بسم الله الرحمن الرحيم Saad Al-Shammari, Ibrahim Sheerah, Mansour Al-Tubaigi ME 594 ; Design of a Micro-Satellite Structure Using ANSYS Package Supervisor

الرحيم الرحمن الله الرحيم بسم الرحمن الله الرحمن بسم الله بسمالرحيم

Saad Al-Shammari , Ibrahim Sheerah ,

Mansour Al-Tubaigi

ME 594 ;

Design of a Micro-Satellite Structure Using ANSYS Package

Supervisor Dr. Khalid Alsaif

Mechanical Engg Department, KSU

Presented by :

ME 594 :presentation; Design of a Micro-Satellite ….Continued….

To To develop a develop a Micro-SatelliteMicro-Satellite (LEO) with a (LEO) with a

total lower mass than other designs.total lower mass than other designs. The The panelspanels, however, should be , however, should be easilyeasily

replacedreplaced or re-arranged. or re-arranged. •This This SatelliteSatellite can be used for the can be used for the purposepurpose

of of data transmissiondata transmission ;as primary mission ;as primary mission

and to and to capture imagescapture images ; ; as a secondary as a secondary

mission.mission.


What are LEO Satellites?Satellites can be divided into three different categories; according to their attitude from earth.•LEO Satellites (Low Earth Orbit) are usually located between 700 km from the earth to 1500 or 2000 km.

The low altitude of the orbit makes the transmission time for a link between a ground station and the satellite much shorter than other satellites.


Satellite Design Objectives

* To * To Transmit DataTransmit Data from ground Remote Sites from ground Remote Sites to the Testing Laboratories .to the Testing Laboratories .•To To Capture Images & Videos Capture Images & Videos from certainfrom certain locations on the earth .locations on the earth .

..For that purpose , our design have to be :..For that purpose , our design have to be :•SimpleSimple..•Cost EffectiveCost Effective•StrongStrong Enough,to withstand launching conditions. Enough,to withstand launching conditions.•Reasonably Reasonably Light WeightLight Weight ;i.e. less than 15 Kg. ;i.e. less than 15 Kg.


• Payload a small ccd camera (Eagle Technology)

• Satellite Structure

• Power Unit

• Attitude Control

• Thermal Control

• Command and Data Handling

• Telecommunications

ME 594 :presentation; Design of a Micro-Satellite ….Continued….Microsatellite Structural Design Procedure

**The following aspects shall be covered:

The structural Design should be Strong and Stiff enough ;with Balancing Mass fixations .

•Design should be Agreed by the Controlling Bodies to permit certification and qualification of structures;

The structural Materials should be Reliable , Reproducible and should be able to Resist the Environmental Factors.*Materials used shall Not be Hazardous

*Total Mass should be Minimized;

*The structure shall be Cost Effective and manufactured by Reliable and Repeatable methods.

*Redundancy should be considered.


Major Design Requirements for a Microsatellite Structure: could be summarized as follows:1- Knowledge of the EnvironmentKnowledge of the Environment

2- Simple Structural Lay-out.

3- Simple Access and Assembly.

4- Center of MassCenter of Mass should be very should be very closeclose to the to the Center of PressureCenter of Pressure

5- IXY , IYZ & IZX should have Near-Zero Values

6- Shielding of Sensitive Electronic Parts (i.e. VT unit)

7-Mechanical Decoupling : Simple Interfaces,

8-Taking into account the Thermal Requirements .9-Precise Choice of MaterialsChoice of Materials: i. e. Strength – Stiffness - Outgasing, Corrosion - Electromagnetic – Availability- Cost – Radiation Humidity,...


Microsatellite Design Concept Procedure


Microsatellite Inner & Outer Views

VHF RECEIVER

UHF TRANSMITER

S-Band TRANSMITER

SOLAR CELLS: on all

6 sides:36cell/side

PCB BOARDS


Microsatellite Detailed Design**In order for the design of our Microsatellite to be ready for

manufacturing , deatailed drawings for the various parts have been included. Among these are :

1)Bottom ( base) Plate

2)Custom Nut (connecting nut)

3)Side Link

4)Side Plate

5)Strengthen Plate

6)Main Supporting Pipe

7)Top (covering) Plate

Bottom ( base) Plate

Custom Nut

Side Link

Side Plate

Strengthen Plate

Supporting Pipe

Top (covering) Plate


Microsatellite Finite Element Modeling via ANSYS

**The Structural Model of our Microsatellite was first designed &

drawn using Mechanical Desktop Software

** The Model was next brought to ANSYS as a DB file

**We then followed the Finite Element Analysis steps using

ANSYS package (ver.10) .

** In the ANSYS analysis , we subjected the model to a Gravity Force of (10 g) due to acceleration of the launching rocket, although a selection of (7g) was also adequate.

QTY NAME MATERIALUNIT MASS

(GRAMS)TOTAL MASS

(GRAMS)

1 BACK BOX COVER ALUMINUM 242.764 242.764

8 SCREW ALUMINUM 2.80838 22.46704

1 TELEMETARYTELEMETAR

Y31.0523 31.0523

1 BOX ALUMINUM 200 200

4 STAND_OFF 6.4 MM HIGHT NAYLON 1.38755 5.5502

1 MODEM BOARD FR4 PCB 62.3158 62.3158

4 SPACER NAYLON 5.40195 21.6078

1 VIDEO TRANSMISSION BOARD FR4 PCB 46.7062 46.7062

12 STAND_OFF 4.4 MM HIGHT NAYLON 4.2747 51.2964

1 POWER PCB FR4 PCB 60 60

1 BATTERY ASSEMBLY ASSEMBLY 682.168 682.168

1 CAM FR4 PCB 10 10

1 PIPE ALUMINUM 205.16 205.16

3 STRENGTH PLATE ALUMINUM 231.101 693.303

1 TRANSMETER TRANSMETER 484 484

6 LINK ALUMINUM 100 600

6 SIDE ALUMINUM 180 1080

1 S-PAND ANTENNA ANTENNA 74.0758 74.0758

2 HOLOW NUT ALUMINUM 50 100

1 TOP_PLATE ALUMINUM 964.799 964.799

2 ANTENNA ANTENNA 30 60

1 RECIEVER RECIEVER 210 210

24 SOLAR CELLS SOLAR CELL 50 1200

1 BOTTOM PLATE ALUMINUM 965.518 965.518

SUM (grams)

8072.7835

SUM (Kg)

8.0727835

MATERIAL

PROPERITES


Static Analysis Using ANSYS PackageStatic Analysis Using ANSYS Package

(ALL PARTS)(ALL PARTS)


**Calculating Center of Pressure; Cp


ME 594 :presentation; Design of a Micro-Satellite ….Continued….ME 594 :presentation; Design of a Micro-Satellite ….Continued….

ME 594 :presentation; Design of a Micro-Satellite ….Continued….ME 594 :presentation; Design of a Micro-Satellite ….Continued….


Static Analysis Using ANSYS Static Analysis Using ANSYS PackagePackage

(WITHOUT SIDE PLATES)(WITHOUT SIDE PLATES)




First Modeshape.avi

Microsatellite Mode Shapes

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Microsatellite Natural Frequencies SET(MODE SHAPE) TIME/FREQ (HZ)

1 22.110 2 22.911 3 23.189 4 23.989 5 24.047 6 24.077 7 25.065 8 25.172 9 27.137 10 27.360 11 28.364 12 28.842 13 29.006 14 29.066 15 29.247 16 29.595 17 29.635 18 30.131 19 31.107 20 31.700

Microsatellite Environmental Testing Prior of being launched to space; micro satellites like all other spacecrafts have to go under

Extensive and rigorous Testing Environments to be qualified for their specific missions. Such tests including THERMAL, MODAL ,VACUUM& VIBRATION TESTING are needed to

satisfy the launch service provider that the satellite will survive the launch environment and it will operate as intended in the Space .

Testing & Evaluation of microsatellites follow Certain Steps :

1) Defining Testing Purpose, Strategy& Philosophy.

2) Defining testing Requirements: (a) Type of Tests . (b) Test Levels 3) Developing Contacts for : (a) Gaining Technical Advice (b) Finding Sponsorship.

4) Produce Qualification Testing Plans.

5) Finding Suitable Equipment to Perform the Test.

6) Designing the Test

7) Performing the Test .

8) Evaluating the Performance (pass/fail evaluation).

Microsatellite Model Testing

Purpose: To Verify the structural detail Design based on a Finite Element Approach.

Two Different Tests

( MODAL Test)

Identify three basic elements :

(1) Natural Frequencies of the structure

(2) Mode Shapes

(3) Damping Ratios associated with each mode.

If the test correlates well with the finite element model :qualification testing may proceed.

Otherwise some adjustments, must be incorporated.

( VIBRATION Test)

The Vibration Testing ,however, is used to measure the natural

frequencies of the structure when it is subjected to random and sinusoidal vibrations in all directions (x, y, z) .


Microsatellite Concluding Remarks

*The total mass of the satellite is about 8.1 Kg

which is less than 15 kg as required.

•The Maximum Stress is 0.4*10^5 Pa , which is far less than modulus of elasticity of aluminum (safe).

•ALL Natural Frequencies exceeded 20 Hz.

* Center of Mass is closed to the Center of Pressure.

QUESTIONS ARE MOST WELLCOMED !

END

of

PRESENTATION ……

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بسم الله الرحمن الرحيم Saad Al-Shammari, Ibrahim Sheerah, Mansour Al-Tubaigi ME 594 ; Design of a Micro-Satellite Structure Using ANSYS Package Supervisor