II I n n n tt t e e e n n n tt t ii i o o o n n n a a a lll l ll yy y B B B ll l a a a n n n kk k

(1)

1

[Distribution Limitation, KARI Proprietary Data] This documents is the property of Korea Aerospace Research

1. INTRODUCTION

Since Korea succeeded in launching the first experimental satellite in 1992, Korea cranked in the KOMPSAT(Korea Mutli-Purpose Satellite) program in 1994, which aims to develop core technologies for world class low earth obit satellite. Through the KOMPSAT series programs, Korea has acquired and will acquire space technologies which are essential not only to meet national spacecraft requirements but also to obtain global market share. Korea Aerospace Research Institute (hereafter referred to as “KARI”) has taken practically key roles in KOMPSAT program since 1994.

KOMPSAT-1, launched in 1999 with 3 year mission life, delivered 6.6m resolution panchromatic image and 1km resolution multi-spectral image to the ground by the end of 2007. KOMPSAT-1 is now classified as ‘un-operational’

after 8 year excellent operation. KOMPSAT-2, which was launched in July 2006, is providing top quality 1m resolution product to commercial satellite image market.

Currently, KOMPSAT-3 and KOMPSAT-5 are being developed at KARI Satellite Integration & Test Center (hereafter referred to as “SITC”). Besides the KOMPSAT series satellites, COMS(Communication, Ocean and Meteorological Satellite) is being integrated at KARI SITC for another successful launch in 2009. COMS program aims to develop a geostationary satellite performing three categories of mission. The first mission is weather monitoring of the full Earth disc, the second one is ocean color monitoring and the third one is the in-orbit verification of Ka-band communication payload technology developed by Korea.

In addition to the above satellites, according to the National Space Development Promotion Plan, KOMPSAT-6, KOMPSAT-7, and another Geostationary Satellite are waiting for development. For these satellites, KARI SITC will be at the hub of development.

(2)

2

[Distribution Limitation, KARI Proprietary Data] This documents is the property of Korea Aerospace Research Institute and shall not be reproduced or distributed without prior authorization. Also, the data contained in this Document, without the permission of KARI, shall not be used or disclosed for any purpose other than TurkSat. The data subject to this restriction is contained on all pages.

2. PROJECT INFORMATION

KARI fully understands that TurkSat AITC will be a national asset and national pride to Turkey as KARI SITC is to the Republic of Korea.

Consequently, KARI will apply its own know-how and experience to make TurkSat AITC become one of the best satellite integration and test facilities in the world.

KARI can provide TurkSat with wide range of support from the consulting to test equipment manufacturing such as the thermal vacuum chamber and the acoustic chamber which are installed at KARI. In fact, all activities to establish the AI&T facility are possible; including the site analysis, site selection and construction. The support width and depth will be decided by mutual agreement between TurkSat and KARI.

3. PURPOSE

KARI hopes that this RFI response document will give TurkSat valuable information to make right direction and decision for TurkSat AITC.

4. SECURITY CLASSIFICATION

All submitted documents by KARI shall be protected from third body’s access and disclosure of any part of these documents shall be prohibited without KARI’s permission.

(3)

3

[Distribution Limitation, KARI Proprietary Data] This documents is the property of Korea Aerospace Research

5. POINT OF CONTACT

For the simplicity, KARI nominates one point of contact for this RFI response. Not only questions about this document but also general inquiries will be welcome and they will be taken care of by this point of contact. The information on the point of contact is as follows:

Dr. Joon-Min Choi

Director, Satellite Test Division Korea Aerospace Research Institute 45 Eoeun-Dong, Youseong-Gu, Daejeon, 305-333, Korea Tel : 82-42-860-2382 Fax : 82-42-860-2234 e-mail : jmchoi@kari.re.kr

6. ORGANIZATION PROFILE

KARI was established in 1989 as a research institute to develop Korean aerospace programs and its mission is to research and develop aerospace technologies, assist in Korean space policy and support international cooperation. KARI currently concentrates its efforts on the development of satellite, launch vehicle, unmanned aircraft and helicopter.

Regarding the development and operation of satellite, at present time, KARI is developing three (3) high-end satellites and managing two (2) experimental satellite programs. The titles of three high-end satellites are KOMPSAT-3, 5 and COMS. The titles of two experimental satellites are STSAT-2 and 3 (Science and Technology Satellite-2, 3). KARI is also operating KOMPSAT-2 and converting the raw image data into value added product for world market.

(4)

4

Regarding the relations between Korean government and KARI, KARI is a research institute which Korean government established and subsidizes.

Ministry of Education, Science & Technology (hereafter referred to as “MEST”) and Ministry of Knowledge and Economy (hereafter referred to as “MKE”) are major government bodies for aerospace development in Korea.

(5)

[Distribution Limitation, KARI Proprietary Data] This documents is the property of Korea Aerospace Research Institute and shall not be reproduced or distributed without prior authorization. Also, the data contained in this Document,

5

7. GENERAL

Korea Aerospace Research Institute (KARI) has run Satellite Integration and Test Center (SITC) since 1996. The SITC started with 11,408 m²floor area (including basement and Launcher Integration Hall, Figure 7.1) to develop low earth orbit observation satellites. Later on, SITC building has expanded its size to 16,291 m² (including Launcher Integration Hall extension, Figure 7.2).

Currently, the SITC is expanding its size again to accommodate GEO satellite development. By the 19^th of April in 2008, the SITC has an extra building of 9,056 m²(Figure 7.3) floor area. Upon the completion, SITC has total 26,073 m² floor area (including 2^nd Launcher Integration Hall extension). Even though it is not recommendable, the KARI’s facility expansion tactic will be applicable to TurkSat if the budget is tight at start. When KARI SITC started in 1996, they had 4 distinctive test halls, such as, integration hall, launch environment test hall, obit environment test hall and electro-magnetic environment test hall (Figure 7.4).

Figure 7.1 KARI SITC in 1996

(6)

6

Figure 7.2 KARI SITC after 1^st extension

Figure 7.3 KARI SITC Extra Building for GEO Satellites

(7)

7

Orbit Environment Test

- Thermal-Vacuum Chamber - Solar Simulator

- Thermal Cycling Chamber

μm Integration & Assembly

- Angular Accuracy : 1/360 - Position Accuracy : 50

o Launch Environment Test

- Vibration Test System - Mass Property System

EMI/EMC Test

- Anechoic Chamber 13(L)x12(W)x7(H)m

Orbit Environment Test

- Thermal-Vacuum Chamber - Solar Simulator

- Thermal Cycling Chamber

μm Integration & Assembly

- Angular Accuracy : 1/360 - Position Accuracy : 50

o Launch Environment Test

- Vibration Test System - Mass Property System

EMI/EMC Test

- Anechoic Chamber 13(L)x12(W)x7(H)m

Figure 7.4 Four Test Halls of KARI SITC in 1996

(8)

8

Figure 7.5 Layout Drawing of KARI SITC 1^st Floor in 1996

TESTHALL #3

TESTHALL #01 TESTHALL #02 TESTHALL #4

Office Subsystem Test Lab

(9)

9

Figure 7.6 Layout Drawing of KARI SITC 1^st Floor after 1^st extension

Figure 7.7 Layout Drawing of KARI SITC Extra Building for GEO Satellites

(10)

10

Figure 7.8 Evolution of KARI SITC

(11)

11

Figure 7.9 Total Layout Drawing of KARI SITC

(12)

12

Figure 7.10 shows the KARI SITC organization. With the similar organization, TurkSat can maintain the AIT facilities and TurkSat can be integrated and tested in the AIT facilities with support of many responsible design engineers. However, the number of AIT personnel is totally dependent on the size of satellite project and the number of those projects.

Figure 7.10 KARI SITC Organization

(13)

13

8. SCHEDULE

Figure 8.1 shows the AIT facility construction schedule(TBD) with long lead test equipment installation, such as, thermal vacuum chamber. At minimum, total 27 months will be needed for building construction and total equipment settlement if KARI SITC is duplicated for TurkSat AITC as much as possible.

(14)

[[Distribution Limitation, KARI Proprietary Data] This documents is the property of Korea Aerospace Research Institute and shall not be reproduced or distributed without prior authorization. Also, the data contained in this Document, without the permission of KARI, shall not be used or disclosed for any purpose other than TurkSat. The data subject to this restriction is contained on all pages.

14 57

Figure 8.1 AIT Facility Establishment Schedule(TBD)

(15)

[[Distribution Limitation, KARI Proprietary Data] This documents is the property of Korea Aerospace Research Institute and shall not be reproduced or distributed without prior authorization. Also, the data contained in this Document,

15 57

9. OPERATIONAL DESCRIPTIONS AND TECHNICAL SPECIFICATIONS

9.1. High-bay and Test Halls

The integration high-bay will be adequate to integrate two GEO satellites in parallel. The suggested area is about 600 m². The MLI room and the clean storage areas for satellite components, parts, adapters and other equipments used in AIT activities are located in the vicinity of the integration high-bay.

All clean areas, including integration and test areas, satisfy class 100,000 cleanliness controlled conditions if only communication payloads are developed. However, for the optical payload, it is recommended to be better than cleanliness class 10,000.

The cranes in the integration and test areas have capabilities to handle minimum 10 ton loads (15 ton is recommended) with variable crane speeds.

[Crane]

All cranes are installed to meet the following lowest speed specifications:

- Up & Down speed: < 0.25 m/min - Lateral Movement Speed: < 0.5 m/min

- Traverse Movement Speed: < 0.5 m/min

2 kinds of forklift are used in the AIT facility. A forklift of at least 5 ton capacity is required outside the AIT facility. This forklift is powered by diesel or gasoline. Extra extension bars which are longer than 5m can be attached to the forklift for the long size equipments. The other forklift which is used in the clean room has 2 ton capacity or less. This forklift uses rechargeable battery to keep the cleanliness in the clean room. Tire cover is used for the case being used in the clean room.

(16)

[[Distribution Limitation, KARI Proprietary Data] This documents is the property of Korea Aerospace Research Institute and shall not be reproduced or distributed without prior authorization. Also, the data contained in this Document, without the permission of KARI, shall not be used or disclosed for any purpose other than TurkSat. The data subject to this restriction is contained on all pages.

16 57

Compressed air outlets are installed at 2 places in the Environment Test Halls and Integration High-bay. Compressed air pressure of the outlets is higher than 10 bars. The outlet valve is T-type 1/4” diameter valve so that 2 air hoses can be connected at the same time. A dehumidifier filter and a pressure controller with gauge are installed between the outlet and connecting hose and they eliminate humidity of compressed air.

9.2. HVAC (Heating, Ventilating and Air Conditioning)

3-fold filter HVAC system is installed to meet cleanliness in the integration High Bay & Environment Test Halls. The first filter is a general filter which eliminates dusts and large particles. The second filter(medium filter) eliminates smaller particles after the first filter. And the third filter(HEPA filter) eliminates 99.5% particles and contaminations.

Clean air flows into the High-bay & Test Halls through air blowing duct on the ceiling and flows down the High-bay & Test Hall from the ceiling. Air in the hall is sucked out through suction duck on the wall. The cleanliness is maintained in the best class range with the air flow system. Air pressure in the clean room maintains the positive pressure of around 0.1 bar difference from AIT facility exterior air pressure. HVAC system meets the following specifications:

Class: 100,000 (or 10,000) Temperature: 23 ± 5 °C Relative Humidity: 45 ± 10 %.

Each test hall and high bay are kept as clean room and has each particle counter for air-borne particulate contamination measurement (MetOne 2400A, HACH ultra analytics, Fig. 9.1). Locally, the particle counter can log measured data in its memory and print the value on the paper. Measuring and printing frequency can be set by a user. All particle counters are connected to one

(17)

17 57

central PC through RS485 communication. The central PC can manage the operation of remote particle counters and download the data from those counters using its own program named as “PortAll2” or customized unique program.

Figure 9.1 Particle Counter

Optionally, particulate and molecular contamination measurement laboratory can be built based on ESA’s standard document (ECSS-Q series).

Particulate contamination on surface can be measured by PFO (Particle Fall- Out, Mk5-5) photometer (Ingenious Systems BV) and sample plates. Molecular contamination on surface can be analyzed by FT-IR (Fourier Transform Infra- Red) spectrometer (Nicolet 6700, Thermo Electron) and witness plates.

(18)

18 57

Figure 9.2 PFO photometer and sample plate (Optional)

Figure 9.3 FT-IR spectrometer and witness plate (Optional)

(19)

19 57

9.3. Electrical infrastructure

The figure 9.4 is the simplified KARI AIT power system.

Figure 9.4 KARI AIT power system

9.4. Office Area

Offices for minimum forty people for AIT management, test equipment operators, test engineers, maintenance staff are necessary. In addition, many extra offices for satellite system engineers, project control officers, joint AIT team with foreign engineers and subcontractors, etc. are needed.

(20)

20 57

Several variable size seminar and meeting rooms are needed. The rest area for 24 hour working shifts, shower room and visitors’ area are also needed. If possible, exhibition area is also recommended.

9.5. Orbit Environment Test Hall

The following is the proposed for the thermal vacuum chamber system referring to KARI thermal vacuum chamber system:

1) All the thermal vacuum system, including pumping system, thermal shroud system, door moving system, will be controlled through PLC integrated with racks. A specific man-machine interface will allow operators to drive the whole system

- Control system will be based on the SIEMENS PLC (S7 400)

- Control system will be divided into two systems; one is remote system with PLC & PC, and the other is local control system with Touch Screen.

- Control & Monitoring system based on windows 2000 or XP will be supplied.

- The total area including chamber, machinery room, control room will be 20m(Width)x20m(Length).

2) The data acquisition equipment with 300 channels capacity will be independent of above chamber control system. The area for the data acquisition equipment is negligible.

(21)

21 57

Figure 9.5 Schematic Diagram of Control System for TV

Total thermal vacuum test system includes vacuum pumping system, thermal shroud system, chamber control system, and data acquisition system with 300 channels. In addition, utility system including LN2 storage tanks, vacuum-jacketed LN2 pipes, GN2 pipes, cooling water system, compressed air system and electrical power supply system is also provided.

Figure 9.6 is the largest thermal vacuum chamber at KARI. Its effective diameter is 8m and effective length is 10m. The chamber was designed by KARI and manufactured by Korea industries. In other words, KARI and Korean Industries have full capabilities to supply the thermal vacuum chamber which Turkey wants.

(22)

22 57

Figure 9.6 KARI Large Thermal Vacuum Chamber (φ 8 x 10 m)

The lower rail of the chamber can support max. 2 tons of specimen mass.

The capacity can be increased depending on requirements. The temperature range of shroud is from -150°C to +110°C by using gaseous nitrogen while it will be -190°C by using LN2. Two LN2 storage tanks with 20,000 liters each are needed.

The target vacuum level is better than 10^-5 mbar, which is attained within 10 hours from atmospheric pressure. Basically, 2 primary pump chains and 2 cryogenic pump chains are proposed to satisfy interchangeable

(23)

23 57

primary/redundant system taking account of long test period. For the economical operation, turbo-molecular pump system is also proposed in addition.

Figure 9.7 shows the KARI thermal vacuum chamber system (φ 3.6 x 3 m, φ 1 x 1.5 m, and φ 0.7 x 1 m) and its control room. Figure 9.8 shows the vacuum pump system for φ 3.6 x 3 m thermal vacuum chamber.

Figure 9.7 KARI thermal vacuum chamber system

(24)

24 57

Figure 9.8 Configuration of Vacuum Pumping System

The control room with 5m(Width)x5m(Length) will be necessary. The control will have capabilities to accommodate other chambers which will be needed in future. The maximum power consumption for thermal vacuum test equipment will be 300kW.

For the ambient pressure thermal test, KARI has several thermal cycling chambers (3.6 m(W) x 3.8 m(L) x 5.0 m(H), 1.1 m × 1.0 m × 1.05 m, and 0.9 m

× 0.95 m × 0.9 m). In addition, a thermal shock chamber and a vacuum bake- out chamber are installed.

The control room with 5m(Width)x5m(Length) will be necessary. The control will have capabilities to accommodate other chambers which will be needed in

(25)

25 57

future. The maximum power consumption for thermal vacuum test equipment will be 300kW.

9.6. Launch Environment Test Hall

The main components of electro-dynamic vibration system are as follows:

- Electro-dynamic shaker with a slip table,

- Power amplifier with optionally a transformer and a cooling unit,

- Vibration control system, - Data acquisition system,

- Seismic mass

Figure 9.9 shows a block diagram of a vibration system. The table 9.1 shows specifications of 80kN and 270kN shakers.

Figure 9.9 Block diagram of a vibration system

(26)

26 57

Table 9.1 Electro-dynamic shakers

Description Shaker

capacity Specimen tested

1

80kN long stroke Slip table 920 x 920mm Head-expander Ø 810mm

80kN Equipment sub system Spacecraft < 800kg

2

270kN long stroke Slip table 2000 x 2000mm Head-expander Ø2000mm

270kN Equipment sub system Spacecraft < 5ton

Figure 9.10 Vertical vibration test

(27)

27 57

Figure 9.11 Lateral vibration test

The Specimen mass is greater than 2 tons. The maximum capacity of shaker in the market is 280 KN. The shaker model is V994 of LDS. If TurkSat needs more power, customized multi shaking system should be used. KARI has the multi-shaking system and the capabilities to integrate this system.

The reaction block(seismic mass) is used to prevent transmission of vibrations and shocks produced by the vibration shakers to the foundations and the building as a whole. The reaction block can also be used to prevent transmissions of other external vibrations or shocks to the specimen (e.g.:

alignment checks, micro-vibration measurements, etc.).

The reaction block principally consists of the inertia block and the suspension system. For the inertia block, the inertia block is mainly designed to increase the static mass of the suspended assembly with respect to the dynamic loads. The mass of the block can be calculated through a simplified model of the shaker system (mass + spring) as being associated with a block + suspension device model (mass + spring in series with the shaker model).

On the basis of knowledge gained in previous experience, a ratio of 8 to 10

(28)

28 57

between the force generated by the vibration facility and mass of the inertia block may be satisfactory.

Examples :

- for a 80 kN shaker, an inertia block of 75 tons is needed, - for a 350 kN shaker, an inertia block of 300 tons is necessary.

The inertia block is to be possibly made of concrete.

The following is the proposed mass properties measurement equipment referring to KARI mass properties measurement equipment:

Specification for Mass properties measurements

- Table Diameter : 1m

- Max. Diameter for L-shaped Fixture : 2m - Max. Weight : 4.5 ton for MOI & static C.G

3.5 ton for POI & dynamic C.G.

- Rotation Speed : 10 ~ 300 RPM - Max. MOI : 5,200 kg-mm²

- Max. POI : 138 x 106 kg-mm² at 25 RPM

(29)

29 57

Figure 9.12 Mass property machine

Figure 9.13 L-fixture for mass property measurements

(30)

30 57

KARI acoustic chamber was designed by KARI and manufactured by Korea industries. In other words, KARI and Korean Industries have full capabilities to supply the acoustic chamber which Turkey wants.

For the acoustic facility, main components are : - the reverberant chamber,

- the noise generator system, - the control command system,

- the data acquisition system (command to the vibration system)

Figure 9.14 shows a block diagram of an acoustic chamber.

Figure 9.14 Block diagram of an acoustic chamber

(31)

31 57

Figure 9.15 Specification of KARI’s Acoustic Chamber

Figure 9.16 Acoustic test

(32)

32 57

The technical characteristics of acoustic control system are as follows:

- Acoustic test noise levels : from 120 dB to 156 dB - Frequency range : 20 Hz to 12.5 kHz

- Number of output channels : 2

- Number of input channels (measurement channels) : - 8 microphones for the servo-controls

- 8 microphones for the specimen - Measurement accuracy : 0.5 dB.

Figure 9.17 Control programs of Acoustic chamber

(33)

33 57

9.7. Electro-Magnetic Test Hall

EMC/EMI test chamber includes a main anechoic chamber, a shielded room, data acquisition equipment and measurement system (multi-meter, oscilloscopes, probes, RF power meter, etc…) The optimized EMC test chamber and measurement system will be designed and configured based on experiences over 10 year on satellite system development.

EMC/EMI Test Chamber

EMC/EMI Test chamber related to test facility and equipment will be based on the following descriptions;

- Measurement tolerances.

Unless exceptional requested for a particular measurement, the tolerance shall be as follows:

a. Distance: ±5%

b. Frequency: ±2%

c. Amplitude, measurement receiver: ±2 dB d. Amplitude, measurement system : ±3 dB e. Time (waveforms): ±5%

- Shielded enclosures

To prevent interaction between the EUT(Equipment Under Test) and the outside environment, shielded enclosures are required for testing. These enclosures prevent external environment signals from contaminating emission measurements and susceptibility test signals from interfering with electrical and electronic items in the vicinity of the test facility.

Shielded enclosures shall be provided adequate attenuation, and sufficiently large such that the EUT arrangement requirements and antenna positioning requirements are satisfied.

(34)

34 57

- Radio Frequency (RF) absorber material

The RF absorber material (carbon impregnated foam pyramids and so forth) is used for performing electric field radiated emissions or radiated susceptibility testing inside a shielded enclosure to reduce reflections of electromagnetic energy and to improve accuracy and repeatability. The RF absorber is placed above, behind, and on both sides of the EUT, and behind the radiating or receiving antenna. Minimum performance of the material is as follows:

a. 6 dB from 80 MHz - 250 MHz b. 10 dB over 250 MHz

- Ground plane.

The EUT is installed on a ground plane that simulates the actual platform. If the actual installation is unknown or multiple installations are expected, then a metallic ground plane is used. The metallic ground plane is about 2.25 square meters in area with the smaller side no less than 76 centimeters.

- Power source impedance

The impedance of power sources providing input power to the EUT is controlled by Line Impedance Stabilization Networks (LISNs) for measurement procedures unless a particular test method is required. In some case, test will request the special LISNs which are designed in according to the specified power impedance on the satellite platform. In that case, it is not included in this bidding.

EMC/EMI Measurements

The EMC/EMI test chamber and equipment will support the emissions and susceptibility tests. The measurement set-up will be as follows:

- Bandwidths for emission testing

The measurement receiver bandwidths are used for emission testing. These bandwidths are specified at the 6 dB down points for the overall selectivity curve of the receivers.

(35)

35 57

- Frequency scanning for susceptibility

For susceptibility measurements, the entire frequency range for each applicable test is scanned. For swept frequency susceptibility testing, frequency scan rates and frequency step sizes of signal sources will not exceed the values. The rates and step sizes are specified in terms of a multiplier of the tuned frequency (fo) of the signal source. Analog scans refer to signal sources which are continuously tuned. Stepped scans refer to signal sources which are sequentially tuned to discrete frequencies. Stepped scans will dwell at each tuned frequency for a minimum of 1 second. Scan rates and step sizes will be decreased when necessary to permit observation of a response.

Overall specification

The EMC/EMI Test chamber will be designed to satisfy the requirements and recommendations stated in space and military standards such as MIL-STD-462 C&D, MSFC, NASA, MIL-STD-1541. Also the dimensions of the EMC/EMI test chamber will be selected to accommodate satellite subsystems or systems in compliance with the measurement procedures such as MIL-STD-462 C&D for testing in the 30 GHz up to 40 GHz frequency range.

Also the EMC/EMI test chamber will be designed for the purpose of protecting the radio frequency environment of the test center against the functional emissions generated by other systems and against any risks of interference from the laboratory’s power generation equipment. Figure 9.18 shows the EMC/EMI test chamber site (for only reference) while Figure 9.19 shows the configuration of the anechoic chamber and the shielded room which will be installed in the assembly, integration, and test center of Customer site.

(36)

36 57

Figure 9.18 EMC/EMI Test Chamber Site (for only reference)

Air Lock Elevator

Amplifier Room

Control Room

Anechoic Chamber

Return duct

Test Hall (4)

Control Air Lock

Equipment Incoming Hall

Equipment Door

21.6 5

5 x 7 m

5 x 7 m 14.4

13.4

15.1

3.4

11 3 4.5

H : 3m

1.5

4 x 5

2.9 ton

H : 8m

Feed-through Panels

1 1

1

(37)

37 57

Figure 9.19 Layout of the EMC/EMI Test Chamber(for only reference)

Overall dimensions of the anechoic chamber are recommended as follows:

a. Length : 15 m (+0.5 m) b. Width : 10 m (+0.5 m) c. Height : 10 m (+0.5 m)

Shielding requirements in shielded rooms (anechoic chamber, control room and amplifier room)

- Attenuation to magnetic field

≥ 70 dB at 14 kHz

≥ 90 dB at 200 kHz - Attenuation to electric field

≥ 120 dB 200 kHz to 50 MHz - Attenuation to plane wave

A m p l i f i e r R o o m

C o n t r o l R o o m

A n e c h o i c C h a m b e r

R e t u r n d u c t 2 1 . 6

13.4

3.4

3 4 . 5

1 . 5

1.5

4 x 5

1 1

1

11 7

1 5 . 1

14.4

(38)

38 57

≥ 120 dB 50 MHz to 1 GHz

≥ 100 dB 1 GHz ~ 40 GHz

Type of tests

The EMC/EMI test chamber will be installed to perform the emissions and susceptibility tests in perfect way as following tests.

- Conducted emission tests in power lead AC/DC, interconnection lines, and bonding strap

- Radiated emission tests on each face of the device under the test - Conducted susceptibility tests

- Radiated susceptibility tests

- Auto compatibility tests (depends on the satellite system) - Electrostatic discharge tests on equipment, and subsystem

Overall description of Measurement System

The measurement system will be installed in the EMC/EMI chamber in customer site. The measurement system will be capable of performing the radiated and conducted emission and susceptibility tests on the satellite units, subsystems and system in compliance with the measurement procedures such as MIL-STD-462 C&D in the range of the frequency 30 Hz up to 40 GHz.

EMI measurement system

EMI measurement system will be located in the anechoic chamber and used to measure the conducted and radiated emission level from the EUT (Electronics under Test) such as satellite or other products of space application. The interference from the measurement equipment will be guaranteed, whether or not operating, the limited specification of at least above 6 dB in accordance with MIL-STD-461 C&D, MIL-STD-462 C&D and MIL-STD-1541. The EMI measurement equipment will classify the following group:

a. instruments for measuring a current, voltage or power and electric field strength

(39)

39 57

b. Antennas and probes

c. Automatic control, record and measurement system (limited to frequency domain measurements)

d. Software and hardware (interface) for automatic control of the measurement system

e. Accessories

EMS Measurement system

EMS measurement system will perform the conducted and radiated susceptibility test, and electrostatic discharge (ESD) test of EUT such as satellite or other products of space application. The EMS measurement equipment classifies the followings group:

a. Signal generators b. Power Amplifiers

c. Current sensing probes and antennas d. Software and interface hardware e. Pulse generators

f. Electrostatic discharge test instrument g. Accessories

(40)

40 57

9.8. Training

Basically, KARI will provide the training about facilities. For engineering work, the following training will be done under the KARI engineer’s supervision:

- test equipment specifications generation - test plan and procedure generation

- Request for Proposal (RFP) generation for test equipment procurement, etc.

Most of all, KARI will emphasizes the hand-on training to Turkish engineers, The hand-on training will be conducted at KARI SITC facilities before Turkish AIT facilities are completed. At current stage, KARI proposes that minimum 2 Turkish engineers will have chance to operate KARI facilities for each equipment. In this training, the test preparation will be conducted with KARI engineers. After the test, the test results will be analyzed with KARI engineers.

The training duration is minimum 5 working days for each trip. However, for the dynamic tests, it will take about 4 weeks from the test preparation to test result analysis. In normal case, shaker manufacturers can only train shaker operation techniques. However, in KARI training, KARI will use Structural and Thermal Model(STM) so that Turkish engineers will have chances to directly install accelerometers on the STM. The dynamic training course includes overall dynamic measurement and analysis techniques such as;

- Sine vibration test for the qualification of satellite system

- Random vibration test for functional verification of satellite components - Since burst test for the verification of integrity for satellite structure

- Separation shock test for the measurement and SRS(Shock Response Spectrum) analysis for separation system

- Modal analysis technique for the identifying the dynamic characteristics

When Turkish engineers complete the dynamic test training, Turkish engineers will have confidence in not only operating the shaker but also dynamic testing TurkSat. The similar training concept will be applied to the

(41)

41 57

thermal vacuum chamber training with the STM.

After Turkish AIT facilities are available, Turkish engineers will have one more chance to have hand-on training with their own test equipment. At Turkish AIT facilities, Turkish engineers will dominate test operation. Our ultimate goal is to give Turkish engineers capabilities to operate their own test equipment without resorting to other help before TurkSat AIT test operating starts. Also observation during relevant test periods in Korea is included, This observation is another good training for beginners.

KARI will provide all necessary documentation including but not limited to AIT operations manuals, maintenance manuals, test procedures and training documents as long as it is legal and it is not against confidentiality rules.

(42)

42 57

9.9. CDRL(Contract Documentation Requirement List)

CDRL will be finalized during contract negotiations. However, the followings are proposed.

CDRL Title : Monthly Schedule Reports Document Description

This report provides a monthly update to schedules for program. It contains, as minimum:

z Overall program development schedule with critical path defined

z Lower level schedules with building construction, equipment design, test, etc.

z Identification of issues & concerns and work approach, if required CDRL Title : Video, Films and Photos

Document Description

Visual record of hardware configuration, buildup and testing are provided as the program progresses. Photographs and video/film are delivered to Turkey.

CDRL Title : Integration and Test Facility Final Review Report Document Description

This document describes configuration of test facility and the interface checking for TurkSat environmental test. The document also outlines the integration and testing planning and procedures utilizing the facility.

CDRL Title : Facility Operation Manual Document Description

This document describes operation guideline for facility operation including maintenance manual and general safety plan for facility operation.

(43)

43 57

CDRL Title : Training Plan Document Description

This document describes training prerequisite, training objectives, training modules, training duration, training timing and location.

CDRL Title : Training Completion Report Document Description

This document describes what Turkish engineers achieve after training completion.

CDRL Title : Training Document Document Description

General knowledge to operate facility is covered and there are individual training documents for specific equipment.

CDRL Title : AI&T Facility Site Selection Analysis Report Document Description

This document describes the analysis results on the AI&T site selection. It contains, as minimum:

z Ground seismic measurement for vibration environment z Soil analysis for electrical ground

z Ground foundation strength analysis

CDRL Title : Thermal Vacuum Chamber Data Package Document Description

This document describes the thermal vacuum test facility for maintenance and operation. It contains, as a minimum;

- Overall System Description including specification - Detail Drawings for main system

- Chamber Operation Logic

(44)

44 57

CDRL Title : Vibration Test System Data Package Document Description

This document includes the shaker system design descriptions and technical specifications. The technical specifications contains, as a minimum;

1. Description 2. Performance

3. General requirement & Installation requirements 4. Operation Environment

5. System acceptance

Acceptance Data Package will be included.

CDRL Title : Mass Properties Measurement System Data Package Document Description

This document includes mass properties system design descriptions and technical specifications. The technical specifications contain, as a minimum;

1. General description of mass properties measurement 2. Accuracy of indication

3. Installation requirements 4. Limitation of test specimen 5. Mounting plate interface 6. Calibration

This document includes as follows:

z Design of fixture for mass properties measurement z Engineering practice guide for mass properties

(45)

45 57

CDRL Title : Acoustic Vacuum Chamber Data (Option) Document Description

This document includes acoustic chamber system design descriptions and technical specifications. The technical specifications contain, as a minimum;

1. Internal dimensions 2. Internal volume 3. Crane capacity 4. Anchor points 5. Opening types 6. Ventilation

This document includes as follows:

z Interface requirement z Utility interface requirement

CDRL Title : EMI Test Facility Requirements Document Description

This document defines the EMI test facility requirements for acceptance and workmanship test of component level, and for flight evaluation of subsystems and system level. It contains, as a minimum;

- Overall measurement system.

- Size of the shielded room and main chamber - Absorber types

- Electrical power; capacities, type of power, etc...

- Crane requirements

- Cleanliness requirements

CDRL Title : EMI Test Facility Verification Plan Document Description

This document defines the verification methods and pass/fail criteria used to verify the EMI test facility requirements. It will include a verification matrix that summaries the verification method and the floor noise control set-up required for the components, subsystems, and system EMI tests.

(46)

46 57