JP6357997B2 - Injection test equipment - Google Patents

Description

  The present invention relates to an injection test apparatus.

For example, devices that are exposed to combustion gas from a rocket motor, such as an engine that sucks combustion gas injected from a flying object equipped with a rocket motor launched from an aircraft, or a launch pad that receives combustion gas from a rocket May change its characteristics when exposed to high-temperature combustion gas.
Then, in order to obtain a change in the characteristics of the device exposed to the combustion gas, an experiment may be performed in which the device is exposed to the combustion gas of the rocket motor on the ground (see Non-Patent Document 1).
Such an experiment is performed, for example, by fixing the rocket motor so as not to move, and igniting the rocket motor in a state where a device for obtaining a characteristic change is disposed in the subsequent stage.

However, as can be seen from the above example, when the rocket motor is actually ignited, the rocket motor moves away from the target to which the combustion gas is injected by its propulsive force. In experiments conducted on the ground, since the rocket motor is fixed, the rocket motor does not move away from the object. For this reason, the device to be tested is exposed to the combustion gas for a longer time than in reality, and it is difficult to obtain an accurate characteristic change.
A rocket motor has a characteristic that once it is ignited, it continues to burn until the fuel is used up. For this reason, generation | occurrence | production of combustion gas cannot be stopped before combustion burns out.

  For this reason, in the conventional injection test on the ground, by using an injection test apparatus equipped with a drop-type shutter, the shutter is dropped and the combustion gas injection path is blocked after a lapse of a certain time from the start of combustion of the rocket motor. A method of forcibly stopping the injection of combustion gas to the test object is employed.

Thomas Breuer, Oliver Mertschat, Dr. Andreas Zeisberger, MTU Aero Engines GmbH, Dachauer Str. 665, D-80995 Munchen, Germany, `` Missile Firing simulation-hot gas ingestion experiments in engine bench testing '', ISABE-2005-1133

  By the way, for example, when considering an engine that is exposed to the combustion gas of a rocket motor mounted on a flying object launched from an aircraft, the rocket motor is generally more than the intake port of the engine after the flying object is launched. Ignite on the downstream side. For this reason, the engine is not exposed to the combustion gas immediately after ignition, but is exposed to the combustion gas after a certain time has elapsed since ignition.

In the above-described injection test apparatus, it is impossible to prevent the combustion gas immediately after ignition from reaching the apparatus to be tested, and it is possible to inject the combustion gas to the test object at an arbitrary timing and for an arbitrary period. Can not.
For this reason, in the conventional injection test on the ground, the actual injection environment may not be sufficiently simulated.

  The present invention has been made in view of the above-described problems, and is an injection test apparatus used in an injection test for injecting combustion gas from a rocket motor onto a test object, and is injected into an injection object. An object is to make it possible to adjust the injection state of the combustion gas with a higher degree of freedom and to reproduce the actual injection environment.

  The present invention adopts the following configuration as means for solving the above-described problems.

  1st invention is an apparatus for injection tests which controls the injection state with respect to the injection target object of the combustion gas injected from the rocket motor, Comprising: It arrange | positions in the middle of the injection path | route of the said combustion gas, and lets the said combustion gas pass through A shielding member having a passage region in part; a driving means for moving the shielding member along a path through which the passage region passes through the injection path of the combustion gas; and the passage region of the shielding member by controlling the driving means Comprises a control means for adjusting the timing of passing through the combustion gas injection path.

  According to a second invention, in the first invention, the shield member is a rotary plate that is driven to rotate about a rotation axis along the injection path and has an opening that serves as the passage region. To do.

According to a third aspect of the present invention, in the second aspect of the invention, the shielding member including the rotating plate is provided with two sheets.
The control means employs a configuration in which the rotation directions of the two rotating plates are reversed and the openings of the two rotating plates are overlapped in the ejection path.

  According to a fourth aspect of the present invention, in the second or third aspect of the present invention, a configuration is employed in which a path closing member that is provided separately from the shielding member and that blocks the combustion gas injection path is provided.

  According to a fifth aspect of the present invention, in the fourth aspect of the present invention, the path closing member is disposed downstream of the shielding member in the combustion gas flow direction.

  According to a sixth invention, in any one of the first to fifth inventions, the chamber surrounding at least the shielding member and the rocket motor except for the combustion gas injection path, and the combustion gas filled in the chamber are the A configuration is adopted in which an exhaust passage for exhausting the combustion gas injection path to the outside of the chamber is provided.

