CN108557095B - Double-member audio system for general-purpose aircraft - Google Patents
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
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Abstract
The invention discloses a double-member audio system for a general-purpose airplane, which can improve the integration level and reliability of an airborne audio system and reduce the overall weight. The system comprises: the system comprises an audio control unit, a front cabin audio control panel, a rear cabin audio control panel, two very high frequency radio stations, a data processor, navigation equipment, headsets and corresponding microphone preamplification components, wherein the headsets and the microphone preamplification components are respectively installed in the front cabin and the rear cabin; the audio control unit is respectively connected with the front cabin audio control panel and the rear cabin audio control panel through two paths of serial interfaces to receive and/or send control signals, and is respectively connected with the front cabin audio control panel and the rear cabin audio control panel through two paths of discrete quantity interfaces to receive audio control source selection signals; the audio control unit is respectively connected with the two VHF radio stations through two paths of serial interfaces to receive and/or send control signals, and is respectively connected with the two VHF radio stations through two paths of analog signal interfaces to receive and/or send analog audio signals.
Description
Technical Field
The invention relates to the technical field of airborne radio of aircrafts, in particular to a double-member audio system for a general-purpose airplane.
Background
With the development of avionic technology, the functions required to be realized by an airborne radio system become increasingly complex, and a comprehensive radio system used on an airplane bears various functions such as airplane internal conversation, external communication, navigation sound listening, warning sound monitoring and the like. However, the existing airborne audio system has a complex structure and is dispersed, so that the size and the weight of the existing airborne audio system are large, the communication reliability inside and outside the aircraft is low, and the existing airborne audio system cannot be applied to small-sized general-purpose aircraft with higher requirements on flexibility, total weight of the aircraft body and reliability.
Disclosure of Invention
It is an object of the present invention to overcome at least the above problems of the prior art and to provide a dual member audio system for a general purpose aircraft that improves the integration and reliability of the onboard audio system while reducing the overall weight.
In order to achieve the above object, the present invention adopts the following aspects.
A dual member audio system for a general purpose aircraft, comprising: the system comprises an audio control unit, a front cabin audio control panel, a rear cabin audio control panel, two very high frequency radio stations, a data processor, navigation equipment, headsets and corresponding microphone preamplification components, wherein the headsets and the microphone preamplification components are respectively installed in the front cabin and the rear cabin;
the audio control unit is respectively connected with the front cabin audio control panel and the rear cabin audio control panel through two paths of serial interfaces to receive and/or send control signals, and is respectively connected with the front cabin audio control panel and the rear cabin audio control panel through two paths of discrete quantity interfaces to receive audio control source selection signals;
the audio control unit is respectively connected with the two VHF radio stations through two paths of serial interfaces to receive and/or send control signals, and is respectively connected with the two VHF radio stations through two paths of analog signal interfaces to receive and/or send analog audio signals;
the audio control unit is connected with a data processor in the airborne integrated radio system through a serial interface to receive and/or send control signals, and is connected with the data processor through a discrete quantity interface to receive emergency control signals;
each navigation unit in the navigation equipment is respectively connected with the audio control unit through one path of analog signal interface so as to respectively send navigation audio signals to the audio control unit, and is respectively connected with the audio control unit through one path of serial interface so as to receive control signals;
the microphones installed in the front cabin and the rear cabin are respectively connected with a microphone preamplifier assembly, and each microphone preamplifier assembly is connected with the audio control unit through an analog signal interface so as to receive and/or send analog audio signals; each microphone preamplifier assembly is connected with the audio control unit through a discrete signal interface to receive emergency control signals;
the audio control unit is connected with the flight parameter recorder through two analog signal interfaces so as to send audio signals of the front cabin and the rear cabin to the audio control unit.
Preferably, the audio control unit is configured to open an in-phone call channel according to the in-phone call request signal, receive audio collected by a headset in one cabin according to the PTT key signal, and send the received audio to the headset in another cabin through the in-phone call channel via the microphone preamplifier assembly.
Preferably, the audio control unit is configured to open a channel of a communication frequency corresponding to the selected vhf radio station according to the radio station selection signal, receive an audio collected by an earphone in one cabin according to the PTT key signal, and send the received audio to the ground radio station or another airplane through a transmitter of the corresponding vhf radio station.
Preferably, the audio control unit is used for receiving audio signals from ground radio stations or other airplanes, and sending the audio signals from the very high frequency radio stations, the navigation audio signals and the audio signals of other cabins to the headsets of the corresponding cabins through the microphone pre-amplification components after the audio signals from the very high frequency radio stations, the navigation audio signals and the audio signals of other cabins are superposed through the corresponding internal communication channels.
Preferably, the audio control unit is used for switching off the internal speech sending channel of any cabin when the cabin is in off-board communication through any very high frequency radio station, so that the pilot of the other cabin cannot receive the internal speech audio of the cabin, and the internal speech receiving channel of each cabin is kept in a switched-on state.
Preferably, the audio control unit is configured to directly send the audio signal from the front headset to a vhf radio station according to the emergency control signal, and send the audio signal received by the vhf radio station to the front headset; and, the audio signal from the rear cabin headset is directly sent to another very high frequency radio station, and the audio signal received through the very high frequency radio station is sent to the rear cabin headset.
Preferably, the data processor is used for receiving the alarm information from the central alarm system and sending the alarm code to the audio control unit; the audio control unit is used for generating or calling a pre-stored warning audio signal according to the warning code and sending the warning audio signal to the headsets of the front cabin and the rear cabin at the same time in fixed volume.
Preferably, the serial interface adopts a full-duplex RS422 interface with a baud rate of 115200 bps; the analog signal interface adopts an audio interface with an analog-to-digital converter and adopts an AWG22# twisted pair shielding wire; the discrete signal interface adopts AWG24# single-core shielding wire, the grounding represents the enabling, and the open circuit represents the non-enabling.
Preferably, the navigation unit in the navigation device comprises a navigation receiver, a range finder, an automatic direction finder and a pointing beacon; the navigation audio signals include a very high frequency omnidirectional beacon/instrument landing audio signal, a rangefinder audio signal, a directional audio signal, and a pointing beacon audio signal.
Preferably, the audio control unit has 28V dc power input and output interfaces to receive power from the on-board power supply and provide 28V dc power to the microphone preamplifier assembly.
In summary, due to the adoption of the technical scheme, the invention at least has the following beneficial effects:
the audio control unit is used for carrying out centralized processing on the internal communication, the external communication, the listening of the navigation sound, the monitoring of the warning sound and the like of the airplane, so that the integration level and the reliability of the airborne audio system are improved, and the overall weight is reduced, so that the airborne audio system can be integrated into an airborne radio system on a small-sized general airplane with only front and back cabins.
Drawings
Fig. 1 is a schematic structural diagram of a two-member audio system according to an embodiment of the present invention.
Fig. 2 is a schematic diagram of implementing a talk-in-phone in a two-member audio system according to an embodiment of the present invention.
Fig. 3 is a schematic diagram of implementing off-board communication in a two-member audio system according to an embodiment of the present invention.
Fig. 4 is a schematic diagram of implementing emergency communication in a two-member audio system according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and embodiments, so that the objects, technical solutions and advantages of the present invention will be more clearly understood. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Fig. 1 is a schematic structural diagram of a two-member audio system according to an embodiment of the present invention, which is applied to a small general-purpose aircraft having front and rear cabins to implement functions of call inside, external communication, emergency communication, navigation sound listening, warning sound monitoring, audio recording, and the like. The two-member audio system of this embodiment comprises an audio control unit ACU, a front cabin audio console ACP1 and a rear cabin audio console ACP2, two very high frequency radio stations (VHF1, VHF2), a data processor CNI, navigation equipment (including a navigation receiver VOR/ILS, a rangefinder DME, a robot ADF, and a pointing beacon MB), headsets (HS1, HS2) and corresponding microphone preamplification modules (JAT1, JAT2) mounted in the front cabin and the rear cabin, respectively.
