JPH0357868A - Combustion pressure control device of gas generator for ram rocket - Google Patents

Abstract

PURPOSE:To improve responsiveness and pressure control accuracy by providing a flow regulating means, which changes a throat area of an injection nozzle in a gas generator to adjust a flow rate of gas, and controlling this means in accordance with a deviation between the detection value and the target value of internal pressure of the gas generator. CONSTITUTION:A ram rocket R is provided with a combustion chamber 4 in the tail part of a gas generator 1 and a plurality of diffusers 14 in a side part. Here a driving means 17 of a pintle 12, which serves as a flow regulating means 42 for adjusting a flow rate of gas with a throat area changed in an injection nozzle 5, is mounted to a head part side of the gas generator 1. While a pressure sensor 40 for detecting a combustion pressure in the gas generator 1 is mounted to a rear part end plate member 9 in the center of which the injection nozzle 5 is formed. The internal pressure of the gas generator thus detected is compared with the target value, generated in a function generator 44, by a servo amplifier 27 with constitution provided so as to give a signal in accordance with this deviation to the driving means 17 as a drive signal.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of Industrial Application The present invention relates to a ram rocket that performs secondary combustion by mixing flammable gas and fresh air introduced from the outside in a combustion chamber.
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 flammable gas and supplies it to a combustion chamber (secondary combustion chamber).

The basic structure of a conventional ram-mouthed vent includes a gas generator and a combustion chamber in order from the head side, and a diffuser on the side that opens toward the head side and communicates with the combustion chamber. The gas generator is loaded with a solid sustainer propellant having a fuel-rich composition, and the combustion chamber is loaded with a solid booster propellant. Then, the above-mentioned ram rocket 1 starts by igniting the booster propellant, and when it reaches a predetermined speed at the end of boost flight, the sustainer propellant is ignited,
The flammable gas generated by the combustion (primary combustion) of the sustainer propellant is mixed with the outside air introduced from the diffuser, and the mixture is continuously burned in the combustion chamber to continue flying (for example, the Japanese Society of Aeronautics and Astronautics) ed. “Aerospace Engineering Handbook Expanded Edition” (October 10, 1982). Maruzen, P655
-656).

Here, in the above-mentioned ram rocket, as shown in FIG.
t is equipped with a flow adjustment mechanism, and the nozzle opening degree (effective opening area of the fuel injection nozzle) is changed by the bottle 105 to control the flow rate of combustible gas, thereby stabilizing combustion and the accompanying thrust. There is something I did.

The gas generator 100 has a sustainer propellant 102 loaded therein and communicates with a combustion chamber 103 via the nozzle 101 . The front three nozzle nozzle 101 has a throat portion 10lb that is continuous to the convergent portion 101a, and the convergent portion 101a has a drive shaft 104 passing through the convergent portion 101a in the diametrical direction, and a bottle 105 that connects the nozzle to the convergent portion 101a. A holder 106 is provided to hold the holder 101 movably in the axial direction.

One end of the drive shaft 104 is connected to a deceleration mechanism 108 of a servo motor 107 provided outside the nozzle, and a sealing material 109 is interposed between the drive shaft 104 and the nozzle wall. The bottle 105 has a conical tip portion extending to the throat portion 10lb, and a spherical cam 110 that is eccentrically fixed to the drive shaft 104 is engaged with the base portion.

The above-mentioned flow rate adjustment mechanism inputs a preset command signal from the outside, rotates the drive shaft 104 around the axis using a servo motor 107,
05 in the axial direction of the nozzle 101, the opening area of the throat portion 101b is changed to adjust the flow rate of the combustible gas.

Problems to be Solved by the Invention However, in conventional gas generators for ram rockets equipped with the flow rate adjustment mechanism as described above, the position of the bottle 105 is simply controlled to change the nozzle opening. Since the actual combustion pressure is not fed back, not only is the response of the combustion pressure to changes in the nozzle opening degree poor, but the control error is also large, and there is a limit to the improvement of the accuracy of pressure control.

This is because even if the position command signal of the bottle 105 is set in advance based on the relationship between the combustion area of the sustainer t[fflX 1 0 2 and the nozzle throat area, the influence of the physical properties of the sustainer propellant 102 This is thought to be due to unpredictable and unstable combustion behavior during combustion.

The present invention was made in view of the above problems.
The purpose is to provide a pressure control device that improves responsiveness and pressure control accuracy by directly feeding back the combustion pressure of a gas generator.

