JP3016903B2 - 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 on page 655.10.4.3 of "Japanese Society of Aeronautics and Astronautics / Aerospace Engineering Handbook / Supplementary Plate" issued 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. 5, a gas flow rate control device is provided in 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 106 for holding the holder 106 so as to be movable 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, and a seal material 109 is interposed between the seal member 109 and the wall of the injection nozzle. The pintle 105 has a conical tip extending to the throat portion 101b, and has a base engaged with a spherical cam 110 having an eccentric position fixed to the drive shaft 104.

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

[0009]

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 of 02 and the combustion pressure to combustion area / nozzle throat area. Therefore, there is a problem that a control error occurs due to variation in characteristics of the sustainer propellant 102, temperature sensitivity, and the like. Further, by detecting the actual pressure in the gas generator and performing feedback control, it is possible to increase the accuracy of the gas flow rate control. However, as shown in FIG. 4, the combustion pressure (P _C ) to the combustion area / The relationship of the nozzle throat area (K _N ) has nonlinear characteristics, and the combustion system gain (K _b ) is significantly different between the low-pressure side and the high-pressure side, and the control accuracy and stability are highly pressure-dependent. since the temperature (T _G1 ~T _G3) the characteristics of the P _C ~K _N changes significantly, there is a disadvantage that it may be difficult to maintain high accuracy, problems in achieving the accuracy of the gas flow control was there.

[0010]

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned conventional problems .
Adjust gas flow rate by changing throat area of injection nozzle
In the control system of the means to perform, by feeding back the actual gas flow rate and automatically adjusting the loop gain of the control system, a gas flow control device of a ram rocket gas generator that can always perform high-precision gas flow control It is intended to provide.

[0011]

According to the present invention, there is provided a gas flow control device for a ram rocket gas generator.
Combustible gas is generated by combustion of solid gas generant in the generator.
When the combustible gas injected from the injection nozzle of the gas generator and the outside air introduced from the diffuser are mixed and burned, the gas flow rate of the injection nozzle is adjusted. Generator basic control means for outputting the target value of the above, flow rate adjusting 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 gas generator, and the temperature of the gas in the gas generator. A temperature sensor to detect, a throat area value of the injection nozzle, an arithmetic unit for calculating an actual gas flow rate from each detection value by the pressure sensor and the temperature sensor, and comparing the target value with a calculated value of the arithmetic unit. Comparison control means for giving a signal corresponding to the difference as a drive signal to the flow rate adjusting means, the pressure sensor and the temperature sensor. Combustion of the gas generating agent of each detected value of
The ratio of the area to the throat area of the injection nozzle, pressure and temperature are processed in a map and gain scheduling data is given to the comparison control means to control the flow rate adjustment means.
A gain controller for automatically adjusting the loop gain of the control system is provided, and the above configuration is used as means for solving the problem.

For example, a function generator is used as the gas generator basic control means in the above-described configuration, and the function generator responds to the passage of time based on the relationship between the characteristics of the gas generating agent, the combustion area, the nozzle throat area, and the like. The target value of the gas 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 Further, the gain controller includes:
A map of combustion pressure to combustion area / nozzle throat area and combustion temperature is preset.

[0013]

According to the gas flow control device for a gas generator for a ram rocket according to the present invention, the gas generator
When adjusting the gas flow rate by changing the throat area of the injection nozzle, a signal corresponding to the difference between the actual gas flow rate obtained from the throat area value, the pressure and temperature values in the gas generator, and the target value is driven. The signal makes the flow
The gas flow rate is feedback-controlled in the control system of the amount adjusting means, and the pressure and temperature values in the gas generator are controlled by the combustion area of the gas generating agent and the throat surface of the injection nozzle.
Processing is performed using a product ratio, pressure, and temperature map, and the loop scheduling gain of the control system of the flow rate adjusting means is automatically adjusted using gain scheduling data obtained thereby.

[0014]

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 port 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 includes an injection nozzle 5 communicating with a combustion chamber 4 in a tank 3 loaded with a sustainer propellant 2 which is a solid 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 has a head end of a cylindrical member 7 constituting a main body portion, and a front end plate member 8 having a base end fixed to the center of the pintle case 6 screwed to the center thereof, 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, one using heat-resistant silicon grease or the like as a medium for transmitting pressure to the piezoelectric transducer is used, and as the temperature sensor 42, a thermocouple or the like is used.

The tank 3 has a tail portion of a rear end plate member 9 screwed to a connecting portion 4a opening to 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 slidingly in contact with the inner surface of the pintle case 6 is fitted. Also, at the tip of the pintle case 6,
A guide ring 16 is fixed, and the guide ring 16 keeps the pintle 12 in a state where its axis coincides with the axis of the injection nozzle 5, and flammable gas enters between the pintle case 6 and the pintle 12. To prevent 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 configuration 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 the 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. Are connected by a joint 23. The nut portion 18b of the ball screw 18 is attached to a nut holder 24. The pintle 12 penetrated through the nut holder 24
By screwing the nut 25 to the male screw portion 12a,
The nut holder 24 and the pintle 12 are connected. As a result, 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.
Using pressure detection value P _C, the temperature values detected by the temperature sensor 42 T _C, and the value A _t of the throat area based on the signal of the potentiometer 26 by the actual gas flow rate M using the following equation
Calculate f.

