CN203502194U - Test cable pulling mechanism - Google Patents
Test cable pulling mechanism Download PDFInfo
- Publication number
- CN203502194U CN203502194U CN201320616503.2U CN201320616503U CN203502194U CN 203502194 U CN203502194 U CN 203502194U CN 201320616503 U CN201320616503 U CN 201320616503U CN 203502194 U CN203502194 U CN 203502194U
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- China
- Prior art keywords
- connecting rod
- test
- pulling
- rod
- hinged
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- Expired - Fee Related
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model relates to a test cable pulling mechanism, which is characterized in that the tail end face of a test prototype and the front end face of test stand are in butt joint, an upper hinge support and a lower hinge support are installed on supporting feet of the stand, and the stand is fixed on a stand base; a pulling connecting rod is hinged on the upper hinge support, and an actuation connecting rod is hinged on the lower hinge support; a pulling plug is inserted in the test prototype and connected with the pulling plug and the pulling connecting rod through a steel wire; an actuator is installed at the bottom part of the stand base, and a push rod of the actuator is hinged with the bottom end of the actuation connecting rod; the pulling connecting rod comprises a vertical rod, the reverse side of the upper end of the vertical rod is welded with a windward plate, the front end is a triangle bracket used for being connected with the steel wire, a cantilever rod stretches out of the middle part, and the bottom end is provided with a stop plate; and the upper end of a pneumatic connecting rod is provided with a limit plate corresponding to the stop plate of the pulling connecting rod.
Description
Technical field
The utility model relates to guided missile environmental test, is specifically related to a kind of test cable Tuo Ba mechanism of guided missile wind tunnel test.
Background technology
Aircraft, when Live Flying, can carry out a series ofly such as separated with roll booster machinery, and roll booster is separated with the electric interface message processor (IMP) tool of aircraft, and radome fairing is separated from Flight Vehicle Structure, and rudder sheet moves to control the actions such as flight attitude.And in aircraft development process, must carry out on ground the simulation of relevant action, with the aircraft relevant action of examining design rationally, reliable, ensure that flight test successfully realizes.
The product size of carrying out free jet test is limited to the size of wind-tunnel, and each free jet test particularly large scale wind-tunnel free jet test funds in need are huger.At present at home, can carry out length is that the wind-tunnel of 2 meters of above full-scale free jet test of aircraft is extremely rare.For these reasons, in aircraft development process, the general integrated free jet test of aircraft and roll booster of can not carrying out, and only can be the in the situation that of conditions permit, the device that design can be simulated relevant action is hung on the free jet test of carrying out full-scale vehicle on full-scale vehicle outward.The way of this plug-in analogue means because scheme is simple, good economy performance, advantage that practicality is high, wide being applied in engineering, test.
Utility model content
The technical problems to be solved in the utility model be for aerospacecraft with roll booster stage separation, to the separated requirement of simulated flight device in the free jet test of ground and roll booster electric interfaces machinery, provide a kind of test cable ground pneumatic de-pulling device.
A test cable Tuo Ba mechanism, is characterized in that comprising test prototype, de-unplugg, steel cable, test bracket, de-connecting rod, upper hinge bearing, lower rocker bar bearing, start connecting rod, actuator, the bracket base of pulling out; The breech face of experimental prototype docks with the front end face of test bracket, and upper hinge bearing, lower rocker bar bearing are arranged on the leg of support, and support is fixed on bracket base; Take off and pull out rod hinge connection on upper hinge bearing, start rod hinge connection is on lower rocker bar bearing; De-unplugg is plugged on test sample, with steel cable, connects de-unplugg and the de-connecting rod that pulls out; Actuator is arranged on bracket base bottom, and the bottom of its push rod and start connecting rod is hinged; Describedly de-pull out connecting rod and comprise vertical rod, the back side, vertical rod upper end is welded with plate windward, and front end is A-frame, for connecting steel cable, and the cantilever lever that stretch out at middle part, for de-ly pulling out the spacing of connecting rod to whole, bottom is provided with check plate; Described Pneumatic connecting rod upper end is provided with the limiting plate corresponding with the de-check plate that pulls out connecting rod, and before on-test, Pneumatic connecting rod is subject to pulling of actuator, and limiting plate props up support by promotion check plate to cantilever lever.
By Aerodynamic force action, in the plate windward of the utility model device, can in free jet test process, accurately complete the de-work of stirring of cable, accurately simulated flight device when with roll booster stage separation, the separation case of cable.
Accompanying drawing explanation
The pneumatic Tuo Ba test cable of Fig. 1 mechanism scheme of installation;
The de-bar linkage structure figure that pulls out of the pneumatic Tuo Ba test cable of Fig. 2 mechanism;
The pneumatic Tuo Ba test cable of Fig. 3 mechanism Pneumatic connecting rod structural drawing
The pneumatic Tuo Ba test cable of Fig. 4 mechanism reed group schematic diagram.
Embodiment:
Below in conjunction with accompanying drawing, the utility model is described further.
A test cable Tuo Ba mechanism, as shown in Figure 1, comprises test prototype 1, de-unplugg 2, steel cable 3, test bracket 4, de-connecting rod 5, upper hinge bearing 6, lower rocker bar bearing 8, start connecting rod 9, actuator 10, the bracket base 11 of pulling out.
The breech face of experimental prototype 1 docks with the front end face of test bracket 4, and upper hinge bearing 6, lower rocker bar bearing 8 are arranged on the leg of support 4, and support 4 is fixed on bracket base 10; De-pull out connecting rod 5 and be hinged on upper hinge bearing 6, start connecting rod 9 is hinged on lower rocker bar bearing 8; De-unplugg 2 is plugged on test sample 1, with steel cable 3, connects de-unplugg 2 and the de-connecting rod 5 that pulls out; Actuator 10 is arranged on bracket base 11 bottoms, and the bottom of its push rod and start connecting rod 9 is hinged.
Take off and pull out connecting rod 5 structures as shown in Figure 2, comprise vertical rod 14, vertical rod 14 back sides, upper end are welded with plate 12 windward, and front end is A-frame 15, for connecting steel cable 3, and the cantilever lever 16 that stretch out at middle part, for whole taking off pulled out to the spacing of connecting rod 5, bottom is provided with check plate 13.
As shown in Figure 3, Pneumatic connecting rod 9 upper ends are provided with the limiting plate 17 corresponding with the de-check plate 13 that pulls out connecting rod 5.Before on-test, Pneumatic connecting rod 9 is subject to pulling of actuator 10, and limiting plate 17 props up support 4 by promotion check plate 13 to cantilever lever 16, and whole linkage assembly is in arrested state, guarantees that wind-tunnel is de-after starting to pull out connecting rod 5 and can not be subject to Aerodynamic force action and move.
When test proceeds to de-while pulling out sequential, pilot system pushes away before providing the push rod that electric signal makes actuator 10, drive start connecting rod 9 to rotate, 17 pairs of de-position limitations that pull out check plate 13 on connecting rod 5 of start connecting rod 9 upper limit plate have been eliminated, the de-plate windward 12 pulling out on connecting rod 5 is subject to Aerodynamic force action and turns clockwise, and by steel cable 3, will take off that unplugg 2 is de-to be pulled out, simulated the electrical cables separate action of aircraft when with roll booster stage separation.
Pneumatic Tuo Ba test cable mechanism be also provided with anti-anti-avulsion pull out connecting rod 5 de-pull out cable after by the airflow function of Base Flow and the reed group 7 of resilience.Figure 4 shows that the vertical view of reed group 7, end face is v-shaped structure, reed group 7 is arranged on the leg of support 4, when de-when pulling out connecting rod 5 and turning clockwise, the de-corresponding reed group of axis 7 indentation, there of pulling out connecting rod 5, de-ly pull out connecting rod 5 and will clamp-on reed group 7 from reed group 7 right-hand members under the effect of inertial force; After this when the de-plate windward 12 that pulls out connecting rod 5 is subject to the Aerodynamic force action resilience of bottom, flow field again, will stop by the v-shaped structure of reed group 7 right-hand members, thereby reach anti-anti-avulsion, pull out connecting rod 5 resiliences.
Claims (1)
1. a test cable Tuo Ba mechanism, is characterized in that comprising test prototype (1), de-unplugg (2), steel cable (3), test bracket (4), de-connecting rod (5), upper hinge bearing (6), lower rocker bar bearing (8), start connecting rod (9), actuator (10), the bracket base (11) of pulling out; The breech face of experimental prototype (1) docks with the front end face of test bracket (4), and upper hinge bearing (6), lower rocker bar bearing (8) are arranged on the leg of support (4), and support (4) is fixed on bracket base (10); The de-connecting rod (5) that pulls out is hinged on upper hinge bearing (6) above, and start connecting rod (9) is hinged on lower rocker bar bearing (8); It is upper that de-unplugg (2) is plugged on test sample (1), with steel cable (3), connects de-unplugg (2) and the de-connecting rod (5) that pulls out; Actuator (10) is arranged on bracket base (11) bottom, and the bottom of its push rod and start connecting rod (9) is hinged; Describedly de-pull out connecting rod (5) and comprise vertical rod (14), vertical rod (14) back side, upper end is welded with plate (12) windward, front end is A-frame (15), be used for connecting steel cable (3), the cantilever lever (16) that stretch out at middle part, for whole taking off pulled out to the spacing of connecting rod (5), bottom is provided with check plate (13); Described Pneumatic connecting rod (9) upper end is provided with the limiting plate (17) corresponding with the de-check plate (13) that pulls out connecting rod (5), before on-test, Pneumatic connecting rod (9) is subject to pulling of actuator (10), and limiting plate (17) will promote check plate (13) to cantilever lever (16) and prop up support (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320616503.2U CN203502194U (en) | 2013-09-30 | 2013-09-30 | Test cable pulling mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320616503.2U CN203502194U (en) | 2013-09-30 | 2013-09-30 | Test cable pulling mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203502194U true CN203502194U (en) | 2014-03-26 |
Family
ID=50333165
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320616503.2U Expired - Fee Related CN203502194U (en) | 2013-09-30 | 2013-09-30 | Test cable pulling mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203502194U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103543100A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Pneumatic test electric cable pulling device |
-
2013
- 2013-09-30 CN CN201320616503.2U patent/CN203502194U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103543100A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Pneumatic test electric cable pulling device |
| CN103543100B (en) * | 2013-09-30 | 2015-11-25 | 中国人民解放军国防科学技术大学 | The pneumatic de-pulling device of a kind of test cable |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140326 Termination date: 20160930 |