JP2980815B2 - Power supply control device for radio - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a power supply control device for a wireless device which controls power supply to a wireless device mounted on an aircraft as a moving object.

[0002]

2. Description of the Related Art For example, when a ground guidance person gives a guidance instruction to an aircraft pilot or performs maintenance and inspection of an aircraft, a hand signal has been generally used. Guidance instructions by voice in wired communication are being issued. In this wired communication, ICS (Inter Communication System) provided in the cockpit of the aircraft
, And a portable wired communication device carried by an instructor can communicate with each other via a wired communication line. In this case, the instructor connects both wired communication devices by connecting the connector of the portable wired communication device to the external connection connector provided near the cockpit of the body.

[0003]

However, this communication system has the following problems. First, due to the wired communication, the guidance staff may not be able to give accurate guidance instructions because their movements are restricted by cables. Second, there is a case where the portable wired communication device connected to the external connection connector of the aircraft is forgotten to be removed. In this case, there is a danger that a serious accident would be caused if the aircraft would fly as it was. I'm crazy. Third, it is difficult and dangerous to connect a portable wired communication device to an external connector provided near a cockpit that is several meters above the ground.

[0004] As a means for solving this problem, it is conceivable to use a pair of wireless devices instead of the wired communication device to give a guidance instruction by wireless communication. However, when the wireless device is energized, unnecessary spurs are constantly radiated from the local oscillator of the receiver and the like, which may interfere with other electronic devices mounted in the cockpit. Occurs. In this case, it is conceivable that the pilot could manually supply power to the radio only when receiving guidance from the pilot, but in manual operation, the power would remain on even during flight. Therefore, at present, no guidance instruction is given by the wireless device. It is also possible to output the instrument data relating to the movement state such as during flight and landing from the aircraft instrument and control the power supply of the radio based on the instrument data. Is connected, there is a possibility that the meter may be adversely affected.

[0005] The present invention has been made in view of the above problems, and has been made in view of the aviation while ensuring the convenience of wireless communication.
The power supply to the onboard radio to the machine, without affecting the aircraft, and to provide a power control device for a radio that can be reliably controlled according to the moving state of the aircraft to its intended .

[0006]

According to a first aspect of the present invention, there is provided a power supply control apparatus for a wireless device , comprising:
A power control device for a wireless device mounted on an aircraft and controlling power supply to a wireless device mounted on the aircraft , and a detection sensor for detecting at least one of a moving speed and a moving acceleration of the aircraft , A control unit that controls power supply to the wireless device based on the detected detection signal.

According to a second aspect of the present invention, there is provided a power supply control device for a wireless device.
The power supply control device according to claim 1 Symbol mounting radio, control unit after supplying power to the radio, the wireless device facing the counterparty radio, the communicable data for notifying the communication enabled state The transmission is controlled via a wireless device.

According to a third aspect of the present invention, there is provided a power supply control device for a wireless device.
The power supply control device radio of claim 1, wherein the detection sensor is at least one of both the moving speed and both the movement acceleration of the aircraft with respect to each of the direction crossing the direction to be the direction and the movement to be movement of the aircraft The control unit controls power supply to the wireless device based on the detected detection signal.

[0009]

According to the power supply control device for a wireless device according to the first aspect, when the aircraft moves, the detection sensor detects at least one of the moving speed and the moving acceleration of the aircraft , and the control unit performs the detected detection. The power supply to the wireless device is controlled based on the signal. For this reason, for example, the control unit stops the power supply to the wireless device when the detection sensor detects the moving speed or the moving acceleration equal to or more than a predetermined value, and when the detection sensor detects the moving speed or the moving acceleration equal to or less than the predetermined value, For example, power supply to a wireless device mounted on the aircraft is controlled according to the moving state of the aircraft , such as supplying power to the aircraft . As a result, when the aircraft is moving, because the radio positively becomes inoperative, thus liable to occur Kou etc. spurious radiation of the local oscillator of the receiver
Results such as interference with advanced other electronic devices of the air motor is reliably prevented, serious aircraft accidents is prevented.

According to the power supply control device of the radio of claim 2, wherein the control unit, after supplying power to the radio, the wireless device facing the counterparty radio, to transmit communicable data Because of the control, the other party can know that the aircraft- side wireless device is ready for communication.

