CN204988755U - Flight gesture simulation frock - Google Patents
Flight gesture simulation frock Download PDFInfo
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- CN204988755U CN204988755U CN201520580252.6U CN201520580252U CN204988755U CN 204988755 U CN204988755 U CN 204988755U CN 201520580252 U CN201520580252 U CN 201520580252U CN 204988755 U CN204988755 U CN 204988755U
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- flight attitude
- connecting rod
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Abstract
The utility model provides a flight gesture simulation frock, flight gesture simulation frock are the bilateral symmetry structure, including loading platform (1), support (2), motor (3) and electric machine drive mechanism (4), motor (3) make loading platform (1) rotate for support (2) through electric machine drive mechanism (4). The advantage does: the actual state of flight of simulated aircraft that can furthest, consequently, the machine that will be surveyed carries an electronic equipment install this flight gesture simulation frock after, can make the machine carry electronic equipment and be in aerial operating condition, when the test system carried an electronic equipment and tests the machine of aerial state, the machine of can discovering carried the problem that electronic equipment probably appears in actual flight to improve the test accuracy, simple structure still has, high advantage is truly spent in the simulation of reliable and stable and state of flight.
Description
Technical field
The utility model belongs to field of aerospace technology, is specifically related to a kind of flight attitude simulation frock.
Background technology
Air environment is the important component part of aircraft, the kind of air environment is more, such as, for measure aircraft altitude height indicator, for measure aircraft position air pressure barometer and for acceleration transducer of measuring aircraft flight acceleration etc.The serviceability of air environment directly determines other air environment serviceabilitys and can aircraft fly safely.Therefore, need often to carry out performance test to air environment, ensure its reliable and stable work.
In prior art, test macro is when carrying out performance test to all kinds of air environment, mainly performance test is carried out to the air environment of stationary state, this kind of method of testing mainly has the following disadvantages: because air environment is when real work, can change along with the change of aspect, that is, the aerial duty of air environment is frequent variations, and simply performance test is carried out to the air environment of stationary state, obviously there is the inaccurate problem of test result.
Utility model content
For the defect that prior art exists, the utility model provides a kind of flight attitude to simulate frock, can effectively solve the problem.
The technical solution adopted in the utility model is as follows:
The utility model provides a kind of flight attitude to simulate frock, described flight attitude simulation frock is bilateral symmetry, comprises loading platform (1), support (2), motor (3) and motor-driven mechanism (4);
Wherein, described loading platform (1) comprises and loads mainboard (1-1) and symmetry is fixedly mounted on left plate (1-2) and the right plate (1-3) of described loading mainboard (1-1) left and right sides;
Described support (2) comprises left socle (2-2) and the right support (2-3) that link (2-1) and symmetry are fixedly mounted on described link (2-1) left and right sides;
In addition, described support (2) and described loading platform (1) are arranged up and down in opposite directions, and described left socle (2-2) is rotatably installed to described left plate (1-2); Described right support (2-3) is rotatably installed to described right plate (1-3);
Described motor (3) makes described loading platform (1) rotate relative to described support (2) by described motor-driven mechanism (4).
Preferably, described left socle (2-2) is rotatably installed to described left plate (1-2) by the 1st ball bearing; Described right support (2-3) is rotatably installed to described right plate (1-3) by the 2nd ball bearing.
Preferably, described 1st ball bearing and described 2nd ball bearing are low resistance ball bearing.
Preferably, also comprise: antenna (5); Described antenna (5) is fixedly installed to the lower surface of described loading mainboard (1-1); Further, described antenna (5) is electrically connected with the tested air environment being fixedly mounted on described loading mainboard (1-1) upper surface.
Preferably, described antenna (5) is symmetrical integrally formed structure, comprising: left connecting rod (5-1), right connecting rod (5-2), left Ji (5-3) and right Ji (5-4); Wherein, the left side of described left connecting rod (5-1) is fixedly connected with described left Ji (5-3); The right side of described left connecting rod (5-1) is fixedly connected with the left side of described right connecting rod (5-2); The right side of described right connecting rod (5-2) is fixedly connected with described right Ji (5-4).
Preferably, described motor-driven mechanism (4) is remote-controlled motor-driven mechanism.
The flight attitude simulation frock that the utility model provides has the following advantages:
Can simulated aircraft actual flight state to greatest extent, therefore, after tested air environment being installed to this flight attitude simulation frock, air environment can be made to be in aerial duty, when the air environment of test macro to airborne status is tested, air environment possibility produced problem in practical flight can be found, thus improve test accuracy; Also there is simple, the reliable and stable and state of flight simulates real solidity advantages of higher of structure.
Accompanying drawing explanation
The flight attitude simulation frock that Fig. 1 provides for the utility model aloft state of flight time structural representation;
The structural representation of flight attitude simulation frock when ground installment state that Fig. 2 provides for the utility model.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in detail:
The deficiency of performance test can only be carried out to the air environment of stationary state for solving existing test macro, the utility model provides a kind of flight attitude to simulate frock, this flight attitude simulation frock has distant control function, therefore, both the simulation of flight attitude can have been carried out on ground, also can hang under high state, by the airflight state of telecontrol analog aircraft, therefore, after tested air environment is installed to this frock, the performance test of the air environment to state of flight can be realized, thus find the potential problems that air environment exists in actual use.
Composition graphs 1, the utility model provides a kind of flight attitude to simulate frock, and flight attitude simulation frock is bilateral symmetry, comprises loading platform 1, support 2, motor 3 and motor-driven mechanism 4;
Wherein, loading platform 1 comprises and loads mainboard 1-1 and symmetry and be fixedly mounted on the left plate 1-2 and right plate 1-3 that load the mainboard 1-1 left and right sides;
Support 2 comprises left socle 2-2 and the right support 2-3 that link 2-1 and symmetry are fixedly mounted on the link 2-1 left and right sides;
In addition, support 2 and loading platform about 1 are arranged in opposite directions, and left socle 2-2 is rotatably installed to left plate 1-2; Right support 2-3 is rotatably installed to right plate 1-3; In specific implementation, left socle 2-2 is rotatably installed to left plate 1-2 by the 1st ball bearing; Right support 2-3 is rotatably installed to right plate 1-3 by the 2nd ball bearing.In addition, as far as possible little for ensureing the rotary resistance of loading platform, the 1st ball bearing and the 2nd ball bearing can all adopt low resistance ball bearing.In FIG, 7 low resistance ball bearing is namely represented.
Motor 3 makes loading platform 1 rotate relative to support 2 by motor-driven mechanism 4.Wherein, motor-driven mechanism adopts remote-controlled motor-driven mechanism, and is powered by accumulator jar.
The said structure that the utility model provides, can simulated aircraft actual flight state to greatest extent, in addition, also has the advantage that structure is simple, lightweight and cost is low.
The using method of above-mentioned flight attitude simulation frock is:
(1) ground test
Tested air environment 6 being fixedly installed to loading platform, when carrying out ground test, making support support on ground or other bases, as shown in Figure 2, be the structural representation of flight attitude simulation frock when ground; The mode of hand rotation loading platform can be adopted, carry out angle definite value correlation test, such as, be fixed measurement every 15 °, realize the test of 0 ~ 180 ° of scope; Also motor can be adopted to drive the mode of loading platform rotation, realize the performance test of air environment under motion state.
(2) test in the air
Tested air environment is fixedly installed to loading platform, by suspender, flight attitude is simulated frock and hang in the air, as shown in Figure 1, be flight attitude simulation frock aloft state of flight time structural representation; Then, adopt remote control mode remote control motor, loading platform is rotated, and the air environment carried by loading platform carries out data back, air environment data is returned by zigbee simultaneously.In specific implementation, the aerial loading platform of the remote controlled with signals of 40m can be met or exceeded by distance, realize 0 ~ 180 ° and freely rotate.
In addition, for aerial test, owing to needing that the status data of air environment or measurement data are returned to land station, therefore, flight attitude simulation frock is also provided with antenna 5; Antenna 5 is fixedly installed to the lower surface loading mainboard 1-1; Further, antenna 5 be fixedly mounted on the tested air environment loading mainboard 1-1 upper surface and be electrically connected.
Antenna 5 is symmetrical integrally formed structure, comprising: left connecting rod 5-1, right connecting rod 5-2, left Ji 5-3 and right Ji 5-4; Wherein, the left side of left connecting rod 5-1 is fixedly connected with left Ji 5-3; The right side of left connecting rod 5-1 is fixedly connected with the left side of right connecting rod 5-2; The right side of right connecting rod 5-2 is fixedly connected with right Ji 5-4.
As can be seen here, the flight attitude simulation frock that the utility model provides has the following advantages:
Can simulated aircraft actual flight state to greatest extent, therefore, after tested air environment being installed to this flight attitude simulation frock, air environment can be made to be in aerial duty, when the air environment of test macro to airborne status is tested, air environment possibility produced problem in practical flight can be found, thus improve test accuracy; Also there is simple, the reliable and stable and state of flight simulates real solidity advantages of higher of structure.
The above is only preferred implementation of the present utility model; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the utility model principle; can also make some improvements and modifications, these improvements and modifications also should look protection domain of the present utility model.
Claims (6)
1. a flight attitude simulation frock, is characterized in that, described flight attitude simulation frock is bilateral symmetry, comprises loading platform (1), support (2), motor (3) and motor-driven mechanism (4);
Wherein, described loading platform (1) comprises and loads mainboard (1-1) and symmetry is fixedly mounted on left plate (1-2) and the right plate (1-3) of described loading mainboard (1-1) left and right sides;
Described support (2) comprises left socle (2-2) and the right support (2-3) that link (2-1) and symmetry are fixedly mounted on described link (2-1) left and right sides;
In addition, described support (2) and described loading platform (1) are arranged up and down in opposite directions, and described left socle (2-2) is rotatably installed to described left plate (1-2); Described right support (2-3) is rotatably installed to described right plate (1-3);
Described motor (3) makes described loading platform (1) rotate relative to described support (2) by described motor-driven mechanism (4).
2. flight attitude simulation frock according to claim 1, it is characterized in that, described left socle (2-2) is rotatably installed to described left plate (1-2) by the 1st ball bearing; Described right support (2-3) is rotatably installed to described right plate (1-3) by the 2nd ball bearing.
3. flight attitude simulation frock according to claim 2, it is characterized in that, described 1st ball bearing and described 2nd ball bearing are low resistance ball bearing.
4. flight attitude simulation frock according to claim 1, is characterized in that, also comprise: antenna (5); Described antenna (5) is fixedly installed to the lower surface of described loading mainboard (1-1); Further, described antenna (5) is electrically connected with the tested air environment being fixedly mounted on described loading mainboard (1-1) upper surface.
5. flight attitude simulation frock according to claim 4, it is characterized in that, described antenna (5) is symmetrical integrally formed structure, comprising: left connecting rod (5-1), right connecting rod (5-2), left Ji (5-3) and right Ji (5-4); Wherein, the left side of described left connecting rod (5-1) is fixedly connected with described left Ji (5-3); The right side of described left connecting rod (5-1) is fixedly connected with the left side of described right connecting rod (5-2); The right side of described right connecting rod (5-2) is fixedly connected with described right Ji (5-4).
6. the flight attitude simulation frock according to any one of claim 1-5, it is characterized in that, described motor-driven mechanism (4) is remote-controlled motor-driven mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520580252.6U CN204988755U (en) | 2015-08-04 | 2015-08-04 | Flight gesture simulation frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520580252.6U CN204988755U (en) | 2015-08-04 | 2015-08-04 | Flight gesture simulation frock |
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| Publication Number | Publication Date |
|---|---|
| CN204988755U true CN204988755U (en) | 2016-01-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520580252.6U Active CN204988755U (en) | 2015-08-04 | 2015-08-04 | Flight gesture simulation frock |
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| CN (1) | CN204988755U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105716819A (en) * | 2016-02-24 | 2016-06-29 | 华南农业大学 | Device and method for medicine chest anti-shock performance test |
-
2015
- 2015-08-04 CN CN201520580252.6U patent/CN204988755U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105716819A (en) * | 2016-02-24 | 2016-06-29 | 华南农业大学 | Device and method for medicine chest anti-shock performance test |
| CN105716819B (en) * | 2016-02-24 | 2017-12-26 | 华南农业大学 | A kind of apparatus and method for medicine-chest anti-oscillating performance test |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Flight gesture simulation frock Effective date of registration: 20170830 Granted publication date: 20160120 Pledgee: Zhongguancun Beijing technology financing Company limited by guarantee Pledgor: Beijing Andawell Aviation Equipment Co., Ltd. Registration number: 2017990000811 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20180309 Granted publication date: 20160120 Pledgee: Zhongguancun Beijing technology financing Company limited by guarantee Pledgor: Beijing Andawell Aviation Equipment Co., Ltd. Registration number: 2017990000811 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |