KR20110034203A - How to measure and calibrate the reticle in place of the helicopter - Google Patents

Abstract

The present invention relates to a method of measuring and calibrating a boresight in a hovering state of the helicopter, the grounding (Hovering) to measure the aiming line of air-to-air / aircraft guided missiles, navigation equipment and radar in the ground state (Hovering) By measuring and calibrating at), the alignment error can be reduced and the measurement time can be shortened.

To this end, the boresight measurement and calibration method of the present invention comprises the steps of: (a) irradiating a laser beam from a bore sight measuring device mounted on a helicopter and simultaneously irradiating a laser beam from a laser of an aircraft alignment reference line (ABRL); ; (b) measuring the laser beam irradiated from the helicopter at a laser sensor control station installed on the ground and calculating a correction amount by a data acquisition computer; (c) transferring the calculated correction amount to the data transmission and receiver (DTR) of the helicopter through the laser sensor control station; (d) transmitting correction data to each device through an internal data interface in the DTR and performing correction based on a preset software (S / W); And (e) transferring the result of performing the correction to the laser sensor control station through the DTR to record and record the correction result.

Description

Method of Compensation and Measurement Boresight from Hovering State of Helicopter

The present invention relates to a method of measuring and calibrating a boresight in a hovering state of the helicopter, and more particularly, to measure air-to-air / to-ground guided missiles, navigation equipment, and radar lines of sight. The present invention relates to a method of measuring and calibrating boresight that can reduce alignment error and reduce measurement time by measuring and correcting in in-flight flying state.

Currently, most of the military aircraft being developed generally apply a method performed by the alignment between the target equipment and the aircraft in the ground state for the alignment of the target equipment with the boresight. Alignment measurements with plates and clinometers are commonplace, and in rare cases, applications with LED pads (PADs) and cameras are being applied.

Conventional boresight measurement and calibration methods use the aircraft / airborne guided missiles, navigation equipment, and radar boresight target equipment with the Aircraft Boresight Reference Line (ABRL) to align the clinometer ( Clinometer is used to measure.

However, an error occurs when the value measured from the ground is measured after a certain operating time after the flight. This is a result of the structural deflection of the ABRL and the mounting surface of each of the boresight target equipments, which results in the elastic change of the structure supported by the landing gear and the rotor operation when the helicopter is taken off. Inevitably occurring due to the change in elasticity of the structure according to the prior art has a difficult problem of measurement and correction for this (see Fig. 1 and 2).

The deflection of the structure by the support point when the gas structure is supported by a landing gear or tri-pad on the ground to perform a boresight between the boresight reference plane and the equipment to be aligned. And the amount of deflection of the structure supported by the rotor during the actual flight is not the same, which is naturally due to the difference between the support point and the support method. According to the difference, the degree of gas deformation affects the boresight result, which causes a misalignment during flight even when performed by the boresight procedure on the ground. In addition, if the deflection and deformation of each component due to the vibration of the aircraft require additional measurement to confirm the problem after a certain flight operation time, the procedure and measurement for the measurement will require a considerable amount of time.

Therefore, in order to solve the above problems, alignment between the aircraft reference plane and the target equipment in the hovering state, which is the actual flight operation state, is required. Therefore, the boresite after the constant flight operation time, which has been raised above, can significantly shorten the measurement procedure and measurement time compared to the conventional method.

The technical problem to be solved by the present invention is to measure and calibrate the airborne air to air guided missiles, navigation equipment and the radar boresight in the hovering state in the ground (Ground) state This can compensate for the problem of deflection of the structure during the flight, allow the alignment to be closer to the actual operating environment of each piece of equipment, and allow the helicopter to fly the most accurate line of sight measurement and calibration. We present a method of measuring and calibrating boresight in a hovering state.

In addition, another technical problem to be achieved by the present invention is an aircraft boresight reference line sensor mounted in the helicopter (aircraft boresight reference line sensor), the line of sight sensor (boresight sensor) of each equipment, and a sensor installed in the ground station (ground ground) We propose a method of measuring and calibrating boresight in a hovering state of a helicopter that measures the physical amount of alignment by the geometric position between each sensor.

As a means for solving the above-described technical problem, the invention described in claim 1, "In the method of measuring and correcting the boresight in the hovering state of the helicopter, (a) the aiming line measurement target mounted on the helicopter Irradiating a laser beam at the equipment and simultaneously irradiating the laser beam at a laser of an aircraft alignment reference line (ABRL); (b) measuring the laser beam irradiated from the helicopter at a laser sensor control station installed on the ground and calculating a correction amount by a data acquisition computer; (c) transferring the calculated correction amount to the data transmission and receiver (DTR) of the helicopter through the laser sensor control station; (d) transmitting correction data to each device through an internal data interface in the DTR and performing correction based on a preset software (S / W); And (e) transmitting the result of performing the correction to the laser sensor control station through the DTR to record and manage the correction result. .

According to the present invention, the deflection of the structure during flight by measuring and correcting the airborne / air ground guided missile, navigation equipment, and radar boresight in a hovering state is measured. It can compensate for the problem, make the alignment closer to the actual operating environment of each equipment, and perform the most accurate line of sight measurement and correction.

DETAILED DESCRIPTION Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings so that those skilled in the art may easily implement the present invention. As those skilled in the art would realize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the present invention. In the drawings, parts irrelevant to the description are omitted in order to clearly describe the present invention, and like reference numerals designate like parts throughout the specification.

Hereinafter, specific technical contents to be implemented in the present invention will be described in detail with reference to the accompanying drawings.

Example

3 is a conceptual diagram of a bore site measurement and correction method in the hovering state of the helicopter according to a preferred embodiment of the present invention, Figure 4 is a block diagram of a bore site measurement and correction system in the hovering state of the helicopter according to the present invention. .

First, the present invention is to measure the laser beam emitted from the helicopter alignment reference line and each aiming line measurement target equipment in a hovering state by the laser sensor station (Laser Sensor Station) 10 installed on the ground of each target equipment From the irradiation angle formed by the laser beam originating from the difference of the helicopter mounting position, the relationship between the target line of the aircraft and the alignment line of the aircraft is measured geometrically, which means that the helicopter is hovering within the effective radiation range of the laser beam. The technical principle is to acquire data. In addition, the calibration is performed on the acquired line data to the data transmitter and receiver mounted in the helicopter through the laser sensor control center 10 to operate the electronic compensation function implemented in each device. Automatically perform crosshair calibration. In order to implement this principle, a data acquisition period considering the effective distance of the laser beam and the helicopter attitude change rate should be achieved. In addition, the technical principle that the calibration data is transmitted to the aircraft through the laser sensor control station 10 of the ground and the line of sight correction is automatically performed.

3 is a correlation between a laser radiation structure including a three-axis information of the aircraft alignment baseline of the helicopter and the target equipment of the boresight, the ground sensor station (10) and data acquisition equipment (Data Acquisition) on the ground The concept of the relationship is shown, and FIG. 4 transmits the correction information calculated from the acquired data to the corresponding equipment of the helicopter, and the information received from the side of the helicopter is electronically corrected by software that is preset through the communication path of the structural diagram inside the helicopter. It represents the concept of compensation.

As shown in FIG. 3, an Aircraft Boresight Reference Line (ABRL) on which a laser beam is irradiated and simultaneously irradiated from each target line measurement target (Equipment 1, Equipment 2) is also installed on the ground. Measured with a Laser Sensor Statio (10). The geometric correlation formed by each laser beam group calculates the alignment range between each boresight target device and the ABRL using a data acquisition computer (20).

The three-axis position information emitted by each target device and ABRL laser obtained by the concept of FIG. 3 is measured by the laser sensor control station 10 installed on the ground, and by the data acquisition computer 20. The correction amount is calculated and transmitted to the data transmitter and receiver (DTR) of the helicopter through the laser sensor control station (10). As a result, as shown in FIG. 4, correction data is transmitted to each equipment through the internal data interface in the DTR, and correction is performed based on a preset S / W.

Each device to be calibrated is equipped with software that can be calibrated by electronic compensation. As a result, the calibration is performed based on an internal subroutine according to the amount of calibration transmitted from the ground. The data is transmitted to the laser sensor control station 10 through a data transmitter and receiver, and the correction result is recorded and managed.

The boresight measurement and calibration theory is applicable to all in-flight helicopters and aircraft equipped with the ship's target equipment.

5 is an operation flowchart of a method for measuring and correcting a bore sight in a hovering state of a helicopter according to the present invention.

First, the laser beam is irradiated from the target line measuring target device mounted on the helicopter, and at the same time, the laser beam is irradiated from the laser of the aircraft line alignment reference line ABRL (step S10).

Then, the laser beam irradiated from the helicopter is measured at a laser sensor control station installed on the ground, and a correction amount is calculated by a data acquisition computer (step S20).

Then, the calculated correction amount is transmitted to the data transmission and receiver (DTR) of the helicopter through the laser sensor control station (step S30).

Then, the DTR transfers correction data to each device through the internal data interface to perform correction based on the preset software S / W (step S40).

Finally, the result of performing the correction is transmitted to the laser sensor control station via the DTR to record and record the correction result (step S50).

As described above, the method of measuring and calibrating the boresight in the hovering state of the helicopter according to the present invention is to measure the aiming line of air-to-air / air to ground missiles, navigation equipment, and radar in a hovering state. By measuring and calibrating in order to reduce the alignment error and reducing the measurement time, it is possible to solve the technical problem of the present invention.

It will be apparent to those skilled in the art that various modifications and changes can be made in the present invention without departing from the spirit or scope of the present invention as defined by the appended claims. It will be appreciated that such modifications and variations are intended to fall within the scope of the following claims.

The method of measuring and calibrating the boresight in the hovering state of the helicopter according to the present invention is applicable to any helicopter capable of hovering (flying in place) equipped with the boresight target equipment.

1 is an explanatory diagram for explaining a boresight measurement and correction method according to the prior art

2 is an example of an EGI boresight procedure of another aircraft T-50.

3 is a conceptual diagram of a bore sight measurement and correction method in a hovering state of a helicopter according to a preferred embodiment of the present invention;

4 is a configuration diagram of a bore sight measurement and correction system in a hovering state of a helicopter according to the present invention;

5 is an operation flowchart of a method for measuring and correcting a bore sight in a hovering state of a helicopter according to the present invention;

[Description of Code for Major Parts of Drawing]

10: Laser Sensor Station on the Ground

20: Data Aquisition Computer

Claims (1)

In the method of measuring and calibrating the boresight in the hovering state of the helicopter, (a) irradiating a laser beam from an aiming vessel measurement target device mounted on a helicopter and simultaneously irradiating a laser beam from a laser of an aircraft aiming line alignment reference line (ABRL); (b) measuring the laser beam irradiated from the helicopter at a laser sensor control station installed on the ground and calculating a correction amount by a data acquisition computer; (c) transferring the calculated correction amount to the data transmission and receiver (DTR) of the helicopter through the laser sensor control station; (d) transmitting correction data to each device through an internal data interface in the DTR and performing correction based on a preset software (S / W); And (e) transferring the result of performing the correction to the laser sensor control station through the DTR to record and manage the correction result; Method of measuring and calibrating the line of sight in place of the helicopter flight including a.

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