According to the power control device for wireless machine according to claim 3, wherein the detection sensor, so detects the moving speed and movement acceleration of the aircraft with respect to each of the direction intersecting the movement direction and the movement direction of the aircraft, for example, If the aircraft is moving in a direction other than the direction in which it should move due to lift, wind, etc., or turning,
The control unit controls power supply to the wireless device based on at least one of the two moving speeds and the two moving accelerations of the aircraft in each of the two directions. For this reason, power supply to the wireless device is controlled more accurately according to the moving state of the aircraft . Further, the control unit, for example, by controlling the power supply to the wireless device based on at least one of the combined movement speed and the combined movement acceleration calculated based on both movement speed and both movement acceleration for each of the two directions,
More precisely, the power supply can be controlled according to the moving state of the aircraft .

[0012]

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a block diagram showing a power supply control device for a radio device according to an embodiment of the present invention.

FIG. 1 shows a block diagram of a wireless communication system 1 for an aircraft. This aircraft radio communication system 1
The wireless device 1a is provided in a cockpit of an aircraft (not shown) and a portable wireless device (the other party's wireless device) 5 carried by the guideman. The wireless device 1a is a wireless device (power control of the wireless device). Device) 2 and a power supply device 4. The control unit 12 of the wireless device 1a, which will be described later,
Connected to CS3.

In this aircraft radio communication system 1, radio communication is performed between a pilot in the aircraft and a ground guidance person using the radio device 1a and the portable radio device 5 at the time of takeoff and landing of the aircraft. In addition to the above, the guide man can guide the aircraft to a predetermined runway and a parking area, and the maintenance staff on the aircraft and the ground maintenance staff can communicate with each other when performing maintenance and inspection of the aircraft. It has become. In this case, when the aircraft is in a landing state, the wireless device 1a automatically supplies power to a later-described transmitting / receiving unit (radio device) 11 in the wireless device 2 to make the transmitting / receiving unit 11 communicable, When the aircraft takes off, control is performed so that the supply of power to the transmitting / receiving unit 11 is automatically stopped so that the spurious radiation does not adversely affect the flight due to interference with the instruments of the aircraft.

The wireless device 2 performs a transmission / reception unit 11 capable of transmitting / receiving an FM signal, transmission / reception control including switching of transmission / reception of the transmission / reception unit 11, and control of the transfer of a microphone signal and a voice signal to / from the ICS 3. The control unit 12 includes a control unit 12 and a sensor unit 13 that detects a moving acceleration of the aircraft during flight and gliding and outputs a detection signal to the control unit 12. In addition, the ICS 3 can communicate with each other by the headset 44 (see FIG. 3) between the pilot and the crew. In this embodiment, the ICS 3 is configured so that the pilot and the crew can communicate with each other. Have been. Further, the power supply device 4 is a device for supplying power to the transmission / reception unit 11, and the supply of power is controlled automatically by the control unit 12 and also by manual operation of the pilot.

Next, the control section 12 and the sensor section 13 will be described in detail with reference to FIG.

The control unit 12 includes a CPU 21, a ROM 22,
RAM 23, encoder / decoder 24, parallel I
An / O unit 25, a display unit 26, an operation unit 27, electronic switches 28 and 29, and a power switch 30 are provided.

The CPU 21 controls the operation of the wireless device 2 such as calculating the moving speed based on the detection signal output from the sensor unit 13 and controlling the transmission and reception of the transmitting and receiving unit 11 and controlling the power supply of the transmitting and receiving unit 11 based on the moving acceleration and the calculated moving speed. Centrally control all operations. The ROM 22 includes an operation program of the CPU 21, communicable data for notifying the portable wireless device 5 that the transmission / reception unit 11 has become communicable, and a control unit 53 of the portable wireless device 5 (see FIG. 2). And activation data for activating. Also, the RAM 23
Temporarily stores the data of the moving acceleration output from the sensor unit 13 and the data of the moving speed after the calculation via the CPU 21.

The encoder / decoder 24 receives data output from the CPU 21 via the bus line, for example,
The device number data of the called portable radio device 5 and the communicable data described above are coded into a predetermined code (digital modulation input) such as a tone signal, and output to a modulator (not shown) of the transmission / reception unit 11 and the modulator. , For example, a message or a code of an aircraft body number (digital modulation output) is decoded into digital data and output to the CPU 21.

The parallel I / O section 25 is an interface circuit, and under the control of the CPU 21, ON signals to the electronic switches 28 and 29 and the power switch 30, transmission / reception frequency data to the transmission / reception section 11, transmission / reception section 11 From CPU to CPU 21 and from ICS3 to CPU
The transfer of the press signal to 21 is performed.

