JPH079217B2 - Combustion pressure controller for gas generator for ram rocket - Google Patents

Description

Description: TECHNICAL FIELD The present invention relates to a ram rocket in which a combustible gas and external air introduced from outside are mixed in a combustion chamber for secondary combustion.
The present invention relates to a combustion pressure control device for a gas generator that functions as a so-called primary combustion chamber that generates a combustible gas and supplies it to a combustion chamber (secondary combustion chamber).

2. Description of the Related Art A ram rocket has a gas generator and a combustion chamber as its basic structure in order from the head side, and a side part is provided with a diffuser that opens to the head side and communicates with the combustion chamber. The gas generator is loaded with a solid sustainer propellant having an excess fuel composition and the combustion chamber is loaded with a solid booster propellant. Then, the above-mentioned ram rocket starts by the ignition of the booster propellant, and when the predetermined speed is reached at the end of the boost flight, the sustainer propellant is ignited,
Combustible gas generated by the combustion (primary combustion) of the sustainer propellant is mixed with the outside air introduced from the diffuser, and the secondary combustion is continuously performed in the combustion chamber to continuously fly (for example, the Japan Aerospace Society). Volume "Aerospace Engineering Handbook Supplement", (Sho 59, 10, 10), Maruzen, P655-656).

Here, in the above-mentioned ram rocket, as shown in FIG. 4, a flow rate adjusting mechanism is provided in the fuel injection nozzle 101 of the gas generator 100, and the nozzle opening (effective opening area of the fuel injection nozzle) is provided by the pintle 105. There is a method in which the flow rate of the combustible gas is controlled by changing the above to stabilize combustion and thrust associated therewith.

The gas generator 100 has a sustainer propellant 1
02 is loaded into the combustion chamber 103 through the nozzle 101.
Is in communication with. The nozzle 101 has a throat portion 101b continuous with the convergent portion 101a, and the convergent portion 101a has a drive shaft 104 penetrating in its diameter direction and a pintle 105 in the axial direction of the nozzle 101. A holder 106 for movably holding is provided.

The drive shaft 104 has one end connected to a speed reduction mechanism 108 of a servo motor 107 provided outside the nozzle, and a sealant 109 interposed between the drive shaft 104 and the nozzle wall. The pintle 105 has a conical tip end extending to the throat portion 101b, and a spherical cam 110 having an eccentric position fixed to the drive shaft 104 is engaged with the base portion.

The flow rate adjusting mechanism described above inputs a preset command signal from the outside to rotate the drive shaft 104 around the axis by the servo motor 107, and the pintle 105 is nozzled through the spherical cam 110.
By moving in the axial direction of 101, the throat portion 101
The flow area of flammable gas is adjusted by changing the opening area of b.

DISCLOSURE OF THE INVENTION Problems to be Solved by the Invention However, in the conventional gas generator for a ram rocket provided with the flow rate adjusting mechanism as described above, the position of the pintle 105 is simply controlled to change the nozzle opening. Since the actual combustion pressure is not fed back, not only the responsiveness of the combustion pressure to the change in the nozzle opening degree is bad, but also the control error is large, and there is a limit in improving the accuracy of pressure control.

This is because even if the position command signal of the pintle 105 is preset based on the relationship between the combustion area of the sustainer propellant 102 and the nozzle throat area, the sustainer propellant 10
It is considered that the cause is the unstable combustion behavior that cannot be predicted during the combustion due to the influence of the physical properties of 2.

The present invention has been made in view of the above problems,
It is an object of the present invention to provide a pressure control device that improves the responsiveness and the accuracy of pressure control by directly feeding back the combustion pressure of the gas generator.

Means for Solving the Problem A first invention is to mix combustible gas injected from an injection nozzle of a gas generator and external air introduced from a diffuser in a combustion chamber and burn the same, and adjust a gas flow rate of the injection nozzle. In a device that variably controls the combustion pressure of a gas generator, a generator basic control unit that outputs a preset target value of the combustion pressure and a flow rate that adjusts the gas flow rate by changing the throat area of the fuel injection nozzle. The adjusting means, a pressure sensor for detecting the internal pressure of the gas generator, and the target value and the actual pressure detected by the pressure sensor are compared, and a signal corresponding to the difference is given to the flow rate adjusting means as a drive signal. And comparison control means.

A second aspect of the invention is to mix combustible gas injected from an injection nozzle of a gas generator and external air introduced from a diffuser in a combustion chamber and burn the same, and adjust a gas flow rate of the injection nozzle to burn pressure of the gas generator. In the device for variably controlling, the generator basic control means for outputting the preset target value of the combustion pressure to the flow rate adjusting means until the pressure of the gas generator after ignition of the gas generator reaches a predetermined value, A flow rate adjusting unit that adjusts the gas flow rate by changing the throat area of the injection nozzle, a pressure sensor that detects the internal pressure of the gas generator, and the difference between the above target value and the actual pressure detected by the pressure sensor are compared. When the internal pressure of the gas generator reaches a predetermined value, comparison control means that outputs a signal corresponding to A signal input to the flow rate adjusting means and a mode switching means for switching from the target value to the output of the comparison control unit.

Action According to the first aspect of the invention, the combustion pressure of the gas generator is feedback-controlled by having the pressure sensor as the feedback element.

According to the second aspect of the invention, the position of the pintle of the flow rate adjusting means is directly controlled initially as in the conventional case, but after the combustion pressure reaches a predetermined pressure, the feedback control is automatically switched to the above-mentioned feedback control. The combustion pressure is feedback controlled.

Embodiment FIGS. 1 and 2 are views for explaining an embodiment of the present invention, in which the left side of each figure is the head side and the right side is the tail side.

As shown in FIG. 2, the ram rocket R has a combustion chamber 4 at the tail of the gas generator 1 and a plurality of diffusers 14 at the sides. Further, on the head side of the gas generator 1, a driving means 17 for the pintle 12 described later is provided.
Is mounted on the head side of the driving means 17,
For example, a nose cone (not shown) for mounting a payload required for flight is connected.

The combustion chamber 4 is loaded with solid booster propellant 30. For this reason, a rocket nozzle 33 is separably incorporated into the inside of the ramjet nozzle 31 provided at the tail of the combustion chamber 4 by using a clamp 32, and a booster propulsion is provided inside the rocket nozzle 33. An igniter 34 for igniting the drug 30 is attached.

The diffuser 14 is open to the head side of the ram rocket R, communicates with the head of the combustion chamber 4, and the opening to the inside of the combustion chamber 4 is closed by a port cover 35. A pyrotechnic product 35a is attached to the surface of the port cover 35 on the diffuser 14 side. In addition, a storage portion 36 is continuously provided on the tail side of the diffuser 14, and a port cover releasing device 37 for operating the pyrotechnic product 35a is stored in the storage portion 36. .

The gas generator 1 includes a tank 3 loaded with a solid sustainer propellant 2 and an injection nozzle 5 communicating with a combustion chamber 4.
And a pipe-shaped pintle case 6 extending toward the injection nozzle 5 inside the tank 3 on the coaxial line.

The tank 3 has a head end of a cylindrical member 7 constituting a main body portion, a front end plate member 8 having a base end of the pintle case 6 fixed to the center thereof screwed thereto, and a tail portion of the front cylindrical member 7, A rear end plate member 9 having the injection nozzle 5 formed at the center is screwed together, and the tip of the pintle case 6 reaches the vicinity of the injection nozzle 5. The sustainer propellant 2 is loaded into the tank 3 through the restrictor 10 over the length of the pintle case 6. A heat insulating material 11 is interposed between the pintle case 6 and the restrictor 10 to enhance the heat protection performance for the pintle 12 inserted in the pintle case 6.

In addition to the igniter 13 for the sustainer propellant 2, a pressure sensor 40 for detecting the combustion pressure in the gas generator 1 is attached to the rear end plate member 9. The output signal of the pressure sensor 40 is input to the loop amplifier 43 as a comparison control means described later via the amplifier 41, and the pressure sensor 40 is substantially connected to the loop amplifier 43 in a pressure feedback loop. Is formed.

Here, as the pressure sensor 40, a sensor using heat-resistant silicon grease or the like as a pressure transmission medium to the piezoelectric conversion element is used.

The tank 3 has a connecting portion 4a that opens at the head of the combustion chamber 4.
In addition, the tail portion of the rear end plate member 9 is screwed. In addition,
A detachable or burnable cover may be provided at the opening of the connecting portion 4a.

When the pintle 12 is inserted in the pintle case 6, the conical tip portion extends to the center of the opening of the nozzle 5, and the base end formed with the male screw portion 12a is the tank 3.
A seal ring 15 that protrudes to the outside and is slidably contacted with the inner surface of the pintle case 6 is fitted near the base end. Also,
A guide ring 16 is fixed to the tip of the pintle case 6, and the guide ring 16 keeps the pintle 12 in a state where its axis coincides with the axis of the injection nozzle 5. Prevents flammable gas from entering between and. On the base end side of the pintle 12 above,
Drive means for axially reciprocating the pintle 12
17 are connected.

The drive means 17 includes a ball screw 18 and a servomotor 19
And a first bracket 21 fixed to the front end plate member 8 having a structure in which the pintle 12 is arranged on the coaxial line of the pintle 12.
Is attached to the screw shaft 18a of the ball screw 18 via a bearing 20 and the like, and the first bracket 2
The servo motor 19 is attached to the second bracket 22 fixed to 0.
Is fixed, and the screw shaft 18a and the output shaft 19a of the servomotor 19 are connected by a joint 23. Ball screw 1
The nut portion 18b of 8 is attached to the nut holder 24.
Then, the nut 25 is screwed onto the male screw portion 12a of the pintle 12 penetrating the nut holder 24 to connect the nut holder 24 and the pintle 12. This allows
The drive means 17 converts the rotational movement of the servo motor 19 into the linear movement of the nut holder 24 via the ball screw 18,
Reciprocate the pintle 12 in the axial direction.

Further, a potentiometer 26 having an input shaft 26a fixed to a nut holder 24 is attached to the first bracket 21 in order to detect the displacement of the pintle 12, and the potentiometer 26 is connected to the servo amplifier 27 in a pintle. It forms 12 position feedback loops. Then, the pintle 12 and the above-mentioned driving means 17 constitute a flow rate adjusting means 42 for adjusting the gas flow rate by changing the throat area of the injection nozzle 5. Here, the driving means 17 is the tank 3
The reason for being on the front side is to minimize the thermal influence of the gas generated by the gas generator 1 and maintain its operating performance.

In front of the servo amplifier 27, in addition to a loop amplifier 43 as comparison control means, a function generator 44 as generator basic control means is provided. The function generator 44 is preset with a target value of the combustion pressure according to the passage of time based on the relationship between the combustion area of the sustainer propellant 2 and the throat area of the injection nozzle 5. Pintle this
Servo amplifier 27 or loop amplifier as 12 position commands
A mode switching means 45 is provided between the function generator 44 and the loop amplifier 43. This mode switching means 45 is mainly composed of a relay switch 46 which is switched when the pressure feedback signal Pc exceeds a predetermined set level, and the output of the function generator 44 is output by the servo amplifier 27 by the operation of the mode switching means 45. And it is adapted to be selectively inputted to either of the loop amplifiers 43.

The ram rocket R equipped with the gas generator 1 described above
When the booster propellant 30 is ignited by the igniter 34, the igniter 34 is blown away to start and accelerate, and when the predetermined speed is reached at the end of the boost flight, the clamp 32 is released and the rocket nozzle 33 is released. , The port cover 35 is crushed by the operation of the pyrotechnic 35a by the port cover release device 37, and the diffuser 14 and the combustion chamber 4
Are brought into communication with each other (state shown in FIG. 1), and further the igniter 13 ignites the sustainer propellant 2.

At this time, since the pressure in the gas generator 1 is substantially zero until just before ignition, the output of the function generator 44 is directly input to the servo amplifier 27 as a position command of the pintle 12 without passing through the loop amplifier 43. . That is, the internal pressure of the gas generator 1 is not fed back until the internal pressure of the gas generator 1 reaches a predetermined pressure, and the pintle 12 is at the command position from the function generator 44, that is, at the fully closed position of the injection nozzle 5 in this embodiment. The pintle 12 is held just in front.

When the sustainer propellant 2 is ignited as described above, the combustible gas generated by the combustion fills the gas generator 1 and a part of the combustible gas is injected from the injection nozzle 5 into the combustion chamber 4. Then, the flammable gas injected into the combustion chamber 4 and the outside air introduced from the diffuser 14 are mixed and continuously burned in the combustion chamber 4 to continue flying.

In such a combustion process, when the internal pressure of the gas generator 1 reaches a predetermined pressure, the relay switch 46 of the mode switching means 45 is switched, and the output of the function generator 44 which has been input to the servo amplifier 27 until then is the loop amplifier. As a result of being input to 43, the position control of the pintle 12 until then is switched to the feedback control based on the pressure feedback signal Pc. That is, the servo motor 19 is driven by using a signal corresponding to the difference between the output signal of the function generator 44 and the pressure feedback signal Pc as a drive signal, and the pintle 12 is moved in the axial direction via the ball screw 18 and the nut holder 24. Thereby, the opening area of the throat portion of the injection nozzle 5 is changed to adjust the flow rate of the combustible gas.

As a result, the ram rocket R moves to the gas generator 1 described above.
As a result, combustion in the combustion chamber 4 and thrust associated therewith are controlled while continuing to fly.

Here, as a result of comparison between the conventional method based on the position control of the pintle 12 and the method of the present invention in which the position control of the pintle 12 and pressure feedback are used together, as shown in FIG. It was found that both the pressure response and the control error were greatly improved.

Further, when the system is configured only with the pressure feedback system of FIG. 1, the pintle 12 will fully close the throat portion of the injection nozzle 5 until the internal pressure of the gas generator 1 reaches a predetermined pressure. Immediately after ignition, the pressure generated from the igniter 13 may be applied to cause an abnormal increase in the internal pressure of the gas generator 1 (see the broken line in FIG. 3).
However, as in the above-described embodiment, the position of the pintle 12 is directly controlled until the internal pressure of the gas generator 1 reaches a predetermined pressure, and the pintle 12 does not fully close the nozzle throat portion. It will be possible to avoid excessive pressure rise.

As described above, according to the first aspect of the present invention, the internal pressure of the gas generator is detected and the feedback control is performed, so that the responsiveness of the combustion pressure is improved and the control error is small as compared with the conventional case. Therefore, the accuracy of combustion pressure control is improved.

According to the second aspect of the invention, in addition to the above-described effects, it is possible to prevent the pressure at the time of ignition of the gas generator from abnormally rising and bursting. In other words, the pressure generated from the igniter can be prevented. This has the effect of alleviating excessive pressure due to the pressure generated by the sustainer propellant.

[Brief description of drawings]

FIG. 1 is a diagram showing an embodiment of the present invention and is an enlarged explanatory view of a main part of FIG. 2, FIG. 2 is an explanatory view of the entire structure of a ram rocket, and FIG. FIG. 4 is a characteristic diagram showing the relationship, and FIG. 4 is a configuration explanatory diagram of a main part of a conventional gas generator. 1 ... Gas generator, 2 ... Sustainer propellant, 4
...... Combustion chamber, 5 ... Injection nozzle, 12 ... Pintle, 14 ...
… Diffuser, 17 …… Driving means, 18 …… Ball screw,
19 ... Servo motor, 40 ... Pressure sensor, 42 ... Flow rate adjusting means, 43 ... Loop amplifier as comparison control means, 44
...... Generator Function generator as basic control means, 45
...... Mode switching means, R …… Lamb rocket.

 ─────────────────────────────────────────────────── ─── Continuation of the front page (56) Reference JP-A-2-161159 (JP, A)

Claims (2)

[Claims] 1. A combustible gas injected from an injection nozzle of a gas generator is mixed with external air introduced from a diffuser in a combustion chamber to burn, and a gas flow rate of the injection nozzle is adjusted to vary a combustion pressure of the gas generator. In the controlled device, the generator basic control means for outputting a preset target value of the combustion pressure, the flow rate adjusting means for adjusting the gas flow rate by changing the throat area of the injection nozzle, and the internal pressure of the gas generator are controlled. A pressure sensor for detecting, and a comparison control unit for comparing the target value with the actual pressure detected by the pressure sensor and applying a signal corresponding to the difference to the flow rate adjusting unit as a drive signal. A combustion pressure control device for a gas generator for a ram rocket. 2. A combustible gas injected from an injection nozzle of a gas generator and external air introduced from a diffuser are mixed and burned in a combustion chamber, and a gas flow rate of the injection nozzle is adjusted to vary a combustion pressure of the gas generator. In the controlled device, a generator basic control means for outputting a preset target value of the combustion pressure to the flow rate adjusting means until the internal pressure of the gas generator reaches a predetermined value after ignition of the gas generator, and an injection nozzle. The flow rate adjusting means for changing the throat area of the gas generator to adjust the gas flow rate, the pressure sensor for detecting the internal pressure of the gas generator, and the target value above and the actual pressure detected by the pressure sensor are compared and the difference is equivalent When the internal pressure of the gas generator reaches a predetermined value, the comparison control means that outputs the signal The amount mode switching means for switching the output of the comparison control means a signal input to the adjusting means from the target value of the combustion pressure control apparatus for ram rocket gas generator, characterized in that it comprises a city.