CN101464215A - Propulsion test device of piezo-electricity type rocket motor - Google Patents
Propulsion test device of piezo-electricity type rocket motor Download PDFInfo
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- CN101464215A CN101464215A CNA2009100101285A CN200910010128A CN101464215A CN 101464215 A CN101464215 A CN 101464215A CN A2009100101285 A CNA2009100101285 A CN A2009100101285A CN 200910010128 A CN200910010128 A CN 200910010128A CN 101464215 A CN101464215 A CN 101464215A
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Abstract
The invention provides a piezoelectric device for testing the thrust of a rocket engine. The testing device belongs to the technical field of sensing measurement and control. The invention particularly relates to the rocket thrust testing technology. The testing device comprises a casing, two piezoelectric quartz crystal groups, a rear flange, a front flange, three upright posts, a lead wire, a lead wire joint and an installation bolt. The upper surface of the casing adopts a stepped structure; left and right elastic pre-tightening rings on the lower surface and the bottom surface of a rear flange installation platform are arranged on the same plane; and projections are formed on the bottom surfaces of left and right fixed ends. The casing part has the characteristics that an integrated structure is adopted, the rigidity is relatively high, the problem that the testing system requires not only a movable bracket but also a fixed bracket is solved, the natural frequency is high, and the measuring accuracy of dynamic force is high. With only two piezoelectric quartz crystal groups, the device has the advantages of simple structure and convenient installation and adjustment. By adopting a combination of a plurality of quartz crystal pieces to improve the sensitivity, the device has good measuring stability. By adopting a tri-upright post structure, the device has sufficient space to install a fuel tube and a solenoid valve, thereby achieving accurate transferring of thrust, and satisfying the requirements of a dynamic force test.
Description
Technical field
A kind of propulsion test device of piezo-electricity type rocket motor of the present invention belongs to sensing observation and control technology field, particularly rocket thrust measuring technology.
Background technology
Aeronautical and space technology is one of modern science and technology field of high integrity, its development be unable to do without the raising of rocket engine development level, and the innovation of rocket engine technology be unable to do without design analysis and experimental test development of technology, and rocket engine thrust measuring technology all is the emphasis that the Engine Block Test field is paid close attention to all the time.Rocket engine is the important component part of modern space aircraft, is widely used in space shuttle, airship, power blocker, satellite and multistage vehicle, and main effect is track control, attitude adjustment, end speed correction etc.Thrust is an important parameter of reflection engine performance index, directly reflects the design performance of engine, and therefore, the thrust test becomes one of gordian technique of engine test.The accurate measurement of rocket engine pulsation thrust has very important significance for spacecraft correction posture adjustment, can not only make aircraft promptly and accurately adjust to suitable attitude, can also avoid adjusting repeatedly the waste of fuel that causes, prolong the serviceable life of aircraft.
Generally adopt strain gauge transducer to measure rocket thrust at present both at home and abroad, " Chinese measuring technology " periodical was rolled up in the 2nd interim article of publishing " design of low thrust liquid-propellant rocket engine dynamic thrust testboard bay " March the 33rd in 2007, adopt strain gauge transducer to design low thrust liquid-propellant rocket engine dynamic thrust testboard bay in a kind of 100N scope, " rocket propulsion " periodical was rolled up in the 6th interim article of publishing " development of electromechanical integration Thrust Measuring System and application " Dec the 30th in 2004, had adopted a kind of strain pressure transducer that rocket engine thrust is tested.In the described strain-type test macro of above-mentioned document, in order to produce bigger strain, all adopted on the structure and decided the form that frame separates with moving frame, decide to adopt between frame and the moving frame spring leaf to connect, cause the natural frequency of test macro lower, there is bigger hysteresis error in dynamic force measurement, needs to adopt the mode of compensation to improve precision.Piezoelectric quartz formula force transducer is a kind of micro-displacement sensor, and advantage such as have rigidity height, good linearity, sluggishness is little, natural frequency is high, particularly high the and stability of insulation impedance is outstanding is highly suitable for various dynamic force measurements.The piezoelectric transducer measuring accuracy is not as strain gauge transducer aspect static force or quasi-static force measurement, mainly be because piezoelectric transducer exists charge leakage and drift, but, can make its static properties satisfy test request by improving requirement to the insulation impedance and the sealing protection of piezoelectric quartz sensor.In addition, strain gauge transducer is subjected to Temperature Influence easily, and long-time stability are bad, and serviceable life is low, and quartz crystal Curie temperature height is not vulnerable to temperature effect, and ageing rate is low, long service life.
Summary of the invention
The technical barrier that the present invention will solve is to overcome the shortcoming that above-mentioned prior art exists, solve the strain-type method of testing since moving frame with decide frame and separate the problem that causes the dynamic measurement precision difference.At the characteristics and the measurement requirement of rocket engine,, invented a kind of propulsion test device of piezo-electricity type rocket motor in conjunction with the good characteristic of piezoelectric quartz force sensor kinetic measurement.This propulsion test device of piezo-electricity type rocket motor is a core with the brilliant group of two groups of piezoelectric quartzes, adopted the integral housing structure, have higher rigidity and natural frequency, eliminated and moved frame in traditional strain-type test macro and decide frame separated structures form, can directly rocket engine be installed to and carry out the thrust test on this proving installation, the dynamic force measurement precision is higher, has that structure is simple and direct, to debug convenience, precision height, cost low.
The technical solution used in the present invention is: a kind of propulsion test device of piezo-electricity type rocket motor is by housing 8, the two groups of brilliant group of piezoelectric quartz 2,2 ＇, rear flange 7, forward flange 5, three column 4,4 ＇, 4 ", lead-in wire 1, pigtail splice 9 and mounting screw form; The upper surface of its middle shell 8 adopts stepped construction, the bottom surface of lower surface left side elasticity preload ring f, right elasticity preload ring f ＇ and rear flange mounting platform j at grade, a part is protruded in the bottom surface of left stiff end b and right stiff end b ＇; There is the lower-left can adjust mounting hole k ", the upper left mounting hole k that adjusts " ' on the left stiff end b of housing 8, lead-in wire 1 is outwards drawn by horizontal lead wire hole d, vertical leads hole c, pigtail splice 9 is equipped with in the centre, side of left side stiff end b, and lead-in wire 1 is by outside pigtail splice 9 lead bodies; Have on the right stiff end b of housing 8 upper rightly adjust mounting hole k, mounting hole k ＇ can be adjusted in the bottom right; Left elasticity preload ring f on the housing 8 and right elasticity preload ring f ＇ have all adopted the semicircular ring structure up and down, and the centre has left groove e and right groove e ＇, and brilliant group 2 of left piezoelectric quartz and the brilliant group of right piezoelectric quartz 2 ＇ are respectively charged into the center of left groove e and right groove e ＇; Third side's block structure of housing 8 is rear flange mounting platform j, and 3 uniform retaining thread hole i are arranged on it, and the center has pilot hole g and housing center pit h; Adopt 3 attachment screws 6 respectively by 3 sunk screw connecting hole r on the rear flange 7 with rear flange 7 and upper left column 4, upper right column 4 ＇ and intermediate column 4 " an end be rigidly connected; Adopt 3 attachment screws 6 respectively by 3 connecting hole n on the forward flange 5 with forward flange 5 and upper left column 4, upper right column 4 ＇ and intermediate column 4 " the other end be rigidly connected; it is the bar p of rectangle that there is the cross section centre of forward flange 5; there is bar center pit q at its center; 3 rocket retaining thread hole o are arranged on the forward flange 5, is used for rocket engine and forward flange 5 are rigidly connected; Adopt 3 screws 3 respectively by 3 fixed orifice r on the rear flange 7 with the rear flange 7, upper left column 4, upper right column 4 ＇, the intermediate column 4 that link together ", forward flange 5 is rigidly connected with housing 8.
3 retaining thread hole i on the rear flange mounting platform j are uniform, are the zero degree line with u-u ＇ line, and its position angle is respectively 90 °, 210 °, 330 °; 3 connecting hole n on the forward flange 5 are uniform, are the zero degree line with m-m ＇ line, and its position angle is respectively 30 °, 150 °, 270 °; 3 rocket retaining thread holes on the forward flange 5.Uniform, be the zero degree line with m-m ＇ line, its position angle is respectively 90 °, 210 °, 330 °; Rear flange 7 is that last 3 sunk screw connecting hole r are uniform, is the zero degree line with t-t ＇ line, and its position angle is respectively 30 °, 150 °, 270 °; Rear flange 7 is that last 3 fixed orifice s are uniform, is the zero degree line with t-t ＇ line, and its position angle is respectively 90 °, 210 °, 330 °.
Remarkable result of the present invention is: housing has adopted monolithic construction, tested engine can directly be fixed on the forward flange 5, because the rigidity of left elasticity preload ring f and right elasticity preload ring f ＇ is higher, its displacement is minimum in test, and deadweight is very little, so inertial force is less to the influence of proving installation.Adopt the three-upright-post structure between forward flange 5 and the rear flange 7, have enough space mounting cartridge and solenoid valve, can realize the accurate transmission of thrust, satisfy the dynamic force test requirement.This proving installation has been eliminated and has been moved frame in traditional strain-type test macro and decide frame separated structures form, has higher rigidity and natural frequency, the dynamic measurement precision height.
Description of drawings
Fig. 1 is the propulsion test device of piezo-electricity type rocket motor three-dimensional plot, and Fig. 2 is the shell structure vertical view, and Fig. 3 is the A-A cut-open view of Fig. 2, and Fig. 4 is the forward flange structural drawing, and Fig. 5 is the rear flange structural drawing.Wherein 1-goes between, the brilliant group of 2-left side piezoelectric quartz, and 2 ＇-right piezoelectric quartz is brilliant to be organized, the 3-screw, the upper left column of 4-, 4 ＇-upper right column, 4 " intermediate column, 5-forward flange, 6-attachment screw; 7-rear flange, 8-housing, 9-pigtail splice; a-pigtail splice threaded hole, b-left side stiff end, b ＇-right stiff end; c-vertical leads hole, d-horizontal lead wire hole, e-left side groove; e ＇-right groove, f-left side elasticity preload ring, f ＇-right elasticity preload ring; g-pilot hole, h-housing center pit, i-retaining thread hole, j-rear flange mounting platform, the upper right mounting hole of adjusting of k-, mounting hole can be adjusted in k ＇-bottom right, k " mounting hole, k can be adjusted in the lower-left " '-upper left mounting hole of adjusting, the n-connecting hole, o-rocket retaining thread hole, p-bar, q-bar center pit, r-sunk screw connecting hole, the s-fixed orifice.
Embodiment
Describe the specific embodiment of the present invention in detail with technical scheme in conjunction with the accompanying drawings, shown in accompanying drawing 1,2,3,4, during assembling brilliant group 2 of left piezoelectric quartz and right piezoelectric quartz crystalline substance are organized the centre that 2 ＇ are respectively charged into left groove e and right groove e ＇, and certain magnitude of interference is arranged, to obtain enough pretightning forces.Adopted the unit crystal groups of 3 pairs of yx types among brilliant group 2 of left side piezoelectric quartz and the brilliant group of right piezoelectric quartz 2 ＇ respectively, the every pair of brilliant group with the unit wafer of two yx types to dress, the peak response direction strict conformance of each wafer and brilliant group, signal is drawn by the electrode slice between the wafer, with 3 pairs of brilliant groups draw the signal parallel connection, by charge amplifier output display voltage value.Adopt 4 screws to adjust by upper right that mounting hole k, bottom right can adjust mounting hole k ＇, the lower-left can be adjusted mounting hole k " and the upper left mounting hole k that adjusts " ' this propulsion test device of piezo-electricity type rocket motor is fixed on the pedestal respectively, require the bottom surface of left elasticity preload ring f, right elasticity preload ring f ＇, rear flange mounting platform j not contact with pedestal, pilot hole g is used for this proving installation is carried out installing and locating, during installation with it in the protrusion locating ring that installs to pedestal.Before and after the rocket thrust test, need earlier this proving installation to be carried out static demarcating, before the static demarcating at first with a bar center pit q who passes forward flange 5 centers of a seizing wire, be fixed on the cover hydraulic loading device after passing housing center pit h again, with the end knotting of wire rope at bar center pit q, hydraulic loading device can draw the bar p on the forward flange 5 to come to apply a power to proving installation by wire rope then.The thrust that produces during the rocket eruption is by forward flange 5, upper left column 4, upper right column 4 ＇, intermediate column 4 "; rear flange 7 is delivered on the rear flange mounting platform j; the friction force between dependence groove face and the piezoelectric quartz crystalline substance group is organized this thrust decomposition on 2 ＇ to brilliant group 2 of left piezoelectric quartz and right piezoelectric quartz crystalline substance; produce electric charge on the quartz crystal surface; by electrode slice electric charge is drawn out in the charge amplifier and amplifies; and convert voltage signal output to, through the A/D data collecting card simulating signal is become the digital signal that computing machine is accepted, the input computing machine, machine collection as calculated, handle, draw each major parameter of institute's fire detecting arrow engine after the computing, show by terminal at last, storage, analyze, record, print.
