JP2000297701A - Poppet type thrustor valve - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve the control characteristic of a missile by providing an orifice driven by a drive mechanism to reciprocate on an outlet section to the discharge passage of high-pressure gas and a needle protruded toward the center of the orifice from the back face of a poppet on the thrustor valve of a solid propellant thrustor. SOLUTION: A needle 9 protruded backward from the back face 51 of a poppet 5 reciprocatable in a poppet chamber 2, is provided on a poppet type thrustor valve used for a thrustor 12 fitted around a missile 13. The needle 9 is reciprocated against an orifice 10. The orifice 10 is provided on the inlet side of a discharge passage 8, and it can be reciprocated by a drive mechanism 11. The passage area of high-pressure gas to the discharge passage 8 from a control chamber 7 is quickly changed by the reciprocation of the needle 9 due to the reciprocation of the poppet 5 and by the reciprocation of the orifice 10 due to the drive mechanism 11, and the high-speed control of thrust can be made.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION The present invention relates to a high-pressure and high-pressure combustion gas generated by burning a solid propellant (hereinafter referred to as "high-pressure gas"). The present invention relates to a poppet-type thruster valve of a solid propellant thruster for obtaining a thrust for directly generating a required turning acceleration and attitude control moment in order to control a flying flying object.

[0002]

2. Description of the Related Art As a device for generating turning acceleration and attitude control moment on a flying object,
In addition to a steering wing type steering device in which air force generated by flying acts on a lift surface to obtain a steering force, the flying device 13 is separated from the center of gravity of the flying object 13 shown in FIG. The thruster 12 for jetting the jet 20 from the side,
As shown in FIG. 4 (b), four jets 20 are provided at equal pitches in the circumferential direction, and the jet of the jet 20 is turned on / off from one of the thrusters 12.
There is a thruster type steering device that generates a thrust F necessary for turning, attitude control, etc., and performs flight.

[0003] Among the thrusters 12 used in such a thruster-type steering device, a high-pressure such as a solid propellant side thruster or the like, in which a jet 20 is generated by the combustion gas of a solid propellant to generate a thrust F, In the thruster 12 using a gas, there is a poppet type thruster valve which performs ON / OFF operation of the thrust F at high speed and uses a floating poppet type valve as a valve for performing frequent turning and attitude control. .

In such a poppet type thruster valve, a poppet is provided in a nozzle so as to be movable back and forth, and the poppet is moved back and forth by controlling the pressure in a control room provided on the back side of the poppet. The thrust F is turned on / off by opening and closing a nozzle outlet for ejecting the jet 20 to the outside.

FIG. 5 is a longitudinal sectional view of a conventional poppet type thruster valve in which such a floating poppet type valve is used. As shown in the figure, in a thruster 12 using a poppet thruster valve, a high-pressure gas consisting of a high-temperature, high-pressure combustion gas generated by burning a solid propellant is transferred from a gas source 1 to a poppet chamber 2. The thrust F is generated by the jet 20 which is guided and passes through the nozzle throat 3 and jets from the nozzle 4.

The high-pressure gas which is guided from the gas source 1 to the poppet chamber 2 to generate a thrust is not only the above-mentioned combustion gas but also a nitrogen gas which has a very large volume change when changing from a liquid state to a gas state. Etc. may be used.

On the other hand, a flow path 6 is provided inside the poppet 5, and the poppet chamber 2 is connected to a control room 7 provided behind the back surface 51 of the poppet 5 by the flow path 6, and a gas source is provided. The high-pressure gas supplied from 1 to the poppet chamber 2 is ejected from the nozzle 4 to generate thrust, and a part of the gas is introduced into the control chamber 7 through the flow path 6, and an opening / closing mechanism 19 is provided from the control chamber 7 on the way. The gas is discharged to the outside through the provided discharge channel 8. As the opening / closing mechanism 19, a mechanism that fully opens and closes the discharge flow path 8 such as a solenoid valve is used.

For this reason, when the discharge passage 8 is opened by the opening / closing mechanism 19, the control chamber 7 communicates with the outside, so that high-pressure gas flows into the control chamber 7 through the passage 6. The pressure in the control chamber 7 flows into the poppet chamber 2 almost without increasing, and the poppet 5
The pressure difference between the pressure acting on the flange 52 provided at the intermediate portion of the
The poppet 5 moves backward and downward in the figure, and an opening is formed between the tip surface 53 of the tapered poppet 5 and the nozzle throat 3, and the high-pressure gas is ejected to the outside and continues to generate thrust.

When the discharge passage 8 is closed by the opening / closing mechanism 19, the high-pressure gas flowing into the control chamber 7 through the passage 6 does not flow out through the discharge passage 8 to the outside. 7 rises and the poppet 5
The poppet 5 moves upward and forward in the drawing due to the pressure difference between the pressure of the high-pressure gas acting on the tip of the nozzle, and the opening formed between the nozzle throat 3 and the tip surface 53 is closed. The ejection of the high-pressure gas from the nozzle throat 3 stops, and no thrust is generated.

That is, the area where the high-pressure gas acts on the back face 51 of the poppet 5 facing the control chamber 7 acts on the tip of the poppet 5 including the flange 52 on the side facing the nozzle throat 3 of the poppet 5. As compared with the pressure receiving area of the high-pressure gas, the pressure of the high-pressure gas flowing into the control chamber 7 and the poppet chamber 2 is smaller by the area of the front end face 53 projecting outside from the nozzle throat 3 due to the closing of the opening / closing mechanism 19. By equalizing, the force acting on the rear surface of the poppet 5 from the control room 7 increases, the poppet 5 is moved forward, the tip surface 53 of the poppet 5 fits into the nozzle throat 3, and the nozzle throat 3 and the tip surface The opening formed between the opening and the opening 53 is closed, and no thrust is generated.

Since the flow rate of the high-pressure gas used for opening and closing the nozzle throat 3 is small by the operation of the opening / closing mechanism 19, the high-pressure gas is ejected from the nozzle throat 3 even if the opening / closing mechanism 19 has a small output. Can be controlled at high speed, and the thrust can be controlled.

However, as shown in FIG. 6, the rear pressure of the poppet 14 applied to the back surface 5 of the poppet 5 is substantially constant, even if the poppet 5 moves upward, without changing the exit area from the control room 7. On the other hand, when the poppet 5 moves upward, the forward pressure 15 of the poppet applied to the front end face 53 of the poppet 5 increases the amount of the front end face 53 protruding out of the nozzle throat 3, so that the pressure becomes lower. It becomes smaller because the exposed area increases.

As described above, in the conventional poppet thruster valve, the poppet pressure 16, which is the sum of the forces applied to the entire poppet 5, does not become zero, and the displacement of the poppet 5 is suppressed. 6, the force acting in the negative direction, that is, the force acting in the negative direction, does not act, and as shown in FIG.
Although the area of the outlet from the control chamber 7 does not change even when the poppet 5 moves upward and the movement of the poppet position x to the right increases, the flange portion of the poppet 5 is substantially constant. The poppet front pressing force 15 acting on the tip portion including the tip 51 rapidly increases because the tip face 53 projects from the nozzle throat 3 to the outside where the high-pressure gas does not act in the poppet chamber 2 as the poppet position x increases. Will decrease.

As a result, the poppet pressure 16 generated by the difference between the poppet rear pressure 14 and the poppet front pressure 15 is obtained.
Decreases rapidly with the increase of the poppet position x, similarly to the poppet front pressure 15, and no negative force acts to suppress the forward movement of the poppet 5, and the poppet 5 is moved to an arbitrary poppet position x. Can not be stopped still. That is, in the conventional poppet-type thruster valve, even when the discharge flow path 8 that can minimize the poppet pressure 16 is fully opened, the poppet pressure 16 cannot be set to 0, and the position of the poppet 5 is static. Therefore, it is not possible to obtain a stable target, and the jet 20 can be controlled only on / off.

Therefore, in controlling the flying object 13, it is not possible to directly generate a control force having a magnitude necessary for performing a required turning acceleration and attitude control moment. It is also conceivable to perform control such as generating a thrust by jetting the jet 20 in a pulse shape and controlling the pulse width to obtain a required turning acceleration in total, but the pulse width control has a minimum limit. Therefore, the required turning acceleration or attitude control moment cannot be generated accurately, and the control characteristics of the flying object deteriorate, and there is a problem that disturbance occurs in the control system.

[0016]

SUMMARY OF THE INVENTION The present invention solves the above-mentioned drawbacks of the conventional poppet thruster valve by changing the area of the outlet from the control chamber and stopping the poppet at an arbitrary position in the front-rear direction. Can control the flying object accurately and generate the necessary control force,
While making the flying object excellent in control characteristics,
An object of the present invention is to provide a poppet thruster valve that does not cause disturbance to a control system.

[0017]

Therefore, the poppet thruster valve of the present invention has the following means.

(1) It is introduced from outside into the poppet room,
A part of the high-pressure gas that is released from the nozzle throat to the outside to generate thrust is introduced into the control chamber provided behind the poppet chamber by a flow passage formed in the poppet that is freely movable in the poppet chamber. Then, the pressure of the high-pressure gas advances the inside of the nozzle throat, and the tapered poppet tip surface that closes the nozzle throat is retracted to open the nozzle throat. Driven by a drive mechanism installed at the rear, the outlet of the discharge flow path that discharges the high-pressure gas introduced into the control room to the outside moves forward and backward, and adjusts the flow rate of the high-pressure gas discharged to the outside to control the poppet tip. An orifice was provided to retract the surface and adjust the nozzle throat to an adjusted opening suitable for control of the flying object.

(2) It is projected from the back of the poppet toward the center of the orifice, moves following the back-and-forth movement of the poppet, and when passing through the center of the orifice, changes the cross-sectional area of the orifice and is introduced into the control room. A needle for controlling the flow rate of the high-pressure gas discharged from the discharge flow path to the outside together with the orifice to provide an adjusted opening degree suitable for controlling the flying object of the nozzle throat is provided.

Accordingly, in order to retreat the closed end face and open the nozzle throat, the control chamber outlet for discharging the high-pressure gas introduced into the control chamber to the outside through the discharge flow path is cut off. Since the area is variable and can be set arbitrarily, the poppet can be stopped at an arbitrary position in the front-rear direction, and the opening formed between the nozzle throat and the tip surface of the poppet can be arbitrarily sized to fly. The control force required for controlling the vehicle can be generated, and the flying object can have excellent control characteristics. In addition, which occurred in conventional pulse control,
There is no disturbance to the control system.

The poppet thruster valve of the present invention employs the following means.

(3) introduced into the poppet room from outside,
A part of the high-pressure gas that is released from the nozzle throat to the outside to generate thrust is introduced into the control chamber provided behind the poppet chamber by a flow passage formed in the poppet that is freely movable in the poppet chamber. Then, the pressure of the high-pressure gas advances the inside of the nozzle throat to retract the tapered poppet tip end surface which closes the nozzle throat, and is provided so as to protrude from the back surface of the poppet so as to open the nozzle throat. The outlet of the discharge passage that discharges the high-pressure gas introduced into the control chamber to the outside moves forward and backward following the forward-backward movement of the poppet, and adjusts the flow rate of the high-pressure gas discharged to the outside to clean the poppet tip surface. An orifice was provided to retract and adjust the opening of the nozzle throat to an adjusted opening suitable for control of the flying object.

(4) Projecting from the tip of the rod of the drive mechanism installed behind the control room toward the center of the orifice, when the drive mechanism drives through the center of the orifice, changes the cross-sectional area of the orifice. The orifice controls the flow rate of the high-pressure gas introduced into the control chamber to the outside from the discharge flow path, and provides a needle that adjusts the opening of the nozzle throat to an adjusted opening suitable for controlling the flying object. Was.

[0024] Thus, similarly to the above-described invention, the cross-sectional area of the control chamber outlet for discharging the high-pressure gas to the outside through the discharge channel can be arbitrarily set variably, and the poppet can be moved in the front-rear direction. Can be stopped at any position, and the opening formed between the nozzle throat and the poppet tip surface can be made any size, and a control force suitable for controlling the flying object can be generated. Therefore, the flying object can have excellent control characteristics.

[0025]

DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of a poppet type thruster valve according to the present invention will be described with reference to the drawings. In addition,
The same members and similar members as those of the conventional poppet thruster valve described in the related art are denoted by the same reference numerals, and description thereof will be omitted as much as possible. FIG. 1 is a longitudinal sectional view showing a first embodiment of a poppet thruster valve according to the present invention. FIG. 1 (a) is a longitudinal sectional view, and FIG. 1 (b) is a force acting on a poppet shown in FIG. 1 (a). FIG.

As shown in FIG. 4, the poppet type thruster valve used for the thruster 12 and mounted around the flying object 13 is provided in the poppet chamber 2 as shown in FIG.
The needle 9 is provided rearwardly from the back surface 51 of the poppet 5 provided in the poppet chamber 2 so as to be able to freely move back and forth inside the poppet chamber 2, and the tapered portion provided at the rear end of the needle is provided rearward of the poppet 5. The orifice 10 is provided so as to be able to move in and out of the central portion by the movement of the orifice.

The orifice 10 is connected to the discharge passage 8
And is movable in the front-rear direction by a drive mechanism 11 installed at the rear of the poppet chamber 2.
The drive mechanism 11 includes an opening / closing mechanism 19 installed in the middle of the discharge flow path of the conventional poppet thruster valve.
While only ON-OFF control is possible, the rod,
In other words, the orifice 10 fixed to the tip of the rod can be arranged at any position in the front-rear direction.

Therefore, in the poppet thruster valve of the present embodiment, the needle 9
Of the high-pressure gas from the control chamber 7 to the discharge channel 8 can be quickly changed by the longitudinal movement of the orifice 10 due to the expansion and contraction of the rod by the drive mechanism 11. That is, by rapidly changing the flow rate of the high-pressure gas discharged from the discharge passage 8 to the outside, the high-pressure gas can be spouted from the nozzle throat 3 at a high speed, and has a unique effect that the thrust can be controlled at a high speed. It can be a poppet thruster valve.

That is, in FIG. 1, when the poppet 5 moves downward in the figure, the tapered rear end of the needle 9 enters the center of the orifice 10, and the exit area from the control chamber 7 decreases. . Further, when the poppet 5 moves upward in the figure, the rear end of the needle 9 comes out of the center from the orifice 10, and the exit area from the control chamber 7 increases.

Here, the pressure of the control chamber 7 is determined by the amount of the high-pressure gas flowing from the flow path 6 and the amount of the high-pressure gas flowing out through the orifice 10 and the flow path 8. Moves upward, the pressure in the control chamber 7 drops rapidly, and when the position of the poppet 5 moves downward, it rises sharply. For this reason, when the force applied to the poppet 5 by the high-pressure gas is expressed with the position x of the poppet 5 as a horizontal axis, as shown in FIG. As it gets larger, it gets smaller rapidly.

When the poppet 5 moves upward, similarly to the conventional poppet thruster valve, the front end face 53 of the poppet 5 is applied to the front of the poppet 5.
Comes out of the nozzle throat 3, so that the area exposed to low pressure increases and decreases. That is, poppet 3
Is zero at a certain point of the poppet position x, and when the poppet 5 is located behind the poppet position x at which the poppet position becomes zero, the poppet pressure 16 is displaced with respect to the displacement of the poppet 5. , That is, a poppet pressure 16 acting in the negative direction can be generated. Thereby, the position of the poppet 5 can be given static stability.

Further, the poppet position x at which the poppet pressure 16 can be reduced to 0, the so-called stable position,
By moving the position 0 in the front-back direction by the drive mechanism 11, the stable position can be changed and the poppet 5 can be stopped at an arbitrary poppet position x. Also,
Since the flow rate of the high-pressure gas injected from the nozzle 4 to the outside is determined by the opening area formed between the nozzle throat 3 and the tip end surface 53 of the poppet 5, by continuously changing the poppet position x, It becomes possible to continuously control the injection flow rate of the high-pressure gas from the nozzle 4, that is, the magnitude of the thrust for controlling the flying object 13.

Since the flow rate of the high-pressure gas flowing out of the discharge passage 8 by the operation of the drive mechanism 11 is small, a small output
Even with a small drive mechanism 11, high-pressure gas ejection changes can be controlled at high speed. Therefore, a small output / small drive mechanism 11
In addition to having characteristics that enable high-speed control such as turning acceleration and attitude control moment, it is possible to continuously control the injection flow rate from the nozzle 4, which is necessary for controlling the flying object. The required turning acceleration, posture control moment, and the like can be generated with high accuracy.

FIG. 3 is a longitudinal sectional view showing a second embodiment of the poppet thruster valve according to the present invention.

In the present embodiment, the orifice 17 is provided on the back surface 51 of the poppet 5, and the drive mechanism 11 that allows the needle 18 to enter and exit the center of the orifice 17 is provided behind the poppet chamber 2. It was provided. That is, in the drawing, when the poppet 5 moves backward and downward in the drawing, the tip of the needle 18 enters the center of the orifice 17 and the outlet area from the control chamber 7 decreases.

In addition, when the needle 18 moves forward in the upper part of the figure, the tip of the needle 18 comes out of the orifice 17 and the outlet area from the control chamber 7 increases. Here, similarly to the first embodiment described above, the pressure in the control chamber 7 is determined by the amount of the high-pressure gas flowing from the flow path 6 and the amount of the high-pressure gas flowing out through the orifice 17 and the discharge flow path 8. Since the pressure is determined, when the position of the poppet 5 moves forward, the pressure in the control chamber 7 decreases, and when the position moves backward, the pressure increases.

Also in this embodiment, when the so-called poppet pressure 16 applied to the poppet 5 is represented as a poppet position x, the force 14 applied to the rear of the poppet 5 is similar to that of the first embodiment shown in FIG. , As the poppet 5 moves forward. Further, when the poppet 5 moves forward, the front end of the poppet 5 applied to the front of the poppet 5 goes out of the nozzle throat 3, so that the area exposed to a low pressure increases and decreases rapidly.

That is, the poppet pressure 16, which is the sum of the forces applied to the poppet 5, becomes zero at a certain point, and a force acts in a negative direction with respect to the displacement of the poppet 5. Thereby, static stability can be given to the position of the poppet 5. Further, by moving the position of the needle 18 in the front-back direction by the driving mechanism 11, the stable position can be changed and the poppet 5 can be stopped at an arbitrary position.

Since the flow rate of the high-pressure gas from the nozzle 4 is determined by the area of the nozzle throat 3, the poppet 5
Is continuously changed, the flow rate of the high-pressure gas can be continuously controlled. Further, since the flow rate handled by the drive mechanism 11 is small, the ejection of the high-pressure gas can be controlled at high speed even with a small output and small drive mechanism. Therefore, it is possible to continuously control the flow rate while having a characteristic capable of high-speed control with a small output and small driving mechanism. Control moment can be generated.

[0040]

As described above, the poppet thruster valve of the present invention is driven by the drive mechanism installed behind the control chamber, and moves back and forth at the outlet to the high pressure gas discharge flow path. A needle protruding from the back of the poppet toward the center of the orifice was provided.

Thus, the poppet can be stopped at any position in the front-rear direction, and the opening formed between the nozzle throat and the tip surface of the poppet can be made any size to control the flying object. Control force can be generated, and the flying object can be made to have excellent control characteristics. In addition, disturbance to the control system does not occur.

Also, the poppet thruster valve of the present invention is driven by an orifice provided from the back of the poppet to an outlet to the high-pressure gas discharge passage, and a drive mechanism provided behind the control chamber. A needle that moves back and forth toward the center of the circle is provided.

Thus, similarly to the above-described invention, the cross-sectional area of the control chamber outlet can be varied and set arbitrarily. The size of the opening formed between them can be arbitrarily set, the flow rate of the high-pressure gas discharged from the control room outlet can be set arbitrarily, and the control can generate a control force suitable for controlling the flying object. Excellent characteristics can be obtained.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional view showing a first embodiment of a poppet type thruster valve of the present invention. FIG. 1 (a) is a longitudinal sectional view, and FIG. 1 (b) works on the poppet shown in FIG. 1 (a). Schematic diagram showing the force,

FIG. 2 is a view showing a force acting on a poppet at each poppet position of the poppet type thruster valve shown in FIG. 1;

FIG. 3 is a longitudinal sectional view showing a second embodiment of the poppet thruster valve according to the present invention;

4A and 4B are diagrams illustrating a flying object in which a control force such as a turning acceleration and a posture control moment is generated by a side thruster. FIG. 4A is a side view, and FIG.
FIG. 3A is a cross-sectional view taken along the line AA shown in FIG.

5A and 5B are diagrams showing a conventional poppet thruster valve, FIG. 5A is a longitudinal sectional view, FIG. 5B is a schematic diagram showing a force acting on the poppet shown in FIG.

FIG. 6 is a diagram showing forces acting on the poppet at each poppet position of the poppet thruster valve shown in FIG.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Gas source 2 Poppet chamber 3 Nozzle throat 4 Nozzle 5 Poppet 51 Back surface 52 Flange part 53 Tip surface 6 Flow path 7 Control room 8 Drain flow path 9 Needle 10 Orifice 11 Drive mechanism 12 Thruster 13 Flying object 14 Poppet rear pressure 15 Poppet front pressure 16 Poppet pressure 17 Orifice 18 Needle 19 Opening / closing mechanism 20 Jet F Thrust x Poppet position

Claims (2)

[Claims] A nozzle having a nozzle throat, a poppet chamber provided behind the nozzle throat, and a control chamber provided behind the poppet chamber, provided in the poppet chamber so as to be movable back and forth, and A flow path for introducing the high-pressure gas introduced into the poppet chamber into the control chamber disposed at the rear rear side, and a tapered tip surface that advances inside the nozzle throat by the high-pressure gas and closes the nozzle throat. A poppet, a poppet thruster valve comprising a discharge flow path for discharging the high-pressure gas to the outside and closing the front end face to open the nozzle throat, and driven by a driving mechanism installed behind the control chamber. An orifice that moves back and forth at an outlet of the high-pressure gas to the discharge channel; A poppet-type thruster valve comprising a needle protruding from the back of a pet toward the center of the orifice. 2. A nozzle having a nozzle throat, a poppet chamber provided behind the nozzle throat, and a control chamber provided behind the poppet chamber, the nozzle being provided movably back and forth in the poppet chamber, and A flow path for introducing the high-pressure gas introduced into the poppet chamber into the control chamber disposed at the rear rear side, and a tapered tip surface that advances inside the nozzle throat by the high-pressure gas and closes the nozzle throat. A poppet thruster valve comprising a poppet and a discharge flow path for discharging the high-pressure gas to the outside and closing the front end surface to open the nozzle throat, wherein the discharge flow path of the high-pressure gas from the back of the poppet And an orifice protruding to the outlet part, and installed behind the control room A poppet-type thruster valve provided with a needle driven by a driving mechanism and moved back and forth toward the center of the orifice.