TWI652954B - Operation mode switching method and electronic device using the same - Google Patents

Abstract

The operation mode switching method of the present invention comprises the steps of: sensing a first acceleration through an acceleration gauge unit; and determining, by the processing unit, whether the following condition is true: a first acceleration ≧ acceleration threshold value, when the determination result is YES, the sense of the air pressure sensing unit Measuring the first air pressure and the second air pressure; determining, by the processing unit, whether the following condition is true: [(second air pressure - first air pressure) / (sensing the time difference between the first air pressure and the second air pressure)] ≧ pressure difference threshold, when judging The result is yes, the electronic device switches to open a flight mode.

Description

Operation mode switching method and electronic device using the same

The present invention relates to an operation mode switching method and an electronic device using the same.

At present, the rapid development of the Internet of Things (IoT), small electronic devices have the function of wireless Internet access and communication. However, according to the International Federal Aviation Administration (FAA) and general airline regulations, wireless communication equipment is prohibited from communicating when the aircraft takes off and land to facilitate flight safety. In other words, when the aircraft is taking off and landing, for flight safety, the power should be turned off or the flight mode should be switched to turn off the wireless communication function.

In the current flight mode switching of IoT products on the market, it is necessary to manually switch, or set the time switch to switch, which is less convenient to use. This will create an associated flight risk when the device leaves or forgets to manually switch the flight mode.

The main object of the present invention is to provide an operation mode switching method, which can improve the usability of the electronic device.

The main object of the present invention is to provide an electronic device which has better usability.

The operating mode switching method of the present invention is for use with an electronic device. The electronic device includes a processing unit, an accelerometer unit, and a barometric sensing unit. The operation mode switching method includes the following steps: sensing the first acceleration through the acceleration gauge unit; determining, by the processing unit, whether the following condition is true: a first acceleration ≧ acceleration threshold; and when the determination result is YES, sensing the first through the air pressure sensing unit The air pressure and the second air pressure; the processing unit determines whether the following condition is true: [(second air pressure - first air pressure) / (sensing the time difference between the first air pressure and the second air pressure)] ≧ air pressure difference threshold; when the judgment result is yes When the electronic device switches to open a flight mode.

In an embodiment of the present invention, the processing unit determines whether the following condition is satisfied: the first acceleration 加速度 an acceleration threshold, and when the determination result is no, the step of sensing the first acceleration through the acceleration gauge unit is performed.

In an embodiment of the present invention, wherein the processing unit determines whether the following condition is true: [(second air pressure - first air pressure) / (sensing time difference between the first air pressure and the second air pressure)] ≧ air pressure difference threshold, when judging When the result is no, the step of sensing the first acceleration through the acceleration gauge unit is performed.

In the embodiment of the present invention, after the step of determining whether the condition of the first acceleration ≧ acceleration threshold is established by the processing unit, the method further comprises: sensing the takeoff air pressure through the air pressure sensing unit; and determining, by the processing unit, whether the following condition is satisfied: the takeoff pressure ≧ The first predetermined air pressure threshold, when the determination result is YES, the processing unit determines [(second air pressure - first air pressure) / (sense time difference between the first air pressure and the second air pressure)] that the condition of the air pressure difference threshold is established. .

In the embodiment of the present invention, the processing unit determines whether the following condition is satisfied: the takeoff air pressure ≧ the first predetermined air pressure threshold, and when the determination result is no, the step of sensing the first acceleration through the acceleration gauge unit is performed.

In an embodiment of the invention, the first predetermined air pressure threshold is a barometric pressure value at an altitude of 465 。.

In the embodiment of the present invention, the processing unit further determines that the condition of the (the second air pressure - the first air pressure) / (the time difference between the first air pressure and the second air pressure) is determined. : The horizontal acceleration is sensed by the acceleration gauge unit; the following condition is determined by the processing unit: the horizontal acceleration ≧ the horizontal acceleration threshold, and when the determination result is YES, the electronic device switches to the flight mode.

In the embodiment of the present invention, the processing unit determines whether the following condition is satisfied: a horizontal acceleration ≧ horizontal acceleration threshold, and when the determination result is no, performing a step of sensing the first acceleration through the acceleration gauge unit.

In an embodiment of the present invention, after the step of switching the electronic mode to the flying mode, the electronic device further includes the following steps: sensing the falling air pressure through the air pressure sensing unit; determining, by the processing unit, whether the following condition is true: the falling air pressure ≦ the second predetermined air pressure threshold When the judgment result is YES, the second acceleration is sensed through the acceleration gauge unit; the processing unit determines whether the following condition is true: The second acceleration=0; when the judgment result is YES, the electronic device switches to close the flight mode.

In the embodiment of the present invention, the processing unit determines whether the following condition is established: the falling air pressure ≦ the second predetermined air pressure threshold, and when the determination result is no, the step of sensing the falling air pressure by the air pressure sensing unit is performed.

In the embodiment of the present invention, the processing unit determines whether the following condition is satisfied: the second acceleration=0, and when the determination result is no, the step of sensing the falling air pressure by the air pressure sensing unit is performed.

The electronic device of the present invention includes an accelerometer unit, a barometric sensing unit, and a processing unit. The accelerometer unit is configured to sense the first acceleration. The air pressure sensing unit is configured to sense the first air pressure and the second air pressure. The processing unit is coupled to the accelerometer unit and the air pressure sensing unit. The processing unit determines whether the following condition is true: the first acceleration ≧ acceleration threshold, when the determination result is YES, the processing unit determines whether the following condition is true: [(second air pressure - first air pressure) / (sensing the first air pressure and the second The time difference of the air pressure)] ≧ ≧ air pressure difference threshold, when the judgment result is YES, the processing unit generates a command to switch the air navigation mode.

In the embodiment of the present invention, the air pressure sensing unit is further configured to sense the takeoff air pressure, and the processing unit further determines whether the following condition is met: the takeoff air pressure ≧ the first predetermined air pressure threshold, and when the determination result is yes, the air pressure sensing unit senses The first air pressure and the second air pressure are measured, and when the determination result is no, the acceleration gauge unit senses the first acceleration.

In an embodiment of the present invention, the acceleration gauge unit is further configured to sense a horizontal acceleration, and the processing unit further determines whether the following condition is met: a horizontal acceleration ≧ a horizontal acceleration threshold, and when the determination result is YES, the processing unit generates a switching-on flight mode. The instruction, when the determination result is no, the acceleration gauge unit senses the first acceleration.

In an embodiment of the invention, the electronic device switches to turn on the flight mode according to the switch-on flight mode command.

In an embodiment of the present invention, the processing unit further senses the falling air pressure while generating the switch-on flight mode command, and the processing unit determines whether the following condition is met: the falling air pressure ≦ the second predetermined air pressure threshold, when determining When the result is YES, the acceleration gauge unit senses the second acceleration, and when the determination result is no, the air pressure sensing unit senses the landing air pressure. And the processing unit determines whether the following condition is true: the second acceleration=0, when the judgment result is yes, the processing The unit output switching closes the flight mode command, and when the determination result is no, the acceleration gauge unit senses the second acceleration.

In an embodiment of the invention, the electronic device switches to close the flight mode according to the switching off the flight mode command.

100‧‧‧Processing unit

200‧‧‧Acceleration unit

300‧‧‧Pneumatic sensing unit

400‧‧‧Wireless communication module

900‧‧‧Electronic devices

1000, 1500, 1700, 1800, 2000, 2500, 2700, 2800, 3000, 4000, 4500, 5000, 5500, 6000‧‧ steps

1 is a block diagram of an embodiment of an electronic device of the present invention.

2 is a block diagram showing different embodiments of an operation mode switching method according to the present invention.

FIG. 3 is a schematic flowchart of an embodiment of an operation mode switching method according to the present invention.

4A and FIG. 4B are schematic flowcharts of different embodiments of an operation mode switching method according to the present invention.

As used herein, "about," or "substantially" includes the values and average values within acceptable deviations of the particular values determined by one of ordinary skill in the art, in view of the measurements and The specific amount of error associated with the measurement (ie, the limits of the measurement system) is measured. For example, "about" can mean within one or more standard deviations of the stated value, or within ±30%, ±20%, ±10%, ±5%. Furthermore, as used herein, "about", "approximately" or "substantially" may select a more acceptable range or standard deviation depending on optical properties, etching properties or other properties, and may apply all properties without a standard deviation. .

All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. It will be further understood that terms such as those defined in commonly used dictionaries should be interpreted as having meanings consistent with their meaning in the context of the related art and the present invention, and will not be construed as idealized or excessive. Formal meaning, unless explicitly defined in this article.

The operation mode switching method of the present invention is used for an electronic device. The electronic device includes a tablet computer, a notebook computer, a desktop computer, a smart phone, a personal digital assistant, an e-book, a digital photo frame, a digital walkman, an electronic dictionary, a GPS navigation machine, and the like.

As shown in the embodiment of FIG. 1, the electronic device 900 of the present invention includes a processing unit 100, an accelerometer unit 200, and a barometric sensing unit 300. The processing unit 100 can be a Central Processing Unit (CPU). Acceleration gauge unit 200 is included as a gravity sensor (G-Sensor) to sense the first acceleration. The processing unit 100 is coupled to the accelerometer unit 200. More specifically, in an embodiment, the processing unit 100 outputs an acceleration sensing command, and the acceleration gauge unit 200 senses the first acceleration according to the acceleration sensing command.

More specifically, the aircraft must be accelerated when it takes off, so it can be judged by the first acceleration whether the aircraft in which the electronic device is located is in a take-off state. In the preferred embodiment, with reference to the technical data of a general civil aircraft, the acceleration at takeoff is 2 m/s ² or more, so the acceleration threshold is preferably 2 m/s ² .

The air pressure sensing unit 300 includes a barometer based on microelectromechanical (MEMS) and piezoresistive pressure sensing technology for sensing the first air pressure and the second air pressure. The processing unit 100 is coupled to the air pressure sensing unit 300. More specifically, in an embodiment, the processing unit determines whether the following condition is met: a first acceleration ≧ acceleration threshold, and when the determination result is YES, the air pressure sensing unit 300 senses the first air pressure according to the air pressure sensing instruction and the first Two air pressures. The processing unit 100 determines whether or not the following conditions are satisfied: [(second air pressure - first air pressure) / (sensing time difference between the first air pressure and the second air pressure)] ≧ air pressure difference threshold.

When the determination result is YES, the processing unit 100 generates a switch-on flight mode command; when the determination result is no, the processing unit 100 outputs an acceleration sensing command. The electronic device switches to turn on the flight mode according to the switch-on flight mode command.

More specifically, since the height can be calculated from the air pressure, the change in the air pressure per unit time is substantially equivalent to the change in height per unit time. More specifically, when the air pressure difference threshold is 0, and [(second air pressure - first air pressure) / (sensing the time difference between the first air pressure and the second air pressure)] ≧ air pressure difference threshold, indicating a height increase, that is, The electronic device is located in an aircraft that is in a climbing state.

In an embodiment, the air pressure sensing unit is further configured to sense the takeoff air pressure. The processing unit 100 further determines whether the following condition is satisfied: the takeoff air pressure ≧ the first predetermined air pressure threshold.

When the determination result is YES, the air pressure sensing unit senses the first air pressure and the second air pressure. When the judgment result is no, the acceleration gauge unit senses the first acceleration. More specifically, When the determination result is YES, the processing unit 100 outputs a dual air pressure sensing command, and the air pressure sensing unit 300 senses the first air pressure and the second air pressure according to the dual air pressure sensing command. When the determination result is no, the processing unit 100 outputs an acceleration sensing instruction, and the acceleration gauge unit 200 senses the first acceleration according to the acceleration sensing instruction. More specifically, in order to ensure the safety of personnel and/or cargo, the pressure in the cabin during the take-off will be pre-stressed. Therefore, whether the aircraft in which the electronic device is located can be judged to be in a take-off state by the takeoff air pressure. In the preferred embodiment, with reference to the technical data of a general civil aircraft, the first predetermined air pressure threshold is a barometric pressure value of 465 海拔 above sea level.

In an embodiment, the accelerometer unit 200 is further configured to sense a horizontal acceleration. More specifically, the air pressure sensing unit 300 is coupled to the processing unit 100, wherein the air pressure sensing unit 300 senses the first air pressure and the second air pressure according to the air pressure sensing command. The processing unit 100 determines whether the following condition is satisfied: [(second air pressure - first air pressure) / (sensing the time difference between the first air pressure and the second air pressure)] ≧ air pressure difference threshold, wherein when the determination result is YES, the processing unit 100 The horizontal acceleration sensing command is output; when the determination result is no, the processing unit outputs an acceleration sensing instruction.

The accelerometer unit 200 further senses the horizontal acceleration based on the horizontal acceleration sensing command. The processing unit determines whether the following conditions are true: horizontal acceleration ≧ horizontal acceleration threshold.

When the determination result is YES, the processing unit 100 generates a switching start flight mode command; when the determination result is no, the acceleration gauge unit 200 senses the first acceleration. In an embodiment, when the determination result is no, the processing unit 100 outputs an acceleration sensing instruction, and the acceleration gauge unit 200 senses the first acceleration according to the acceleration sensing instruction.

More specifically, in addition to the height change, the aircraft has a horizontal acceleration, so when the aircraft is measured to have a height change, it is further confirmed by the horizontal acceleration whether the aircraft in which the electronic device is located is in a climbing state.

In an embodiment, the processing unit 100 further senses the falling air pressure while generating the switch-on flight mode command. More specifically, the processing unit 100 generates a landing air pressure sensing command while generating a switch-on flight mode command, and the air pressure sensing unit 300 senses the landing air pressure according to the landing air pressure sensing command. The processing unit 100 determines the following Whether the piece is established: the landing pressure ≦ second predetermined air pressure threshold, when the judgment result is YES, the acceleration gauge unit 200 senses the second acceleration, and when the determination result is no, the air pressure sensing unit senses the landing air pressure again. More specifically, in an embodiment, when the determination result is yes, the processing unit 100 outputs a second acceleration sensing instruction, and the acceleration gauge unit 200 senses the second acceleration according to the second acceleration sensing instruction; when the determination result is Otherwise, the processing unit outputs a falling air pressure sensing command, and the air pressure sensing unit senses the falling air pressure again according to the falling air pressure sensing command.

Since the height can be calculated from the air pressure, the drop air pressure is sensed, which is substantially equivalent to the sense height. More specifically, when the landing of the aircraft is stopped, the ground height is 0, and the altitude of the landing site is less than a preset value, and the preset air pressure is the second predetermined air pressure threshold. Therefore, it is possible to determine whether the aircraft in which the electronic device is located is in a landing stop state by dropping the air pressure. In the preferred embodiment, with reference to the technical data of a general civil aircraft, the second predetermined air pressure threshold is a barometric pressure value of 100 海拔 above sea level.

After the acceleration gauge unit 200 senses the second acceleration according to the second acceleration sensing command, the processing unit determines whether the following condition is satisfied: the second acceleration=0, wherein when the determination result is YES, the processing unit 100 outputs the switching off the flight mode command. The electronic device switches to close the flight mode according to the switching off the flight mode command; when the determination result is no, the acceleration gauge unit 200 senses the second acceleration. More specifically, in an embodiment, when the determination result is no, the processing unit 100 outputs the second acceleration sensing instruction again, so that the acceleration gauge unit 200 senses the second acceleration according to the second acceleration sensing instruction.

More specifically, when the landing of the aircraft is stopped, the acceleration is zero, so that the second acceleration can be used to determine whether the aircraft in which the electronic device is located is in a landing stop state.

As shown in the embodiment of FIG. 2, the electronic device 900 of the present invention further includes a wireless communication module 400. The wireless communication module 400 includes communication modules that conform to mobile communication technology standards, IEEE 802.11 standards, Bluetooth standards, and the like. The wireless communication module 400 is coupled to the processing unit 100. When the electronic device 900 switches to the flight mode, the wireless communication module 400 is turned off. When the electronic device 900 switches to the flight mode, the wireless communication module 400 is turned on. More specifically, in this embodiment, the electronic device 900 is switched by Turn on or leave the flight mode to turn the wireless communication module 400 off or on. However, in various embodiments, the electronic device 900 can be turned off, turned on, or functionally adjusted by switching the on or off flight mode to other modules coupled to the processing unit.

The operation mode switching method of the present invention is further explained below. As shown in the flowchart of the embodiment shown in FIG. 3, the operation mode switching method of the present invention includes, for example, the following steps.

In step 1000, the first acceleration is sensed through the acceleration gauge unit. More specifically, as shown in the embodiment of FIG. 1 , the first acceleration of the electronic device 900 is sensed through the accelerometer unit 200 coupled to the processing unit 100 . The accelerometer unit 200 is included as a gravity sensor (G-Sensor).

Step 1500: The processing unit determines whether the following condition is true: a first acceleration ≧ acceleration threshold (condition 1)

More specifically, as shown in the embodiment shown in FIG. 1, the processing unit 100 receives the first acceleration that senses the self-acceleration gauge unit, and determines whether the above-described condition 1 is established by calculation. Wherein, the next step is performed when the judgment result is YES. In the preferred embodiment, step 1000 is performed when the determination is negative.

Further, the aircraft must be accelerated when taking off. Therefore, through steps 1000 and 1500, it can be determined whether the aircraft in which the electronic device is located is in a take-off state, and whether to perform the next step is determined. Among them, referring to the technical data of the general civil aircraft, the acceleration at takeoff is 2 m/s ² or more, so the acceleration threshold is preferably 2 m/s ² .

In step 2000, the first air pressure and the second air pressure are sensed by the air pressure sensing unit. More specifically, in the embodiment shown in FIG. 1 , the first air pressure and the second air pressure are sensed by the air pressure sensing unit 300 coupled to the processing unit 100 .

In step 2500, the processing unit determines whether the following condition is true: [(second air pressure - first air pressure) / (sensing the time difference between the first air pressure and the second air pressure)] ≧ air pressure difference threshold (condition 2)

More specifically, in the embodiment shown in FIG. 1 , the processing unit 100 receives the sensing time of the first air pressure, the second air pressure, and the two air pressures sensed from the air pressure sensing unit 300, and determines the above by calculation. Whether condition 2 is true. The next step is performed when the judgment result is YES. In the preferred embodiment, step 1000 is performed when the determination is negative.

Further, since the height can be calculated from the air pressure, the change in the air pressure per unit time is substantially equivalent to the change in height per unit time. More specifically, when the air pressure difference threshold is 0, and [(second air pressure - first air pressure) / (sensing the time difference between the first air pressure and the second air pressure)] ≧ air pressure difference threshold, indicating a height increase, that is, The electronic device is located in an aircraft that is in a climbing state. Therefore, through step 2000 and step 2500, it can be determined whether the aircraft where the electronic device is located is in a climbing state, and whether to perform the next step is determined.

In step 3000, the electronic device switches to activate a flight mode. More specifically, the electronic device can turn off or turn on the wireless communication module by switching on or off the flight mode. However, in various embodiments, the electronic device can be turned off, turned on, or functionally adjusted by switching the on or off flight mode to other modules coupled to the processing unit.

In summary, according to the operation mode switching method of the present invention, the electronic device can automatically switch to the flying mode when the aircraft is taken off and climbs, without manual setting by the user, so that the electronic device has better usability. Observing from different angles, the aircraft must first accelerate and then climb when taking off. Therefore, the operation mode switching method of the present invention determines whether the aircraft is accelerated by steps 1000 and 1500, and then judges whether the aircraft climbs in steps 2000 and 2500, as an electronic device. The basis for switching the flight mode is not only effective but also avoids misjudgment and causes the electronic device to switch to the flight mode.

As shown in FIG. 4A and FIG. 4B, the operation mode switching method of the present invention further includes step 1700 and step 1800 between step 1500 and step 2000.

At step 1700, the takeoff air pressure is sensed by the air pressure sensing unit. More specifically, as shown in the embodiment of FIG. 1, the air pressure sensing unit 300 coupled to the processing unit 100 senses the takeoff air pressure.

In step 1800, it is determined by the processing unit whether the following conditions are met: takeoff pressure ≧ first predetermined air pressure threshold (condition 3)

More specifically, as shown in the embodiment shown in FIG. 1, the processing unit 100 receives the takeoff air pressure sensed from the air pressure sensing unit 300, and determines whether the above listed condition 3 is established by calculation. The next step is performed when the judgment result is YES. In the preferred embodiment, step 1000 is performed when the determination is negative.

Further, in order to ensure the safety of personnel and / or goods, the aircraft is starting The pressure in the flight space will be pre-pressurized. Therefore, through steps 1700 and 1800, it can be determined whether the aircraft in which the electronic device is located is in a take-off state. In other words, in order to determine whether the aircraft in which the electronic device is located is in a take-off state, in addition to the steps 1000 and 1500, steps 1700 and 1800 may be added as duplicate confirmations to reduce false positives (for example, the high-speed railway in the acceleration is misjudged as The plane is at the takeoff.) Wherein, referring to the technical data of the general civil aircraft, the first predetermined air pressure threshold is preferably an air pressure value of 465 海拔 above sea level.

As shown in the flowchart of the different embodiments shown in FIG. 4A and FIG. 4B, the operation mode switching method of the present invention further includes step 2700 and step 2800 between step 2500 and step 3000.

In step 2700, the horizontal acceleration is sensed through the acceleration gauge unit. More specifically, as shown in the embodiment of FIG. 1, the acceleration level unit 200 coupled to the processing unit 100 senses the horizontal acceleration.

Step 2800, the processing unit determines whether the following condition is true: horizontal acceleration ≧ horizontal acceleration threshold (condition 4)

More specifically, as in the embodiment shown in FIG. 1, the processing unit 100 receives the sensed horizontal acceleration of the self-acceleration gauge unit 200, and determines whether the above-described condition 4 is established by calculation. The next step is performed when the judgment result is YES. In the preferred embodiment, step 1000 is performed when the determination is negative.

Further, in addition to the height change, the aircraft must have a horizontal acceleration, so when measuring the altitude change of the aircraft, it can be further confirmed by the horizontal acceleration whether the aircraft where the electronic device is located is in a climbing state. In other words, in order to determine whether the aircraft in which the electronic device is located is in a climbing state, in addition to step 2000 and step 2500, step 2700 and step 2800 may be added as duplicate confirmation to reduce misjudgment (for example, a high-speed high-rise elevator in a climbing position) Misjudged as the plane in the climb).

As shown in FIG. 4A and FIG. 4B, the operation mode switching method of the present invention further includes step 4000, step 4500, step 5000, step 5500, and step 6000 after step 3000.

In step 4000, the landing pressure is sensed by the air pressure sensing unit. More specifically, as shown in the embodiment of FIG. 1, the air pressure sensing unit 300 coupled to the processing unit 100 senses the falling air pressure.

In step 4500, it is determined by the processing unit whether the following conditions are met: the falling pressure ≦ the second predetermined air pressure threshold (condition 5)

More specifically, as shown in the embodiment shown in FIG. 1, the processing unit 100 receives the sensed drop pressure from the air pressure sensing unit 300, and determines whether the above listed condition 5 is established by calculation. The next step is performed when the judgment result is YES. In the preferred embodiment, step 4000 is performed when the determination is negative.

Further, when the landing of the aircraft is stopped, the ground height is 0, and the altitude of the landing site is less than a preset value, and the preset air pressure is the second predetermined air pressure threshold. Therefore, through steps 4000 and 4500, it can be determined whether the aircraft where the electronic device is located is in a landing stop state. Wherein, referring to the technical data of the general civil aircraft, the second predetermined air pressure threshold is a pressure value of 100 海拔 above sea level.

In step 5000, the second acceleration is sensed through the acceleration gauge unit. More specifically, as shown in the embodiment of FIG. 1, the second acceleration is sensed by the accelerometer unit 200 coupled to the processing unit 100.

Step 5500, the processing unit determines whether the following condition is true: the second acceleration=0 (condition 6)

More specifically, as shown in the embodiment shown in FIG. 1, the processing unit 100 receives the second acceleration that senses the self-acceleration gauge unit 200, and determines whether the above-described condition 6 is established by calculation. The next step is performed when the judgment result is YES. In the preferred embodiment, step 5000 is performed when the determination is negative.

Further, when the landing of the aircraft is stopped, the acceleration is 0. Therefore, through steps 5000 and 5500, it can be determined whether the aircraft where the electronic device is located is in a landing stop state.

In step 6000, the electronic device switches to turn off the flight mode. In summary, through the step 4000, the step 4500, the step 5000, the step 5500, and the step 6000, the operation mode switching method of the present invention can automatically switch the off-air mode when the aircraft is landed and stopped, without the user Manual setting for increased ease of use.

While the foregoing description of the preferred embodiments of the invention, the embodiments of the invention The spirit and scope of the principles of the invention. Modifications of many forms, structures, arrangements, ratios, materials, components and components can be made by those skilled in the art to which the invention pertains. Therefore, the embodiments disclosed herein should It is intended to be illustrative of the invention and not to limit the invention. The scope of the present invention is defined by the scope of the appended claims, and the legal equivalents thereof are not limited to the foregoing description.

Claims (17)

An operating mode switching method for use in an electronic device, wherein the electronic device includes a processing unit, an accelerometer unit, and a barometric sensing unit, the operating mode switching method includes the step of: sensing one through the accelerometer unit The first acceleration is determined by the processing unit: the first acceleration is an acceleration threshold; when the determination result is YES, the first air pressure and the second air pressure are sensed by the air pressure sensing unit; The processing unit determines whether the following condition is true: [(the second air pressure - the first air pressure) / (sensing the time difference between the first air pressure and the second air pressure)] a pressure difference threshold; when the judgment result is yes, Sensing a horizontal acceleration through the acceleration gauge unit; determining, by the processing unit, whether the condition is: the horizontal acceleration ≧ a horizontal acceleration threshold; and when the determination result is YES, the electronic device switches to start a flight mode. The operation mode switching method of claim 1, wherein the processing unit determines whether the following condition is satisfied: the first acceleration ≧ the acceleration threshold, and when the determination result is no, performing the transmitting the acceleration unit to sense the first An acceleration step. The operation mode switching method according to claim 1, wherein the processing unit determines whether the following condition is satisfied: [(the second air pressure - the first air pressure) / (sensing the time difference between the first air pressure and the second air pressure) And ≧ ≧ the air pressure difference threshold, when the determination result is no, the step of sensing the first acceleration through the acceleration gauge unit is performed. The operation mode switching method of claim 1, wherein after the step of determining, by the processing unit, the condition that the first acceleration ≧ the acceleration threshold is established, the method further comprises: sensing the flying air pressure through the air pressure sensing unit; The processing unit determines whether the following condition is met: the takeoff air pressure is a first predetermined air pressure threshold, and when the determination result is YES, the processing unit determines [(the second air pressure - the first air pressure) / (senses the first The time difference between one air pressure and the second air pressure)) 是否 Is the condition of the air pressure difference threshold established? The operation mode switching method of claim 4, wherein the processing unit determines whether the following condition is true: The takeoff air pressure is the first predetermined air pressure threshold. When the determination result is no, the step of sensing the first acceleration through the acceleration gauge unit is performed. The operation mode switching method of claim 4, wherein the first predetermined air pressure threshold is a gas pressure value of an altitude of 465 。. The operation mode switching method of claim 1, wherein the processing unit determines whether the following condition is met: the horizontal acceleration ≧ a horizontal acceleration threshold, and when the determination result is no, performing the transmitting the acceleration metric unit to sense the first An acceleration step. The operation mode switching method of claim 1, wherein after the step of switching the electronic mode to start the flight mode, the method further includes the step of: sensing a drop air pressure through the air pressure sensing unit; and determining, by the processing unit, the following condition Whether it is established: the landing pressure is a second predetermined air pressure threshold; when the determination result is yes, a second acceleration is sensed through the acceleration gauge unit; and the processing unit determines whether the following condition is true: the second acceleration=0; And when the judgment result is YES, the electronic device switches to turn off the flight mode. The operation mode switching method of claim 8, wherein the processing unit determines whether the following condition is satisfied: the landing pressure ≦ the second predetermined air pressure threshold, and when the determination result is no, performing the sensing through the air pressure sensing unit The step of measuring the drop pressure. The operation mode switching method of claim 8, wherein the processing unit determines whether the following condition is met: the second acceleration=0, and when the determination result is no, performing the sensing of a falling air pressure through the air pressure sensing unit The steps. An electronic device includes: an accelerometer unit for sensing a first acceleration and a horizontal acceleration; a barometric sensing unit for sensing a first air pressure and a second air pressure; and a processing unit coupled Connected to the accelerometer unit and the air pressure sensing unit, the processing unit determines whether the following condition is met: the first acceleration is an acceleration threshold, and when the determination result is yes, the processing unit determines whether the following condition is satisfied; [(the second air pressure - the first air pressure) / (sensing the time difference between the first air pressure and the second air pressure)] ≧ a pressure difference threshold, when the determination result is YES, the processing unit further determines whether the following conditions are Set up: the horizontal acceleration ≧ a horizontal acceleration threshold. When the judgment result is YES, the processing unit generates a switching start flight mode command. The electronic device of claim 11, wherein: the air pressure sensing unit is further configured to sense a flying air pressure, and the processing unit further determines whether the following condition is met: the take-off air pressure is a first predetermined air pressure threshold, and the determination result is In the case of YES, the air pressure sensing unit senses the first air pressure and the second air pressure, and when the determination result is no, the acceleration gauge unit senses the first acceleration. The electronic device of claim 11, wherein: the processing unit senses whether the following condition is met: the horizontal acceleration is a horizontal acceleration threshold, and the determination result is no, the acceleration gauge unit senses the first acceleration. The electronic device of any one of claims 11 to 13, wherein the first predetermined air pressure threshold is an air pressure value at an altitude of 465 。. The electronic device of any one of claims 11 to 13, wherein the electronic device switches to turn on a flight mode according to the switching on the flight mode command. The electronic device of any one of claims 11 to 13, wherein: the processing unit further senses a drop air pressure while generating the switch-on flight mode command, and the processing unit determines the following condition Is it established: the landing pressure is a second predetermined air pressure threshold, and when the determination result is YES, the acceleration gauge unit senses a second acceleration, and when the determination result is no, the air pressure sensing unit senses the falling air pressure; And the processing unit determines whether the following condition is met: the second acceleration=0, when the determination result is yes, the processing unit outputs a switching off flight mode command, and when the determination result is no, the acceleration gauge unit senses the Second acceleration. The electronic device of claim 16, wherein the electronic device switches according to the switching off the flight mode command Turn off the flight mode.