U.S. patent application number 11/826009 was filed with the patent office on 2008-01-17 for aircraft toy.
This patent application is currently assigned to TOMY COMPANY, LTD.. Invention is credited to Takashi Ichikawa.
Application Number | 20080014826 11/826009 |
Document ID | / |
Family ID | 38512121 |
Filed Date | 2008-01-17 |
United States Patent
Application |
20080014826 |
Kind Code |
A1 |
Ichikawa; Takashi |
January 17, 2008 |
Aircraft toy
Abstract
An aircraft toy includes an aircraft toy body which receives a
control data in an infrared ray which is transmitted from a
controller by an infrared sensor module and flies according to the
control data; and a chip composing the infrared sensor module is
attached on a front surface of a substrate, the substrate includes
a translucent portion which passes the infrared ray from a rear
side of the substrate, and the chip is attached to the translucent
portion of the substrate.
Inventors: |
Ichikawa; Takashi;
(Tochigi-shi, JP) |
Correspondence
Address: |
STAAS & HALSEY LLP
SUITE 700, 1201 NEW YORK AVENUE, N.W.
WASHINGTON
DC
20005
US
|
Assignee: |
TOMY COMPANY, LTD.
Tokyo
JP
|
Family ID: |
38512121 |
Appl. No.: |
11/826009 |
Filed: |
July 11, 2007 |
Current U.S.
Class: |
446/34 |
Current CPC
Class: |
A63H 27/02 20130101;
A63H 30/04 20130101 |
Class at
Publication: |
446/34 |
International
Class: |
A63H 27/20 20060101
A63H027/20 |
Foreign Application Data
Date |
Code |
Application Number |
Jul 12, 2006 |
JP |
2006-191824 |
Claims
1. An aircraft toy, comprising: an aircraft toy body which receives
a control data in an infrared ray which is transmitted from a
controller by an infrared sensor module and flies according to the
control data, wherein a chip composing the infrared sensor module
is attached on a front surface of a substrate, and the substrate
comprises a translucent portion which passes the infrared ray from
a rear side of the substrate, and the chip is attached to the
translucent portion of the substrate.
2. The aircraft toy as claimed in claim 1, wherein a fuselage of
the aircraft toy body is constructed in a thin plate shape, and is
constructed so that both of principal surfaces face a left and a
right of the aircraft toy body, and the substrate is attached to
the fuselage so that the both of principal surfaces face the left
and the right of the aircraft toy body.
Description
BACKGROUND OF THE INVENTION
[0001] 1. Field of the Invention
[0002] The present invention relates to an aircraft toy, and more
particularly to an aircraft toy comprising an aircraft toy body
which flies by an infrared control data.
[0003] 2. Description of the Related Art
[0004] Conventionally, an aircraft toy which comprises an aircraft
body and a controller for operating the aircraft body is known as
an aircraft toy. This aircraft toy is constructed so that the
aircraft body is made to fly in a straight line or in a circle by
an infrared control data from the controller (for example,
JP7-40897A).
[0005] Concerning this aircraft toy, the main body of the aircraft
body is formed with foamed resin.
[0006] In the aircraft toy in which the main body of the aircraft
body is formed with foamed resin, an infrared sensor module which
receives the infrared control data is generally attached to a
fuselage. In this case, a chip which composes the infrared sensor
module is attached to the fuselage via a substrate.
[0007] In the case of the above described aircraft toy, there is a
need to make the infrared control data from the controller be
receivable regardless of the direction in which the aircraft toy
body is located with respect to the controller.
[0008] However, there are cases where the infrared sensor module
cannot receive the infrared control data when the infrared control
data is transmitted from a side of the surface (rear surface) of
the aircraft toy body which is opposite of the surface (front
surface) of the aircraft toy body to which the chip composing the
infrared sensor module is attached.
[0009] In such case, the aircraft toy body becomes temporarily
inoperable.
SUMMARY OF THE INVENTION
[0010] In view of the above problem, an object of the present
invention is to provide an aircraft toy which can surely receive a
control data of infrared ray.
[0011] In accordance with a first aspect of the present invention,
an aircraft toy comprises an aircraft toy body which receives a
control data in an infrared ray which is transmitted from a
controller by an infrared sensor module and flies according to the
control data; and a chip composing the infrared sensor module is
attached on a front surface of a substrate, the substrate comprises
a translucent portion which passes the infrared ray from a rear
side of the substrate, and the chip is attached to the translucent
portion of the substrate. In such case, the adhesive agent which
adheres the chip is preferably transparent. Further, the electrode
pattern for electrically connecting the chip is preferably
translucent. However, in case where the electrode pattern is not
made to be translucent, there is a need to compose the electrode
pattern in a lattice pattern so that the light passing from the
rear side of the substrate is not blocked. The translucent portion
may be formed by forming holes on the substrate.
[0012] Preferably, a fuselage of the aircraft toy body is
constructed in a thin plate shape and is constructed so that both
of principal surfaces face a left and a right of the aircraft toy
body, and the substrate is attached to the fuselage so that the
both of principal surfaces face the left and the right of the
aircraft toy body.
[0013] According to the present invention, the chip which composes
the infrared sensor module is attached to the translucent part of
the substrate. Therefore, the infrared control data from the side
of the surface (front surface) of the aircraft toy body to which
the chip composing the infrared sensor module is attached and the
infrared control data from the side of the surface (rear surface)
of the aircraft toy body which is opposite of the surface to which
the chip is attached can be received surely.
BRIEF DESCRIPTION OF THE DRAWINGS
[0014] The present invention will be fully understood from the
detailed description given hereinafter and the accompanying
drawings given by way of illustration only, and thus are not
intended as a definition of the limits of the present invention,
wherein:
[0015] FIG. 1 is a perspective view showing an outer appearance of
an aircraft toy to which the present invention is applied;
[0016] FIG. 2 is a plan view of an aircraft toy;
[0017] FIGS. 3A and 3B are diagrams showing the structure of a tail
unit of an aircraft toy;
[0018] FIG. 4 is a block diagram showing the circuit structure of a
controller;
[0019] FIG. 5 is a block diagram showing the circuit structure of
an aircraft body of an aircraft toy;
[0020] FIG. 6 is a diagram showing steps of a manufacturing method
of a foamed molded body; and
[0021] FIG. 7 is a diagram of a substrate in a state where an
infrared sensor module is attached.
PREFERRED EMBODIMENT OF THE INVENTION
[0022] Hereinafter, an aircraft toy according to the present
invention will be described with reference to the drawings.
[0023] FIG. 1 is a perspective view of an aircraft toy; FIG. 2 is a
plan view of an aircraft body; FIGS. 3A and 3B are diagrams showing
the attachment arrangement of a rudder; FIG. 4 is a block diagram
showing the circuit structure of a controller; and FIG. 5 is a
block diagram showing the circuit structure of an aircraft
body.
(Overall Structure of the Aircraft Toy)
[0024] As shown in FIG. 1, an aircraft toy 1 comprises an aircraft
body 2 and a controller 3. The aircraft body 2 is operated by the
controller 3, and for example, the aircraft body 2 can be flown in
a small space such as inside of a room or the like. In such case,
the flight speed of the aircraft body 2 can be adjusted by the
controller 3, and the aircraft body 2 is allowed to fly in a left
circle and a right circle by the controller 3.
(Structure of the Aircraft Body)
1. Overall
[0025] The main body of the aircraft body 2 comprises a fuselage
21, a main wing 22, a horizontal tail 23, a trimtab 24, and a
rudder 25. The above components are composed of foamed resin molded
bodies. Concerning the aircraft toy 1 of the embodiment,
polystyrene is used as a material of the foamed resin molded body,
for example. The manufacturing method of the foamed molded body
will be described later.
2. Main Wing
[0026] In the aircraft body 2 of the embodiment, the main wing 22
is a left and right integrated type. The main wing 22 is attached
above the front part of the fuselage 21. However, the main wing 22
may be the left and right integrated type which is to be attached
to the fuselage 21 by being inserted in a slit formed on the
fuselage 21. Further, the main wing 22 may be a left and right
separated type in which the left wing and the right wing are to be
attached to the left side and the right side of the fuselage 21,
respectively. Moreover, the main wing 22 may be attached under the
front part of the fuselage 21.
3. Fuselage
[0027] In the aircraft body 2 of the embodiment, the fuselage 21 to
which the main wing 22 is attached is not specifically limited, and
the fuselage 21 is constructed by pasting two foamed plastic thin
plates together from the left and the right. A plurality of through
holes 21a which penetrate the fuselage 21 in the left-and-right
direction are formed on the fuselage 21. In such way, the weight of
the aircraft body 2 is reduced. In the fuselage 21, a rear side of
the part to which the main wing 22 is attached is in a notched
shape at an upper part thereof. A motor 27 for propeller drive is
attached to the fuselage 21 so that a propeller 26 positions at the
notched part. The motor 27 for propeller drive is driven and
controlled according to the control data from the controller 3. In
the aircraft body 2 of the embodiment, the propeller 26 is
constructed so as to rotate in the clockwise direction when seen
from the rear of the aircraft body 2. By all means, the propeller
26 may rotate in the counterclockwise direction. Further, it is
needless to say that the propeller 26 may be attached at the front
end of the fuselage 21.
[0028] Moreover, the rear portion of the notched part functions as
a vertical tail in the fuselage 21.
4. Horizontal Tail
[0029] The horizontal tail 23 is attached above the rear end of the
fuselage 21. Although it is not specifically limited, in the
aircraft body 2 of the embodiment, the horizontal tail 23 is
constructed so that the left wing and the right wing are
integrated. A notch 23a is formed at a center in a left-and-right
direction of the rear edge of the horizontal tail 23. The notch 23a
is left-right asymmetric when seen as a plan view. The notch 23a is
to regulate the left and the right rudder angles of the rudder 25,
and the edge of the notch 23a composes a stopper when the rudder 25
moves.
[0030] The trimtab 24 formed in a vertical tail-like shape is
attached on an upper surface of the horizontal tail 23 so as to
project upward.
5. Trimtab
[0031] The trimtab 24 is attached to the fuselage 21 in a state of
being slanted with respect to the central axis of the fuselage 21
so that, compared with the front part of the trimtab 24 in the
direction of flight, the rear part of the timtab 24 in the
direction of flight be away from either the left or the right side
of the aircraft body 2 in which the propeller slipstream is
stronger. Concerning the propeller aircraft toy 1 of the
embodiment, the propeller 26 rotates in the clockwise direction
when seen from the rear of the aircraft body 2. Because the
propeller slipstream is stronger in the right side of the aircraft
body 2, the trimtab 24 is attached to the fuselage 21 in a state of
being slanted with respect to the fuselage 21, so that the rear end
of the trimtab 24 in the direction of flight shifts to the left
side of the aircraft body 2 comparing to the front end of the
trimtab 24 in the direction of flight, when the aircraft body 2 is
seen from above.
6. Rudder
[0032] The rudder 25 is attached at a rear end of the fuselage 21.
As shown in FIG. 3, the rudder 25 is linked to a vertical shaft 21b
which is attached to the fuselage 21. That is, one end of the
linkage member 25a is fixed to the rudder 25. The linkage member
25a is inserted into a coil C which is attached to the fuselage 21,
and the other end of the linkage member 25a engages with the
vertical axis 21b. The linkage member 25a is composed of a
non-magnetic body, and a permanent magnet 25b is attached to the
part of the linkage member 25a which is inserted into the coil C.
The permanent magnet 25b is attached to the linkage member 25a so
that either the N pole or the S pole faces either the left side or
the right side of the aircraft body 2 and the other of the N pole
or the S pole faces the other side of the aircraft body 2. When the
electric current flows in the coil C, the rudder 25 is to move in
either the left or the right direction according to the current
direction.
[0033] The upper end of the rudder 25 projects from the notch 23a
of the horizontal tail 23. When the rudder 25 moves in a
left-and-right direction, the movement of the rudder 25 is to be
regulated by the edges of the notch 23a. In such case, the notch
23a is constructed so that the maximum rudder angle in either the
left side or the right side of the aircraft body in which the
propeller slipstream is stronger is smaller comparing to the
maximum rudder angle in the other side of the aircraft body.
Concerning the propeller aircraft toy 1 of the embodiment, the
propeller 26 rotates in the clockwise direction when the aircraft
body 2 is seen from the rear. Because the propeller slipstream is
stronger in the right side of the aircraft body 2, the notch 23a is
formed so that the maximum rudder angle in the right side of the
aircraft body 2 is smaller comparing to the maximum rudder angle in
the left side of the aircraft body 2.
7. Manufacturing Method of the Foamed Molded Body (FIG. 6)
[0034] A manufacturing method of the foamed molded body having a
thickness of 2 mm, for example, will be described. First, the
primary foaming is carried out for resin beads by using a foaming
machine which is different from the mold. In this case, for
example, resin beads having diameters between 0.3 mm and 0.8 mm are
used. The resin beads are made into resin beads of 3 mm in
diameter. Next, the resin beads for which the primary foaming is
carried out are introduced in the cavity in a state where a space
is provided between the matching surfaces of each mold which are
used for the secondary foaming.
[0035] Subsequently, the molds are clamped after filling the cavity
with the resin beads for which the primary foaming is carried out.
That is, the matching surfaces of each mold are made to be in
contact with one another completely. In such way, spaces between
the resin beads become smaller. In this condition, the secondary
foaming is carried out for the resin beads and the resin beads are
molded. Accordingly, foamed molded bodies formed in thin plates
having high foaming ratio and which are homogeneous can be
obtained.
[0036] As described above, by filling the cavity with the resin
beads for which the primary foaming is carried out in a state where
the matching surfaces of each mold are separated from one another,
even the resin beads which are larger than the space thickness of
the cavity (2 mm; the space thickness in a clamped condition) can
fill the cavity. Further, the above case is advantageous comparing
to the case where the cavity is filled with the resin beads in a
clamped condition because the cavity can be surely filled with the
resin beads for which the primary foaming is carried out even when
the resin beads which are smaller than the space thickness (2 mm)
of the cavity is used. For example, in a case where the cavity is
filled with the resin beads in a clamped condition, the mold cannot
be surely filled unless the resin beads are made to be about 1 mm
in diameter by reducing the ratio of primary foaming when the space
thickness of the cavity is about 2 mm. Further, when the secondary
foaming is carried out while the cavity is not surely filled with
the resin beads, the molded body will be full of holes. Meanwhile,
when the resin beads for which the primary foaming is carried out
are introduced in the cavity in a state where a space is provided
between the matching surfaces of each mold which are to be used for
the secondary foaming, even the resin beads having diameter of more
than 1 mm can surely fill the cavity.
[0037] When the main wing 22 composed of the foamed molded body is
made according to the above described method, a main wing of 22.8
cubic centimeters in volume and 0.36 g in weight (that is, 0.0157 g
per 1 cubic centimeter) was obtained.
8. Other
[0038] For example, a battery 28 such as an electrolytic double
layer capacitor or the like is attached at the front end of the
fuselage 21. Further, a substrate 29 to which various types of
electronic/electrical parts and electronic/electrical circuits are
provided is attached to the fuselage 21. A terminal 27 to charge
the power source 28 is provided on the substrate 29.
(Construction of the Controller 3)
[0039] FIG. 1 shows the controller 3. A knob 3a for controlling the
propeller and a knob 3b for controlling the rudder are provided on
the controller 3. Among them, the knob 3a for controlling the
propeller is to control the rotating speed of the propeller 26.
Meanwhile, the knob 3b for controlling the rudder is to move the
rudder 25 in the left-and-right direction. Further, a power switch
3c and an infrared LED 3d are provided on the controller 3.
[0040] FIG. 4 is a block diagram showing the circuit structure of
the controller 3. As shown in FIG. 4, the controller 3 comprises an
IC 300 for control, an input unit 301, an IC 302 for infrared
remote control transmission, an amplifier 303, a transmission unit
304, and a charging unit 305. Among the above, the charging unit
305 is to charge the battery 28 (for example, an electrolytic
double layer capacitor) of the aircraft body 2. Here, though it is
not shown in the drawing, a battery which is the power source is
installed in the controller 3.
[0041] Here, the input unit 301 comprises the knob 3a for
controlling the propeller and the knob 3b for controlling the
rudder. The IC 300 for control comprises a ROM and a RAM which are
omitted from the drawing. The IC 300 for control generates the
control data based on operation information which is input from the
input unit 301. The IC 302 for infrared remote control transmission
encodes and modulates the control data which is generated by the IC
300 for control according to a given rule. The amplifier 303
amplifies the control data which is modulated by the IC 302 for
infrared remote control transmission, and the transmission unit 304
transmits the control data which is amplified by the amplifier to
the aircraft body 2. The transmission unit 304 comprises the
infrared LED 3d.
(Circuit Structure of the Aircraft Body 2)
[0042] The circuit structure of the aircraft body 2 is shown in
FIG. 5. As shown in FIG. 5, the aircraft body 2 comprises an
infrared sensor module 200a, an IC 200b for receiving an infrared
remote control, an IC 201 for control, a motor drive unit 202, and
a coil drive unit 203. The infrared sensor module 200a comprises a
receiving unit such as a photoconductive diode, a phototransistor,
or the like which receives the infrared control data, an amplifying
unit to amplify the infrared control data which is received by the
receiving unit, and a detection unit to detect the infrared control
data which is amplified by the amplifying unit. The infrared sensor
module 200a is composed by one chip. The IC 200b for receiving the
infrared remote control comprises a registor to temporarily store
the infrared control data which is detected by the detection unit,
a clock generating unit to generate a control clock, and a decoder
to decode the data which is encoded according to a given rule
(encoded data). The IC 201 for control comprises a CPU, a ROM, and
a RAM, which are omitted from the drawing. Further, the IC 201 for
control stores the control data in the RAM, and controls the
movement of the aircraft body 2 according to the program in the
ROM. The motor drive unit 202 stops the driving of the motor M for
propeller drive according to an order from the IC 201 for control,
starts the driving of the motor, and changes the rotation speed of
the motor. Meanwhile, the coil drive unit 203 stops supplying the
power to the coil C for rudder drive, starts supplying the power to
the coil C, and changes the direction of the electricity current
which supplies electricity to the coil C according to an order of
the IC 201 for control.
[0043] Here, as shown in FIG. 7, the infrared sensor module 200a,
the IC 200b for receiving the infrared remote control, and the IC
201 for control are adhered to the substrate 29. The substrate 29
is attached to the fuselage 21 so that both of the principal
surfaces face the left and the right of the aircraft body 2. In the
embodiment, a material such as glass epoxy is used as the substrate
29, for example, and a substrate in which the thickness is about
0.4 mm is used. Therefore, the substrate 29 allows the infrared ray
to pass through.
[0044] In such case, the chips which compose the infrared sensor
module 200a and the IC 200b for receiving the infrared remote
control, respectively, are adhered to the substrate 29 by a
transparent resin adhesive agent (for example, transparent epoxy
resin) and are coated with transparent resin. Further, an electrode
pattern 29a which is formed on the substrate 29 is in a lattice
pattern. Concerning the watermarked part of the lattice pattern, it
is constructed so as not to block the light passing though from the
rear side of the substrate 29. Therefore, the infrared control data
from the side of the surface (front surface) of the aircraft toy
body to which the chip composing the infrared sensor module 200a is
attached and the infrared control data from the side of the
opposite surface (rear surface) can be received surely.
[0045] Moreover, the IC 201 for control is coated with resin for
blocking ultraviolet ray (for example, black epoxy resin).
[0046] Here, each chip and the electrode pattern are electrically
connected directly or via a wire.
[0047] The embodiment of the present invention is described above.
However, the present invention is not limited to the embodiment,
and can be variously modified within the gist of the invention.
[0048] The entire disclosures of Japanese Patent Application No.
2006-191824 filed on Jul. 12, 2006 including specification, claims,
drawings and abstract thereof are incorporated herein by reference
in its entirety.
* * * * *