CN103644995B - The surface installation of test unlocking force - Google Patents
The surface installation of test unlocking force Download PDFInfo
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- CN103644995B CN103644995B CN201310713632.8A CN201310713632A CN103644995B CN 103644995 B CN103644995 B CN 103644995B CN 201310713632 A CN201310713632 A CN 201310713632A CN 103644995 B CN103644995 B CN 103644995B
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Abstract
The present invention realizes a kind of surface installation testing unlocking force, and it comprises: 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 below the rear side being positioned at described launcher changeover mechanism, for the hanger applied thrust below launcher; Dynamometry and register system, comprise force cell and the registering instrument of communication connection, the thrust suffered by the hanger of described force cell on testing and launching frame, the data that described registering instrument records for recording described force cell.The present invention can be used for routine inspection, with the unlocking force size of Accurate Measurement rail launcher.Determine the stressed change of rail launcher emission process, Data support is provided to be separated and to improve emitter design to analysis firing mount and analyzes reference.
Description
Technical field
The invention belongs to air armament and launch ground checkout equipment field, particularly a kind of surface installation testing unlocking force.
Background technology
Rail launcher is widely used in the transmitting of various guided missile, and in order to effectively fix the guided missile carried before transmission, rail launcher adopts locking bomb retaining device to fix guided missile usually.During MISSILE LAUNCHING, propulsion system produce the holdback force effect that thrust exceedes launcher, and the fixing of locking bomb retaining device washed open by guided missile, is separated with launcher.
Unlocking force should be designed to the overload power being greater than guided missile carry in carrier aircraft, is less than again the low temperature average thrust of missile propulsion system simultaneously.Waving at this scope drawback lock power guarantee, in the situations such as turning, locking bomb retaining device is fixed on guided missile on orientor, simultaneously also can ensure that guided missile starts smoothly overcome holdback force and leave orientor, and guided missile start also can be within the acceptable range from impulsing of causing of frame.
Inhibition (the being called for short unlocking force afterwards) size measuring rail launcher accurately effectively can ensure the safety and reliability that firing mount is separated.Analyze the stressing conditions of guided missile on guide rail, main holdback force is the friction force on the locking power that formed of launcher locking bomb retaining device (rear be called for short locking device) and guide rail.
The mode of present normally used examination unlocking force has two kinds: one, directly use relevant device to test locking device during test, and the power recorded is thought the approximate value of actual unlocking force; Two, the minimum average thrust in guarantee process carries out test of unblanking, and as locking device is unblanked, thinks that unlocking force meets the demands, namely ensures 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.
During the actual unlocking force of launching petite combination guided missile at unmanned plane is analyzed, can find the locking power (namely the result of method one not accurate) of unlocking force much larger than locking device, this illustrates in such cases, and 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 caused launched by launcher also needs stricter control, and using method two tests the requirement that unlocking force can not meet emission security.
Therefore, need at present a kind ofly dual lock power to carry out the proving installation of more Measurement accuracy, particularly analyze firing mount that unmanned plane launches petite combination guided missile when being 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 testing unlocking force, to realize more accurately measuring unlocking force.
To achieve these goals, the present invention realizes a kind of surface installation testing unlocking force, and it comprises: 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 below the rear side being positioned at described launcher changeover mechanism, for the hanger applied thrust below launcher; Dynamometry and register system, comprise force cell and the registering instrument of communication connection, the thrust suffered by the hanger of described force cell on testing and launching frame, the data that described registering instrument records for recording described force cell.
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 the cavity for holding launcher and hanger thereof, described launcher changeover mechanism is positioned at the top of described cavity.
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 vertical direction and the moveable installing plate of 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 below described fixed head, and has multiple interface 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 adjustably installed on described ground supports frame, so that the angle of adjustment launcher.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, described thrust generator comprises: runner, comprises a through hole, is provided with internal thread in described through hole; Screw rod, horizontally 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 below launcher.
In a kind of preferred implementation of the surface installation of above-mentioned test unlocking force, described thrust generator comprises: oil cylinder, is horizontally disposed with, and comprises cylinder body and piston rod, described cylinder body is fixed, and the external part of described piston rod is used for the hanger applied thrust below launcher.
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, be provided with sliding-rail sliding mechanism between described thrust mounting bracket and described ground supports frame, move in the horizontal direction for described thrust mounting bracket; Also be provided with sliding-rail sliding mechanism between the both sides of described installing plate and described thrust mounting bracket, move at vertical direction for described installing plate.
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 multiple deep hole above described launcher changeover mechanism, the other end of described connecting link is selectively fixed in different described deep holes, to realize the adjustable angle of described launcher changeover mechanism.
As from the foregoing, the present invention includes ground supports frame, launcher changeover mechanism, as the thrust generator of thrust simulation equipment and dynamometry and register system.The power moved ahead from frame that thrust simulation equipment provides more stable power to be subject to for guided missile during analog transmissions.Thrust data in dynamometry and the detachment process of register system record firing mount.Can obtain according to data the stressed change that guided missile moves on rail launcher, also directly can measure the maximum resistance that guided missile in the process of unblanking is subject to simultaneously.
Visible, the present invention can be used for routine inspection, with the unlocking force size of Accurate Measurement rail launcher.Determine the stressed change of rail launcher emission process, Data support is provided to be separated and to improve emitter design to analysis firing mount and analyzes reference.In other preferred implementations, the present invention by changing the mechanical interface connecting emitter, can also test to mate multiple rail emitter.
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 appearance schematic diagram of the launcher changeover mechanism of the embodiment of the present invention.
Fig. 4 a, 4b, 4c are the outside drawing of the thrust mounting bracket of 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 be the embodiment of the present invention install and use schematic diagram.
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.
Specifically, ground supports frame 1 is for providing stable support for whole equipment, and in the present embodiment, the middle part of ground supports frame 1 is the box cavity of a longitudinal direction.When applying, 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 namely 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 below the rear side of launcher changeover mechanism 2, is positioned at below the rear side of launcher changeover mechanism 2 to make thrust generator 4.When applying, thrust generator 4 is for guided missile (hanger) 7 applied thrust below launcher 6.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 the thrust suffered by the guided missile 7 on testing and launching frame 6, and registering instrument 52 is for recording the data that force cell 51 records.
At the present embodiment, ground supports frame 1 and thrust mounting bracket 3 are framed structure, and square steel tube can be adopted to be welded, and structure and manufacture craft are all fairly simple.
As shown in Figure 3 a, launcher changeover mechanism 2 comprises fixed head 22, the web joint 21 of 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 multiple through hole (unmarked), is installed on the steel pipe on ground supports frame 1 by fixed head 22 by bolt (or U-bolt) and nut etc.Web joint 21 is positioned at below fixed head 22, is connected therebetween by web joint 23.From Fig. 3 a, web joint 22 has multiple interface (through hole) so that connect the launcher 6 of different size.
Preferably, be installed on the steel pipe of ground supports frame 1, so that the angle of adjustment launcher 6 fixed head 22 adjustable angle of launcher changeover mechanism 2.
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, and be also aforementioned container cavity inside top, the side along joint 221 is provided with multiple deep hole.Meanwhile, one end of joint 221 and one end of fixed head 22 hinged.The side of fixed head 22 and one end of connecting link 222 hinged, the other end of connecting link 222 is selectively fixed on arbitrary deep hole of joint 221 side.Connecting link 222 is fixed on the position, hole that joint 221 is different, forms different triangle rock-steady structures, the angular setting of whole fixed head 22 can be realized.
In order to adapt to the needs of different launcher 6, so that adjust the position of thrust generator 4 in time, as Fig. 4 a, thrust mounting bracket 3 comprises four parallel longitudinal holding poles 31 and multiple horizontal pole, is provided with at vertical direction and the moveable installing plate 32 of horizontal direction between pole 31.
Thrust generator 4 is installed on installing plate 32 by securing members such as bolts.The adjustable design of installing plate 32 can adjust the thrust line location of thrust generator 4 easily, guarantees that the thrust line of thrust generator 4 is consistent with the bullet axle of test guided missile 7.
Preferably, as shown in Fig. 4 a, Fig. 4 b, Fig. 4 c, inside the pole 31 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 along guide shaft 311 after vertical direction slides into correct position, be 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.The I-shaped slide block 331 that one end embeds guide groove 332 is fixed with at the front side top of thrust mounting bracket 3.Thrust mounting bracket 3 is moved in the guide groove 332 of pole 33 in the horizontal direction by slide block 331, when moving to the position of needs, 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 bedplate 43 is fixed on the installing plate 32 of thrust mounting bracket 3.Runner 42 is rotatably installed on bearing 44 by structures such as bearings.Be a through hole at the center of runner 42, in through hole, be provided with internal thread.Screw rod 41, horizontally through the through hole at runner 42 center, makes runner 42 and screw rod 41 be moved by screw drive principle drive screw 41.When rotating wheel 42 makes screw rod 41 move forward, screw rod 41 can, to guided missile 7 applied thrust below launcher 6, 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, is fixed by cylinder body when applying, and makes the external part of piston rod for the hanger applied thrust below launcher.
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 is inserted in screw 511 and 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, certain angle can be provided with satisfied test.Thrust mounting bracket 3 is arranged on the rear side of ground supports frame 1, and thrust generator 4 can be made to move to adjust height and the direction of horizontal direction, ensures 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 rotates and screw rod 41 is stretched out forward, promotes guided missile 7 and moves forward along guide rail on the guide rail of launcher 6.Force cell 51 is arranged on screw rod 41 front end 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, the present embodiment can be utilized in actual transmission before measurement examination unlocking force.The test of dispatching from the factory of usual emitter 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 recorded may reach 1.5 times even higher of locking power, therefore, test-based examination can be carried out by the present embodiment.
In actual transmitting, process time of unblanking is very short, is usually 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, comparatively real processes is slow for whole process of unblanking, therefore can carry out according to the result of ground test the phase analysis unblanked in process, start principle and the process of whole process of unblanking can be analyzed more accurately, judge whether whole process of unblanking meets the demands or which part needs perfect further.
Described in comprehensive, the present invention can motion process when the hangers such as ground simulation guided missile are launched on shoe, and test unlocking force is more accurate.Secondly, the relative real processes of simulation process of the present invention is slow, is convenient to divide the influence factor of different phase to moving on rails and analyzes.In addition, the present invention can also stressed size vertically in more accurate testing and launching process, checks whether emitter meets the requirements.
As known by the technical knowledge, the present invention can be realized by other the embodiment not departing from its Spirit Essence or essential feature.Therefore, above-mentioned disclosed embodiment, with regard to each side, all just illustrates, is not only.Within the scope of the present invention all or be all included in the invention being equal to the change in scope of the present invention.
Claims (9)
1. test a surface installation for unlocking force, it 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 below the rear side being positioned at described launcher changeover mechanism, described thrust generator comprises: the runner with a through hole, is provided with internal thread in described through hole; Screw rod, horizontally 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 below launcher;
Dynamometry and register system, comprise force cell and the registering instrument of communication connection, described force cell is compressive stress sensor, its rear end is provided with a screw, the front end of described screw rod is inserted in described screw to make described force cell be fixed on described screw rod, thus, described force cell is between the front end of described screw rod and the breech face of described hanger, for testing the thrust suffered by the described hanger on described launcher, the data that described registering instrument records for recording described force cell.
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 the cavity for holding launcher and hanger thereof, and described launcher changeover mechanism is positioned at the top of described cavity.
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 vertical direction and the moveable installing plate of 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 below described fixed head, and has multiple interface 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 adjustably installed on described ground supports frame, so that the angle of adjustment launcher.
6. 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 used for the hanger applied thrust below launcher.
7. 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.
8. the surface installation of test unlocking force according to claim 3, is characterized in that, is provided with sliding-rail sliding mechanism between described thrust mounting bracket and described ground supports frame, moves in the horizontal direction for described thrust mounting bracket;
Also be provided with sliding-rail sliding mechanism between the both sides of described installing plate and described thrust mounting bracket, move at vertical direction for described installing plate.
9. 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 multiple deep hole above described launcher changeover mechanism, the other end of described connecting link is selectively fixed in different described deep holes, to realize the adjustable 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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| CN103644995B true CN103644995B (en) | 2015-11-18 |
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| 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 |
| 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 |
| WO2020112049A2 (en) * | 2018-08-08 | 2020-06-04 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| WO2020112048A2 (en) * | 2018-08-08 | 2020-06-04 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A test system for throwing mechanisms |
| 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 |
| 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 |
| CN112229611B (en) * | 2020-08-27 | 2023-03-31 | 芜湖航翼集成设备有限公司 | Aircraft guide rail emitter testing arrangement |
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