Relay device and detonation method for detonation system

Abstract

A relay device is needed for the detonation system that can reliably transmit the detonation signal to each detonator while enhancing safety. [Solution] The relay device 20 for the detonation system 1 relays the signal from the blaster 3 to the detonator 10 installed on the working face or the working face surface 41 that is the target of blasting. The relay device 20 has a flying body 30, an upstream receiver 23, and a downstream transmitter 24. The flying body 30 flies by remote control or autopilot. The upstream receiver 23 is installed on the flying body 30 and receives the upstream detonation signal from the blaster 3 wirelessly. The downstream transmitter 24 is installed on the flying body 30 and transmits a downstream detonation signal wirelessly to the detonator 10 when the upstream receiver 23 receives the upstream detonation signal. The detonator 10 detonates based on the downstream detonation signal.

Description

Technical Field

[0001] The present invention relates to a relay device for an ignition system provided in an ignition system used at a site for excavation such as a tunnel, a site for crushing such as a rock, a site for crushing a structure such as a building, etc., and an ignition method using the relay device for the ignition system.

Background Art

[0002] Patent Document 1 discloses an ignition system used in blasting operations at an excavation site such as a tunnel. A plurality of charging holes are formed in the face of the blasting target. The charging holes are formed, for example, with a substantially circular opening having a diameter of several cm and a depth of several m. In each charging hole, an ignition detonator is inserted on the inner side, and explosive is inserted on the front side of the ignition detonator. The blasting machine is installed at a remote location away from the face. The blasting machine transmits an ignition signal to the ignition detonator in the charging hole. A relay device is provided between the blasting machine and the ignition detonator. An ignition signal is wirelessly sent from the blasting machine to each ignition detonator via the relay device. Thereby, the electric detonator of the ignition detonator is ignited and the explosive is detonated.

[0003] As described in Patent Document 1, a conventional relay device for an ignition system is installed in the vicinity of the face or in a hole formed in the face. Therefore, there is room for improvement in order to reduce the labor for installing the relay device and to improve the safety of the installation work. Also, since ignition is performed with the relay device installed, the relay device cannot be reused and it is necessary to prepare relay devices for the number of blasts. Therefore, there is room for improvement from the viewpoints of resource consumption and running cost.

[0004] Furthermore, the relay device's antenna is fixed at a specific position and angle. Similarly, the detonator's antenna is fixed at a specific position and angle within the propellant hole. Therefore, when the relay device's antenna transmits the detonation signal, the generated magnetic field is determined by a predetermined distribution. Depending on the position of the detonator, the magnetic field may not be detectable, making it difficult to receive the detonation signal. To reduce the running costs of the detonators and to prevent the detonators and propellant holes from becoming larger, it is desirable to have a compact, single-axis antenna for the detonators. Therefore, there was room for improvement to make communication from the relay device to each detonator more reliable. [Prior art documents] [Patent Documents]

[0005] [Patent Document 1] International Publication No. 2022 / 014530 [Overview of the Initiative] [Problems that the invention aims to solve]

[0006] Therefore, a relay device for the detonation system is needed that can reliably transmit the detonation signal to each detonator while enhancing safety. [Means for solving the problem]

[0007] One feature of this disclosure relates to a relay device for a detonation system that relays a signal from an blaster to a detonator installed at the blasting face or target. The relay device for a detonation system comprises a flying body, an upstream receiver, and a downstream transmitter. The flying body is operated remotely or automatically. The upstream receiver is installed on the flying body and wirelessly receives an upstream detonation signal from the blaster. The downstream transmitter is installed on the flying body and wirelessly transmits a downstream detonation signal to the detonator when the upstream receiver receives the upstream detonation signal. The detonator detonates based on the downstream detonation signal.

[0008] Therefore, the relay device can be positioned in the air near the tunnel face or the target to be blasted without the operator having to approach the tunnel face or the target to be blasted. Moreover, the detonator can be detonated by wirelessly transmitting a downstream detonation signal from the blaster to the detonator via the relay device, without the operator having to approach the tunnel face or the target to be blasted. This increases the safety of the blasting. Furthermore, the flying vehicle increases the degree of freedom in positioning the relay device in the air. This allows for more reliable transmission of the downstream detonation signal from the relay device to each detonator. In addition, the flying vehicle allows the relay device to be recovered during blasting. This contributes to resource conservation and reduction of running costs.

[0009] According to other features of this disclosure, the aircraft has rotor blades. The aircraft remains stationary at a predetermined position relative to the face or target to be blasted by the rotor blades. Therefore, the relay device transmits the downstream detonation signal while stationary at the predetermined position. This allows the aircraft to move to a second predetermined position where communication with the detonator is easier, even if the detonator is located in a position where communication is difficult at the first predetermined position. This allows the aircraft to move efficiently while reliably transmitting the downstream detonation signal from the relay device to each detonator.

[0010] According to other features of this disclosure, the aircraft has a control receiver and a holding mechanism. The control receiver receives control signals for remote control. The holding mechanism detachably holds the downstream transmitter. The holding mechanism is remotely controlled via the control receiver. Therefore, the relay device can fly smoothly together with the aircraft. For example, a downstream transmitter fixed to the aircraft may interfere with the aircraft's takeoff and landing. Using the control receiver and holding mechanism, the downstream transmitter can be attached to and detached from the aircraft while the aircraft is in flight. Therefore, even when using a large downstream transmitter, for example, the relay device can fly smoothly.

[0011] According to other features of this disclosure, the downstream transmitter transmits a first downstream detonation signal as a downstream detonation signal when the aircraft is in a first position or orientation. A second downstream detonation signal is transmitted as a downstream detonation signal when the aircraft moves from the first position to a second position or changes orientation from the first orientation to the second orientation. Thus, the downstream transmitter transmits the downstream detonation signal multiple times at multiple positions or orientations. This suppresses the transmission of the downstream detonation signal to multiple detonators without transmission. Therefore, the downstream detonation signal can be transmitted to each detonator more reliably.

[0012] According to other features of this disclosure, the downstream transmitter transmits multiple downstream detonation signals. A controller is mounted on the aircraft. The controller controls the aircraft to move away from the face or target after the downstream transmitter has transmitted the last downstream detonation signal. Thus, after the transmission of the last downstream detonation signal, the relay device is moved away from the face or target before the detonator detonates. This allows the relay device to be reused without being consumed for each blast.