The display unit 26 displays the moving acceleration and moving speed of the aircraft in each of three axial directions described later, and the transmitting / receiving unit 11.
The LCD displays information such as the power on / off state and the transmission state of communicable data. The operation unit 27 is for controlling the transmission / reception unit 11 and the like by manual operation, and specifically, controls power supply to the transmission / reception unit 11, zero-speed reset control for moving speed described later, transmission control for communicable data, and the like. There are provided operation switches for manually operating the. The electronic switches 28 and 29 turn on / off the transmission of the microphone signal and the audio signal between the transmission / reception unit 11 and the ICS 3, and the power switch 30 supplies power from the power supply device 4 to the transmission / reception unit 11. Turn on / off. The electronic switch 2
When the switches 8 and 29 are off, the impedance as viewed from the ICS3 side is high impedance so as not to affect the ICS3.

On the other hand, the sensor unit 13 described above
1 and a signal processing unit 42. Sensor 41
Is an acceleration sensor based on a so-called semiconductor strain gage method, in which three piezo elements are arranged in three directions orthogonal to each other in a front direction (direction to be moved), a lateral direction and a vertical direction of an aircraft (hereinafter, referred to as a “three axis direction”) ) Is output in such a manner as to output a voltage proportional to the distortion received, thereby detecting the moving acceleration applied to the aircraft in each of the three axial directions by an analog value. In addition, the signal processing unit 42 includes a DSP (Digital Sign).
After amplifying the moving acceleration signal in each of the three axial directions output from the sensor 41, the signal is converted into digital data and output to the CPU 21.

Next, the portable wireless device 5 will be described with reference to FIG.

The portable radio device 5 comprises an antenna 51, a transmission / reception unit 52, a control unit 53, a display unit 54, and a speaker 55.

The transmission / reception unit 52 receives a radio signal transmitted by the radio device 1a via the antenna 51 or transmits a radio signal to the radio device 1a via the antenna 51.
The control unit 53 outputs a predetermined alarm sound to the speaker 55 when transmission / reception switching of the transmission / reception unit 52, transmission / reception frequency switching, and transmission of communicable data from the wireless device 1a is performed. It performs alarm sound control to display the contents of the alarm.

Next, aircraft guidance control in the aircraft radio communication system 1 will be described.

When a power switch (not shown) is turned on,
The control unit 12 is energized, and the CPU 21 performs a vector operation on the acceleration of the sensor 41 in each of the three axial directions, which is input via the signal processing unit 42, and performs a combined movement acceleration with respect to the direction in which the aircraft is moving. Is calculated, and the resultant moving speed is integrated to calculate the resultant moving speed of the aircraft, that is, the moving speed of the aircraft.

When the aircraft is in a landing state, the sensor 41
However, since the moving acceleration data of the negative value is gradually output, the calculated combined moving speed gradually approaches “0”.
In this case, when the combined movement speed becomes equal to or less than a predetermined value (for example, a speed lower than the stall speed of the aircraft) after the combined movement acceleration reaches a predetermined value (for example, an acceleration close to the acceleration at the time of maximum deceleration), The CPU 21 outputs power-on data to the parallel I / O unit 25.

The parallel I / O unit 25 includes a power switch 3
An "L" signal is output to 0, and the power switch 30 is turned on. Thereby, power is automatically supplied from the power supply device 4 to the transmission / reception unit 11. Further, the CPU 21 includes a display unit 26
To turn on the power of the transmitting / receiving section 11. When using a frequency synthesizer for the local oscillator of the receiver,
When the conditions of the moving acceleration and the moving speed are met, the power-on data is not output immediately, but the internal timer is operated, and the power-on data is output when a predetermined time has elapsed. This is because the local oscillator oscillates at various frequencies until the frequency locks, so that the power is supplied to the transmission / reception unit 11 after the aircraft has finished gliding to reduce the effect on the flight of the aircraft. This is because it is preferable.

When the transmission / reception unit 11 is energized, the CPU
21 outputs the transmission / reception frequency data via the parallel I / O unit 25, and oscillates the transmission local frequency and the reception local frequency at predetermined frequencies. Also, CPU
The 21 outputs an “H” signal to the electronic switch 29 via the parallel I / O unit 25, and outputs the audio signal received by the transmission / reception unit 11 to the ICS 3. Next, the CPU 21
After reading the communicable data from the ROM 22, it outputs a press signal (control data) as a transmission / reception switching signal to the transmission / reception unit 11 via the parallel I / O unit 25, and outputs the same via the encoder / decoder unit 24. , And outputs communicable data to the transmission / reception unit 11. Thus, a wireless signal modulated by the communicable data is automatically output via the antenna 43.

