where = The maximal altitude of a satellite is given by the formula Y = yo + (R+ yo) vo) [2 ( 1 + 1/1 ) - ¹] ₁ ¹]₁ 201 yo is the altitude of the active part of the trajectory, g the acceleration of gravity on the surface of the earth and R the radius of the earth. f(v, 0) V² 2013 (1 + 10), 1 = VI − 4X(1 — À) cos² O, The function Y can be linearized in the domain of practically possible values of the random arguments. The initial velocity V and the launching angle are normal random variables with probability density = 1 2πσ.σ.V1 – με 2 2 1 x exp 2r exp { − 2 (1 — 1³5) [(º = 9)² + (ª − 9) ² - 2, (0 - 0X0 - 0)]}. σ8 Find the approximate value of the variance for the maximal altitude of the satellite.
where = The maximal altitude of a satellite is given by the formula Y = yo + (R+ yo) vo) [2 ( 1 + 1/1 ) - ¹] ₁ ¹]₁ 201 yo is the altitude of the active part of the trajectory, g the acceleration of gravity on the surface of the earth and R the radius of the earth. f(v, 0) V² 2013 (1 + 10), 1 = VI − 4X(1 — À) cos² O, The function Y can be linearized in the domain of practically possible values of the random arguments. The initial velocity V and the launching angle are normal random variables with probability density = 1 2πσ.σ.V1 – με 2 2 1 x exp 2r exp { − 2 (1 — 1³5) [(º = 9)² + (ª − 9) ² - 2, (0 - 0X0 - 0)]}. σ8 Find the approximate value of the variance for the maximal altitude of the satellite.
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![where
λ
f(v, 0)
=
=
yo is the altitude of the active part of the trajectory, g the acceleration of gravity
on the surface of the earth and R the radius of the earth.
The maximal altitude of a satellite is given by the formula
1+1
yo) [2 (+ / - 1]
[2(1
V2
28R (1 + 2/2), 1 = V₁ — 4λ(1 − à) cos² ©,
-
The function Y can be linearized in the domain of practically possible
values of the random arguments. The initial velocity V and the launching
angle are normal random variables with probability density
1
2πσ.σ.11
Y = yo + (R+ yo)
x exp
XP
-
2
2
2
{-20 - 15 [(º − 9)² + (º ¬‚ 9)²
2(1
-
r2)
-
2r
(v - v)(0 -
"]}
Find the approximate value of the variance for the maximal altitude of the
satellite.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F202011ff-3259-44eb-b547-b7900627d8d2%2F73630694-b6a6-4926-97d5-4f25bc40cefd%2Flomod7_processed.jpeg&w=3840&q=75)
Transcribed Image Text:where
λ
f(v, 0)
=
=
yo is the altitude of the active part of the trajectory, g the acceleration of gravity
on the surface of the earth and R the radius of the earth.
The maximal altitude of a satellite is given by the formula
1+1
yo) [2 (+ / - 1]
[2(1
V2
28R (1 + 2/2), 1 = V₁ — 4λ(1 − à) cos² ©,
-
The function Y can be linearized in the domain of practically possible
values of the random arguments. The initial velocity V and the launching
angle are normal random variables with probability density
1
2πσ.σ.11
Y = yo + (R+ yo)
x exp
XP
-
2
2
2
{-20 - 15 [(º − 9)² + (º ¬‚ 9)²
2(1
-
r2)
-
2r
(v - v)(0 -
"]}
Find the approximate value of the variance for the maximal altitude of the
satellite.
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