KR101050424B1 - Instrumentation pod system for testing the flying of an aircraft - Google Patents

Abstract

PURPOSE: A measurement pod system for aircraft flight test is provided to improve the efficiency of flight test by systematically analyzing flight safety control and quantitative data based on real time monitoring at the ground. CONSTITUTION: A measurement pod system for aircraft flight test comprises an image signal receiving part(110), a GPS/AHRS receiver(120), a temperature controller, a controller(130), a memory unit(140), a transmission unit(150), and a power supply unit(160). The image signal receiving part receives the status information of image pod system and the aviation video signal of aircraft from the image pod system. The GPS / AHRS receiver respectively receives the attitude information of aircraft. The temperature controller keeps the inside temperature of the housing within a fixed temperature range. The controller outputs the attitude information or stores in the memory. The temperature controller is controlled. The memory unit stores the location information of the image pod system, of the status information and attitude information of an aircraft, and the status information of the measurement pod system. The transmission unit receives and synthesizes the video signal and measuring data. The combined signal is transmitted to a ground control station.

Description

Instrumentation pod system for testing the flying of an aircraft

The present invention relates to a measurement pod system for aircraft flight testing (pod-type vessel under the wing of fuel, engine, etc.), and more specifically, to an air force using a weapon system (air-to-air, air-to-air) under research / development or introduced overseas. Measurement of aircraft stability, maneuverability, and other aerodynamic characteristics of the aircraft and its flight characteristics at the time of launch or release of the weapon system, when the flight test is carried out on an aircraft (e.g., fighter aircraft) operating in A measurement pod system for aircraft flight testing from which data can be obtained.

Flight measurement systems are very important as the only means of obtaining data to verify the performance of the weapon system at all different flight test stages. In general, flight measurement systems are the same as the design and fabrication stages of research and development of weapon systems. In other words, all the test data are obtained through the measurement system while the ground test and the flight test are performed by constructing the measurement system together with the production of the weapon system. However, when the measurement system is configured in addition to the existing system other than the development system, problems such as securing the space for mounting the system, securing the cable passage for the signal interface between the sub-systems, and modifying the existing system due to the new installation, In particular, in case of aircraft introduced from abroad, structural modifications are virtually impossible. This is because, even in the case of an aircraft, even minor modifications are directly related to the safety of the aircraft, and the safety review according to the modification is possible only by the designers of the original manufacturer.

In addition, when conducting flight tests with weapon systems under development or introduced into the aircraft operating by the Air Force, the stability, maneuverability, and aerodynamic characteristics of the aircraft following the installation of the weapon system and the aircraft at the time of launch or release It is not possible to obtain quantitative measurement data in real time for the flight characteristics of. The acquisition of such measurement data is based on the qualitative reporting of the pilot who performed the mission.

The present invention has been made in consideration of the above matters, and when performing a flight test by attaching a weapon system (air-to-air, air-to-air) under research / development or introduced overseas to an aircraft (eg, a fighter) operating in the Air Force In addition, it provides a measurement pod system for aircraft flight testing that can acquire quantitative measurement data on the aircraft's stability, maneuverability, and other aircraft's aerodynamics with the weapon system and the aircraft's flight characteristics when the weapon system is launched or dropped. There is a purpose.

Another object of the present invention is to develop similar to the Air Combat Maneuvering Instrumentation (ACMI) pod, which is a common training system for air force aircraft, to measure the flight flight test of the aircraft, which can omit the flight verification procedure for the measurement pod operation. To provide a Ford system.

In order to achieve the above object, the aircraft flight test measurement pod system according to the present invention,

It is a system for acquiring measurement data about the flight characteristics of the aircraft during launch or release of the weapon system by being mounted on one wing of an aircraft that is equipped with a new weapon system or an external shape.

An image signal receiver configured to receive flight image signals of the aircraft transmitted from the image pod system mounted on the other wing of the aircraft and status information (BIT information) in the image pod system;

A GPS / AHRS receiver configured to receive position information of the aircraft from a global positioning system (GPS) and flight position information of the aircraft from an attitude and heading reference system (AHRS);

A temperature control device installed in the housing of the metrology pod system, the temperature control device for maintaining a temperature in the housing within a preset temperature range so that device elements installed in the housing can operate normally;

Receives status information (BIT information) in the video pod system received from the video signal receiver, position information and flight position information of the aircraft received through the GPS / AHRS receiver, A control unit for outputting the data as a single measurement data for transmission to the ground control station, storing the result in a memory, and controlling the temperature control device;

A memory unit for storing the state information (BIT information) of the video pod system, the position information and the flight position information of the aircraft, and the state information (BIT information) of the measurement pod system, which are combined by the control unit;

A transmitter which receives the video signal received through the video signal receiver and measurement data output from the controller, synthesizes the two signals, and transmits the synthesized video / measurement data synthesized signal to a ground control station; And

It is characterized in that it comprises a power supply for receiving the AC voltage from the aircraft equipped with the instrumentation pod system is converted into a DC voltage of a predetermined size, and supplies the necessary power to the components.

The video signal receiver may include a duplexer that separates a transmission signal from an image pod system received through an antenna into two different frequency flight image signals and state information (BIT information) of the image pod system; The FM receiver receives the video signal separated by the duplexer and restores the original signal, and the wireless communication network unit receives the state information (BIT information) of the video pod system separated by the duplexer and restores the original signal. do.

In addition, the temperature control device generates a heat or stops heating by operating on / off (ON / OFF) in accordance with a temperature sensor for detecting a temperature in the measurement pod housing and a control signal of the controller according to the temperature detection through the temperature sensor. It includes a heating pad.

Preferably, the controller further has a function of monitoring the voltage converted by the power supply and the voltage supplied to the components.

In addition, preferably, the control unit has a function of downloading information stored in the memory unit to an external inspection equipment PC through Ethernet, and a function of debugging the operation program of the measurement pod system. Have more.

The transmitter may include an encoder that receives a video signal (analog video signal) restored to an original signal by an FM receiver of the video signal receiver, and converts the video signal into a digital video signal, and the digital video converted by the encoder. A multiplexer which receives a signal and measurement data output from the control unit, and combines the two signals into a digital signal (video / measured data composite signal), and a digital signal (video / measured data composite signal) synthesized by the multiplexer. And a transmitter for high speed transmission via the antenna.

In addition, a high power amplifier is further provided between the transmitter and the antenna to increase the output of the signal transmitted from the transmitter.

In addition, an MPEG-2 encoder is preferably used as the encoder, and a quadrature phase shift keying (QPSK) transmitter is used as the transmitter.

In addition, the power supply unit AC-DC converter for converting the AC voltage provided from the aircraft to a DC voltage of a predetermined size, and DC- for converting the DC voltage converted by the AC-DC converter back to a DC voltage of a different size It includes a DC converter.

Further, preferably, a predetermined portion of the measurement pod housing is further provided with an electromagnetic interference (EMI) filter for blocking electromagnetic interference (interference) from the electromagnetic waves generated from the measurement pod system to the aircraft equipped with the measurement pod system.

In addition, preferably, a predetermined weight of the measuring pod housing is further provided with a dummy weight for holding the overall center of gravity of the measuring pod housing.

According to the present invention, when testing the flight characteristics of the aircraft equipped with a new weapon system or an external shape to the aircraft, by mounting the measurement pod system of the present invention to perform the flight test stability of the aircraft according to the weapon system, Quantitative measurements of maneuverability and other aircraft aerodynamics and aircraft flight characteristics at the time of launch or release of the weapon system can be obtained. Thus, flight safety control and quantitative data can be systematically analyzed through real-time monitoring on the ground, thereby increasing the efficiency of flight testing.

1 is a view schematically showing the overall system configuration of the measurement pod system for aircraft flight test according to the present invention.
2 is a view showing the appearance of a measurement pod system for aircraft flight test according to the present invention.
3 is a plan view and a side view in a partial cross-sectional view of the metrology pod system of FIG. 2.
Figure 4 is a view showing a state equipped with the aircraft aircraft flight test instrumentation pod system according to the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1 to 4 show a measurement flight pod system for aircraft flight test according to the present invention, Figure 1 is a view showing the overall system configuration, Figure 2 is a view showing the appearance of the measurement pod, Figure 3 is Figure 2 Is a plan view and a side view in a partial cross-sectional state of a metrology pod of FIG. 4, and FIG. 4 is a view showing a state where the metrology pod system is mounted on an aircraft.

Referring to Figures 1 to 4, the aircraft flight test measurement pod system according to the present invention is mounted on one wing of the aircraft to perform a flight test equipped with a new weapon system or an external shape aircraft flight of the weapon system during launch or release As a system for acquiring measurement data on a characteristic, an image signal receiver 110, a GPS / AHRS receiver 120, a temperature controller, a controller 130, a memory 140, a transmitter 150, and a power supply unit ( 160).

The video signal receiving unit 110 is an image pod system mounted on the other wing of the aircraft (about this "aircraft flight test image pod system" filed by the same applicant as the present applicant, application number: 10-2010-0016941) Receives flight video signals from the aircraft and status information (BIT information) in the video pod system (e.g., information on the normal operation of each component of the video pod system, temperature information in the video pod housing, etc.). .

The GPS / AHRS receiver 120 receives the position information of the aircraft from the Global Positioning System (GPS) and the flight attitude information of the aircraft from the Attitude and Heading Reference System (AHRS), respectively.

The temperature control device is installed in the housing 100h (see FIG. 2) of the metering pod system and maintains the temperature in the housing 100h within a preset temperature range so that the device elements installed in the housing 100h can operate normally. It is for.

The controller 130 inputs state information (BIT information) in the image pod system received from the image signal receiver 110 and position information and flight position information of the aircraft received through the GPS / AHRS receiver 120. This is combined with the status information (BIT information) in the metrology pod system (eg, information on the normal operation of each component of the metrology pod system, temperature information in the metrology pod housing, etc.) and sent to the ground control station as a metrology data. Output for transmission, stored in memory, and control the temperature controller. In this case, as the controller 130, a microcomputer unit (MCU) may be used.

The memory unit 140 stores the state information (BIT information) of the image pod system, the position information and flight attitude information of the aircraft, and the state information (BIT information) of the measurement pod system, which are combined by the control unit 130. do. In this case, as the memory unit 140, a NAND flash memory may be used.

The transmitter 150 receives the video signal received through the video signal receiver 110 and the measurement data (video pod BIT information + measurement pod BIT information + GPS / AHRS information) output from the controller 130, respectively. The two signals are synthesized and the synthesized video / measured data is transmitted to the ground control station.

The power supply unit 160 receives an AC voltage (for example, AC 115V, 400Hz) from an aircraft equipped with the measurement pod system, and converts it into a DC voltage (for example, DC 24V, DC 12V) having a predetermined size. Supply the power required for the first component.

Here, the video signal receiver 110 transmits a transmission signal from an image pod system received through an antenna (for example, an industrial, scientific and medical (ISM) -band antenna) and a flying video signal of two different frequencies. A duplexer 111 that separates the status information (BIT information) of the video pod system, an FM receiver 112 that receives the video signal separated by the duplexer 111 and restores the original signal to the original signal; It includes a wireless communication network 113 for receiving the state information (BIT information) of the image pod system separated by the duplexer 111 to restore to the original signal. Here, ZigBee may be used as the wireless communication network 113.

In addition, the temperature control device is turned on / off in accordance with a temperature sensor 301 for detecting a temperature in the measurement pod housing 100h and a control signal of the controller 130 according to temperature detection through the temperature sensor 301. (ON / OFF) includes a heating pad (not shown) to operate or stop the heating.

In addition, preferably, the control unit 130 further has a function of monitoring the voltage supplied by the power supply unit 160 and the voltage supplied to the components. To this end, the controller 130 is equipped with a software program that performs a function for monitoring the voltage supplied to each component (image signal receiver, GPS / AHRS receiver, transmitter, memory and the controller itself).

In addition, the control unit 130 preferably downloads the information stored in the memory unit 140 to an external inspection equipment PC (not shown) via Ethernet, and to the operation program of the measurement pod system. It also has a function to perform debugging.

In addition, the transmitter 150 receives an image signal (analog image signal) restored to the original signal by the FM receiver 112 of the image signal receiver 110 and converts it into an encoder (encoder) ( 151 and a multiplexer which receives the digital video signal converted by the encoder 151 and the measurement data output from the controller 130 and combines the two signals into a digital signal (video / measured data composite signal). ) 152, and a transmitter 153 for high-speed transmission of the digital signal (video / measurement data composite signal) synthesized by the multiplexer 152 through the antenna.

In addition, a high output amplifier 154 is further provided between the transmitter 153 and the antenna to increase the output of the signal transmitted from the transmitter 153.

In addition, the encoder 151 is preferably an MPEG-2 encoder, and the transmitter 153 is a quadrature phase shift keying (QPSK) transmitter.

In addition, the power supply unit 160 is an AC-DC converter for converting an AC voltage (for example, AC 115V, 400Hz) provided from the aircraft to a DC voltage (for example, DC 24V) of a predetermined size, and the AC A DC-DC converter for converting the DC voltage converted by the DC converter back into a DC voltage of another magnitude (for example, DC 12V).

In addition, preferably, a predetermined portion of the measurement pod housing 100h has an electromagnetic interference (EMI) filter 302 for blocking electromagnetic interference (interference) from an electromagnetic wave generated from the measurement pod system on an aircraft equipped with the measurement pod system. ) Is installed.