[0027]

(Equation 1)

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 generator basic 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. Furthermore, each signal from the pressure sensor 41 and the temperature sensor 42 is also input to the gain controller 47. The gain controller 47 has a combustion area / nozzle throat area (K _N )
A map of pressure (P _C ) and combustion temperature (T _G ) is set in advance, and the pressure and temperature values are processed using this map to implement a pressure-based gain schedule input to the servo amplifier 45. .

When the igniter 34 ignites the booster propellant 30, the ram rocket R equipped with the gas generator 1 blows off the igniter 34 to start the vehicle.
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, the port cover 35 is crushed by the operation of the pyrotechnic 35a by the port cover releasing device 37, and the diffuser 14 and the combustion chamber 4 are brought into communication (the state shown in FIG. 1). Ignite.

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.

The gain controller 47 processes the detected values of the pressure and temperature in the gas generator 1 using the above-described map, and converts a signal obtained thereby into gain scheduling data as shown in FIG.
5 is given. That is, as described in the related art section, the relationship between the combustion pressure (P _C ) and the combustion area / nozzle throat area (K _N ) has a non-linear characteristic (see FIG. 4).
Moreover greatly varies braking <br/> control system loop gain of the flow rate adjusting means 44 by the change in the characteristic change and combustion system gain with temperature _{(T G1 ~T G3)} of the gas (K _b), the intact input of the driving signal Since an error occurs in the flow rate according to the value, the flow rate adjustment is performed based on the data from the gain controller
Automatically adjusts the loop gain of the control system of the adjusting means 44 ,
As a result, the loop gain is kept constant.
Thereby, the pressure dependency of the control characteristics and the temperature dependency of the characteristics of the sustainer propellant 2 are eliminated, and high-precision controllability is always ensured.

Thus, the control system of the flow rate adjusting means 44
The ram rocket R continues to fly while the combustion in the combustion chamber 4 and the thrust associated therewith are controlled by performing feedback control of the actual gas flow rate while automatically adjusting the loop gain.

[0034]

As evident from the foregoing description, according to the gas flow controller ram rocket gas generator of the present invention, the gas
Changing the throat area of the generator injection nozzle
The value of throat area and gas
With a feedback control by detecting the actual gas flow from the pressure and temperature in the scan generator, the pressure sensor
The values detected by the temperature sensor and the temperature sensor are
And the throat area ratio of the spray nozzle and the pressure and temperature
Gain obtained by processing with
Since the loop gain of the control system of the flow rate adjusting means is automatically adjusted based on the data, stable and accurate gas flow rate control can always be performed.

[Brief description of the drawings]

FIG. 1 is an explanatory diagram showing a gas flow control device according to an embodiment of the present invention, 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 graph showing the relationship between combustion pressure and gain for different temperatures.

FIG. 4 is a graph showing the relationship between combustion area / nozzle throat area and combustion pressure at different temperatures.

FIG. 5 is a cross-sectional view illustrating a conventional gas flow control device.

[Explanation of symbols]

R Ram rocket 1 Gas generator 2 Sustainer propellant (gas generating agent) 5 Injection nozzle 12 Pintle 14 Diffuser 17 Driving mechanism 41 Pressure sensor 42 Temperature sensor 43 Computing unit 44 (12, 17) Flow control unit 45 Servo amplifier (Comparison control unit) ) 46 Function generator (Generator basic control means) 47 Gain controller

────────────────────────────────────────────────── ─── 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] 1. A gas generating agent which is solid in a gas generator.
When a combustible gas is generated by the combustion of the gas generator and the combustible gas injected from the injection nozzle of the gas generator and the outside air introduced from the diffuser are mixed and burned, a device for adjusting the gas flow rate of the injection nozzle is used in advance. Generator basic control means for outputting a set value of the gas flow rate, flow rate adjusting 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 gas generator, and the inside of the gas generator. A temperature sensor that detects the temperature of the gas, a computing unit that computes an actual gas flow rate from the value of the throat area of the injection nozzle, and values detected by the pressure sensor and the temperature sensor, and the target value and the computed value of the computing device. Comparing control means for comparing the flow rate adjusting means with a signal corresponding to the difference as a drive signal, Gas each detected value by the pressure sensor and a temperature sensor
The ratio of the combustion area of the generator and the throat area of the injection nozzle, the pressure and the temperature are processed by a map, and the comparison control means is provided with the gain scheduling data to obtain the flow rate.
A gain controller for automatically adjusting a loop gain of a control system of an adjusting means; and a gas flow control device for a gas generator for a ram rocket.