JP2001193564A - Control method and control device for ramjet engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a control method and control device for ramjet engine capable of controlling not to generating nonstarting when an operating state is unstable. SOLUTION: This control method and control device calculate a position of shock wave S at an intake for calculating a variation in the calculated position of shock wave S from a fixed position to control a ramjet engine J by adjusting angle of a variable exhaust nozzle N such that the variation is cancelled. When the variation (f) in the calculated position of shock wave S exceeds a predetermined range, the fixed position is moved to a direction such that nonstarting will hardly occur.

Description

Description: TECHNICAL FIELD The present invention relates to a ramjet engine.
And a control device for controlling Learn more
Indicates the position of the shock wave at the intake inside the engine.
Ramje to control to a predetermined position according to the state of fluctuation of state quantity
The present invention relates to a control method and a control device for a cut engine. [0002] Conventionally, a ramjet engine has been controlled.
Occurs inside and outside the engine as a method or control device
The position of the shock wave generated in the intake regardless of disturbance
Or control the engine pressure to be constant.
Are known (for example, see Japanese Patent Application Laid-Open No. 10-3112).
No. 45, Japanese Patent Application Laid-Open No. 10-311773 and
See JP-A-9-203348). That is, a ramjet engine is a flying object
High efficiency in the speed range where Mach speed exceeds Mach 2
You. However, although operating stability is not always good,
Suddenly operating the aircraft or engine
If the operating conditions inside and outside the engine change,
Shock wave generated at the air intake
Sometimes unstarted, which is discharged to the outside
You. When this unstart occurs, most of the time the engine
Is misfired and the engine thrust changes greatly,
The line state becomes unstable. [0004] Therefore, in order not to cause un-start,
Even if some disturbance occurs inside or outside the gin, it will start inside the intake
A method to control the generated shock wave to be kept at a fixed position
Have been proposed (see the above-mentioned prior arts). However, according to recent studies, it has been found that the engine
The pressure fluctuates drastically depending on the combustion state in the engine, and as a result
The position of the shock wave generated in the intake is also intense at high frequencies
Fluctuating phenomenon has been confirmed (for example, Experime
ntal Approach to the HYPRMarch 5 Ramjet Propulsion
 System, 34th AIAA / ASME / SAE / ASEE Joint Conference
& Exhibit). In this regard, the conventional shock wave level
The position control method is controlled to keep the average shock wave position constant.
Control of the actuator.
Complete suppression of high frequency vibration at the shock wave position
Can not. Therefore, in each of the above prior arts,
The deviation also increases the amplitude of this high-frequency vibration,
Avoid the situation when it is more likely to happen
There is a problem that is difficult. [0006] The present invention relates to such a conventional technique.
The operation state is uneasy due to the problem of surgery
Control to prevent un-starting when it becomes constant
Ramjet engine control method and control device
The purpose is to provide a device. SUMMARY OF THE INVENTION A ramjet device according to the present invention is provided.
The engine control method determines the shock wave at the intake
A ramjet engine control method that controls the position
Move the predetermined position according to the fluctuation of the shock wave position.
It is characterized by that. [0008] The control of the ramjet engine of the present invention.
The control method is to control the shock wave at the intake to a predetermined position
Ramjet engine control method,
It is difficult for non-start to occur depending on the fluctuation state of the shock wave position
It is preferable to move in the direction. More specifically, the ramjet jet of the present invention
The engine control method depends on the position of the shock wave in the intake.
And the predetermined position of the calculated shock wave position
A procedure for calculating the deviation from
Adjusting the angle of the variable exhaust nozzle
A control method of the jet engine, wherein the calculated impact
When the fluctuation amount of the position of the strike wave exceeds a predetermined range, the predetermined
The feature is to move the position in the direction in which unstarting is unlikely to occur.
I do. Here, the position of the shock wave is, for example,
It is calculated based on the pressure distribution inside the block. On the other hand, the control of the ramjet engine of the present invention
The control device includes a shock wave position calculation unit and an exhaust nozzle control unit.
Wherein the shock wave position calculating means includes an impact of the intake.
Calculating the wave position, the exhaust nozzle control means calculates
Of the shock wave position from the specified position
Ram to adjust the angle of the variable exhaust nozzle to eliminate
A control device for a jet engine, wherein the calculated value is
When the fluctuation amount of the shock wave position exceeds a predetermined range, the predetermined
The feature is to move the position in the direction in which unstarting is unlikely to occur.
I do. Here, the shock wave position calculating means includes an intake
The position of the shock wave is calculated based on the pressure distribution inside the shock. The control method of the ramjet engine of the present invention and
According to the control and control equipment, sudden operation of the aircraft or engine
The operating state inside and outside the engine changes due to
When the shock wave position fluctuates greatly within the
Move the target position of the shock wave to the downstream side of the intake
This makes it difficult to cause a start-up. That
To stabilize the operating state of the ramjet engine
be able to. BRIEF DESCRIPTION OF THE DRAWINGS FIG.
The present invention will be described based on an embodiment, but the present invention
It is not limited only to the embodiment. Control method of ramjet engine J of the present invention
FIG. 1 shows a block diagram of a control device C used in the method,
The control device C includes a pressure measurement unit 10 and a control device main body 20.
To drive the nozzle flap F of the variable exhaust nozzle N
And a slip flap driving device 30 as a main component.
It is assumed to be. In FIG. 1, reference numeral 11 denotes a pressure cell.
Sensor, symbol I is intake, symbol I_TIs an intake slot
R, ram combustor, and S, shock wave
Show. As shown in FIG. 2, the pressure measuring unit 10
The required number of pressure sensors 11 are placed at a predetermined distance on the side wall of intake I.
It is assumed to be arranged in. The control device main body 20 includes the pressure measuring unit 10.
Based on the pressure distribution in intake I detected by
A shock wave position estimating unit 21 for estimating the position of the shock wave S;
Of the estimated shock wave position from the target position
Then, the operation angle of the variable exhaust nozzle N is calculated, and this calculated value is
Shock wave position control instructed to the nozzle flap drive device 30
Calculating the fluctuation amount f of the estimated shock wave position
Shock wave position fluctuation calculating unit 23 and the calculated fluctuation
Change the shock wave target position when the amount f exceeds the specified range
And a shock wave position fluctuation control unit 24
You. For example, the position of the shock wave S is on the ram combustor R side.
, The shock wave position controller 22 sets the deviation to a positive value.
And the angle calculated from the deviation of the variable exhaust nozzle N
Command to close the ram combustor R to increase the pressure.
Let Conversely, intake throat I_TA place shifted to the side
The shock wave position control unit 22 detects the deviation as a negative value
Then, the variable exhaust nozzle N is opened by an angle calculated from the deviation.
Command to lower the pressure in the ram combustor R
Try to zero. Further, the variation amount σ of the position of the shock wave S
If exceeds the predetermined range, the shock wave position variation control unit 24
The target position of the shock wave S in the intake I is set to the ram combustor R side.
To the shock wave position control unit 22 to move the
I do. The position of the shock wave S is controlled by the intake
I will provide a bypass flow path and adjust the bypass amount
It may be done like this. Thus, the control device body 20 is
In general, a program for executing the above functions on a computer.
The ram is stored. In addition, this control device book
In order to run the ramjet engine J on the body 20,
Programs such as fuel flow control programs
Stored. The nozzle flap driving device 30 is, for example,
Actuator and link driven by this actuator
Mechanism, and responds to the angle specified by the control device body 20.
The link mechanism is operated by the actuator
The angle of the variable exhaust nozzle N (more specifically, the nozzle exhaust
The angle of the lap F) is adjusted to a predetermined value. Next, based on the pressure detected by the pressure measuring unit 10,
An example of a method for calculating the position of the shock wave S by using
You. The method of calculating the position of the shock wave S
In ku I, the pressure drops before the shock wave S,
Utilizing the phenomenon that the pressure increases after the shock wave S
And a control device based on the measurement value from the pressure measurement unit 10.
Detects the minimum pressure of the pressure measuring unit 10 in the main body 20
Sensor 11_LSensor 11 before and after_B, 11_APressure and
By each differential pressure with the minimum pressure, the sensor 11_LBefore and after
Calculating the position of the shock wave S by proportionally distributing between 1/2
It is. For example, a cell arranged on the side wall of intake I
The pressure measurement results shown in Fig. 3 are obtained by the sensor group.
If this is the case, the control device body 20 determines that the position of the shock wave S is
Low pressure (P in the example shown)_Three) Sensor (example shown)
Then K_Three) Position (in the example shown, X _Three)
Set. In other words, the position of the shock wave is determined by X₀Toss
Then, X_Three± X₀/ 2 range. And
This ± X₀Sensor 1 in which the minimum pressure is detected in the range of / 2
1_LBefore and after (K in the example shown)_Two, K_Four) Measuring pressure
(In the example shown, P_Two, P_Four) And sensor K_ThreeMeasurement pressure P_ThreeWith
Calculate the position X of the shock wave S by proportional distribution using the differential pressure
You. This can be expressed by the following equation (1). X = X_Three-X₀/ 2 + X₀* A / (A + B) (1) where A = P_Two−P_Three B = P_Four−P_{Three [ 0025 ]} In another embodiment of the present invention, a shock wave
Techniques for evaluating the variation level of the position of S include variance and actual
It is also possible to use methods such as effective value, peak-to-peak, etc.
You. In addition, the position of the shock wave is controlled using the engine pressure.
In the system, the target position of the shock wave S depends on the amount of pressure fluctuation.
The position may be changed. Next, the present invention will be described in detail with reference to examples.
You. Example and Comparative Example A test apparatus T shown in FIG.
In the case where the fuel supply amount is changed in
According to the control logic of FIG. 5 which shows the method more specifically
The position of the shock wave S when the angle of the variable exhaust nozzle N is adjusted
6 and FIG.
FIG. Note that in FIG._DIs a dummy intake
Is shown. That is, in the control logic 50 of FIG.
The shock wave position detection logic 51 uses the shock wave
The strike wave position Y is detected at a predetermined cycle, and the shock wave position Y is detected.
And a shock wave target preset as an engine design point
The difference value ΔX from the position X is determined by the shock wave position controller 5
2 is input. The shock wave position controller 52 includes:
The nozzle of the variable exhaust nozzle N so that the difference value ΔX becomes 0
Manipulate the corner. As a result, the internal pressure of intake I changes
Then, the position of the shock wave S in the intake I moves. Further, the standard deviation calculation logic 53 detects the impact
Shock wave position Y detected by wave position detection logic 51
Is calculated. The calculated standard deviation σ and
Preset standard deviation threshold σ_SIs the difference value Δσ
It is input to the shock wave fluctuation width controller 54. here
If the difference value Δσ is equal to or greater than a predetermined value,
A correction signal for correcting the target position X is output.
The shock wave target position X is corrected. Therefore, the fuel is supplied to the ram combustor 55.
The change Q is added, and as a result, the shock wave position Y becomes large at a high frequency.
When it starts to fluctuate, the shock wave fluctuation width control
The shock wave target position X is corrected by the control of the roller 54.
You. FIG. 6 shows a standard in the control logic of FIG.
Deviation threshold σ_SIs a large value (8 or more in the example shown)
, That is, an increase in the fluctuation amount σ of the shock wave position Y
Experimental results when the shock wave target position X is not corrected regardless of the size
It is a graph which shows a result (comparative example). That is, the test apparatus T includes the main 1 and
Fuel is supplied via two main fuel supply paths of main 2
You. Time t₀From time t₁Until, constant only from main 1
A quantity of fuel is supplied. Time t₁From the main 2
Fuel supply is started. This fuel change Q causes an impact
The wave position Y starts to fluctuate violently. At this time, the nozzle angle
The average value of the strike wave position Y is the shock wave target position X (in the illustrated example,
(Position about 10 mm from the intake opening)
It is operated at such an angle. Therefore, in the example of FIG.
Thereafter, the average value of the shock wave position Y matches the shock wave target position X.
While the standard deviation σ of the shock wave position increases
Left unattended. Therefore, in this state the shock wave
S may be discharged to the outside of the engine, causing unstart.
Performance is improved. FIG. 7 shows the standard deviation threshold value σ._SCause a non-start
Set to an appropriate value (about 3 in the example shown)
An example is shown (Example). That is, the fuel change Q
And the shock wave position Y fluctuates greatly at time t_SShock
If the standard deviation σ of the wave position Y exceeds 3, the target shock wave position
X is corrected, and a shock is applied to the corrected target shock wave position X.
The nozzle angle is adjusted so that the wave position Y matches. this
As a result, the shock wave position Y is a position where unstarting is unlikely to occur (illustrated in FIG.
In the example, a position about 30 mm from the intake opening)
As it moves, the standard deviation σ also decreases. In addition, this
In the state of, the shock wave position deviates from the design point,
When the position Y moves downstream from the opening of the intake I,
In addition, since the fluctuation width of the shock wave position Y becomes small,
Is less likely to occur. As described above, in this embodiment, the shock wave position Y
The target position X of the shock wave S is
To the downstream side of intake I, resulting in non-start
Ram jets even if the fuel supply changes
A stable operation is ensured in the engine J. Further, the set value of the standard deviation threshold value σ is increased.
Just set it to an appropriate value, regardless of the fluctuation of the shock wave position Y.
To return to the conventional control that keeps the target position X at the design point
Is also possible. The present invention has been described based on the embodiments and examples.
The present invention has been described with reference to such an embodiment and
The present invention is not limited to the embodiments, and various modifications are possible.
You. For example, calculation of shock wave position is limited to the method described above.
However, other methods can be used. An example
For example, pressure measurements around the minimum pressure
A descending straight line and an ascending straight line approximating that part with a constant value
Create and calculate the intersection of both straight lines as the position of the shock wave.
You may do it. In addition, flight speed, flight altitude, flight attitude
Variable intake when there are changes in flight conditions such as
Intake, and the invention with its variable intake
They may be combined. As described in detail above, according to the present invention,
When controlling the shock wave at the intake at a predetermined position
Then, the predetermined position is moved according to the fluctuation state of the shock wave position.
Therefore, a ramjet engine
In the operating state, avoid the occurrence of
The operating state of the cut engine can be easily stabilized.
Wear. This allows ramjets to be used in supersonic aircraft, etc.
Stability when the engine is installed
An excellent effect is obtained.

[Brief description of the drawings]

FIG. 1 is a block diagram of a control device applied to a control method of a ramjet engine of the present invention.

FIG. 2 is a schematic diagram of a pressure measurement unit used in the control device.

FIG. 3 is a graph showing an example of a pressure distribution inside an intake detected by a pressure sensor of the pressure measuring unit.

FIG. 4 is a schematic view of a test apparatus used in Examples and Comparative Examples.

FIG. 5 is a control block diagram illustrating a control method of a ramjet engine according to the present invention.

FIG. 6 is a graph of a measurement result in a comparative example.

FIG. 7 is a graph of a measurement result in the example.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 10 Pressure measurement part 11 Pressure sensor 20 Control device main body 21 Shock wave position estimation part 22 Shock wave position control part 23 Shock wave position fluctuation calculation part 24 Shock wave position fluctuation control part 30 Nozzle flap drive device 50 Control logic C control device J Ramjet engine I Intake I _D dummy intake I _T intake throat R ram combustor N variable exhaust nozzle F nozzle flaps T test device

 ──────────────────────────────────────────────────続 き Continuing from the front page (72) Katsuhiro Kobe 1-1, Kawasaki-cho, Akashi-shi Kawasaki Heavy Industries, Ltd. Inside the Akashi Plant (72) Inventor Takao Oshima 1-1-1, Kawasaki-cho, Akashi-shi Kawasaki Heavy Industries, Ltd. Inside the Akashi Factory (72) Inventor Makoto Utano 1-1, Kawasaki-cho, Akashi-shi Kawashige Techno Services Co., Ltd. Akashi Works

Claims (9)

[Claims] 1. A method for controlling a ramjet engine for controlling a shock wave in an intake to a predetermined position, wherein the predetermined position is moved according to a fluctuation state of the shock wave position. 2. A method for controlling a ramjet engine for controlling a shock wave at an intake to a predetermined position, wherein the predetermined position is moved in a direction in which unstarting is unlikely to occur in accordance with a fluctuation state of the shock wave position. Ramjet engine control method. 3. A step of calculating a position of a shock wave in an intake, a step of calculating a deviation of a calculated position of the shock wave from a predetermined position, and a step of adjusting an angle of a variable exhaust nozzle so as to eliminate the deviation. A control method for a ramjet engine, comprising: moving the predetermined position in a direction in which non-starting is unlikely to occur when the calculated amount of change in the position of the shock wave exceeds a predetermined range. Ramjet engine control method. 4. The ramjet engine control method according to claim 3, wherein the position of the shock wave is calculated based on a pressure distribution inside the intake. 5. A shock wave position calculating means, and an exhaust nozzle control means, wherein the shock wave position calculating means calculates a shock wave position of an intake, and the exhaust nozzle control means calculates a position of the calculated shock wave position from a predetermined position. A ramjet engine control device that calculates a shift and adjusts the angle of a variable exhaust nozzle to eliminate the shift, wherein the calculated shock wave position variation exceeds a predetermined range, A ramjet engine control device for moving a position in a direction in which non-starting is unlikely to occur. 6. The control device for a ramjet engine according to claim 5, wherein said shock wave position calculating means calculates a position of the shock wave based on a pressure distribution inside the intake. 7. A ramjet engine comprising the ramjet engine control device according to claim 5. 8. A flying object comprising the ramjet engine according to claim 7. 9. A test body comprising the control device for a ramjet engine according to claim 5 or 6.