This propulsion test device of piezo-electricity type rocket motor has higher sensitivity and natural frequency, dynamic measurement precision is higher, need not to adopt the mode of compensation to improve precision, can directly carry out the thrust test, be particularly useful for the dynamic test of low-thrust rocket rocket engine.In addition, this proving installation only needs the brilliant group of two groups of piezoelectric quartzes, and structure is simple and direct, and is easy to operate.
Claims (2)
1. propulsion test device of piezo-electricity type rocket motor, it is characterized in that, proving installation by housing (8), the brilliant group of two groups of piezoelectric quartzes (2,2 '), rear flange (7), forward flange (5), three columns (4,4 ', 4 "), lead-in wire (1), pigtail splice (9) and mounting screw form; The upper surface of its middle shell (8) adopts stepped construction, the bottom surface of lower surface left side elasticity preload ring (f), right elasticity preload ring (f ') and rear flange mounting platform (j) at grade, the bottom surface of left stiff end (b) and right stiff end (b ') is protruded a part of; There is the lower-left can adjust mounting hole (k "), the upper left mounting hole (k " ') of adjusting on the left stiff end (b) of housing (8), lead-in wire (1) is outwards drawn by horizontal lead wire hole (d), vertical leads hole (c), pigtail splice (9) is equipped with in the centre, side of left side stiff end (b), and lead-in wire (1) is by outside pigtail splice (9) lead body; Have on the right stiff end (b) of housing (8) upper rightly adjust mounting hole (k), mounting hole (k ') can be adjusted in the bottom right; The left elasticity preload ring (f) on the housing (8) and the structure of employing semicircular ring up and down of right elasticity preload ring (f '), the centre has left groove (e) and right groove (e '), and the brilliant group of brilliant group of left piezoelectric quartz (2) and right piezoelectric quartz (2 ') is respectively charged into the center of left groove (e) and right groove (e '); Third side's block structure of housing (8) is rear flange mounting platform (j), and 3 uniform retaining thread holes (i) are arranged on it, and the center of rear flange mounting platform (j) has pilot hole (g) and housing center pit (h); (end of 4 ") is rigidly connected with upper left column (4), upper right column (4 ') and intermediate column with rear flange (7) by 3 the sunk screw connecting holes (r) on the rear flange (7) respectively to adopt 3 attachment screws (6); Adopt 3 attachment screws (6) respectively by 3 connecting holes (n) on the forward flange (5) with forward flange (5) and upper left column (4), upper right column (4 ') and intermediate column (other end of 4 ") is rigidly connected; it is the bar (p) of rectangle that there is the cross section centre of forward flange (5); there is bar center pit (q) at its center; 3 rocket retaining thread holes (o) are arranged on the forward flange (5), is used for rocket engine and forward flange (5) are rigidly connected; (4 "), forward flange (5) are rigidly connected with housing (8) with the rear flange (7) that links together, upper left column (4), upper right column (4 '), intermediate column by 3 fixed orifices (r) on the rear flange (7) respectively to adopt 3 screws (3).
2. according to the described a kind of propulsion test device of piezo-electricity type rocket motor of claim 1, it is characterized in that 3 the retaining thread holes (i) on the rear flange mounting platform (j) are uniform, are the zero degree line with u-u ' line, its position angle is respectively 90 °, 210 °, 330 °; 3 connecting holes (n) on the forward flange (5) are uniform, are the zero degree line with m-m ' line, and its position angle is respectively 30 °, 150 °, 270 °; 3 rocket retaining thread holes (o) on the forward flange (5) are uniform, are the zero degree line with m-m ' line, and its position angle is respectively 90 °, 210 °, 330 °; 3 sunk screw connecting holes (r) on the rear flange (7) are uniform, are the zero degree line with t-t ' line, and its position angle is respectively 30 °, 150 °, 270 °; 3 fixed orifices (s) on the rear flange (7) are uniform, are the zero degree line with t-t ' line, and its position angle is respectively 90 °, 210 °, 330 °.
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| Application Number | Priority Date | Filing Date | Title |
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| CNA2009100101285A CN101464215A (en) | 2009-01-15 | 2009-01-15 | Propulsion test device of piezo-electricity type rocket motor |
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| Application Number | Priority Date | Filing Date | Title |
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| CNA2009100101285A CN101464215A (en) | 2009-01-15 | 2009-01-15 | Propulsion test device of piezo-electricity type rocket motor |
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| CN101464215A true CN101464215A (en) | 2009-06-24 |
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| CNA2009100101285A Pending CN101464215A (en) | 2009-01-15 | 2009-01-15 | Propulsion test device of piezo-electricity type rocket motor |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101813537A (en) * | 2010-03-18 | 2010-08-25 | 北京理工大学 | Micro-thruster array testing table |
| CN102519643A (en) * | 2011-12-13 | 2012-06-27 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Six-component force measuring system of engine vector spray pipe |
| CN102818676A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Thrust rack in-situ calibration system |
| 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 |
| CN103267642A (en) * | 2013-05-24 | 2013-08-28 | 北京航空航天大学 | Engine thrust frame suitable for measuring thrust from 1N to 300N |
| CN105300699A (en) * | 2015-11-20 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for evaluating engine thrust transient performance |
| CN105649817A (en) * | 2015-12-31 | 2016-06-08 | 西安航天动力试验技术研究所 | Vector thrust loading device for attitude control engine |
| CN104483131B (en) * | 2014-12-24 | 2016-09-14 | 武汉大学 | A kind of solid appearance control dynamical system test bed device |
| CN106014691A (en) * | 2016-07-29 | 2016-10-12 | 北京航天试验技术研究所 | Vacuum-thrust-vector measurement system capable of adjusting rocket-motor swinging direction in real time |
| CN106441675A (en) * | 2016-11-08 | 2017-02-22 | 烟台职业学院 | Non-load-sharing piezoelectric thrust test device |
| CN106595935A (en) * | 2016-12-14 | 2017-04-26 | 中国燃气涡轮研究院 | Aero-engine vector force test stand capable of realizing self-decoupling |
| CN106596108A (en) * | 2016-11-04 | 2017-04-26 | 上海新力动力设备研究所 | Inclined-jet-pipe solid rocket engine test rack of quick assembly type |
| CN107421684A (en) * | 2017-07-28 | 2017-12-01 | 大连理工大学 | Multidimensional Composite Nozzle device unit thrust calculation method |
| CN107831015A (en) * | 2017-10-24 | 2018-03-23 | 大连理工大学 | A kind of high thrust solid propellant rocket piezoelectric tester |
| CN107860504A (en) * | 2017-10-10 | 2018-03-30 | 西安航天动力试验技术研究所 | The Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine |
| CN107870053A (en) * | 2017-10-10 | 2018-04-03 | 西安航天动力试验技术研究所 | A kind of attitude control engine thrust-measuring device |
| CN108362426A (en) * | 2018-01-22 | 2018-08-03 | 赵国庆 | A kind of aeroengine thrust detection device |
| CN110411752A (en) * | 2019-08-07 | 2019-11-05 | 西安近代化学研究所 | A kind of solid propellant rocket high speed rotation test clamping device |
| CN117129222A (en) * | 2023-10-27 | 2023-11-28 | 天津市联众金属结构有限公司 | Engine reverse thrust test vehicle |
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| CN101813537B (en) * | 2010-03-18 | 2011-06-22 | 北京理工大学 | Micro-thruster array testing table |
| CN101813537A (en) * | 2010-03-18 | 2010-08-25 | 北京理工大学 | Micro-thruster array testing table |
| CN102519643A (en) * | 2011-12-13 | 2012-06-27 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Six-component force measuring system of engine vector spray pipe |
| CN102818676A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Thrust rack in-situ calibration system |
| 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 |
| CN102818671B (en) * | 2012-08-16 | 2014-06-18 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN102818676B (en) * | 2012-08-16 | 2014-07-02 | 北京航空航天大学 | Thrust rack in-situ calibration system |
| CN103267642A (en) * | 2013-05-24 | 2013-08-28 | 北京航空航天大学 | Engine thrust frame suitable for measuring thrust from 1N to 300N |
| CN103267642B (en) * | 2013-05-24 | 2015-08-19 | 北京航空航天大学 | A kind of motor power frame being applicable to measurement 1N to 300N thrust |
| CN104483131B (en) * | 2014-12-24 | 2016-09-14 | 武汉大学 | A kind of solid appearance control dynamical system test bed device |
| CN105300699B (en) * | 2015-11-20 | 2017-08-25 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of assessment method of motor power transient performance |
| CN105300699A (en) * | 2015-11-20 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for evaluating engine thrust transient performance |
| CN105649817A (en) * | 2015-12-31 | 2016-06-08 | 西安航天动力试验技术研究所 | Vector thrust loading device for attitude control engine |
| CN106014691B (en) * | 2016-07-29 | 2018-08-31 | 北京航天试验技术研究所 | A kind of vacuum thrust vector measurement system that can be adjusted rocket engine in real time and wave direction |
| CN106014691A (en) * | 2016-07-29 | 2016-10-12 | 北京航天试验技术研究所 | Vacuum-thrust-vector measurement system capable of adjusting rocket-motor swinging direction in real time |
| CN106596108A (en) * | 2016-11-04 | 2017-04-26 | 上海新力动力设备研究所 | Inclined-jet-pipe solid rocket engine test rack of quick assembly type |
| CN106596108B (en) * | 2016-11-04 | 2019-06-11 | 上海新力动力设备研究所 | One kind can the oblique jet pipe Solid Rocket Engine Test frame of quick assembled type |
| CN106441675A (en) * | 2016-11-08 | 2017-02-22 | 烟台职业学院 | Non-load-sharing piezoelectric thrust test device |
| CN106441675B (en) * | 2016-11-08 | 2019-02-26 | 烟台职业学院 | A kind of no load sharing piezoelectric type propulsion test device |
| CN106595935A (en) * | 2016-12-14 | 2017-04-26 | 中国燃气涡轮研究院 | Aero-engine vector force test stand capable of realizing self-decoupling |
| CN106595935B (en) * | 2016-12-14 | 2019-10-18 | 中国燃气涡轮研究院 | Rack can be measured from uncoupled aero-engine vectorial force |
| CN107421684A (en) * | 2017-07-28 | 2017-12-01 | 大连理工大学 | Multidimensional Composite Nozzle device unit thrust calculation method |
| CN107421684B (en) * | 2017-07-28 | 2019-06-07 | 大连理工大学 | Multidimensional Composite Nozzle device unit thrust calculation method |
| CN107870053B (en) * | 2017-10-10 | 2020-02-21 | 西安航天动力试验技术研究所 | Attitude control engine thrust measuring device |
| CN107870053A (en) * | 2017-10-10 | 2018-04-03 | 西安航天动力试验技术研究所 | A kind of attitude control engine thrust-measuring device |
| CN107860504A (en) * | 2017-10-10 | 2018-03-30 | 西安航天动力试验技术研究所 | The Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine |
| CN107860504B (en) * | 2017-10-10 | 2020-04-07 | 西安航天动力试验技术研究所 | Accurate dynamic thrust of appearance accuse engine measures calibration integrated device |
| CN107831015B (en) * | 2017-10-24 | 2019-06-07 | 大连理工大学 | A kind of high thrust solid propellant rocket piezoelectric tester |
| CN107831015A (en) * | 2017-10-24 | 2018-03-23 | 大连理工大学 | A kind of high thrust solid propellant rocket piezoelectric tester |
| CN108362426B (en) * | 2018-01-22 | 2020-06-30 | 绍兴市秀臻新能源科技有限公司 | Aeroengine thrust detection equipment |
| CN108362426A (en) * | 2018-01-22 | 2018-08-03 | 赵国庆 | A kind of aeroengine thrust detection device |
| CN110411752A (en) * | 2019-08-07 | 2019-11-05 | 西安近代化学研究所 | A kind of solid propellant rocket high speed rotation test clamping device |
| CN110411752B (en) * | 2019-08-07 | 2021-06-15 | 西安近代化学研究所 | Clamping device for high-speed rotation test of solid rocket engine |
| CN117129222A (en) * | 2023-10-27 | 2023-11-28 | 天津市联众金属结构有限公司 | Engine reverse thrust test vehicle |
| CN117129222B (en) * | 2023-10-27 | 2023-12-29 | 天津市联众金属结构有限公司 | Engine reverse thrust test vehicle |
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