unit 2 includes a towing member 21 adapted to be connected to the flying vehicle 9, a retracting mechanism 22 connected to an end of the towing member 21 opposite to the flying vehicle 9, and a retracting mechanism 22 connected to the retracting member 21. The mechanism 22 is used for operating the retracting mechanism 22 to retract the towing member 21, thereby controlling the operating member 23 of the flying vehicle 9. In the first embodiment, in order to equal the triangular equidistant distribution of the actuating units 2, the traction members 21 are preferably steel cables or ropes, and the one end connected to the flying vehicle 9 is also approximately triangular. In accordance with the specific type of the flying vehicle 9, the principle is that the position of the flying vehicle 9 can be effectively driven when towing. In addition, the specific type of each retracting mechanism 22 can be a roller for the individual traction member 21 to be wound around and storing a certain length for retracting, and each operating member 23 can drive the individual retracting mechanism 22 Rotating, thereby achieving the purpose of retracting and retracting the traction member 21.

Referring to Fig. 3 and in conjunction with Fig. 2, when the flight vehicle 9 is deviated due to airflow or other external environmental conditions, as long as at least one of the three actuating units 2 is selected for operation according to the direction of the deflection, The towing member 21 corresponding to the offset is pulled back or lengthened, thereby compensating for the offset and keeping the flying vehicle 9 at least within a set range. For example, when the flying vehicle 9 generates an offset D1 as shown in FIG. 3, the offset D1 directly corresponds to the extension direction of one of the traction members 21a from the longitudinal view, and is far away The direction is shifted, so it is possible to select and operate the operating member 23 corresponding to the towing member 21a, and by retracting the towing member 21a, the purpose of returning the flying vehicle 9 to the original set position is achieved.

Referring to Figure 4 and in conjunction with Figure 2, in addition to operating a single actuation unit 2, if the offset D2 of the flight vehicle 9 does not correspond to the extension direction of any traction element 21 as shown in Figure 4, you can choose to adjust The operating elements 23 corresponding to the two traction elements 21b and 21c, which are located on the opposite side of the offset direction, simultaneously retract the traction elements 21b and 21c. By virtue of the different components of the traction elements 21b and 21c, The purpose of providing compensation and correction for the offset D2 is achieved.

It should be particularly noted that although the adjustment methods shown in Figures 3 and 4 are all adjusted by retracting the traction member 21, in actual implementation, of course, it can also be adjusted by releasing more length. The method of the traction member 21 is adjusted, or in response to the adjustment of a specific actuating unit 2, and other actuating units 2 are also adjusted to achieve the effect of a balanced position. It is not limited to the implementation scenarios shown in Figures 3 and 4 . In addition, if the towing members 21 of all the actuating units 2 are retracted or released at the same time, the operation of stably descending or ascending the flying vehicle 9 can be achieved, and it can be adjusted freely according to different requirements.

Refer to Figure 5, which is a second embodiment of a control device for a new type of flying vehicle. The difference between this second embodiment and the first embodiment is that this second embodiment includes four actions distributed equally at four corners. Unit 2. Compared with the first embodiment in this second embodiment, the towing members 21 of the four actuating units 2 correspond substantially to the four directions of the vertical coordinate system. When you want to perform control adjustment, you can more intuitively refer to the components corresponding to the two mutually perpendicular axes of the vertical coordinate system to select the actuating unit 2 to be operated.

Refer to FIG. 6, which is a third embodiment of a control device for a new type of flying vehicle. The difference between this third embodiment and the first embodiment is that the third embodiment also includes a message connected to the three actions. The central control unit 3 of the unit 2. The central control unit 3 includes a direction sensor 31 suitable for being arranged on the flight vehicle 9, and an information connection to the direction sensor 31 and to the operating elements 23 for sensing the direction according to the direction. The sensing information of the detector 31 controls the automatic controller 32 for the operation of the operating elements 23. The direction sensor 31 of the central control unit 3 of the third embodiment may be specifically a compass, a global positioning system (GPS, Global Positioning System), a satellite navigation system (GNSS, Global Navigation Satellite System) , Gyroscope, or gravimeter, as long as it can provide direction, azimuth, or location information. With the direction sensor 31, the deviation of the flying vehicle 9 can be accurately sensed, and specific parameters related to the deviation can be provided. Therefore, the automatic controller 32 controls the operating elements 23 through objective and accurate actual data. In addition to the advantages of automatic control, the automatic controller 32 can of course also exert better adjustment accuracy.

To sum up, the control device of the new type of flight vehicle, as long as the towing members 21 of the at least three actuating units 2 are properly allocated to the connection points of the flight vehicle 9, the actuating units 2 can be individually Responsible for a certain adjustment range and orientation, and together constitute a control mechanism for maintaining the flight vehicle 9 within a set range. When the flight vehicle 9 shifts, it is only necessary to adjust at least one actuating unit 2 to correspond to the The towing member 21 tows the flying vehicle 9 to adjust the flying vehicle 9 to the original preset position, assisting the flying vehicle 9 to maintain the setting range, and optimizing the stability of the flying vehicle 9. Therefore, it can indeed achieve the purpose of cost-new type.

However, the above are only examples of the present model, and should not be used to limit the scope of implementation of the present model, all simple equivalent changes and modifications made in accordance with the patent scope of the present model application and the contents of the patent specification still belong to This new patent covers the scope.

2: Actuating unit 21: Towing parts 21a: Towing parts 21b: Towing parts 21c: traction piece 22: Retractable organization 23: operating parts 3: Central control unit 31: Orientation sensor 32: automatic controller 9: Flying vehicle D1: offset D2: offset

The other features and effects of the present invention will be clearly presented in the embodiments with reference to the drawings, among which: Figure 1 is a schematic diagram illustrating an existing inflatable flying vehicle; Figure 2 is a schematic diagram illustrating a first embodiment of the control device of the new type of flight vehicle; Figure 3 is a schematic top view illustrating the operation of the three actuating units of the first embodiment; Fig. 4 is a schematic diagram similar to Fig. 3, illustrating the adjustment when the flight vehicle has a deviation from that of Fig. 3; Figure 5 is a schematic diagram illustrating a second embodiment of the control device of the new type of flight vehicle; and Fig. 6 is a schematic diagram illustrating a third embodiment of the control device of the new type of flight vehicle.

2: Actuating unit

21: Towing parts

22: Retractable organization

23: Operating parts

9: Flying vehicle

Claims (4)

A control device for a flight vehicle, including: At least three actuating units, the actuating units are arranged on the ground at intervals, and each of the actuating units includes a towing member adapted to be connected to the flying vehicle, and an end connected to the towing member opposite to the flying vehicle A retractable mechanism and a retractable mechanism connected to the retractable mechanism and used for operating the retractable mechanism to retract and retract the towing member, thereby controlling the operating member of the flying vehicle. The control device of the flight vehicle described in claim 1 includes three actuating units, wherein the actuating units are equidistantly distributed in a triangle. The control device of the flight vehicle according to claim 1 includes four actuating units, wherein the actuating units are equidistantly distributed at four corners. The control device for a flight vehicle according to any one of claims 1 to 3, further comprising a central control unit connected to the at least three actuating units, wherein the central control unit includes a control unit suitable for being installed on the flight vehicle There is a direction sensor and an information connected to the direction sensor and connected to the operating parts, and an automatic controller for controlling the operation of the operating parts according to the sensing information of the direction sensor.

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