CN102269540A - Measurement device for unbalanced impulse - Google Patents
Measurement device for unbalanced impulse Download PDFInfo
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- CN102269540A CN102269540A CN2011101606284A CN201110160628A CN102269540A CN 102269540 A CN102269540 A CN 102269540A CN 2011101606284 A CN2011101606284 A CN 2011101606284A CN 201110160628 A CN201110160628 A CN 201110160628A CN 102269540 A CN102269540 A CN 102269540A
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- rolling
- axis
- launching tube
- sensor
- pull bar
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- A Measuring Device Byusing Mechanical Method (AREA)
- Testing Of Balance (AREA)
Abstract
The invention discloses a measurement device for unbalanced impulse, comprising a base (1), a rolling shaft A (2), further comprising a rolling shaft B (3), a bearing, a clasp (5), a front pull rod (6), a rear pull rod (7) and a sensor (8). The rolling shaft A (2) and the rolling shaft B (3) are arranged in parallel; the base (1) is connected with the rolling shaft A (2) and the rolling shaft B (3) and in threaded connection with the front pull rod (6); a concaved cambered surface in the middle of the upper surface of the rolling shaft A (2) and the rolling shaft B (3) is in contact with a launching tube (9). The front pull rod (6) and the rear pull rod (7) are in threaded connection with the sensor (8), and the rear pull rod (7) is in threaded connection with the clasp (5). During the launching, impulse on the launching tube is transmitted to the sensor (8), a value of a launching tube force is directly measured by the sensor (8), and the unbalanced impulse of the launching tube is calculated by integration of time. The device has a simple structure, integrally obtains the unbalanced impulse of the launching tube by directly measuring the relationship between force and time.
Description
Technical field
The present invention relates to the measurement mechanism of a kind of measurement mechanism, particularly a kind of uneven momentum.
Background technology
The measurement mechanism of present uneven momentum is generally the pendulum model structure, form and comprise pedestal, turning cylinder and lifting rope, being about to object under test is suspended in the air with lifting rope, come uneven momentum in the evaluation work process by amplitude of fluctuation around the shaft in the emission process, this device is an indirectly measurement equipment, and shortcoming is to need more supporting measurement device, complex structure, accuracy is lower, can not react the time dependent relation of momentum.
Summary of the invention
The object of the present invention is to provide a kind of measurement mechanism of uneven momentum, solved the problem that the uneven momentum in the emission process can't directly be measured.
A kind of measurement mechanism of uneven momentum comprises: pedestal, axis of rolling A, axis of rolling B also comprise: bearing, clip, anterior pull bar, rear portion pull bar, sensor.Axis of rolling A and axis of rolling B are arranged in parallel, and axis of rolling A, axis of rolling B upper surface middle part all have recessed cambered surface, and this cambered surface contacts with the launching tube cambered surface, and axis of rolling A, axis of rolling B are connected with base bearing, and pedestal and anterior pull bar are spirally connected.Anterior pull bar, rear portion pull bar and sensor two ends are spirally connected, and rear portion pull bar and clip are spirally connected, clip and launching tube clamping.
When launching a guided missile, launching tube is sliding on axis of rolling A and axis of rolling B under the momentum effect, because of clip and launching tube connect firmly, so the suffered momentum of launching tube is delivered on the sensor through clip.Sensor directly records the numerical value of launching tube power, by the integral and calculating launching tube imbalance momentum to the time.
This measurement mechanism is simple in structure, and by directly measuring power and time relation, integration just can draw the uneven momentum of launching tube.
Description of drawings
The front view of the measurement mechanism of a kind of uneven momentum of Fig. 1;
The measurement mechanism sectional view of a kind of uneven momentum of Fig. 2.
1. pedestal 2. axis of rolling A 3 axis of rolling B 4. bearings 5. clips 6. anterior pull bar 7. rear portion pull bars 8. sensors 9. launching tubes.
The specific embodiment
A kind of measurement mechanism of uneven momentum comprises: pedestal 1, axis of rolling A2 also comprise axis of rolling B3, bearing 4, clip 5, anterior pull bar 6, rear portion pull bar 7, sensor 8.Axis of rolling A2 and axis of rolling B3 are arranged in parallel, and axis of rolling A2, axis of rolling B3 upper surface middle part all have recessed cambered surface, and this cambered surface contacts with launching tube 9 cambered surfaces, and axis of rolling A2, axis of rolling B3 are connected with pedestal 1 bearing 4, and pedestal 1 is spirally connected with anterior pull bar 6.Anterior pull bar 6, rear portion pull bar 7 are spirally connected with sensor 8 two ends, and rear portion pull bar 7 is spirally connected with clip 5, clip 5 and launching tube 9 clampings.
When launching a guided missile, launching tube 9 is sliding on axis of rolling A2 and axis of rolling B3 under the momentum effect, because of clip 5 and launching tube 9 connect firmly, so launching tube 9 suffered momentums are delivered on the sensor 8 through clip 5.Sensor 8 directly records the numerical value of launching tube power, by the integral and calculating launching tube imbalance momentum to the time.
Claims (1)
1. the measurement mechanism of a uneven momentum comprises: pedestal (1), axis of rolling A(2), it is characterized in that also comprising axis of rolling B(3), bearing (4), clip (5), anterior pull bar (6), rear portion pull bar (7), sensor (8); Axis of rolling A(2) and axis of rolling B(3) be arranged in parallel, axis of rolling A(2), axis of rolling B(3) upper surface middle part all has recessed cambered surface, this cambered surface contacts with launching tube (9) cambered surface, axis of rolling A(2), axis of rolling B(3) be connected with pedestal (1) bearing (4), pedestal (1) and anterior pull bar (6) are spirally connected; Anterior pull bar (6), rear portion pull bar (7) are spirally connected with sensor (8) two ends, and rear portion pull bar (7) is spirally connected with clip (5), clip (5) and launching tube (9) clamping;
When launching a guided missile, launching tube (9) under the momentum effect at axis of rolling A(2) and axis of rolling B(3) go up to slide, because of clip (5) and launching tube (9) connect firmly, so the suffered momentum of launching tube (9) is delivered on the sensor (8) through clip (5); Sensor (8) directly records the numerical value of launching tube power, by the integral and calculating launching tube imbalance momentum to the time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110160628 CN102269540B (en) | 2011-06-15 | 2011-06-15 | Measurement device for unbalanced impulse |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110160628 CN102269540B (en) | 2011-06-15 | 2011-06-15 | Measurement device for unbalanced impulse |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102269540A true CN102269540A (en) | 2011-12-07 |
| CN102269540B CN102269540B (en) | 2013-12-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110160628 Active CN102269540B (en) | 2011-06-15 | 2011-06-15 | Measurement device for unbalanced impulse |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102269540B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104048557A (en) * | 2014-05-28 | 2014-09-17 | 北京航天发射技术研究所 | Ejection additional load simulation test system |
| CN104764551A (en) * | 2015-04-14 | 2015-07-08 | 南京理工大学 | Dynamic unbalance impulse testing device |
| CN108168384A (en) * | 2017-11-21 | 2018-06-15 | 北京强度环境研究所 | A kind of full bullet of guided missile tilts swing testing system |
| CN111623665A (en) * | 2020-03-31 | 2020-09-04 | 四川航天燎原科技有限公司 | Missile launching forward-impact recoil test system and method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1469240A (en) * | 1922-03-22 | 1923-10-02 | William C Palmer | Device for testing the recuperative power in a gun |
| US3727455A (en) * | 1970-12-05 | 1973-04-17 | Rheinmetall Gmbh | Impulse transmitter for dynamic devices for testing pieces of ordnance |
| EP0469665A1 (en) * | 1990-07-30 | 1992-02-05 | Schweizerische Eidgenossenschaft vertreten durch die Eidg. Munitionsfabrik Thun der Gruppe für Rüstungsdienste | Adjustment and test-firing device for small calibre weapons |
| CN2261615Y (en) * | 1996-05-30 | 1997-09-03 | 南京理工大学 | Testing apparatus for bore pressure of guns |
| CN201508270U (en) * | 2009-09-25 | 2010-06-16 | 宁波拓普减震系统股份有限公司 | Novel power assembly rotation inertia testing platform |
-
2011
- 2011-06-15 CN CN 201110160628 patent/CN102269540B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1469240A (en) * | 1922-03-22 | 1923-10-02 | William C Palmer | Device for testing the recuperative power in a gun |
| US3727455A (en) * | 1970-12-05 | 1973-04-17 | Rheinmetall Gmbh | Impulse transmitter for dynamic devices for testing pieces of ordnance |
| EP0469665A1 (en) * | 1990-07-30 | 1992-02-05 | Schweizerische Eidgenossenschaft vertreten durch die Eidg. Munitionsfabrik Thun der Gruppe für Rüstungsdienste | Adjustment and test-firing device for small calibre weapons |
| CN2261615Y (en) * | 1996-05-30 | 1997-09-03 | 南京理工大学 | Testing apparatus for bore pressure of guns |
| CN201508270U (en) * | 2009-09-25 | 2010-06-16 | 宁波拓普减震系统股份有限公司 | Novel power assembly rotation inertia testing platform |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104048557A (en) * | 2014-05-28 | 2014-09-17 | 北京航天发射技术研究所 | Ejection additional load simulation test system |
| CN104764551A (en) * | 2015-04-14 | 2015-07-08 | 南京理工大学 | Dynamic unbalance impulse testing device |
| CN108168384A (en) * | 2017-11-21 | 2018-06-15 | 北京强度环境研究所 | A kind of full bullet of guided missile tilts swing testing system |
| CN108168384B (en) * | 2017-11-21 | 2019-11-12 | 北京强度环境研究所 | A kind of full bullet inclination swing testing system of guided missile |
| CN111623665A (en) * | 2020-03-31 | 2020-09-04 | 四川航天燎原科技有限公司 | Missile launching forward-impact recoil test system and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102269540B (en) | 2013-12-18 |
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