JPS60216055A - Heat insulative member fixing structure for rocket nozzle - Google Patents

Abstract

PURPOSE:To secure heat insulation members firmly without adhesive by covering the heat insulation members arranged on the outercircumferential surface section of nozzle skirt with heat-resistant mesh while securing said members to the nozzle skirt through said mesh. CONSTITUTION:Each carbon felt chip 27 of heat insulation member is overlapped while shifting sequentially to cover the outercircumferential face of skirt nozzle 21 and stitched through a slinger 28 to cover while developing the net 29 formed with carbon fiber threads while contacting tightly with the felt chip 27. Then the front end is bound to the front end of skirt 21 together with the felt chip 27 through fastening slinger 30a while to bind the rear end through another slinger 30b to the front end of skirt 21 together with the felt chip 27. The felt 27 is restricted by the stretched net 29 to secure the heat insulation member firmly and tightly without requiring adhesive.

Description

DETAILED DESCRIPTION OF THE INVENTION [Technical Field of the Invention] The present invention relates to a fixed 4VJ construction of a heat insulating member when the heat insulating member is disposed on the outer peripheral surface of a nozzle skirt.

(Technical Background) A rocket nozzle whose nozzle nose is made of carbon-carbon composite material is lightweight and has excellent heat resistance, and even when exposed to high-temperature combustion gas of 2000 to 2500"C when the rocket motor is operated, the rocket nozzle is lightweight and has excellent heat resistance. The nozzle skirt provides the necessary structural strength.

By the way, such a rocket nozzle, for example,
When the apogee motor M is used to place the satellite S on its final orbit as shown in the figure, the nozzle skirt 10 itself is
It is necessary to reduce the influence of thermal radiation from this nozzle socket 10 to the satellite S as much as possible.

Therefore, in order to suppress the influence of heat radiation from the nozzle skirt on other structures as described above, a heat insulating member is arranged and fixed on the outer peripheral surface of the nozzle skirt.

[Prior Art and Problems] Conventionally, a fixing structure for fixing a heat insulating member to the outer peripheral surface of a nozzle skirt as described above has been shown in FIG. 2, for example.

In the rocket nozzle 20 of the same drawing, 21 is a nozzle skirt formed of the composite material, and 22 is a nozzle skirt 2.
a skirt holder connected to the front end of the nozzle skirt 21 and the skirt holder 22,
A nozzle boulder 24 is fixed to the outer periphery of the nozzle skirt 21 through an insulator 23, especially at the portion facing the outer periphery of the nozzle skirt 21, and an insert 26 for forming a nozzle throat 25 is fitted to the inner periphery of the nozzle bolder 24. It is worn. Reference numeral 27 denotes a carbon felt piece serving as a heat insulating member having a substantially fan shape, and each carbon felt piece 27 is sequentially shifted and overlapped to form a nozzle skirt 2.
1, and each carbon felt I piece 27 is sewn together with a slinger 28, which is a carbon fiber thread. Furthermore, each carbon felt piece 27 sewn together by this slinger 28 has its nozzle skirt 21
A cement-based heat-resistant adhesive B is applied to the contact surfaces between the insulator 23 and the nozzle holder 24, and the rocket nozzle 20 is fixed to the rocket nozzle 20 by the adhesive B.

In the fixing structure of the heat insulating member attached to the rocket nozzle as described above, the carbon felt pieces 27 sewn together by the slinger 28 into a layered structure are fixed to the nozzle skirt 21 with adhesive B. Therefore, sufficient adhesion to the nozzle skirt 21 can be ensured.

However, when a rocket motor employing such a rocket nozzle 20 is operated, the nozzle skirt 21 itself becomes extremely dry, and gas is generated from the adhesive B.

As a result, when such a rocket nozzle 20 is adopted in the aboji motor M installed in the satellite S as described above, the gas generated from the adhesive B permeates through the carbon felt piece 27, and the permeated gas is transferred to the satellite S. The impact on onboard electronic equipment, solar cells, etc. is a problem, and special measures must be taken to prevent gas seals from entering Satellite S.

Furthermore, when the nozzle skirt becomes larger as the rocket motor becomes larger, the amount of the adhesive B increases, and the weight of the adhesive B itself becomes non-negligible.

[Objective of the Invention] The present invention has been made in view of the above, and it is possible to reliably fix a heat insulating member disposed on the outer peripheral surface of a nozzle skirt to the nozzle skirt without using an adhesive. It is intended to provide a fixed structure.

[Structure of the Invention] In order to achieve the above object, the present invention covers a heat insulating member disposed on the outer circumferential surface of a nozzle skirt with a heat-resistant net, and the heat-resistant mesh covers the heat insulating member in the nozzle skirt. -1./j.

[Embodiments of the invention] Hereinafter, embodiments of the present invention will be described based on the drawings.

FIG. 3 is a half-pi side view showing one embodiment of the present invention. In the same figure, the basic structure of the rocket nozzle 2o is the same as that shown in FIG.
1, an insulator 23, a nozzle holder 24, and an inlet 26 for forming a nozzle O-1-25.

Then, as in the past, each carbon felt piece 27 serving as a heat insulating member having a substantially sector-shaped shape is sequentially shifted and tied together to cover the outer peripheral surface of the nozzle skirt 21, and each carbon felt piece 27 is sewn together by a slinger 28. It is being Furthermore, each carbon felt piece 27 sewn together by the slinger 28 is shaped with carbon fiber thread, and its front end is tightened by a slinger 30a as shown in FIG. 27 to the front end of the nozzle skirt 21, and the rear end of the same slinger 30b as shown in FIG.
This allows the carbon felt piece 27 to be tied to the vortex 21a formed at the rear end of the nozzle skirt 21. The net 29 and each of the tightening slingers 30a and 30b are tied together with carbon fiber thread or the like, and the net 29 and the slingers 30.
a and 30b is further ensured.

As described above, according to this embodiment, the nozzle skirt 21
Since the carbon felt piece 27 sewn together by the slinger 28 that covers the outer circumferential surface of the This enables fixation that can withstand As a result, the conventional adhesive B is not required, the problem of gas generation is solved, and the net 29 is also lighter in mm than the adhesive B, so that the rocket nozzle 20 can be made of pumice.

It should be noted that each carbon fer interior 7, which is superimposed in layers, is likely to separate between layers during rocket flight, but according to this embodiment, such separation in the living room can be prevented by the net 29. can.

FIG. 6(a) is a side view of Ii showing another embodiment, and FIG. 6(b)
) is its external view. In this embodiment, the carbon felt piece covering the nozzle skirt is covered with a net, and the carbon felt piece on the large diameter side of the nozzle skirt, where there is a particularly high possibility of displacement, is covered with a net.

In FIG. 6, the basic structure of the rocket nozzle 20 is approximately the same as shown in FIGS.
A cavity H is formed between the nozzle holder 24 and the holding member 24a, and an insulator 31 is provided at the front end of the holding member 24a.

Then, the outer circumferential surface of the nozzle skirt 21 is covered with approximately sector-shaped carbon felt pieces 27 which are sequentially shifted and overlapped, and each carbon felt piece 27 is sewn together by a slinger 28. For example, after the carbon felt pieces 27 in such a state are stacked in four layers, the rear end of the nozzle having a diameter of a predetermined L1 or more is placed on a net 29, and both front and rear ends are held together with the carbon felt pieces 27 by slingers 30a and 30b. It is tied to the nozzle skirt 21. In addition, Netsu]-29 and Slinger 30a, 30b
As in the example described in tiJ, the carbon felt pieces 2 are tied together with carbon iim threads, etc., and the fifth layer of carbon felt pieces 2
7 and the fourth layer carbon felt piece 27, the net 29 is also sewn to the same layer 11.

As in the second embodiment, the stretched net 29 covers the part where displacement is likely to occur, that is, the rear end of the nozzle, to improve the adhesion between the carbon 71118 piece 27 and the nozzle skirt 21 in this part. Even if the
The entire heat insulating part made up of the carbon felt pieces 27 hardly shifts and is effectively fixed.

[Effects of the Invention] As described above, according to the present invention, the heat-insulating member disposed on the outer peripheral surface of the nozzle skirt is covered with a heat-resistant net, and the heat-insulating member is covered by the heat-resistant mesh. Since it is fixed to the nozzle skirt, there is no need for a contacting agent during the fixing, and the problem of gas generation from the contacting agent is solved, and the weight of the rocket nozzle can also be reduced.

[Brief explanation of drawings]

Fig. 1 is a dimensional explanatory diagram of the Aboji motor, Fig. 2 is a half-sectional view of the entire rocket nozzle showing a conventional 4N structure for fixing the heat insulating member, and Fig. 3 is an example of the fixing structure for the heat insulating member according to the present invention. FIGS. 4 and 5 are enlarged sectional views showing details of the end of the rocket nozzle in FIG. 3, and FIG. 6(a) is a half-sectional view of the entire rocket nozzle shown in FIG. A sectional view of the entire rocket nozzle showing another example of the structure, FIG. 6(b) is an external view of the example shown in FIG. 6(a). 20... D-cut nozzle 21... Nozzle skirt 22... Skirt holder 23... Insulator 24... Nozzle holder 25... Nozzle throat 26... Insert 27... Carbon felt piece 28 ...Slinger 29...Net 30a, 3
0b...Slinger patent applicant Nissan Motor Co., Ltd.

Claims (1)

[Claims] A heat insulating member in a rocket nozzle, characterized in that a heat insulating member disposed on the outer peripheral surface of a nozzle skirt is covered with a heat-resistant net, and the heat insulating member is fixed to the nozzle skirt by the heat-resistant net. fixed structure.