JP4001667B2 - Rocket thrust direction control device - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
TECHNICAL FIELD The present invention relates to a thrust direction control device for a rocket, and more particularly to a thrust direction control device by secondary fluid injection (referred to as Secondary Liquid Injection Thrust Vector Control, SITVC or LITVC), and more specifically, ejects fluid from a side wall downstream of a nozzle throat. Thus, the present invention relates to an apparatus for controlling a thrust direction by causing a secondary fluid to interfere with a main flow and generating a lateral force (aspect ratio thrust) in a wall direction as a result.
[0002]
[Prior art]
As conventional SITVC or LITVC, those using liquid (N ₂ O ₄ , freon, sodium perchlorate aqueous solution), cold gas (N ₂ , He), etc. in addition to hot gas as secondary injection fluid are widely known. (See, for example, “Enhanced Aerospace Engineering Handbook”, Sho 59.10.10, published by Maruzen Co., Ltd., P652-654, and JP-A-1-277666, etc.).
[0003]
[Problems to be solved by the invention]
In the conventional thrust direction control device as described above, in order to control the pitch and yaw of the rocket, at least four injection ports for the secondary injection fluid provided in the nozzle are necessary, and each injection port is independent. It is necessary to install multiple injection fluid storage tanks, electro-hydraulic servo valves for driving the injection valves, and a hydraulic power source around the nozzle. The airtightness confirmation work requires a great number of man-hours, which is not preferable.
[0004]
In particular, when a blow-down type oil tank that uses high-pressure nitrogen gas or the like is used as the hydraulic source, and depending on the secondary injection fluid used, a high-pressure gas and secondary injection fluid filling device is required as a launching facility. In addition, there is a problem that the operation work just before the launch becomes troublesome.
[0005]
The present invention has been made paying attention to the problems as described above. By taking out a part of the combustion gas in the chamber of the rocket propulsion engine and using it as a secondary injection fluid, the equipment is simplified and the weight is reduced. At the same time, the present invention intends to provide a thrust direction control device that reduces the number of man-hours for airtightness confirmation and operation.
[0008]
According to the first aspect of the present invention, the nozzle formed in the rear wall surface of the nozzle of the solid rocket motor and the combustion gas in the chamber of the solid rocket motor is taken out without passing through the nozzle. A gas passage for supplying to the injection port, an injection valve for opening / closing the gas passage or the injection port, and an upstream side of the injection port in the gas passage for capturing the molten solid contained in the combustion gas. And collecting means for collecting . A plurality of the injection ports are provided at equal positions in the circumferential direction of the nozzle, and combustion gas is selectively injected from any one of the injection ports. An annular collection means is provided concentrically, and the collection means is shared by a plurality of injection ports .
[0012]
The invention described in claim 2 is characterized in that a collecting passage having a substantially labyrinthal cross section is formed by providing a plurality of partition walls inside the collecting means in the invention described in claim 1 .
[0013]
The invention described in claim 3 is characterized in that the injection valve in the invention described in claim 1 or 2 is driven to open and close by a solenoid.
[0014]
Therefore, in the first aspect of the present invention, the combustion gas in the combustion chamber of the solid rocket motor is once taken out without going through the nozzle, and then used as a secondary injection fluid from the injection port behind the nozzle throat portion. When injected into the nozzle, a lateral force in the direction of the injected wall is generated as in the prior art, and the thrust direction of the entire rocket is controlled. In particular, by selectively injecting combustion gas from any of a plurality of injection ports provided at equal positions in the nozzle circumferential direction, the pitch of the rocket and the attitude in the yaw direction can be controlled.
[0015]
Accordingly, it is sufficient if there is a passage for taking out combustion gas in the chamber and leading it to the injection port, and an injection valve for opening and closing the injection port, and a conventional tank or the like for storing the secondary injection fluid becomes unnecessary. .
[0016]
Here, in the solid rocket motor, the performance of the calorific value is increased by using aluminum or the like as an additive in the propellant itself. Therefore, the combustion gas in which the aluminum is dissolved, that is, aluminum oxide (alumina ) Will be included.
[0017]
Therefore, while the combustion gas in the chamber of the solid rocket motor is once taken out , the collection means is provided on the upstream side of the injection valve, so the molten solid matter such as alumina contained in the combustion gas is collected in the collection means. Collected and removed. By doing in this way, adhesion of the alumina to an injection valve etc. can be prevented.
[0021]
In the second aspect of the present invention, a plurality of partition walls are provided inside the collecting means to form a collecting passage having a substantially labyrinthal cross section, so that combustion gas passes through the collecting passage. By colliding with the partition walls, molten solids such as alumina adhere to the partition walls and are collected.
[0022]
In the third aspect of the invention, the above-described injection valve is driven to open and close by a solenoid, thereby eliminating the need for a conventional electro-hydraulic servo valve, hydraulic source, and the like.
[0023]
【The invention's effect】
According to the first aspect of the present invention, part of the combustion gas in the combustion chamber of the solid rocket motor is once taken out and used as a secondary injection fluid to be injected into the nozzle from the injection port behind the nozzle throat. As a result, not only can the posture control in the pitch and yaw directions be easily performed, but the secondary injection fluid storage tank, which has been required in the past, is no longer required. It is possible to reduce the man-hour required for the property confirmation work, eliminate the need for a fluid filling device in the launch facility, and reduce the operation man-hour required for the fluid filling.
[0024]
In addition, since a plurality of injection ports share a single annular collecting means provided outside the nozzle, the collection volume per injection port and thus the collection capacity can be increased. In addition to ensuring a large amount, the molten solid material such as alumina contained in the combustion gas is removed in advance by the collecting means , and then this is used as a secondary injection fluid to be injected. The object does not adhere to the injection valve and hinder the sealing performance, and the reliability is improved.
[0029]
According to the second aspect of the present invention, since a plurality of partition walls are provided inside the collecting means to form a collecting passage having a substantially labyrinthal cross section, the effect similar to that of the first aspect of the invention is provided. In addition, there is an effect that the collection path of the collection means can be secured longer and the collection ability can be further improved.
[0030]
According to the third aspect of the present invention, since the injection valve for injecting the combustion gas as the secondary injection fluid is driven by a solenoid, no conventional servo valve or hydraulic source is required. Thus, in addition to the same effect as that of the first or second aspect of the invention, there is an effect that further simplification and weight reduction of the entire apparatus can be realized.
[0031]
FIGS. 1 to 3 are diagrams showing a basic technology as a premise of the present invention, and show an example in which the present invention is applied to a solid rocket motor as a rocket propulsion engine.
[0032]
In FIG. 1, 2 is a chamber of the solid rocket motor 1, 3 is a nozzle provided at the rear of the chamber 2, and a propellant 5 is loaded into the chamber 2 via an insulator 4. This propellant 5 is a composite system in which a solid oxidizer powder such as ammonium perchlorate is mixed and cured using a polymer fuel (synthetic rubber) represented by unterminated hydroxyl group polybutadiene (HTPB) as a binder. In addition, an aluminum powder is added as an additive to improve performance as the calorific value increases.
[0033]
A ring-shaped holder 7 that is concentric with the nozzle 3 is mounted on the outer periphery of the nozzle 3 at a position rearward of the nozzle throat portion 6. As shown, electromagnetic injectors 8 each having a solenoid 9 as a drive source are provided. The nozzle injection port 10 of each electromagnetic injection valve 8 opens into the nozzle 3 through a port 11 formed in the holder 7 and an injection port 12 formed in the nozzle 3.