In addition, preferably, a predetermined weight of the measurement pod housing 100h is further provided with a dummy weight 303 for holding the overall center of gravity of the measurement pod housing 100h.

Then, the operation of the aircraft flight test instrumentation pod system according to the present invention having the above configuration will be briefly described.

When the flight test is performed with the measurement pod system of the present invention mounted on one wing of an aircraft (for example, a fighter jet) and an image pod system mounted on the other wing of the aircraft, a signal is transmitted from the image pod system. Then, the video signal receiving unit 110 is a flight video signal of the aircraft transmitted from the video pod system side and the status information (BIT information) in the video pod system (for example, whether or not the normal operation of each component of the video pod system) Information, temperature information in an image pod housing, etc.) is received through an antenna (ISM-band antenna).

When the transmission signal from the video pod system is received through the video signal receiver 110 in this way, the duplexer 111 of the video signal receiver 110 receives the received signal at two different frequencies. And status information (BIT information) of the video pod system. Then, the FM receiver 112 receives the video signal separated by the duplexer 111 and restores the original signal, and the wireless communication network (ZigBee) 113 of the video pod system separated by the duplexer 111 Receives the status information (BIT information) and restores the original signal.

In addition, the GPS / AHRS receiver 120 receives the position information of the aircraft from the Global Positioning System (GPS) and the flight attitude information of the aircraft from the Attitude and Heading Reference System (AHRS), respectively.

As described above, when the video signal receiver 110 and the GPS / AHRS receiver 120 respectively receive and transmit signals, the controller 130 receives status information (BIT information) in the video pod system received from the video signal receiver 110. And, by receiving the position information and flight position information of the aircraft received through the GPS / AHRS receiver 120, the status information (BIT information) in the measurement pod system (for example, whether each component of the measurement pod system is operating normally Information, temperature information in the measurement pod housing, etc.) is output as a measurement data for transmission to the ground control station, and the measurement data is stored in the memory unit 140.

When the measurement data (video pod BIT information + measurement pod BIT information + GPS / AHRS information) is output by the control unit 130 as described above, the transmitter 150 transmits the measured data and the FM receiver of the video signal receiver 110 ( Each of the video signals passed through 112) is received, the two signals are synthesized, and the synthesized video / measurement data composite signal is transmitted to the ground control station. That is, the encoder 151 of the transmitter 150 receives the video signal (analog video signal) restored to the original signal by the FM receiver 112 of the video signal receiver 110 and converts it into a digital video signal. The multiplexer 152 receives the digital video signal converted by the encoder 151 and the measurement data output from the controller 130 and converts the two signals into digital signals (video / measured data composite signals). The transmitter 153 transmits the digital signal synthesized by the multiplexer 152 (video / measured data synthesized signal) to the ground control station through the antenna. As a result, ground control stations (ground base stations) can acquire quantitative measurements of aircraft stability, maneuverability, and other aerodynamic characteristics of aircrafts, as well as aircraft flight characteristics when weapon systems are launched or dropped. Therefore, flight safety control and quantitative data can be systematically analyzed through real-time monitoring on the ground, thereby increasing the efficiency of flight test.

Measurement pod system according to the present invention as described above is to measure the flight characteristics of the aircraft in connection with the new weapons system (air-to-air, air-to-air ground) or external shape on the aircraft currently operating in the air force, any modification to the aircraft It is a system that can obtain flight data of an aircraft during flight test without adding.

The shape of the pod housing of the instrumentation pod system of the present invention is designed and manufactured similarly to the Air Combat Maneuvering Instrumentation (ACMI) pod, which is a common training system for air force aircrafts, and thus the aircraft flight verification procedure for operating the instrumentation pod system. Can be omitted. The measurement pod system of the present invention can be mounted on a wing tip launcher or a pylon launcher of an aircraft, and is designed to use a 115V AC, 400 kW power supply for general weapon system operation in an aircraft. As described above, the measurement pod system of the present invention is a GPS / AHRS receiver for measuring aircraft flight position and position data, a multiplexer for synthesizing flight data and video signals, a transmitter for transmitting measurement data, an image signal receiver, and an aircraft. Temperature control means for temperature control in the measuring pod housing are provided to protect the system according to the temperature change (-54 ° C to 50 ° C) during flight. The measurement pod system of the present invention proved its performance through environmental tests, electromagnetic tests, ground tests and flight tests.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, Accordingly, the true scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of the same should be construed as being included in the scope of the present invention.

110 ... video signal receiver 111 ... duplexer
112 FM receiver 113 Wireless network part
120 ... GPS / AHRS receiver 130 ... controller
140 Memory unit 150 Transmitter unit
151 ... encoder 152 ... multiplexer
153 ... QPSK Transmitter 154 ... High Power Amplifier
160.Power supply unit 301 ... Temperature sensor
302 ... EMI filter 303 ... dummy weight

Claims (12)

It is a measurement pod system for aircraft test flight, which is mounted on one wing of an aircraft that is equipped with a new weapon system or an external shape to acquire measurement data about the aircraft flight characteristics during the launch or release of the weapon system.
An image signal receiver configured to receive flight image signals of the aircraft and state information in the image pod system transmitted from the image pod system mounted on the other wing of the aircraft;
A GPS / AHRS receiver configured to receive position information of the aircraft from a global positioning system (GPS) and flight position information of the aircraft from an attitude and heading reference system (AHRS);
A temperature control device installed in the housing of the metrology pod system, the temperature control device for maintaining a temperature in the housing within a preset temperature range so that device elements installed in the housing can operate normally;
The ground control station receives the status information in the video pod system received from the video signal receiver, the position information and flight attitude information of the aircraft received through the GPS / AHRS receiver, and combines the status information in the measurement pod system as one measurement data. A control unit which outputs for transmission to a furnace and stores it in a memory and controls the temperature control device;
A memory unit for storing the state information of the image pod system, the position information and the flight position information of the aircraft, and the state information of the measurement pod system, which are combined by the control unit;
A transmitter which receives the video signal received through the video signal receiver and measurement data output from the controller, synthesizes the two signals, and transmits the synthesized video / measurement data synthesized signal to a ground control station; And
Power supply required for the video signal receiver, the GPS / AHRS receiver, the temperature controller, the controller, the memory and the transmitter to receive an AC voltage from an aircraft equipped with a measurement pod system and convert the AC voltage into a DC voltage having a predetermined size. Aircraft flight test instrumentation pod system, characterized in that it comprises a power supply for supplying. The method of claim 1, wherein the video signal receiver,
A duplexer that separates the transmission signal from the video pod system received through the antenna into two different frequency flying video signals and the status information of the video pod system;
An FM receiver for receiving an image signal separated by the duplexer and restoring the original signal;
Aircraft flight test measurement pod system, characterized in that it comprises a wireless communication network for receiving the state information of the image pod system separated by the duplexer to restore the original signal. The method of claim 1, wherein the temperature control device,
A temperature sensor for detecting a temperature in the measurement pod housing;
And a heating pad configured to generate heat or stop heating by an ON / OFF operation according to a control signal of the controller according to the temperature detection through the temperature sensor. The method of claim 1,
The control unit may further monitor a voltage converted by the power supply unit and a voltage supplied to the image signal receiver, the GPS / AHRS receiver, the temperature controller, the controller, the memory unit, and the transmitter. Measurement pod system for aircraft flight test, characterized in that it has. The method of claim 1,
The control unit may further have a function of downloading information stored in the memory unit to an external inspection equipment PC through Ethernet, and debugging of an operation program of a measurement pod system. Instrumented pod system for aircraft flight testing. The method of claim 1, wherein the transmitting unit,
An encoder for receiving a video signal restored to the original signal by the FM receiver of the video signal receiver and converting the video signal into a digital video signal;
A multiplexer configured to receive the digital video signal converted by the encoder and the measurement data output from the controller, and combine the two signals into digital signals;
And a transmitter for transmitting a high speed digital signal synthesized by the multiplexer through an antenna. The method of claim 6,
And a high power amplifier is further provided between the transmitter and the antenna to increase the output of the signal transmitted from the transmitter. The method of claim 6,
And the encoder is an MPEG-2 encoder. The method of claim 6,
The transmitter is a quadrature phase shift keying (QPSK) type transmitter transmitter for aircraft flight test, characterized in that. The method of claim 1, wherein the power supply unit,
An AC-DC converter for converting an AC voltage provided from an aircraft into a DC voltage having a predetermined size;
And a DC-DC converter for converting the DC voltage converted by the AC-DC converter back into a DC voltage having a different size. The method of claim 1,
A predetermined portion of the measurement pod housing further includes an electromagnetic interference (EMI) filter for blocking electromagnetic interference (interference) from the electromagnetic waves generated from the measurement pod system on the aircraft equipped with the measurement pod system. Test instrumentation pod system. The method of claim 1,
The measurement pod system for aircraft flight test, characterized in that the dummy weight (dummy weight) for holding the entire center of gravity of the measurement pod housing is further installed in a predetermined portion of the measurement pod housing.

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