CN103644995A - Ground device for testing unlocking force - Google Patents
Ground device for testing unlocking force Download PDFInfo
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- CN103644995A CN103644995A CN201310713632.8A CN201310713632A CN103644995A CN 103644995 A CN103644995 A CN 103644995A CN 201310713632 A CN201310713632 A CN 201310713632A CN 103644995 A CN103644995 A CN 103644995A
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- launcher
- thrust
- supports frame
- ground supports
- unlocking force
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Abstract
The invention relates to a ground device for testing unlocking force. The ground device comprises a ground supporting frame, a launching rack changeover mechanism, a thrust providing device and a force-measuring and recording system, wherein the ground supporting frame is used for providing stable supporting; the launching rack changeover mechanism is installed on the upper portion of the ground supporting frame and used for fixing a launching rack; the thrust providing device is fixed on the ground supporting frame, located below the rear side of the launching rack changeover mechanism and used for exerting thrust on a hung object below the launching rack; the force-measuring and recording system comprises a force-measuring sensor and a recorder which are in communication connection, the force-measuring sensor is used for measuring thrust which the hung object below the launching rack is subject to, and the recorder is used for recording data measured by the force-measuring sensor. The ground device can be used for conventional inspection so as to precisely measure the unlocking force of the track type launching rack. Stress changes in the launching rack launching process is determined so as to provide data support and analysis reference for analyzing gun carrier separation and perfecting launcher design.
Description
Technical field
The invention belongs to air armament transmitting ground checkout equipment field, particularly a kind of surface installation of testing unlocking force.
Background technology
Rail formula launcher is widely used in the transmitting of various guided missiles, and for the effectively fixing guided missile carrying before transmitting, rail formula launcher adopts locking bomb retaining device to fix guided missile conventionally.During MISSILE LAUNCHING, propulsion system produce the holdback force effect that thrust surpasses launcher, and guided missile is washed the fixing of locking bomb retaining device open, carries out separated with launcher.
Unlocking force should be designed to be greater than the overload power of guided missile carry in carrier aircraft, is less than again the low temperature average thrust of missile propulsion system simultaneously.At this scope drawback lock power guarantee, waving, in the situations such as turning, locking bomb retaining device is fixed on guided missile on orientor, also can guarantee simultaneously guided missile smoothly starting overcome holdback force and leave orientor, and impulsing of causing from frame of guided missile starting also can be within the acceptable range.
Inhibition (the being called for short afterwards unlocking force) size of measuring accurately rail formula launcher can effectively guarantee the safety and reliability of firing mount separation.Analyze the stressing conditions of guided missile on guide rail, main holdback force is the locking power of launcher locking bomb retaining device (being called for short afterwards locking device) formation and the friction force on guide rail.
The mode of present normally used examination unlocking force has two kinds: while one, testing, directly use relevant device to test locking device, and the power recording is thought to the approximate value of actual unlocking force; Two, the minimum average thrust in assurance process unblanks to test, and as locking device, unblanks to think that unlocking force meets the demands, and guarantees that the higher limit of unlocking force does not exceed designing requirement.From the results of view, true unlocking force is greater than the value of method one, is less than the value of method two.
In the actual unlocking force of unmanned plane transmitting petite combination guided missile is analyzed, can find that unlocking force is much larger than the locking power (result that is method one is accurate not) of locking device, this illustrate in such cases, the extra holdback force such as rail friction power affects and also can not be ignored.Meanwhile, unmanned plane own wt ratio has man-machine lighter, and the retroaction size that launcher transmitting causes also needs stricter control, and using method two test unlocking force can not meet the requirement of emission security.
Therefore, need at present a kind ofly can dual lock power carry out the more proving installation of Measurement accuracy, particularly analyze the firing mount of unmanned plane transmitting petite combination guided missile when separated, more need unlocking force proving installation accurately.
