This presentation is actually made to manifest better ways for testing of rockets. In this presentation I actually divide rocket into its parts and then discuss testings of each part. Me and my presentors want to show the ways for testings of rockets that are using most powerful countries in the world.

1. “ROCKET TESTING”

2. “BY SHEIKH MARYAM”
CO PRESENTORS:
 AMMARA KHALID
 SUMAR FAROOQ
ROLL NO’s : 786
DEPARTMENT OF SPACE SCIENCE
UNIVERSITY OF PUNJAB, PAKISTAN

3.  WHY WE INTENDED TO
CHOOSE THIS TOPIC:
The main reason to choose this topic
is to manifest better ways for testing
of a rocket for our country.
We will trying to show the ways for
testing that are using most powerful
countries in the world.

4. CONTENTS
 ROCKET ENGINE TESTING
1. SEA LEVEL TESTING
2. ALTITUDE TESTING
 ROCKET PAYLOAD TESTING
1. SPACE SIMULATION TESTING
2. ACOUSTIC TESTING
3. THERMAL VACCUM TESTNG
4. ELECTROMAGNETIC
COMPATIBILITY TESTING
 ROCKET BOOSTER TESTING
 ROCKET PIPE TESTING
1.HELIUM DETECTOR
 ROCKET PROPELLANT TESTING
1. INTERNAL IGNITION TEST
2. STRAND TESTING
3. CARD GAP TESTING
 TESTING SITES IN WORLD

5. ROCKET ENGINE TESTING

6. SEA LEVEL TESTING
Sea level static testing is much more simple as
compared to altitude testing. Sea level testing has a
facility to direct the rocket exhaust safely towards
the open atmosphere.

7. A DEMONSTRATION ON ROCKET ENGINE
WITH THE HELP OF VIDEO:

8. ALTITUDE TESTS
A typical chamber operating pressure of
0.16 Pisa (equivalent to an altitude of
100,000 feet) is established inside this
chamber.
Sometimes this type of test is also called
THRMAL VACCUM TESTS.

9. WHY IS IT REQUIRED TO TEST THE ROCKET IN ALTITUDE PLACE
FACILITIES :
ROBERT FROST (Instructor and Flight Controller at NASA)
He said:
“It isn't. For example, NASA does a lot of its testing at Stennis in Mississippi
and SpaceX in McGregor, Texas - neither of which are at high altitude. Altitude
testing does not need to be done up in the mountains. It can be done anywhere
because it is done in an enclosed chamber where the pressure is dropped to be
very low.”

10. ROCKET PAYLOAD
TESTING

11. SPACE
SIMULATION
TESTS
This test is necessary in order to ensure
the heat balance of a payload and its
effectiveness.
The space simulation chamber
reproduces the exact space environment,
variations in temperature (- 174 ° C to +
120 ° C), solar radiation.

12. ACOUSTIC TEST
A vibrational environment is created as a result
of noises caused by the rocket being launched to
verify wether the satellite can function normally
after bearing such acoustic vibrations and
whether the designs and analysis of the payload
structure meet the acoustic vibration
requirements.
Frequency = 45Hz – 11,200Hz (approx.)
 front figure descripts: ROSETTA (a satellite) IN
ACOUSTIC TEST CHAMBER

13. THERMAL VACCUM TESTING
The thermal vacuum chambers are used for
the purpose of simulating a payload circling
in an orbit, in order to test a payload’s
operating performance in the space
environment, where near vacuum and great
temperature fluctuation conditions are
present.
Air pumping rate= 10-5 mbars in 4 Hours.
Temp. range= 77K - ~400 K
 FIGURE DESCRPTION= Payload in thermal vacuum
chamber.

14. ELECTRO-
MAGNETIC
COMPATIBILITY
TESTS
 It is used to check that electromagnetic field
response produced by the satellite itself under
normal operation, and to find out the
electromagnetic wave interference limit for which
the satellite can tolerate.
 Figure descripts; PAYLOAD(Satellite) in anechoic chamber
and ready for electro magnetic compatibility test.

15. ROCKET BOOSTER
TESTING

16. Closely resemble with testing of rocket
engines.
Do not required testing in thermal
vacuum chamber.

18. “ROCKET PIPES
TESTING”

19. HELIUM LEAK DETECTOR
 Also known as MASS SPECTROMTER
DETECTOR.
 PRESSURE TESTING (For Larger
volumes)
 VACCUM TESTING

20. A STANDARDIZATION FOR
PREVENTING LEAKEGES IN PIPES
Standards of leak-tightness verification of rocket units and joints
Units, joints
Permissible non-tightness,
m3Pa/s
Tank 10-7
Tank bottom 10-8
Automatic units 10-9
Pipelines 10-9
Coupling 10-9

21. ROCKET PROPELLANT TESTING

22. STRAND TESTING
(CRAWFORD STRAND
BURNER)
Very quick, simple and economic method.
To test the burn rate of solid propellant.
Propellant strand is tested in the high
pressure vessel.
Electric signals recorded at different time
intervals so that burning rate can be
measured.

23. CARD GAP TESTING
 Used to determine the sensitivity of a material
to the shock from a detonation.
 Detonation indication indicates sensitivity of a
material.
 Usage acetate cards.
 More than 20 times this test is conducted.

24. INTERNAL IGNITION
TEST
 The test material will transition from a deflagration to
an explosion under high thrust.

26. ROCKET TESTING
SITES IN THE WORLD

27. MARSHALL SPACE FLIGHT CENTRE
HIGH DOWN ROCKET TEST SITE

28. OTHER TESTING SITES IN WORLD
TESTING SITE NAME NAME OF COUNTRIES
MARSHALL SPACE FLIGHT CENTRE (NASA) UNITED STATES OF AMERICA
ATK PROMONTRY POINT UNITED STATES OF AMERICA
SUPARCO PAKISTAN
WOOMERA TEST RANGE AUSTRALIA- SOUTH AUSTRALIA
GEEx (GIANT ENGINE EXPERIMENT)
LEEx ( LARGE ENGINE EXPERIMNET)
BLUE ORIGIN, TEXAS
BLUE ORIGIN, WASHINGTON
HIGH DOWN ROCKET TEST SITE UNITED KINGDOM
DLR LAMPOLSHAUSEN GERMANY
NOSHIRO ROCKET TESTING CENTRE JAPAN
ISRO PROPULSION COMPLEX INDIA
GLENN RESEARCH CENTRE UNITED STATES OF AMERICA

29. A COMPLETE ANIMATION OF TESTING OF
ROCKET

30. REFRENCES
 http://www.etusersgroup.org/IP-internal-ignition-test/
 http://www.nspo.org.tw/services/en/service_i1.htm
 https://en.wikipedia.org/wiki/Rocket_engine_test_facility
 https://en.wikipedia.org/wiki/Crawford_burner
 http://www.heliumleakdetection.net/Helium-Leak-Testing/what-is-helium-leak-
detection.html

31. ANY QUESTIONS ???

32. THANK YOU !!!