JP3170480U - Aircraft GPS device - Google Patents

Abstract

To provide an aircraft GPS device that can reduce installation effort and requires less installation space. A first antenna for receiving a GPS signal from a GPS satellite, a second antenna for communicating with a mobile phone communication network, and the GPS signal as a data signal for the mobile phone communication network. The interface circuit to be converted is accommodated in an integral casing 71, and an attachment member 8 is provided for coupling the casing 71 to the support arm 63 of the landing gear of the helicopter. [Selection] Figure 3

Description

  The present invention relates to an aircraft GPS device that receives a GPS signal from a GPS (Global Positioning System) satellite and detects the position of the aircraft.

  One example of this type of GPS device is described in Patent Document 1. Here, a GPS device is mounted on an unmanned helicopter. That is, a GPS receiver, a data communication device, and a control board are housed in a self-supporting control box attached to the side of the aircraft, and a GPS antenna and a communication antenna are attached to each part of the aircraft.

WO06 / 104158

  However, the above-described conventional GPS device has a problem in that it is necessary to individually install devices necessary for the configuration of the GPS device in the airframe, and it takes time and effort to secure an installation space.

  SUMMARY OF THE INVENTION The present invention solves such a problem, and an object thereof is to provide an aircraft GPS device that can reduce the installation effort and requires less installation space.

  In order to achieve the above object, in the first device, a first antenna (72) for receiving a GPS signal from a GPS satellite (S) and converting the GPS signal into a data signal for a cellular phone communication network. The interface circuit (74) and the second antenna (73) that communicates with the mobile phone communication network by the data signal are accommodated in an integral casing (71), and the casing (71) is accommodated. An attachment member (8) to be coupled to the aircraft body (63) is provided.

  In the first device, since the first antenna, the second antenna, and the interface circuit are integrally provided in the casing, and the casing is coupled to the fuselage with the mounting member, the installation effort can be reduced and the installation space can be reduced. Less

  In the second device, the mounting member includes holding members (82, 83) that hold the casing (71) so as to be rotatable around a holding point (85).

  In the second device, the posture can be easily changed by rotating the housing around the holding point.

  In the third device, the aircraft is a helicopter, and the mounting member (8) is coupled to the landing gear (6) of the helicopter so as to hold the support arm (63) of the helicopter. A coupling member (84) is provided.

  In the third device, the position of the housing can be easily changed by loosening the coupling of the coupling members to pivot the housing around the support arm.

  The reference numerals in the parentheses indicate the correspondence with specific means described in the embodiments described later.

  As described above, according to the aircraft GPS device of the present invention, it is possible to reduce the installation effort and to reduce the space for installation.

It is a top view of the helicopter provided with the GPS apparatus which shows one Embodiment of this invention. It is an expansion perspective view of a GPS apparatus, and is a perspective view from the X arrow direction of FIG. It is an expansion perspective view of a GPS apparatus, and is a perspective view from the Y arrow direction of FIG. It is an enlarged side view of a GPS apparatus, and is a side view from the Z arrow direction of FIG. It is an electrical system diagram of a GPS device.

  The embodiment described below is merely an example, and various design improvements made by those skilled in the art without departing from the gist of the present invention are also included in the scope of the present invention.

  FIG. 1 shows a plan view of a helicopter from which a main rotor as an aircraft is omitted. 1, the front half of the fuselage (the right half of FIG. 1) is wide and forms a cockpit 1 having a pair of left and right windshields 11 at the front end. A tail boom 2 extends rearward from the cockpit 1, a tail rotor 3 is provided on the side surface of the rear end thereof, and a vertical stabilizing plate 4 extending in the vertical direction is projected. Horizontal stabilizers 5 are projected in the horizontal direction from both side surfaces in the middle of the tail boom 2.

  Landing gears 6 protrude obliquely downward from the left and right positions on the bottom of the aircraft body of the cockpit 1. Each of the left and right landing gears 6 includes a skid 61 that contacts the ground and support arms 62 and 63 that support the vehicle body at the front and rear positions thereof. In the present embodiment, the GPS device 7 of the present invention, which will be described in detail later, is provided on the rear support arm 63 of the right landing gear 6.

  2 to 4 show the external appearance of the GPS device 7 attached to the support arm 63 of the landing gear 6. Here, FIG. 2 is a perspective view seen from the direction of arrow X in FIG. 1, and FIG. 3 is a perspective view seen from the direction of arrow Y in FIG. 4 is a side view seen from the direction of the arrow Z in FIG.

  In each figure, the casing 71 of the GPS device 7 has a rectangular parallelepiped closed box shape, and is attached to a support arm 63 by an attachment member 8 as will be described in detail later. Note that. Reference numeral 64 in each figure denotes a step member provided between the front and rear support arms 62 and 63.

  A first antenna 72 having a flat circular housing is provided on the upper side surface of the casing 71 so as to receive a GPS signal from the GPS satellite S (FIG. 5). In addition, a plate-like second antenna 73 projects downward from the lower side surface of the casing 71 so as to communicate with the mobile phone communication network. The casing 71 houses a GPS communication unit 74 (FIG. 5) as an interface circuit and a DC-DC converter circuit 75 that supplies power to the GPS communication unit 74. The DC-DC converter circuit 75 converts the DC 24V power supplied from the control panel 9 (FIG. 1) provided in the cockpit 1 through the power line 96 (FIG. 5) into a DC 5V power and converts it to the GPS communication unit 74. Supply. In addition, the heat sink 751 for cooling of the converter circuit 75 is protruded from the rear side surface of the housing 71 (FIG. 4).

  FIG. 5 shows an electrical system diagram of the GPS device. A first antenna 72 and a second antenna 73 are connected to the GPS communication unit 74 provided in the housing 71. The GPS signal received by the first antenna 72 and including the distance signal to the GPS satellite S is subjected to a moving average process or the like by the GPS communication unit 74, and then converted into a packet communication signal to be transmitted from the second antenna 73 to the mobile phone. Sent to the net.

  The ground center server computer connected to the cellular phone network calculates the position, altitude, speed, etc. of the helicopter based on the GPS signals from the four GPS satellites S, and sends the calculation results to the required client computer. Display the screen. A control panel 9 provided in the cockpit 1 (see FIG. 1) includes a power switch 91 (FIG. 5), lamps 82 for power supply “PWR”, GPS signal reception “GPS”, and radio wave reception “RX”, 83 and 84 are provided, and the control panel 9 and the casing 71 are connected by a cable 97 (see FIGS. 2 and 3) in which a power line 96 and a signal line 95 are housed. Note that a DC 24V power line 98 is connected to the control panel 9.

  The attachment member 8 includes a substantially trapezoidal frame body 81, and holding plates 82 and 83, which are holding members, are fixed to the long side and the short side of the frame body 81 which are parallel to each other. Keeping parallel to each other. The mounting member 8 is fixed to the support arm 63 by a U-shaped bolt 84 (FIG. 2), which is a connecting member provided at the end of the holding plate 82. It extends inward in the direction. The housing 71 of the GPS device 7 is disposed between the front and rear holding plates 82 and 83 extending in parallel, and the front and rear side surfaces of the housing 71 facing the holding plates 82 and 83 are caulking members at substantially the center thereof. It is connected to the holding plates 82 and 83 so as to be rotatable by means of 85.

  Each of the holding plates 82 and 83 is formed with an arc-shaped elongated hole 86 centered on the caulking member 85 at a symmetrical position with the caulking member 85 as a holding point of the casing 71 interposed therebetween. Is inserted with bolts 87 screwed into the front and rear side surfaces of the casing 71.

  With such a structure, the aircraft GPS device 7 of the present invention is easily mounted on the helicopter body by attaching the casing 71 to the support arm 63 via the holding plate 82 by the U-shaped bolt 84 of the attachment member 8. be able to. At this time, by loosening the nut of the U-shaped bolt 84, the casing 71 can be pivoted to an appropriate position around the support arm 63, and by loosening the bolt 87, the casing 71 is held at its holding point (caulking member 85). ) Tilt can be adjusted to an appropriate angle around.

DESCRIPTION OF SYMBOLS 12 ... 1st antenna, 13 ... 2nd antenna, 6 ... Landing gear, 63 ... Support arm (machine body), 71 ... Housing, 74 ... GPS communication unit (interface circuit), 8 ... Mounting member, 82, 83 ... Holding Plate (holding member), 84 ... U-shaped bolt (coupling member), 85 ... crimping member (holding point), S ... GPS satellite.

Claims (3)

A first antenna for receiving a GPS signal from a GPS satellite, an interface circuit for converting the GPS signal into a data signal for a mobile phone communication network, and communication with a communication destination via the mobile phone communication network by the data signal An aircraft GPS device characterized in that a second antenna to be performed is housed in an integral housing, and an attachment member for coupling the housing to an aircraft body is provided. The aircraft GPS device according to claim 1, wherein the attachment member includes a holding member that holds the casing so as to be rotatable around a holding point. 3. The aircraft according to claim 1, wherein the aircraft is a helicopter, and the attachment member includes a coupling member that is loosely coupled to the landing gear so as to hold the supporting arm of the landing gear of the helicopter. GPS device.

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