CN108362426B - Aeroengine thrust detection equipment - Google Patents
Aeroengine thrust detection equipment Download PDFInfo
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- CN108362426B CN108362426B CN201810061045.8A CN201810061045A CN108362426B CN 108362426 B CN108362426 B CN 108362426B CN 201810061045 A CN201810061045 A CN 201810061045A CN 108362426 B CN108362426 B CN 108362426B
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- 238000001514 detection method Methods 0.000 title claims abstract description 21
- 238000012360 testing method Methods 0.000 claims abstract description 17
- 239000004973 liquid crystal related substance Substances 0.000 claims description 10
- 230000005484 gravity Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/13—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring the tractive or propulsive power of vehicles
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
Abstract
The invention discloses an aircraft engine thrust detection device which comprises a base, wherein the base is fixedly arranged on the ground, a test hole is formed in the middle position of the upper surface of the base, a pressure device is arranged in the base, the pressure device is composed of a sliding part sleeved in the test hole, a pressure plate, pressure sensors and signal connectors, the pressure plate is positioned in the sliding part and is in sliding connection with the inner side surface of the sliding part, the pressure sensors are positioned below the pressure plate and are fixedly connected with the lower surface of the pressure plate and are uniformly distributed, the signal connectors are positioned on the right side of the pressure sensors and are fixedly connected with the middle position below the right side surface of the pressure sensors, a fixing device is arranged above the pressure plate. The invention has the advantages of simple structure and strong practicability.
Description
Technical Field
The invention relates to the technical field of aero-engine performance testing, in particular to aero-engine thrust detection equipment.
Background
When the aeroengine leaves a factory or repairs faults, thrust detection is needed, relevant experiments are conducted, dynamic changes of the thrust under different air pressure conditions are generated, good conditions are determined according to the changing effect of the thrust, a traditional testing method generally tests on a horizontal guide rail, and due to the fact that the gravity of the aeroengine is too large, even if the friction factor is small, the great friction force can be brought, and the objectivity of detection is affected.
Disclosure of Invention
The invention aims to solve the problems and designs an aircraft engine thrust detection device.
The technical scheme of the invention is that the thrust detection equipment for the aircraft engine comprises a base, wherein the base is fixedly arranged on the ground, a test hole is formed in the middle position of the upper surface of the base, a pressure device is arranged in the base, the pressure device comprises a sliding part sleeved in the test hole, a pressure plate which is positioned in the sliding part and is in sliding connection with the inner side surface of the sliding part, pressure sensors which are positioned below the pressure plate and are fixedly connected with the lower surface of the pressure plate and are uniformly distributed, and a signal connector which is positioned on the right side of the pressure sensors and is fixedly connected with the middle position below the right side surface of the pressure sensors, a fixing device is arranged above the pressure plate, and the fixing device comprises a sliding groove formed in the middle position of the upper surface of the pressure plate, a bearing sliding block which is positioned in the sliding groove and is in sliding connection with the sliding groove, a, The device comprises a contact plate, a first bearing shaft, a first bearing sleeve, a second bearing shaft and a second bearing sleeve, wherein the contact plate is positioned on the right side of a bearing frame and fixedly connected with the middle position above the surface of the right side of the bearing frame, the first bearing shaft is positioned in front of the contact plate and fixedly connected with the front surface of the contact plate, the first bearing sleeve is sleeved outside the first bearing shaft and rotatably connected with the first bearing shaft, the second bearing shaft is positioned behind the contact plate and fixedly connected with the rear surface of the contact plate, the second bearing sleeve is sleeved outside the second bearing shaft and rotatably connected with the second bearing shaft, a fastening device is arranged above the fastening device, and the fastening device comprises a first front connecting shaft, a first mounting hole, a second mounting hole and a rear connecting piece, the first mounting hole is formed in the middle position of the rear surface of the front connecting piece, the first rear connecting shaft is positioned above the first bearing sleeve and fixedly connected with the upper surface of, The hydraulic cylinder is characterized by comprising a mounting hole II, a main hydraulic cylinder, an oil inlet pipe and an oil outlet pipe, wherein the mounting hole II is formed in the middle position of the front surface of the rear connecting piece, the base is sleeved in the mounting hole II, the main hydraulic cylinder is sleeved in the mounting hole I, the oil inlet pipe is fixedly connected with the front of the middle position of the upper surface of the main hydraulic cylinder above the main hydraulic cylinder, and the oil outlet pipe is fixedly connected with the rear of the middle position of the upper surface of the main hydraulic cylinder above the main hydraulic.