Means for Solving the Problems The first invention mixes and burns combustible gas injected from an injection nozzle of a gas generator and outside air introduced from a diffuser in a combustion chamber, and adjusts the gas flow rate of the injection nozzle. In a device that variably controls the combustion pressure of a gas generator using The N adjustment means and a pressure sensor that detects the internal pressure of the gas generator compare the target value and the actual pressure detected by the pressure sensor, and apply a signal corresponding to the difference to the flow rate adjustment means as a drive signal. and comparison control means.

Further, the second invention is to mix and burn the combustible gas injected from the injection nozzle of the gas generator and the outside air introduced from the diffuser in the combustion chamber, and adjust the gas flow rate of the injection nozzle to increase the combustion pressure of the gas generator. In the apparatus for variable control of the gas generator, the basic control means outputs a preset combustion pressure target value to the flow rate adjustment means until the pressure of the gas generator reaches a predetermined value after the gas generator is ignited. , a flow rate adjustment means 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 a comparison between the above target value and the actual pressure detected by the pressure sensor. A comparison control means outputs a signal corresponding to the difference as a drive signal, and when the internal pressure of the gas generator reaches a predetermined value, the signal input to the flow rate adjustment means is switched from the target value to the output of the comparison control means. and mode switching means.

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

Further, according to the second invention, initially the position of the bottle of the flow rate adjusting means is directly controlled as in the conventional case, but after the combustion pressure reaches a predetermined pressure, the control is automatically switched to the above-mentioned feedbank control. The combustion pressure is now under feedback control.

Embodiment FIGS. 1 and 2 are diagrams for explaining one 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 includes a combustion chamber 4 in the tail of the gas generator 1, and a plurality of diffusers 14 on the sides. Further, on the head side of the gas generator 1, a drive means 17 for a bottle 12, which will be described later, is mounted, and furthermore, on the head side of the drive means 17, a bay load necessary for flight, etc., is mounted. Connect the nose cone (not shown).

The combustion chamber 4 is loaded with a solid booster propellant 30 . Therefore, inside the ramjet nozzle 3I provided at the tail of the combustion chamber 4, a rocket nozzle 33 is removably installed using a clamp 32, and a booster propulsion nozzle 33 is also installed inside the rocket nozzle 33. medicine 30
An igniter 34 is attached for igniting.

The diffuser 14 opens toward the head of the ram rocket R and communicates with the combustion chamber 4 near the head, and the opening into the combustion chamber 4 is closed by a boat force bar 35. . Diffuser l of the boat cover 35
A pyrotechnic device 35a is attached to the fourth side surface. Also,
A storage section 36 is connected to the tail side of the diffuser 14, and the pyrotechnics 35a are stored in the storage section 36.
A boat cover release device 37 for operating the boat cover is housed.

The gas generator 1 includes a tank 3 loaded with a solid sustainer propellant 2, an injection nozzle 5 communicating with a combustion chamber 4, and a pipe-shaped bottle extending toward the injection nozzle 5 inside the tank 3. A torque case 6 is provided on the same axis.

The tank 3 has a front end plate member 8, which has the proximal end of the pintle case 6 fixed in the center, screwed to the head of a cylindrical member 7 constituting the main body, and a tail part of the front cylindrical member 7. It has a configuration in which a rear end plate member 9 with the injection/zzle 5 formed in the center is screwed together, and the tip of the bottle case 6 reaches near the injection nozzle 5. The sustainer propellant 2 is loaded into the tank 3 over the length of the pintle case 6 via a restrictor 1o. And bottle case 6 and restrictor l
By interposing a heat insulating material 11 between the pintle case 6 and the pintle case 6, the heat protection performance for the pintle l2 inserted in the pintle case 6 is enhanced.

Further, in addition to the igniter 13 for the sustainer propellant 2, a pressure sensor 40 for detecting the combustion pressure in the gas generator is attached to the rear end plate member 9.

The output signal of this pressure sensor 40 is input to a loop amplifier 43 as a comparison control means to be described later through an amplifier 41, and the pressure sensor 40 substantially forms a pressure feedback loop with the loop amplifier 43. ing.

Here, as the pressure sensor 40, one using heat-resistant silicone grease or the like as a pressure transmission medium to the piezoelectric transducer is used.

The tank 3 has a connecting portion 4 that opens at the head of the combustion chamber 4.
The tail portion of the rear end plate member 9 is screwed to a. Note that the opening of the connecting portion 4a may be provided with a cover having a detachment function or burnout function.

When the pintle 12 is inserted into the pintle case 6, the conical tip extends to the center of the opening of the nozzle 5, and the base end formed with the male thread 12a protrudes to the outside of the tank 3. A seal ring 15 is fitted in the vicinity of the proximal end to slide on the inner surface of the pintle case 6.

Further, a guide ring 16 is fixed to the tip of the pintle case 6, and this guide ring 16 keeps the axis of the pintle l2 coincident with the axis of the injection nozzle 5, and also keeps the axis of the pintle l2 coincident with the axis of the injection nozzle 5. This prevents flammable gas from entering between the bottle and the bottle 12. The above bottle
A driving means 17 for reciprocating the bottle 12 in the axial direction is connected to the base end side of the bottle 2.

The driving means 17 has a configuration in which a ball screw 18 and a servo motor 19 are arranged on the same axis of the bottle 12, and is connected to a first bracket 21 fixed to the front end plate member 8 via a bearing 20 or the like. At the same time, the screw shaft 18a of the ball screw 18 is attached to the second bracket 22 fixed to the first bracket 20,
The servo motor l9 is fixed, and the screw shaft 1 is
8a and the output shaft 19a of the servo motor 19 are connected by a joint 23. The nut portion tab of the ball screw 18 is attached to a nut holder 24. The male threaded portion 1 of the pintle 12 is passed through the nut holder 24.
By screwing the nut 25 onto 2a, the front S self-nut header 24 and the bottle 12 are connected. Thereby, the driving means 17 converts the rotational motion of the servo motor 19 into linear motion of the nyh holder 24 via the ball screw 18, and causes the bottle 12 to reciprocate in the axial direction.

Further, the input shaft 26a is attached to the nut holder 24 in the l-th bracket 2l in order to detect the displacement of the pintle 12.
A fixed potentiometer 26 is attached, and this potentiometer 26 forms a position feedback loop of the bottle l2 with the servo amplifier 27. The pintle 12 and the driving means I7 described above constitute a flow rate adjusting means 42 that changes the throat area of the injection nozzle 5 to adjust the gas flow rate. Here, the reason why the drive means 17 is located on the front side of the tank 3 is to minimize the thermal influence of the gas generated by the gas generator 1 and maintain its operational performance.

In the preceding stage of the servo amplifier 27, in addition to a loop amplifier 43 as a comparison control means, a function generator 44 as a basic control means for the gerator is provided. The function generator 44 has a target combustion pressure value set in advance in accordance with 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. This is output to the servo amplifier 27 or loop amplifier 43 as a position command for the pintle 12, and the function generator 44
A mode switching means 45 is provided between the loop amplifier 43 and the loop amplifier 43 . This mode switching means 45 is mainly composed of a relay switch 46 that is activated when the pressure feedback signal PC exceeds a predetermined set level. The signal is selectively input to one of the loop amplifiers 43.

Ram rocket R equipped with the above gas generator 1 is
When the booster propellant 30 is ignited by the igniter 34,
The igniter 34 is blown off to start and accelerate, and when the boost flight ends and a predetermined speed is reached,
When the clamp 32 is released, the location nozzle 33 is removed, and the boat cover release device 37 releases the pyrotechnics 3.
5a, the port cover 35 is crushed and the diffuser 14 and the combustion chamber 4 are brought into communication (the state shown in FIG. 1).
Furthermore, the Zastainer propellant 2 is ignited by the igniter l3.

At this time, since the pressure within 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 for the bottle 12 without passing through the loop amplifier 43. In other words, the internal pressure of the gas generator i is not fed back until the internal pressure of the gas generator 1 reaches a predetermined pressure, and the bottle l2 is at the commanded position from the function generator 44, that is, in this embodiment, slightly below the fully closed position of the injection nozzle 5. A bottle 12 is held in front.

When the sustainer propellant 2 is ignited as described above, the gas generator 1 is filled with flammable gas generated by its combustion, and a portion is injected into the combustion chamber 4 from the injection nozzle 5. Then, the combustible gas injected into the combustion chamber 4 and the outside air introduced from the diffuser 14 are mixed and continuously combusted in the combustion chamber 4, thereby continuing to fly.

In such a combustion process, when the internal pressure of the gas generator l reaches a predetermined pressure, the relay switch 46 of the mode switching means 45 switches, and until then the servo amplifier 27
As a result of inputting the output of the function generator 44, which had been manually operated, to the loop amplifier 43, the previous position control of the pintle l2 is switched to feedback control based on the pressure feedback signal Pc. In other words, function generator 4
By using a signal corresponding to the difference between the output signal of No. 4 and the pressure feedback signal Pc as a drive signal to drive the servo motor l9, and moving the pintle l2 in the axial direction via the ball screw l8 and the nut holder 24, injection is performed. The flow rate of the combustible gas is adjusted by changing the opening area of the throat portion of the nozzle 5.

As a result, Ram Rocket R uses the gas generator 1
This allows the aircraft to continue flying while the combustion in the combustion chamber 4 and the accompanying thrust are controlled.

Here, as a result of comparing the conventional method based on the position control of the pintle 12 and the method of the present invention which uses the above-mentioned position control of the pintle 2 in combination with pressure feedback, we found that the method of the present invention is as shown in FIG. It was found that both pressure response and control error were significantly improved.

In addition, if the system is configured with only the pressure feeder nozzle system shown in Fig. 1, the bottle 12 will fully close the throat part of the injection nozzle 5 until the internal pressure of the gas generator 1 reaches a predetermined pressure. Immediately after, igniter l3
There is a risk that the internal pressure of the gas generator 1 will rise abnormally due to the pressure generated by the gas generator 1 (see the broken line in Fig. 3). By directly controlling the position of the bottle 12 so that the bottle 12 does not fully close the nozzle throat, abnormal pressure increases can be avoided.

Effects of the Invention As described above, according to the first invention, by detecting the internal pressure of the gas generator and performing feedback control, the responsiveness of the combustion pressure is improved compared to the conventional method, and the control error is reduced. This improves the accuracy of combustion pressure control.

Further, according to the second invention, in addition to the above-mentioned effects, it is possible to prevent the pressure at the time of ignition of the gas generator from abnormally increasing and bursting, in other words, the pressure generated from the igniter and This has the effect of alleviating excessive pressure caused by the pressure generated from the sustainer propellant.

[Brief explanation of drawings]

Fig. 1 is a diagram showing an embodiment of the present invention, and is an enlarged explanatory view of the main part of Fig. 2, Fig. 2 is an explanatory diagram of the overall configuration of a ram rocket, and Fig. 3 is a diagram showing the relationship between combustion pressure and time of the gas generator. A characteristic diagram showing the relationship, FIG. 4 is an explanatory diagram of the configuration of the main parts of a conventional gas generator. DESCRIPTION OF SYMBOLS 1... Gas generator, 2... Sustainer propellant, 4... Combustion chamber, 5... Injection nozzle, 12... Pintle, Engineering 4... Diffuser, l7... Drive means, l8 ... Ball screw, 19 ... Servo motor, 4
0...Pressure sensor, 42...Flow rate adjustment means, 43.
...Loop amplifier as comparison control means, 44...Function generator as generator basic control means, 45...
- Mode switching means, R-... Ram rocket.

Claims (2)

[Claims] (1) Combustible gas injected from the injection nozzle of the gas generator and outside air introduced from the diffuser are mixed and combusted in the combustion chamber, and the gas flow rate of the injection nozzle is adjusted to variably control the combustion pressure of the gas generator. In such a device, the generator basic control means outputs a preset target value of combustion pressure, the flow rate adjustment means changes the throat area of the injection nozzle to adjust the gas flow rate, and the internal pressure of the gas generator is detected. A pressure sensor; and comparison control means for comparing the target value and the actual pressure detected by the pressure sensor and applying a signal corresponding to the difference as a drive signal to the flow rate adjustment means. Characteristic combustion pressure control device for gas generators for ram rockets. (2) Combustible gas injected from the injection nozzle of the gas generator and outside air introduced from the diffuser are mixed and combusted in the combustion chamber, and the gas flow rate of the injection nozzle is adjusted to variably control the combustion pressure of the gas generator. In such a device, the generator basic control means outputs a preset combustion pressure target value to the flow rate adjustment means until the internal pressure of the gas generator reaches a predetermined value after the gas generator is ignited; A flow rate adjustment means that adjusts the gas flow rate by changing the area, a pressure sensor that detects the internal pressure of the gas generator, and a signal corresponding to the difference between the target value and the actual pressure detected by the pressure sensor. mode switching means that switches the signal input to the flow rate adjustment means from the target value to the output of the comparison control means when the internal pressure of the gas generator reaches a predetermined value. A combustion pressure control device for a gas generator for a ram rocket, characterized by comprising: