CN202372206U - Airspeed pressure altitude checking device for unmanned aerial vehicle - Google Patents
Airspeed pressure altitude checking device for unmanned aerial vehicle Download PDFInfo
- Publication number
- CN202372206U CN202372206U CN2011205281215U CN201120528121U CN202372206U CN 202372206 U CN202372206 U CN 202372206U CN 2011205281215 U CN2011205281215 U CN 2011205281215U CN 201120528121 U CN201120528121 U CN 201120528121U CN 202372206 U CN202372206 U CN 202372206U
- Authority
- CN
- China
- Prior art keywords
- pressure
- airspeed
- altimeter
- air speed
- aerial vehicle
- 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
Images
Landscapes
- Measuring Fluid Pressure (AREA)
Abstract
The utility model discloses an airspeed pressure altitude checking device for an unmanned aerial vehicle. A pressure source is connected with an airspeed pressure altimeter and an onboard air data unit. The output ends of the airspeed pressure altimeter and the onboard air data unit are connected with the input end of a comparison link which is connected with a display mechanism. An excitation signal is directly transmitted into the airspeed pressure altimeter by the pressure source, and is compared with data from an onboard air data unit of a tested object, a result is output to the display mechanism, and a tester judges the operating state of the tested object. The data acquisition and processing links of a sensor, a data acquisition mechanism, a microprocessor and the like are eliminated, and the excitation signal transmitted by the pressure source is directly transmitted to the airspeed pressure altimeter through a pressure pipeline, so that the device is simple and compact; in addition, an intermediate link for signal transmission is eliminated, so that measurement reliability is improved; and the problems about special interfaces of the device are solved, the universality of the device is improved, and cost is also lowered.
Description
Technical field
The utility model relates to detection technique, specifically, relates to a kind of device that is used for the verification of middle-size and small-size unmanned plane air speed barometer altitude.
Background technology
Mostly the air speed barometer altitude ground calibration equipment of present middle-size and small-size unmanned plane is the ground special inspecting equipment; As shown in Figure 1; Its cardinal principle is to provide pumping signal by pressure source 1; After sensor 2 conversion, send microprocessor 4 to after gathering through data acquisition mechanism 3 and handle, last with come to compare 5 the result outputed to indication mechanism 6 to the data of airborne atmosphere data machine 7.
This kind calibration equipment requires to be furnished with sensor device, data collector and micro processor, apparatus etc., the equipment relative complex, and bulky not portable, cost is higher; And test interface is single, and versatility is low.
Summary of the invention
The purpose of the utility model provides a kind of easy calibration equipment, makes to have reduced the intermediate link that signal transmits simultaneously by equipment concision and compact more, has improved measuring reliability; Reduce links such as microprocessor, improved measuring reliability.
For realizing above-mentioned purpose; The utility model is taked following technical scheme; A kind of unmanned plane air speed barometer altitude calibration equipment is characterized in that, pressure source connects air speed pressure altimeter and airborne atmosphere data machine; The output terminal of air speed pressure altimeter and airborne atmosphere data machine is connected with the input end of comparison link, and the comparison link is connected with indication mechanism.
The principle of work of the utility model is; Provide pumping signal by pressure source; Directly get into the air speed pressure altimeter, compare with the data from the airborne atmosphere data machine of checked object the result is outputed to indication mechanism, testing crew is judged the duty of checked object thus.
The beneficial effect of the utility model is:
A) data acquisition, the processing procedure link of aspects such as sensor, data acquisition mechanism, microprocessor have been reduced; Pressure source is provided pumping signal directly conduct to the air speed pressure altimeter through pressure piping; Make equipment concision and compact more; Reduce the intermediate link of signal transmission simultaneously, improved measuring reliability.
B) reduced link such as microprocessor,, reduced the special purpose interface problem that this kind equipment exists, increased the versatility of equipment so no longer use digital communication interface.
C) middle-size and small-size unmanned plane all compares sensitivity to expense usually, and this utility model has reduced expense budget under the prerequisite that has satisfied test request, satisfies requirement cheaply.
Description of drawings
Fig. 1 is existing calibration equipment principle schematic.
Fig. 2 is the calibration equipment principle schematic of the utility model.
Embodiment
Below in conjunction with accompanying drawing and embodiment to the utility model with further specifying; Referring to Fig. 2; A kind of unmanned plane air speed barometer altitude calibration equipment is characterized in that, pressure source 1 connects air speed pressure altimeter 8 and airborne atmosphere data machine 7; The output terminal of air speed pressure altimeter 8 and airborne atmosphere data machine 7 is connected with the input end of comparison link 5, and comparison link 5 is connected with indication mechanism 6.
Embodiment:Providing pumping signal by pressure source 1 (being generally vacuum air pump) is force value; This pressure generally is divided into malleation and negative pressure; Get into air speed pressure altimeter 8 respectively through pressure piping malleation and negative pressure, this table can directly resolve air speed and barometer altitude into correspondence with force value.Another branch of while pressure piping conducts to the airborne atmosphere data machine 7 of checked object and obtains the air speed barometer altitude value output of checked object; Compare 5 through the data that obtain with air speed pressure altimeter 8 result outputed to indication mechanism 6, testing crew can be judged the duty of the airborne atmosphere data machine 7 of checked object through difference between the two.
In actual the use, air speed and barometer altitude are separated verification:
A) air speed verification
The static port of pitot and the static port of airspeed indicator directly communicate with atmosphere; Start force (forcing) pump; Then the force value that receives of pitot ram compression mouthfeel can change; The air speed value that on airspeed indicator, can show a correspondence, the checked object atmosphere data chance pressure of experiencing pitot converts the air speed value into and shows aboard or on the airplane synthetic tester simultaneously.But the reading with airspeed indicator in the calibration equipment is the then duty of verification atmosphere data machine of benchmark.
B) barometer altitude verification
The pitot aperture of pitot directly communicates with atmosphere; Start drawdown pump; Then the force value experienced of pitot static port can change; The barometer altitude value that on pressure altimeter, can show a correspondence, the checked object atmosphere data chance pressure of experiencing pitot converts the barometer altitude value into and shows aboard or on the airplane synthetic tester simultaneously.But the reading with pressure altimeter in the calibration equipment is the then duty of verification atmosphere data machine of benchmark.
Claims (1)
1. unmanned plane air speed barometer altitude calibration equipment; It is characterized in that; Pressure source (1) connects air speed pressure altimeter (8) and airborne atmosphere data machine (7); The output terminal of air speed pressure altimeter (8) and airborne atmosphere data machine (7) is connected with the input end of comparison link (5), and comparison link (5) is connected with indication mechanism (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205281215U CN202372206U (en) | 2011-12-16 | 2011-12-16 | Airspeed pressure altitude checking device for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205281215U CN202372206U (en) | 2011-12-16 | 2011-12-16 | Airspeed pressure altitude checking device for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202372206U true CN202372206U (en) | 2012-08-08 |
Family
ID=46595903
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205281215U Expired - Fee Related CN202372206U (en) | 2011-12-16 | 2011-12-16 | Airspeed pressure altitude checking device for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202372206U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105501464A (en) * | 2015-12-16 | 2016-04-20 | 成都赫尔墨斯科技有限公司 | Method for testing performance of aviation airborne radio communication and navigation system during test flight |
| CN107438751A (en) * | 2016-09-27 | 2017-12-05 | 深圳市大疆创新科技有限公司 | For detecting the method, apparatus and unmanned plane of flying height |
| CN107883980A (en) * | 2017-10-27 | 2018-04-06 | 北京机电工程研究所 | Pressure altimeter base level dynamic testing method |
-
2011
- 2011-12-16 CN CN2011205281215U patent/CN202372206U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105501464A (en) * | 2015-12-16 | 2016-04-20 | 成都赫尔墨斯科技有限公司 | Method for testing performance of aviation airborne radio communication and navigation system during test flight |
| CN105501464B (en) * | 2015-12-16 | 2018-03-06 | 成都赫尔墨斯科技股份有限公司 | The radio communication of flight test airborne and the method for navigation system performance |
| CN107438751A (en) * | 2016-09-27 | 2017-12-05 | 深圳市大疆创新科技有限公司 | For detecting the method, apparatus and unmanned plane of flying height |
| CN107883980A (en) * | 2017-10-27 | 2018-04-06 | 北京机电工程研究所 | Pressure altimeter base level dynamic testing method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2516570A1 (en) | Gas monitoring system and sidestream gas measurement system adapted to communicate with a mainstream gas measurement system | |
| CN202372206U (en) | Airspeed pressure altitude checking device for unmanned aerial vehicle | |
| ES2847283T3 (en) | Pitot-static air data test system with pilot and copilot verification | |
| CN110873604A (en) | Transformer noise vibration on-line monitoring system | |
| CN104359689B (en) | EMUs braking performance test method and test device | |
| CN103207089B (en) | A kind of vehicle test information comprehensive acquisition system | |
| CN110926685A (en) | Overload protection device of micro-differential pressure sensor and micro-differential pressure detection system | |
| CN206930413U (en) | A kind of valves leakage acoustic detector | |
| CN102103016A (en) | SF6 gas density relay calibrator | |
| KR101084527B1 (en) | Flying data storage apparatus for aerial vehicle | |
| CN105004463A (en) | Piston type propeller engine thrust measuring method and piston type propeller engine thrust measuring device | |
| CN107044870A (en) | A kind of multi-parameter portable warehousing and transportation facilities detector | |
| CN102455238A (en) | Online calibration method of indicator diagram test equipment and connection structure thereof | |
| CN104833464A (en) | Multifunctional airtight detector and detection method thereof | |
| CN110926527A (en) | General sensor test equipment | |
| CN203745139U (en) | Rapid online testing device for pressure/differential pressure transmitter | |
| CN102564791A (en) | Pressure regulating property testing system of gas pressure regulator | |
| CN102331530A (en) | Signal testing method | |
| CN114878270A (en) | Oxygen concentration measuring device and measuring method | |
| CN211262470U (en) | Transformer noise vibration on-line monitoring system | |
| CN204964098U (en) | Backpressure formula pressure sensor | |
| KR102627338B1 (en) | Inspection device of flight instruments for pitot and static system | |
| CN204279972U (en) | A kind of aviator's life support anti-lotus subsystem testing fixture | |
| CN207557754U (en) | A kind of detection device of electronic type vacuum pressure controller | |
| CN202599571U (en) | Bayonet-type polished-rod sensor |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120808 Termination date: 20191216 |