The right side of the bearing frame in the fixing device is provided with an auxiliary frame, the right side of the auxiliary frame is provided with an auxiliary hydraulic cylinder, and the telescopic end of the auxiliary hydraulic cylinder is provided with an auxiliary sleeve.
And four corners above the base are provided with protection columns.
An air inlet device is arranged between the protection columns and consists of a fan frame, a fan mounting hole and an auxiliary fan, wherein the fan frame is positioned above the base, two ends of the fan frame are fixedly connected with the middle position of the protection columns respectively, the fan mounting hole is formed in the middle position of the fan frame, and the auxiliary fan is positioned in the fan mounting hole and is fixedly connected with the fan frame.
And an air pressure sensor is arranged in the middle of the surface of the inner side of the protection column.
The base front surface intermediate position is equipped with liquid crystal display, the liquid crystal display right side is equipped with control panel.
The rear of the sliding groove is provided with a balancing device, and the balancing device is composed of a gear rack, a balancing motor seat, a balancing motor and a driving gear, wherein the gear rack is located at the rear of the sliding groove and fixedly connected with the upper surface of the pressure plate, the balancing motor seat is located at the rear of the bearing sliding block and fixedly connected with the rear surface of the bearing sliding block, the balancing motor is sleeved in the balancing motor seat, and the driving gear is sleeved on the outer side of an output.
And a protection net is arranged behind the auxiliary fan and fixedly connected with the outer side surface of the auxiliary fan.
And the right side of the upper surface of the pressure plate is provided with a fixing part which is symmetrical and consistent with the fixing device in structure.
The base is internally provided with an oil tank, the main hydraulic cylinder, the oil inlet pipe, the oil outlet pipe and the auxiliary hydraulic cylinder are connected through oil pipes, and the signal connector, the auxiliary fan, the air pressure sensor, the liquid crystal display screen, the control panel and the balance motor are electrically connected.
According to the aero-engine thrust detection device manufactured by the technical scheme, the horizontal pressure plate bears the gravity of the aero-engine and the bearing frame, meanwhile, the aero-engine downward thrust is borne, the stress is more stable compared with the situation that the thrust is tested in the horizontal direction, the air inlet device can adjust the pressure of an air inlet of the aero-engine and test the thrust under different conditions under the monitoring of the air pressure sensor, and the pressure sensors positioned at four corners below the pressure plate can basically and evenly distribute the thrust from the aero-engine.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft engine thrust detection device according to the invention;
FIG. 2 is a top view of an aircraft engine thrust detection apparatus of the present invention;
FIG. 3 is an enlarged view of a portion of the pressure device of the present invention;
FIG. 4 is an enlarged partial view of the fastening device of the present invention;
FIG. 5 is an enlarged view of a portion of the balancing apparatus of the present invention;
in the figure, 1, a base; 2. a test well; 3. a pressure device; 4. a slider; 5. a pressure plate; 6. a pressure sensor; 7. a signal connector; 8. a fixing device; 9. a sliding groove; 10. a load-bearing slider; 11. a bearing frame; 12. a contact plate; 13. a first bearing shaft; 14. a first bearing sleeve; 15. a second bearing shaft; 16. a second bearing sleeve; 17. a fastening device; 18. a front connecting shaft; 19. a front connector; 20. a first mounting hole; 21. a rear connecting shaft; 22. a rear connector; 23. a second mounting hole; 24. an oil tank; 25. a master cylinder; 26. an oil inlet pipe; 27. an oil outlet pipe; 28. an auxiliary frame; 29. an auxiliary hydraulic cylinder; 30. an auxiliary sleeve; 31. a guard post; 32. an air intake device; 33. a fan frame; 34. a fan mounting hole; 35. a protection net; 36. an auxiliary fan; 37. an air pressure sensor; 38. a liquid crystal display screen; 39. a control panel; 40. a balancing device; 41. a gear rack; 42. a balance motor base; 43. a balancing motor; 44. a drive gear.
Detailed Description
The invention is described in detail below with reference to the accompanying drawings, and as shown in fig. 1-5, an aircraft engine thrust detection apparatus includes a base 1, the base 1 is fixedly mounted on the ground, a test hole 2 is formed in a middle position of an upper surface of the base 1, a pressure device 3 is arranged in the base 1, the pressure device 3 is composed of a slider 4 sleeved in the test hole 2, a pressure plate 5 located in the slider 4 and slidably connected with an inner side surface of the slider 4, pressure sensors 6 located below the pressure plate 5 and fixedly connected with a lower surface of the pressure plate 5 and uniformly distributed, and a signal connector 7 located on a right side of the pressure sensors 6 and fixedly connected with a middle position below a right side surface of the pressure sensors 6, a fixing device 8 is arranged above the pressure plate 5, and the fixing device 8 is composed of a sliding groove 9, a sliding, A bearing slide block 10 positioned in the sliding groove 9 and connected with the sliding groove 9 in a sliding manner, a bearing frame 11 positioned above the bearing slide block 10 and fixedly connected with the upper surface of the bearing slide block 10, a contact plate 12 positioned on the right side of the bearing frame 11 and fixedly connected with the middle position above the right side surface of the bearing frame 11, a bearing shaft I13 positioned in front of the contact plate 12 and fixedly connected with the front surface of the contact plate 12, a bearing sleeve I14 sleeved outside the bearing shaft I13 and rotatably connected with the bearing shaft I13, a bearing shaft II 15 positioned behind the contact plate 12 and fixedly connected with the rear surface of the contact plate 12, and a bearing sleeve II 16 sleeved outside the bearing shaft II 15 and rotatably connected with the bearing shaft II 15, wherein a fastening device 17 is arranged above the fixing device 8, and the fastening device 17 comprises a front connecting shaft 18 positioned above the bearing sleeve I14 and fixedly connected with the upper surface of the bearing sleeve I14, a front connecting piece 19 sleeved outside the front connecting shaft 18 and rotatably connected with the front connecting shaft, A first mounting hole 20 formed in the middle of the rear surface of the front connecting piece 19, a rear connecting shaft 21 fixedly connected with the upper surface of the second bearing sleeve 16 and positioned above the second bearing sleeve 16, a rear connecting piece 22 rotatably connected with the rear connecting shaft 21 and sleeved outside the rear connecting shaft 21, a second mounting hole 23 formed in the middle of the front surface of the rear connecting piece 22, a main hydraulic cylinder 25 with a base sleeved in the second mounting hole 23 and a telescopic end sleeved in the first mounting hole 20, an oil inlet pipe 26 fixedly connected with the front of the middle of the upper surface of the main hydraulic cylinder 25 and positioned above the main hydraulic cylinder 25, and an oil outlet pipe 27 fixedly connected with the rear of the middle of the upper surface of the main hydraulic cylinder 25 and positioned above the main hydraulic cylinder 25; an auxiliary frame 28 is arranged on the right side of the bearing frame 11 in the fixing device 8, an auxiliary hydraulic cylinder 29 is arranged on the right side of the auxiliary frame 28, and an auxiliary sleeve 30 is arranged at the telescopic end of the auxiliary hydraulic cylinder 29; four corners above the base 1 are provided with protection columns 31; an air inlet device 32 is arranged between the protection columns 31, and the air inlet device 32 is composed of a fan frame 33 which is positioned above the base 1 and two ends of which are respectively fixedly connected with the middle position of the protection column 31, a fan mounting hole 34 which is arranged at the middle position of the fan frame 33, and an auxiliary fan 36 which is positioned in the fan mounting hole 34 and is fixedly connected with the fan frame 33; an air pressure sensor 37 is arranged in the middle of the inner side surface of the protection column 31; a liquid crystal display screen 38 is arranged in the middle of the front surface of the base 1, and a control panel 39 is arranged on the right side of the liquid crystal display screen 38; a balancing device 40 is arranged behind the sliding groove 9, and the balancing device 40 is composed of a gear rack 41 which is positioned behind the sliding groove 9 and fixedly connected with the upper surface of the pressure plate 5, a balancing motor seat 42 which is positioned behind the bearing slider 10 and fixedly connected with the rear surface of the bearing slider 10, a balancing motor 43 which is sleeved in the balancing motor seat 42 and a driving gear 44 which is sleeved outside the output shaft of the balancing motor 43; a protection net 35 is arranged behind the auxiliary fan 36, and the protection net 35 is fixedly connected with the outer side surface of the auxiliary fan 36; the right side of the upper surface of the pressure plate 5 is provided with a fixing part which is symmetrical with the fixing device 8 and has the same structure; an oil tank 24 is arranged in the base 1, the main hydraulic cylinder 25, the oil inlet pipe 26, the oil outlet pipe 27 and the auxiliary hydraulic cylinder 29 are connected through oil pipes, and the signal connector 7, the auxiliary fan 36, the air pressure sensor 37, the liquid crystal display screen 38, the control panel 39 and the balance motor 43 are electrically connected.