[0034]
In addition, a conduit 13 serving as a gas passage is provided between each electromagnetic injection valve 8 and the rear part of the chamber 2 so that the inlet side of each electromagnetic injection valve 8 and the inner space of the rear part of the chamber 2 are provided. Are connected to each other, and a filter 14 as a collecting means is interposed in each intermediate portion of each conduit 13.
[0035]
As shown in FIG. 3, each electromagnetic injection valve 8 moves the pin 15 up and down by reciprocating the spool 15 by the solenoid 9 to open and close the nozzle injection port 10. In the state, the port 18 communicating with the upper space of the nozzle body 17 is blocked by the spool 15, while the other port 19 adjacent to the port 18 communicates with the inlet port 22 via the bypass ports 20 and 21. Thus, the pintle 16 is pushed down by the combustion gas pressure acting on the inlet port 22 side, thereby blocking the flow of the combustion gas from the inlet port 22 side to the nozzle injection port 10 side. That is, the pintle 16 closes the nozzle injection port 10 due to the pressure receiving area difference between the upper surface of the large-diameter portion 16a and the lower surface of the large-diameter portion 16a.
[0036]
On the other hand, when the solenoid injection valve 8 is opened, if the spool 15 is moved to the left by the solenoid 9, the port 18 is opened to the outside and the other port 19 is shut off. External space pressure is applied to the space. As a result, the combustion gas pressure on the inlet port 22 side acts on the pintle 16 upward, and the nozzle injection port 10 opens when the pintle 16 rises.
[0037]
Here, the spool 15 and the pintle 16 and the sliding portion thereof are made of, for example, ceramic among the portions that become the gas passages in the valve case 23 of the electromagnetic injection valve 8, while the other portions are formed. It is covered with a CFRP insulator 24 to provide thermal protection.
[0038]
Further, as shown in FIG. 2, the filter 14 includes a plurality of partition walls (partition plates) 27 that are also made of CFRP in a case 26 whose inner peripheral surface is covered with an insulator 25 made of CFRP. At the same time, communication holes 28 are formed in a staggered manner in each partition wall 27, whereby a collection passage 29 having a substantially labyrinth cross section is formed in the filter 14.
[0039]
Therefore, according to the present technology, a high-temperature and high-pressure gas is generated with combustion of the propellant 5 in the chamber 2, and this combustion gas is ejected to the rear of the nozzle 3 through the nozzle throat portion 6. Get the thrust required for flight. This combustion gas temperature reaches, for example, 3500 ° K, and contains a melted aluminum powder blended as an additive, that is, alumina that is a molten solid. 14 also acts on the electromagnetic injection valve 8.
[0040]
Then, any one of the above four electromagnetic injection valves 8 is ON / OFF controlled at a necessary timing, and as described above, the spool 15 is moved forward from the position indicated by the solid line in FIG. As a result, the pintle 16 moves upward and the nozzle injection port 10 is opened.
[0041]
For example, when the electromagnetic injection valve 8A shown in FIG. 1 is opened, combustion gas is injected as a secondary injection gas from the nozzle injection port 10 into the nozzle interior 3 through the injection port 12 formed in the nozzle 3 itself, and the nozzle throat section 6 Is mixed with the main combustion gas that has passed through the nozzle 3 and ejected to the outside of the nozzle 3. At this time, the mixed region of the secondary injection gas injected from the injection port 12 and the main combustion gas, that is, the pressure at the portion from the injection port 12 at which the secondary injection gas is injected toward the outlet of the nozzle 3 is higher than the other portions. Therefore, a lateral force Fs opposite to the injection direction of the secondary injection gas is generated, which changes the pitch of the rocket body or the attitude in the yaw direction.
[0042]
Although the combustion gas contains alumina as described above, the alumina contained in the combustion gas is collected by passing through the filter 14 installed on the upstream side of each electromagnetic injection valve 8, and the spool 15 As a result, it is possible to prevent alumina from adhering to movable parts such as the pintle 16 and the like. That is, the high-temperature and high-pressure combustion gas passes through the relatively long labyrinth-like collecting passage 29 in the filter 14 before entering each electromagnetic injection valve 8, so that the temperature of the combustion gas gradually decreases and is finally reached. Specifically, while the temperature is lower than the heat-resistant temperature of each element forming the electromagnetic injection valve 8, the alumina component in the combustion gas is caused to enter each partition wall 27 by the temperature drop of the combustion gas itself and the collision between the gas and each partition wall 27. It is removed by adhering.
[0043]
As described above, according to the present technology, since a part of the combustion gas in the chamber 2 is taken out and effectively used as the secondary injection gas, a tank for the secondary injection gas becomes unnecessary. Of course, since the molten solid contained in the combustion gas is removed by the filter 14 to promote the temperature drop, the above-described poor sealing performance of the electromagnetic injection valve 8 due to the adhesion of the molten solid is prevented. In addition, the heat resistance durability of the electromagnetic injection valve 8 is also improved.
[0044]
Figure 4 is a graphical illustration of an exemplary embodiment of the present invention on the assumption the basic technique, whereas the filter 14 is also independent for each previous elementary the art the electromagnetic injection valve 8, this embodiment This embodiment is different in that a plurality of electromagnetic injectors 8 share a single filter 34.
[0045]
That is, an annular filter 34 is disposed on the outer periphery of the nozzle 3 concentrically with the nozzle 3, and the inner peripheral surface of the case 30 of the filter 34 is thermally protected by an insulator 31 made of CFRP. In addition, the inner space is partitioned by a plurality of partition walls 32 made of perforated disk-shaped CFRP, and further, communication holes 33 are formed in each partition wall 32 in a positional relationship that is farthest from each other. Yes. Thus, a collection passage 35 having a substantially labyrinth cross section is formed in the filter 34.
[0046]
The collection principle of the filter 34 in the present embodiment is the same as that of the basic technology described above, but there is an advantage that the total length of the collection passage 35 can be ensured to be very large as compared with the basic technology .
[Brief description of the drawings]
FIG. 1 is a diagram showing a basic technology as a premise of the present invention, and is a cross-sectional explanatory view of a main part of a solid rocket motor.
2 is an explanatory cross-sectional view of a main part of the filter shown in FIG.
3 is a cross-sectional explanatory view of the electromagnetic injection valve shown in FIG.
FIG. 4 is an explanatory cross-sectional view of a relevant part showing a typical embodiment of the present invention.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Solid rocket motor 2 ... Chamber 3 ... Nozzle 5 ... Propellant 6 ... Nozzle throat part 8 ... Electromagnetic injection valve 12 ... Injection port 13 ... Conduit (gas passage)
14 ... Filter 27 ... Partition 28 ... Communication hole 29 ... Collection passage 32 ... Partition 33 ... Communication hole 34 ... Filter 35 ... Collection passage

Claims (3)

An injection port formed in the wall surface behind the nozzle throat portion among the nozzles of the solid rocket motor,
A gas passage for taking out the combustion gas in the chamber of the solid rocket motor without passing through the nozzle and supplying it to the injection port;
An injection valve for opening and closing the gas passage or the injection port;
A collecting means provided on the upstream side of the injection port in the gas passage, and collecting the molten solid contained in the combustion gas;
With
A plurality of the injection ports are provided at equal positions in the circumferential direction of the nozzle, and the combustion gas is selectively injected from any one of the injection ports,
An apparatus for controlling the thrust direction of a rocket, characterized in that an annular collecting means is provided concentrically on the outside of the nozzle, and the collecting means is shared by a plurality of injection ports . 2. The thrust direction control device for a rocket according to claim 1, wherein a plurality of partition walls are provided inside the collecting means to form a collecting passage having a substantially labyrinthal cross section. The thrust direction control device for a rocket according to claim 1 or 2, wherein the injection valve is driven to open and close by a solenoid.

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