CN115680943A - Rocket engine heat radiation measuring device - Google Patents
Rocket engine heat radiation measuring device Download PDFInfo
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- CN115680943A CN115680943A CN202211352835.4A CN202211352835A CN115680943A CN 115680943 A CN115680943 A CN 115680943A CN 202211352835 A CN202211352835 A CN 202211352835A CN 115680943 A CN115680943 A CN 115680943A
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- rocket engine
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- 230000005855 radiation Effects 0.000 title claims abstract description 28
- 238000005259 measurement Methods 0.000 claims abstract description 12
- 239000000523 sample Substances 0.000 claims description 7
- 238000001514 detection method Methods 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 3
- 230000000750 progressive effect Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 8
- 230000007547 defect Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 230000000875 corresponding effect Effects 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
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- 230000004907 flux Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
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Abstract
The invention provides a rocket engine thermal radiation measuring device, comprising: an undercarriage adapted to move in a predetermined direction parallel to the rocket motor axis; the pushing device is used for pushing and pulling the underframe to move along the preset direction; the turntable is rotationally connected with the underframe through a turntable support rod; the turntable support rod extends perpendicular to the ground; the end surface of the turntable is parallel to the ground; the heat flow sensor is arranged on the end face of the turntable; and the rotating device is used for driving the turntable to rotate. The device overcomes the defects that the heat radiation measuring device in the prior art is high in manufacturing cost and relatively inaccurate in measurement due to the arrangement of a plurality of measuring points.
Description
Technical Field
The invention relates to the technical field of rocket engine testing, in particular to a rocket engine thermal radiation measuring device.
Background
The rocket engine gas tail flame thermal radiation field has a large range, and the state of the thermal radiation field can be reflected only by measuring the heat flow density values at different positions and directions. Therefore, in the prior art, a plurality of heat flow sensors are arranged, and measuring points are placed at different positions in different directions and distances from an engine. However, the heat flow sensors are high in price, the measurement cost of the heat flow sensors is high, and the normal flow of the gas tail flame of the rocket engine can be disturbed due to the fact that a plurality of measuring point supports are arranged in a rocket engine test room, so that the measurement is inaccurate.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defects of high cost and relatively inaccurate measurement caused by arranging a plurality of measuring points in the heat radiation measuring device in the prior art.
In order to solve the above technical problem, the present application provides a rocket engine thermal radiation measuring apparatus, comprising:
an undercarriage adapted to move in a predetermined direction parallel to an axis of the rocket motor;
the pushing device is used for pushing and pulling the underframe to move along the preset direction;
the turntable is rotationally connected with the underframe through a turntable support rod; the turntable support rod extends perpendicular to the ground; the end surface of the turntable is parallel to the ground;
the heat flow sensor is arranged on the end face of the turntable;
and the rotating device is used for driving the rotating disc to rotate.
Optionally, more than two heat flow sensors are arranged, and the heat flow sensors are uniformly distributed around the circumference of the rotating shaft center of the turntable; in the process of one circle of rotation of the turntable, every time the preset point reaches the heat flow sensor, the orientation of the heat flow sensor probe which arrives at each time is different.
Optionally, in the process of one rotation of the turntable, when the preset point reaches the heat flow sensor, the directions of the heat flow sensor probes which come each time are uniformly distributed in a circle.
Optionally, the rotating device comprises:
the shell is fixed on the bottom frame;
the gear shaft is connected to an output shaft of the first motor; and outer teeth are arranged on the periphery of the turntable and are meshed with the gear shaft.
Optionally, the gear shaft is on a side adjacent to the rocket motor relative to the carousel strut.
Optionally, the vehicle further comprises a slide rail fixed on the ground, and the underframe slides on the slide rail.
Optionally, a scale is marked on the slide rail.
Optionally, a pulley is rotatably connected to the bottom of the underframe and is matched with the sliding rail.
Optionally, the pushing device comprises:
the shell of the second motor is fixed with the ground;
the screw rod is connected to an output shaft of the second motor; the bottom frame is in threaded connection with the lead screw.
Optionally, the first motor and the second motor are both explosion-proof progressive motors.
By adopting the technical scheme, the invention has the following technical effects:
1. according to the rocket engine thermal radiation measuring device provided by the invention, the bottom frame is moved and stays at different positions in the rocket engine thermal radiation field through the pushing device, and the heat flow sensor is driven by the turntable to be positioned at different positions to measure the heat flow of the gas tail flame of the rocket engine, so that the heat flow measurement at multiple positions and multiple directions in the engine tail flame space is completed by using fewer sensors, and the manufacturing cost of experimental equipment is reduced. In addition, because the device adopts the turntable support rod extending towards the axis of the rocket engine, the chassis with relatively large volume is far away from the rocket engine as far as possible, the normal flow of the tail flame is prevented from being interfered, and the turntable with the end surface parallel to the axis of the rocket engine is arranged at the top end of the rod to be used as a bearing platform of the heat flow sensor.
2. The thermal radiation measuring device of the rocket engine provided by the invention simulates the effect of rotating and measuring a plurality of sets of rotating mechanisms by only driving the rotating disc to rotate and matching with the heat flow sensors in different directions to be in place in sequence, so that the structure of the device becomes very compact, the sectional area of the whole device in heat flow is reduced, the manufacturing cost is reduced, the complexity of the device is also reduced, and the working reliability of the device is greatly improved.
3. The rocket engine heat radiation measuring device provided by the invention can adopt the motor with lower angular resolution to rotate the periphery of the turntable through the gear shaft to obtain the rotating angle with enough precision, thereby reducing the manufacturing cost of equipment, and because the extended gear shaft belongs to a slender part, the section in a flow field is smaller, the influence on the flow of tail flames is relatively lower, especially because the turntable support rod is already in the tail flame flow field, if the flow direction of the tail flames is exactly consistent with the connecting line from the gear shaft to the turntable support rod, the negative influence brought by the additionally arranged gear shaft 4 is very little.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a top view of the relationship between the turntable and the heat flow sensor in the first embodiment of the present invention;
FIG. 3 is a top view of a second embodiment of the present invention illustrating the relationship between the turntable and the heat flow sensor;
fig. 4 is a schematic view of the orientation of a heat flux sensor in a multi-turn position of a second embodiment of a turntable according to the present invention.
Description of reference numerals:
1. a rocket motor; 2. a heat flow sensor; 3. a turntable; 4. a gear shaft; 5. a turntable support rod; 6. a slide rail; 7. a first motor; 8. a lead screw; 9. a second motor; 10. a chassis; 11. a pulley.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Furthermore, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The embodiment provides a rocket engine thermal radiation measuring device.
In one embodiment, as shown in fig. 1 and 2, it comprises a base frame 10, a pushing device, a turntable 3 and a rotating device. The undercarriage 10 is adapted to move in a predetermined direction parallel to the axis of the rocket motor 1. The pushing device is used for pushing and pulling the chassis 10 along the preset direction. The rotary disc 3 is rotatably connected with the underframe 10 through a rotary disc support rod 5. The turntable support 5 extends perpendicularly to the ground. The end face of the rotary table 3 is parallel to the ground. The heat flow sensor 2 is arranged on the end face of the rotating disc 3. The rotating device is used for driving the rotating disc 3 to rotate.
When the device is used, under the condition that the gas tail flame of the rocket engine enters a stable state, the underframe 10 is moved and stays at different positions in a heat radiation field of the rocket engine through the pushing device, and the heat flow sensor 2 is driven to be positioned at different positions through the turntable 3 to measure the heat flow of the gas tail flame of the rocket engine, so that the heat flow measurement of multiple positions and multiple directions in an engine tail flame space is completed by using fewer sensors, and the manufacturing cost of experimental equipment is reduced. In addition, because the device adopts the turntable support rod 5 extending towards the axis of the rocket engine 1, the chassis 10 with relatively large volume is far away from the rocket engine 1 as far as possible, the normal flow of the tail flame is prevented from being interfered, and the turntable 3 with the end surface parallel to the axis of the rocket engine 1 is arranged at the top end of the rod to be used as a bearing platform of the heat flow sensor 2.
Based on the above embodiments, in a preferred embodiment, as shown in fig. 3 and 4, the heat flow sensors 2 have more than two, and the heat flow sensors 2 are uniformly distributed around the rotation axis center circumference of the rotating disk 3. Taking four heat flow sensors 2 as an example, the orientation of each heat flow sensor 2 can be seen in fig. 3, and the orientation layout is different for each incoming heat flow sensor 2 probe every time a preset point reaches a heat flow sensor 2 during one rotation of the turntable 3. In particular, referring to fig. 4, in the position of the thermal flow sensor 2 located at the upper right side in the figure, each time the turntable 3 rotates 45 °, the orientation of the new thermal flow sensor 2 probe is different from the previous one (the rear thermal flow sensor 2 is shown by a dotted line), so that after the four thermal flow sensors 2 are all rotated around the axis of the turntable 3, four different detection orientations are formed, which is equivalent to that the detection of four different orientations is performed by using one thermal flow sensor 2 to rotate at the position. Similarly, because the four heat flow sensors 2 are circumferentially and uniformly distributed, when the heat flow sensor 2 at one position is in place, the other positions can generate the situation that the new heat flow sensor 2 reaches the position of the heat flow sensor 2 before rotation, and finally the whole rotary disc 3 achieves the effect equivalent to that the four heat flow sensors 2 rotate independently to perform measurement in different directions. Obviously, a different number of heat flow sensors 2 is provided, and the corresponding effect can be achieved, and is not limited to the four presented in the embodiment of fig. 4.
The reason for this arrangement is that, because the angles of the detection head of the heat flow sensor 2 and the nozzle of the rocket engine 1 are different, different measurement values are obtained, and aiming at the anisotropy of the tail flame heat radiation field, the heat flow sensor 2 can acquire data towards different directions at the same point position, so that the characteristic of the tail flame heat radiation field can be more comprehensively mastered. If the scheme that the four heat flow sensors 2 rotate independently to perform measurement is adopted, a corresponding driving or transmission device needs to be configured for each heat flow sensor 2, so that the manufacturing cost of the equipment is increased, and the sectional area of the equipment in the tail flame airflow is increased due to the fact that the corresponding devices are additionally arranged, so that the normal flow of the tail flame is hindered, and the measurement accuracy is reduced. The scheme adopts a mode that only the rotating disc 3 is driven to rotate and the heat flow sensors 2 in different directions are matched to be in place in sequence, so that the effect of rotating and measuring four sets of rotating mechanisms is simulated, the structure of the device becomes very compact, the sectional area of the whole device in heat flow is reduced, the manufacturing cost is reduced, the complexity of the device is also reduced, and the working reliability of the device is greatly improved.
Based on the above embodiment, in a preferred embodiment, as shown in fig. 4, during one rotation of the turntable 3, every time a preset point reaches the heat flow sensor 2, the directions of the heat flow sensor 2 probes which come each time are circumferentially distributed. That is, in fig. 4, the orientation of the alternate heat flow sensors 2 forms a cross-shaped layout with a circumferential division of 90 degrees. The orientation of the heat flow sensor 2 probe which is uniformly distributed on the circumference can more comprehensively measure the thermal radiation field of the tail flame of the engine, and the characteristics of the thermal radiation field are comprehensively reflected.
Based on the above embodiments, in a preferred embodiment, as shown in fig. 1, the rotating device includes: a first motor 7 and a gear shaft 4. The shell of the first motor 7 is fixed on the bottom frame 10; the gear shaft 4 is connected to an output shaft of the first motor 7; the outer periphery of the turntable 3 is provided with external teeth which are meshed with the gear shaft 4.
The reason for this is that the rotation angle of the turntable 3 sometimes has higher precision requirement, and the adoption of the motor to directly rotate the turntable support rod 5 through the transmission mechanism will necessitate not only adding the motor to the base frame 10, but also adding the corresponding transmission mechanism, so as to increase the total volume of the relevant part of the base frame 10, and further generate more adverse effects on the flowing of the tail flame. If the motor is adopted to directly drive the turntable support rod 5, the angular resolution of the motor is higher, and the total cost of the equipment is increased. The scheme can adopt a motor with lower angular resolution to rotate the periphery of the turntable 3 through the gear shaft 4 to obtain a rotating angle with enough precision, so that the manufacturing cost of equipment is reduced, the protruding gear shaft 4 belongs to a slender part, the cross section in a flow field is smaller, the influence on tail flame flow is relatively lower, particularly, the turntable support rod 5 is already in the tail flame flow field, and if the flow direction of the tail flame just coincides with the connecting line from the gear shaft 4 to the turntable support rod 5, the negative influence brought by the addition of the gear shaft 4 is very little.
Based on the above embodiment, in a preferred embodiment, as shown in fig. 1, the gear shaft 4 is located on the side closer to the rocket motor 1 with respect to the turntable strut 5. The gear shaft 4 is located at a position closer to the front than the turntable support rod 5, so that the tail flame of the engine has strong thrust, and if the turntable support rod 5 is subjected to the too strong thrust, the turntable support rod is easy to bend, so that the end face of the turntable 3 is not parallel to the axis of the rocket engine 1 and serves as a fixed platform of the heat flow sensor 2, the measurement accuracy is reduced due to unstable platform, and the cross section area in a flow field is possibly increased after the turntable 3 deflects, so that the adverse interference on the tail flame is increased. And the forward gear shaft 4 replaces the turntable support rod 5 in advance to shield the tail flame to a certain extent, thereby ensuring the stability of the turntable 3.
Based on the above embodiments, in a preferred embodiment, as shown in fig. 1, the device further includes a slide rail 6 fixed to the ground, and the base frame 10 slides on the slide rail 6. The chassis 10 may be biased out of the predetermined path due to the strong thrust of the tail flame of the engine, but the experimental record may consider the measured data to be data on the predetermined path, thereby causing the deviation of the experimental data. After the slide rail 6 is additionally arranged, the chassis 10 can be ensured to move along a given route, and the reliability of experimental data is ensured.
Based on the above embodiments, in a preferred embodiment, as shown in fig. 1, scales are marked on the slide rails 6, which can be used for measuring the distance between the centers of the circles of the disks, so as to calculate the coordinates of the sensor, thereby directly observing the displacement of the bottom frame 10 when the displacement measuring device of the bottom frame 10 fails.
Based on the above embodiments, in a preferred embodiment, as shown in fig. 1, a pulley 11 is rotatably connected to the bottom of the base frame 10, and the pulley 11 is adapted to the slide rail 6. Under the action of strong thrust of the tail flame of the engine, the situation that the sliding is difficult to slide due to large friction force can be met by adopting a simple sliding rail and sliding block structure, so that the sliding block 11 is additionally arranged to reduce the pushing resistance, and the device can be displaced smoothly.
Based on the above embodiments, in a preferred embodiment, as shown in fig. 1, the pushing device comprises a second motor 9 and a lead screw 8. The shell of the second motor 9 is fixed with the ground; the screw rod 8 is connected to an output shaft of the second motor 9; the base frame 10 is in threaded connection with the lead screw 8. The transmission mode of the lead screw 8 can provide high-precision movement for the bottom frame 10, and the displacement can be obtained by calculating the rotation turns of the motor, so that the accuracy of test data is improved.
Based on the above embodiment, in a preferred embodiment, as shown in fig. 1, the first motor 7 and the second motor 9 are explosion-proof progressive motors. Compared with a servo motor, the improved motor has the advantage of low price, and the explosion-proof motor avoids the potential safety hazard that fuel in a rocket engine test field is leaked and ignited by the motor.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. This need not be, nor should it be exhaustive of all embodiments. And obvious variations or modifications of the invention may be made without departing from the spirit or scope of the invention.
Claims (10)
1. A rocket engine thermal radiation measuring device, comprising:
-an undercarriage (10) adapted to move along a predetermined direction parallel to the axis of the rocket motor (1);
the pushing device is used for pushing and pulling the bottom frame (10) to move along the preset direction;
the turntable (3) is rotationally connected with the bottom frame (10) through a turntable support rod (5); the turntable support rod (5) extends vertical to the ground; the end surface of the turntable (3) is parallel to the ground;
the heat flow sensor (2) is arranged on the end face of the rotary disc (3);
and the rotating device is used for driving the rotating disc (3) to rotate.
2. A rocket engine bolometric measurement device according to claim 1, wherein the number of thermal flow sensors (2) is more than two, the thermal flow sensors (2) being uniformly distributed around the circumference of the rotation axis of the turntable (3); in the process that the turntable (3) rotates for one circle, every time when the preset point reaches the heat flow sensor (2), the orientation of the detection head of each arriving heat flow sensor (2) is different.
3. A rocket engine thermal radiation measuring device according to claim 2, characterized in that the orientation of the heat flow sensor (2) probes coming each time is circumferentially distributed every time a predetermined point arrives at the heat flow sensor (2) during a revolution of the turntable (3).
4. A rocket engine thermal radiation measuring device as recited in claim 1, wherein said rotating means comprises:
the first motor (7), the outer cover is fixed on the chassis (10);
a gear shaft (4) connected to an output shaft of the first motor (7); external teeth are arranged on the periphery of the rotary table (3) and meshed with the gear shaft (4).
5. A rocket engine thermal radiation measuring device according to claim 4, characterized in that the gear shaft (4) is located at the side close to the rocket engine (1) with respect to the turntable strut (5).
6. A rocket engine thermal radiation measuring device according to claim 1, further comprising ground-fixed slide rails (6), the chassis (10) sliding on the slide rails (6).
7. A rocket engine thermal radiation measuring device according to claim 6, characterized in that on the slide rails (6) scales are marked.
8. A rocket engine thermal radiation measuring device according to claim 6, characterized in that the bottom of the chassis (10) is rotatably connected with a pulley (11), and the pulley (11) is matched with the slide rail (6).
9. A rocket engine thermal radiation measuring device as recited in claim 4, wherein said urging means comprises:
the shell of the second motor (9) is fixed with the ground;
the lead screw (8) is connected to an output shaft of the second motor (9); the bottom frame (10) is in threaded connection with the lead screw (8).
10. A rocket engine thermal radiation measuring device according to claim 9, characterized in that the first electric machine (7) and the second electric machine (9) are explosion-proof progressive electric machines.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202211352835.4A CN115680943A (en) | 2022-10-31 | 2022-10-31 | Rocket engine heat radiation measuring device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211352835.4A CN115680943A (en) | 2022-10-31 | 2022-10-31 | Rocket engine heat radiation measuring device |
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| CN115680943A true CN115680943A (en) | 2023-02-03 |
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