JPH07212122A - Satellite communication equipment - Google Patents

Abstract

PURPOSE:To simplify the interfacing in packaging and to obtain a stable communication channel by forming by connecting a pair of antennas, that of transmission/reception branching filters, that of transmission parts, and that of reception parts to an input distributor and an output distributor. CONSTITUTION:The antennas 1a, 1b are arranged so that the beam of the one on one side is located at a position where it is prevented from being blocked by a rotary blade 2 when that of the one on the other side is blocked by the rotary blade. In this way, a reception desired wave via a satellite can be received normally by at least one antenna, an it is outputted to either the reception part 14a or 14b via the transmission/reception branching filters 6a, 6b connected to the antennas 1a, 1b. Therefore, the output of demodulators 10a, 10b can be received successively by synthesizing by an output synthesizer 12. While, a transmission desired signal is distributed by the input distributor 2, and is sent to the transmission parts 13a, 13b, respectively, and is transmitted from the antennas 1a, 1b via the transmission/reception branching filters 6a, 6b from the transmission parts 7a, 7b. Therefore, the beam of the antenna can be transmitted to the satellite without being blocked by the rotary blade 2 simultaneously.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a satellite communication device installed in a helicopter.

[0002]

2. Description of the Related Art FIG. 2 is a diagram showing an arrangement example of antennas of a conventional satellite communication device installed in a helicopter body. The figure shows an example in which there is a pair of satellite communication antennas that constitute space diversity. FIG. 3 includes the relationship between the antenna of FIG. 2 and the rotor, for example, Japanese Patent Laid-Open No. 2-295205.
FIG. 6 is a configuration block diagram of a satellite communication device based on the conventional idea shown in FIG. 2 and 3, 1a and 1b are satellite communication antennas, 2 is a rotor, 3 is a helicopter fuselage, 4
Is an antenna selector, 5 is a blade rotation synchronizing signal detector, 6 is a duplexer, 7 is a transmitter, 8 is a modulator, 9 is a receiver, 10
Is a demodulator.

Next, the operation will be described with reference to FIGS. Arranged so that when the beam of one antenna of the pair of satellite communication antennas 1a and 1b installed on the helicopter fuselage 3 is blocked by the rotor blade 2, the beam of the other antenna is not shielded by the rotor blade 2. Has been done. The antenna switch 4 is switched by the output signal of the blade rotation synchronization signal detector 5, and any antenna whose beam is not blocked is always selected. Therefore, the desired transmission signal is the modulator 8, the transmitter 7, the transmission / reception component. The desired reception signal is transmitted via the wave filter 6 and the satellite communication antenna 1a or 1b, and is obtained as the output of the demodulator 10 via the satellite communication antenna 1a or 1b, the transmission / reception demultiplexer 6 and the receiver 9.

[0004]

The conventional satellite communication device is configured as described above, and since antenna switching is performed regardless of the carrier wave phase of a transmission / reception signal, the communication system of the communication system requiring the carrier wave synchronous reproduction is used. In this case, there was a problem that the satellite communication line could not be maintained due to loss of synchronization due to the transient of antenna switching. In addition, there is a problem that the mounting interface between the rotor of the helicopter and the antenna including the antenna switching device becomes complicated because the signal detection in synchronization with the rotation of the helicopter rotor is required.

The present invention has been made in order to solve the above problems. Even in the case of a communication system that requires synchronous reproduction of a carrier wave of a transmission / reception signal, a synchronization signal synchronized with the rotation of the helicopter rotor is required. In other words, it is an object of the present invention to obtain a satellite communication device that can avoid the influence of a helicopter rotor blade and maintain a communication line, and that simplifies the mounting interface when installing on a helicopter.

[0006]

In order to achieve the above object, the satellite communication apparatus according to the present invention is such that at least one of a pair of antennas for satellite communication installed in a helicopter body has a beam of one antenna that rotates the helicopter. When shielded by the wing, the antenna of the other antenna beam is arranged at a position not shielded by the rotary wing of the helicopter, and a transmitter and receiver connected to each of the antennas via a duplexer, An input distributor that distributes and supplies the desired transmission signal to the plurality of transmitting units, and an output combiner that combines the desired receiving signals from the plurality of receiving units are provided.

[0007]

In the satellite communication device of the present invention configured as described above, signals at different shielding timings by the rotor blades of the helicopter are transmitted to at least a pair of transmitting and receiving antennas for satellite communication installed in the helicopter body. Even in the case of communication that requires synchronous reproduction of carrier waves, by making the transmitting and receiving systems exist independently and combining the output of the above multiple communication channel signals, full-duplex communication is performed regardless of the motion of the rotor blades. The line can be maintained. Moreover, since the synchronous detection of the helicopter rotor is not required, the mounting interface between the helicopter rotor and the antenna including the switching device is simplified.

