CN204241143U - Free jet test motor power measurement mechanism - Google Patents
Free jet test motor power measurement mechanism Download PDFInfo
- Publication number
- CN204241143U CN204241143U CN201420422371.4U CN201420422371U CN204241143U CN 204241143 U CN204241143 U CN 204241143U CN 201420422371 U CN201420422371 U CN 201420422371U CN 204241143 U CN204241143 U CN 204241143U
- Authority
- CN
- China
- Prior art keywords
- frame
- connecting rod
- elasticity connecting
- engine
- measurement mechanism
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Testing Of Engines (AREA)
Abstract
The utility model belongs to Aeronautics and Astronautics technical field, is specifically related to a kind of free jet test motor power measurement mechanism.This device comprises moving frame, determines frame, for the axial elasticity connecting rod of measurement engine axial force measured and the longitudinal elasticity connecting rod for measuring engine lift to be measured; The measurement of engine axial force, lift and pitching moment when can realize engine complete machine free jet test by this device.
Description
Technical field
The utility model belongs to Aeronautics and Astronautics technical field, relates to a kind of device for airspace engine test, is specifically related to a kind of free jet test motor power measurement mechanism.
Background technology
Generally adopt the method for ground free jet test to obtain the overall performance of air suction type power engine at present both at home and abroad, wherein thrust parameter is one of important parameter characterizing engine performance.Therefore air suction type power engine thrust measurement technology seems most important.
In free jet test, high stagnation temperature high-Mach-number flow flows through test section, and wherein a part enters engine chamber, and in order to ensure that wind-tunnel starts smoothly, testpieces projected area is generally not more than 20% of test section area, and namely blockage ratio is less than 20%.
Current traditional rocket engine thrust frame adopt survey sensor and engine axis coaxially arranged, directly can affect engine charge according to this metering system, and blockage ratio is larger.Because in the process of carrying out engine free stream test, engine can produce component and a moment of both direction, the axial thrust of engine body, the lift of thrust perpendicular to axial direction and pitching moment respectively, but above-mentioned existing measurement mechanism can only measure engine axial thrust, obvious this metering system is not suitable for engine free stream test.
Along with carrying out in a deep going way of airbreathing motor research, need complete machine free jet test and motor power is measured, in order to adapt to reseach of engine needs, brand-new thrust measurement stand need be developed and obtain motor power parameter.
Utility model content
In order to solve the problem in background technology, the utility model proposes and a kind ofly meet the free jet test motor power measurement mechanism simultaneously can measuring engine axial thrust, lift and pitching moment in free jet test process.
Concrete technical scheme of the present utility model is:
A kind of free jet test motor power measurement mechanism, is characterized in that: comprise connect successively according to engine lift direction to be measured determine frame, longitudinal elasticity connecting rod and moving frame;
Described moving frame is made up of vertical rack and level frame; Engine to be measured is installed in the upper surface of described vertical rack, and lower surface is fixedly connected with level frame; Described level frame with determine frame keeping parallelism; Described longitudinal elasticity connecting rod has many groups and is evenly arranged in level frame and determines between frame;
The axial elasticity connecting rod set gradually to force direction according to engine shaft to be measured and force-bearing base;
Described force-bearing base is fixedly mounted on to be determined on frame; Described axial elasticity connecting rod has one group; Described axial elasticity connecting rod one end is connected with vertical rack, and the other end is connected with force-bearing base; The joint face of the joint face of described force-bearing base and axial elasticity connecting rod and level frame and axial elasticity connecting rod is parallel to each other;
Described axial elasticity connecting rod comprises a pair elastic hinge and is arranged on force snesor between two elastic hinges;
Described longitudinal elasticity connecting rod is identical with axial elasticity bar linkage structure.
Above-mentioned measurement mechanism also comprises the latch mechanism for limiting moving frame movement; Described latch mechanism comprises the multiple vertex of a cone assemblies being separately positioned on vertical rack both sides; Described vertex of a cone assembly comprises drive unit, is arranged on the holder of drive unit stiff end and is arranged on the vertex of a cone of drive unit movable end; Described holder with determine frame and be fixedly connected with.
Above-mentioned vertical rack is provided with taper hole; The quantity of described taper hole is consistent with the quantity of the vertex of a cone; The position of described taper hole and the position one_to_one corresponding of the vertex of a cone.
Above-mentionedly determine frame, vertical rack and level frame and all adopt steel frame construction, and shape is rectangle.
Above-mentioned drive unit adopts Driven by Hydraulic Cylinder.
The utility model has the advantage of:
1, the utility model adopts axial elasticity connecting rod and longitudinal elasticity connecting rod, and when achieving free jet test, the measurement of the axial force of complete machine Full-scale engine, lift and pitching moment, makes test effect greatly promote.
2, axial elasticity connecting rod of the present utility model and longitudinal elasticity connecting rod all adopt elastic hinge and force snesor unitized construction, and the machine decomposition of power is effective, have higher Buckling Load.Effectively reduce other component force and moments to measuring the interference of component, by is concerned about that measurement component is delivered to the force snesor of respective direction.
3, arrange latch mechanism in moving frame both sides in the utility model, when starting shooting when avoiding test or shut down, shock load is more greatly to the impact failure that moving frame, sensor and elastic hinge cause.
Accompanying drawing explanation
Fig. 1 is structure diagram of the present utility model.
Reference numeral is as follows:
1-moving frame, 11-vertical rack, 111-taper hole, 12-level frame, 2-determine frame, 3-axial elasticity connecting rod, 31-elastic hinge, 32-force snesor, 4-longitudinal elasticity connecting rod, 5-engine main body to be measured, 6-latch mechanism, 61-vertex of a cone assembly, 611-cylinder body, 612-holder, the 613-vertex of a cone, 7-force-bearing base.
Embodiment
The utility model, when carrying out carrying out free jet test to airspace engine, because the measurement mechanism of routine can only measure engine axial thrust, now devises a kind of measurement mechanism simultaneously can measuring engine axial thrust, lift and pitching moment.
Below by way of accompanying drawing 1, device of the present utility model is described:
Note: in figure, Fx is the axial force of engine to be measured, and Fy represents the lift of engine to be measured, Mz is the pitching moment of engine to be measured.
This measurement mechanism comprise connect successively according to engine lift direction to be measured determine frame 2, longitudinal elasticity connecting rod 4 and moving frame 1;
Specifically: moving frame 1 is made up of vertical rack 11 and level frame 12; Engine 5 to be measured is installed in the upper surface of vertical rack 11, and lower surface is fixedly connected with level frame 12; Level frame 11 with determine frame 2 keeping parallelism; Longitudinal elasticity connecting rod 4 has 4 groups and is evenly arranged in level frame 12 and determines between frame 2;
The axial elasticity connecting rod 3 set gradually to force direction according to engine shaft to be measured and force-bearing base 7;
Specifically: force-bearing base 7 is fixedly mounted on to be determined on frame 2; Axial elasticity connecting rod 3 has one group; This axial elasticity connecting rod 3 one end is connected with level frame 12, and the other end is connected with force-bearing base 7; Force-bearing base 7 is parallel to each other with the joint face of axial elasticity connecting rod 3 and the joint face of level frame 12 and axial elasticity connecting rod 3;
Axial elasticity connecting rod 3 comprises a pair elastic hinge 31 and is arranged on force snesor 32 between two elastic hinges;
Longitudinal elasticity connecting rod 4 is identical with axial elasticity connecting rod 3 structure, the force snesor 32 that each group longitudinal elasticity connecting rod also comprises a pair elastic hinge 31 and is arranged between two elastic hinges 31.
Special also have: determine frame 2 in this device, vertical rack 11, level frame 12 be rectangle and all adopt steel-frame structure, build skeleton, reduce quality, reach the matched well of rigidity and quality under the prerequisite of guarantee rigidity with shaped steel;
Special feature is also: due to the startup of wind-tunnel during test and when stopping shock load comparatively large, the normally several times of steady state (SS).Therefore in order to ensure that moving frame 1, elastic hinge 31, force snesor 32 are not destroyed under shock load, this measurement mechanism also comprises the latch mechanism 6 for limiting moving frame movement;
This latch mechanism 6 comprises the multiple vertex of a cone assemblies 61 being separately positioned on vertical rack 11 both sides; Vertex of a cone assembly 61 comprises drive unit 611, is arranged on the holder 612 of drive unit 611 stiff end and is arranged on the vertex of a cone 613 of drive unit 611 movable end; Holder 612 with determine frame 2 and be fixedly connected with.
