JP6247873B2 - Gas flow control device - Google Patents

Description

  The present invention relates to a flying object gas flow rate control device.

A ramjet refers to a rocket engine that does not have a mechanical compression device such as a turbine and a compressor unlike a turbojet and includes an air intake, a combustor, and an exhaust nozzle.
In such a ramjet-type rocket, immediately after the launch of the flying object, the propellant mounted inside is combusted and accelerated to a predetermined speed by the acquired propulsive force, and the combustion of the propellant is completed. A method is generally adopted in which air intake is started later and fuel is mixed and burned separately with the fuel mounted on the flying object.

  In the rocket as described above, a gas flow rate control device for adjusting the flow rate of supplying fuel to the combustion chamber is already known, for example, described in Patent Document 1 below.

  The conventional gas flow control device described in Patent Document 1 is a driving unit in the gas flow control device 37 after burning the propellant 33 mounted in a flying body 40 as shown in FIG. 37a is rotationally driven. As a result, as shown by the arrow in FIG. 1B, combustible gas (hereinafter referred to as gas) generated from the gas generator 36 flows into the combustion chamber 35. Note that this gas flows into the combustion chamber 35 via the valve 38 in this figure.

2A and 2B are views taken along arrows AA in FIG.
In FIG. 2A, the nozzle 37b provided in the gas flow rate control device 37 is in a state where the valve 38 is completely communicated. FIG. 2B shows the driving unit 37a rotated from the state of FIG. 2A around the rotation shaft 37c, and only a part of the nozzle 37b and the valve 38 communicate with each other. It is in a state. Thus, by rotating the drive unit 37a, it is possible to adjust the area (hereinafter referred to as effective area) where the nozzle 37b and the valve 38 communicate with each other, and thereby the flow rate of the gas flowing into the combustion chamber 35 It is possible to adjust.

US Pat. No. 6,405,526

  However, in the gas flow control device as described above, the effective areas of the nozzle 37b and the valve 38 are not circular as shown in FIG. Therefore, a drift occurs in the gas flowing through the valve 38, and the inside of the valve 38 may be locally eroded.

  Therefore, an object of the present invention is to provide a gas flow rate control device capable of adjusting the flow rate while preventing the occurrence of gas drift.

In order to achieve the above object, according to the present invention, the gas generator is disposed between a gas generator that generates combustible gas and a combustion chamber that combusts the gas, and flows into the combustion chamber from the gas generator. A gas flow control device for a flying body that adjusts a gas flow rate,
A hollow cylindrical valve member fixed to a partition wall that hermetically partitions the gas generator and the combustion chamber, and having a hollow hole with one end communicating with the combustion chamber and the other end closed;
A slider member attached to the outer periphery of the other end of the valve member and slidable in the axial direction of the valve member;
A drive device for sliding the slider member in the axial direction of the valve member,
The valve member is provided on the outer periphery of the other end portion in the circumferential direction, and has a plurality of vent holes communicating the outer peripheral surface with the hollow hole. .

Further, according to an embodiment of the present invention, the drive device has one end attached integrally with the slider member, and a drive shaft extending toward the combustion chamber with a gap from the valve member;
A linear motion actuator that moves the drive shaft in the axial direction.

According to the present invention, by providing a plurality of vent holes provided circumferentially on the outer periphery of the other end portion and communicating the outer peripheral surface and the hollow hole, gas drift occurs when gas flows into the valve member. Can be prevented.
Therefore, according to the present invention, the flow rate can be adjusted while preventing the occurrence of gas drift.

It is explanatory drawing of the gas flow control apparatus in a prior art. It is a front view of the gas flow control apparatus in a prior art. It is explanatory drawing of the flying body provided with the gas flow rate control apparatus in this invention. It is explanatory drawing of the gas flow control apparatus at the time of the gas inflow in this invention. It is explanatory drawing of the gas flow control apparatus at the time of the gas inflow stop in this invention. It is explanatory drawing of the flying body in the middle of the gas inflow to the combustion chamber in this invention.

