TWI490018B - Adjusting device for calibrating center of gravity of remote control aircraft - Google Patents

Description

Remote control aircraft center of gravity adjustment device

The present invention relates to a remote center aircraft centering device, and more particularly to a remote center vehicle centering device for instantaneously measuring the center of gravity of a remotely piloted aircraft.

The position of the center of gravity of the aircraft seriously affects its balance, handling and safety. Therefore, it is equipped with a center of gravity measuring device for monitoring the position of the center of gravity on advanced aircraft such as airplanes or helicopters, and even more is capable of actively adjusting the position of the center of gravity. The center of gravity adjustment device. However, model remote control aircraft such as remote control aircraft or RC helicopters cannot be installed with the center of gravity measuring device on the fuselage based on cost and weight considerations. Furthermore, the remote control aircraft is small in size and light in weight, so during flight. It is very susceptible to external factors such as wind speed and humidity, making the adjustment of the center of gravity position is particularly important for remote-controlled aircraft players. Once the center of gravity is not placed in the proper position, it will directly lead to poor flight stability of the remote-controlled aircraft. Even the situation that the fuselage could not be manipulated and crashed.

It is known that the center of gravity measuring device of the remote control aircraft mainly includes two types of bracket type and suspension type, wherein the bracket type center of gravity measuring device (for example, "Great Planes CG Machine") is a bracket having two fulcrums through a remote control aircraft. The fuselage is placed on the bracket and adjusts the contact position of the fuselage with the two fulcrums, so that the fuselage is kept horizontal, and the center of gravity of the fuselage is measured. However, when the size of the remote control aircraft is large, the user may have difficulty adjusting the contact position between the fuselage and the two fulcrums due to the heavy weight of the remote control aircraft, and the accident may cause the fuselage to be attached to the bracket. Drop, and even if the center of gravity of the fuselage is successfully measured, the fuselage needs to be taken from the bracket To adjust the center of gravity, return the body to the bracket and re-center the center of gravity to confirm that the center of gravity has been adjusted to the proper position. Accordingly, if the size of the remote control aircraft is large, the use of the bracket type center of gravity measuring device for center-of-gravity adjustment has problems such as inconvenience in operation and complicated steps, and there is a risk of damaging the body. Moreover, the bracket of the bracket center of gravity measuring device must be placed on a horizontal plane, and the measured center of gravity position is completely accurate. If the surface of the bracket is slightly deviated from the horizontal level, the accuracy of the center of gravity measurement will be drastically reduced.

In contrast, a suspended center of gravity measuring device (for example, Vanessa CG Machine) includes two slings wound around a pole, and the two slings are used to hang a wing of a remotely controlled aircraft, so that the RC is The fuselage is suspended in a horizontal state, and the position of the center of gravity of the fuselage is indicated by a plumb that is freely suspended from one of the poles. For a large-sized remote-controlled aircraft, compared with the bracket-type center-of-gravity measuring device, it is easier to measure the center of gravity of the body using the hanging center-of-gravity measuring device, and the center of gravity adjustment is not required to remove the body. However, it is still too much trouble to hang the remotely piloted aircraft every time the center of gravity is measured and adjusted. In addition, the hanging center-of-gravity measuring device must fix the pole to a sufficient height to suspend the remote-controlled aircraft, so that the suspended center-of-gravity measuring device cannot be carried to the flight field, causing the user to be outdoors. If you want to adjust the center of gravity of the fuselage in response to wind direction, gust strength or humidity, you can still use the equipment that is not ideal.

Furthermore, whether it is a stent center of gravity measuring device or a suspended center of gravity measuring device, it is only possible to measure the position of the center of gravity of the remotely piloted aircraft in a single axial direction. In detail, the direction in which the remotely piloted aircraft extends along its fuselage is a longitudinal axis. It is known that the center of gravity measuring device of the remotely controlled aircraft can only measure the position of the center of gravity in the direction of the longitudinal axis, and the remotely piloted aircraft The position of the center of gravity in the direction of the longitudinal axis affects the stability of its pitch control; however, the direction in which the remotely piloted aircraft is perpendicular to the longitudinal axis and extends along its wing is a horizontal axis, which is the transverse axis The position of the center of gravity on the center will affect the stability of the roll control of the remote control aircraft, but it is known that the center of gravity measuring device of the remote control aircraft cannot measure the position of the center of gravity in the direction of the horizontal axis, so that the remote control Aircraft players can only roughly balance the weight of the two sides of the wing through visual inspection, resulting in poor accuracy of center of gravity adjustment.

In summary, it is urgent to provide a remote-controlled aircraft center-of-gravity adjustment device for measuring the center of gravity of various sizes of remote-controlled aircraft, and at the same time facilitating the user to adjust the center of gravity to adjust the center of gravity of the remote-controlled aircraft to an appropriate position.

An object of the present invention is to provide a remote center aircraft centering device, which uses two brackets to carry an aircraft, and the weight of the two frames is measured by two gravity sensors to calculate the total weight of the aircraft. And calculating a position of the center of gravity of the aircraft, thereby driving a pointing element disposed on one of the struts connecting the two brackets to position the pointing element opposite the center of gravity, having a simplified overall weight and center of gravity measurement of the aircraft Convenient for the center of gravity adjustment.

Another object of the present invention is to provide a remote centering device for adjusting the center of gravity of the aircraft, which is provided with a length adjusting portion respectively for the struts and the receiving portion provided at one end of the bracket, so that the aircraft can be applied to aircraft of different sizes, and The other end of the bracket is provided with a seat body, so that the center of gravity adjustment device of the aircraft can be used on any plane, which has the effect of improving the applicable range.

A further object of the present invention is to provide a remote center aircraft centering adjustment device. After calculating the center of gravity of the aircraft in a longitudinal axis direction, the two wings of the aircraft can be respectively placed on the two brackets to measure the aircraft. The position of the center of gravity in the direction of the horizontal axis has the effect of improving the accuracy of the center of gravity adjustment.

In order to achieve the foregoing object, the technical means for the present invention includes: a remote center of gravity adjustment device for a remote control aircraft, comprising: a rod, comprising a sliding seat and a sliding table, the sliding seat being disposed along the pole, The sliding table is movably disposed on the sliding seat, and the sliding table is provided with a pointing component, and the supporting rod is further provided with a driving member coupled to the sliding seat or the sliding table for driving the sliding table Sliding along the sliding seat; two brackets are respectively coupled to the two ends of the strut, and the two ends of the bracket are respectively provided with a body and a receiving portion, and the receiving portion is connected with a gravity And a control unit coupled to the driving member of the strut and the gravity sensor of the two brackets respectively.

The gravity centering device of the remote control aircraft of the present invention, wherein the sliding seat is a screw, the sliding table is a screw, the sliding table is screwed to the sliding seat, and the driving member is coupled to the sliding seat to drive The carriage rotates to drive the slide to slide along the slide.

The remote-controlled aircraft center-of-gravity adjustment device of the present invention, wherein the pointing device is a laser emitter for generating a laser beam.

The remote-controlled aircraft center-of-gravity adjustment apparatus of the present invention, wherein the pointing element is coupled to the slide via a pivotal member such that the pointing element is pivotable relative to the strut.

In the center of gravity adjustment device of the remote control aircraft of the present invention, the positioning portion defines a positioning hole, and the positioning hole is opposite to the gravity sensor, and a positioning member is received in the positioning hole.

The gravity center centering device of the remote control aircraft of the present invention, wherein the positioning member abuts the gravity sensor via the positioning hole.

The gravity centering device of the remote control aircraft of the present invention, wherein the positioning member comprises two symmetrical cylinders for clamping an object carried by the bearing portion, so that the weight of the object is concentratedly transmitted to the object through the positioning hole. Gravity sensor.

The gravity centering device of the remote control aircraft of the present invention, wherein the bearing portion of the two brackets is provided with an aircraft, the gravity sensor measures the weight of the bearing portion, and the control unit receives the gravity The sensed weight is sensed and summed to produce the total weight of the aircraft.

The gravity center centering device of the remote control aircraft of the present invention, wherein the control unit calculates the position of the center of gravity of the aircraft according to the following formula: Dx=(F×D)÷W, where x is the position of the center of gravity of the aircraft and one of the receiving portions The distance is F, the weight of the bearing part, D is the distance of the two mounting parts, and W is the total weight of the aircraft.

The remote center aircraft centering device of the present invention, wherein the control unit is provided A display panel for displaying the total weight of the aircraft and the position of the center of gravity.

The remote center aircraft centering device of the present invention, wherein the pole and the two supports Each of the receiving portions of the rack is provided with a length adjusting portion.

In the remote center of gravity adjustment device of the present invention, the length adjustment portion of the pole is provided with a scale for reading the distance between the two sockets.

The gravity center centering device of the remote control aircraft of the present invention, wherein the receiving portion is provided with a clamping member.

The center-of-flight adjustment device of the remote control aircraft of the present invention, wherein the bracket is coupled with the support rod between the base body and the receiving portion, the bracket is provided with a height adjusting portion, and the height adjusting portion is disposed at the receiving portion and the The joint between the strut and the bracket is used to adjust the height of the receiving portion.

The gravity centering device of the remote control aircraft of the present invention, wherein the bracket and the receiving portion are coupled to the pole, the bracket is provided with a height adjusting portion, and the height adjusting portion is disposed on the seat body and the branch Between the rod and the joint of the bracket, the height of the pole is adjusted.

The gravity centering device of the remote control aircraft of the present invention, wherein the bracket is coupled between the seat body and the receiving portion, and the pole is provided with a level.

〔this invention〕

1‧‧‧ pole

11‧‧‧Slide

12‧‧‧ slide table

121‧‧‧ pointing elements

122‧‧‧ pivotal parts

122a‧‧‧Fixed Department

122b‧‧‧ pivoting department

13‧‧‧ Drives

14‧‧‧ Length Adjustment Department

141‧‧‧ scale

15‧‧‧ level

2‧‧‧ bracket

21‧‧‧ body

22‧‧‧Holding Department

221‧‧‧Positioning holes

222‧‧‧ Positioning parts

222a‧‧‧Cylinder

223‧‧‧Clamping parts

224‧‧‧ Length Adjustment Department

23‧‧‧Gravity sensor

24‧‧‧ Height Adjustment Department

25‧‧‧ Height Adjustment Department

3‧‧‧Control unit

31‧‧‧ display panel

G‧‧‧Center of gravity

P‧‧‧Aircraft

P1‧‧‧ wing

P11‧‧‧ endpoint

X‧‧‧vertical axis direction

Y‧‧‧ horizontal axis direction

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is an external view of a preferred embodiment of the present invention.

Figure 2 is a partial enlarged view of a preferred embodiment of the present invention.

Figure 3 is a diagram of the use of the preferred embodiment of the present invention.

Figure 4 is a diagram of the use of the preferred embodiment of the present invention.

Figure 5 is a diagram of the use of the preferred embodiment of the present invention.

Figure 6 is a diagram showing the use of the preferred embodiment of the present invention.

Figure 7 is an external view of another embodiment of the preferred embodiment of the present invention.

The above and other objects, features and advantages of the present invention will become more <RTIgt; Coupling means that the two devices can transfer data to each other by means of a wired entity, a wireless medium or a combination thereof (for example, a heterogeneous network), which is common in the technical field to which the present invention pertains. Knowledge people can understand.

Referring to FIG. 1 , the center of gravity adjustment device of the remote control aircraft of the preferred embodiment of the present invention comprises a rod 1 and two brackets 2 , respectively, and the two brackets 2 are respectively coupled to the two ends of the rod 1 , and The bracket 2 can be combined with the struts 1 by a detachable combination (for example, locking or splicing) or a non-detachable combination (for example, welding or bonding), or can be combined with the struts 1 The invention is integrally formed, and the invention is not limited.

The strut 1 is provided with a sliding seat 11 and a sliding table 12 along which the sliding seat 11 is disposed, and the sliding table 12 is movably disposed on the sliding seat 11. Thereby, the slide table 12 can slide along the carriage 11. The struts 1 are further provided with a driving member 13 coupled to the sliding seat 11 or the sliding table 12 for driving the sliding table 12 along the sliding seat 11 to be displaced relative to the struts 1 . More specifically, in the embodiment, the slide 11 is a conventional screw, and the slide 12 is a conventional screw. The slide 12 is screwed to the slide 11 to be movably disposed on the slide. The slider 11 is on. The driving member 13 can be selected as a conventional motor and coupled to the sliding seat 11 . The driving member 13 drives the sliding seat 11 to rotate clockwise or counterclockwise, respectively, so as to drive the sliding table 12 along the sliding seat 11 . Reciprocating. However, the slide 11 and the slide 12 may be combined with the conventional transmission structure such as a gear row, a gear rail, a pulley and a pulley or a flexible mechanism, in addition to the screw and the screw. The invention is not limited to this.

Referring to FIG. 2 together, the sliding table 12 is provided with a pointing element 121. The pointing device 121 can be a cylinder, and preferably has a reduced diameter at the end for pointing in a specific direction; or, in the embodiment, the pointing device 121 can be a conventional laser emitter for generating The laser beam is marked in a particular direction. In addition, the pointing element 121 is preferably coupled to the sliding table 12 via a pivoting member 122 such that the pointing element 121 can pivot relative to the strut 1 and the pointing element 121 is preferably perpendicular to the strut 1 Pivot. In detail, the pivoting member 122 includes a fixing portion 122a and a pivoting portion 122b. The fixing portion 122a is coupled to the sliding table 12, and the pivoting portion 122b is pivotally connected to the fixing portion 122a for the pointing The element 121 is disposed, and the pivoting portion 122b is pivoted perpendicularly to the strut 1, so that the pointing element 121 disposed on the pivoting portion 122b is pivoted perpendicularly to the strut 1.

The structure of the two brackets 2 can be designed to be identical, so that only one of the brackets 2 will be described below. The two ends of the bracket 2 are respectively provided with a body 21 and a receiving portion 22, and the strut 1 is coupled between the seat body 21 and the receiving portion 22. The base 21 is configured to abut against a ground or other flat surface. The receiving portion 22 is connected to a gravity sensor 23 for sensing the weight carried by the receiving portion 22. In detail, the receiving portion 22 is preferably provided with a positioning hole 221, and the positioning hole 221 is in communication with the gravity sensor 23, and a positioning member 222 is accommodated in the positioning hole 221. The positioning member 222 can be used for supporting the object carried by the receiving portion 22 and abutting the gravity sensor 23 via the positioning hole 221. In this embodiment, the positioning member 222 is positioned. The member 222 includes two symmetrical cylinders 222a for holding the object carried by the receiving portion 22 to transfer the weight of the object to the gravity sensor 23 via the positioning hole 221 . However, the shape and specification of the positioning member 222 can be matched with the object to be carried by the receiving portion 22, so that the receiving portion 22 can be positioned to support different types and sizes of remotely controlled aircraft by replacing the positioning member 222.

The remote center of gravity adjustment device of the preferred embodiment further includes a control unit 3, which may be a micro control unit (MCU) or other conventional computing device, respectively coupled to the driving member of the pole 1 13 and the gravity sensor of the two brackets 2 23, to receive the weight sensed by the gravity sensor 23. The control unit 3 can calculate the position of the center of gravity of the object shared by the two mounting portions 22 according to the weight sensed by the two gravity sensors 23, and control the driving member 13 to drive the sliding table 12 along the sliding The seat 11 is slipped to indicate the position of the center of gravity.

Please refer to FIG. 3, which is a use diagram of a center-of-gravity adjustment device for a remote control aircraft according to a preferred embodiment of the present invention. The center-of-flight adjustment device of the remote control aircraft of the preferred embodiment is used for standing on a plane via the seat body 21 of the two brackets 2, and the pivoting member 122 of the sliding table 12 is preferably adjusted, so that the pointing device 121 continues. Point in the direction perpendicular to and away from the plane. An aircraft P is placed on the receiving portion 22 of the two brackets 2 to be supported by the positioning members 222 of the two receiving portions 22, respectively. The aircraft P may be a conventional remote control flying device such as a remote control aircraft or a remote control helicopter, and the total weight W of the aircraft P is respectively carried by the two mounting portions 22. The weight of the bearing portion 22 is transmitted to the gravity sensor 23 via the positioning member 222 and the corresponding positioning hole 221, so that the two gravity sensors 23 can separately measure the two bearings. The weight of the part 22. The control unit 3 receives the weight sensed by the gravity sensor 23 and adds up to the total weight W of the aircraft P.

Wherein, the receiving portion 22 can be provided with a clamping member 223 for clamping and fixing the aircraft P to avoid inadvertent collision during the center of gravity adjustment, causing the aircraft P to slide off from the bearing portion 22; The height adjustment portion 24 is further disposed between the receiving portion 22 and the joint portion of the support rod 1 and the bracket 2 for adjusting the height of the receiving portion 22 When the type of the aircraft P supported by the two mounting portions 22 is different, the height adjusting portion 24 can still be used to adjust the height of the receiving portion 22 so that the fuselage of the aircraft P can be parallel to the strut 1 .

Since the distance D of the two mounting portions 22 is known, the control unit 3 can calculate the distance between the center of gravity G of the aircraft P and any of the receiving portions 22 according to the following formula (1): Dx=(F× D)÷W (1) Wherein, F is the weight of one of the mounting portions 22, and is measured by the gravity sensor 23 connected to the receiving portion 22; x is the center of gravity G of the aircraft P and the receiving portion 22 The distance. When the positioning portion 22 is provided with the positioning hole 221 and the positioning member 222, the weight of the bearing portion 22 is the weight supported by the positioning member 222, and the positioning hole of the positioning member 222 is received. The 221 is in communication with the gravity sensor 23, so the gravity sensor 23 can directly measure the weight supported by the positioning member 222.

Referring to FIG. 4, after the control unit 3 calculates the gravity center position G of the aircraft P, the driving member 13 is controlled to drive the sliding table 12 to slide along the sliding seat 11 so as to be disposed on the sliding table. The pointing element 121 of 12 is opposite to the center of gravity position G, thereby indicating the center of gravity position G. Since the pointing element 121 is a laser emitter in the present embodiment, the pointing element 121 can generate a laser beam to mark the center of gravity position G of the fuselage of the aircraft P. In addition, the control unit 3 can also be provided with a display panel 31, which can be a variety of conventional display devices such as a seven-segment display, a liquid crystal display or a light-emitting diode display, for displaying the total weight W and the center of gravity of the aircraft P. Position G, convenient for the user to adjust the center of gravity.

Accordingly, the user can know the center of gravity G of the aircraft P via the pointing element 121. If the center of gravity position G is not an appropriate position, the aircraft P can be directly removed by adjusting without removing the aircraft P from the two mounting portions 22. The position of the battery or the fuel tank or the like is added or assembled to perform the adjustment of the center of gravity position G, and the control unit 3 will repeat the above action during the adjustment to continuously mark the instantaneous center of gravity of the aircraft P with the pointing element 121. The position G is convenient for the user to quickly adjust the center of gravity position G to an appropriate position. In contrast, the user can also know the total weight W of the aircraft P and the center of gravity position G through the display panel 31, thereby performing center of gravity adjustment, so that the remote center of gravity adjustment device of the preferred embodiment has a perfect weight. And center of gravity measurement function.

It should be noted that the struts 1 are preferably provided with a length adjusting portion 14 for adjusting the length of the struts 1 so that the center of gravity adjusting device of the remote control aircraft of the preferred embodiment can Suitable for aircraft P with different axial lengths. However, when the length of the strut 1 is adjusted by the length adjusting portion 14, the distance D of the two receiving portions 22 is changed so that the distance D does not have a certain value. Therefore, the length adjusting portion 14 is preferably provided with a scale 141. For the user to read the distance D of the two mounting portions 22 and input the control unit 3, so that the control unit 3 can still correctly calculate the position of the center of gravity of the aircraft P after the distance D is changed. Similarly, the two mounting portions 22 can also be respectively provided with a length adjusting portion 224 for adjusting the length of the receiving portion 22, so that the remote-controlled aircraft center-of-gravity adjusting device of the preferred embodiment can be applied to different bodies. Width of the aircraft P.

In addition, as shown in FIGS. 5 and 6, the pointing element 121 is coupled to the slide table 12 via a pivoting member 122 such that the pointing element 121 can pivot relative to the strut 1 . When the driving member 13 drives the sliding table 12 to slide along a longitudinal axis direction X such that the pointing element 121 is opposite to the center of gravity G of the aircraft P, the user can make the pointing element 121 perpendicular to the The struts 1 (i.e., perpendicular to the longitudinal axis direction X) pivot such that the pointing element 121 indicates the end point P11 of the wing P1 on both sides of the aircraft P and the center of gravity position G in a horizontal axis direction Y. In order to facilitate the calibration of the wing P1, the adjustment of the aircraft P is made easier. Wherein, the longitudinal axis direction X is a direction in which the aircraft P extends along the fuselage thereof, and the horizontal axis direction Y is a direction in which the aircraft P is perpendicular to the longitudinal axis and extends along the wing P1 thereof.

In order to ensure the accuracy of the position C of the center of gravity calculated by the control unit 3, after the measurement of the center of gravity G of the aircraft P in the longitudinal direction X is completed by the above process, the two wings P1 of the aircraft P can be respectively set. In the receiving portion 22 of the two brackets 2, the connecting line between the two wings P1 and the end point P11 corresponding to the center of gravity position G in the horizontal axis direction Y is parallel to the strut 1 and the same strip The plumb line intersects, and the center of gravity G′ of the aircraft P in the horizontal axis direction Y is calculated by the control unit 3 through the above principle, and whether the center of gravity position G, G′ of the second measurement is coincident to determine whether The center of gravity position G is the correct center of gravity of the aircraft P.

It is noted that the plane against which the base 21 of the two brackets 2 abuts is preferably a horizontal plane. However, the user carries the preferred remote control center of gravity adjustment device to the flight field. In use, it is difficult to ensure that the ground on which the two brackets are erected is a horizontal plane, which easily causes an error in the total weight W and the center of gravity position G of the measured aircraft P. In view of this, please refer to FIG. 7 , in another embodiment of the center-of-gravity center-adjusting device of the preferred embodiment, the bracket 2 may be provided with another height adjusting portion 25, and the height adjusting portion 24 is disposed. Between the seat body 21 and the joint portion of the strut 1 and the bracket 2, the height of the strut 1 is adjusted so that the plane of the seat body 21 of the two brackets 2 is not horizontal. The user adjusts the height of the strut 1 through the height adjusting unit 25, and the strut 1 can still be adjusted to the level. Furthermore, a level 15 can be attached to the pole 1 to facilitate horizontal alignment of the pole 1.

In summary, the gravity centering device of the remote control aircraft of the present invention utilizes two brackets 2 to carry an aircraft P, and the weights carried by the two brackets 2 are respectively measured by the two gravity sensors 23 to generate a total The total weight W of the aircraft P, and the position G of the center of gravity of the remotely controlled aircraft is calculated, so as to drive the pointing element 121 disposed on one of the poles 1 connected to the two brackets 2, the pointing element 121 and the center of gravity position G Relative position. Thereby, the user can simply place the aircraft P on the two brackets 2 via the remote center of gravity adjustment device of the present invention, and quickly adjust the center of gravity position G to an appropriate position according to the indication of the pointing element 121. The location does have the effect of simplifying the total weight of the remotely piloted aircraft and measuring the center of gravity to facilitate center-of-gravity adjustment.

Furthermore, the gravity centering device of the remote control aircraft of the present invention is provided with a length adjusting portion through the support rods 1 and the receiving portion 22 provided at one end of the bracket 2, so that it can be applied to remotely piloted aircraft of different sizes, and The other end of the bracket 2 is provided with a seat body 21, so that the remote center of gravity adjustment device can be used on any plane. Compared with the known bracket type center of gravity measuring device, it is not suitable for a large-sized remote control aircraft; it is known that the suspended center of gravity measuring device cannot be carried to the flight field, and the gravity center centering device of the remote control aircraft of the present invention does have an improved application range. efficacy.

In addition, another object of the present invention is to provide a remote center aircraft centering adjustment device, which can be calculated by calculating the center of gravity position G of the aircraft P in a longitudinal axis direction X. The two wings P1 of the device P are respectively placed on the two brackets 2 to measure the center of gravity position G' of the aircraft P in a horizontal axis direction Y, and whether or not the two center of gravity positions G, G' coincide with each other to determine the The center of gravity G is the correct center of gravity of the aircraft P, and it has the effect of improving the accuracy of the center of gravity adjustment.

While the invention has been described in connection with the preferred embodiments described above, it is not intended to limit the scope of the invention. The technical scope of the invention is protected, and therefore the scope of the invention is defined by the scope of the appended claims.

1‧‧‧ pole

11‧‧‧Slide

12‧‧‧ slide table

121‧‧‧ pointing elements

122‧‧‧ pivotal parts

13‧‧‧ Drives

14‧‧‧ Length Adjustment Department

141‧‧‧ scale

2‧‧‧ bracket

21‧‧‧ body

22‧‧‧Holding Department

221‧‧‧Positioning holes

222‧‧‧ Positioning parts

222a‧‧‧Cylinder

223‧‧‧Clamping parts

224‧‧‧ Length Adjustment Department

23‧‧‧Gravity sensor

24‧‧‧ Height Adjustment Department

3‧‧‧Control unit

31‧‧‧ display panel

Claims (15)

A remote centering machine center-of-gravity adjusting device comprises: a rod comprising a sliding seat and a sliding table, the sliding seat is disposed along the supporting rod, the sliding table is movably disposed on the sliding seat, and the sliding table is arranged on the sliding table a directional member is provided, the directional member is coupled to the sliding table via a pivoting member, such that the directional member is pivotable relative to the struts, the struts are further provided with a driving member coupled to the sliding seat or The sliding table is configured to drive the sliding table to slide along the sliding seat; the two supporting frames are respectively coupled to the two ends of the supporting rod, and the two ends of the supporting frame are respectively provided with a body and a receiving portion, The mounting portion is connected to a gravity sensor; and a control unit is coupled to the driving member of the strut and the gravity sensor of the two brackets. The remote-controlled aircraft center-of-gravity adjusting device according to the first aspect of the invention, wherein the sliding seat is a screw, the sliding table is a screw, the sliding table is screwed to the sliding seat, and the driving component is The sliding seat is coupled to drive the sliding seat to drive the sliding table to slide along the sliding seat. The remote-controlled aircraft center-of-gravity adjustment device of claim 1, wherein the pointing device is a laser emitter for generating a laser beam. The center of gravity adjustment device of the remote control aircraft of claim 1, wherein the receiving portion defines a positioning hole, and the positioning hole is in communication with the gravity sensor, and a positioning member is received in the positioning hole. The remote-controlled aircraft center-of-gravity adjustment device of claim 4, wherein the positioning member abuts the gravity sensor via the positioning hole. The remote-controlled aircraft center-of-gravity adjusting device according to claim 5, wherein the positioning member comprises two symmetrical cylinders for clamping an object carried by the receiving portion to pass the weight of the object The positioning holes are concentratedly transmitted to the gravity sensor. For example, the center of gravity adjustment device of the remote control aircraft described in claim 1 is The bearing portion of the two brackets is provided with an aircraft, the gravity sensor measures the weight of the bearing portion, and the control unit receives the weight sensed by the gravity sensing and adds the total The total weight of the aircraft. The remote-controlled aircraft center-of-gravity adjusting device according to claim 7, wherein the control unit calculates a position of a center of gravity of the aircraft according to the following formula: Dx=(F×D)÷W, where x is the center of gravity of the aircraft The distance between the position and one of the receiving portions, F is the weight of the bearing portion, D is the distance between the two bearing portions, and W is the total weight of the aircraft. The remote-controlled aircraft center-of-gravity adjusting device according to claim 8, wherein the control unit is provided with a display panel for displaying the total weight of the aircraft and the position of the center of gravity. The remote center aircraft centering device as described in claim 1, 2, 3, 4, 5, 6, 7, 8, or 9, wherein the strut and the receiving portion of the two brackets are respectively provided with a Length adjustment section. The remote center of gravity adjustment device of claim 10, wherein the length adjustment portion of the pole is provided with a scale for reading the distance between the two sockets. The remote-controlled aircraft center-of-gravity adjusting device according to claim 1, 2, 3, 4, 5, 6, 7, 8, or 9, wherein the receiving portion is provided with a clamping member. The remote center aircraft centering device as described in claim 1, 2, 3, 4, 5, 6, 7, 8, or 9, wherein the bracket and the bearing portion are coupled to the bracket The struts are provided with a height adjusting portion disposed between the receiving portion and a joint portion of the struts and the bracket for adjusting the height of the receiving portion. The remote center aircraft centering device as described in claim 1, 2, 3, 4, 5, 6, 7, 8, or 9, wherein the bracket and the bearing portion are coupled to the bracket The struts are provided with a height adjusting portion disposed between the seat body and the joint portion of the struts and the bracket for adjusting the height of the struts. The gravity center centering device of the remote control aircraft of claim 14, wherein the bracket and the bearing portion are coupled to the pole, and the pole is provided with a level.