JPH0452858B2 - - Google Patents

Description

[Detailed description of the invention] (1) Industrial application field The present invention relates to a ram rocket.

(2) Background of the technology After the ram rocket accelerates to a predetermined speed at which effective ram pressure is obtained by combustion of the booster propellant, an air injection port (hereinafter referred to as port ) is injected into the air pressurized by the ram pressure, and sustainer fuel is injected and combusted to perform ramjet propulsion.

Therefore, the front part of the combustion chamber must be sealed during booster propulsion, and the compressed air must be taken into the combustion chamber during ramjet propulsion.

(3) Prior Art A conventional ram rocket of this type is shown in Fig. 1 (AIAA-78-1059).

In Fig. 1, 1 is a motor case, which has an end plate 2 at the front and a partition wall 3 at an intermediate position, a heat-resistant insulator is attached to the inner surface, and a combustion chamber 4 serving as a booster and a sustainer is formed behind the partition wall 3. A plurality of gas outlets 5 are arranged around the axis of the bulkhead 3, and these gas outlets 5 are closed by a closure 14 during booster propulsion.

6 is a sustainer nozzle fixed to the motor case 1; 7 is a booster nozzle fitted to the sustainer nozzle so that it can be ejected rearward; 8 is a breakable joint for releasably coupling the booster nozzle to the sustainer nozzle; and 9 are four differential users attached to the outer periphery of motor case 1 with an open front.
Reference numeral 0 designates a removable port cover that closes the ports provided at the rear ends of these differential users and partitions the differential user 9 and the combustion chamber 4.

This port cover 10 uses the Neumann effect of a normal wire explosive to make the port 15 detachable.
The port cover 10, which has been fitted into the port 15 in advance, is either cut and separated from the port 15 or is crushed with explosives.

Further, 11 is an internal combustion type booster propellant loaded in the combustion chamber 4, 13 is an edge burning type sustainer propellant loaded in front of the bulkhead 3, and 15 is an ignition device for the sustainer propellant 13.

A ram rocket is assembled by attaching the stabilizing blades 16, a front head (not shown), etc. to the ram rocket motor having the above structure.

However, in conventional ram rockets as described above, the port cover is removed using pyrotechnics, so as the number of ports increases, the ignition system becomes complicated and reliability decreases. Great care must be taken in its design and manufacture, and care must also be taken in its handling.

(4) Purpose of the Invention The present invention has been made in view of the above, and provides a ram rocket that is highly reliable and easy to handle by allowing the port cover to be separated without the use of pyrotechnics. The purpose is to

(5) Structure of the Invention The above object is to provide an air injection port between a booster propellant chamber and a sustainer propellant chamber, and to provide the air injection port in the sustainer propellant chamber on the front end plate of the booster propellant chamber. An opening for allowing air from the air injection port to flow into the booster propellant chamber is provided at a location corresponding to the position of the nozzle, and a lid is provided for closing this opening from the booster propellant chamber side. This is achieved by a ram rocket provided with a nozzle closure that closes the nozzle and supports the lid.

(6) Embodiments of the invention Next, embodiments of the invention will be described based on the drawings.

2 to 4 show a ram rocket according to an embodiment of the present invention.

In Fig. 2, 21 is a motor case;
A sustainer propellant chamber 24 is formed at the front of the motor case 21 between a front mirror plate 22 and a rear partition wall 23, and this sustainer propellant chamber 24 is filled with sustainer fuel 25. A nozzle 26 for ejecting gas is provided approximately in the center of the rear bulkhead 23, and an igniter 27 is attached to face the sustainer propellant.

A booster propellant chamber 28 is formed at the rear of the motor case 21 between an end plate 29 and a booster nozzle 30. Inside this booster propellant chamber 28 is an internal combustion type booster propellant 31.
is provided, and after the combustion of this booster propellant chamber 31 is completed, the sustainer propellant 25 is combusted within this booster propellant chamber 28. Further, a sustain nozzle 33 is provided outside the booster nozzle 30, and the booster nozzle 30 is connected to, for example, a Maruman type clamp 7 and a separation set (not shown) so that the booster nozzle 30 can be discharged rearward after the booster propellant is burned. They are connected by a breakable joint 34 constructed in this manner.

Approximately the center of the end plate of the booster propellant chamber, that is, the rear partition wall 23 of the sustainer propellant chamber 24
A lid body 35 is provided with an opening at a position corresponding to the nozzle 26 and closes this opening during booster propulsion.
has been established. As shown in FIG. 3, the lid 35 is fitted into the end plate 29 from inside the booster propellant chamber 28, and can be removed by pressing from the outside (left side in the figure). Note that the reference numeral 36 in the figure indicates an insulator (not shown in FIG. 2) attached to the inner wall of the booster propellant chamber 28.

An air passage 37 is formed between the sustainer propellant chamber 24 and the booster propellant chamber 28, and a port 38 is opened in the motor case 21 forming this air passage 37. A differential user 39 is connected in series.

Further, the nozzle 26 of the sustainer propellant chamber 24
A nozzle closure 40 is provided to seal the nozzle 26, and the nozzle closure 40 is configured to abut and support the lid 35.

Therefore, in the ram rocket according to this embodiment, during booster propulsion, the lid body 35 is pressed outward by the pressure inside the booster propellant chamber 28, and the end plate 29
In addition to being supported by the nozzle closure 40, the strength of the end plate 29 does not need to be as strong as conventional ones, and the weight can be reduced. When the predetermined booster propulsion is completed, a pressure detector (not shown) detects the pressure in the booster propellant chamber, as shown in FIG. 4, and the booster nozzle 30 is disconnected. This operation is performed by operating the separation nut described above and breaking the breakable joint 34. Then igniter 2 in the sustainer propellant chamber
7 to ignite the sustainer propellant 25. Then, the pressure inside the sustainer propellant chamber 24 increases,
Nozzle closure 40 that sealed the nozzle 26
blown backwards. At this time, the nozzle closure 4
0 presses the lid 35 of the front head plate 29 of the booster propellant chamber 28 backward, and discharges the lid 35 from the booster propellant chamber 28 to the outside through the sustainer nozzle 33. Similarly, the nozzle closure 40 is also discharged to the outside, and air compressed by ram pressure as the rocket advances is injected into the booster propellant chamber 28 from the port 38 through the air passage 37 via the diff user 39. At the same time, the sustainer propellant 25 is transferred from the nozzle 26 to the booster propellant chamber 28.
The rocket is propelled by a ramjet by being ejected into the air and mixed with the compressed air and burned.

As described above, according to the ram rocket of this embodiment, air can be introduced into the combustion chamber without using pyrotechnics when transitioning from booster propulsion to sustainer propulsion. Furthermore, even when this ram rocket is being stored, the sustainer propellant is not exposed to the atmosphere directly, which prevents the performance of the propellant from deteriorating.

In this embodiment, the lid 35 has been described as being integrally formed, but the lid may be of a split type. In this case, the lid can be more smoothly discharged from the booster propellant chamber.

(7) Effects of the Invention As explained above, according to the present invention, an opening is provided in the end plate of the booster propellant chamber, and this opening is covered with a lid body, and this lid body is supported and the sustainer propellant chamber is provided with an opening. After installing a nozzle closure that closes the nozzle, air can be reliably introduced into the booster propellant chamber to perform sustainer propulsion without the need for any pyrotechnics, and it is also handled with special care during assembly. This has the effect of being able to be performed without requiring special attention.

[Brief explanation of the drawing]

FIG. 1 is a sectional view showing a conventional ram rocket, FIG. 2 is a sectional view of a ram rocket according to an embodiment of the present invention, FIG. 3 is an enlarged sectional view showing the lid of the ram rocket shown in FIG. 2, and FIG. 3 is an explanatory sectional view showing the operating state of the ram rocket shown in FIG. 3. FIG. 24...Sustainer propellant chamber, 26...Nozzle, 28
...booster propellant chamber, 29...end plate (front end plate),
35...Lid body, 38...Port, 40...Nozzle closure.

Claims (1)

[Claims] 1. Open an air injection port between the booster propellant chamber and the sustainer propellant chamber, and install an air injection port in the front head plate of the booster propellant chamber at a location corresponding to the nozzle provided in the sustainer propellant chamber. An opening through which air from the air injection exit port flows into the booster propellant chamber is provided, and a lid body is provided to close this opening from the booster propellant chamber side, while the nozzle is provided with a cover that closes the nozzle. A ram rocket characterized by being provided with a nozzle closure that supports the lid.