International Core Journal of Engineering 2020-26 | Page 176

F y F z
S
,
represent the physical force on the micro-body; t
c
represents the viscous dissipation term; s represents the
obtained immediately by the above formula. It is worth
noting that when the number of base stations is insufficient,
three-dimensional coordinate positioning cannot be
performed. When the number of base stations is only one,
only distance measurement can be performed. When there
are two base stations, two-dimensional coordinate
measurement can be performed. When the number of base
stations is three or more, three-dimensional coordinate
measurement can be performed, and the number of base
stations is larger. More, the more accurate the measurement
results [4].
S
volume concentration of the component s; and s represents
the productivity of the substance s. It is also necessary to
increase the gas state equation for compressible gas flow [5].
This formula is used as the theoretical basis to generate a
mesh for fluent analysis. The body sizing sets the entire mesh
size to 3mm. The face sizing sets the mesh size of the
underwater part of the aircraft to 1mm. The generated mesh
is as follows:
B. Aircraft hull analysis
Basic analysis of the aircraft part. (1) Conservation
equation. The analysis of the part of the aircraft is carried out
for CFD calculation. The differential equations for
controlling the fluid flow are solved by numerical calculation,
and the discrete distribution of the flow field in the
continuous domain is obtained. Generally, the conservative
control equations involved in CFD calculation mainly
include the following four types.
(1) Continuous equation.
w U
 div  U u  0
w t
(2) Momentum equation
w W
w  U u 
w W
w U w W
 div  U uu u    xx  yx  zx  F x
w t
w x w x
w y
w z
Figure 3. Flow field distribution and pressure distribution.
w W
w W
w  U v 
w U w W
 div  U vu u    xy  yy  zy  F y
w t
w y w x
w y
w z
The water flow shear force simulation of the underwater
part model is shown in the figure:
w W
w  U w 
w W
w U w W
 div  U wu u    xz  yz  zz  F x
w t
w z w x
w y
w z
(3) Energy equation
w  U T 
T 
 div  U uT
w t
§ k
·
div
di ¨
gradT ¸  S T
¨ c
¸
© p
¹
Figure 4. Simulation of water flow shear force.
Therefore, it can be seen from the CFD simulation that
the theoretical part of the aircraft in the communication
system is extremely feasible, and the dual-track dual-body
design has a good effect of reducing drag.
(4) Component equation
w U c s
 div  U uc s 
w t
In
the
di ª ¬ D S grad  U c s  º ¼  S s
div
above
w D x w D y w D z
grad  D 


w x
w y
w z ;
C. Conclusion
This paper proposes a three-in-one interactive
communication system. The command center uses the PWM
dual signal channel to control the main aircraft, and the
main aircraft has a shipyard. At work, the aircraft arrives at
the place of danger and launches a bionic unmanned boat to
form a search network. After encountering the distressed
person, it expands into an airbag and returns to the position,
formulas,
w D w D w D


w x w y w z ; F x ,
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