JP3220858B2 - Supersonic intake for flying objects - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a supersonic
The present invention relates to a throat control method for a quick intake .

[0002]

2. Description of the Related Art Conventionally, a supersonic intake for changing an inlet shape has a variable mechanism such as an actuator 2 or a motor built in a supersonic ramp unit 1 as shown in FIG.
The variable lamp 3 was constituted. Since the configuration of the variable mechanism of the variable lamp 3 is complicated, it is necessary to maintain the driving accuracy of the movable unit and to pay attention so that no trouble occurs. Further, the variable mechanism of the variable lamp 3 has a large number of parts, is large, and is expensive.

[0003] A supersonic intake having such a variable ramp 3 is generally used for an aircraft, but it is difficult to use it for a flying object. That is, since the flying object is significantly smaller than the aircraft and the supersonic intake is correspondingly smaller, it becomes difficult to incorporate a variable mechanism such as the actuator 2 or the motor as in the related art. In addition, flying objects need to be lighter than aircraft, and the incorporation of a variable mechanism that increases weight must be avoided. Furthermore, the flying object is used only once, and the opening adjustment of the supersonic intake is performed only once,
Since continuous opening adjustment is unnecessary, a variable mechanism such as an actuator 2 or a motor having an expensive and complicated function is not suitable.

[0004]

Therefore, the present invention requires a small variable mechanism without using a variable mechanism such as an actuator or a motor , has a simple structure, has a small number of parts, and requires a special drive (power) source. Throat opening of supersonic intake with high accuracy using a lightweight, compact and low-cost variable mechanism
It was to carry out the adjustment of flight-body supersonic intake
It is intended to provide a throat control method .

[0005]

SUMMARY OF THE INVENTION To solve the above-mentioned problems, a throat control system for a supersonic intake for a flying object according to the present invention is provided.
One of the methods is to change the supersonic intake for the flying object.
A variable lamp mechanism is provided in the supersonic ramp section facing the cowl.
Swing the ramp in the continuous flow path and the flat plate inside the throat
Link mechanisms enabled and forward / reverse movement of each link mechanism
Memory alloy displaced by energization to produce
And a bias spring that generates a spring force.
The variable mechanism of the variable ramp is started by a bias spring before starting.
Stop at the movement start position and open the throat to a constant flow area
The vertical shock wave passes through the throat
Pressure or temperature is detected by a sensor installed near the throat.
The detection signal reaches a predetermined value in the control circuit.
After confirming the start by detecting the
Energize the metal alloy to shorten its length and resist the bias spring
Rotate each link mechanism, and inside the ramp and throat of the flow path
Set the flat plate at a specified angle and cut the throat
It is characterized in that the area is reduced.

[0006] The supersonic intake for a flying object of the present invention
Another one of the throat control methods is the aforementioned throat control method.
In the method, a total pressure pipe is provided outside the intake and the total pressure pipe is provided.
Control by sending the total pressure taken in from the control circuit
The circuit estimates the flying Mach number from the total pressure,
For each Mach number, the flow ramp and the flat inside the throat
The angle of the plate is set in advance so that it becomes the proper angle, and the shape
Equipped with a memory to change the amount of electricity to the memory alloy, start
After confirmation, the total pressure taken in from the total pressure pipe is skipped by the control circuit.
Estimate the Mach number and calculate the actual
Make sure that the angle of the ramp and the flat plate in the channel
The length by appropriately changing the amount of electricity to the shape memory alloy
And rotate the link mechanism to ramp and throat the flow path.
Set the inner flat plate at an appropriate angle and fly the throat
The feature is that the cross-sectional area of the flow channel is reduced to match the Mach number.
Is what you do.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the method for controlling the throat of a supersonic intake for a flying object according to the present invention will be described with reference to the drawings . First, a flight that implements this throat control method.
Explain the configuration of the supersonic intake for the vehicle
As shown in FIG. 1, the ramps 3a, 3b of the flow path facing the cowl 5 and connected to the supersonic ramp section 1 and the flat plate 3c inside the throat 4 cannot be rocked by the link mechanisms 6, 6 ', respectively. , The lamps 3 a and 3 b are variable lamps 3. The lamp 3a has its tip pivotally supported at the rear end of the supersonic ramp portion 1 as shown in FIG. 2, and the lamp 3b has an elongated hole 7 at its tip connected to the rear end side surface of the lamp 3a by a pin 8. ing. As shown in FIG. 3, the flat plate 3c has a long hole 7 at the rear end thereof connected to a front end of the inner wall 9 of the throat 4 by a pin 10. The upper end of the link mechanism 6 is shown in FIG.
As shown in FIG. 3, the upper end of the link mechanism 6 'is connected to the lower surface of the flat plate 3c as shown in FIG. 3, and the lower end of the link mechanism 6' is connected to the supports 11, 11 '. It is supported at 12 '. Rotary shaft 12, 12 '
The outer periphery of T has a lower end fixed to supports 11, 11 ', respectively.
A shape memory alloy strip 13 made of an i-Ni alloy and a bias spring 14 are passed over the connection. Each support 1
At both ends of the shape memory alloy strip 13 at 1 and 11 ′, an electric wire 16 for energization is connected from a control circuit 15 installed in the inner wall 9 of the throat 4. The control circuit 15
Is connected to a pressure sensor (or temperature sensor) 17 provided near the throat 4, and a pressure (or temperature) signal detected by the pressure sensor 17 is sent to the control circuit 15. When the (or temperature) signal reaches a predetermined value, it is detected that starting has occurred, and the control circuit 1
The variable mechanism 18 is configured so that the shape memory alloy 13 is energized by the electric wires 5 through 5. The lamps 3a, 3b may be connected by links 19, 20 instead of the slots 7 and the pins 8 as shown in FIG.

A method of controlling the throat in the supersonic intake for a flying object configured as described above will be described.
Since the lamps 3a, 3b and the flat plate 3c are not rocked before starting, current does not flow through the shape memory alloy strip 13 of the variable mechanism 18, and the link mechanisms 6, 6 'are moved by the spring force of the bias spring 14. As shown in FIG. 5, the motor stops at a predetermined starting position turned clockwise, the lamps 3a and 3b of the flow path and the flat plate 3c inside the throat 4 are lying down, and the throat 4 is in a constant flow path.
Open to cross section . When the start occurs and the vertical shock wave passes through the throat 4, the pressure is detected by the pressure sensor 17, and the control circuit 15 detects that the detection signal has reached a predetermined value, and the start is confirmed. conduct current to the shape memory alloy strip 13 of the adjustable-<br/> varying mechanism 18, the shape memory alloy strip 13 in the hot state to reduce the so long as shown in FIG. 6, the spring force of the bias spring 14 The link mechanisms 6 and 6 'are rotated to the left via the rotating shafts 12 and 12' to set the flow path ramps 3a and 3b and the flat plate 3c inside the throat 4 at a predetermined angle. Reduce to a predetermined channel cross-sectional area.

[0009] Next will be explained with reference to FIG. Another one embodiment of the flying-body supersonic intake throat control method of the present invention. First, a flight that implements this throat control method.
The configuration of the supersonic intake for the vehicle will be described.
In the supersonic intake for the flying object shown in FIG.
In the throat control method , the purpose of setting the ramps 3a, 3b of the flow path and the flat plate 3c inside the throat 4 at a predetermined angle is only for starting, but in the throat control method in the flying supersonic intake shown in FIG. , Not only starting, but also flying after starting ramp 3 according to the Mach number
Setting the angles of a, 3b and the flat plate 3c is also an important purpose. In a supersonic intake, a shock wave pattern appropriate for the flying Mach number exists. Oblique shock waves emanating from the lamp tip as shown in FIG. _{8 I 1, I 2, I} 3,
If the form shed I ₄ cowl lip 5a, flight Mach number is as shown if Figure 9 is lower than the design value,
When the flying Mach number is higher than the design value, it becomes as shown in FIG. 10, and the flow rate or the total pressure recovery rate (the ratio of the total pressure at the intake outlet to the total pressure of the inflow air) is higher than the characteristic value at the design Mach number. descend. Therefore, in order to obtain the optimum performance in the flight speed range, the ramps 3a, 3a,
It is necessary to adjust the angles of 3b and flat plate 3c. As the Mach number increases, the oblique shock wave tilts. Therefore, it is preferable to increase the angles of the lamps 3a, 3b and the flat plate 3c as the Mach number increases. For this purpose, the supersonic intake for a flying object shown in FIG. 7 has the same configuration as the supersonic intake for a flying object shown in FIG. 1, and a total pressure pipe 21 is provided outside the intake and taken in from the total pressure pipe 21. The total pressure is sent to the control circuit 15. The control circuit 15 estimates the flying Mach number from the total pressure and , for each Mach number, the inside of the ramps 3a, 3b and the throat 4 of the flow path. The angle of the flat plate 3c is set in advance so as to be an appropriate angle,
Memory 2 for changing the amount of electricity to shape memory alloy strip 13
2 Bei Eteiru. The mounting position of the total pressure pipe 21 is shown in FIG.
As shown in the figure, the surface of the cowl 5 or the outer surface of the side wall of the intake may be used.

[0010] describing such throat control method in constructed flying-body supersonic intake to about
Before the start and before the start, the operation is exactly the same as the throat control method of the above-mentioned supersonic intake for a flying object.
Thereafter, the flying Mach number is estimated by the control circuit 15 based on the total pressure taken from the total pressure pipe 21 provided outside the intake, and the flow path for each Mach number preset in the memory 22 provided in the control circuit 15 is determined. On the basis of the angles of the flat plates 3c inside the ramps 3a, 3b and the throat 4, the control circuit 15 controls the actual angles of the ramps 3a, 3b and the flat plate 3c with respect to the estimated flying Mach number.
By changing the amount of electricity to the shape memory alloy strip 13 by changing the temperature of the shape memory alloy strip 13 to make the length appropriate,
By rotating the link mechanisms 6, 6 ' , the ramps 3a, 3b and the flat plate 3c are set at an appropriate angle, and the throat is reduced to a cross-sectional area corresponding to the Mach number .

[0011]

As can be seen from the above description, the method for controlling the throat of a supersonic intake for a flying object according to the present invention does not use a large variable mechanism such as an actuator or a motor at the time of starting as in the prior art. With a small variable mechanism that operates by the displacement of the shape memory alloy and the spring force of the bias spring, the angle of the ramp in the flow path and the flat plate inside the throat can be adjusted appropriately, and the cross-sectional area of the throat flow path can be kept constant.
By estimating the number of flight Mach from the total pressure of the intake external to the proper lamp and the angle of the flat plate of the internal throat of suits flow path to the flight Mach number after startup, the
Make the throat a cross-sectional area that matches the Mach number of the flying object
Can be set. Therefore, the throat opening can be accurately adjusted.
Wear. In addition, the supersonic intake for a flying object of the present invention
The throat control method is simple in configuration, has a small number of parts, does not require a special drive (power) source, and uses a lightweight, compact and low-cost variable mechanism to adjust the throat opening.
Because there is very useful as a throat control method for a supersonic intake in flying object comprising a one-time use.

[Brief description of the drawings]

FIG. 1 is a schematic vertical sectional view showing a configuration of a supersonic intake for a flying object that implements one of the throat control methods of the present invention.

FIG. 2 is an enlarged view of a portion A in FIG.

FIG. 3 is an enlarged view of a portion B in FIG. 1;

FIG. 4 is a diagram showing an example of a partial modification of FIG. 2;

FIG. 5 is a longitudinal sectional view of an essential part showing a state before starting of the supersonic intake for a flying object of FIG. 1;

FIG. 6 is a vertical sectional view showing a main part of the supersonic intake for a flying object shown in FIG. 1 at the time of starting.

FIG. 7 is another embodiment of the throat control method of the present invention.
That is a schematic longitudinal sectional view showing the structure of a flying-body supersonic intake.

FIG. 8 is a diagram illustrating a generation form of oblique shock waves and vertical shock waves at a design Mach number in a supersonic intake.

FIG. 9 is a diagram showing a mode of generation of oblique shock waves and vertical shock waves when the Mach number is lower than a design Mach number in a supersonic intake.

FIG. 10 is a diagram showing a mode of generation of oblique shock waves and vertical shock waves when the Mach number is higher than a design Mach number in a supersonic intake.

FIG. 11 is a longitudinal sectional view of a main part showing a conventional supersonic intake.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Supersonic ramp part 3a, 3b Lamp of flow path 3c Flat plate inside throat 4 Throat 5 Cowl 6, 6 'Link mechanism 7 Slot 8 Pin 9 Inner wall of throat 10 Pin 11, 11' Support 12, 12 'Rotation Shaft 13 Shape memory alloy strip 14 Bias spring 15 Control circuit 16 Electric wire 17 Pressure sensor 18 Variable mechanism 19, 20 Link 21 Total pressure tube 22 Memory

────────────────────────────────────────────────── ─── Continuation of the front page (56) References JP-A-4-342695 (JP, A) JP-A-9-291850 (JP, A) JP-A-10-332728 (JP, A) (58) Field (Int.Cl. ⁷ , DB name) F42B 10/00 B64D 33/02 G05D 3/00

Claims (2)

(57) [Claims] A variable supersonic intake for a flying object.
The variable mechanism of the pump is connected to the supersonic ramp
The ramp in the flow path and the flat plate inside the throat can be swung.
Link mechanism and the operation of each link mechanism
Shape memory alloys displaced by energizing
And a bias spring generating a spring force.
The variable mechanism of the lamp is started by a bias spring before starting
Stop at the start position and open the throat to a constant flow area,
When the start occurs and the vertical shock wave passes through the throat,
Detects pressure or temperature with a sensor located near the funnel
That the detection signal has reached a predetermined value by the control circuit.
After detecting the start and confirming the start, the shape memory of the variable mechanism
The length is shortened by energizing the alloy.
By rotating the link mechanism, the ramp and throat
Set the flat plate at a specified angle and set the throat
A supersonic inn for a flying object characterized in that it is reduced to a product
Take throat control method. 2. A supersonic inn for a flying object according to claim 1.
In the take throat control method, outside the intake
A control circuit for providing a total pressure pipe and controlling a total pressure taken from the total pressure pipe
Control circuit and let the control circuit fly from the total pressure.
In addition to estimating the C number, the run
The angle of the flat plate inside the pump and throat will be the correct angle
To change the amount of electricity to the shape memory alloy.
After checking the start, take in the memory from the total pressure tube.
Fly the total pressure with the control circuit.
Angle of ramp and flat plate in actual flow path corresponding to Mach number
Change the amount of power to the shape memory alloy so that
To the appropriate length, and rotate the link mechanism to
Set the lamp and the flat plate inside the throat to the proper angle
And fly the throat.
Supersonic intension for flying objects, characterized in that
The method of controlling the throat of the work.