US 9,428,264 B2Granted

Nose for supersonic flying object

AssigneeJapan Aerospace Exploration Agency

InventorsNaoko Tokugawa, Taro Kawai, Ayako Tozuka, Yoshine Ueda, Hiroaki Ishikawa

Life of this patent

Estimating the term…

Abstract

Provided is a nose for a supersonic flying object, which has a natural laminar flow nose shape capable of suppressing laminar-turbulent transition and drastically reducing a frictional drag. The nose for a supersonic flying object has a low resistive body shape symmetrical about a central axis as a base shape, wherein the base shape is approximately a cone shape having a linear, simple convex curve, or simple concave curve generatrix and a deformation element having a wavy shape is added to the base shape.

Claims4

Dependent claims

A nose for a supersonic flying object, having a body shape symmetrical about a central axis as a base shape, and having a shape obtained by deforming said base shape by a deformation component having a wavy shape, characterized in that:

said base shape described by local radius R(x) is approximately a cone shape having a linear, simple convex curve, or simple concave curve generatrix;
said deformation component is a sinusoidal deformation for deforming said base shape as a whole into a wave shape in at least one of a circumferential direction and an axial direction, which is expressed by
dR
⁡
(
x
,
ϕ
)
=
W
x
⁡
(
x
)
×
∑
t
=
1
t
∞
⁢
{
Φ
t
⁡
(
ϕ
)
×
Ψ
t
⁡
(
x
,
x
0
⁢
t
⁡
(
ϕ
)
)
}
[
Equation
⁢
⁢
1
]
as modulation of the local radius R(x),
where Φ(φ) is a circumferential direction deformation component term,
Ψ(x, x0t(φ)) is an axial direction deformation component term,
x is an axial direction location from a tip of the nose,
φ is a circumferential direction angle from a leeward ray of symmetry of the nose,
L is an overall axial direction length,
Wx(x) is a weighting function for ensuring zero deformation on respective axial direction ends (x=0 and x=L),
t∞=1;
and
said circumferential direction deformation component term and said axial direction deformation component term are expressed by
⁢
Φ
t
⁡
(
ϕ
)
=
∑
j
=
0
j
⁢
∞
⁢
D
j
×
cos
⁢
{
k
j
×
ϕ
+
r
j
⁡
(
x
/
L
)
}
[
Equation
⁢
⁢
2
]
Ψ
t
⁡
(
x
,
x
0
=
0
)
=
∑
i
=
0
i
∞
⁢
[
B
i
⁡
(
x
)
×
sin
⁢
{
2
⁢
π
×
n
i
×
(
x
/
L
)
+
π
×
m
i
}
]
[
Equation
⁢
⁢
3
]
where x0t (φ)=x0=0,
D, k, r, B (x), n, and m are terms dependent on a circumferential direction amplitude, a circumferential direction wave number, a circumferential direction phase, an amplitude having x in said axial direction as a function, an axial direction wave number, and an axial direction phase, respectively;
D=0−1
k=0−3
r=0
m=0−1.5
n=0−2 and
D+k+t+m+n>0.

166 more elements

said base shape described by local radius R(x) is approximately a cone shape having a linear, simple convex curve, or simple concave curve generatrix,
said deformation component is a local wavy deformation for deforming a part of said base shape locally into a wave shape, which is expressed by
dR
⁡
(
x
,
ϕ
)
=
W
x
⁡
(
x
)
×
∑
t
=
1
t
∞
⁢
{
Φ
t
⁡
(
ϕ
)
×
Ψ
t
⁡
(
x
,
x
0
⁢
t
⁡
(
ϕ
)
)
}
[
Equation
⁢
⁢
1
]
as modulation of the local Radius R(x),
where Φ(φ) is a circumferential direction deformation component term,
Ψ(x, x0t(φ)) is an axial direction deformation component term,
x is an axial direction location from a tipoff the nose,
φ is a circumferential direction angle from a leeward ray of symmetry of the nose,
L is an overall axial direction length,
Wx(x) is a weighting function for ensuring zero deformation on respective axial direction ends (x=0 and x=L), and
t∞=2;
and
said circumferential direction deformation component term and said axial direction deformation component term are expressed by
⁢
Φ
t
⁡
(
ϕ
)
=
ɛ
0
⁢
t
+
E
0
⁢
t
⁢
∫
-
∞
∞
⁢
⁢
ⅆ
β
·
E
t
⁡
(
β
)
⁢
cos
⁡
(
β
⁢
{
ϕ
-
ϕ
0
⁢
t
}
)
[
Equation
⁢
⁢
4
]
Ψ
t
⁡
(
x
,
x
0
⁢
t
⁡
(
ϕ
)
)
=
F
1
⁢
t
×
(
{
tanh
⁡
[
(
x
-
x
0
⁢
t
⁡
(
ϕ
)
)
L
×
F
2
⁢
t
]
+
1
}
×
{
-
tanh
⁡
[
(
x
-
x
0
⁢
t
⁡
(
ϕ
)
)
L
×
F
2
⁢
t
]
+
1
}
+
F
3
⁢
t
)
+
G
0
⁢
t
⁢
∫
-
∞
∞
⁢
⁢
ⅆ
α
·
G
t
⁡
(
α
)
⁢
cos
⁡
(
2
⁢
πα
⁢
{
x
-
x
0
⁢
t
⁡
(
ϕ
)
}
/
L
)
[
Equation
⁢
⁢
5
]
where ε0t, E0t, Et are respectively terms relating to a circumferential direction amplitude,
F1t, F3t, G0t, Gt are respectively terms relating to an axial direction amplitude,
α, F2t are terms relating to an axial direction wave number,
β is a circumferential direction wave number,
φ0t is a circumferential direction deformation location,
x0t(φ) is any function relating to an axial direction deformation location.
ε0t=0−1,
E0t=0−0.159155,
φ0t=7.599089−9.118907,
F1t=0−0.001416,
F2t=3.5,
F3t=˜0.423077−˜0.001815, and
G0t=0−0.000132.

260 more elements

Dependencies are inferred from the claim text.

Facts

Application: 13/881,307Filed 21 Oct 2011
Priority: JP 2010-2458962 Nov 2010
Published: US 2013/0214094 A122 Aug 2013
Granted: 30 Aug 2016
Term ends: Not estimatedThe source records don’t support an estimate.

Classification9 codes

B64C 21/10
Influencing air flow over aircraft surfaces by affecting boundary layer flow: using other surface properties, e.g. roughness
B64C 1/0009
Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like: aerodynamic aspects
B64C 30/00
Supersonic type aircraft
F42B 10/46
Streamlined projectiles: streamlined nose cones; Windshields; Radomes

Family

US 2013/0214094 A1Pre-grant publication · published 22 Aug 2013
US 9,428,264 B2This patent

From the US filing history. Foreign family members aren’t listed.

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Abstract

said base shape described by local radius R(x) is approximately a cone shape having a linear, simple convex curve, or simple concave curve generatrix;
said deformation component is a sinusoidal deformation for deforming said base shape as a whole into a wave shape in at least one of a circumferential direction and an axial direction, which is expressed by
dR
⁡
(
x
,
ϕ
)
=
W
x
⁡
(
x
)
×
∑
t
=
1
t
∞
⁢
{
Φ
t
⁡
(
ϕ
)
×
Ψ
t
⁡
(
x
,
x
0
⁢
t
⁡
(
ϕ
)
)
}
[
Equation
⁢
⁢
1
]
as modulation of the local radius R(x),
where Φ(φ) is a circumferential direction deformation component term,
Ψ(x, x0t(φ)) is an axial direction deformation component term,
x is an axial direction location from a tip of the nose,
φ is a circumferential direction angle from a leeward ray of symmetry of the nose,
L is an overall axial direction length,
Wx(x) is a weighting function for ensuring zero deformation on respective axial direction ends (x=0 and x=L),
t∞=1;
and
said circumferential direction deformation component term and said axial direction deformation component term are expressed by
⁢
Φ
t
⁡
(
ϕ
)
=
∑
j
=
0
j
⁢
∞
⁢
D
j
×
cos
⁢
{
k
j
×
ϕ
+
r
j
⁡
(
x
/
L
)
}
[
Equation
⁢
⁢
2
]
Ψ
t
⁡
(
x
,
x
0
=
0
)
=
∑
i
=
0
i
∞
⁢
[
B
i
⁡
(
x
)
×
sin
⁢
{
2
⁢
π
×
n
i
×
(
x
/
L
)
+
π
×
m
i
}
]
[
Equation
⁢
⁢
3
]
where x0t (φ)=x0=0,
D, k, r, B (x), n, and m are terms dependent on a circumferential direction amplitude, a circumferential direction wave number, a circumferential direction phase, an amplitude having x in said axial direction as a function, an axial direction wave number, and an axial direction phase, respectively;
D=0−1
k=0−3
r=0
m=0−1.5
n=0−2 and
D+k+t+m+n>0.

166 more elements

Facts

Application

13/881,307Filed 21 Oct 2011

Priority

JP 2010-2458962 Nov 2010

Published

US 2013/0214094 A122 Aug 2013

Granted

30 Aug 2016

Term ends

Not estimatedThe source records don’t support an estimate.

Classification9 codes

B64C 21/10
Influencing air flow over aircraft surfaces by affecting boundary layer flow: using other surface properties, e.g. roughness
B64C 1/0009
Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like: aerodynamic aspects
B64C 30/00
Supersonic type aircraft
F42B 10/46
Streamlined projectiles: streamlined nose cones; Windshields; Radomes