Thereafter, every time the CPU 21 receives a press signal from the ICS 3 via the parallel I / O unit 25, the CPU 21 outputs a press signal to the transmission / reception unit 11 via the parallel I / O unit 25, "H" on the expression switch 28
A signal is output, and a microphone signal from the ICS 3 is output to the transmission / reception unit 11.

When the control unit 53 of the portable radio device 5 receives the communicable data via the transmission / reception unit 52, the control unit 53
5 to output a predetermined alarm sound, and display on the display unit 54 that the transmission / reception unit 11 on the aircraft side is ready for communication. As a result, the guide member can know that the aircraft to be guided has landed and is ready for communication, and can guide the aircraft by wireless communication.

When the aircraft lands and stops, the CP
The composite moving speed calculated by U21 should indicate "0", but there are cases where errors in the integration operation are accumulated and the composite moving speed does not become "0". In this case, by operating the movement speed zero reset switch of the operation unit 27, the calculated combined movement speed can be reset to “0”. As a result, the accumulated error of the speed calculation can be eliminated.

On the other hand, when the aircraft takes off, contrary to the landing, the CPU 21 determines that the synthetic movement acceleration is a predetermined acceleration (for example, an acceleration smaller than the maximum acceleration at takeoff) and the synthetic movement speed is a predetermined acceleration. Until the speed (for example, a speed lower than the stall speed) is exceeded, the transmission / reception unit 11 is kept energized, and if it is determined that the combined acceleration and the combined movement speed have reached the predetermined acceleration and speed, the parallel I An “H” signal is output to the power switch 30 via the / O unit 25. As a result, supply of power to the transmission / reception unit 11 of the power supply device 4 is automatically stopped, unnecessary radio waves such as local oscillation are not radiated from the transmission / reception unit 11, and interference with advanced electronic equipment of the aircraft is eliminated. Can be.

The wireless device 1a is controlled so that the manual operation of the operation unit 27 is given priority. Specifically, for example, even when the combined movement acceleration has not reached the predetermined acceleration and the calculated combined movement speed has not reached the predetermined speed, the power switch of the operation unit 27 is turned off. The CPU 21 detects this, outputs an “H” signal to the power switch 30 via the parallel I / O unit 25, and stops the supply of power from the power supply device 4 to the transmission / reception unit 11. After the power supply control is manually performed once, the manual priority control is released, and the automatic power supply control based on the sensor signal from the sensor unit 13 is performed again.

As described above, according to the present embodiment, the CPU
When detecting that the aircraft has taken off and has attained the combined movement acceleration and combined movement speed that are equal to or greater than the predetermined value, the power supply to the transmitting / receiving unit 11 is stopped. As a result, the transmission / reception unit 11
Is inactive, and interference with other electronic devices in the cockpit due to spurious radiation of the local oscillator of the transmission / reception unit 11 is reliably prevented.

After the CPU 21 supplies power to the transmission / reception unit 11, the CPU 21 controls the portable radio device 5 opposite to the transmission / reception unit 11 to transmit communicable data. Can communicate with each other, that is, the aircraft is in a take-off / landing state. Furthermore, since the CPU 21 calculates the combined movement speed and combined movement acceleration for each of the three axial directions and controls the power supply to the transmission / reception unit 11, the aircraft receives lift, wind, or the like, or moves by turning. The power supply to the transmission / reception unit 11 is controlled more accurately according to the flight and gliding state of the aircraft, for example, when the vehicle is moving in a direction other than the direction in which it should be performed or receiving a moving acceleration.

Note that the sensor 41 is not limited to the one that detects the moving acceleration in the three axis directions, but may be one that detects the acceleration in one direction or two directions intersecting each other. In this case, the CPU 21 controls power supply to the transmission / reception unit 11 based on the moving acceleration in one or two directions and / or the moving speed calculated based on the moving acceleration. Furthermore, a speed sensor may be used instead of the acceleration sensor, and power supply may be controlled based on at least one of the detected speed and the acceleration differentiated from the speed. Furthermore, the acceleration sensor is not limited to the semiconductor strain gauge method,
A capacitance type, a servo type, a metal strain gauge type, and a piezoelectric type may be used.

When the vehicle is about to land, the integrated travel speed from the time when the combined travel speed reaches a set speed near the speed lower than the stall speed of the aircraft is integrated, and the calculated flight distance information or the slippage is calculated. When the distance information reaches a predetermined value (for example, 1 km), power may be supplied to the transmitting / receiving unit 11. However, in this case, when the movement acceleration continuously increases, the CPU 21 stops the power supply because the aircraft is in the state of takeoff again.

