CN203732077U - Detection device for rapidly detecting working state of attitude heading computer - Google Patents
Detection device for rapidly detecting working state of attitude heading computer Download PDFInfo
- Publication number
- CN203732077U CN203732077U CN201420053654.6U CN201420053654U CN203732077U CN 203732077 U CN203732077 U CN 203732077U CN 201420053654 U CN201420053654 U CN 201420053654U CN 203732077 U CN203732077 U CN 203732077U
- Authority
- CN
- China
- Prior art keywords
- attitude
- detection device
- balance
- test
- roll
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Abstract
The utility model discloses a detection device for rapidly detecting the working state of an attitude heading computer, aiming at providing an attitude heading rapid detection device which is convenient to detach and install, low in cost and capable of saving test time. The detection device disclosed by the utility model is realized by the following technical scheme: a pitching auxiliary rotary shaft is rotatably connected in a rotary hole of a rectangular body through a U-shaped groove of a saddle-shaped support below a balance plate; the saddle-shaped support and the rectangular body are located at the both sides of the length centre line of the balance plate respectively; a transversal rolling cam is composed of an H-shaped rolling wheel; the central rotary shaft of the H-shaped rolling wheel is rotatably connected between two right-angled plate support seats fixedly connected to a working platform and coupled below a two-foot cam groove at the free end of the saddle-shaped support by virtue of the two right-angled plate support seats. According to the detection device disclosed by the utility model, the problems that free rotation in a pitching direction and a transversal rolling direction can be realized only by a three-shaft rotary table, time and labour are consumed, the three-shaft rotary table is heavy and inconvenient to carry, and limit conditions are many in the prior art are solved.
Description
Technical field
The utility model relates to a kind of attitude of flight vehicle heading system ATE (automatic test equipment), simulated flight device attitude course, and for the attitude course computer on aircraft provides incentive environment, the pick-up unit of the duty of test pose course computer.
Background technology
Heading and attitude system ATE (automatic test equipment) is the ATE (automatic test equipment) based on ATE technology, and to the test of offing normal of air craft carried boat appearance various parts, the functional performance that completes parts detects, safeguards calibration and fault diagnosis.Main unit under test (UUT, Unit Under Test) comprises Magnetic Sensor, magnetic heading corrected Calculation device, course position indicator, navigator's indicator, full attitude integration gyro, group amplifier, control enclosure etc.Test macro adopts gpib bus and vxi bus mixed mode.Wherein vxi bus is system bus, is responsible for the transmission of system-wide data and measuring command.System bus is linked on central computer, and central computer is managed system-wide detection and failure diagnostic process.Along with the development of airborne equipment measuring technology, the comprehensive and test environment to Test coverage and the accordance of actual application environment are had higher requirement.Test according to import test platform classic method, if with more than 20 ten thousand yuan of a set of needs of import test platform three axle rate table.
Present stage to the method for testing of attitude course computer 18 is: 1, fixed test, is about to boat appearance computing machine and is fixed on the flight attitude of verifying aircraft on erecting frame; 2, discrete point test, is about to boat appearance computing machine and removes from erecting frame, manually carries out attitude adjustment, although can produce certain pitching, roll signal, can only carry out functional detection to the flight attitude of aircraft.The weak point that adopts above two kinds of modes to test is that test period length, test result and actual job state depart from larger, test fixture bulky complex, response curve is discontinuous, and first method can not produce needed pitching, roll signal, can not verify the flight attitude of aircraft completely, need just can realize freely rotating of pitch orientation and roll direction by three-axle table, take time and effort.And three-axle table itself is also very heavy, is inconvenient to carry, and restrictive condition is more, and test period is long, test result and actual job state depart from larger.And second method only can be carried out functional test, can not produce continual and steady signal reliably, degree of stability and poor reliability, can not carry out performance test, the flight attitude of the aircraft producing can not continue to keep, and can not carry out deep checking to the technical feature of product simultaneously.Technical requirement and functional requirement can not obtain complete test.
Summary of the invention
For the test period length, test result and the actual job state that overcome existing measuring technology existence depart from a larger difficult problem, the utility model provides a kind of easy accessibility, and cost is low, can save the attitude course speed detector of test duration.
The utility model solves the technical scheme that its technical matters adopts, the pick-up unit of a kind of fast detecting attitude course computer 18 duties, comprise for the balance of fixing tested aspect course computer 18 and pulling, the roll cam of the pitching auxiliary spindle 3 of simulated aircraft pitch attitude and simulated aircraft roll attitude, it is characterized in that: described pitching auxiliary spindle 4 is by connecting firmly the shape of a saddle support U-lag below balance is pulled, be rotatably connected to turning in hole of cuboid 2, the both sides that described shape of a saddle support and cuboid 2 lay respectively at described balance pulls length center line, described roll cam is made up of H shape roller 16, the centre rotational axis of this H shape roller 16 is by connecting firmly two L-square bearings on workbench 17, be rotatably connected between two L-square bearings, be coupled in the below of described shape of a saddle support free end bipod cam path, described centre rotational axis is spatially mutually vertical with described pitching auxiliary spindle 4, by rectangular coordinate system, H shape roller 16 is axially rotated with y, the lateral attitude of roll direction is provided, pitching auxiliary spindle 4 produces x axial-rotation, the attitude of pitch orientation is provided.
The utility model has following beneficial effect than prior art.
The utility model adopts and connects firmly below balance is pulled, spatially mutually vertical, the pitching auxiliary spindle of pitch orientation attitude and the roll cam that roll attitude is provided, only by two orthogonal rotatable two axle rotatable platforms, do not need just can realize freely rotating of pitch orientation and roll direction by three-axle table, solve boat appearance computing machine has been fixed on to the flight attitude of verifying aircraft on erecting frame, fixed test import test platform, can not produce pitching, roll signal, can only rely on three-axle table just can realize freely rotating of pitch orientation and roll direction, take time and effort, three-axle table heaviness, carrying is inconvenient, restrictive condition is many, test period is long, test result and actual job state depart from larger problem.Solve boat appearance computing machine has been removed from erecting frame, manually carried out attitude and adjust discrete point test, can not produce continual and steady signal reliably, the defect of poor reliability.
The utility model adopts the balance of fixing tested aspect course computer 18 to pull top board, its size can be adjusted according to the concrete size flexible design of attitude course computer 18, simulated aircraft provides the exquisiteness combination of pitching and roll attitude turning axle and bearing to make turntable that pitching, roll signal can be provided continuously, and can produce appropriate damping, platform can not fallen voluntarily, meet attitude course computer 18 Acceptance Test demands.
Easy accessibility.Added installation.The utility model only combination of the exquisiteness by structural member reduces the volume of turntable, has solved the shortcomings such as existing test fixture bulky complex and response curve be discontinuous.Provide continuously pitching, the roll pumping signal of sustainable variation according to test procedure, to realize to attitude course be.Can rotate arbitrarily in roll direction and pitch orientation, can check polarity.Panel can separate, and realizes two attitude course computers 18 are adjusted respectively to attitude, realizes the independent test of two boat appearance course computers.Quick, the full mode test of system.
The utility model can directly be installed to any workbench 17(as desk, lathe etc.).When test, can provide the signal of stable pitching, roll passage, not only can greatly save the test duration.Because test process is without the installation direction of the equipment of adjustment, therefore can in a check process, isolate all existing problems without interrupt test.
The top board that the utility model forms for two detachable panels of fixing tested aspect course computer 18, can change flexibly different size according to the concrete size of attitude course computer 18, after separating, top board can provide respectively boat appearance, course signal for two aspect course computers 18, by a main shaft and two upper rotating shafts, for simulated aircraft provides pitching and roll attitude, by two bearings of pitch axis and main shaft, exquisite combination makes turntable that pitching, roll signal can be provided continuously.
And the degree of tightness by regulating radiai adjustment pin on platform provides appropriate damping for main shaft, guarantee that rotatable platform can not fall voluntarily in test process, make equipment under test remain at any time present position.
The import test platform using relatively, the utility model can be saved nearly 3 times of costs.
Brief description of the drawings
Below in conjunction with drawings and Examples, the utility model is further illustrated.
Fig. 1 is the schematic three dimensional views of the utility model pick-up unit.
Fig. 2 is the front view of Fig. 1.
Fig. 3 is the left view of Fig. 1.
Fig. 4 is the use view of this pick-up unit.
In figure: in figure: 1 balance is pulled, 2 cuboids, 3 clamp nuts, 4 pitching auxiliary spindles, 5 hexagon socket head cap screws, 6 Compress Springs, 7 screws, 8 nuts, 9 bolts, 10 auricles, 11 roller radial peg, 12 L-square bearings, 13 radiai adjustment pins, 14 axle head eccentric pins, 15 main shafts, 16H shape roller, 17 workbenches, 18 attitude course computers.
Embodiment
Consult Fig. 1-Fig. 3.In embodiment described below, the pick-up unit of fast detecting attitude course computer 18 duties, comprise for the balance of fixing tested aspect course computer 18 pull 1, the pitching auxiliary spindle 4 of simulated aircraft pitch attitude and the roll cam of simulated aircraft roll attitude.Described roll cam is made up of H shape roller 16.Balance plate 1 is for putting and fixed pose course computer 18.Balance 1 the effect of pulling is simulation attitude course computer 18 installation site aboard.When test, attitude course computer 18 is exported attitude course signal by cable, adjust the attitude course of the attitude course simulated aircraft of balance plate 1, whether the duty of test pose course computer 18 is consistent with the attitude course of balance plate judges that whether attitude course computer 18 is normal, unanimously normal, no person is undesired.Pitching auxiliary spindle 4, by connecting firmly the shape of a saddle support U-lag below balance is pulled, is rotatably connected to turning in hole of cuboid 2, locks by clamp nut 34, produces axial x rotation, provides the motion of pitch orientation, simulated aircraft pitch attitude.The centre rotational axis of H shape roller 16, by connecting firmly two L-square bearings on workbench 17, is rotatably connected between two L-square bearings.Two rollers on H shape roller 16 connect firmly at main shaft 15 two ends by radial peg 13, are axially rotated and rest on optional position with y, and the lateral attitude of simulated aircraft roll direction is provided.L-square bearing 12 circular arc boss are provided with contact H shape roller 16 rotary middle spindle radiai adjustment pins 11.Two radiai adjustment pins 11 insert respectively two ends L-square bearing 12 and contact H shape roller 16 rotary middle spindles, the damping can increase big H shape roller 16 and rotate around the spindle time.Eccentric pin 14 is through L-square bearing 12 and H shape roller 16, when increasing the damping of big H shape roller 16, also ensures that stomach H type roller can be along main shaft axial translation while rotating around the spindle.The both sides that shape of a saddle support and cuboid 2 lay respectively at balance pulls 1 length center line, H shape roller 16 is coupled in the below of described shape of a saddle support free end bipod cam path.Centre rotational axis is spatially mutually vertical with described pitching auxiliary spindle 4, and by rectangular coordinate system, H shape roller 16 is axially rotated with y, and the lateral attitude of roll direction is provided, and pitching auxiliary spindle 4 produces x axial-rotation, and the attitude of pitch orientation is provided.
Balance is pulled 1 and can be made up of two separable independent assortment panels, as the top board of fastening aircraft attitude course computer 18.Balance is provided with the mounting hole for fastening aircraft attitude course computer 18 in the middle of pulling 1.Two balances are pulled the independent assortment panel of 1 separation by the auricle 10 connecting firmly on its lower butt joint edge, are fixed together by bolt 9 and nut 8 through two auricles 10.Auricle 10 is fixed on balance and pulls 1 below by being set with the screw 7 of Compress Spring 6 and hexagon socket head cap screw 5.After bolt 9 is taken off, two balance plates 1 will separate completely, two attitude course computers 18 will be placed in respectively on the independent assortment panel of balance plate 1, can realize the simulation that roll, course angle are provided for two attitude course computers 18 simultaneously.When this rotatable platform need to be tested an attitude course computer 18 simultaneously, two balances are pulled to 1 combination and be fixed as one.
Consult Fig. 4.The present invention is fixed on desk, then will needs checkout equipment boat appearance course computer to be placed on the balance plate 1 of rotatable platform, test cable one end is connected to the other end on boat appearance course computer and is connected on the primary flight display PFD of aircraft.When test, boat appearance course computer is powered up, and output boat appearance, the course data of test boat appearance course computer.Need to carry out roll inspection time, tester directly pulls the balance plate 1 of two axle rotatable platforms, and the appearance computing machine that makes to navigate is tilted to the right, the horizon instrument right avertence of the upper full compass picture disply of primary flight display PFD, otherwise, horizon instrument left avertence.While carrying out pitching inspection, pull the balance plate 1 of the attitude course computer 18 2 axle rotatable platforms in rack, the appearance computing machine that makes to navigate upwards comes back, and the horizon instrument of the upper full compass picture disply of PFD moves downward, otherwise horizon instrument moves upward.This device can provide multiple attitudes to aircraft, there is the independent mode in four kinds of upper and lower, left and right, and by these four kinds of independent modes, also can mutually be combined into upper left, upper right, bottom left, four kinds of array modes of bottom right, increase the attitude of supplying with aircraft, increased the complete of test.
Claims (4)
1. the pick-up unit of a fast detecting attitude course computer duty, comprise for the balance of fixing tested aspect course computer (18) and pulling, the pitching auxiliary spindle (3) of simulated aircraft pitch attitude and the roll cam of simulated aircraft roll attitude, it is characterized in that: described pitching auxiliary spindle (4) is by connecting firmly the shape of a saddle support U-lag below balance is pulled, be rotatably connected to turning in hole of cuboid (2), the both sides that described shape of a saddle support and cuboid (2) lay respectively at described balance pulls length center line, described roll cam is made up of H shape roller (16), the centre rotational axis of this H shape roller (16) is by connecting firmly two L-square bearings on workbench (17), be rotatably connected between two L-square bearings, be coupled in the below of described shape of a saddle support free end bipod cam path, described centre rotational axis is spatially mutually vertical with described pitching auxiliary spindle (4), by rectangular coordinate system, H shape roller (16) is axially rotated with y, the lateral attitude of roll direction is provided, pitching auxiliary spindle (4) produces x axial-rotation, the attitude of pitch orientation is provided.
2. by the pick-up unit of fast detecting attitude course computer duty claimed in claim 1, it is characterized in that, L-square bearing (12) circular arc boss is provided with contact H shape roller (16) rotary middle spindle radiai adjustment pin (11).
3. by the pick-up unit of fast detecting attitude course computer duty claimed in claim 1, it is characterized in that, balance is pulled (1) and is made up of two separable independent assortment panels, as the top board of fastening aircraft attitude course computer (18).
4. by the pick-up unit of fast detecting attitude course computer duty claimed in claim 1, it is characterized in that, two balances are pulled independent assortment panel that (1) separate by the auricle (10) connecting firmly on its lower butt joint edge, are fixed together by bolt (9) and nut (8) through two auricles (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420053654.6U CN203732077U (en) | 2014-01-27 | 2014-01-27 | Detection device for rapidly detecting working state of attitude heading computer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420053654.6U CN203732077U (en) | 2014-01-27 | 2014-01-27 | Detection device for rapidly detecting working state of attitude heading computer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203732077U true CN203732077U (en) | 2014-07-23 |
Family
ID=51202143
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420053654.6U Expired - Fee Related CN203732077U (en) | 2014-01-27 | 2014-01-27 | Detection device for rapidly detecting working state of attitude heading computer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203732077U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104571124A (en) * | 2014-12-17 | 2015-04-29 | 华中科技大学 | Three-degree-of-freedom attitude simulation device for underwater vehicle |
| CN114061655A (en) * | 2021-10-29 | 2022-02-18 | 中国石油天然气集团有限公司 | Dynamic non-contact transmission unit test evaluation device |
-
2014
- 2014-01-27 CN CN201420053654.6U patent/CN203732077U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104571124A (en) * | 2014-12-17 | 2015-04-29 | 华中科技大学 | Three-degree-of-freedom attitude simulation device for underwater vehicle |
| CN104571124B (en) * | 2014-12-17 | 2017-01-18 | 华中科技大学 | Three-degree-of-freedom attitude simulation device for underwater vehicle |
| CN114061655A (en) * | 2021-10-29 | 2022-02-18 | 中国石油天然气集团有限公司 | Dynamic non-contact transmission unit test evaluation device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107741238B (en) | Angular rate gyro testing device | |
| CN106289710B (en) | Aerofoil profile model dynamometric system | |
| CN107575437B (en) | Performance test experiment table for aviation hydraulic pump and hydraulic pipeline | |
| CN102620892B (en) | Dynamic balance testing method for rotatable part | |
| CN101509820B (en) | Triaxial air bearing table balance method and apparatus thereof | |
| CN205262671U (en) | Torsion -testing appearance calibrating device | |
| CN104776861B (en) | Flexible calibration device for calibrating wind tunnel vision measurement system | |
| CN105699100B (en) | The random adjustable image-type four-wheel position finder calibrating installation of sync bit | |
| WO2019007259A1 (en) | Device and method for measuring six-degree-of-freedom displacement of vehicle wheel during suspension characteristic test | |
| CN203732077U (en) | Detection device for rapidly detecting working state of attitude heading computer | |
| CN103117444B (en) | Arc guide rail angle adjustment testing frame for field strength antenna | |
| CN209279936U (en) | It is a kind of for detecting the detection device of wheel hub jitter values | |
| CN109387329A (en) | Small drone weight center of gravity measuring device and measuring method | |
| CN104458125A (en) | Device for measuring center of mass | |
| CN103234765B (en) | Split reassembling type vehicle four-wheel position finder calibrating installation | |
| CN105466663B (en) | The accurate device for measuring wind-tunnel Transonic Test section local air flow angle of deviation | |
| CN204535922U (en) | A kind of mass property measures auxiliary clamp | |
| CN106813696B (en) | Six-degree-of-freedom control device | |
| CN105679178A (en) | High-precision double-wheel shaft double-vernier earth's axis precession demonstration and quantitative measurement experiment instrument | |
| CN108106851B (en) | Small unmanned aerial vehicle engine push-pull force test acquisition test system | |
| CN104477409A (en) | Device and method for allowing three-axis turntable to be uniaxial | |
| CN204269296U (en) | A kind of centroid measurement equipment | |
| CN203870468U (en) | Mechanical failure debugging device used for rotorcraft | |
| CN105841957A (en) | Device used for testing torque output of solar sailboard drive mechanism and test platform body | |
| CN110186431A (en) | A kind of testing apparatus for verticality and its testing calibration method of axis |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140723 Termination date: 20180127 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |