JP3016904B2 - Gas flow controller for gas generator for ram rocket - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ram rocket that mixes combustible gas with introduced outside air and burns the mixture.
The present invention relates to a gas flow control device used for a gas generator as a supply source of the combustible gas.

[0002]

2. Description of the Related Art A ram rocket is disclosed in, for example,
It is described in p.655, page 10.4.2 of "Aerospace Engineering Handbook, supplemented edition of Japan Society of Aeronautics and Astronautics" published by Maruzen in March.

[0003] That is, the ram rocket has a gas generator and a combustion chamber from the head side, and has a diffuser on the side part that opens to 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.

[0004] The ram rocket starts by igniting the booster propellant, ignites the sustainer propellant when a predetermined speed is reached upon completion of the boost flight, and combusts the combustible gas generated by the combustion of the sustainer propellant. The air continues to fly by mixing with outside air introduced from the diffuser and continuously burning in the combustion chamber.

Here, in the above-described ram rocket, as shown in FIG. 3, a gas flow rate control device is provided at an injection nozzle 101 of a gas generator 100 to change the internal pressure of the gas generator 100 or the introduced air pressure. In some cases, the flow rate of the flammable gas is adjusted in response to stabilize combustion and the resulting thrust.

The gas generator 100 has a sustainer propellant 102 loaded therein and communicates with a combustion chamber 103 via the injection nozzle 101. The injection nozzle 101 has a throat portion 101b continuous with the convergent portion 101a, and the convergent portion 101a is provided with a drive shaft 104 penetrating in the diameter direction and a pintle 105 with the injection nozzle 101b.
And a holder for movably holding the holder in the axial direction.

The drive shaft 104 is provided at one end with a speed reduction mechanism 108 of a servomotor 107 provided outside the injection nozzle.
Are connected to each other, and a seal material 109 is interposed between the injection nozzle and the wall of the injection nozzle. The pintle 105 is
The conical tip portion extends to the throat portion 101b, and the base portion engages a spherical cam 110 having an eccentric position fixed to the drive shaft 104.

In the above gas flow control device, the pintle 105 is moved in the axial direction of the injection nozzle 101 via the spherical cam 110 as the drive shaft 104 is rotated around the axis by the servomotor 107. Thus, the flow area of the combustible gas is adjusted by changing the opening area of the throat portion 101b.

The above-mentioned gas flow control device is described in, for example, AGARD Lecture Series No. 136 "RAM
JET AND RAMROCKET PROPULSION ”(NAT
O published October 1984), pages 7-26, 27.

[0010]

However, in the above conventional gas flow control device, the sustainer propellant 1
The position of the pintle 105 is controlled to change the opening area of the throat portion 101b by a position command signal set in advance from the relationship of the combustion speed to combustion pressure characteristics and the combustion pressure to combustion area / nozzle throat area of No. 02. However, there is a problem that a control error occurs due to variations in characteristics of the sustainer propellant 102, temperature sensitivity, and the like, and there has been a problem in improving the accuracy of gas flow control.

[0011]

SUMMARY OF THE INVENTION An object of the present invention is to solve the above-mentioned conventional problems, and it is possible to improve the accuracy of gas flow control by feeding back the actual gas flow rate. It is an object of the present invention to provide a gas flow control device for a generator.

[0012]

SUMMARY OF THE INVENTION A gas flow controller for a gas generator for a ram rocket according to the present invention is designed to mix and combust flammable gas injected from an injection nozzle of a gas generator with outside air introduced from a diffuser. In the apparatus for adjusting the gas flow rate of the injection nozzle, generator basic control means for outputting a preset target value of the gas flow rate, flow rate adjustment means for adjusting the gas flow rate by changing the throat area of the injection nozzle, A pressure sensor for detecting the internal pressure of the generator, a temperature sensor for detecting the temperature of the gas in the gas generator, a value At of the throat area of the injection nozzle, detection values Pc and Tc of the pressure sensor and the temperature sensor , and a gas constant R And ratio
From the heat ratio γ , the actual gas flow rate Mf And a comparison control unit that compares the target value and the calculated value of the calculation unit and applies a signal corresponding to the difference to the flow rate adjustment unit as a driving unit. The above structure is used as means for solving the problem.

For the gas generator basic control means in the above configuration, for example, a function generator is used, and based on the relationship among the characteristics of the gas generating agent, the combustion area, the nozzle throat area, etc. The target value of the flow rate is set. In addition, for example, a pintle extending to the throat portion of the injection nozzle and a driving mechanism of the pintle are used as the flow rate adjusting means. In this case, the position detection signal of the pintle is supplied to the arithmetic unit as a value of the throat area. It is possible to

[0014]

In the gas flow control device for a ram rocket gas generator according to the present invention, when adjusting the gas flow rate by changing the throat area, the value of the throat area At , the values of the pressure and temperature in the gas generator P
Calculated from c, Tc, gas constant R and specific heat ratio γ by the above formula
By using a signal corresponding to the difference between the obtained actual gas flow rate Mf and the target value as a drive signal, the gas flow rate is feedback-controlled.

[0015]

1 and 2 are views for explaining one embodiment of the present invention. 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,
On the side, a plurality of diffusers 14 are provided. Also,
On the head side of the gas generator 1, a pintle 1
A second drive mechanism 17 is mounted, and a nose cone (not shown) for mounting equipment necessary for flying is connected to the head side of the drive mechanism 17.

The combustion chamber 4 is loaded with a solid booster propellant 30. Therefore, a clamp 32 is provided inside a ramjet nozzle 31 provided at the tail of the combustion chamber 4.
The rocket nozzle 33 is detachably incorporated by using a rocket, and an igniter 34 for igniting the booster propellant 30 is mounted inside the rocket nozzle 33.

The diffuser 14 opens toward the head of the ram rocket R and communicates with the combustion chamber 4 near the head. The opening into the combustion chamber 4 is closed by a boat cover 35. It is. A pyrotechnic 35a is attached to the surface of the port cover 35 on the diffuser 14 side. A storage section 36 is continuously provided on the tail side of the diffuser 14, and a port cover release device 37 for operating the pyrotechnic 35a is provided in the storage section 36.
Is stored.

As shown in FIG. 1, the gas generator 1 is provided with an injection nozzle 5 communicating with a combustion chamber 4 in a tank 3 loaded with a solid sustainer propellant 2 as a gas generating agent .
A pipe-shaped pintle case 6 extending toward the injection nozzle 5 inside the tank 3 is provided on a coaxial line.

The tank 3 is screwed to the head of a cylindrical member 7 constituting a main body part, and a front end plate member 8 having a base end of the pintle case 6 fixed at the center, and a tail portion of the cylindrical member 7. The rear end plate member 9 having the injection nozzle 5 formed at the center is screw-connected, 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 via the restrictor 10 over the length of the pintle case 6. By interposing a heat insulating material 11 between the pintle case 6 and the restrictor 10, the thermal protection performance for the pintle 12 inserted in the pintle case 6 is enhanced.

A pressure sensor 41 for detecting the pressure inside the gas generator 1 is provided on the rear end plate member 9.
In addition to the temperature sensor 42 for detecting the temperature of the gas and the gas, an igniter (not shown) for the sustainer propellant 2 is attached. The pressure sensor 41 and the temperature sensor 42
Are output to the arithmetic unit 43.

As the pressure sensor 41, a sensor using heat-resistant silicon grease or the like as a medium for transmitting pressure to the piezoelectric transducer is used. As the temperature sensor 42, a thermocouple or the like is used.

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

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 having the male thread 12 a is positioned outside the tank 3. In the vicinity of the base end, a seal ring 15 that slides on the inner surface of the pintle case 6 is mounted. A guide ring 16 is fixed to the distal end of the pintle case 6.
6 keeps the pintle 12 in a state where its axis coincides with the axis of the injection nozzle 5 and prevents flammable gas from entering between the pintle case 6 and the pintle 12. A drive mechanism 17 for reciprocating the pintle 12 in the axial direction is connected to the base end side of the pintle 12.

The drive mechanism 17 has a structure in which a ball screw 18 and a servomotor 19 are disposed on the same axis as the pintle 12. A first bracket 21 fixed to the front end plate member 8 includes a bearing 20. The screw shaft 18a of the ball screw 18 is attached through the like, and the servo motor 19 is fixed to a second bracket 22 fixed to the first bracket 21, and the screw shaft 18a and the output shaft 19a of the servo motor 19 are connected to each other. Are connected by a joint 23. The nut portion 18b of the ball screw 18 is attached to a nut holder 24. Then, the nut holder 24 and the pintle 12 are connected by screwing a nut 25 to the external thread portion 12 a of the pintle 12 penetrated through the nut holder 24. Thus, the drive mechanism 17 converts the rotational movement of the servo motor 19 into the linear movement of the nut holder 24 via the ball screw 18 and reciprocates the pintle 12 in the axial direction.

In order to detect the displacement of the pintle 12, a potentiometer 26 having an input shaft 26a fixed to a nut holder 24 is attached to the first bracket 21. The output signal of the potentiometer 26 is used to correspond to the value of the throat area determined by the displacement of the pintle 12, and is input to the calculator 43. In this embodiment, the pintle 12 and the above-described drive mechanism 17 constitute a flow rate adjusting means 44 for adjusting the gas flow rate by changing the throat area of the injection nozzle 5. Here, the reason why the drive mechanism 17 is located on the front side of the tank 3 is to minimize the influence of heat generated by the gas generated by the gas generator 1 and maintain its operation performance.

The computing unit 43 is provided with the pressure sensor 41 described above.
Of the actual gas flow rate M by the following equation, using the pressure detection value Pc obtained from the temperature sensor 42, the temperature detection value Tc obtained by the temperature sensor 42, and the throat area value At based on the signal of the potentiometer 26.
Calculate f.

[0028]

[Formula]

[0029]

Note that R is a gas constant and γ is a specific heat ratio.

The actual gas flow rate (Mf) is input to a servo amplifier 45 as comparison control means and compared with a target value from a function generator 46 as basic generator control means. This target value is set in advance as a gas flow rate with time based on the relationship between the combustion speed and the combustion pressure characteristic of the sustainer propellant 2 and the relationship between the combustion pressure and the combustion area / nozzle throat area. . The servo amplifier 45 compares the actual gas flow rate with the target value, and sets a signal corresponding to the difference as a drive signal as a drive signal.
To the servo motor 19 in FIG.

When the igniter 34 ignites the booster propellant 30, the ram rocket R equipped with the gas generator 1 blows off the igniter 34 and starts.
When the vehicle accelerates and reaches a predetermined speed with the end of the boost flight, the clamp 32 is released to release the rocket nozzle 3.
3 is disengaged and the port cover 35 is crushed by the operation of the pyrotechnic 35 by the port cover release device 37 to bring the diffuser 14 and the combustion chamber 4 into communication (the state shown in FIG. 1). Ignite 2.

Then, the combustible gas generated by the combustion of the sustainer propellant 2 and the outside air introduced from the diffuser 14 are mixed in the combustion chamber 4 and continuously burned. The flow rate control device compares the actual gas flow rate calculated based on the value of the nozzle throat area, the detected value of the pressure and the temperature in the gas generator 1 with the target value from the function generator 46, and corresponds to the difference. By driving the servo motor 19 as a drive signal and moving the pintle 12 in the axial direction via the ball screw 18 and the nut holder 24, the opening area of the throat portion of the injection nozzle 5 is changed to change the flammable gas. Adjust the flow rate.

By such feedback control of the gas flow rate, the ram rocket R keeps flying while controlling the combustion in the combustion chamber 4 and the thrust associated therewith.

[0035]

As described above, according to the gas flow rate control device for a ram rocket gas generator of the present invention, the injection
Nozzle throat area value, pressure sensor and temperature sensor
Since the actual gas flow rate is detected based on each detected value and feedback control is performed, for example, even if the characteristics of the gas generating agent vary, the control error is reduced, and the accuracy of the gas flow rate control is reduced. Can be significantly improved.

[Brief description of the drawings]

FIG. 1 is an explanatory diagram showing a gas flow control device according to an embodiment together with a cross section of a main part of a ram rocket.

FIG. 2 is a cross-sectional view illustrating the entire ram rocket.

FIG. 3 is a cross-sectional view illustrating a conventional gas flow control device.

[Explanation of symbols]

 R Ram rocket 1 Gas generator 5 Injection nozzle 12 Pintle 14 Diffuser 17 Driving mechanism 41 Pressure sensor 42 Temperature sensor 43 Computing unit 44 (12, 17) Flow rate adjusting means 45 Servo amplifier (comparison control means) 46 Function generator (Generator basic control) means).

────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Yasushi Watanabe Nissan Motor Co., Ltd., 2 Takaracho, Kanagawa-ku, Yokohama-shi, Kanagawa Prefecture (56) References JP-A-3-57868 (JP, A) JP-A-60 −243353 (JP, A) (58) Field surveyed (Int. Cl. ⁷ , DB name) F02K ^7/ 10-7/18

Claims (1)

(57) [Claims] When a combustible gas injected from an injection nozzle of a gas generator and outside air introduced from a diffuser are mixed and burned, a device for adjusting a gas flow rate of the injection nozzle is provided. Generator basic control means for outputting the target value, flow rate adjusting means for adjusting the gas flow rate by changing the throat area of the injection nozzle, pressure sensor for detecting the internal pressure of the gas generator, and detecting the temperature of the gas in the gas generator Temperature sensor, the value At of the throat area of the injection nozzle, the detection values Pc and Tc by the pressure sensor and the temperature sensor, and the gas constant R
And the actual heat flow rate Mf from the specific heat ratio γ And a comparison control unit that compares the target value and the calculated value of the arithmetic unit and applies a signal corresponding to the difference as a drive signal to the flow rate adjustment unit. Gas flow control means of a ram rocket gas generator.