Summary of the invention
The object of the present invention is to provide a kind of surface installation of testing unlocking force, to realize, more accurately measure unlocking force.
To achieve these goals, the present invention realizes a kind of surface installation of testing unlocking force, and it comprises: ground supports frame, for stable support is provided; Launcher changeover mechanism, is installed on described ground supports frame top, for fixed launcher rack; Thrust generator, is fixed on described ground supports frame, and is positioned at the rear side below of described launcher changeover mechanism, for the hanger applied thrust to launcher below; Dynamometry and register system, comprise force cell and the registering instrument of communication connection, and described force cell is for testing the suffered thrust of hanger on launcher, and described registering instrument is for recording the data that described force cell records.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, described ground supports frame is framed structure, and the middle part of described ground supports frame is that described launcher changeover mechanism is positioned at the top of described cavity for holding the cavity of launcher and hanger thereof.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, the rear side of described cavity is provided with thrust mounting bracket, described thrust mounting bracket is included in movably installing plate of vertical direction and horizontal direction, and described thrust generator is installed on described installing plate.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, described launcher changeover mechanism comprises: fixed head, is fixed on described ground supports frame; Web joint, is located at described fixed head below, and has a plurality of interfaces so that connect different launchers.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, described launcher changeover mechanism angle in vertical plane is installed on described ground supports frame adjustablely, so that adjust the angle of launcher.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, described thrust generator comprises: runner, comprise a through hole, and in described through hole, be provided with internal thread; Screw rod, flatly, through described through hole, described runner drives described screw rod to move by screw drive principle, makes described screw rod to the hanger applied thrust of launcher below.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, described thrust generator comprises: oil cylinder, be horizontally disposed with, and comprise cylinder body and piston rod, described cylinder body is fixed, and the external part of described piston rod is for the hanger applied thrust to launcher below.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, described force cell is compressive stress sensor, and described compressive stress sensor is fixed on the top of described screw rod.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, between described thrust mounting bracket and described ground supports frame, be provided with sliding-rail sliding mechanism, for described thrust mounting bracket, move in the horizontal direction; Between the both sides of described installing plate and described thrust mounting bracket, be also provided with sliding-rail sliding mechanism, for described installing plate, at vertical direction, move.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, the front end of described launcher changeover mechanism is articulated with described ground supports frame, middle part is hinged with one end of a connecting link, described ground supports frame is provided with a plurality of deep holes above described launcher changeover mechanism, the other end of described connecting link is selectively fixed in different described deep holes, adjustable to realize the angle of described launcher changeover mechanism.
As from the foregoing, the present invention includes ground supports frame, launcher changeover mechanism, as thrust generator and dynamometry and the register system of thrust analog machine.The power moving ahead from frame that guided missile when thrust analog machine provides more stable power for analog transmissions is subject to.Dynamometry and register system record the thrust data in firing mount detachment process.According to data, can obtain the stressed variation that guided missile moves on formula launcher in-orbit, also can directly measure the maximum resistance that in the process of unblanking, guided missile is subject to simultaneously.
Visible, the present invention can be used for routine inspection, with the unlocking force size of Accurate Measurement rail formula launcher.Determine the stressed variation of rail formula launcher emission process, Data support to be provided and to analyze reference analyzing firing mount separation and improving emitter design.In other preferred implementations, the present invention can also connect by replacing the mechanical interface of emitter, to mate multiple rail formula emitter, tests.
Accompanying drawing explanation
Fig. 1 is the monnolithic case figure of the embodiment of the present invention.
Fig. 2 is the side view of the embodiment of the present invention.
Fig. 3 a, 3b are the profile schematic diagram of the launcher changeover mechanism of the embodiment of the present invention.
The outside drawing of the thrust mounting bracket that Fig. 4 a, 4b, 4c are the embodiment of the present invention.
Fig. 5 is the force cell of the embodiment of the present invention and the outside drawing of recording unit.
Fig. 6 is the outside drawing of the thrust generator of the embodiment of the present invention.
Fig. 7 is the schematic diagram of installing and using of the embodiment of the present invention.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further details.
As depicted in figs. 1 and 2, the embodiment of the present invention comprises ground supports frame 1, launcher changeover mechanism 2, thrust mounting bracket 3, thrust generator 4, dynamometry and register system 5.
Particularly, ground supports frame 1 is used to whole equipment that stable support is provided, and in the present embodiment, the middle part of ground supports frame 1 is a box cavity longitudinally.When application, ground supports frame 1 is also for supported and suspended launcher 6 and guided missile 7, and as Fig. 7, launcher 6 and guided missile 7 are arranged in the above-mentioned cavity of ground supports frame 1.Launcher changeover mechanism 2 is for fixed launcher rack 6, and it is installed on ground supports frame 1 top, is also fixed on the top of aforementioned cavity inside.Thrust generator 4 is fixed on ground supports frame 1 by a thrust mounting bracket 3, and thrust mounting bracket 3 is positioned at the rear side below of launcher changeover mechanism 2, so that thrust generator 4 is positioned at the rear side below of launcher changeover mechanism 2.When application, thrust generator 4 is for the guided missile to launcher 6 belows (hanger) 7 applied thrusts.In other embodiments, thrust generator also can be directly fixed on ground supports frame.Dynamometry and register system 5 comprise force cell 51 and the registering instrument 52 of communication connection, and wherein, force cell 51 is for testing the suffered thrust of guided missile 7 on launcher 6,52 data that record for recording force cell 51 of registering instrument.
At the present embodiment, ground supports frame 1 and thrust mounting bracket 3 are framed structure, can adopt square steel tube to be welded, and structure and manufacture craft are all fairly simple.
As shown in Figure 3 a, launcher changeover mechanism 2 comprises the web joint 21 of fixed head 22, level and vertical web joint 23.Wherein, fixed head 22 is fixed on the container cavity top of ground supports frame 1, which is provided with a plurality of through holes (unmarked), can fixed head 22 be installed on the steel pipe on ground supports frame 1 by bolt (or U-bolt) and nut etc.Web joint 21 is positioned at fixed head 22 belows, between the two, by web joint 23, connects.From Fig. 3 a, web joint 22 has a plurality of interfaces (through hole) so that connect the launcher 6 of different size.
Preferably, fixed head 22 angles of launcher changeover mechanism 2 are installed on the steel pipe of ground supports frame 1 adjustablely, so that adjust the angle of launcher 6.
More preferably, as shown in Figure 3 b, fixed head 22 is connected with the joint 221 of ground supports frame 1 by connecting link 222, and joint 221 is fixed on ground supports frame 1 top, is also aforementioned container cavity inside top, along the side of joint 221, is provided with a plurality of deep holes.Meanwhile, one end of one end of joint 221 and fixed head 22 is hinged.One end of the side of fixed head 22 and connecting link 222 is hinged, and the other end of connecting link 222 is selectively fixed on arbitrary deep hole of joint 221 sides.Connecting link 222 is fixed on to the different position, hole of joint 221, forms different triangle rock-steady structures, can realize the angular setting of whole fixed head 22.
In order to adapt to the needs of different launchers 6, so that adjust in time the position of thrust generator 4, as Fig. 4 a, thrust mounting bracket 3 comprises four parallel longitudinal holding poles 31 and a plurality of horizontal pole, is provided with at vertical direction and horizontal direction installing plate 32 movably between pole 31.
Preferably, as shown in Fig. 4 a, Fig. 4 b, Fig. 4 c, in pole 31 inner sides of thrust mounting bracket 3, be fixed with longitudinal guide shaft 311, slide block 312 is set on guide shaft 311 slidably.Installing plate 32 is arranged on slide block 312, when slide block 312 slides into after correct position at vertical direction along guide shaft 311, is bolted slide block 312 spacing.Meanwhile, the pole 33 of lateral arrangement is guide rail structure, and it is horizontally fixed on the rear side of ground supports frame 1, and its inside is a T font guide groove 332.Above the front side of thrust mounting bracket 3, be fixed with the I-shaped slide block 331 that one end embeds guide groove 332.Thrust mounting bracket 3 moves by slide block 331 along continuous straight runs in the guide groove 332 of pole 33, while moving to the position needing, spacing fixing by bolt.
As Fig. 5, thrust generator 4 comprises runner 42, screw rod 41, bearing 44 and bedplate 43.Wherein, bearing 44 is fixed on bedplate 43, and 43 of bedplates are fixed on the installing plate 32 of thrust mounting bracket 3.Runner 42 is rotatably installed on bearing 44 by structures such as bearings.At runner 42 center, be a through hole, in through hole, be provided with internal thread.Screw rod 41 flatly, through the through hole at runner 42 centers, makes runner 42 and screw rod 41 move by screw drive principle drive screw 41.When rotating wheel 42 moves forward screw rod 41, screw rod 41 can, to guided missile 7 applied thrusts of launcher 6 belows, drive guided missile 7 to move along the guide rail of launcher 6.
In other embodiments, thrust generator can also be an oil cylinder, and it is horizontally disposed with, and this oil cylinder comprises cylinder body and piston rod, when application, cylinder body is fixed, and is made the external part of piston rod for the hanger applied thrust to launcher below.
As Fig. 6, the force cell 51 of the present embodiment is compressive stress sensor, and its rear end is provided with a screw 511.Again as shown in Figure 6, the front end 411 of screw rod 41 inserts in screw 511 force cell 51 is fixed on screw rod 41.During application, force cell 51 is between the front end of screw rod 41 and the breech face of guided missile 7.
As from the foregoing, the launcher changeover mechanism 2 of the present embodiment is arranged on ground supports frame 1 top, for hanging different portable launchers, by adjusting the installation site of coupling part, can provide certain angle to meet test.Thrust mounting bracket 3 is arranged on the rear side of ground supports frame 1, can make thrust generator 4 move to adjust height and the direction of horizontal direction, guarantees that the thrust line of thrust generator 4 and the axle center of tested guided missile 7 are consistent.Thrust generator 4 provides steady propulsion, and runner 42 rotations are stretched out forward screw rod 41, promote guided missile 7 and along guide rail, move forward on the guide rail of launcher 6.Force cell 51 is arranged on screw rod 41 front ends of thrust generator 4, the acting force between the contact point of measurement thrust generator 4 and tested guided missile 7.
When carrier aircraft dual lock power has higher requirements, can utilize the present embodiment in actual transmission before measurement examination unlocking force.Conventionally the emitter test of dispatching from the factory is equivalent to unlocking force by the locking power of locking bomb retaining device and tests, other holdback force factor dual lock power on actual guide rail also have a certain impact, the actual unlocking force recording may reach 1.5 times even higher of locking power, therefore, can carry out test-based examination by the present embodiment.
In actual transmitting, the process time of unblanking is very short, is conventionally less than 1 second, and in whole process, very difficult data measured and division stage are analyzed.The present embodiment is in the process of unblanking of ground simulation reality, because thrust provides slower, the truer process of the whole process of unblanking is slow, therefore the phase analysis that can unblank in process according to the result of ground test, can analyze more accurately start principle and the process of the whole process of unblanking, judge whether the whole process of unblanking meets the demands or which partly needs further perfect.
Described in comprehensive, the present invention can be when the hanger transmittings such as ground simulation guided missile the motion process on shoe, test unlocking force is more accurate.Secondly, the relatively true process of simulation process of the present invention is slow, is convenient to divide different phase the influence factor of moving on guide rail is analyzed.In addition, the present invention can also more accurately test in emission process stressed size vertically, checks whether emitter meets the requirements.
As known by the technical knowledge, the present invention can realize by other the embodiment that does not depart from its Spirit Essence or essential feature.Therefore, above-mentioned disclosed embodiment, with regard to each side, all just illustrates, and is not only.Change within the scope of the present invention all or within being equal to scope of the present invention is all included in the invention.
Claims (10)
1. a surface installation of testing unlocking force, is characterized in that, comprising:
Ground supports frame, for providing stable support;
Launcher changeover mechanism, is installed on described ground supports frame top, for fixed launcher rack;
Thrust generator, is fixed on described ground supports frame, and is positioned at the rear side below of described launcher changeover mechanism, for the hanger applied thrust to launcher below;
Dynamometry and register system, comprise force cell and the registering instrument of communication connection, and described force cell is for testing the suffered thrust of hanger on launcher, and described registering instrument is for recording the data that described force cell records.
2. the surface installation of test unlocking force according to claim 1, it is characterized in that, described ground supports frame is framed structure, and the middle part of described ground supports frame is that described launcher changeover mechanism is positioned at the top of described cavity for holding the cavity of launcher and hanger thereof.
3. the surface installation of test unlocking force according to claim 2, it is characterized in that, the rear side of described cavity is provided with thrust mounting bracket, and described thrust mounting bracket is included in movably installing plate of vertical direction and horizontal direction, and described thrust generator is installed on described installing plate.
4. the surface installation of test unlocking force according to claim 1, is characterized in that, described launcher changeover mechanism comprises:
Fixed head, is fixed on described ground supports frame;
Web joint, is located at described fixed head below, and has a plurality of interfaces so that connect different launchers.
5. the surface installation of test unlocking force according to claim 1, is characterized in that, described launcher changeover mechanism angle in vertical plane is installed on described ground supports frame adjustablely, so that adjust the angle of launcher.
6. the surface installation of test unlocking force according to claim 1, is characterized in that, described thrust generator comprises:
Runner, comprises a through hole, in described through hole, is provided with internal thread;
Screw rod, flatly, through described through hole, described runner drives described screw rod to move by screw drive principle, makes described screw rod to the hanger applied thrust of launcher below.
7. the surface installation of test unlocking force according to claim 1, is characterized in that, described thrust generator comprises:
Oil cylinder, is horizontally disposed with, and comprises cylinder body and piston rod, and described cylinder body is fixed, and the external part of described piston rod is for the hanger applied thrust to launcher below.
8. the surface installation of test unlocking force according to claim 6, is characterized in that, described force cell is compressive stress sensor, and described compressive stress sensor is fixed on the top of described screw rod.
9. the surface installation of test unlocking force according to claim 3, is characterized in that, between described thrust mounting bracket and described ground supports frame, is provided with sliding-rail sliding mechanism, for described thrust mounting bracket, moves in the horizontal direction;
Between the both sides of described installing plate and described thrust mounting bracket, be also provided with sliding-rail sliding mechanism, for described installing plate, at vertical direction, move.
10. the surface installation of test unlocking force according to claim 5, it is characterized in that, the front end of described launcher changeover mechanism is articulated with described ground supports frame, middle part is hinged with one end of a connecting link, described ground supports frame is provided with a plurality of deep holes above described launcher changeover mechanism, the other end of described connecting link is selectively fixed in different described deep holes, adjustable to realize the angle of described launcher changeover mechanism.
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| CN201310713632.8A CN103644995B (en) | 2013-12-20 | 2013-12-20 | The surface installation of test unlocking force |
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| CN201310713632.8A CN103644995B (en) | 2013-12-20 | 2013-12-20 | The surface installation of test unlocking force |
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| CN103644995A true CN103644995A (en) | 2014-03-19 |
| CN103644995B CN103644995B (en) | 2015-11-18 |
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| CN106225967A (en) * | 2016-07-20 | 2016-12-14 | 中国人民解放军军械工程学院 | A kind of portable blocking force detection equipment |
| CN107643105A (en) * | 2017-10-30 | 2018-01-30 | 程鹏 | A kind of weather modification rocket launcher detector |
| CN108414255A (en) * | 2017-12-07 | 2018-08-17 | 上海航天精密机械研究所 | A kind of push type firing mount separation simulation device |
| CN109341924A (en) * | 2018-11-13 | 2019-02-15 | 河南普航电子设备有限公司 | Integral type missile launcher unlocks force test device |
| CN110274719A (en) * | 2019-06-12 | 2019-09-24 | 芜湖天航装备技术有限公司 | A kind of device for measuring force and its test method launching bomb shackle |
| WO2020112049A3 (en) * | 2018-08-08 | 2020-07-09 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| WO2020112048A3 (en) * | 2018-08-08 | 2020-07-09 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| CN111964820A (en) * | 2020-07-15 | 2020-11-20 | 芜湖天航装备技术有限公司 | Unlocking force measuring device of locking mechanism and using method thereof |
| CN112229611A (en) * | 2020-08-27 | 2021-01-15 | 芜湖航翼集成设备有限公司 | Aircraft guide rail emitter testing arrangement |
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| CN106225967A (en) * | 2016-07-20 | 2016-12-14 | 中国人民解放军军械工程学院 | A kind of portable blocking force detection equipment |
| CN106225967B (en) * | 2016-07-20 | 2019-02-19 | 中国人民解放军军械工程学院 | A kind of portable blocking force detection device |
| CN107643105A (en) * | 2017-10-30 | 2018-01-30 | 程鹏 | A kind of weather modification rocket launcher detector |
| CN107643105B (en) * | 2017-10-30 | 2024-04-02 | 程鹏 | Weather modification rocket launcher detector |
| CN108414255A (en) * | 2017-12-07 | 2018-08-17 | 上海航天精密机械研究所 | A kind of push type firing mount separation simulation device |
| GB2589792B (en) * | 2018-08-08 | 2022-08-03 | Tusas Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| US11933591B2 (en) | 2018-08-08 | 2024-03-19 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | Test system for throwing mechanisms |
| WO2020112048A3 (en) * | 2018-08-08 | 2020-07-09 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| US11994371B2 (en) | 2018-08-08 | 2024-05-28 | Tusas—Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | Test system for throwing mechanisms |
| GB2589792A (en) * | 2018-08-08 | 2021-06-09 | Tusas Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| GB2590003A (en) * | 2018-08-08 | 2021-06-16 | Tusas Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| WO2020112049A3 (en) * | 2018-08-08 | 2020-07-09 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| GB2590003B (en) * | 2018-08-08 | 2022-09-21 | Tusas Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| CN109341924A (en) * | 2018-11-13 | 2019-02-15 | 河南普航电子设备有限公司 | Integral type missile launcher unlocks force test device |
| CN109341924B (en) * | 2018-11-13 | 2024-03-26 | 河南普航电子设备有限公司 | Integrated missile launcher unlocking force testing device |
| CN110274719A (en) * | 2019-06-12 | 2019-09-24 | 芜湖天航装备技术有限公司 | A kind of device for measuring force and its test method launching bomb shackle |
| CN110274719B (en) * | 2019-06-12 | 2023-12-12 | 芜湖天航装备技术有限公司 | Force measuring device for ejection hook and test method thereof |
| CN111964820A (en) * | 2020-07-15 | 2020-11-20 | 芜湖天航装备技术有限公司 | Unlocking force measuring device of locking mechanism and using method thereof |
| CN112229611A (en) * | 2020-08-27 | 2021-01-15 | 芜湖航翼集成设备有限公司 | Aircraft guide rail emitter testing arrangement |
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| CN103644995B (en) | 2015-11-18 |
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