Aerospace and Electronic Systems Magazine February 2018 - 48

Remote Sensing Satellites Conceptual Design

Figure 13.

The matching diagram, design points, and the BLD.

So, if there were more PDs in the allowable design area the
best point is which has the higher value of f/D.
C

Among the PDs with the same f/H values, the best point is
which has the higher value of f/D.

Table 10.

Design Points


GSD

Q

x

f/D

f/H

4.75E-07

30

0.6

2.00E-06

2.53

6.67E-08

In the allowable design area, the focus is on the corner which
has the highest values of f/D and f/H.

4.75E-07

30

0.5

2.00E-06

2.11

6.67E-08

4.75E-07

30

0.4

3.18E-06

2.68

1.06E-07

Since the best orbit altitude in this case is the least and Hmin =
600Km, so according to Table 10, the BLD specifications are as
written in the Table 11.

4.75E-07

30

0.4

2.00E-06

1.68

6.67E-08

C

C

Among the design points with the same Q, the best point is
which has the higher values of f/H and f/D.

Sizing of Cubesat Optical Payload
According to Table 5, the constraints of the maximum mass and
the maximum power consumption of the cubesat optical payload
are as follows:
M ≤ 1.5 Kg

Table 11.

The BLD Specifications


4.75E-07

μm

GSD

30

m

Q

0.6

-

x

2.00E-06

μm
-

P ≤ 1.8 W

f/D

2.53

In order to size the intended cubesat optical payload, the scaling method could be used. In this method, one of the MDPs should
be selected as the scaling criterion and then the cubesat optical
payload could be sized using the scaling statistical relations and
based on an existing instrument. Due to the lack of enough statisti-

f/H

48

6.67E-08

-

H

600

Km

f

40

mm

D

15.82

mm

IEEE A&E SYSTEMS MAGAZINE

FEBRUARY 2018



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