[0013] According to other features of this disclosure, the downstream transmitter has a first coil, a second coil, and a third coil. The first coil is wound around the axis of a first axis. The second coil is wound around the axis of a second axis that extends in a direction intersecting the first axis. The third coil is wound around the axis of a third axis that extends in a direction intersecting both the first and second axes. Thus the downstream transmitter has a three-dimensional structure with three coils having mutually different axial directions. By flying the relay device in an aircraft, the three-dimensional downstream transmitter can be positioned in any position or orientation in the air. This allows for more reliable transmission of the downstream detonation signal from the downstream transmitter to each detonator positioned at various locations on the face or target of blasting.

[0014] According to other features of this disclosure, the upstream receiver is rod-shaped and mounted on the upper part of the aircraft. The downstream transmitter is larger and more annular than the upstream receiver and mounted on the lower part of the aircraft. Therefore, the upstream receiver can be provided in a shape, size, and position that does not interfere with the flight of the aircraft. The downstream transmitter can be provided in a large, annular size that is suitable for transmitting a downstream detonation signal in a frequency band with good rock penetration. Moreover, the downstream transmitter can be positioned so as not to interfere with the flight of the aircraft.

[0015] Another feature of this disclosure relates to a method for detonating a detonator installed at the face of a blasting site or target. The blaster, having moved away from the face of the blasting site or target, transmits a first upstream detonation signal wirelessly. The upstream receiver of a relay device installed on the aircraft receives the first upstream detonation signal. The downstream transmitter of the relay device installed on the aircraft transmits a first downstream detonation signal wirelessly to the detonator. The aircraft moves from a first position to a second position, or changes direction from a first orientation to a second orientation. The blaster transmits a second upstream detonation signal wirelessly. The upstream receiver receives the second upstream detonation signal. The downstream transmitter transmits a second downstream detonation signal wirelessly. The aircraft moves away from the face of the blasting site or target. The detonator, having received the first downstream detonation signal and / or the second downstream detonation signal, detonates.

[0016] Therefore, the relay device can be positioned in the air near the working face or the target to be blasted without the operator having to approach the working face or the target to be blasted. Moreover, the detonator can be detonated by wirelessly transmitting a downstream detonation signal from the blaster to the detonator via the relay device without the operator having to approach the working face or the target to be blasted. This increases the safety of the blasting. Furthermore, the downstream transmitter transmits the downstream detonation signal multiple times from multiple positions or orientations that can be moved by the aircraft. The detonator detonates upon receiving one of the multiple downstream detonation signals. This ensures that the downstream detonation signal is transmitted to each detonator more reliably. In addition, the relay device can be evacuated and recovered from the working face or the target to be blasted by the aircraft before the detonator detonates. This allows for resource conservation and reduction of running costs.

[0017] According to other features of this disclosure, the first upstream detonation signal and the first downstream detonation signal include first delay information relating to a first delay time. The second upstream detonation signal and the second downstream detonation signal include second delay information relating to a second delay time shorter than the first delay time. When the detonator receives the first downstream detonation signal, it calculates a first detonation time by adding a preparation time to the first delay time. When the detonator receives the second downstream detonation signal, it calculates a second detonation time by adding a preparation time to the second delay time. The detonator detonates either after the first detonation time has elapsed since receiving the first downstream detonation signal, or after the second detonation time has elapsed since receiving the second downstream detonation signal.

[0018] Therefore, for example, the transmission time difference between the first upstream detonation signal and the second upstream detonation signal, the second delay time, is made shorter than the first delay time. This makes it possible to make the detonation time when the detonator detonates after the first detonation time has elapsed from the time the first downstream detonation signal is received the same as the detonation time when the detonator detonates after the second detonation time has elapsed from the time the second downstream detonation signal is received. In this way, by transmitting multiple downstream detonation signals to the detonator with staggered transmission times, signal transmission leaks can be suppressed, and the detonator can be detonated at the same time regardless of which downstream detonation signal it receives. [Brief explanation of the drawing]

[0019] [Figure 1] This diagram shows the overall configuration of the detonation system according to the first embodiment and a schematic diagram of the tunnel excavation site. [Figure 2] This is a perspective view of the relay device. [Figure 3] This is a side view of the relay unit with the downstream transmitter removed. [Figure 4] This is a block diagram of the detonation system. [Figure 5] This is a flowchart showing the detonation process in a detonation system. [Figure 6] This diagram schematically shows the detonation times of detonators corresponding to multiple downstream detonation signals. [Figure 7] This is a perspective view of the relay device according to the second embodiment. [Figure 8]It is a perspective view of the relay device and the flying object according to the third embodiment.

Mode for Carrying Out the Invention

[0020] The first embodiment of the present disclosure will be described with reference to FIGS. 1 to 6. The same reference numerals in the description mean the same elements having the same functions without redundant description. The detonation system 1 is used to detonate the explosive 2 to excavate or crush structures such as tunnels, seabeds, rocks, buildings, etc. In this embodiment, as shown in FIG. 1, the excavation site of the tunnel 40 will be described as an example. At the inner part of the tunnel 40, a face (heading face) 41 to be blasted stands upright in the vertical direction. A plurality of charging holes 41a are provided in the face 41 at predetermined intervals in the vertical and horizontal directions. The charging holes 41a extend linearly along the plane normal direction of the face 41. The charging holes 41a are drilled to a depth of several meters, for example, in a circular shape with a diameter of 30 mm to 100 mm.

[0021] As shown in FIGS. 1 and 4, each charging hole 41a is loaded with a cylindrical detonator 10 and a plurality of cylindrical explosives 2. The detonator 10 is loaded on the inner side of the charging hole 41a with the electric detonator 13 on the front side. The plurality of explosives 2 are loaded on the front side of the detonator 10. The innermost explosive 2 adjacent to the detonator 10 is the parent die 2a into which the electric detonator 13 is inserted. The parent die 2a is ignited and detonated by the electric detonator 13. On the front side of the parent die 2a, a plurality of booster dies 2b are arranged along the charging hole 41a. The plurality of booster dies 2b are detonated in a chain reaction by the detonation of the parent die 2a. The entrance of the charging hole 41a in front of the explosive 2 is sealed with a sealing member 41b such as clay. Although only the structure inside one charging hole 41a is described in detail in FIGS. 1 and 4 for convenience of explanation, the same structure is provided in other charging holes 41a.

[0022] As shown in Figure 1, the detonation system 1 has a blaster 3 that transmits a detonation signal, etc. The blaster 3 is used at a sufficiently far distance, for example, about 100m to 1000m from the tunnel face 41. The blaster 3 has an antenna 3a that can transmit radio signals in the UHF band (300MHz to 3GHz), for example. The blaster 3 has an input unit 3b that allows input operation to transmit a detonation signal.

[0023] As shown in Figure 4, the blaster 3 has an electronic circuit 3c electrically connected to an antenna 3a and an input unit 3b. The electronic circuit 3c is equipped with a calculation unit 3d and a timer circuit 3e. The calculation unit 3d calculates the delay time of the delay information to be attached to the detonation signal based on the input signal from the input unit 3b and the time counted by the timer circuit 3e. The antenna 3a transmits the detonation signal with the attached delay information multiple times. The delay time differs for each detonation signal; for example, the longer the time counted by the timer circuit 3e, the shorter the calculated delay time for each detonation signal.

[0024] As shown in Figure 1, the detonation system 1 has a controller 4 that can remotely control the aircraft 30, which will be described later. The controller 4 is used in the vicinity of the blaster 3, for example, at a sufficiently far distance of about 100m to 1000m from the face 41. The controller 4 has an antenna 4a that transmits and receives radio signals at a different frequency from the blaster 3, for example, in the 2.4GHz band. The controller 4 has an input unit 4b into which a program for manually controlling or automatically controlling the aircraft 30 can be input. Based on the input from the input unit 4b, a radio signal is transmitted from the antenna 4a. The controller 4 has an output unit 4c that can display the signal received by the antenna 4a. The signal received by the antenna 4a is, for example, video footage from a camera mounted on the aircraft 30.

[0025] As shown in Figure 1, the detonator 10 has a cylindrical body tube 11. The body tube 11 is provided with a diameter smaller than the diameter of the propellant hole 41a. As shown in Figure 4, the body tube 11 houses an electronic circuit 12, an electric detonator 13, and an antenna 14. The electronic circuit 12 is provided with a capacitor 12a that stores power for driving and detonation. The electronic circuit 12 is provided with an ignition unit 12b that is electrically connected to the electric detonator 13. After the electronic circuit 12 receives a detonation signal via the antenna 14, the ignition unit 12b supplies power from the capacitor 12a to the electric detonator 13 for a predetermined detonation time. This causes the electric detonator 13 to ignite and detonate the explosive 2.

[0026] As shown in Figure 1, the antenna 14 is formed into a coil shape by being wound in an annular shape around the axis K, which is the extension direction of the main cylinder 11. The axis K extends in the direction of the propellant hole 41a, which is substantially perpendicular to the working face 41. The antenna 14 transmits and receives radio signals at frequencies with good penetration into rock, for example, 1 kHz to 500 kHz. The antenna 14 also serves as a receiving coil that receives electrical energy wirelessly. The antenna 14 receives electrical energy at frequencies of 1 kHz to 500 kHz from a separately prepared power supply device. The antenna 14 receives electrical energy immediately before or after loading the detonator 10 into the propellant hole 41a.

[0027] As shown in Figure 4, the electronic circuit 12 is equipped with a memory unit 12c, a calculation unit 12d, and a timer circuit 12e. The memory unit 12c stores a pre-set preparation time for each detonator 10. The preparation time is set to be shorter for detonators 10 closer to the center of the face 41 and longer for detonators 10 closer to the ends. The calculation unit 12d calculates the detonation time by adding the preparation time stored in the memory unit 12c to the delay time of the delay information included in the detonation signal received by the antenna 14. The timer circuit 12e counts the detonation time calculated by the calculation unit 12d and then transmits a signal to the ignition unit 12b. The timer circuit 12e counts the detonation time related to any of the multiple detonation signals, for example, it counts the detonation time related to the last detonation signal that was successfully received. After receiving the signal from the timer circuit 12e, the ignition unit 12b supplies power to the electric detonator 13.

[0028] As shown in Figure 1, the detonation system 1 has a relay device (relay device for detonation system) 20 that relays the transmission of detonation signals from the blaster 3 to multiple detonators 10. As shown in Figure 2, the relay device 20 has a box-shaped relay device body 21 mounted on the top of the flying body 30. The relay device body 21 is equipped with an upstream receiver 23, which is a rod-shaped upright antenna. As shown in Figure 4, the upstream receiver 23 is electrically connected to a control circuit 22 inside the relay device body 21. The upstream receiver 23 receives the radio detonation signal from the antenna 3a of the blaster 3 at a frequency of, for example, 300 MHz to 3 GHz. The analog detonation signal received by the upstream receiver 23 is detected and output as a digital signal to the control circuit 22.

[0029] As shown in Figure 2, the relay device 20 has a downstream transmitter 24 at the bottom of the aircraft 30. The downstream transmitter 24 is an annular antenna extending around the axis of the first axis J1. The first axis J1 extends approximately horizontally, for example, when the aircraft 30 is stationary in the air. As shown in Figure 4, the downstream transmitter 24 is electrically connected to a control circuit 22 in the relay device body 21. The detonation signal received by the upstream receiver 23 is transmitted to the downstream transmitter 24 via the control circuit 22. The digital detonation signal transmitted by the control circuit 22 is modulated into an analog signal and output to the downstream transmitter 24. The downstream transmitter 24 wirelessly transmits the detonation signal to each detonator 10 at a frequency of, for example, 1 kHz to 500 kHz, more preferably 30 kHz to 300 kHz.

[0030] As shown in Figure 2, the downstream transmitter 24 has a coil 24a. The coil 24a is provided in an annular shape, for example, with a diameter of 300 mm to 1500 mm. The number of turns in which the coil 24a is wound is, for example, 3 to 30. The downstream transmitter 24 has an annular and tubular frame member 24c with approximately the same diameter as the coil 24a. The coil 24a is inserted into the frame member 24c and wound around it. The coil 24a maintains its annular shape by being held by the annular frame member 24c. This suppresses changes in impedance in the circuit including the coil 24a. The frame member 24c is formed from an insulating material such as synthetic resin or a wooden frame. In the case of a wooden frame, for example, the coil may be wound in a square shape around the outer circumference of a cross shape made of two rods, or the coil may be wound in a hexagonal shape around the outer circumference of a shape made of three intersecting rods.

[0031] As shown in Figure 3, the downstream transmitter 24 is detachable from the underside of the aircraft 30. The downstream transmitter 24 is provided with a connection part 24b. The connection part 24b is provided with a connection terminal that is electrically connected to the coil 24a. The downstream transmitter 24 is mounted on the underside of the aircraft 30 in a position with the connection part 24b facing upwards. At this time, the coil 24a and the control circuit of the relay device body 21 (see Figure 4) are electrically connected via the connection part 24b.

[0032] As shown in Figure 2, the flying body 30 is integrated with the relay device body 21. The flying body 30 is a remotely controlled flying device, commonly known as a drone. The flying body 30 is a movable mechanism that can move the relay device 20 to any position and orientation. The flying body 30 has multiple rotors 31, for example, four rotors 31. Each rotor 31 rotates by the drive of a rotor motor 31a. By rotating the multiple rotors 31, the relay device 20, including the flying body 30, can be flown and stationary in any position and orientation in the air. As shown in Figure 3, a holding mechanism 33 consisting of a pair of movable arms is provided at the bottom of the flying body 30. The holding mechanism 33 detachably holds the connection part 24b of the downstream transmitter 24. The holding mechanism 33 can hold the connection part 24b of the downstream transmitter 24 by rotating inward by a holding motor 33a (see Figure 4). The holding mechanism 33 can release the connection portion 24b of the downstream transmitter 24 by rotating outward with the holding motor 33a.

[0033] As shown in Figure 4, the aircraft 30 is equipped with a control transceiver 32 that can wirelessly transmit and receive signals from the antenna 4a of the control unit 4. The control transceiver 32 transmits and receives wireless signals, for example, in the 2.4GHz band. The aircraft 30 is mounted on a controller 34. The controller 34 is electrically connected to the rotor motor 31a, the holding motor 33a, and the control transceiver 32. The controller 34 drives the rotor motor 31a or the holding motor 33a based on the operation signals received by the control transceiver 32 from the control unit 4. This rotates the rotor 31 (see Figure 1) and allows the relay device 20, including the aircraft 30, to fly. It also drives the holding mechanism 33 to attach and detach the downstream transmitter 24. The relay device 20 is equipped with a power supply 25 that supplies power to the relay device body 21 and the various structures of the aircraft 30.

[0034] Referring to Figures 4 and 6, the delay information of the delay time included in each detonation signal and the detonation time for each detonator 10 will be explained. An example will be given in the case where four upstream and downstream detonation signals are transmitted, from the first to the fourth. The blaster 3 transmits the first upstream detonation signal at time t0. The first delay time D1 included in the first upstream and downstream detonation signal is the time from time t0 to a predetermined time td. The blaster 3 transmits the second upstream detonation signal after the first transmission time difference E1 has elapsed from time t0. The second delay time D2 included in the second upstream and downstream detonation signal is the time obtained by subtracting the first transmission time difference E1 from the first delay time D1.

[0035] The blaster 3 transmits a third upstream detonation signal after a second transmission time difference E2 has elapsed from time t0. The third delay time D3 included in the third upstream / downstream detonation signal is the time obtained by subtracting the second transmission time difference E2 from the first delay time D1. The blaster 3 transmits a fourth upstream detonation signal after a third transmission time difference E3 has elapsed from time t0. The fourth delay time D4 included in the fourth upstream / downstream detonation signal is the time obtained by subtracting the third transmission time difference E3 from the first delay time D1. The initial first delay time D1 and the final fourth delay time D4 are set so that the relay device 20 can be moved from the vicinity of the working face 41 to the vicinity of the blaster 3 between the time the detonator 10 receives the final fourth downstream detonation signal and time td. In other words, the relay device 20 moves from the vicinity of the tunnel face 41 to the vicinity of the blaster 3 during the fourth delay time D4, which is obtained by subtracting the third transmission time difference E3 from the first delay time D1.

[0036] Therefore, regardless of which of the first to fourth downstream detonation signals a detonator 10 receives, time td becomes the end time of the delay time or the start time of the preparation time. This is the same for all detonator 10s. Each detonator 10 stores different preparation times P1 to P5. The first detonator 10 detonates with a detonation time equal to time td plus preparation time P1. Similarly, the second, third, fourth, and fifth detonator 10 detonate with a detonation time equal to time td plus preparation times P2, P3, P4, and P5, respectively. Therefore, each detonator 10 detonates with the same detonation time regardless of which of the first to fourth downstream detonation signals it receives.

[0037] Referring to Figures 1-6, a series of operations will be described in which a detonation signal is transmitted from the blaster 3 to multiple detonators 10 via the relay device 20. First, the aircraft 30 is flown in the vicinity of the blaster 3 and the control unit 4 with the downstream transmitter 24 detached. The holding mechanism 33 of the aircraft 30 is driven to hold the connection part 24b of the downstream transmitter 24 (step 01 in Figure 5; hereinafter referred to as S01). The downstream transmitter 24 is electrically connected to the relay device body 21. The operation proceeds to transmit the first upstream / downstream detonation signal with n=1 (S02). The aircraft 30 is moved remotely together with the relay device 20 to a first position near the face 41 and stopped, or stopped in a first orientation near the face 41 (S03). The first orientation is, for example, a posture in which the axis K of the detonator 10 and the first axis J1 of the coil 24a are approximately parallel.

[0038] The antenna 3a of the blaster 3 transmits a first upstream detonation signal including first delay information (S04). The first delay time D1 included in the first delay information is calculated by the calculation unit 3d. The upstream receiver 23 of the relay device 20 receives the first upstream detonation signal (S05). The downstream transmitter 24 of the relay device 20 transmits a first downstream detonation signal including first delay information (S06).

[0039] The antennas 14 of each detonator 10 in the propellant hole 41a receive the first downstream detonation signal (S07). If the antennas 14 of the detonator 10 successfully receive the first downstream detonation signal, the calculation unit 12d of the detonator 10 calculates the first detonation time by adding the first delay time D1 included in the first delay information and the preparation time stored in the storage unit 12c (S08). If the antennas 14 of the detonator 10 fail to receive the first downstream detonation signal, the detonator 10 remains in a waiting state until it successfully receives subsequent downstream detonation signals. After step S08, the timer circuit 12e of the detonator 10 counts the first detonation time (S09).

[0040] Next, 1 is added to n and the operation to transmit the second upstream / downstream detonation signal is initiated (S10). If n becomes greater than or equal to nmax (for example, 4 in Figure 6) when 1 is added to n, the operation proceeds to S12. If n is less than nmax, the process returns to S03. The aircraft 30 is moved together with the relay device 20 to a second position near the face 41 and brought to rest, or brought to rest in a second orientation near the face 41 (S03). The second position, third position, fourth position, etc. are, for example, positions moved along the face 41 from the first position. The second position, third position, fourth position, etc. are, for example, positions that gradually move away from the face 41 starting from the first position. The second orientation, third orientation, fourth orientation, etc. are, for example, orientations obtained by changing the direction of the first axis J1 of the coil 24a horizontally at predetermined angular intervals from the first orientation. The predetermined angle intervals are, for example, 120°, 90°, 60°, 45°, etc. The predetermined angle intervals do not have to be uniform; they may be uneven.

[0041] The antenna 3a of the blaster 3 transmits a second upstream detonation signal containing second delay information (S04). The second delay time D2 included in the second delay information is calculated by the calculation unit 3d as the time obtained by subtracting the first transmission time difference E1, which is the time from the first upstream detonation signal to the transmission of the second upstream detonation signal, from the first delay time D1. Thereafter, steps S03 to S10 are repeated until n is greater than or equal to nmax. In S09, the timer circuit 12e of the detonator 10 counts the nth detonation time related to the last successfully received nth downstream detonation signal.

[0042] When n is greater than or equal to nmax, the aircraft 30, together with the relay device 20, flies remotely to the vicinity of the blaster 3 from the face or the face surface 41 which is the target of blasting (S12). The downstream transmitter 24 can be removed while the evacuated aircraft 30 is stationary in the air. This prevents the downstream transmitter 24 from interfering with the landing of the aircraft 30, allowing the aircraft 30 to land stably. After the timer circuit 12e of each detonator 10 counts the detonation time, the ignition unit 12b supplies power to the electric detonator 13 (S13). The electric detonator 13 detonates the explosive 2 from the back of the propellant hole 41a in the order of the main die 2a and then the auxiliary die 2b (S14).

[0043] As described above, the relay device 20 for the detonation system 1 relays the signal from the blaster 3 to the detonator 10 installed on the tunnel face or the tunnel face surface 41 that is the target of blasting, as shown in Figures 1 and 4. The relay device 20 has a flying body 30, an upstream receiver 23, and a downstream transmitter 24. The flying body 30 flies by remote control or autopilot. The upstream receiver 23 is installed on the flying body 30 and receives the upstream detonation signal from the blaster 3 wirelessly. The downstream transmitter 24 is installed on the flying body 30 and transmits a downstream detonation signal wirelessly to the detonator 10 when the upstream receiver 23 receives the upstream detonation signal. The detonator 10 detonates based on the downstream detonation signal.

[0044] Therefore, the relay device 20 can be positioned in the air near the tunnel face 41 without the worker having to approach the tunnel face 41. Moreover, the detonator 3 can transmit a downstream detonation signal wirelessly to the detonator 10 via the relay device 20, thereby detonating the detonator 10, without the worker having to approach the tunnel face 41. This increases the safety of the blasting. Furthermore, the flying body 30 increases the degree of freedom in positioning the relay device 20 in the air. This allows for more reliable transmission of the downstream detonation signal from the relay device 20 to each detonator 10. In addition, the flying body 30 allows the relay device 20 to be recovered during blasting. This contributes to resource conservation and reduction of running costs.

[0045] As shown in Figures 1 and 2, the aircraft 30 has rotor blades 31. The aircraft 30 is stationary at a predetermined position relative to the face or the face surface 41 that is the target of blasting, by means of the rotor blades 31. Therefore, the relay device 20 transmits the downstream detonation signal while stationary at the predetermined position. This allows the aircraft 30 to be moved to a second predetermined position where communication with the detonator 10 is easier, even if there is a detonator 10 in a position that is difficult to communicate with at the first predetermined position. This allows the aircraft 30 to be moved efficiently while the downstream detonation signal can be reliably transmitted from the relay device 20 to each detonator 10.

[0046] As shown in Figures 3 and 4, the aircraft 30 has a control transceiver (control receiver) 32 and a holding mechanism 33. The control transceiver 32 receives control signals for remote control. The holding mechanism 33 detachably holds the downstream transmitter 24. The holding mechanism 33 is remotely controlled via the control transceiver 32. Therefore, the relay device 20 can fly smoothly together with the aircraft 30. For example, a downstream transmitter 24 fixed to the aircraft 30 may interfere with the takeoff and landing of the aircraft 30. By using the control transceiver 32 and the holding mechanism 33, the downstream transmitter 24 can be attached to and detached from the aircraft 30 while the aircraft 30 is in flight. Therefore, even when using a large downstream transmitter 24, for example, the relay device 20 can fly smoothly.

[0047] As shown in Figures 1 and 5, the downstream transmitter 24 transmits a first downstream detonation signal as a downstream detonation signal when the aircraft 30 is in a first position or orientation. When the aircraft 30 moves from the first position to the second position or changes orientation from the first to the second orientation, it transmits a second downstream detonation signal as a downstream detonation signal. Therefore, the downstream transmitter 24 transmits the downstream detonation signal multiple times at multiple positions or orientations. This suppresses the transmission of the downstream detonation signal to multiple detonators 10. As a result, the downstream detonation signal can be transmitted to each detonator 10 more reliably.

[0048] As shown in Figures 4 and 5, the downstream transmitter 24 transmits multiple downstream detonation signals. A controller 34 is mounted on the aircraft 30. The controller 34 controls the aircraft 30 to move away from the face 41 after the downstream transmitter 24 transmits the last downstream detonation signal. Therefore, after the transmission of the last downstream detonation signal and before the detonator 10 detonates, the relay device 20 is moved away from the face 41. This allows the relay device 20 to be reused without being consumed for each blast.

[0049] As shown in Figure 2, the upstream receiver 23 is rod-shaped and mounted on the upper part of the aircraft 30. The downstream transmitter 24 is larger and ring-shaped than the upstream receiver 23 and mounted on the lower part of the aircraft 30. Therefore, the upstream receiver 23 can be mounted in a shape, size, and position that does not interfere with the flight of the aircraft 30. The downstream transmitter 24 can be mounted in a large, ring-shaped size that is suitable for transmitting a downstream detonation signal in a frequency band with good rock penetration. Moreover, the downstream transmitter 24 can be positioned so as not to interfere with the flight of the aircraft 30.

[0050] As shown in Figures 1, 4, and 5, in the detonation method for a detonator 10 installed on a tunnel face or tunnel face surface 41 that is to be blasted, the blaster 3, which is separated from the tunnel face surface 41, transmits a first upstream detonation signal wirelessly. The upstream receiver 23 of the relay device 20 installed on the aircraft 30 receives the first upstream detonation signal. The downstream transmitter 24 of the relay device 20 installed on the aircraft 30 transmits a first downstream detonation signal wirelessly to the detonator 10. The aircraft 30 moves from a first position to a second position, or changes direction from a first direction to a second direction. The blaster 3 transmits a second upstream detonation signal wirelessly. The upstream receiver 23 receives the second upstream detonation signal. The downstream transmitter 24 transmits a second downstream detonation signal wirelessly. The aircraft 30 moves away from the tunnel face surface 41. The detonator 10, having received the first downstream detonation signal and / or the second downstream detonation signal, detonates.

[0051] Therefore, the relay device 20 can be positioned in the air near the tunnel face 41 without the worker having to approach the tunnel face 41. Moreover, the detonator 10 can be detonated by wirelessly transmitting a downstream detonation signal from the blaster 3 to the detonator 10 via the relay device 20 without the worker having to approach the tunnel face 41. This increases the safety of the blasting. Furthermore, the downstream transmitter 24 transmits the downstream detonation signal multiple times from multiple positions or orientations that can be moved by the flying body 30. The detonator 10 detonates upon receiving one of the multiple downstream detonation signals. This ensures that the downstream detonation signal is transmitted to each detonator 10 more reliably. In addition, the relay device 20 can be evacuated and recovered from the tunnel face 41 by the flying body 30 before the detonator 10 detonates. This allows for resource conservation and reduction of running costs.

[0052] As shown in Figures 5 and 6, the first upstream detonation signal and the first downstream detonation signal contain first delay information relating to the first delay time. The second upstream detonation signal and the second downstream detonation signal contain second delay information relating to the second delay time, which is shorter than the first delay time. When the detonator 10 receives the first downstream detonation signal, it calculates the first detonation time by adding the preparation time to the first delay time. When the detonator 10 receives the second downstream detonation signal, it calculates the second detonation time by adding the preparation time to the second delay time. The detonator 10 detonates either when the first detonation time has elapsed since receiving the first downstream detonation signal, or when the second detonation time has elapsed since receiving the second downstream detonation signal.

[0053] Therefore, for example, the second delay time is made shorter than the first delay time by the difference in transmission time between the first upstream detonation signal and the second upstream detonation signal. This makes it possible to make the detonation time when the detonator 10 detonates after the first detonation time has elapsed from the time it receives the first downstream detonation signal the same as the detonation time when the detonator 10 detonates after the second detonation time has elapsed from the time it receives the second downstream detonation signal. In this way, by transmitting multiple downstream detonation signals to the detonator 10 with staggered transmission times, signal transmission leaks can be suppressed, and the detonator 10 can detonate at the same time regardless of which downstream detonation signal it receives.

[0054] Other embodiments of the present disclosure will be described with reference to Figure 7. The detonation system 50 of the second embodiment has a relay device 51 instead of the relay device 20 shown in Figure 1. The relay device 51 has a downstream transmitter 52 instead of the downstream transmitter 24 shown in Figure 1. In the following description, only the parts that differ from the first embodiment will be described in detail.

[0055] As shown in Figure 7, the downstream transmitter 52 has three coils: a first coil 52a, a second coil 52b, and a third coil 52c. The first coil 52a is an annular coil wound around the axis of a first shaft J1 that extends substantially horizontally. The second coil 52b is an annular coil wound around the axis of a second shaft J2 that is substantially perpendicular to the first shaft J1 and extends substantially horizontally. The second coil 52b is an annular coil wound around the axis of a third shaft J3 that is substantially perpendicular to the first shaft J1 and substantially perpendicular to the second shaft J2 and stands vertically.

[0056] As shown in Figure 7, the first coil 52a, the second coil 52b, and the third coil 52c are annular structures of approximately the same diameter, for example, annular structures with a diameter of 300 mm to 1500 mm. The first coil 52a, the second coil 52b, and the third coil 52c have approximately the same number of turns, for example, 3 to 30. The first axis J1, the second axis J2, and the third axis J3 are approximately perpendicular to each other at the center of the downstream transmitter 52. The downstream transmitter 52 forms a spherical three-dimensional structure. The first coil 52a, the second coil 52b, and the third coil 52c are each annular and tubular and are inserted into and wound around a frame member 52d made of insulating material. The downstream transmitter 52 is detachably held at the bottom of the aircraft 30 (see Figure 3). The first coil 52a, the second coil 52b, and the third coil 52c transmit downstream detonation signals containing the same delay information at the same frequency, for example, 1kHz to 500kHz, more preferably 30kHz to 300kHz, to each other, based on the upstream detonation signal received by the upstream receiver 23 from the blaster 3.

[0057] As shown in Figure 7, the first axis J1, the second axis J2, and the third axis J3 are approximately orthogonal to each other, so that the distribution and direction of the magnetic fields generated by the first coil 52a, the second coil 52b, and the third coil 52c are mutually different. This reduces the number of times the orientation of the downstream transmitter 52 is changed, while still allowing the detonation signal generated by one of the first coil 52a, the second coil 52b, or the third coil 52c to be transmitted to the antenna 14 (see Figure 1) of the detonator 10.

[0058] As shown in Figure 7, the downstream transmitter 52 has a first coil 52a, a second coil 52b, and a third coil 52c. The first coil 52a is wound around the axis of the first shaft J1. The second coil 52b is wound around the axis of the second shaft J2, which extends in a direction intersecting the first shaft J1. The third coil 52c is wound around the axis of the third shaft J3, which extends in a direction intersecting both the first shaft J1 and the second shaft J2. Therefore, the downstream transmitter 52 has a three-dimensional structure with three coils having mutually different axial directions. By flying the relay device 20 on the aircraft 30, the three-dimensional downstream transmitter 52 can be positioned in any position or orientation in the air. Therefore, the downstream detonation signal can be transmitted more reliably from the downstream transmitter 52 to each detonator 10 positioned at various locations on the face 41.

[0059] Other embodiments of the present disclosure will be described with reference to Figure 8. The detonation system 60 of the eighth embodiment has a relay device 61 instead of the relay device 20 shown in Figure 3. The relay device 61 is separate from the aircraft 30 and is detachably held on the aircraft 30. In the following description, only the parts that differ from the first embodiment will be described in detail.

[0060] As shown in Figure 8, the relay device 61 comprises a relay device body 62, an upstream receiver 63, and a downstream transmitter 64, all integrally mounted together. The downstream transmitter 64 has a similar shape to the downstream transmitter 24 (see Figure 3) and is an annular antenna extending around the axis of the first axis J1. The first axis J1 extends approximately horizontally, for example, when the aircraft 30 is stationary in the air. The downstream transmitter 64 has, for example, an annular coil 64a with a diameter of 300 mm to 1500 mm. The number of turns in which the coil 64a is wound is, for example, 3 to 30. The coil 64a is inserted and wound inside an annular and tubular frame member 64b made of insulating material. The downstream transmitter 64 transmits a detonation signal wirelessly to each detonator 10 (see Figure 1) at a frequency of, for example, 1 kHz to 500 kHz, more preferably 30 kHz to 300 kHz.

[0061] As shown in Figure 8, the relay unit body 62 is integrally connected to the upper part of the downstream transmitter 64. An upstream receiver 63, which is a rod-shaped antenna, extends from the relay unit body 62. The upstream receiver 63 receives a radio detonation signal from the antenna 3a (see Figure 1) of the blaster 3 at a frequency of, for example, 300 MHz to 3 GHz.

[0062] As shown in Figure 8, the relay device 61 is detachably held by a holding mechanism 33 at the bottom of the aircraft 30. The holding mechanism 33 supports the entire relay device 61 by holding, for example, the relay device body 62. With this configuration, the relay device 61 can be attached to and detached from the aircraft 30 without the need to electrically connect each electrical component of the relay device 61 to each electrical component of the aircraft 30. The relay device 61 described above provides the same effects as the first embodiment.

[0063] Although embodiments of the present invention have been described above, it will be apparent to those skilled in the art that many substitutions, improvements, and modifications are possible without departing from the purpose of the present invention. Therefore, embodiments of the present invention may include all substitutions, improvements, and modifications that do not depart from the spirit and purpose of the appended claims. For example, embodiments of the present invention are not limited to the above structure and can be modified as follows.

[0064] For example, detonation systems 1, 50, and 60 can be used for tunnel excavation work, as described above. Alternatively, they may be applied to demolition work on structures such as buildings or to seabed excavation work. Detonation systems 1, 50, and 60 have been shown as examples in which the blaster 3 and the controller 4 are separate components. Alternatively, the blaster 3 and the controller 4 may be combined into a single component.

[0065] An example of a detonation system 1, 50, 60 that transmits a detonation signal via relay devices 20, 51, 61 is shown. In addition, relay devices 20, 51, 61 may also be used to transmit a signal to the blaster 3 indicating that each detonator 10 has completed preparation for detonation. For example, signals to verify the ID of each detonator 10 loaded in each propellant hole 41a, or signals to store the preparation time in each detonator 10, may be transmitted and received via relay devices 20, 51, 61. In this case, the upstream receiver 23 also functions as a transmitter. The downstream transmitters 24, 52, 64 also function as receivers.

[0066] An example of a detonation system 1,50,60 is provided in which relay devices 20,51,61 are flown to the vicinity of the tunnel face 41 when transmitting a detonation signal. In addition, for example, in the event of a non-detonation, the relay devices 20,51,61 may be flown to the vicinity of the tunnel face 41, and the mounted camera may be used to remotely scout the undetonated propellant hole 41a. Furthermore, by providing arms or the like on the relay devices 20,51, the system may be configured to recover the explosives 2, etc., from the undetonated propellant hole 41a.

[0067] The shape, arrangement, and orientation of the downstream transmitters 24, 52, and 64 on the aircraft 30 are not limited to those exemplified and may be changed as appropriate. For example, each coil 24a, 52a, 52b, 52c, and 64a may be arranged in an elliptical or polygonal ring shape. Downstream transmitters 24 and 64 equipped with one coil each 24a and 64a, and downstream transmitter 52 equipped with three coils 52a, 52b, and 52c are given as examples. Alternatively, for example, a downstream transmitter equipped with two coils whose axes intersect each other may be provided in the relay device. Downstream transmitter 52 in which the first axis J1, second axis J2, and third axis J3 are approximately perpendicular to each other is given as an example, but it is not necessary for any or all of the three axes to intersect. Downstream transmitters 24, 52, and 64 in which the first axis J1 is held in an approximately horizontal position on the aircraft 30 are given as examples. Alternatively, the first axis J1 may be tilted with respect to the horizontal direction.

[0068] The downstream transmitters 24, 52, and 64 are shown as examples in which each coil 24a, 52a, 52b, 52c, and 64a is inserted into frame members 24c, 52d, and 64b to maintain their shape. Alternatively, for example, the material of each coil 24a, 52a, 52b, 52c, and 64a may be a conductive material with high mechanical strength, and the shape may be maintained without using frame members.

[0069] The detonation systems 1, 50, and 60, which transmit the detonation signal multiple times, are shown as examples. Alternatively, for example, the detonation signal may be transmitted only once. Compared to transmitting the signal multiple times, the certainty of transmitting the detonation signal to all detonators 10 is reduced, but the work time can be shortened while maintaining the high level of safety of the blasting and the advantage of being able to recover the relay devices 20, 51, and 61.

[0070] Between the transmission of the first downstream detonation signal and the transmission of the second downstream detonation signal, the downstream transmitters 24, 52, and 64 may both move from the first position to the second position and change their orientation from the first to the second. The time intervals between each of the multiple detonation signals transmitted may be equal or unequal. Detonation systems 1, 50, and 60 are shown as examples in which the aircraft 30 remains stationary in the air during the transmission and reception of detonation signals. Alternatively, for example, the aircraft 30 may be moved at a low speed while the detonation signals are transmitted and received. An example is shown in which the aircraft 30 flies by the rotation of a rotor blade 31. Alternatively, for example, the aircraft may be levitated by a helium balloon or the like. [Explanation of Symbols]

[0071] 1…Detonation system 2... Explosives, 2a... Main die, 2b... Additional die 3...blaster, 3a...antenna, 3b...input unit, 3c...electronic circuit, 3d...calculation unit 3e... Timer circuit 4...Controller, 4a...Antenna, 4b...Input, 4c...Output 10...detonator 11…Main body tube 12...electronic circuit, 12a...condenser, 12b...ignition section, 12c...storage section, 12d...calculation section 12e...Timer circuit 13… Electric detonator 14… Antenna (receiving coil) 20…(Relay device for detonation system) 21…Relay device main unit 22...Control circuits 23…Upstream receiver 24... Downstream transmitter, 24a... Coil, 24b... Connection part, 24c... Frame member 25…Power supply 30... Flying object 31... Rotary blade, 31a... Rotary blade motor 32…Control transmitter / receiver (control receiver) 33...Holding mechanism, 33a...Holding motor 34…Controller 40...Tunnel 41...Face (face, target for blasting), 41a...Explosive hole, 41b...Sealing member 50…Detonation system (second embodiment) 51…(Relay device for detonation system) 52... Downstream transmitter, 52a... First coil, 52b... Second coil, 52c... Third coil 52d...frame member 60…Detonation system (third embodiment) 61…(Relay device for detonation system) 62…Relay device main unit 63…Upstream receiver 64... Downstream transmitter, 64a... Coil, 64b... Frame member D1...First delay time, D2...Second delay time, D3...Third delay time, D4...Fourth delay time E1...First transmission time difference, E2...Second transmission time difference, E3...Third transmission time difference P1,P2,P3,P4,P5…preparation time J1...First axis, J2...Second axis, J3...Third axis, K...Axis (of the detonator antenna)

Claims

1. A relay device for a detonation system that relays signals from an blaster to a detonator installed at the blasting face or target, Aircraft that fly by remote control or autopilot, An upstream receiver is provided on the aircraft to wirelessly receive an upstream detonation signal from the blaster, A relay device for a detonation system, which is provided on the aircraft and has a downstream transmitter that wirelessly transmits a downstream detonation signal to the detonator when the upstream receiver receives the upstream detonation signal, and the detonator detonates based on the downstream detonation signal.

2. A relay device for a detonation system according to claim 1, The aforementioned flying object is a relay device for a detonation system having rotor blades that remain stationary at a predetermined position relative to the face or the target to be blasted.

3. A relay device for a detonation system according to claim 2, The aforementioned flying object is a relay device for a detonation system, comprising a control receiver for receiving control signals for remote control and a holding mechanism for detachably holding the downstream transmitter, wherein the holding mechanism is remotely controlled via the control receiver.

4. A relay device for a detonation system according to any one of claims 1 to 3, The downstream transmitter is a relay device for a detonation system that transmits a first downstream detonation signal as the downstream detonation signal when the aircraft is in a first position or orientation, and transmits a second downstream detonation signal as the downstream detonation signal when the aircraft moves from the first position to a second position or changes orientation from the first orientation to a second orientation.

5. A relay device for a detonation system according to any one of claims 1 to 3, The downstream transmitter transmits the downstream detonation signal multiple times. A relay device for a detonation system, in which a controller is mounted on the aircraft to control the aircraft to move away from the face or the target to be blasted after the downstream transmitter has transmitted the final downstream detonation signal.

6. A relay device for a detonation system according to any one of claims 1 to 3, The downstream transmitter is a relay device for a detonation system having a first coil wound around the axis of a first shaft, a second coil wound around the axis of a second shaft extending in a direction intersecting the first shaft, and a third coil wound around the axis of a third shaft extending in a direction intersecting both the first and second shafts.

7. A relay device for a detonation system according to any one of claims 1 to 3, The upstream receiver is rod-shaped and mounted on the upper part of the aircraft. The downstream transmitter is larger and more annular than the upstream receiver, and is a relay device for the detonation system located on the underside of the aircraft.

8. A method for detonating a detonator installed at the face of a blasting site or on a target, A blaster that has moved away from the face or the target to be blasted transmits a first upstream detonation signal wirelessly. The upstream receiver of the relay device installed on the aircraft receives the first upstream detonation signal. The downstream transmitter of the relay device installed on the aircraft transmits a first downstream detonation signal wirelessly to the detonator. The aforementioned flying object moves from a first position to a second position, or changes its orientation from a first orientation to a second orientation. The aforementioned blaster transmits a second upstream detonation signal wirelessly. The upstream receiver receives the second upstream detonation signal. The downstream transmitter transmits a second downstream detonation signal wirelessly. The flying object moves away from the face or the target of blasting, A detonation method in which the detonator detonates upon receiving the first downstream detonation signal and / or the second downstream detonation signal.

9. A detonation method according to claim 8, The first upstream detonation signal and the first downstream detonation signal include first delay information relating to a first delay time. The second upstream detonation signal and the second downstream detonation signal include second delay information relating to a second delay time shorter than the first delay time. The detonation method involves the detonator being detonated either when the first downstream detonation signal is received, the first detonation time is calculated by adding a preparation time to the first delay time, when the second downstream detonation signal is received, the second detonation time is calculated by adding a preparation time to the second delay time, and the detonation occurring either when the first detonation time has elapsed since the first downstream detonation signal was received, or when the second detonation time has elapsed since the second downstream detonation signal was received.

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