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Solid Rocket Boosters Separation System Development for the ILR-33 Amber 2K Rocket

Jan Kierski
Jan Kierski
, 
Arthur Pazik
Arthur Pazik
 oraz 
Dawid Cieśliński
Dawid Cieśliński
   | 13 wrz 2023
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Article Category: Research Article
Data publikacji: 13 wrz 2023
Zakres stron: 16 - 27
Otrzymano: 26 wrz 2022
Przyjęty: 29 maj 2023
DOI: https://doi.org/10.2478/tar-2023-0014
Słowa kluczowe
© 2023 Jan Kierski et al., published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Figure 1.

Comparison of both versions of the ILR-33 AMBER rocket: top – original design; bottom – 2K version.
Comparison of both versions of the ILR-33 AMBER rocket: top – original design; bottom – 2K version.

Figure 2.

Components of the separation system.
Components of the separation system.

Figure 3.

Phases of the separation process – 1. Initial flight configuration. 2. Upper node pyrotechnic release, the gas springs are pushing the boosters outwards. 3. Maximum deflection angle of the SRBs while being attached to the core, lower node release. 4. SRBs’ separation and their ballistic flight (no recovery systems for SrB foreseen). SRB, solid rocket booster.
Phases of the separation process – 1. Initial flight configuration. 2. Upper node pyrotechnic release, the gas springs are pushing the boosters outwards. 3. Maximum deflection angle of the SRBs while being attached to the core, lower node release. 4. SRBs’ separation and their ballistic flight (no recovery systems for SrB foreseen). SRB, solid rocket booster.

Figure 4.

Velocity map contours (ANSYS Fluent) for a supersonic case with coordinate system and angles definitions. 3D symmetry was applied in all cases.
Velocity map contours (ANSYS Fluent) for a supersonic case with coordinate system and angles definitions. 3D symmetry was applied in all cases.

Figure 5.

CFD results for SRB normal force behaviour at supersonic velocity (nominal separation conditions). Positive values support the separation, whereas a negative one pushes the SRB towards the core. CFD, computational fluid dynamics; SRB, solid rocket booster.
CFD results for SRB normal force behaviour at supersonic velocity (nominal separation conditions). Positive values support the separation, whereas a negative one pushes the SRB towards the core. CFD, computational fluid dynamics; SRB, solid rocket booster.

Figure 6.

Deflection angle as function of time since separation initiation for chosen flight cases.
Deflection angle as function of time since separation initiation for chosen flight cases.

Figure 7.

Upper node principle of operation.
Upper node principle of operation.

Figure 8.

Upper node release mechanism functional test stand.
Upper node release mechanism functional test stand.

Figure 9.

Upper node test results.
Upper node test results.

Figure 10.

Separation system functional test stand.
Separation system functional test stand.

Figure 11.

Functional test – comparison between the test and simulation data.
Functional test – comparison between the test and simulation data.

Figure 12.

Different separation phases – frames from the high-speed camera.
Different separation phases – frames from the high-speed camera.

j.tar-2023-0014.utab.001

• Normal force coefficient (–) cY (α,δ)
• Axial force coefficient (–) cZ (α,δ)
• Centre of pressure location (m) ZCP (α,δ) and YCP (α,δ)

j.tar-2023-0014.utab.002

• Linear displacement x(t)
• Time of operation top
• Initial force Fp = F(xp)
• End force Fk = F(xk)
• Work W=∫xpxkF(x)dx

j.tar-2023-0014.utab.003

• Linear displacement Z(t) (sign convention shown in Figure 4)
• Angular displacement δ(t) (sign convention shown in Figure 4)
• Release angle δgr
• Time of operation tδgr
eISSN:
2545-2835
Język:
Angielski
Częstotliwość wydawania:
4 razy w roku
Dziedziny czasopisma:
Engineering, Introductions and Overviews, other, Geosciences, Materials Sciences, Physics
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