CN217270524U - Rocket engine center positioning thrust vector dynamometer - Google Patents
Rocket engine center positioning thrust vector dynamometer Download PDFInfo
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- CN217270524U CN217270524U CN202122795159.5U CN202122795159U CN217270524U CN 217270524 U CN217270524 U CN 217270524U CN 202122795159 U CN202122795159 U CN 202122795159U CN 217270524 U CN217270524 U CN 217270524U
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- force sensor
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- component force
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Abstract
The utility model discloses a rocket engine center positioning thrust vector dynamometer, which consists of a lower cover plate flange, a three-component force sensor A, a three-component force sensor B, a three-component force sensor C, a three-component force sensor D, an upper cover plate flange, a positioning pin A and a positioning pin B; the three-component force sensor A, the three-component force sensor B, the three-component force sensor C and the three-component force sensor D are respectively arranged on a groove of the lower cover plate flange, and the upper cover plate flange is connected with the lower cover plate flange through a boss circular hole structure; and the positioning pin A and the positioning pin B are used for circumferentially positioning the lower cover plate flange.
Description
Technical Field
The utility model relates to a thrust vector dynamometer especially relates to a rocket engine center location thrust vector dynamometer.
Background
In an ideal state, the thrust action line of the rocket engine is overlapped with the central axis of the engine, but actually, the thrust action line of the engine deviates from the theoretical central axis of the engine due to the geometric asymmetry of the engine, the deformation caused by the asymmetrical flow of high-temperature and high-pressure fuel gas through a spray pipe and the ablation of the throat part of the spray pipe and the like because of the limitation of processing precision, so that the thrust eccentricity is generated.
Rocket motor thrust is a space vector that is not coincident with the theoretical central axis of the rocket motor. During the operation of the rocket engine, the size, the direction and the position of the acting point of the rocket engine are constantly changed along with time.
Rocket engine thrust vector measurement usually adopts a mode of combined measurement of a plurality of force sensors, and mutual coupling interference among the sensors has great influence on a final measurement result. Particularly in the implementation level, the main thrust of the rocket engine is far larger than the lateral thrust, and the interference of the lateral component force generated by the deflection of the main thrust on the measurement accuracy is greatly influenced. The spatial positioning of the individual sensors also has a great influence on the measurement accuracy.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model lies in overcoming the influence that the side direction component interference that has now produced because the incline of main thrust disturbs measurement accuracy. The effect of the spatial positioning of the individual sensors on the measurement accuracy.
In order to solve the above problems, the utility model discloses a realize through following scheme: the rocket engine center positioning thrust vector dynamometer consists of a lower cover plate flange, a three-component force sensor A, a three-component force sensor B, a three-component force sensor C, a three-component force sensor D, an upper cover plate flange, a positioning pin A and a positioning pin B; the three-component force sensor A, the three-component force sensor B, the three-component force sensor C and the three-component force sensor D are respectively installed on a groove of the lower cover plate flange, and the upper cover plate flange is connected with the lower cover plate flange through a boss circular hole structure. And the positioning pin A and the positioning pin B are used for circumferentially positioning the lower cover plate flange.
Since the proposal is adopted, compared with the prior art, the utility model has the advantages that: the lateral component force interference generated by the deflection of the main thrust is eliminated, the space positioning of each sensor is accurate, and the measuring precision of the thrust vector of the dynamometer is high.
Drawings
FIG. 1 is a cross-sectional view of a lower cover plate of a force measuring cell;
FIG. 2 is a three-dimensional view of the lower cover plate of the force gauge;
FIG. 3 is a cross-sectional view of the upper cover plate of the force measuring cell;
FIG. 4 is a three-dimensional view of the upper cover plate of the force gauge;
FIG. 5 is a cross-sectional view of the load cell assembly;
fig. 6 is an assembled three-dimensional exploded view of the load cell.
In the drawings
1. Lower cover plate flange 2, three fens force transducer A3, three fens force transducer B
4. Three-component force sensor C5, three-component force sensor D6, upper cover plate flange
7. Positioning pin A8, positioning pin B
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
8 bolt holes with the diameter of 10 are arranged on a flange (1) of a cover plate under the dynamometer and are used for being tightly connected with external equipment. The lower cover plate flange (1) is matched with an external device phi 80 boss through a phi 80 round hole to realize axial positioning. Two phi 10 positioning pin holes are processed on the lower cover plate flange (1), and the circumferential positioning of the dynamometer on external equipment is realized through the positioning pins.
The three-way force sensor is designed to be 55 multiplied by 60, the key point of the design of the force measuring instrument lies in the accurate positioning of the three-way force sensor, the screw holes cannot be accurately positioned, in order to effectively position, the length, the width and the height of the four used three-way force sensors are measured at three positions respectively, and the measurement results are shown in tables 1, 2, 3 and 4. It can be seen from the table that the three-component force sensor a (2), the three-component force sensor B (3), the three-component force sensor C (4) and the three-component force sensor D (5) have the same external dimensions, the heights are 59.94mm, and the lengths and the widths are 55 +/-0.01 mm. Four sides of the three-component force sensor A (2), the three-component force sensor B (3), the three-component force sensor C (4) and the three-component force sensor D (5) are used as positioning surfaces, four positioning square grooves with the depth of 3mm are milled on the lower cover plate flange (1), the size is 55mm, the upper deviation is 0.05mm, and the lower deviation is 0. The center distance between adjacent square grooves is 115mm, the upper deviation is 0.05mm, and the lower deviation is 0. Accurate positioning of three fens force transducer A (2), three fens force transducer B (3), three fens force transducer C (4), three fens force transducer D (5) positions has been realized like this through apron flange (1) down. A hollow cylindrical bulge is processed at the center of the lower cover plate flange (1), and a positioning hole is processed in the bulge.
TABLE 1 three-way force SENSOR A EXTERNAL SCALE
| Is long and long | Width of | Height of | |
| 1 | 54.99 | 55.00 | 59.94 |
| 2 | 55.00 | 55.00 | 59.94 |
| 3 | 55.00 | 55.00 | 59.94 |
TABLE 2 three-dimensional force sensor B overall dimension
| Long and long | Width of | High (a) | |
| 1 | 54.99 | 54.99 | 59.94 |
| 2 | 54.99 | 55.00 | 59.94 |
| 3 | 54.99 | 55.00 | 59.94 |
TABLE 3 three-dimensional force sensor C external dimension
| Long and long | Width of | Height of | |
| 1 | 55.01 | 55.01 | 59.94 |
| 2 | 55.01 | 55.01 | 59.94 |
| 3 | 55.01 | 55.01 | 59.94 |
TABLE 4 three-dimensional force sensor D physical dimension
| Long and long | Width of | High (a) | |
| 1 | 55.00 | 55.00 | 59.94 |
| 2 | 55.00 | 55.01 | 59.94 |
| 3 | 55.00 | 55.00 | 59.94 |
In order to avoid over positioning, a sensor positioning square groove is not arranged on the upper cover plate flange (6), a cylindrical protrusion is machined in the center of the upper cover plate flange (6), and a hole shaft positioning method is adopted to perform center positioning with a positioning hole in the cylindrical protrusion in the center of the lower cover plate flange (1). And meanwhile, two phi 10 positioning pin holes are formed in the upper cover plate flange (6), and the upper cover plate flange (6) and the three-component force sensor A (2), the three-component force sensor B (3), the three-component force sensor C (4) and the three-component force sensor D (5) are circumferentially positioned through the positioning pins A (7) and the positioning pins B (8).
The present invention has not been described in detail as is known to those skilled in the art.
Claims (3)
1. A rocket engine center positioning thrust vector dynamometer is characterized by consisting of a lower cover plate flange (1), a three-component force sensor A (2), a three-component force sensor B (3), a three-component force sensor C (4), a three-component force sensor D (5), an upper cover plate flange (6), a positioning pin A (7) and a positioning pin B (8); a bolt hole is arranged on a flange (1) of a lower cover plate of the dynamometer and is used for being tightly connected with external equipment; the lower cover plate flange (1) is matched with a boss of external equipment through a circular hole to realize axial positioning; two positioning pin holes are processed on the lower cover plate flange (1), and the peripheral positioning of the dynamometer on external equipment is realized through the positioning pins.
2. The rocket engine center positioning thrust vector dynamometer according to claim 1, wherein four sides of a three-component force sensor A (2), a three-component force sensor B (3), a three-component force sensor C (4) and a three-component force sensor D (5) are used as positioning surfaces, four positioning square grooves with the depth of 3mm are milled on a lower cover plate flange (1), the upper deviation is 0.05mm, and the lower deviation is 0; the center distance between adjacent square grooves is 115mm, the upper deviation is 0.05mm, and the lower deviation is 0; therefore, the accurate positioning of the positions of the three-component force sensor A (2), the three-component force sensor B (3), the three-component force sensor C (4) and the three-component force sensor D (5) is realized through the lower cover plate flange (1); a hollow cylindrical bulge is processed at the center of the lower cover plate flange (1), and a positioning hole is processed in the bulge.
3. The rocket engine center positioning thrust vector dynamometer according to claim 1, wherein in order to avoid over-positioning, no sensor positioning square groove is arranged on the upper cover plate flange (6), a cylindrical protrusion is machined in the center of the upper cover plate flange (6), and a hole axis positioning method is adopted to perform center positioning with a positioning hole in the cylindrical protrusion in the center of the lower cover plate flange (1); and meanwhile, two phi 10 positioning pin holes are formed in the upper cover plate flange (6), and the upper cover plate flange (6) is circumferentially positioned with the three-component force sensor A (2), the three-component force sensor B (3), the three-component force sensor C (4) and the three-component force sensor D (5) through the positioning pins A (7) and the positioning pins B (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122795159.5U CN217270524U (en) | 2021-11-16 | 2021-11-16 | Rocket engine center positioning thrust vector dynamometer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122795159.5U CN217270524U (en) | 2021-11-16 | 2021-11-16 | Rocket engine center positioning thrust vector dynamometer |
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| Publication Number | Publication Date |
|---|---|
| CN217270524U true CN217270524U (en) | 2022-08-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122795159.5U Active CN217270524U (en) | 2021-11-16 | 2021-11-16 | Rocket engine center positioning thrust vector dynamometer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114215661A (en) * | 2021-11-16 | 2022-03-22 | 北京航天试验技术研究所 | Rocket engine center positioning thrust vector dynamometer |
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2021
- 2021-11-16 CN CN202122795159.5U patent/CN217270524U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114215661A (en) * | 2021-11-16 | 2022-03-22 | 北京航天试验技术研究所 | Rocket engine center positioning thrust vector dynamometer |
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