[0008]

Embodiments of the present invention will be described below.
FIG. 1 is a configuration block diagram showing a system of the satellite communication device of the present invention. In FIG. 1, 1a and 1b are antennas and 2
Is one of the rotor blades, 6a and 6b are transmission / reception duplexers, and 7a and 7b
Is a transmitter, 8a and 8b are modulators, 9a and 9b are receivers,
10a and 10b are demodulators, 11 is an input distributor, and 12 is an output combiner. 13a is a transmitter having a transmitter 7a and a modulator 8a, 14a is a receiver having a receiver 9a and a demodulator 10a, 13b is a transmitter having a transmitter 7b and a modulator 8b, and 14b is a receiver 9b and a demodulator. 10b is a receiver.

In the figure, when the beam of either one of the pair of antennas 1a and 1b for satellite communication is blocked by the rotor blades 2, the other beam is arranged so that it is not blocked by the rotary blades 2 so that the satellites via the satellite are connected. The desired radio wave is normally received by at least one antenna, and the above antenna 1
The signal is output to either of the receivers 14a and 14b via the transmission / reception demultiplexers 6a and 6b connected to a and 1b, respectively. Therefore, by combining the outputs of the demodulators 10a and 10b with the output combiner 12, it is possible to continuously receive desired reception radio waves without interruption. On the other hand, the desired signal to be transmitted is divided into two by the input distributor 11 and sent to the transmitters 13a and 13b, respectively, and from the transmitters 7a and 7b via the duplexers 6a and 6b to the antennas 1a and 1b.
Transmit as uplink radio waves to communication satellites. The beams of the pair of antennas 1a and 1b for satellite communication are simultaneously transmitted without being blocked by the rotor 2. Therefore, only one partner antenna is required for communication via satellite, but by providing two receiving units. , The reception signals can be continuously received by combining the outputs of both. Therefore, even in the case of a communication method that requires synchronized reproduction of carrier waves,
For both transmission and reception, the communication channels before combination are independent from each other, and the shielding time by the rotor 2 is also different from each other. Therefore, each communication channel should hold carrier synchronization during the shielding time or make a quick recovery at the end of the shielding. The communication line can be maintained.

In the above embodiments, a satellite communication device for distributing and synthesizing a pair of antennas, a pair of communication channels consisting of a transmitting section and a receiving section connected to the respective antennas, and input / output signals of these will be described. However, the present invention is not limited to the pair of antennas and the pair of communication channels, and the same applies to the case of a plurality of communication channels having a plurality of pairs of antennas and a transmitter and a receiver connected to each of the antennas. .

[0011]

As described above, according to the present invention, at least a pair of transmission / reception antennas for satellite communication installed in a helicopter fuselage receive signals with different shield timings by the rotor blades of the helicopter in the transmission / reception system. Even if it is a communication method that requires synchronous reproduction of the carrier waves of the transmission / reception signals, it is necessary to have a synchronization signal that is synchronized with the rotation of the helicopter rotor by allowing them to exist independently and combining the output of the above multiple communication channel signals. As a result, it is possible to obtain a satellite communication device that can avoid the influence of the helicopter rotor blades, maintain a stable communication line, and simplify the mounting interface when installing the helicopter.

[Brief description of drawings]

FIG. 1 is a configuration block diagram showing a system of a satellite communication device of the present invention.

FIG. 2 is a diagram showing an arrangement example of satellite communication antennas installed in the helicopter body of the present invention and the related art.

FIG. 3 is a configuration block diagram showing a system of a conventional satellite communication device.

[Explanation of symbols]

 1a, 1b Antenna 2 Rotor 3 Airframe 4 Antenna selector 5 Blade rotation synchronization signal detector 6a, 6b Transmit / receive demultiplexer 7a, 7b Transmitter 8a, 8b Modulator 9a, 9b Receiver 10a, 10b Demodulator 11 Input distribution Unit 12 Output combiner 13a, 13b Transmitter 14a, 14b Receiver

Claims (1)

[Claims] 1. A position at which a beam of one antenna of at least one pair of antennas for satellite communication installed in a helicopter fuselage is blocked by a rotor of the helicopter while a beam of the other antenna is not shielded by a rotor of the helicopter. An antenna arranged on the antenna, a transmitter and a receiver connected to each of the antennas via transmission / reception duplexers, an input distributor that distributes and supplies a desired transmission signal to the plurality of transmitters, A satellite communication device, comprising: an output combiner for combining desired reception signals from a plurality of receiving units.