DE6600205U - ATTACHING A FRONT OR INNER BURNER DRIVE KIT FOR SOLID FUEL ROCKET ENGINES. - Google Patents

Description

Attachment of a front or internal burner set for solid fuel drives

The invention relates to a fastening of a front or inner burner bracket set for solid rocket engines inside the combustion chamber housing, zv? isohen its inside and the outside circumference of the propellant or an insulating layer enveloping them, the differences in thermal expansion occurring between the propellant charge and the combustion cannon housing allowing free annular gap arranged is, which is completely filled with an elastic layer, the radially outside with the inside of the Brennlcamraergehäuses and radially inside with the outer circumference of the Propellant charge or the insulation layer is firmly connected.

An arrangement of a fuel propellant in the furnace housing of a rocket engine according to (Sen shows the features listed above in the Austrian patent law * * ** t ^ · 3 ^ 2, after which the free annular gap between the inside

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of the combustion chamber housing and the outer circumference of the propellant set along its entire length with one made of oussasphalt! existing thermoplastic mass filled i3t that

is more flexible than the propellant and its outer surface

with the inside of the combustion chamber housing and dorsn j;

Inner surface adhering to the outer circumference of the propellant charge>

connected 1st, so that the latter also in the axial direction |

O is fixed to the BrennkaHuner housing. The well-known |

Attachment is disadvantageous insofar as extremely low |

ambient temperatures, especially in winter and |

occur especially in arctic zones, the asphalt hard |

and becomes brittle, losing its elasticity and I '

becomes sensitive to shock. There is also the risk that f,

that by the strong contraction of the propellant, its ii

The coefficient of thermal expansion is a power of ten of (

!! that of steel or another metal from which the fuel

-, kanunersehltuses is usually made, distinguishes,

mutual detachment of the adhesive surfaces can occur
Another disadvantage of the known design is that
that at very high ambient temperatures * such as those in deserts
occur, the asphalt is too soft, so that a sufficient attachment of the propellant charge la combustion chamber housing
is questioned at all.

The invention is based on the object, the disadvantages to avoid the flawed execution and . Attitude of a constructive and manufacturing quality a « fold 'arrangement one under all operating conditions functionally reliable execution to obtain.

To solve the problem is proposed according to the invention, the layer provided in the opening made of foamed plastic with pressurized gas inlet Making conclusions · This means that the invention moderate layer between the combustion chamber housing © and dsm Propellant under pretension »

The layer according to the invention, which is advantageously kept under tension in the annular gap, is capable of supporting the propellant charge in the combustion chamber housing without play even at extremely low temperatures. Also occur in conjunction "hang with the inventive arrangement in the aforementioned temperature range in the adhesion surfaces between the inside of BrennkammergehSuses and the outer surface of the" eyfindungsgesäßen layer on the one hand and the AuBenumfang AEE @ propellant charge and the inner surface of the erfinaungsgemäßeQ layer on the other hand, since duroh no harmful tensile stresses on ^ the Tension over the whole Taasp

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the pressure on the adhesive tape is retained. Through this Mutual detachment or mutual tearing of the filiches attached to one another is not possible.

In addition, lilßfc dia grindurucsrremltße Sehlöhfe. dur »uh edna

sufficient elastisoh-nachßloblge shear shaping auoh i
"an expansion of the propellant charge in axial direction on

In the drawing is an exemplary embodiment of the invention shown. Show it

Flg. 1 a solid rocket engine in the Lüngssonnltt, Fig * 2 «a section along the line 1I-XI of Fig. I,

Pig. 3 shows a sector-shaped section of the engine according to FIGS. 1 and 2 in an enlarged ifeßstab.

Inside a combustion chamber housing 1 is a solid propellant 2, which is designed as a hollow burner with a central interior 3. One between that The outer circumference of the propellant charge 2 or the outer circumference of an insulation layer 4 surrounding it and the inside of the Brennkammers'chiluses 1 provided rinsing gap 5

for the resilient support of the. Propellant charge 2 opposite

dom BrcnnkainincrgehJiusü 2 filled with an elastic mass or layer 6. This is on the one hand with the inside of the BrcnnkamraargchUuscs 1 and on the other hand with the outside of the propellant charge 2 _; dot »outside of the insulation layer 4 firmly bonded. As a result, the propellant charge 2 is supported not only in the radial but also in the axial direction. As can be seen from FIG. 3, a plastic is provided as the mass for forming the base layer, which is mixed with suitable chemicals before it is introduced into the longitudinal gap 5 Layer 6 formed in this way is thereby under tension _a

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Claims (1)

Attachment of a front or inner burner cover for solid rocket engines within the combustion chamber housing, between its inside and the outer circumference of the propellant or an insulating layer enveloping it, an annular gap that allows the thermal expansion differences between the propellant and the combustion chamber housing is arranged, which is completely filled with an elastic seal radially outwardly connected fcsthaftend with the inside of Erennkammergehäuses and radially inner with the outer periphery of the propellant charge or of the insulation layer, characterized gekennzeleh η ο t t that provided in the free annular gap (5) layer (6) made on £? Qsohiiuinte ! s plastic contains pressurized gas pockets (7).