According to the present invention, the shielding member partially provided with the combustion gas passage region is moved by the driving means, and the driving means is further controlled by the control means.
For this reason, it becomes possible to control the movement (for example, movement speed and movement timing) of a shielding member, and the timing and period when the passage area of a shielding member overlaps with the combustion gas injection path | route can be set arbitrarily.
Therefore, according to the present invention, there is provided an injection test apparatus for use in an injection test for injecting combustion gas from a rocket motor onto a test object, and the injection state of the combustion gas injected into the injection object is more free. The degree can be adjusted to be high, and the actual injection environment can be reproduced more.

It is sectional drawing which shows schematic structure of the apparatus for injection tests in one Embodiment of this invention. It is the arrow line view which looked at the 1st rotation board and 2nd rotation board with which the apparatus for injection tests in one Embodiment of this invention is provided from the rotating shaft direction. It is the perspective view which showed typically a part of apparatus for injection test in one Embodiment of this invention. It is a disassembled perspective view of the apparatus for injection tests in one Embodiment of this invention shown in FIG. It is a block diagram which shows the electrical connection of the apparatus for injection tests in one Embodiment of this invention. It is a timing chart for demonstrating operation | movement of the apparatus for injection tests in one Embodiment of this invention. It is an operation | movement figure which shows the relationship between the 1st rotation board and 2nd rotation board, and injection opening for demonstrating operation | movement of the apparatus for injection test in one Embodiment of this invention. It is a schematic diagram illustrated about the various cases about the both ends in the rotation direction of the opening with which the apparatus for injection tests in one Embodiment of this invention is provided, and the shape of the injection opening. It is a figure which shows the relationship between the moving amount | distance of the 1st rotary plate and the 2nd rotary plate in each case of FIG. 8, and the opening degree of the opening for injection. It is a schematic block diagram which shows the modification of the chamber with which the apparatus for injection tests in one Embodiment of this invention is provided.

  Hereinafter, an embodiment of an injection test apparatus according to the present invention will be described with reference to the drawings. In the following drawings, the scale of each member is appropriately changed in order to make each member a recognizable size.

FIG. 1 is a cross-sectional view showing a schematic configuration of an injection test apparatus S1 of the present embodiment. As shown in this figure, the injection test apparatus S1 of the present embodiment includes a first rotating plate 1 (shielding member), a second rotating plate 2 (shielding member), a first shaft 3, and a second shaft 4. A first bearing 5, a second bearing 6, a first servo motor 7 (driving means), a second servo motor 8 (driving means), a first rotating plate sensor 9, and a second rotating plate. A sensor 10, a gate shutter device 11, a gate shutter opening detection sensor 12, a gate shutter closing detection sensor 13, a chamber 14, and a fixing device 15 are provided.
FIG. 2 is an arrow view of the first rotating plate 1 and the second rotating plate 2 viewed from the direction of the rotation axis. FIG. 3 is a perspective view schematically showing a part of the injection test apparatus S1 of the present embodiment. FIG. 4 is an exploded perspective view of the injection test apparatus S1 of the present embodiment shown in FIG.

The injection test apparatus S1 of the present embodiment performs an injection object of combustion gas when performing an injection test in which the combustion gas injected from the rocket motor M is injected to a test object (not shown) (not shown). It is for controlling the injection state with respect to.
Specifically, the injection test apparatus S1 of the present embodiment controls the injection timing and the injection time of the combustion gas for the injection target.

The first rotating plate 1 is disposed in the middle of the injection path X of the combustion gas injected from the rocket motor M as shown in FIGS. 1, 3 and 4, and is combusted as shown in FIGS. An opening 1a (passing region) for allowing gas to pass therethrough is provided in part.
More specifically, the first rotating plate 1 is a disc that is driven to rotate about a rotation axis L that is parallel to the injection path X below the injection path X, and is on the rocket motor M side. It functions as a shielding member that shields the combustion gas by receiving the combustion gas on the surface facing the surface.
As shown in FIG. 2, the first rotating plate 1 is formed with an opening 1 a which is set in an arc shape with the rotation axis L as a center at a position overlapping the injection path X by the rotation of the first rotating plate 1. Has been. And when the said opening 1a overlaps with the injection path | route X, the 1st rotation plate 1 lets a combustion gas pass to the test object side (right side in FIG. 1).

Moreover, as shown in FIG. 2, the opening 1a is an arc-shaped elongated hole, and both ends in the rotation direction are curved outward. The first rotating plate 1 includes a sensor detection plate 1b disposed in the peripheral area on the opposite side across the opening 1a and the rotation axis L.
The sensor detection plate 1b is detected by the first rotary plate sensor 9, and both ends thereof are arranged on a straight line connecting the end of the opening 1a and the rotation axis L. In the injection test apparatus S1 of the present embodiment, the position of the opening 1a can be detected by detecting the sensor detection plate 1b.
The first rotating plate 1 includes an alignment weight 1c for aligning the center of gravity of the first rotating plate 1 with the rotation axis L at a position symmetrical to the sensor detection plate 1b.

The second rotating plate 2 is disposed in the middle of the injection path X of the combustion gas injected from the rocket motor M as shown in FIGS. 1, 3 and 4, and is combusted as shown in FIGS. An opening 2a (passage region) through which gas passes is provided in part.
More specifically, the second rotating plate 2 is a disc that is driven to rotate about the rotation axis L as in the same manner as the first rotating plate 1. The second rotating plate 2 is a disk having a smaller diameter than the first rotating plate 1. However, the second rotating plate 2 may be a disc having the same diameter as the first rotating plate 1, or the first rotating plate 1 may be a disc having a smaller diameter than the second rotating plate 2.
As shown in FIG. 2, the second rotating plate 2 is formed with an opening 2 a which is set in an arc shape with the rotation axis L as a center at a position overlapping the injection path X by the rotation of the second rotating plate 2. Has been. And when the said opening 2a overlaps with the injection path | route X, the 2nd rotary plate 2 lets a combustion gas pass to the test object side (right side in FIG. 1).
However, as shown in FIG. 1, the second rotating plate 2 is disposed downstream of the first rotating plate 1 in the combustion gas injection direction. For this reason, even if the opening 2 a overlaps the injection path X, the combustion gas passes through the second rotation plate 2 if the opening 1 a of the first rotation plate 1 does not overlap the injection path X. There is nothing.

Further, as shown in FIG. 2, the opening 2a is an arc-shaped long hole, and both ends in the rotation direction are curved outward. The second rotating plate 2 includes a sensor detection plate 2b disposed in the peripheral area on the opposite side across the opening 2a and the rotation axis L.
The sensor detection plate 2b is detected by the second rotary plate sensor 10, and both ends thereof are arranged on a straight line connecting the end of the opening 2a and the rotation axis L. In the injection test apparatus S1 of the present embodiment, the position of the opening 2a can be detected by detecting the sensor detection plate 2b.
The second rotating plate 2 includes an alignment weight 2c for aligning the center of gravity of the second rotating plate 2 with the rotation axis L at a position symmetrical to the sensor detection plate 2b.

Returning to FIG. 1, the first shaft 3 is a shaft for rotationally driving the first rotating plate 1, and is fixed to the center of the first rotating plate 1.
The second shaft 4 is a shaft for rotationally driving the second rotating plate 2, and is fixed to the center of the second rotating plate 2.
The first bearing 5 is a bearing for supporting the first shaft 3. The second bearing 6 is a bearing for supporting the second shaft 4.

  The first servo motor 7 is a power source for rotationally driving the first rotary plate 1, and rotationally drives the first rotary plate 1 along a path through which the opening 1 a passes the injection path X. The first servo motor 7 is connected to the end of the first shaft 3 and transmits rotational power to the first rotating plate 1 via the first shaft 3.

  The second servo motor 8 is a power source for rotationally driving the second rotary plate 2, and rotationally drives the second rotary plate 2 along a path through which the opening 2 a passes the injection path X. The second servo motor 8 is connected to the end of the second shaft 4 and transmits rotational power to the second rotating plate 2 via the second shaft 4.

The first rotary plate sensor 9 detects the presence or absence of the first rotary plate sensor detection plate 1 b, and is disposed below the first rotary plate 1.
The second rotary plate sensor 10 detects the presence or absence of the second rotary plate sensor detection plate 2b, and is disposed below the second rotary plate 2.
The first rotating plate sensor 9 and the second rotating plate sensor 10 are arranged at positions shifted from the injection path X by 180 ° with the rotation axis L as the center.

The gate shutter device 11 is for shielding combustion gas separately from the first rotating plate 1 and the second rotating plate 2, and includes a gate shutter 11a (path closing member) that closes the injection path X, and a gate shutter 11a. And an actuator 11b for dropping from above the injection path X.
The gate shutter 11a is disposed so as to block the injection path X on the downstream side of the first rotary plate 1 and the second rotary plate 2 in the combustion gas injection direction.

The gate shutter opening detection sensor 12 is a sensor for detecting that the gate shutter 11a is open, and is provided on the injection path X in order to detect that the gate shutter 11a is located above the injection path X. It is arranged above.
The gate shutter closing detection sensor 13 is a sensor for detecting that the gate shutter 11a is closed, and is disposed below the injection path X to detect that the gate shutter 11a is blocking the injection path X. Has been.

The chamber 14 is provided so as to surround the first rotary plate 1, the second rotary plate 2, and the rocket motor M except for the injection path X, and includes an injection opening 14 a corresponding to the injection path X. This chamber 14 is a part of the combustion gas injected from the rocket motor M and goes around the first rotating plate 1 and the second rotating plate 2 without passing through the original injection path X to reach the test object. It is for confining gas.
The ejection opening 14a is a circular opening centered on the ejection path X, and is a position shifted by 180 ° about the rotation axis L with respect to the first rotation plate sensor 9 and the second rotation plate sensor 10. Is arranged.

  3 and 4, a duct 16 (exhaust flow path) is provided for exhausting the combustion gas filled in the chamber 14 to the outside of the chamber 14 while avoiding the injection path X. ) Is connected. The duct 16 extends to a position where the exhausted combustion gas does not affect the test object (for example, a position downstream of the test object in the injection direction of the combustion gas), and the exhausted combustion gas The combustion gas filled in the chamber 14 is exhausted to a position where the gas does not affect the test object.

  Returning to FIG. 1, the fixing device 15 is for fixing the rocket motor M, and is disposed inside the chamber 14. The fixing device 15 sets the posture of the rocket motor M toward the injection path X and fixes it.

  FIG. 5 is a block diagram for showing the electrical connection of the injection test apparatus S1 of the present embodiment. As shown in this figure, the injection test apparatus S1 of the present embodiment includes a control device 17 (control means) and an operation switch display panel 18 in addition to the above-described configuration.

The control device 17 controls the entire operation of the injection test device S1 of the present embodiment. The first servo motor 7, the second servo motor 8, the first rotating plate sensor 9, and the second rotating plate sensor. 10, the actuator 11b of the gate shutter device 11, the gate shutter opening detection sensor 12, the gate shutter closing detection sensor 13, and the operation switch display panel 18 are electrically connected.
More specifically, the control device 17 includes a PLC (Programmable Logic Controller) 17a, a first servo amplifier 17b, and a second servo amplifier 17c. The PLC is electrically connected to the first rotating plate sensor 9, the second rotating plate sensor 10, the actuator 11b of the gate shutter device 11, the gate shutter opening detection sensor 12, the gate shutter closing detection sensor 13, and the operation switch display panel 18. It is connected to the. The first servo amplifier 17b controls the first servomotor 7, and the second servo amplifier 17c controls the second servomotor 8.

In the injection test apparatus S1 of the present embodiment, the control device 17 controls the first servo motor 7 and the second servo motor 8 to thereby control the opening 1a of the first rotating plate 1 and the second rotating plate 2. The timing and passage speed of the opening 2a through the injection path X are adjusted.
More specifically, in the injection test apparatus S1 of the present embodiment, the rotation directions of the first rotating plate 1 and the second rotating plate 2 are reversed, so that the openings 1a and 2a overlap in the injection path X. The rotation of the first rotating plate 1 and the rotation of the second rotating plate 2 are controlled.

As shown in FIG. 5, the control device 17 is connected to the power source D and is supplied with power from the power source D.
The PLC 17a of the control device 17 is electrically connected to the ignition device Ma of the rocket motor M, and the rocket motor M can be ignited by controlling the ignition device Ma. The ignition device Ma is ignited by passing a current through the ignition unit of the rocket motor M, and is disposed outside the chamber 14 together with the control device 17.

  The operation switch display panel 18 is a man-machine interface capable of displaying and operating the operation switches, and is configured by, for example, a touch panel having both an input device and an output device. Instead of the operation switch display panel 18, an input device and a display device may be provided separately.

Next, the operation of the thus configured injection test apparatus S1 of the present embodiment will be described with reference to the timing chart of FIG.
In the injection test apparatus S1 of the present embodiment, the first rotating plate 1 and the second rotating plate 2 are opened at a preset rotational speed and opened before performing the operation shown in the timing chart of FIG. An operation of rotating the first rotating plate 1 and the second rotating plate 2 in synchronism is performed so that 1a and the opening 2a overlap in the injection path X. In the injection test apparatus S1 of the present embodiment, the required time between the full opening and the full opening of the injection opening 14a is 0.1 seconds, and the full opening time of the injection opening 14a is 0.1 seconds. Thus, the rotation of the first rotating plate 1 and the second rotating plate 2 is controlled.

Specifically, the PLC 17 a receives the detection signal from the first rotary plate sensor 9, and the first servo amplifier 17 b controls the rotation of the first servo motor 7 to control the first rotary plate 1. Further, the PLC 17 a receives the detection signal from the second rotating plate sensor 10, and the second servo amplifier 17 c controls the rotation of the second servo motor 8 to control the second rotating plate 2.
Here, in the injection test apparatus S1 of the present embodiment, the opening 1a and the sensor detection plate 1b are arranged 180 degrees apart from each other about the rotation axis L, and the injection opening 14a and the first are arranged around the rotation axis L. The rotating plate sensor 9 is arranged 180 ° apart. Therefore, in the first servo amplifier 17b, the timing at which the sensor detection plate 1b is detected by the first rotary plate sensor 9 is the timing at which the front end in the rotation direction of the opening 1a is applied to the center of the injection opening 14a (the injection path X). For example, the first servomotor 7 (that is, the first rotating plate 1) is feedback-controlled by performing control so that the rotation angle of the first servomotor 7 becomes 0 °.
Further, in the injection test apparatus S1 of the present embodiment, the opening 2a and the sensor detection plate 2b are arranged 180 degrees apart from each other about the rotation axis L, and further the injection opening 14a and the second rotation about the rotation axis L. The plate sensor 10 is arranged with a 180 ° offset. Therefore, in the second servo amplifier 17c, the timing at which the sensor detection plate 2b is detected by the second rotary plate sensor 10 is the timing at which the tip in the rotation direction of the opening 2a is applied to the center (injection path X) of the injection opening 14a. For example, the second servomotor 8 (that is, the second rotating plate 2) is feedback-controlled by performing control so that the rotation angle of the second servomotor 8 becomes 0 ° at the timing.

  When the first rotating plate 1 and the second rotating plate 2 are rotated in synchronism in this way, as shown in FIGS. 7A to 7J, the ejection opening 14a moves between the openings 1a and 2a. Accordingly, after being opened from the center, it is closed toward the center.

Then, after the first rotary plate 1 and the second rotary plate 2 are rotated in synchronization, when an injection test start signal is input from the operation switch display panel 18, the PLC 17a, as shown in FIG. Counting of the set countdown time T is started.
Then, the PLC 17a compares the detected waveform A1 from the first rotating plate sensor 9 and the detected waveform B1 from the second rotating plate sensor 10 immediately before the countdown time T becomes 0, and compares the detected waveform A1 with the first rotating plate 1 and A final confirmation is made as to whether the synchronization with the second rotating plate 2 is accurately taken. Here, when it is determined that the synchronization is not achieved, the PLC 17a stops the injection test. For example, the PLC 17a compares the rising timings of the detection waveform A1 and the detection waveform B1, and determines that synchronization is established when the difference is within 0.01 seconds.

  When the synchronization between the first rotating plate 1 and the second rotating plate 2 is accurately taken, the PLC 17a causes the falling timing of the detection waveform A2 following the detection waveform A1 (the detection waveform B2 following the detection waveform B1). The ignition device is operated by raising the output voltage of the ignition signal input to the ignition device Ma at the timing of falling), and thereby the rocket motor M is ignited by passing a current through the ignition part of the rocket motor M.

Then, for about 0.2 seconds while the next detection waveform A3 and the detection waveform B3 after the ignition of the rocket motor M are detected (that is, while the opening 1a and the opening 2a overlap in the injection path X), Combustion gas from the rocket motor M is injected toward the test object from the injection opening 14a.
That is, in the injection test apparatus S1 of the present embodiment, the combustion gas after a certain time has elapsed after the rocket motor M is ignited is sprayed onto the test object.

Further, the PLC 17a increases the output voltage of the command signal input to the actuator 11b of the gate shutter device 11 in accordance with the falling timing of the detection waveform A3. Block X.
Then, the PLC 17a completes the operation after confirming the operation of the gate shutter 11a based on the detection signal from the gate shutter opening detection sensor 12 and the detection signal from the gate shutter closing detection sensor 13.

As described above, according to the injection test apparatus S1 of the present embodiment, after the rocket motor M is ignited, the period excluding the period during which the detection waveform A3 and the detection waveform B3 are output (in FIG. In the region shown), the injection path X is closed and the combustion gas is shielded.
And combustion gas is sprayed on a test object only while detection waveform A3 and detection waveform B3 are output.

According to the injection test apparatus S1 of the present embodiment as described above, the first rotating plate 1 and the second rotating plate 2 partially provided with the openings 1a and 2a that are the passage regions of the combustion gas are the first servo. It is moved by the motor 7 and the second servo motor 8, and the first servo motor 7 and the second servo motor 8 are controlled by the control device 17.
Therefore, it is possible to control the rotational movement of the first rotating plate 1 and the second rotating plate 2, and the openings 1a, 2a of the first rotating plate 1 and the second rotating plate 2 overlap the combustion gas injection path X. Timing and period can be set arbitrarily.
Therefore, according to the injection test apparatus S1 of the present embodiment, it is possible to adjust the injection state of the combustion gas injected to the test target that is the injection target with a higher degree of freedom and to reproduce the actual injection environment. Is possible.

Moreover, in the apparatus S1 for injection test of this embodiment, the structure whose shielding member in this invention is a rotating plate is employ | adopted.
For this reason, it is possible to increase the speed of the shielding member by taking a sufficient time until the combustion gas is injected, and the first servo motor 7 and the second servo motor 8 having a small output can be used. Furthermore, when the combustion gas is shielded, the area exposed to the combustion gas always changes, so that the rise in the surface temperature of the first rotating plate 1 and the second rotating plate 2 is suppressed, and the first rotating plate 1 and the second rotation. The life of the plate 2 can be ensured for a long time, and the first rotating plate 1 and the second rotating plate 2 need not be formed of a special heat resistant material.

  Further, in the injection test apparatus S1 of the present embodiment, a configuration is adopted in which the first rotating plate 1 and the second rotating plate 2 are rotated in opposite directions so that the openings 1a and 2a are overlapped in the injection path X. ing. For this reason, it is possible to shorten the time from the full closing to the full opening of the injection opening 14a. Furthermore, it is possible to open from the center, and it is possible to prevent the combustion gas injected from the injection opening 14a from being biased.

Further, the injection test apparatus S1 of the present embodiment includes a gate shutter 11a that is separate from the first rotating plate 1 and the second rotating plate 2 and closes the injection path X.
Therefore, after the combustion gas is injected from the injection opening 14a, the combustion gas is injected from the injection opening 14a even when the first rotating plate 1 and the second rotating plate 2 are continuously rotated. Can be prevented.

In the injection test apparatus S1 of the present embodiment, the gate shutter 11a is disposed on the downstream side of the first rotating plate 1 and the second rotating plate 2 in the combustion gas flow direction.
For this reason, the timing at which the combustion gas is directly injected into the gate shutter 11a is only the timing at which the opening 1a and the opening 2a overlap, and is limited. For this reason, an increase in the surface temperature of the gate shutter 11a is suppressed, and a long life can be secured. Further, it is not necessary to form the gate shutter 11a with a special heat resistant material.

In addition, the injection test apparatus S1 of the present embodiment includes a chamber 14 surrounding the first rotating plate 1, the second rotating plate 2, and the rocket motor M, and the combustion gas filled in the chamber 14 is injected into the injection path X. A duct 16 for avoiding exhaust is provided.
For this reason, it becomes possible to suppress that combustion gas goes around the 1st rotating plate 1 and the 2nd rotating plate 2, and is injected to a test object.

  As mentioned above, although preferred embodiment of this invention was described referring drawings, this invention is not limited to the said embodiment. Various shapes, combinations, and the like of the constituent members shown in the above-described embodiments are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.

For example, in the above-described embodiment, the configuration in which the shielding members are the first rotary plate 1 and the second rotary plate 2 has been described.
However, the present invention is not limited to this, and the shielding member need not be a rotating plate. For example, it is also possible to use a slide plate that has an opening as the shielding member and slides in the vertical direction or the horizontal direction.
Furthermore, it is also possible to adopt a configuration in which the shielding member is a switching mechanism that can switch the flow path of the combustion gas to a flow path toward the test object and a flow path that is removed from the test object. Further, the shielding member can be constituted by a spherical member having a through hole through which the fuel gas can pass. Further, the shielding member can be a door. The shielding member may be a cylindrical member that surrounds the rocket motor M and has a slit.
In this way, when the shielding member has another configuration, the driving means is also changed according to the shielding member. For example, when the slide plate is used as the shielding member, the drive means is a slide device.

Moreover, in the said embodiment, the both ends in the rotation direction of the opening 1a and the both ends in the rotation direction of the opening 2a are the circular arc shape curved toward the outer side, and the structure where the injection opening 14a is circular was demonstrated.
However, the present invention is not limited to this, and the shapes of both ends of the opening 1a in the rotation direction, both ends of the opening 2a in the rotation direction, and the ejection opening 14a may be changed.

8 and 9 are diagrams for explaining verification of various cases regarding both ends in the rotation direction of the opening and the shape of the injection opening.
FIG. 8 is a schematic view illustrating various cases regarding both ends in the rotation direction of the opening and the shape of the injection opening. FIG. 9 is a diagram showing the relationship between the amount of movement of the first rotating plate and the second rotating plate and the opening of the injection opening in each case of FIG.
In this verification, as shown in FIG. 8, the injection opening has a circular case, a square case, a square case rotated by 45 degrees, and both ends of the openings of the first rotating plate and the second rotating plate are circular arcs. The case, the straight case, and the case bent at a right angle were combined.
As a result, it was confirmed that the case opened from the center of the injection opening in any case, and it was confirmed that CASE 4 (the case of the above embodiment) is closest to the ideal state shown in FIG.

Moreover, in the said embodiment, the structure which encloses the rocket motor M, the 1st rotary plate 1, and the 2nd rotary plate 2 in the single chamber 14 was demonstrated.
However, the present invention is not limited to this. For example, as shown in FIG. 10, the sub-chamber 14 </ b> A that surrounds the injection region of the combustion gas of the rocket motor M while avoiding the injection path X inside the chamber 14. And a sub-chamber 14B surrounding the first rotating plate 1 and the second rotating plate 2 may be further installed. In such a case, as shown in FIG. 10B, a duct 16A is connected to each of the sub-chambers 14A and 14B.
By adopting such a configuration, the combustion gas shielded by the first rotating plate 1 and the second rotating plate 2 is transferred to other devices (first servo motor 7, second servo motor 8, and rocket motor M). Touching can be suppressed.

  DESCRIPTION OF SYMBOLS 1 ... 1st rotating plate (shielding member), 1a ... Opening (passing area), 2 ... 2nd rotating plate (shielding member), 2a ... Opening (passing area), 7 ... 1st servo motor ( Drive means), 8... Second servo motor (drive means), 11 b... Gate shutter (path closing member), 14... Chamber, 14 a. ...... Control device (control means), L ... Rotating shaft, X ... Injection path, M ... Rocket motor

Claims (6)

An injection test device for controlling an injection state of an injection target of combustion gas injected from a rocket motor,
A shielding member that is disposed in the middle of the combustion gas injection path and partially has a passage region through which the combustion gas passes;
Drive means for moving the shielding member in a path through which the passage region passes through the combustion gas injection path;
An injection test apparatus comprising: control means for adjusting the timing at which the passage region of the shielding member passes through the injection path of the combustion gas by controlling the driving means.   The injection test apparatus according to claim 1, wherein the shielding member is a rotating plate that is driven to rotate about a rotation axis along the injection path and has an opening serving as the passage region. Two shielding members made of the rotating plate are provided,
3. The injection test according to claim 2, wherein the control unit reverses the rotation direction of the two rotating plates and overlaps the openings of the two rotating plates in the injection path. 4. apparatus.   4. The injection test apparatus according to claim 2, further comprising a path closing member that is provided separately from the shielding member and blocks the combustion gas injection path.   The injection test apparatus according to claim 4, wherein the path closing member is disposed downstream of the shielding member in the flow direction of the combustion gas.   A chamber surrounding at least the shielding member and the rocket motor except for the combustion gas injection path; and an exhaust passage for exhausting the combustion gas filled in the chamber to the outside of the chamber while avoiding the combustion gas injection path. An injection test apparatus according to any one of claims 1 to 5, further comprising:

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