  A preferred embodiment of the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

FIG. 3 is an explanatory diagram of a flying object provided with a gas flow rate control device according to the present invention.
The flying object 20 of the present invention is assumed to include a gas flow rate control device 10, a motor case 12, a propellant 13, a nozzle 14, a combustion chamber 15, and a gas generator 16.

The flying object 20 in this example is assumed to be a rocket bullet flying in the air toward a target point, for example. In FIG. 3, a configuration near the rear end in the traveling direction of the flying object 20 is illustrated.
Further, as shown in FIG. 3, the flying body 20 in this example acquires the propulsive force by burning the propellant 13 mounted therein immediately after launching. Then, after the combustion of the propellant 13 is completed, an air intake port (not shown) is opened. Thus, the gas generated from the gas generator 16 and the air introduced from the outside are mixed and combusted in the combustion chamber 15 to obtain a propulsive force, and the flight is continued.
In addition, this air intake port may be provided in the side surface of the flying body 20, and the opening may be made after combustion of the propellant 13 is completed.

In this example, it is assumed that the motor case 12 has a hollow shape and has a propellant 13 loaded therein.
Further, the motor case 12 in this example has an ignition device (not shown) provided with an ignition agent (not shown), for example, at its axial center, and by igniting the ignition agent by this ignition device, It is assumed that the propellant 13 starts to burn and gives propulsion to the flying object 20.

  In this example, the nozzle 14 is provided in communication with the rear end of the motor case 12 in the flight direction, and injects gas generated by the propellant 13 and the like backward in the flight direction.

The combustion chamber 15 gives a propulsive force to the flying object 20 by burning the gas generated from the propellant 13 and the gas generator 16 inside.
The combustion chamber 15 in this example is assumed to be in communication with a valve member 1 described later via a connecting portion 15a.

The gas generator 16 mixes external air to generate combustible gas for combustion in the combustion chamber 15. In this example, the gas generator 16 is ahead of the flying direction of the flying object 20 relative to the combustion chamber 15. positioned.
For example, the gas generator 16 may store solid fuel therein and generate gas by burning it with an ignition device (not shown).

In this example, the partition 17 partitions the gas generator 16 and the combustion chamber 15 in an airtight manner.
With this configuration, all the gas generated by the gas generator 16 flows into the combustion chamber 15 via the gas flow rate control device 10.

The partition wall 18 further partitions the space on the gas generator 16 side partitioned by the partition wall 17.
By having this configuration, it is possible to prevent the direct acting actuator 3b described later from coming into contact with the gas generated by the gas generator 16.
Details of the gas flow control device 10 of the present invention will be described later.

FIG. 4 is an explanatory diagram of a gas flow rate control device at the time of gas inflow in the present invention, and FIG. 5 is an explanatory diagram of the gas flow rate control device at the time of gas inflow stop in the present invention.
The gas flow rate control device 10 according to the present invention is installed between the gas generator 16 and the combustion chamber 15 and adjusts the flow rate of the gas flowing into the combustion chamber 15 from the gas generator 16.
In this example, the gas flow rate control device 10 includes a valve member 1, a slider member 2, and a drive device 3.

In this example, the valve member 1 is fixed to the partition wall 17 and has a hollow hole 1a with one end communicating with the combustion chamber 15 and the other end closed, and is assumed to have a hollow cylindrical shape. doing.
The valve member 1 is assumed to have a plurality of vent holes 1c described later.
By having this configuration, only the fluid introduced into the hollow hole 1 a inside the valve member 1 from the plurality of vent holes 1 c can flow into the combustion chamber 15.

The plurality of vent holes 1c are provided on the outer periphery of the other end portion 1b in the circumferential direction, and communicate with the outer peripheral surface and the hollow hole 1a. In this example, a plurality of vent holes 1c are assumed. .
With this configuration, when gas flows into the hollow hole 1a from the plurality of vent holes 1c, the gas flows inward in the axial direction of the valve member 1 and concentrates at the center thereof, and then flows toward the combustion chamber 15. become. Therefore, the gas does not concentrate toward a specific position on the inner wall of the valve member 1 (the inner wall of the hollow hole 1a), and it is possible to prevent a gas drift from occurring.
Therefore, according to the present invention, it is possible to prevent the occurrence of gas drift.

  In this example, the description has been given of the four vent holes. However, it is preferable that these vent holes are provided at equal intervals along the outer periphery of the other end portion 1b of the valve member 1. . Further, the number of vent holes is not limited to four, and may be, for example, eight vent holes.

The slider member 2 is attached to the outer periphery of the other end 1 b of the valve member 1 and is slidable in the axial direction of the valve member 1.
The slider member 2 has a through hole (not shown) directed in the axial direction of the valve member 1. With this configuration, the slider member 2 can pass through the valve member 1 through the through hole and slide in the axial direction of the valve member 1.

By having this configuration, the slider member 2 can be positioned so as to cover the plurality of vent holes 1 c of the valve member 1. Therefore, when the slider member 2 covers the plurality of vent holes 1c, it is possible to prevent the gas from flowing into the hollow hole 1a.
Furthermore, by adjusting the sliding distance of the slider member 2, it becomes possible to adjust the open areas of the plurality of vent holes 1c. Therefore, this makes it possible to adjust the flow rate of the gas flowing into the combustion chamber 15.

  In order to allow the slider member 2 to completely cover the plurality of vent holes 1c, it is necessary to adjust the length of the width of the slider member 2 (the axial length of the valve member 1).

  Further, it is assumed that the slider member 2 has an axial sectional area larger than the sectional area of the valve member 1. For example, in the example shown in FIG. 4, it is a polygonal flat plate, and the sectional area of the slider member 2 in the axial direction is larger than the sectional area of the valve member 1.

  With this configuration, when the gas flows into the valve member 1, the slider member 2 receives not only the pressure in the gas inflow direction but also the pressure directed in the opposite direction. For this reason, the pressure in the gas inflow direction can be offset to some extent. Therefore, the slider member 2 does not receive excessive pressure in the gas inflow direction, and thus has an advantage that it is not necessary to excessively increase the driving force when the slider member 2 is slid.

The driving device 3 slides the slider member 2 in the axial direction of the valve member 1.
The driving device 3 in this example is assumed to have a plurality of driving shafts 3a, a linear motion actuator 3b, a housing 3c, a nut member 3d, and a screw shaft member 3e.

One end of each of the plurality of drive shafts 3a is integrally attached to the slider member 2, and extends toward the combustion chamber 15 while being spaced from the valve member 1. In this example, the plurality of drive shafts 3a includes two drive shafts 3a. Assumes something.
In the example of FIG. 4, the slider member 2 has a horizontally long shape, and the two drive shafts 3 a are respectively attached to the horizontally long tip portions so that the respective drive shafts 3 a and the valve member 1 are spaced from each other. It is designed to be separated from each other.
With this configuration, it is possible to increase the distance between the valve member 1 and the drive shaft 3a, and thus it is possible to suppress heat inflow from the valve member 1 to the drive shaft 3a. Therefore, it is not necessary to take an excessive heat inflow countermeasure for the drive shaft 3a.

In addition, in order to adjust the space | interval of a valve member and the drive shaft 3a, the structure which employ | adopted what changed the shape of the slider member 2 (for example, adoption of further horizontally long shape etc.) may be sufficient.
In order to slide the slider member 2 in the axial direction of the valve member 1, it is preferable that each drive shaft 3 a and the valve member 1 are attached in parallel.

  Further, the drive shaft 3a in this example is composed of two drive shafts 3a. However, if the slider member 2 can be stably moved, the drive shaft 3a can be driven from one or more drive shafts 3a. It may be. In the case where three or more drive shafts 3a are provided, the shape of the slider member 2 (valve) can be attached so that the distance between the drive shafts 3a and the valve member 1 can be equal. It is necessary to change the axial sectional shape of the member 1 to a circular shape or the like.

  The linear actuator 3b is attached to all the other ends of the plurality of drive shafts 3a, and moves the plurality of drive shafts 3a along the axial direction of the valve member 1.

Specifically, as shown in FIG. 5, for example, a housing 3c having a single shape is connected to all the other ends of the plurality of drive shafts 3a, and the slider member 2, the plurality of drive shafts 3a, It is provided so that it can move integrally with the body 3c. Then, the nut member 3d provided in the housing 3c and the other end of the screw shaft member 3e having one end connected to the linear motion actuator 3b are caused to function as a ball screw. As a result, the rotational motion obtained from the linear motion actuator 3b is converted into translational motion by this ball screw, and the slider member 2, the plurality of drive shafts 3a, and the housing 3c are integrated in the axial direction of the valve member 1. It may be configured to be moved.
Even when the above-described slider member 2 or the like moves, the valve member 1 does not move because it is connected to the combustion chamber 15. Therefore, since the slider member 2 moves in the axial direction of the valve member 1 with respect to the valve member 1, the plurality of vent holes 1 c can be opened and closed by the slider member 2.

  In addition, in this example, although the structure which has the some drive shaft 3a was demonstrated, the structure which has only the single drive shaft 3a may be sufficient.

FIG. 6 is an explanatory diagram of a flying object during gas inflow into the combustion chamber in the present invention.
As shown in FIG. 6, after combustion of the propellant 13 in the combustion chamber 15, gas inflow by the gas generator 16 is started and the slider member 2 is moved in a direction to open the plurality of vent holes 1 c. By this, it becomes possible to start the flow of gas into the combustion chamber 15 by the gas generator 16.
In addition, by providing a lid member (not shown) in the connecting portion 15a, it is possible to prevent gas from the gas generator 16 from flowing into the combustion chamber 15 during combustion of the propellant 13, for example, combustion of the propellant 13 The configuration may be such that when this is completed, the lid member is removed to allow gas to flow into the combustion chamber 15.

  Further, in the present invention, an example in which only one gas flow rate control device 10 is mounted on the flying object 20 has been described. The flow rate may be adjusted more precisely.

According to the present invention, the valve member 1 has the plurality of vent holes 1c provided at equal intervals along the circumferential direction of the outer periphery thereof, so that gas drift is prevented when gas flows into the valve member 1. It can be prevented from occurring.
Therefore, according to the present invention, the flow rate can be adjusted while preventing the occurrence of gas drift.

  The present invention is not limited to the above-described embodiment, and various changes can be made without departing from the scope of the present invention.

DESCRIPTION OF SYMBOLS 1 Valve member 1a Hollow hole 1b Other end part 1c Vent hole 2 Slider member 3 Drive device 3a Drive shaft 3b Direct acting actuator 3c Case 3d Nut member 3e Screw shaft member 10 Gas flow control device 12 Motor case 13 Propellant 14 Nozzle 15 Combustion chamber 15a Connecting part 16 Gas generator 17 Partition 18 Partition 20 Flying object

Claims (2)

A gas flow control device for a flying object that is installed between a gas generator that generates combustible gas and a combustion chamber that combusts the gas, and that adjusts the flow rate of gas flowing from the gas generator into the combustion chamber. There,
A hollow cylindrical valve member fixed to a partition wall that hermetically partitions the gas generator and the combustion chamber, and having a hollow hole with one end communicating with the combustion chamber and the other end closed;
A slider member attached to the outer periphery of the other end of the valve member and slidable in the axial direction of the valve member;
And a driving device for sliding the slider member in the axial direction of the valve member,
Said valve member is provided in the other end periphery in the circumferential direction, it has a plurality of vent holes communicating the hollow bore and the outer peripheral surface thereof,
The plurality of vent holes are provided at one position in the axial direction, and the open area of each of the vent holes is adjusted by adjusting the sliding distance of the slider member. It is configured to adjust the flow rate of gas flowing into the combustion chamber,
The flying body gas flow rate control device , wherein the slider member is formed in a plate shape having a thickness in the axial direction . The drive device has one end integrally attached to the slider member, and a drive shaft extending toward the combustion chamber with a gap from the valve member;
The gas flow rate control device according to claim 1, further comprising: a linear motion actuator that moves the drive shaft in the axial direction.

Images