If the moving speed displayed on the display unit 26 is different from the flight speed indicated by the instrument of the aircraft, it may be configured so that correction can be made by manual operation, The moving speed may be reset to zero based on a reset signal or an incoming signal (such as a squelch signal, an RSSI signal, and a voice signal).

Further, the radio 2 and the portable radio 5
Is not limited to the simplex-type wireless device described in the present embodiment, but may be a duplex-type wireless device. Further, the two transceiver transceivers 11 and 52 can employ any modulation scheme. Also, a circuit (so-called VOX circuit) for automatically generating a press signal based on the audio signal output of the headset of the ICS 3 is provided by the control unit 12.
And the transmission / reception switching of the transmission / reception unit 11 may be controlled by the press signal.

Further, the wireless device 1a is a portable wireless device 5
May be configured to control on / off of the power supply of the transmitting / receiving unit 52. Specifically, in the normal state, the transmission / reception unit 52 is set to the intermittent operation mode, and after the wireless device 2 is turned on, the CPU 21 reads out the start data from the ROM 22, and the encoder / decoder unit 24 and the transmission / reception unit 11 By sending activation data via
The control unit 53 that has received the activation data may control the transmission and reception unit 52 to operate continuously. In this case, the operation unit 2
7, the start data may be transmitted by manual operation. Note that the control unit 53 may be set to the sleep mode at the normal time, and the control unit 53 may be set to the normal operation mode by the squelch signal or the RSSI signal. As described above, the current consumption of the portable wireless device 5 can be reduced.

In addition, although the embodiments have been described by taking an aircraft as an example in the embodiments, the invention is not limited to this, and the present invention can also be applied to mobiles such as automobiles. The aircraft in the present invention is a concept including an airplane, a helicopter, an airship, and the like.

[0044]

As described above, according to the power supply control device for a wireless device of the present invention, the detection sensor detects at least one of the moving speed and the moving acceleration of the aircraft , and the control unit controls the wireless device based on the detection signal. Since the power supply to the wireless device is controlled, forgetting to turn off or turn on the power of the wireless device can be prevented. As a result, when the aircraft is moving, the wireless device is definitely in a non-operating state, so that it is possible to prevent interference with other electronic devices in the cockpit due to spurious radiation of the local oscillator of the receiver. Also, when communication by the wireless device is required, such as when the aircraft is stopped, power can be automatically supplied to the wireless device.

Further, after the control unit, which supplies power to radio, the wireless device facing the counterparty radio, for controlling to transmit the communicable data, the other party, aviation
It is possible to know that the machine- side wireless device is ready for communication.

Further, the detection sensor detects the direction to move,
And at least one of the two moving speeds and the two moving accelerations in each of the directions intersecting the direction, the moving state of the aircraft can be detected more accurately. As a result, the control unit can more accurately control the power supply to the wireless device according to the moving state of the aircraft .

[Brief description of the drawings]

FIG. 1 is a block diagram of an aircraft wireless communication system 1 according to an embodiment of the present invention.

FIG. 2 is a block diagram of a portable wireless device according to an embodiment of the present invention.

FIG. 3 is a block diagram of a wireless device according to an embodiment of the present invention.

[Explanation of symbols]

 1a Wireless device 2 Wireless device 4 Power supply device 5 Portable wireless device 11 Transmitter / receiver unit 12 Control unit 13 Sensor unit 21 CPU 41 Sensor

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. ⁶ , DB name) H04B 7/26 H04Q 7/00-7/38

Claims (3)

(57) [Claims] Claims: 1. An aircraft mounted on a moving body ,
A power supply control device of the radio to control the power supply to the onboard radio aircraft, a sensor for detecting at least one of the moving speed and movement acceleration of the aircraft, based on the detected detection signal And a control unit for controlling power supply to the wireless device. 2. The control unit, after supplying power to the wireless device, controls a counterpart wireless device facing the wireless device.
Power control device 1 Symbol mounting radio claims the communicable data for notifying the communication enabled state and controls to transmit via the radio. Wherein the detection sensor is configured to detect at least one of both the moving speed and both the movement acceleration of the aircraft with respect to the direction of each intersecting the direction to be the direction and the movement to be movement of the aircraft the control unit may, according to claim 1, characterized in that to control the power supply to the radio on the basis of the detected detection signal or
3. The power supply control device for a wireless device according to 2.