The audio control unit ACU is respectively connected with the front cabin audio control panel ACP1 and the rear cabin audio control panel ACP2 through two paths of serial interfaces to receive and/or send control signals such as channel selection and volume adjustment, and is respectively connected with the front cabin audio control panel ACP1 and the rear cabin audio control panel ACP2 through two paths of discrete quantity interfaces to receive an audio control source selection signal ACP SEL IO;
the ACU is respectively connected with two VHF radio stations VHF1 and VHF2 through two paths of serial interfaces to receive and/or send control signals such as channel selection, volume adjustment and the like, and is respectively connected with two VHF radio stations VHF1 and VHF2 through two paths of analog signal interfaces to receive and/or send analog audio signals;
the ACU is connected with a data processor CNI in the airborne integrated radio system through a serial interface to receive and/or send control signals such as channel selection, volume adjustment and the like, and is connected with the CNI through a discrete quantity interface to receive an emergency control signal EMCY;
a navigation receiver VOR/ILS, a distance measuring machine DME, an automatic orientation machine ADF and a pointing beacon MB in the navigation equipment are respectively connected with an ACU through a path of analog signal interface so as to respectively send navigation sounds such as a very high frequency omnidirectional beacon VOR/instrument landing ILS audio signal, a distance measuring machine audio signal, a directional audio signal and a pointing beacon audio signal to the ACU, and are respectively connected with the ACU through a path of serial interface so as to receive audio control signals such as channel selection and volume adjustment;
the headset HS1 and HS2 (which can be an integral structure of an earphone and a microphone, and can also be formed by separately arranging an earphone and a microphone) arranged in the front cabin and the rear cabin are respectively connected with a microphone preamplification component JAT1 and JAT2, and each JAT is connected with the ACU through an analog signal interface to receive and/or send analog audio signals; each microphone preamplifier assembly is connected with the ACU through a discrete signal interface to receive an emergency control signal EMCY;
the ACU is connected with a flight parameter recorder (FDR) through two analog signal interfaces so as to send audio signals of a front cabin and a rear cabin to the ACU, thereby realizing the sampling and recording of the audio signals on the aircraft; the ACU also has 28V dc power input and output interfaces to take power from the on-board power supply and provide 28V dc power to the microphone pre-amplification assemblies JAT1, JAT 2.
In the above embodiment, the serial interface may adopt a full-duplex RS422 interface with a baud rate of 115200 bps; the analog signal interface can adopt an audio interface with an analog-to-digital converter and adopts AWG22# twisted-pair shielded wires; the discrete signal interface can adopt AWG24# single-core shielding wire, the grounding represents the enabling, and the open circuit represents the non-enabling.
FIG. 2 is a schematic diagram of a two-member audio system implementing a talk-in-flight in accordance with an embodiment of the present invention, showing a logical schematic diagram of a forward flight pilot initiating a talk to a aft flight pilot.
First, the pilot in the cockpit opens the talk switch on the cockpit audio control board ACP1 to send a talk request signal INTCOM SEL to the ACU, which opens the talk channel in accordance with the talk request signal. When the front cabin pilot speaks, a PTT1 button connected with the ACU is pressed, and AUDIO AUDIO collected by the headset is amplified through a microphone preamplification component JAT1 and then input into the ACU. The ACU sends the received AUDIO over the intercom channel via the microphone pre-amp component to the headset worn by the cockpit pilot. Also, the cockpit pilot may send a volume setting signal VOICE SET to the ACU via a talk-in adjust knob on the cockpit audio control panel ACP2 to cause the ACU to adjust the volume of the transmitted audio.
Fig. 3 is a schematic diagram of a two-member audio system implementing off-board communications according to an embodiment of the present invention, showing a logical schematic diagram of a forward and aft cabin pilot communicating with a ground station or other aircraft via either of two very high frequency stations VHF1, VHF 2.
As shown in fig. 3, the cockpit pilot tunes the VHF frequency to the ground station or other aircraft corresponding communication frequency on the corresponding audio control panel ACP and presses the very high frequency station button VHF1 or VHF2 on the ACP to send a station select signal VHF SEL to the ACU; the ACU correspondingly opens the channel of the communication frequency corresponding to the VHF of the selected VHF station. A pilot presses a PTT1 or PTT2 key connected with the ACU, and an AUDIO signal AUDIO collected by an earphone is amplified by a microphone preamplifier assembly JAT and then is input into the ACU; the ACU transmits the audio signal to a ground station or other aircraft via a corresponding VHF transmitter. Furthermore, the ACU may also output audio signals output to the VHF to the corresponding JAT so that the speaking pilot may listen to his own voice through the headset.
When the external AUDIO signal is received, the VHF1 or the VHF2 inputs the AUDIO signal AUDIO received from a ground radio or other airplane into the ACU, and the ACU superimposes the AUDIO signal from the VHF1 or the VHF2, the AUDIO signal from the navigation tone, and the AUDIO of the other cabin via the corresponding internal communication channel and transmits the superimposed AUDIO signal to the headset of the corresponding cabin via the JAT. Furthermore, the pilot may send a volume setting signal VOICE SET to the ACU via an adjustment knob on the audio control board ACP to cause the ACU to adjust the volume of the received channel audio or to turn off the receiving channel.
When any pilot in the front cabin and the rear cabin presses a corresponding very high frequency station button on the ACP to carry out communication outside the aircraft, namely VHF1 or VHF2, the ACU disconnects the internal speech sending channel of the cabin, so that the pilot in the other cabin cannot receive the internal speech audio of the cabin, and the internal speech receiving channel of each cabin is kept connected. When any pilot in the front rear cabin uses any one of the two very high frequency stations VHF1 and VHF2 to carry out communication outside the aircraft, the pilot in the other cabin can not simultaneously use the same very high frequency station to carry out communication outside the aircraft.
Fig. 4 is a schematic diagram of a two-member audio system implementing emergency communication according to an embodiment of the present invention. When the emergency communication outside the aircraft is carried out, any pilot in the front cabin and the rear cabin presses a corresponding ACP emergency communication button in the front cabin and the rear cabin to send an emergency control signal EMCY to the ACU; the ACU will automatically tune the communication frequency of VHF1 or VHF2 to the emergency frequency of 121.5MHz or 156.8MHz depending on the emergency control signal of the front or rear cabin. The forecabin pilot defaults to using the VHF1 radio for emergency calls and the rear cabin pilot defaults to using the VHF2 radio for emergency calls. When an emergency call is carried out, a pilot presses a PTT1 or PTT2 key connected with an ACU (access control unit), the ACU directly sends the audio signal of the headset of the front cabin to a VHF (very high frequency) broadcasting station VHF1 and sends the received VHF1 audio signal to the headset of the front cabin; the ACU sends the audio signal of the rear cabin headset to the VHF2 of the very high frequency broadcasting station directly, and sends the received VHF2 audio signal to the rear cabin headset. In emergency communication, the front and rear cabin pilots respectively communicate through the designated radio stations, the very high frequency radio stations cannot be switched through the ACP at will, and the volume of the received audio is still allowed to be adjusted or the receiving channel is closed by sending a volume setting signal void SET through the ACP.
In the preferred embodiment, the data processor CNI receives the alarm information from the central alarm system and sends the alarm code to the ACU through the RS422 interface; the ACU generates (e.g., by a text-to-speech TTS module) or invokes a pre-stored (e.g., 256 alert phrases may be stored, each alert tone being up to 3 seconds in length) alert audio signal from the alert code and sends it to the front and rear cabin headphones simultaneously at a fixed volume. Moreover, neither the front nor the back cabin ACPs allow for adjusting the volume of the alarm audio or for closing the alarm receiving channel by sending a volume setting signal sound SET to the ACU.
The foregoing is merely a detailed description of specific embodiments of the invention and is not intended to limit the invention. Various alterations, modifications and improvements will occur to those skilled in the art without departing from the spirit and scope of the invention.
Claims (9)
1. A dual member audio system for a general purpose aircraft, the dual member audio system comprising: the system comprises an audio control unit, a front cabin audio control panel, a rear cabin audio control panel, two very high frequency radio stations, a data processor, navigation equipment, headsets and corresponding microphone preamplification components, wherein the headsets and the microphone preamplification components are respectively installed in the front cabin and the rear cabin;
the audio control unit is respectively connected with the front cabin audio control panel and the rear cabin audio control panel through two paths of serial interfaces to receive and/or send control signals, and is respectively connected with the front cabin audio control panel and the rear cabin audio control panel through two paths of discrete quantity interfaces to receive audio control source selection signals;
the audio control unit is respectively connected with the two VHF radio stations through two paths of serial interfaces to receive and/or send control signals, and is respectively connected with the two VHF radio stations through two paths of analog signal interfaces to receive and/or send analog audio signals;
the audio control unit is connected with a data processor in the airborne integrated radio system through a serial interface to receive and/or send control signals, and is connected with the data processor through a discrete quantity interface to receive emergency control signals;
each navigation unit in the navigation equipment is respectively connected with the audio control unit through one path of analog signal interface so as to respectively send navigation audio signals to the audio control unit, and is respectively connected with the audio control unit through one path of serial interface so as to receive control signals;
the microphones installed in the front cabin and the rear cabin are respectively connected with a microphone preamplifier assembly, and each microphone preamplifier assembly is connected with the audio control unit through an analog signal interface so as to receive and/or send analog audio signals; each microphone preamplifier assembly is connected with the audio control unit through a discrete signal interface to receive emergency control signals;
the audio control unit is connected with the flight parameter recorder through two analog signal interfaces so as to send audio signals of the front cabin and the rear cabin to the audio control unit; when any pilot in the front cabin and the rear cabin presses a very high frequency radio button VHF1 or VHF2 on a front cabin audio control board or a rear cabin audio control board to carry out communication outside the aircraft, the audio control unit disconnects a voice-in sending channel of the cabin, so that the pilot in the other cabin cannot receive voice-in audio of the cabin, and a voice-in receiving channel of each cabin is kept in a connected state; when any pilot in the front cabin and the rear cabin uses the VHF station VHF1 or VHF2 for off-board communication, the external communication function of the same VHF station of the audio control panel of the other cabin is shielded.
2. The two-member audio system according to claim 1, wherein the audio control unit is configured to open a talk channel according to the talk request signal, receive audio collected through a headset in one cabin according to the PTT button signal, and transmit the received audio to a headset in another cabin through the talk channel via the microphone preamplifier assembly.
3. The two-member audio system according to claim 1, wherein the audio control unit is configured to open a channel of a communication frequency corresponding to the selected vhf radio station according to the radio station selection signal, receive audio collected through an ear microphone in one of the bays according to the PTT button signal, and transmit the received audio to the ground radio station or other aircraft through a transmitter of the corresponding vhf radio station.
4. The two-member audio system according to claim 3, wherein the audio control unit is configured to receive audio signals from a ground radio station or other aircraft, and to send the audio signals from the VHF radio station, the navigation audio signal, and the audio signals from other cabins to the microphones of the corresponding cabins via the microphone pre-amplification components after superimposing the audio signals via the corresponding internal communication channels.
5. The two-member audio system according to claim 1, wherein the audio control unit is configured to directly feed the audio signal from the front microphone to a vhf station according to the emergency control signal, and to feed the audio signal received through the vhf station to the front microphone; and, the audio signal from the rear cabin headset is directly sent to another very high frequency radio station, and the audio signal received through the very high frequency radio station is sent to the rear cabin headset.
6. The dual-member audio system of claim 1, wherein the data processor is configured to receive an alert message from a central alert system and send an alert code to the audio control unit; the audio control unit is used for generating or calling a pre-stored warning audio signal according to the warning code and sending the warning audio signal to the headsets of the front cabin and the rear cabin at the same time in fixed volume.
7. The dual member audio system of any of claims 1-6, wherein the serial interface employs a full duplex RS422 interface with a baud rate of 115200 bps; the analog signal interface adopts an audio interface with an analog-to-digital converter and adopts AWG22# twisted-pair shielded wires; the discrete signal interface adopts AWG24# single-core shielding wire, the grounding represents the enabling, and the open circuit represents the non-enabling.
8. The dual member audio system of any of claims 1-6, wherein the navigation unit in the navigation device comprises a navigation receiver, a range finder, an automatic direction finder, and a pointing beacon; the navigation audio signals include a very high frequency omnidirectional beacon/instrument landing audio signal, a rangefinder audio signal, a directional audio signal, and a pointing beacon audio signal.
9. The dual member audio system of any of claims 1-6, wherein the audio control unit has 28V DC power input and output interfaces to draw power from an on-board power device and provide 28V DC power to the microphone pre-amplification assembly.
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| CN201810333249.2A CN108557095B (en) | 2018-04-13 | 2018-04-13 | Double-member audio system for general-purpose aircraft |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202414156U (en) * | 2011-12-28 | 2012-09-05 | 中国航空工业集团公司第六三一研究所 | General airplane audio controller |
| CN203698669U (en) * | 2013-12-13 | 2014-07-09 | 中电科航空电子有限公司 | Audio-frequency comprehensive processing system |
| CN106789499A (en) * | 2016-12-12 | 2017-05-31 | 石家庄飞机工业有限责任公司 | A kind of integrated avionic system for light-small aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB201105520D0 (en) * | 2011-03-31 | 2011-08-17 | Bae Systems Plc | Unmanned air vehicle communications |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202414156U (en) * | 2011-12-28 | 2012-09-05 | 中国航空工业集团公司第六三一研究所 | General airplane audio controller |
| CN203698669U (en) * | 2013-12-13 | 2014-07-09 | 中电科航空电子有限公司 | Audio-frequency comprehensive processing system |
| CN106789499A (en) * | 2016-12-12 | 2017-05-31 | 石家庄飞机工业有限责任公司 | A kind of integrated avionic system for light-small aircraft |
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Effective date of registration: 20211012 Address after: 610000 floor 5, building 5, No. 99, west section of Hupan Road, Tianfu new area, Chengdu, China (Sichuan) pilot Free Trade Zone, Chengdu, Sichuan Patentee after: CHENGDU HERMES TECHNOLOGY Co.,Ltd. Patentee after: CHENGDU ZIRUI QINGYUN AERONAUTICAL AND ASTRONAUTICAL TECHNOLOGY Co.,Ltd. Address before: 610000 Chengdu, Sichuan, China (Sichuan) free trade trial area, 5 floor, 5 building, 99 west of Lake Road, Tianfu New District, Chengdu. Patentee before: CHENGDU HERMES TECHNOLOGY Co.,Ltd. |