JP4237873B2 - Flying object - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a flying object ejected from an aircraft, and more specifically, the flying object has a substantially cylindrical shape, and has a stable wing of a folding and unfolding structure for stabilizing the flight posture at the rear of the outer periphery of the fuselage and the flying object. Is equipped with an antenna for transmitting and receiving radio waves, a power source, and a control electronic circuit, and while mounted on the aircraft, the outer peripheral surface of the flying object is placed on a container provided on the aircraft together with the injection means for emitting the flying object. It relates to flying objects that can be accommodated alongside.
[0002]
[Prior art]
As a means of defense when an aircraft is attacked by a radio wave-guided missile, it is a conventional substitute for an aircraft by reflecting the radio waves radiated from the missile into the air by scattering aluminum foil called chaff in the air. It has been done.
[0003]
However, Chaff is effective for missiles that are simply guided by radar reflected waves, but is not effective for missiles that fly by tracking the Doppler frequency of a fast moving target. There is a problem.
On the other hand, the thing of the mechanism which inject | emits the flying body as a kite from an aircraft, and this flying body radiates | emits the electromagnetic wave corresponded to the reflected wave of the radiation wave of a missile is also employ | adopted.
[0004]
In order to stabilize the flying posture of the flying object, usually, a plurality of stabilizing wings are attached to the rear of the fuselage of the flying object. There are two types of stabilizer wings: one that is fixed radially to the rear of the fuselage, and one that is folded along the outer periphery of the fuselage and accommodated in a container while the flying object is mounted on the aircraft.
In the case of the former type in which the stable wings are fixed radially to the rear part of the fuselage, a large storage space is required inside the aircraft, and the mounting efficiency is not good. On the other hand, in the case of the latter type in which the stabilizing wing is folded and accommodated in the container, it is usually necessary to equip the container with a folding and unfolding mechanism of the stabilizing wing, which increases the size of the container, and thus a large container storage space is required. Even in this case, the mounting efficiency is not good.
[0005]
The present applicant has solved the above-mentioned problems, can easily and miniaturize the mechanism for folding and unfolding the stable wing, and can firmly fix the deployed stable wing to increase the degree of freedom of the flying attitude of the flying object. We have already proposed a stable wing folding deployment structure of the body.
As shown in FIG. 12, the flying body 1 shown in Japanese Patent Laid-Open No. 6-74696 has a plurality of stabilizing blades 3 radially attached to the rear part of the cylindrical body 2 of the flying body 1. And while the flying object 1 is mounted on the aircraft, the stabilizing wing 3 is folded as shown by a broken line, and when ejected from the aircraft, the stabilizing wing 3 is radially expanded as shown by a solid line. Yes.
[0006]
The specific mounting structure of the stabilizer wing 3 is a hinge connection having a hinge shaft 4 parallel to the center axis of the fuselage at each apex portion formed in the shape of a rectangular tube, for example, on the outer peripheral surface of the rear part of the fuselage 2. The end face shape of the fuselage side hinge 5a and the stabilizing blade side hinge 5b (see FIG. 13) connected to each other at the hinge shaft 4 is formed in a slope shape inclined at an angle of, for example, 45 degrees with respect to the hinge rotation surface. For example, the compression spring 7 is arranged between the front fuselage side hinge 5a and the rear stable wing side hinge 5b on the same axis as the hinge shaft 4 and constantly urges the stable wing side hinge 5b toward the fuselage side hinge 5a. Is installed. Here, reference numeral 9 indicates an injection means for injecting a flying object composed of an explosive chamber and a piston.
[0007]
Thus, while the flying object 1 is mounted on the aircraft, the stabilizing wing 3 is folded and accommodated in the cartridge (container) 8 as shown in FIG. 13, and after being launched from the aircraft, the outer peripheral surface of the fuselage 2 Can be deployed and fixed radially.
[0008]
[Problems to be solved by the invention]
However, since the flying body 1 has a structure in which the stabilizing blade 3 is attached to the outer peripheral surface of the rear portion of the cylindrical body 2 of the flying body 1 via hinge coupling, the outer circumferential surface of the stabilizing blade 3 and the hinge coupling is In a state where the cartridge 8 is accommodated in contact with the inner peripheral surface of the cartridge 8, it is necessary to make the diameter of the body 2 smaller than the inner diameter of the cartridge 8 in order to ensure the space volume of the stabilizing blade 3 and the hinge coupling portion. Therefore, there is a problem that a gap is generated between the front portion of the body 2 and the cartridge 8 (see FIG. 13).
[0009]
That is, since the outer diameter of the front part of the body 2 cannot be increased to a size close to the inner diameter of the cartridge 8, the mounting space volume of the antenna 6 and the electronic circuit (not shown) in the front part of the body 2 is small. Therefore, it is necessary to provide the antenna 6, the electronic circuit, and the like long in the axial direction of the body 2. For this reason, the center of gravity of the flying object 1 cannot be provided at the front position, and the load is distributed in the axial direction of the fuselage 2 around the center of gravity, resulting in a state of large moment of inertia, thereby improving flight stability. It becomes an obstacle in case. Here, the flight stability refers to a stable flight attitude (wind weather stability) in which a flying object 1 launched vertically downward from an aircraft changes its flight attitude to a horizontal direction opposite to the air current and rides on the air current. That means.
[0010]
The present invention was made in order to further improve the flying object proposed by the applicant, and the center of gravity of the flying object can be provided at the front position, and the load is axially centered on the center of gravity. It is an object of the present invention to provide a flying object that is concentrated in the state of inertia and has a small moment of inertia, and thus has excellent flight stability.
[0011]
[Means for Solving the Problems]
The flying object according to the present invention is a flying object ejected from an aircraft, and the flying object main body is formed in a substantially cylindrical shape, and is folded by a hinge structure at the rear part of the flying object main body while being mounted on the aircraft. In addition, it has a stable wing having a structure that is urged by an urging member to expand radially when ejected from an aircraft, and an antenna for transmitting and receiving radio waves, a power source, and an electronic circuit are provided in the flying body body. In the flying object that is accommodated along the outer peripheral surface of the flying object body in a container provided in the aircraft together with the injection means for injecting the flying object while being mounted on the aircraft, The diameter of the part is a stepped cylindrical shape larger than the diameter of the rear part (the invention according to claim 1).
[0012]
As a result, when the stabilizing wing is folded and accommodated in a container that is slightly larger than the outer shape of the flying object, the front part of the flying object body is formed with a larger diameter than the rear part. The center of gravity of the flying object can be provided at the front position by providing an electronic circuit etc. in the axial direction of the cylinder in the front of the main body, and the load is concentrated in the axial direction of the cylinder around the center of gravity. Thus, a flying object having a small moment and excellent in flying stability can be obtained.
[0013]
Further, in the flying object according to the present invention, the power source and the electronic circuit are formed long in the radial direction of the flying body main body so as to be substantially close to the inner peripheral surface of the flying body main body and short in the axial direction. And is substantially accommodated in the large-diameter front portion of the flying body main body so that the center of gravity of the flying body is positioned forward and the load is concentrated near the center of gravity (according to claim 2). Invention) and the above-described effects of the present invention can be suitably achieved.
[0014]
Further, in the flying object according to the present invention, the antenna occupies a predetermined space volume and is formed long in the radial direction of the flying object body so as to be substantially the same as the diameter of the front part of the flying object body. When the front body of the flying body is housed in front of the front portion of the flying body (invention according to claim 3), the above-described book The effects of the invention can be achieved more suitably. Further, since the antenna has a large diameter, the antenna performance is good.
[0015]
In the flying object according to the present invention, the electronic circuit includes a power control circuit that controls power supplied from a power source, and the power control circuit includes a substrate and an electronic component mounted on the substrate. And a metal plate for heat dissipation formed on the back surface of the substrate, the substrate is provided with a bent portion, and the substrate is bent at the bent portion with the electronic component mounting surface facing outward, The metal plates are joined (invention according to claim 4).
[0016]
Conventionally, a power control circuit consisting of a board on which electronic components are mounted is housed in a module case for heat dissipation in order to efficiently dissipate the heat generated from the electronic components. Therefore, in order to secure a constant mounting space volume, it was necessary to provide the board (and module case) long in the axial direction of the flying object. Instead of providing a module case, a metal plate with a small proportion of the space volume is provided, so that the required space volume can be reduced compared to the case where a module case is provided, and electronic components are mounted on both sides of the board. The required space volume can also be reduced by increasing the mounting efficiency. For this reason, the substrate is formed in a short length in the axial direction of the flying object, It can be achieved in the preferred effects of the present invention that describes. Further, since the weight is reduced by not providing the module case, for example, the center of gravity can be easily provided forward by providing the reduced weight as a balancer at the tip of the flying object.
[0017]
In this case, the flying object is further formed of a metal material, and the end of the metal plate is connected to the flying object so that heat can be radiated to the outside from the flying object (the invention according to claim 5). The heat of the plate can be radiated more efficiently through the flying object.
In this case, furthermore, the folding portion of the power control circuit includes a slit along the folding direction, a rounded cutout portion along the direction perpendicular to the folding direction, and a fold along the direction perpendicular to the folding direction. When at least one of them is formed (invention according to claim 6), it can be easily bent at the bent portion, which is preferable.
[0018]
Further, in the flying body according to the present invention, the external signal connection terminal provided in the electric circuit is bent from the inner peripheral surface of the flying body main body to the outer peripheral surface at the open end of the flying body main body. The end of the external signal connection terminal is fixed, the bent portion of the external signal connection terminal forms a flat portion, and the flat portion supplies an external signal when the flying object is accommodated in the container. When the flying object is ejected while being in surface contact with the electrode, the external signal connection terminal and the external electrode are separated (invention according to claim 7).
[0019]
Conventionally, this external signal interface is performed by an ambulatory connector or the like, and when the flying object is ejected, the cable is cut and the ambiguous connector or the like is separated. However, in this case, cables, ambulatory connectors, etc. remain around the antenna, which may hinder the flying stability of the flying object, and may also hinder the emission of radio waves from the antenna. . In the case of the present invention, the external signal connection terminal is bent and fixed to the outer peripheral surface of the flying object body, and the flat surface portion is in surface contact with the external electrode. In the state in which the flying object is accommodated in the container, it can be reliably energized with an external electrode (not shown). Since the signal connection terminal does not cover the periphery of the antenna, it does not hinder the emission of radio waves from the antenna.
[0020]
DETAILED DESCRIPTION OF THE INVENTION
A preferred embodiment of a flying object according to the present invention (hereinafter referred to as this embodiment) will be described below with reference to the drawings.
First, as a flying body according to the present embodiment, a front flying body equipped with an antenna in the front is shown in FIG. 1 in a state where the stabilizing wing is spread, and in FIG. 2, a state in which the stabilizing wing is folded is shown. 3 shows a state in which the flying object for front is housed in a container.
[0021]
The appearance shape of the forward flying object (hereinafter simply referred to as a flying object unless otherwise specified) 10 is basically the same as that of the conventional flying object 1 described above. That is, a plurality of stabilizing blades 14 are radially attached to the rear portion of the flying body 10 (body) 12 of the flying body 10 by the hinge structure (hinge coupling) 16. While the flying object 10 is mounted on the aircraft, the stabilizer wing 14 is folded and stored in a container described later as shown in FIG. 2, and when ejected from the aircraft, the stabilizer wing 14 is shown in FIG. It is set as the structure which expands radially. Here, reference numeral 18 indicates an antenna made of a tungsten material having a large specific weight.
[0022]
The appearance of the flying object 10 is different from that of the conventional flying object 1 in that a stepped portion 12a is provided at a substantially central position in the axial direction of the substantially cylindrical flying object body 12, and the diameter D1 of the front part 12b of the flying object body is the rear part. It is the point formed larger than the diameter D2 of 12c (refer FIG. 2).
Therefore, as shown in FIG. 3, the diameter of the front portion 12 b of the flying body 12 is substantially the same as the diameter of the inner periphery of the container 20 in the state of being accommodated in the rectangular container 20 while being mounted on the aircraft. Thus, there is almost no gap between the front portion 12 b of the flying body 12 and the container 20 as in the case of the conventional flying body 1. That is, in the case of the conventional flying body 1, as described above, since the stabilizing wing 3 is attached to the outer peripheral surface of the rear portion of the cylindrical body 2, a special space for accommodating the stabilizing wing 3 is required. When a cartridge (container) 8 having a constant diameter is accommodated, a gap is formed between the front portion of the body 2 and the inner peripheral surface of the cartridge 8, but in the case of the flying object 10 of the present invention, the flying object body The rear portion 12c of the twelve is reduced in diameter, and the stabilizing blade 14 is accommodated in the space secured by reducing the diameter. Therefore, in the case where the flying bodies 1 and 10 are accommodated in the container 20 of the same size, the present invention. As for the thing, the diameter of the front part 12b of the flying body main body 12 can be formed larger than the conventional thing. As a result, the antenna 18 that requires a certain space volume is provided shorter in the length direction of the flying object 10 than the conventional antenna 6, and the electronic circuit described later also has a flying object compared to the conventional object. It can be formed in a short length in the length direction and can be stored in a container.
[0023]
In FIG. 3, reference numeral 22 indicates an injection means for injecting a flying body composed of the same explosive chamber and piston as those of the conventional one.
Next, the assembly structure of the flying object 10 will be described.
In the exploded perspective view of the flying object 10 shown in FIG. 4, the flying object 10 has the flying object body 12 and the antenna 18 having the stabilizing wings 14 described above, and the center of gravity position is finely adjusted at the rear end portion of the flying object 10. A balancer 24 is provided, and a balancer 26 is also provided inside the flying body 12. The following electronic circuits and the like are accommodated in the flying body 12.
[0024]
The thermal battery 28 whose outer shape is formed in a cylindrical shape incorporates a heater that receives a predetermined signal and is energized to generate heat, and a power source that generates electricity by generating heat from the heater and outputs electric power to each electronic circuit (see FIG. Not shown.) The delay line 30 wound around the cylindrical iron core is for emitting a delayed amplified output at a predetermined transmission cycle.
The electronic circuit includes a radio wave control circuit 32 that controls radio waves to be transmitted and received and a power control circuit 34 that controls the power supplied from the thermal battery 28 and outputs the power to the radio wave control circuit 32. The radio wave control circuit 32 has a configuration in which a transmission electronic circuit 32a, a modulation electronic circuit 32b, and a reception electronic circuit 32c are stacked and integrated, and each is formed of an aluminum material.
[0025]
Here, details of the power control circuit 34 will be described with reference to FIG.
The power control circuit 34 is substantially composed of a flexible substrate (hereinafter simply referred to as a substrate) 36 and an electronic component 38 mounted on the substrate 36 (FIG. 5A). The substrate 36 is provided with a bent portion 40 at substantially the center. For example, round-shaped notches 41 are formed at both ends of the bent portion 40 along a direction perpendicular to the bending direction. Two metal plates 42 made of, for example, aluminum or the like are attached to the back surface of the substrate 36 (the surface opposite to the mounting surface of the electronic component 38) except for the bent portion 40. Reference numeral 44 denotes an external signal connection terminal to be described later.
[0026]
After mounting the electronic component 38 on the substrate 36 (FIG. 5B), the substrate 36 is bent at the bent portion 40 with the mounting surface of the electronic component 38 facing outward, and the metal plate 42 is bonded using an epoxy resin or the like. Thus, the power control circuit 34 is completed. The electronic component 38 is wired to the pattern of the substrate 36 by wire bonding or reflow soldering. In addition, a resin coating is applied as a moisture-proof measure.
[0027]
The power control circuit 34 configured as described above has a resin coating and is easily moisture-proof, so there is no need to provide a module case for the purpose of moisture prevention. Since electronic parts 38 are mounted on both sides and mounting efficiency is high, a large space volume is not required. In addition, since the metal plate 42 is attached to the back surface of the substrate 36, heat generated from the electronic components 38 mounted with high density is easily radiated through the metal plate 42, and power control is performed by the metal plate 42. The rigidity of the circuit 34 is ensured. Note that mounting electronic components on both sides of the board for high-density mounting is generally performed, but in this case, if one side is mounted with high-temperature solder and the other side is mounted with low-temperature solder, it is acceptable on both sides. There is a problem that the mounting density does not necessarily improve because the electronic parts are arranged according to the temperature, and in order to avoid this problem, if the electronic parts are soldered at once with the jig fixed, the mounting density is not necessarily improved. There is a problem that it is difficult to do.
[0028]
Further, in the present invention, since the rounded cutout portion 42 is formed in the bent portion 40, the substrate 36 can be easily bent. In addition, although it is possible to bend as it is without providing the bending part 40 of this invention in the flexible substrate 36, in this case, when the curvature at the time of bending is small, it is difficult to bend, and in order to eliminate the difficulty in this bending If the thickness of the flexible substrate 36 is reduced, the thickness and the number of patterns formed on the flexible substrate 36 are limited, and the mounting density cannot be increased.
[0029]
Here, instead of forming the round-shaped cutout portion 42 in the bent portion 40, a fold 46 is formed in the bent portion 40 as shown in FIG. 6, or along the bending direction as shown in FIG. The substrate 36 can also be easily bent by forming the slit 48.
When assembling the flying object 10, first, after attaching the cable assembly 50 to the radio wave control circuit 32, the power control circuit 34 is arranged on the upper surface of the radio wave control circuit 32. The power control circuit 34 and the attachment member 52 are fixed with screws 54 in a state where the portion is sandwiched between the attachment members 52. At this time, the balancer 54 is attached to the front end.
[0030]
Next, after the radio wave control circuit 32 and the power control circuit 34 are fitted around the delay line 30, the thermal battery 28 is attached to the rear end of the delay line 30. And after accommodating these integrated components in the inside of the flying body main body 12, the antenna 18 is attached to the front of the flying body main body 12, and the balancer 24 is attached to the rear end, thereby completing the flying body 10. .
[0031]
Here, the power control circuit 34 will be further described.
As shown in FIG. 5, an external signal connection terminal 44 is provided at the end of the printed circuit board 36 constituting the power control circuit 34. The external signal connection terminal 44 is formed of copper foil. The A plurality of branched ends of the printed circuit board 36 provided with the external signal connection terminals 44 are bent into a cylindrical shape along the inner peripheral surface of the flying body 12 as shown in FIG. And the front-end | tip of the external signal connection terminal 44 is bend | folded outside so that the open end of the flying body main body 12 may be covered, and the plane part 44a is formed.
[0032]
Conventionally, this signal interface is performed by an ambulatory connector or the like, and when the flying object is ejected, the cable is cut and the ambulatory connector or the like is separated. However, in this case, cables, ambulatory connectors, etc. remain around the antenna, which may hinder the flying stability of the flying object, and may also hinder the emission of radio waves from the antenna. . In the case of the present invention, as shown in FIG. 3, the external signal connection terminal 44 is bent and fixed to the outer peripheral surface of the flying body 12, and the plane portion 44a of the injection means 22 constituting the external electrode Since the surface contact with the piston 22a, the external signal connection terminal 44 does not affect the flight stability of the flying object 10, and when the flying object 10 is accommodated in the container, the external electrode (not shown) is reliably energized. In addition, in the state in which the flying object 10 is ejected, power is cut off and the external signal connection terminal 44 does not cover the periphery of the antenna 18, which interferes with radiation of radio waves from the antenna 18. There is nothing.
[0033]
8 and 9 show an outline of the internal structure of the flying object 10 in which the above-described components are accommodated.
As described above, the diameter of the flying body 12 in the direction (radial direction, for example, the vertical direction in FIG. 8) orthogonal to the length direction (axial direction, left-right direction in FIG. 8) of the flying object 10 is the front portion 12b and the rear portion 12c. Therefore, the electronic circuit composed of the radio wave control circuit 32 and the power control circuit 34 has a large mounting space for the electronic components in the radial direction. It is formed in a short length in the vertical direction and is almost completely accommodated in the front portion 12b of the flying body main body 12.
[0034]
Therefore, as schematically shown in FIG. 10, the load is concentrated in the vicinity of the center of gravity as compared with the conventional case, and the inertia moment is small. Therefore, the center of gravity is coupled with the shortening of the antenna 18 described above. Is located in front of the flying object 10 and the load of each component such as an electronic circuit is concentrated in the vicinity of the center of gravity. Therefore, the flying object 10 has excellent flight stability. Further, since the antenna 18 has a large diameter, the antenna performance is good. The electronic components 38 are densely integrated and generate a large amount of heat during use. However, heat is transmitted to the metal plate 42 and attachment members 52 at both ends of the metal plate 42 are further transferred from the metal plate 42. , 52, heat is transmitted to the flying object body 12 to be radiated to the outside, and further, heat is transmitted to the antenna 18 having a large heat capacity through the flying object body 12, and then radiated to the outside. Although not described, the electronic component 38 serving as a heat generation source is directly attached to the metal plate 42 and can be radiated well.
[0035]
Next, as a modification of the present embodiment, an exploded perspective view of a rear flying object (hereinafter simply referred to as a flying object) 60 provided with an antenna at the rear end is shown in FIG. In FIG. 11, among the constituent elements (components) of the flying object 60, the same constituent elements as those of the flying object 10 of the present embodiment are denoted by the same reference numerals as those of the present embodiment. Description is omitted.
[0036]
The rear flying object 60 is different from the front flying object 10 in that the antenna 18 is housed in the rear end of the flying object body 12 and the thermal battery 28 is connected to the front of the flying object body 12 in this connection. The center of gravity of the flying object 60 is secured forward by providing a balancer 62 at the tip of the flying object body 12. Also in this case, the electronic circuit composed of the radio wave control circuit 32 and the power control circuit 34 is formed in a short length in the length direction of the flying object 60, as in the case of the flying object 10 for the front. The flying body 60 is almost completely accommodated in the front portion of the flying body main body 12, and the flying body 60 is excellent in flying stability. Further, regarding the electronic circuit and the thermal battery 28, the same parts can be shared by simply changing the arrangement for the rear and the front, and the manufacturing cost is reduced.
[0037]
【The invention's effect】
According to the flying object of the present invention, the flying object is ejected from the aircraft, and the flying object main body is formed in a substantially cylindrical shape, and the rear part of the flying object main body is folded by a hinge structure while being mounted on the aircraft. In addition, it has a stable wing that is urged by an urging member to expand radially when ejected from an aircraft, and an antenna for transmitting and receiving radio waves, a power source, and an electronic circuit are provided in the flying body. In the flying body that is accommodated along the outer peripheral surface of the flying object body in a container provided in the aircraft together with the injection means for emitting the flying object while being mounted on the aircraft, the flying object body has a front diameter. Since the stepped cylindrical shape is larger than the diameter of the rear part, when the stabilizer wing is folded and accommodated in a container that is slightly larger than the outer shape of the flying object, the flying object body is formed with a larger diameter than the rear part. At the front of The center of gravity of the flying object can be provided in the forward position by providing the child circuit etc. in a short shape in the axial direction of the cylinder, and the load is concentrated in the axial direction of the cylinder around the center of gravity, resulting in a state of small moment of inertia. Therefore, it is possible to obtain a flying object excellent in flying stability.
[0038]
Further, according to the flying object of the present invention, the power source and the electronic circuit are formed long in the radial direction of the flying object main body so as to be substantially close to the inner peripheral surface of the flying object main body and short in the axial direction. The above-described effects of the present invention are suitable because the formed body is substantially accommodated in the front part having a large diameter of the flying body, and the center of gravity of the flying body is positioned forward and the load is concentrated near the center of gravity. Can be played.
[0039]
Further, according to the flying object according to the present invention, the antenna occupies a predetermined space volume and is formed long in the radial direction of the flying object body so as to be substantially the same as the diameter of the front part of the flying object body. In addition, since it is formed in a short length in the axial direction and is accommodated in front of the front portion of the flying object body, the above-described effects of the present invention can be more suitably achieved in the flying object for the front having the antenna. Moreover, since the antenna has a large diameter, the antenna performance is good.
[0040]
According to the flying object of the present invention, the electronic circuit has a power control circuit that controls power supplied from a power source, and the power control circuit includes a board and an electronic component mounted on the board. And a metal plate for heat dissipation formed on the back surface of the substrate, the substrate is provided with a bent portion, the substrate is bent at the bent portion with the electronic component mounting surface facing outward, and the metal plate is joined. Therefore, the required space volume can be reduced and the required space volume can also be reduced by mounting electronic components on both sides of the substrate and increasing the mounting efficiency. Thus, the above-described effects of the present invention can be suitably achieved. In addition, since the weight is reduced by not providing the module case that has been provided in the past, the center of gravity can be easily provided forward by, for example, providing a balancer at the tip of the flying object.
[0041]
In this case, the flying object is made of a metal material, and the end of the metal plate is connected to the flying object so that heat can be radiated to the outside from the flying object. It is possible to dissipate heat more efficiently.
In this case, furthermore, slits along the folding direction, rounded cutouts along the direction perpendicular to the folding direction, and creases along the direction perpendicular to the folding direction are provided at the folding portion of the power control circuit. Since at least one of them is formed, it can be easily bent at the bent portion.
[0042]
Further, according to the flying object of the present invention, the external signal connection terminal provided in the electric circuit is bent from the inner peripheral surface of the flying object main body to the outer peripheral surface at the open end of the flying object main body and externally connected to the outer peripheral surface. The end of the signal connection terminal is fixed, the bent portion of the external signal connection terminal forms a flat surface, and the flat surface is in surface contact with the external electrode that supplies the external signal when the flying object is accommodated in the container. In addition, since the external signal connection terminal and the external electrode are separated when the flying object is ejected, the external signal connecting terminal does not affect the flying stability of the flying object. Can be reliably energized with an external electrode (not shown) in the state of being accommodated in the container, and the energization is cut off and the external signal connection terminal covers the periphery of the antenna when the flying object is ejected. No Never give any trouble to the radio wave radiation from the antenna.
[Brief description of the drawings]
BRIEF DESCRIPTION OF DRAWINGS FIG. 1 is a diagram for explaining a state in which a stable wing of a flying object according to an embodiment is opened, (a) is a front view of the flying object, and (b) is a right side surface of the flying object. FIG.
FIGS. 2A and 2B are diagrams for explaining a state in which the stable wing of the flying object according to the present embodiment is closed, FIG. 2A is a front view of the flying object, and FIG. 2B is a right side view of the flying object. FIG.
FIG. 3 is a view for explaining a state in which the flying object according to the present embodiment is housed in a container, (a) is a front view showing the flying object through the interior of the container; b) is a right side view showing the flying object through the interior of the container.
FIG. 4 is an exploded perspective view of a flying object according to the present embodiment.
FIGS. 5A and 5B are diagrams for explaining a power control circuit according to the present embodiment, in which FIG. 5A shows a state in which a flexible substrate is deployed, and FIG. 5B shows a state in which electronic components are mounted on the flexible substrate. (C) shows a state where the flexible substrate is folded.
6 is a modification of the bent portion of the power control circuit of FIG.
7 is another modification of the bent portion of the power control circuit of FIG.
FIG. 8 is a front view of the flying object seen through the electronic circuit and the like for explaining a state in which the electronic circuit and the like are accommodated inside the flying object body of the flying object according to the present embodiment.
FIG. 9 is a cross-sectional view taken along line IX-IX in FIG. 8 for explaining a state in which an electronic circuit or the like is housed inside the flying body of the flying body according to the present embodiment.
FIG. 10 is a diagram showing the arrangement of components of a flying object according to a conventional example and this embodiment for explaining a difference in the position of the center of gravity.
FIG. 11 is an exploded perspective view of a flying object according to a modification of the present embodiment.
FIGS. 12A and 12B are diagrams for explaining a conventional flying object, in which FIG. 12A is a perspective view of the flying object, and FIG. 12B is a view of the flying object as viewed from the rear;
FIG. 13 is a view for explaining a state in which a conventional flying object is accommodated in a container, (a) is a front view showing the flying object through the inside of the container, and (b) is a view of the container. It is the right view which showed the flying body through the inside.
[Explanation of symbols]
10, 60 flying object
12 Aircraft body
14 Stabilized wing
16 Hinge structure
18 Antenna
20 containers
22 Injection means
28 Thermal battery
30 delay line
32 Radio wave control circuit
34 Power control circuit
36 Flexible substrate
38 Electronic components
40 Folding part
41 Ear-shaped cutout
42 Metal plate
44 External signal connection terminal
44a Plane section
46 Eclectic
48 slits

Claims (5)

A flying object ejected from an aircraft, and the flying object body is formed in a substantially cylindrical shape, and the rear part of the flying object body is folded by a hinge structure while being mounted on the aircraft, and attached when it is ejected from the aircraft. It has a stable wing having a structure that is urged by a biasing member and expands radially, and an antenna for transmitting and receiving radio waves, a power source, and an electronic circuit are provided in the flying body, and is mounted on the aircraft. In the flying object that is accommodated along the outer peripheral surface of the flying object main body in the container provided in the aircraft together with the injection means for emitting the flying object,
The flying body has a stepped cylindrical shape in which the front diameter is larger than the rear diameter,
The front part of the flying body has a size that fits in the container with little gap between the container and the container,
The antenna is made of tungsten, and is formed long in the radial direction of the flying body main body so as to be substantially the same as the diameter of the front portion of the flying body main body, and is formed in a short length in the axial direction, It is housed in front of the front part of the flying body,
The power source and the electronic circuit are formed in a short length in the length direction of the flying body so as to be substantially close to the inner peripheral surface of the flying body, and are adjacent to the antenna, A flying object characterized in that it is housed in the large-diameter portion. The electronic circuit has a power control circuit for controlling power supplied from a power source,
The power control circuit is composed of a substrate, an electronic component mounted on the substrate, and a heat dissipation metal plate formed on the back surface of the substrate,
2. The flying body according to claim 1, wherein the board is provided with a bent portion, the board is bent at the bent portion with the electronic component mounting surface facing outward, and the metal plate is joined. .   The flying object according to claim 2, wherein the flying object is made of a metal material, and an end portion of the metal plate is connected to the flying object so that heat can be radiated to the outside from the flying object.   At least one of a slit along the folding direction, a round notch along the direction perpendicular to the folding direction, and a crease along the direction perpendicular to the folding direction at the folding portion of the power control circuit. The flying object according to claim 2, wherein the flying object is formed.   The external signal connection terminal provided in the electric circuit is bent from the inner peripheral surface of the flying body to the outer peripheral surface at the open end of the flying body, and the end of the external signal connection terminal is formed on the outer peripheral surface. When the external signal connection terminal is bent, the bent portion forms a flat surface, and when the flying object is accommodated in the container, the flat surface comes into surface contact with the external electrode that supplies the external signal and the flying object is emitted. 3. The flying object according to claim 2, wherein the external signal connection terminal and the external electrode are separated when the external signal is connected.

Images