Further, the locking in order to ensure latch mechanism is more reliable, safety, and the utility model is also provided with taper hole 111 on vertical rack 11; The quantity of taper hole 111 is consistent with the quantity of the vertex of a cone 613; The position of taper hole 111 and the position one_to_one corresponding of the vertex of a cone 613.
The load of operationally bearing due to latch mechanism is very large, therefore, drive unit adopts the mode of hydraulic pressure to drive vertex of a cone work, and can bear axial load and radial shear load (in fact this drive unit can also adopt the mode of cylinder or the mode of mechanical rotation).
According to the above-mentioned description to apparatus structure, now the practical application of this device is described:
During free jet test, engine produces axial thrust, lift and pitching moment three components; Axial elasticity connecting rod and longitudinal thrust connecting rod is passed to by comprehensively stressed for engine by moving frame, by can obtain the relational expression that axial thrust, lift and pitching moment represent by above-mentioned 5 survey sensor output valves to thrust-measuring device static demarcating, according to the size of the axial thrust of force snesor numerical evaluation present engine, lift and pitching moment.
During test, transient force is produced very large when wind-tunnel starts or stops, damage may be caused to measurement mechanism, therefore before wind-tunnel starts or stops, need, with the vertex of a cone on the vertex of a cone assembly of oil pressure ejection, to insert it into the taper hole on moving frame vertical rack, make moving frame and determine frame and be connected locked, formation is rigidly connected, and bears the shock load of instability during startup/parking.After flow field is stable, latch mechanism can carry out unlocking the vertex of a cone is exited taper hole.
Claims (5)
1. a free jet test motor power measurement mechanism, is characterized in that: comprise connect successively according to engine lift direction to be measured determine frame, longitudinal elasticity connecting rod and moving frame;
Described moving frame is made up of vertical rack and level frame; Engine to be measured is installed in the upper surface of described vertical rack, and lower surface is fixedly connected with level frame; Described level frame with determine frame keeping parallelism; Described longitudinal elasticity connecting rod has many groups and is evenly arranged in level frame and determines between frame;
The axial elasticity connecting rod set gradually to force direction according to engine shaft to be measured and force-bearing base;
Described force-bearing base is fixedly mounted on to be determined on frame; Described axial elasticity connecting rod has one group; Described axial elasticity connecting rod one end is connected with vertical rack, and the other end is connected with force-bearing base; The joint face of the joint face of described force-bearing base and axial elasticity connecting rod and level frame and axial elasticity connecting rod is parallel to each other;
Described axial elasticity connecting rod comprises a pair elastic hinge and is arranged on force snesor between two elastic hinges;
Described longitudinal elasticity connecting rod is identical with axial elasticity bar linkage structure.
2. free jet test motor power measurement mechanism according to claim 1, is characterized in that: described measurement mechanism also comprises the latch mechanism for limiting moving frame movement; Described latch mechanism comprises the multiple vertex of a cone assemblies being separately positioned on vertical rack both sides; Described vertex of a cone assembly comprises drive unit, is arranged on the holder of drive unit stiff end and is arranged on the vertex of a cone of drive unit movable end; Described holder with determine frame and be fixedly connected with.
3. free jet test motor power measurement mechanism according to claim 2, is characterized in that: described vertical rack is provided with taper hole; The quantity of described taper hole is consistent with the quantity of the vertex of a cone; The position of described taper hole and the position one_to_one corresponding of the vertex of a cone.
4. the free jet test motor power measurement mechanism according to claim 1 or 2 or 3, is characterized in that: describedly determine frame, vertical rack and level frame and all adopt steel frame construction, and shape is rectangle.
5. the free jet test motor power measurement mechanism according to Claims 2 or 3, is characterized in that: described drive unit adopts Driven by Hydraulic Cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420422371.4U CN204241143U (en) | 2014-07-29 | 2014-07-29 | Free jet test motor power measurement mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420422371.4U CN204241143U (en) | 2014-07-29 | 2014-07-29 | Free jet test motor power measurement mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204241143U true CN204241143U (en) | 2015-04-01 |
Family
ID=52770624
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420422371.4U Active CN204241143U (en) | 2014-07-29 | 2014-07-29 | Free jet test motor power measurement mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204241143U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104155042A (en) * | 2014-07-29 | 2014-11-19 | 西安航天动力试验技术研究所 | Device for measuring thrust of free jet test engine |
| CN107478366A (en) * | 2017-07-03 | 2017-12-15 | 河北汉光重工有限责任公司 | A kind of underwater metal fuel motor power test device |
| CN114166462A (en) * | 2022-01-21 | 2022-03-11 | 夏青元 | Vehicle-mounted aircraft pneumatic parameter comprehensive measurement system for simulating wind tunnel flow field |
| RU2818443C1 (en) * | 2023-10-27 | 2024-05-02 | Федеральное Автономное Учреждение "Центральный институт авиационного моторостроения имени П.И. Баранова" | Universal loading device |
-
2014
- 2014-07-29 CN CN201420422371.4U patent/CN204241143U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104155042A (en) * | 2014-07-29 | 2014-11-19 | 西安航天动力试验技术研究所 | Device for measuring thrust of free jet test engine |
| CN107478366A (en) * | 2017-07-03 | 2017-12-15 | 河北汉光重工有限责任公司 | A kind of underwater metal fuel motor power test device |
| CN107478366B (en) * | 2017-07-03 | 2019-09-10 | 河北汉光重工有限责任公司 | A kind of underwater metal fuel motor power test device |
| CN114166462A (en) * | 2022-01-21 | 2022-03-11 | 夏青元 | Vehicle-mounted aircraft pneumatic parameter comprehensive measurement system for simulating wind tunnel flow field |
| RU2818443C1 (en) * | 2023-10-27 | 2024-05-02 | Федеральное Автономное Учреждение "Центральный институт авиационного моторостроения имени П.И. Баранова" | Universal loading device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104155042A (en) | Device for measuring thrust of free jet test engine | |
| CN102556363B (en) | Servo motor type undercarriage retractile follow-up loading system and loading method of loading system | |
| CN204241143U (en) | Free jet test motor power measurement mechanism | |
| CN110779811A (en) | Rainfall seepage and blasting vibration coupling simulation soft rock shear rheology test system | |
| CN103033374B (en) | Test device of vertical structure model of shield tunnel | |
| CN203011609U (en) | Flow-field pressure detecting device used for supersonic-velocity wind tunnel | |
| CN105716888B (en) | A kind of wing-box experimental rig and its method | |
| CN102494908A (en) | Servo-motor aerodynamic load analog device of aircraft landing gear folding and unfolding | |
| CN109900479B (en) | Six-dimensional vector force/moment loading device for simulating working state of engine | |
| CN105387992A (en) | Airfoil profile support device and support method | |
| CN204064656U (en) | A kind of thrust bearing axial force test unit | |
| CN102182695A (en) | Tester for axial force of pump | |
| CN202330169U (en) | Mining anchor rod test device | |
| CN102680151B (en) | Anchor rod torque testing device and method | |
| CN110779812A (en) | Rainfall seepage and blasting vibration coupling simulation soft rock shear rheology test shear box | |
| CN205446272U (en) | Hydro -cylinder test bench frame | |
| CN109060291B (en) | Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft | |
| CN102808760A (en) | Testing device for three-level fluid dynamic pressure mechanical seal | |
| CN106057059B (en) | A kind of space flight barrel shell axle pressure test loads fixture system | |
| CN206002292U (en) | A kind of installation saves pull bar thrust charger | |
| CN111337340B (en) | Testing arrangement of simply-supported stringer of side end test piece configuration | |
| CN210802752U (en) | Supersonic engine test bench air inlet thrust measuring device | |
| CN202732307U (en) | Three-stage fluid dynamic pressure mechanical sealing test device | |
| CN205950656U (en) | Shock absorber spring frock that changes outfit fast | |
| CN203479530U (en) | Barrel-type moving frame inlaying linear bearings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |