CN1523334A - Military helmet gravity center and rotating inertia metering equipment - Google Patents
Military helmet gravity center and rotating inertia metering equipment Download PDFInfo
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- CN1523334A CN1523334A CNA031045367A CN03104536A CN1523334A CN 1523334 A CN1523334 A CN 1523334A CN A031045367 A CNA031045367 A CN A031045367A CN 03104536 A CN03104536 A CN 03104536A CN 1523334 A CN1523334 A CN 1523334A
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Abstract
The invention relates to a device to test center of gravity and moment of inertia of the military helm, it is set with a wiggly table frame which is fixed with a fixing helm box, a base is set under the fixing helm box, a butterfly board is set on the top of the base, a bending pivot bearing is installed between the wiggly table frame and the butterfly board, three force sensors are installed between the butterfly board and the basal plate, a vibrating-frequency sensor is installed between the wiggly table frame and the basal plate, a cam lift locking mechanism is set under the butterfly board and composed of cam post-rod mechanism and spacing slide board, where the force and vibrating frequency sensors are connected with the computer circuit data through transmission lines. It provides an objective and quantitative evaluation basis for stable parameters of military helm. It heightens precision and speed of measuring moment of inertia, easy to operate.
Description
Technical field
The present invention relates to a kind of military helmet center of gravity and rotational inertia test apparatus, but use the centre of gravity place and the moment of inertia of the various model military helmets of this device rapid test.
Technical background
The stability of military helmet is to influence the key factor that the helmet is worn performance.Evaluation to helmet stability can divide subjective assessment and two kinds of methods of objective evaluation.The former refers to that mainly the personnel's that wear according to the helmet subjective feeling estimates qualitatively to the stability of the helmet; The latter then is that the special-purpose apparatus of utilization is measured the objective parameter that characterizes stability, provides quantitative evaluation.At present, the evaluation of helmet stability mostly is subjective qualitative evaluation, and in the mode that size of the organization is tried on, carried out survey, information obtains that the cycle is long, and influence factor is many, and is mainly qualitative information, and information fuzzy is unfavorable for theoretical analysis.Aspect the research of military helmet stability objective evaluation, the Asko Vilenius of Univ Melbourne Australia has set up the evaluating apparatus of a cover SPH-4 military helmet dynamic performance in its doctorate paper, this device comprises the multiple sensor that links to each other with computing machine, directly be loaded on the SPH-4 helmet that test personnel wear, obtain parameters such as acceleration, displacement, vibration frequency, hysteresis performance.This device is comparatively numerous and diverse, and data are subjected to the influence of helmet wearer physiologic factor bigger.In addition, US military research institution is more to comfortableness, the Study on Stability of military helmet, but up to the present, does not see the open source literature report that the dependence test device is arranged.Domestic still do not have similar document and a patent report openly studied yet.Therefore, need to propose a kind of military helmet center of gravity and rotational inertia test apparatus.
Summary of the invention
The object of the present invention is to provide a kind of military helmet center of gravity and rotational inertia test apparatus, but use the centre of gravity place and the moment of inertia of the various model military helmets of this device rapid test.
The objective of the invention is to realize: a kind of military helmet center of gravity and rotational inertia test apparatus by following technical proposals, this device top is provided with a wiggly table frame, be fixed with a fixing helm box on this wiggly table frame, this device bottom is provided with a base, this base top is provided with butterfly plate, a crooked fulcrum roller is housed between described wiggly table frame and the butterfly plate, three force transducers are installed between described butterfly plate and the base plate, a vibration frequency sensor is installed between described wiggly table frame and the base plate, be provided with a cam lifting lockable mechanism below the described butterfly plate, described cam lifting lockable mechanism is made of described force transducer cam ejection pin mechanism and limit skateboard, the vibration frequency sensor is connected with the computer circuits data by transmission line.
When the present invention used, general's helmet was inverted in the fixing helm box, and the Z of center of gravity is the reference position to coordinate with helmet top.For measuring the center principal moment of inertia and the principal direction of the helmet, and and then determine moment of inertia around arbitrary axis, must measure the moment of inertia of six direction.This device rocks the pivot center direction to be determined, changes helmet rotation direction, can record the moment of inertia on the different directions.
The present invention has following advantage:
1, the present invention provides a kind of objective, quantitative evaluation foundation to the military helmet stability parameter by the measurement of centre of gravity place and moment of inertia.
2, the present invention realizes the conversion of measuring task by cam lifting lockable mechanism, focus position measurement and rotation inerttia can be realized on same set of measurement mechanism, because of knowing centre of gravity place in real time, needn't painstakingly center of gravity be adjusted on the rotation, be aided with calculating and can get moment of inertia.Improved the precision and the speed of rotation inerttia, and easy to operate.
3, the present invention adopts crooked fulcrum roller to realize the single-degree-of-freedom twisting motion of low frequency, little damping, large amplitude, has avoided the general axis bearing structure complicated and have friction, gap, collision, problem such as lubricated, has improved measuring accuracy.
4, the present invention has realized and the data transfer of computing machine that the user can finish setting, measuring operation, data processing, data base administration and the data presentation of measuring condition and print under the guide of software, easy to use.
Description of drawings
The invention will be further described below in conjunction with drawings and Examples
Fig. 1 is a structural representation of the present invention
Fig. 2 is that V-type cushion block of the present invention uses synoptic diagram
Fig. 3 is wiggly table frame vertical view of the present invention (the B-B cut-open view of Fig. 1)
Fig. 4 is a crooked fulcrum roller synoptic diagram of the present invention
Fig. 5 is the cut-open view (the A-A cut-open view of Fig. 4) of crooked fulcrum roller
Fig. 6 is butterfly plate vertical view of the present invention (the C-C cut-open view of Fig. 1)
Fig. 7 is a cam ejection pin mechanism synoptic diagram of the present invention
Fig. 8 is a metering circuit block diagram of the present invention
Fig. 9 is a frequency sensor circuit diagram of the present invention
Figure 10 is sensor circuit of the present invention and serial ports of computers communication synoptic diagram
Embodiment
Referring to accompanying drawing 1, Fig. 3 and Fig. 4, military helmet center of gravity of the present invention and rotational inertia test apparatus top are provided with a wiggly table frame 8, be fixed with a fixing helm box 1 on this wiggly table frame, this device bottom is provided with a base 13, this base is to be a rectangular base shape, be provided with base plate 24, front panel, squab panel, left side wallboard 23 and right wallboard 14, this base top is provided with butterfly plate 11, a crooked fulcrum roller 9 is housed between described wiggly table frame and the butterfly plate, three force transducers 25 are installed between described butterfly plate and the base plate, a vibration frequency sensor 26 is installed between described wiggly table frame and the base plate, be provided with a cam lifting lockable mechanism 20 below the described butterfly plate, described cam lifting lockable mechanism is made of described force transducer cam ejection pin mechanism and limit skateboard, the vibration frequency sensor is connected with the computer circuits data by transmission line.
The fixing helm box 1 of present embodiment is used for fixing military helmet 5.Fixing helm box adopts polylith organic glass 4 to make, and its inwall size equates with the full-size of the length of military helmet to be measured.Army's helmet is inverted in the box, and the Z of center of gravity is the reference position to coordinate (vertically to) with helmet top.Helmet attitude lock-screw 2 is arranged on the fixing helm box and adjust slide block 3, can be used to regulate the relative position between military helmet and the fixing helm box.
For measuring the center principal moment of inertia and the principal direction of military helmet, and and then determine moment of inertia around arbitrary axis, must measure the moment of inertia of six direction.The pivot center direction of rocking of the present invention is determined, changes military helmet rotation direction, can record the moment of inertia on the different directions.
Wherein, the moment of inertia of X, Y, Z direction can for the moment of inertia of measured X Y, YZ, ZX direction, can be provided with a V-type cushion block 27 directly by recording after the reference planes that change fixing helm box between described fixing helm box and described wiggly table frame.Referring to shown in Figure 2, the angle on two inclined-planes of described V-type cushion block is 45 ° when being placed on fixing helm box on the V-type cushion block, under the deadweight effect of fixing helm box, two adjacent side is fitted on two inclined-planes of V-type cushion block, the rotation center 28 of fixing helm box can be realized the location of fixing helm box on XY, YZ, ZX direction thus by the center of V-type cushion block.
Referring to Fig. 1 and Fig. 3, wiggly table frame 8 is worktable of carrying fixing helm box, and this stand main body is an aluminium disks, the disk back side is spoke and rib structure, there are two chutes that intersect vertically 801 in the front, and four continuously adjustable slide blocks 7 in position are arranged in the chute, and screw 6,10 is arranged on the slide block.During use, earlier four slide blocks are screwed on the disk of wiggly table frame, fixing helm box is placed, moving slider makes it contact with fixing helm box then, tightens the screw on the slide block at last, fixedly fixing helm box.When using the V-type cushion block, a pair of slide block on the wiggly table frame is the V-type cushion block fixedly, and another is to fixing fixing helm box then.The chute edge posts rule, can read the position of fixing helm box thus.Be provided with a horizontal bubble 802 in the middle of the wiggly table frame, can detect the horizontal situation of wiggly table frame.The moved end of wiggly table frame lower surface and crooked fulcrum roller 9 is affixed, and the center of circle of wiggly table frame is on the pivot center of crooked fulcrum roller.One stop hole (not illustrating among the figure) is arranged on wiggly table frame, and this stop hole communicates with stop hole on the crooked fulcrum roller fixed part, can reach the purpose that stops the wiggly table frame rotation by a stop pin.
The free torsional oscillation of wiggly table frame is realized by crooked fulcrum roller.Referring to Fig. 4 and Fig. 5, described crooked fulcrum roller has two pairs to be the staggered spring leaf of installing 903,904 of cruciform, two pairs of cross-spring sheets are vertical mutually in the space, its two ends are fixed on the bearing body 905 by screw 902 respectively, bearing body is installed by flange 901 and described wiggly table frame, and an end affixed with described wiggly table frame is the moved end, and an end affixed with described butterfly plate is quiet end, by the flexural deformation of four spring leafs, realize the rotation of moved end with respect to quiet end.The size of cross-spring sheet designs and checks according to the requirement of rigidity, intensity and stability.
Referring to Fig. 1 and Fig. 7, cam ejection pin mechanism of the present invention is made up of eccentric wheel 19, cam base 21, push rod disk 22, transmission shaft 15, bearing pin 16, disc type sleeve 17, dog screw 18, and the push rod disk contacts with butterfly plate, drives the butterfly plate motion.Referring to Fig. 1 and Fig. 6, there are 29, two limit skateboards of a limit skateboard described butterfly plate both sides, and each is T-shaped, be fixed on the base plate of base, for moving up and down of butterfly plate provides guiding, its top is provided with baffle plate 12, when the butterfly plate upward movement is locked during to this baffle plate.When measuring, the manual control cam ejection pin mechanism descends wiggly table frame, and this moment, dish plate contacted with three force transducers on being installed in base plate, and device enters measurement center of gravity operating mode.When needs conversion measuring task of the present invention is promptly carried out the surveying work of military helmet moment of inertia, the manual control cam ejection pin mechanism rises wiggly table frame, dish plate moves up to simultaneously and compresses baffle position, the not moved end and the dish plate of crooked fulcrum roller are locked on the base, and wiggly table frame can be done the FREE TORSION motion.If a stop pin is inserted in the stop hole of wiggly table frame, the present invention can withdraw from surveying work.
Three pressure transducers that are installed on the base plate become DATA REASONING of the present invention and treatment circuit with a vibration frequency sensor with other test instrumentations and calculation mechanism, referring to shown in Figure 8.When measuring gravity, pressure transducer utilizes the bending strain bridge circuit that force signal is converted into electric signal, and this signal carries out linear amplification and shaping through amplification and rectification circuit, handles the back by modulus (A/D) conversion and single-chip microcomputer and shows the numerical value that records with nixie display.Survey frequency adopts infrared sensor, and this sensor is made up of an infrared-emitting diode and an infrared reception triode.One catch is arranged on the wiggly table frame, and when worktable was done twisting vibration, catch moved back and forth transmitting and receiving between the end of sensor, and the sensor measurement frequency multiply by the catch number for the stand vibration frequency.Referring to shown in Figure 9, add the voltage bias of one+12V at the emitting diode end, be connected in series one 462 Ω current-limiting resistance, make electric current less than 30mA, diode drop is 1.2-2V.The receiving end triode adopts the common collector connection, and output data is handled through amplifying shaping, A/D conversion and single-chip microcomputer, obtains the vibration period of wiggly table frame, is shown on the nixie display.Be provided with a plurality of control buttons on the control panel of above-mentioned nixie display, can be provided with options such as the baud rate of zero point of measuring numerical value, range, low alarm limit, serial communication and data addresses.Be connected by serial data line between described force transducer and vibration frequency sensor and the computing machine, referring to shown in Figure 10.Amplification and rectification circuit, modulus A/D conversion and single-chip microcomputer processing and Displaying Meter are packaged into an integral body, and the subsequent conditioning circuit of the subsequent conditioning circuit of three force transducers and measurement torsional frequency is packaged into a dynamometry instrument and a frequency instrument respectively.Measurement data after the above-mentioned instrument processing transmits by RS485 communication data line, input computing machine after the RS485-RS232 conversion, and the service data process software calculates centre of gravity place and the moment of inertia of testing the helmet.
When using the present invention to carry out the military helmet measurement, regulate wiggly table frame earlier and be horizontal, connect metering circuit, open measurement instrument and computing machine.Then, operation " army's helmet center of gravity and moment of inertia testing software " on computers, access the software main frame window, just can carry out initial setting to helmet box parameter and army's helmet center of gravity parameter behind click " parameter setting " menu, wherein helmet box parameter can pre-deposit helmet box database.Just can select the army of entering helmet center of gravity measurement interface or rotation inerttia interface after clicking " army's helmet is measured " menu, select and fill in relevant measurement option, under the guide of software, finish measurement and data handling procedure.Measuring the data obtained can the army's of depositing in helmet database, can inquire about in case of necessity.Helmet box database and army's helmet database enter by clicking " database retrieval " menu.In addition, the user can obtain the help of operation instructions from the Help menu.
Claims (2)
1, a kind of military helmet center of gravity and rotational inertia test apparatus, it is characterized in that: this device top is provided with a wiggly table frame (8), be fixed with a fixing helm box (1) on this wiggly table frame, this device bottom is provided with a base (13), this base top is provided with butterfly plate (11), a crooked fulcrum roller (9) is housed between described wiggly table frame and the butterfly plate, three force transducers (25) are installed between described butterfly plate and the base plate, a vibration frequency sensor (26) is installed between described wiggly table frame and the base plate, be provided with a cam lifting lockable mechanism (20) below the described butterfly plate, described cam lifting lockable mechanism is made of described force transducer cam ejection pin mechanism and limit skateboard, the vibration frequency sensor is connected with the computer circuits data by transmission line.
2, military helmet center of gravity according to claim 1 and rotational inertia test apparatus is characterized in that: be provided with a V-type cushion block (27) between described fixing helm box and the described wiggly table frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031045367A CN100340849C (en) | 2003-02-17 | 2003-02-17 | Military helmet gravity center and rotating inertia metering equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031045367A CN100340849C (en) | 2003-02-17 | 2003-02-17 | Military helmet gravity center and rotating inertia metering equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1523334A true CN1523334A (en) | 2004-08-25 |
| CN100340849C CN100340849C (en) | 2007-10-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB031045367A Expired - Fee Related CN100340849C (en) | 2003-02-17 | 2003-02-17 | Military helmet gravity center and rotating inertia metering equipment |
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| CN (1) | CN100340849C (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100453992C (en) * | 2005-09-17 | 2009-01-21 | 冯昌荣 | Precision balance measuring instrument |
| CN101793583A (en) * | 2010-03-19 | 2010-08-04 | 天津修船技术研究所 | Gravity center measurement instrument of propeller blade with variable screw pitch |
| CN103003680A (en) * | 2010-07-08 | 2013-03-27 | 国立大学法人东京工业大学 | Rigid body property identification device and rigid body property identification method |
| CN105181245A (en) * | 2015-08-11 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plate inertia measurement apparatus |
| CN105737827A (en) * | 2016-03-24 | 2016-07-06 | 苏州合欣美电子科技有限公司 | Measuring system for carrier moving track based on accelerated speed and angular speed |
| CN106768632A (en) * | 2017-01-06 | 2017-05-31 | 南京航空航天大学 | High accuracy helmet mass property measuring system and its measuring method |
| CN109932130A (en) * | 2019-04-09 | 2019-06-25 | 中国人民解放军空军特色医学中心 | A kind of gravity center measurement device and center of gravity measurement method |
| CN111060253A (en) * | 2019-12-12 | 2020-04-24 | 南京乾利合科技有限责任公司 | Gravity center and inertia adjusting device for ship and ocean engineering model |
| CN112697345A (en) * | 2020-12-04 | 2021-04-23 | 哈尔滨工业大学 | Method and device for measuring rigid body inertia tensor |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2572378Y (en) * | 2002-10-18 | 2003-09-10 | 中国人民解放军总后勤部军需装备研究所士兵系统研究中心 | Tester for gravity center and rotary inertia of military helmet |
-
2003
- 2003-02-17 CN CNB031045367A patent/CN100340849C/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100453992C (en) * | 2005-09-17 | 2009-01-21 | 冯昌荣 | Precision balance measuring instrument |
| CN101793583A (en) * | 2010-03-19 | 2010-08-04 | 天津修船技术研究所 | Gravity center measurement instrument of propeller blade with variable screw pitch |
| CN103003680A (en) * | 2010-07-08 | 2013-03-27 | 国立大学法人东京工业大学 | Rigid body property identification device and rigid body property identification method |
| US9188503B2 (en) | 2010-07-08 | 2015-11-17 | Tokyo Institute Of Technology | Rigid body characteristic identification system and rigid body characteristic identification method |
| CN103003680B (en) * | 2010-07-08 | 2015-11-25 | 国立大学法人东京工业大学 | Rigid body characteristic recognition device and rigid body characteristics recognizing method |
| CN105181245B (en) * | 2015-08-11 | 2018-08-24 | 中国航空工业集团公司西安飞机设计研究所 | Plate inertia measuring device |
| CN105181245A (en) * | 2015-08-11 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plate inertia measurement apparatus |
| CN105737827A (en) * | 2016-03-24 | 2016-07-06 | 苏州合欣美电子科技有限公司 | Measuring system for carrier moving track based on accelerated speed and angular speed |
| CN106768632A (en) * | 2017-01-06 | 2017-05-31 | 南京航空航天大学 | High accuracy helmet mass property measuring system and its measuring method |
| CN109932130A (en) * | 2019-04-09 | 2019-06-25 | 中国人民解放军空军特色医学中心 | A kind of gravity center measurement device and center of gravity measurement method |
| CN111060253A (en) * | 2019-12-12 | 2020-04-24 | 南京乾利合科技有限责任公司 | Gravity center and inertia adjusting device for ship and ocean engineering model |
| CN112697345A (en) * | 2020-12-04 | 2021-04-23 | 哈尔滨工业大学 | Method and device for measuring rigid body inertia tensor |
| CN112697345B (en) * | 2020-12-04 | 2023-04-07 | 哈尔滨工业大学 | Method and device for measuring rigid body inertia tensor |
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| Publication number | Publication date |
|---|---|
| CN100340849C (en) | 2007-10-03 |
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Granted publication date: 20071003 Termination date: 20100217 |