Aerospace and Electronic Systems Magazine February 2018 - 50

Remote Sensing Satellites Conceptual Design
Also in this case, none of the constraints including payload mass
and power consumption have been violated. Due to the higher amount
of payload mass, volume, and power consumption using the MDP, f
then it is better to use these values in the rest of the design process.

Step 9. Rechecking the statistical society of other classes of
satellites with the resulting design plane.
The achieved design plane will be the best choice according to the
features of the pilot satellite class which introduced in the first step.
In this step the created design plane must be verified and validated,
applied to the other classes of satellites. If not applicable, the previous steps from the first to the eighth must be repeated again for the
desired class of satellites.

FEATURES AND ADVANTAGES OF SATELLITE SIZING USING
THE DESIGN PLANE TECHNIQUE
Wertz generally categorizes space missions into need-based and
capability-driven missions [1]. The similarity of these two categories is to meet the mission objectives and user's needs better (performance), faster (schedule), cheaper (cost), and less risk. So in
both cases, the starting point of the system design process will be
hearing the voice of customers. The customer's request is usually
presented in the form of a "Request for Proposal" (RFP). Typically, RFPs should contain mission requirements, constraints, and
operating conditions of the system. Then the mission engineering
team in response to the request should provide a proposal which
is technical, reasonable, clear, and understandable for customers
and investors as well. Performance Sizing, or sizing in brief, is a
process that can be used to provide a proposal with the above characteristics. Performance sizing is a quick process in which the mission and PRs are translated in to the best combination of the DDs.
This combination represents a BLD, based on which the weight,
size, power consuming, and the design, manufacturing and operations costs could be estimated. The satellite sizing model that its
idea is presented in this paper has the following features:
C

Minimizes the MDPs required for representing a BLD;

Quickness in implementation of the technique;

C
C

The ability to negotiate about the requirements and constraints through the sensitivity analysis based on the PPs;
The ability to observe the allowable design area (each point
in the allowable design area represents an allowable combination of the DDs or a PD);

REFERENCES
[1]

[2]

[3]

[4]
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[7]
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[9]

The ability to visually choose the best PD as a BLD;
Tangible and understandable BLD selection process for
customers and other stakeholders (as codesign promotes designing with rather than for end-users [31]).

[10]

[11]

CONCLUSION
The purpose of this paper was to represent the idea of establishing a quick model for conceptual design and performance sizing
50

of a satellite using the design plane technique; the design plane
technique was used previously only for sizing the aircrafts and in
this research. The purpose was to implement the same procedure
for sizing the satellites. In the aircraft design process, sizing is
often done in the conceptual or preliminary design phase, but using this method, the satellite performance sizing process can be
performed even before the start of the design process and it can
be used for providing a technical proposal in response to a RFP.
Using the design plane technique to create a BLD, the designer
will be able to investigate all the PDs, and choosing the BLD
visually, it will be tangible and understandable for the customers
and as a result they will be able to perform trade studies in the
design plane framework.
The generic model extracted for the performance sizing of the
airplanes using the design plane technique indicates that the model could be generalized to all of the engineering systems. Since
the imaging payload is a subsystem of a cubic satellite system
then creating the design plane and its performance sizing indicates the conceivability of such a 2D space for a remote sensing
satellite system. The next stage of the research will focus on this
purpose.

[12]

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FEBRUARY 2018

Table of Contents for the Digital Edition of Aerospace and Electronic Systems Magazine February 2018