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Seylosian Space and Aeronautics Administration


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FROM: Emerson Rawlins, Director Seylosian Space and Aeronautics Administration

TO: Minister Alexander Bellmont, Ministry of Transport and Economic Exchange

 

Minister Bellmont, we are pleased continued good news regarding the development of the Kirkwall Spaceport. Administration, research, and development offices have had construction finished for some time now. Our current focus is on construction for fabrication buildings, laboratories, and future launch sites. Still some fabrication facilities have been operation moving us closer towards the goals set out for static engine tests.

Staffing and recruitment appears to be going smoothly. Research partnerships with every major Seylosian university have yielded an enormous potential pool of both sources of research and potential staff as we push forward with development. We've also had the time to look over aerospace talent from Aamotech since the rumors of a sale of a portion of the company to Seylos have been confirmed. A number of their current workforce would fit well in our Research and Development division without impacting the Aamotech branch significantly. We've also begun the process of reaching out for international talent who may already have experience in this field to further bolster our efforts. Talks are also underway with the city of Kirkwall about the future housing situation as the amount of staff at the Spaceport continues to grow.

We are close to setting the official time for a first static rocket engine test, which we will inform your office of when it has been set in stone. The test will involve the first Seylosian engine prototype, which for the time being we are simple naming the SRE-1. The SRE-1 will try achieve a thrust of 197,000 pounds of force with a scheduled burn time of thirty seconds. Development is continuing for a expendable launch system that will be compatible with SRE type engines for test launches.

We would like to thank the Ministry for its continued support of the SSAA, and I would like to add that I am incredibly proud of the work our staff has already accomplished here. I have no doubts in my mind that Seylos will make it to the stars.

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  • 4 weeks later...

RESULTS:

STATIC ENGINE TEST

MODEL SRE-1-L

Test Number: 003

Burn Time: 15 seconds

Thrust Target: 197,000 lbs

jlvejai.gif

Video Footage of Test# 003

 

SUMMARY:

This test has produced additional gains to thrust from previous tests. Current burn thrust is at 169,000lbs, an approximate five percent gain from Test# 002. Burn duration has been kept the same at fifteen seconds. This test has revealed engine nozzle instability after passing 6 seconds of burn time. Nozzle deviation was measured between three to four degrees once maximum thrust was achieved. Additional design measures will be recommended to be put in place to prevent this issue. Liquid fuel mixture seems to be biggest factor behind sub optimal thrust from burns.

Static test housing is continuing to perform as expected. Engine shows no significant movement during firing sequence.

Continued tests are expected, and current trends show expected further improvement in engine output.

 

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  • 2 weeks later...

Continued design efforts have yielded a rocket chassis that can hold the SRE-1 engine and can be fitted for testing as soon as possible.

  • Two solid rocket boosters. These will be planned to be 31.6 meters in height and contain a potential maximum thrust of 3 million pounds. The proposed solid propellant will be a mixture of Amonium Perchlorate, Aluminium, and Hydroxyl-terminated polybutadiene. Proposed solid fuel burn time will be 130 seconds. Fully loaded mass will be 170,000 kg.
  • Core stage will be powered by an SRE-1-L Engine, burning for 540 seconds. It will burn on a mixture of Liquid Hydrogen and Liquid Oxygen. This stage will be 24 meters tall with a diameter of 5.4 meters. Total loaded mass will be 184,000 kg.
  • The second stage will be powered by the SRE-1 Engine, burning a mixture of Monomethylhydrazine and Dinitrogen tetroxide as liquid propellant. Empty mass of the second stage will be 1200 kg.

 

image.png

 

Above is the planned designed for the rocket, now being called LVS-01.

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  • 2 weeks later...

RESULTS:

STATIC ENGINE TEST

MODEL SRE-1

 

Test Number: 005

Burn Time: 15 seconds

Thrust Target: 1,497,000 lbs

YGNx4L1.gif

 

Summary:

SRE-1 Solid Rocket Engines performed extremely well in this test, having achieved 95% of the target thrust set forth in the LVS-01 design proposal. The design team recommends ceasing testing on other proposed solid rocket designs and focusing all efforts on the SRE-1 for integration into the LVS-01.

Nozzle deviation was within acceptable parameters, though the testing team recommends additional efforts to prevent this from becoming a future problem. Engine housing remained stable as with the previous recorded tests for this engine, and fuel mixture has been deemed optimal for production deployment.

Continued tests are expected, and current trends lead the design team to believe that the SRE-1 will reach or exceed its thrust design expectations.

 

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  • 1 month later...

RESULTS:

STATIC TEST

MODEL LVS-01

Test Number: 001

Burn Time: 15 seconds

 

 

Summary:

Test model for engine testing suffered catastrophic failure approximately ten seconds after beginning to burn. Engine thrust proved to be too stressful on tower clamps holding the LVS-01 rocket in place. After ten seconds of burn, the clamps failed, allowing the rocket to temporarily lift itself off the pad. After another five seconds of burn time, internal stresses appear to have caused a massive failure in the SRE-01 engine resulting in an initial explosion disabling the engine. The rocket fell back to the ground after the loss of thrust, resulting in the remaining fuel reserves within the rocket to explode on contact with the ground. The LVS-01 rocket is a total loss along with all equipment on it. The launch pad and tower suffered severe damage and will have to be rebuilt.

While significant equipment loss did occur, teams on site and that were monitoring the test were able to gather a large quantity of usable date that will be invaluable in further research and fabrication efforts. Incidents like these are not considered rare during initial stages of rocket design.

 

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