Aerospace and Electronic Systems Magazine February 2018 - 38

Remote Sensing Satellites Conceptual Design

SATELLITE SIZING USING THE DESIGN PLANE TECHNIQUE
The purpose of performance sizing in this article is to identify the
best combination of DDs in allowable design area in the design plane.
Each combination of the DDs in the allowable design area represents
a point that is named point design (PD). The PDs are the solutions
which meet all the constraints and requirements of the mission but
may not be the best possible solution. In each stage of the mission
engineering process, the PDs could be considered a temporal criteria
of progress. The PDs are expected to meet the following purposes:
C
C

C

To prove the feasibility of mission objectives;

Step 8. Creating a variety of design planes and selecting the best;
Step 9. Rechecking the statistical society of other classes of satellites with the resulting design plane.
According to the research team, the rapid sizing method using
the design plane technique, can be applied to all kinds of engineering systems, so the payload subsystem of a remote sensing cubesat
has been selected as the case study of the article. To clarify the
formation process of the design plane with the aim of satellite sizing and conceptual design, this case has been sized based on the
stepwise method and the results are given at the end of each step.

To prove that the mission and performance constraints and
requirements are satisfiable;

Step 1. Determination of statistical society based on classification of satellites and then collecting statistical samples.

To create a basis for negotiations with customers to modify
the requirements and constraints (according to 20/80 rule).

The airplane design plane is applicable for all types of airplanes
including twenty mission classes, two weight classes (light and
heavy), and two application classes (military and civil), and is the
same for jet and propeller engines in its totality [9]. The satellites
can be divided into six broad categories based on their mission or
payloads: (1) observation or sensing, (2) communications, (3) navigation, (4) in situ sampling and observations, (5) sample return,
and (6) crew life support and transportation [1]. Based on weight
they can be divided to large and small satellites. Given the importance of orbit in satellite design, the variety of orbits is considered
in their division as well.
Therefore, the design plane which will be created for satellite
sizing is better to be honest for all classes of satellites including
mission, weight and position.
After collecting, the statistical samples should be divided into
two groups. The first, which has more members, will be used for
creating the design plane and the other will be used for rechecking
the results.
The specifications of remote sensing cubesat, for which the
payload subsystem has been sized using the design plane technique, are as follows:

The PD is valuable because it can be presented quickly and simply. It is important to take the PD not more serious than it is. The best
PD is named BLD. By progressing the mission engineering process,
the BLD will be compared with the other solutions in terms of performance. If there is a better point, then the old BLD will be replaced
with the new one. By completing the system design, the BLD will
be confirmed and finally it will be accepted as the system design.
After confirming the BLD, mass, size, power, and the total lifecycle cost including design, manufacture, test, launch, and satellite mission operations will be calculated. The performance sizing
process will be considered as a part of conceptual design phase, so
the accuracy and volume of calculations will be in compliance with
this phase of design.
After verification and validation, this method will enable the
designer to respond a proposal to a customer's request in the shortest possible time.

THE PROPOSED METHOD TO ACHIEVE THE OBJECTIVES
OF THE STUDY
The proposed method to achieve the objectives of the study is a
step-by-step approach as follows:
Step 1. Determination of statistical society based on classification
of satellites and then collecting statistical samples;

C

Three-unit (3U) cubesat

C

Mission class: remote sensing

C

Weight class: small satellite-nanosatellite (1-10 Kg)

C

Position class: LEO (Circular, Sun synchronous)

Step 2. Determination of phases and the associated modes of the
satellites performance;

Step 2. Determination of phases and the associated modes of
the satellites performance.

Step 3. Determination of PRs and quantitative criteria (performance parameter);

The requirements which dominate the system design are divided in
to four categories based on their effect on performance, cost, risk,
or schedule [1]. Some of them may have an affect on more than one
feature. Since the overall strategy is "Design for Performance",
this study is focused on requirements in the field of performance.
According to Figure 4, PRs are entirely dependent on phases and
the associated modes of the satellite performance. So, for the statistical population collected in the previous step, the performance
phases and associated modes should be fully determined.
The performance phases and associated modes of the sample
remote sensing cubesat is depicted in the Table 1 [4], [16], [17].

Step 4. Determination of performance constraints and quantitative
criteria (performance parameter);
Step 5. Determination of system DPs;
Step 6. Identification of system MDPs;
Step 7. Redefining the performance parameters based on the
MDPs; determination of DDs and design space dimensionality reduction;
38

IEEE A&E SYSTEMS MAGAZINE

FEBRUARY 2018



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