The embodiment is characterized in that the base is fixedly arranged on the ground, a test hole is formed in the middle position of the upper surface of the base, a pressure device is arranged in the base and consists of a sliding part sleeved in the test hole, a pressure plate positioned in the sliding part and slidably connected with the inner side surface of the sliding part, pressure sensors positioned below the pressure plate and fixedly connected with the lower surface of the pressure plate and uniformly distributed, and a signal connector positioned on the right side of the pressure sensors and fixedly connected with the middle position below the right side surface of the pressure sensor, a fixing device is arranged above the pressure plate and consists of a sliding groove formed in the middle position of the upper surface of the pressure plate, a bearing slide block positioned in the sliding groove and slidably connected with the sliding groove, a bearing frame positioned above the bearing slide block and fixedly connected with the upper surface of the bearing slide block, a contact plate positioned on the right side of the bearing frame, A first bearing shaft positioned in front of the contact plate and fixedly connected with the front surface of the contact plate, a first bearing sleeve sleeved outside the first bearing shaft and rotatably connected with the first bearing shaft, a second bearing shaft positioned behind the contact plate and fixedly connected with the rear surface of the contact plate, and a second bearing sleeve sleeved outside the second bearing shaft and rotatably connected with the second bearing shaft, wherein a fastening device is arranged above the fastening device, and the fastening device comprises a front connecting shaft positioned above the first bearing sleeve and fixedly connected with the upper surface of the first bearing sleeve, a front connecting member sleeved outside the front connecting shaft and rotatably connected with the front connecting shaft, a first mounting hole formed in the middle position of the rear surface of the front connecting member, a rear connecting shaft positioned above the second bearing sleeve and fixedly connected with the upper surface of the second bearing sleeve, a rear connecting member sleeved outside the rear connecting shaft and rotatably connected with the rear connecting shaft, a second mounting hole formed in the middle position of the front, The base is sleeved in the second mounting hole, the telescopic end of the base is sleeved in the first mounting hole, the main hydraulic cylinder is positioned above the main hydraulic cylinder and fixedly connected with the front of the middle position of the upper surface of the main hydraulic cylinder, and the oil inlet pipe is positioned above the main hydraulic cylinder and fixedly connected with the rear of the middle position of the upper surface of the main hydraulic cylinder.
In the embodiment, before the aircraft engine is placed in the testing device, the parameters of the pressure sensor are reset through the control panel, then the position of the fixing device on the pressure plate is adjusted, then the aircraft engine is placed in the middle of the two fixing devices, the fixing devices are continuously adjusted to enable the first bearing sleeve and the second bearing sleeve to be attached to the outer surface of the aircraft engine, then the main hydraulic cylinder in the fastening device is started to enable the first bearing sleeve and the second bearing sleeve to tightly hold the outer surface of the aircraft engine, then the auxiliary hydraulic cylinder in the auxiliary frame is started to assist in fixing the aircraft engine, then the balancing device finely adjusts the position of the fixing device to enable the pressure sensor below the pressure plate to be stressed uniformly, then the auxiliary fan in the air inlet device is started to change the air pressure of the air inlet of the aircraft engine, and the thrust values under different conditions are.
The technical solutions described above only represent the preferred technical solutions of the present invention, and some possible modifications to some parts of the technical solutions by those skilled in the art all represent the principles of the present invention, and fall within the protection scope of the present invention.
Claims (10)
1. The utility model provides an aeroengine thrust check out test set, includes base (1), its characterized in that, base (1) fixed mounting is subaerial, base (1) upper surface intermediate position is opened there is test hole (2), be equipped with pressure device (3) in base (1), pressure device (3) by suit slider (4) in test hole (2), be located slider (4) and with slider (4) inboard surface sliding connection's pressure plate (5), be located pressure plate (5) below and pressure plate (5) lower fixed surface be connected and evenly distributed's pressure sensor (6) and be located pressure sensor (6) right side and with pressure sensor (6) right side surface below intermediate position fixed connection's signal connector (7) constitute jointly, pressure plate (5) top is equipped with fixing device (8), fixing device (8) by opening sliding tray (9) in pressure plate (5) upper surface intermediate position, A bearing slide block (10) which is positioned in the sliding groove (9) and is in sliding connection with the sliding groove (9), a bearing frame (11) which is positioned above the bearing slide block (10) and is fixedly connected with the upper surface of the bearing slide block (10), a contact plate (12) which is positioned at the right side of the bearing frame (11) and is fixedly connected with the middle position above the right side surface of the bearing frame (11), a bearing shaft I (13) which is positioned in front of the contact plate (12) and is fixedly connected with the front surface of the contact plate (12), a bearing sleeve I (14) which is sleeved outside the bearing shaft I (13) and is rotatably connected with the bearing shaft I (13), a bearing shaft II (15) which is positioned behind the contact plate (12) and is fixedly connected with the rear surface of the contact plate (12) and a bearing sleeve II (16) which is sleeved outside the bearing shaft II (15) and is rotatably connected with the bearing shaft II (15) are jointly formed, and a, the fastening device (17) comprises a front connecting shaft (18) which is positioned above the first bearing sleeve (14) and fixedly connected with the upper surface of the first bearing sleeve (14), a front connecting piece (19) which is sleeved outside the front connecting shaft (18) and rotatably connected with the front connecting shaft (18), a first mounting hole (20) which is formed in the middle position of the rear surface of the front connecting piece (19), a rear connecting shaft (21) which is positioned above the second bearing sleeve (16) and fixedly connected with the upper surface of the second bearing sleeve (16), a rear connecting piece (22) which is sleeved outside the rear connecting shaft (21) and rotatably connected with the rear connecting shaft (21), a second mounting hole (23) which is formed in the middle position of the front surface of the rear connecting piece (22), a main hydraulic cylinder (25) which is sleeved in the second mounting hole (23) and provided with a telescopic end in the first mounting hole (20), an oil inlet pipe (26) which is positioned above the main hydraulic cylinder (25) and fixedly connected with the middle position of the upper surface of the main hydraulic cylinder (25) and an oil inlet pipe (25) An oil outlet pipe (27) fixedly connected with the rear part of the middle position of the upper surface.
2. The aircraft engine thrust detection device of claim 1, wherein an auxiliary frame (28) is arranged on the right side of the bearing frame (11) in the fixing device (8), an auxiliary hydraulic cylinder (29) is arranged on the right side of the auxiliary frame (28), and an auxiliary sleeve (30) is arranged at the telescopic end of the auxiliary hydraulic cylinder (29).
3. The aircraft engine thrust detection device according to claim 1, wherein protection columns (31) are arranged at four corners above the base (1).
4. The aircraft engine thrust detection device according to claim 3, wherein an air intake device (32) is arranged between the protection columns (31), and the air intake device (32) is composed of a fan frame (33) which is positioned above the base (1) and two ends of which are respectively fixedly connected with the middle position of the protection column (31), a fan mounting hole (34) which is formed in the middle position of the fan frame (33), and an auxiliary fan (36) which is positioned in the fan mounting hole (34) and is fixedly connected with the fan frame (33).
5. The aircraft engine thrust detection device according to claim 3, characterized in that an air pressure sensor (37) is arranged in the middle of the inner side surface of the protection column (31).
6. The aircraft engine thrust detection device according to claim 1, wherein a liquid crystal display (38) is arranged in the middle of the front surface of the base (1), and a control panel (39) is arranged on the right side of the liquid crystal display (38).
7. The aircraft engine thrust detection device according to claim 1, wherein a balancing device (40) is arranged behind the sliding groove (9), and the balancing device (40) is composed of a gear rack (41) which is arranged behind the sliding groove (9) and fixedly connected with the upper surface of the pressure plate (5), a balancing motor base (42) which is arranged behind the bearing sliding block (10) and fixedly connected with the rear surface of the bearing sliding block (10), a balancing motor (43) sleeved in the balancing motor base (42), and a driving gear (44) sleeved outside an output shaft of the balancing motor (43).
8. The aircraft engine thrust detection device according to claim 4, wherein a protection net (35) is arranged behind the auxiliary fan (36), and the protection net (35) is fixedly connected with the outer side surface of the auxiliary fan (36).
9. The aircraft engine thrust detection device according to claim 1, characterized in that the pressure plate (5) is provided, on the right of its upper surface, with a fixing portion symmetrical and structurally identical to the fixing means (8).
10. The aircraft engine thrust detection device according to claim 1, wherein an oil tank (24) is arranged in the base (1), the main hydraulic cylinder (25), the oil inlet pipe (26), the oil outlet pipe (27) and the auxiliary hydraulic cylinder (29) are connected through oil pipes, and the signal connector (7), the auxiliary fan (36), the air pressure sensor (37), the liquid crystal display screen (38), the control panel (39) and the balance motor (43) are electrically connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810061045.8A CN108362426B (en) | 2018-01-22 | 2018-01-22 | Aeroengine thrust detection equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810061045.8A CN108362426B (en) | 2018-01-22 | 2018-01-22 | Aeroengine thrust detection equipment |
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| Publication Number | Publication Date |
|---|---|
| CN108362426A CN108362426A (en) | 2018-08-03 |
| CN108362426B true CN108362426B (en) | 2020-06-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810061045.8A Active CN108362426B (en) | 2018-01-22 | 2018-01-22 | Aeroengine thrust detection equipment |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110702293A (en) * | 2019-11-28 | 2020-01-17 | 北京航天三发高科技有限公司 | Supersonic engine test bed air inlet thrust measuring device and using method |
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| SU1758454A2 (en) * | 1990-10-17 | 1992-08-30 | Конструкторское бюро химического машиностроения | Device for measuring engine thrust force |
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN102788698A (en) * | 2012-08-13 | 2012-11-21 | 中国航天科技集团公司第四研究院四0一所 | Ground rotation testing device for solid rocket engine |
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN103217295A (en) * | 2013-03-28 | 2013-07-24 | 南京航空航天大学 | Ground test rack system of aviation piston engine |
| CN103353399A (en) * | 2013-07-03 | 2013-10-16 | 山河智能装备股份有限公司 | Mechanical performance testing table for piston engine |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
-
2018
- 2018-01-22 CN CN201810061045.8A patent/CN108362426B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1758454A2 (en) * | 1990-10-17 | 1992-08-30 | Конструкторское бюро химического машиностроения | Device for measuring engine thrust force |
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN102788698A (en) * | 2012-08-13 | 2012-11-21 | 中国航天科技集团公司第四研究院四0一所 | Ground rotation testing device for solid rocket engine |
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN103217295A (en) * | 2013-03-28 | 2013-07-24 | 南京航空航天大学 | Ground test rack system of aviation piston engine |
| CN103353399A (en) * | 2013-07-03 | 2013-10-16 | 山河智能装备股份有限公司 | Mechanical performance testing table for piston engine |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
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Effective date of registration: 20200526 Address after: 312000 No. 1439 Wenchang Road, Lanting Street, Keqiao District, Shaoxing City, Zhejiang Province Applicant after: Shaoxing Xiuzhen New Energy Technology Co.,Ltd. Address before: Debio Street Town, Nong'an County in Jilin province Nong'an 130200 Changchun Municipal Committee of five group 47 Applicant before: Zhao Guoqing |
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