CN105043759B - A kind of unmanned plane launcher detection method and device - Google Patents
A kind of unmanned plane launcher detection method and device Download PDFInfo
- Publication number
- CN105043759B CN105043759B CN201510352830.5A CN201510352830A CN105043759B CN 105043759 B CN105043759 B CN 105043759B CN 201510352830 A CN201510352830 A CN 201510352830A CN 105043759 B CN105043759 B CN 105043759B
- Authority
- CN
- China
- Prior art keywords
- launcher
- unmanned plane
- detection
- aerial vehicle
- ejection
- 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 invention discloses a kind of unmanned plane launcher detection method and device, whether the three-dimensional Euler attitude angle that the detectable launcher of the present invention is installed meets launch angle requirement for the static launcher for judging to install；The ejection force size of launching cradle, speed, the acceleration change of ejection travel, obtainable initial velocity, acceleration at the end of ejection, for judging launcher dynamic property are also can detect that by analog transmissions；Can whether abnormal according to the status data real-time judgment launcher of detection, if being alarmed in the presence of abnormal by abnormal indicating module, the status data detected can be sent to host computer by wireless communication module, and be shown in host computer, and data can also be stored in memory and analyzed for later data.The characteristics of present invention has cheap, easy to carry, can detect before unmanned aerial vehicle ejecting each time, can carry out the detection of static, dynamic multiple parameters, and dynamic detection process is consistent with unmanned aerial vehicle ejecting take-off process, and the validity of detection is strong.
Description
Technical field
The invention belongs to mechanical detection field, more particularly to a kind of unmanned plane launcher detection method and device.
Background technology
Taking off for fixed-wing unmanned plane need to reach certain initial velocity, and then provide lift by air force, and allow solid
Determine wing unmanned plane and reach certain initial velocity, a kind of method is to allow aircraft sliding run on the runway of ground to accelerate, and another is to pass through
Launcher ejection obtains enough initial velocity.
But launcher before catapult-assisted take-off with the presence or absence of failure or launcher lay whether level, the elastic force that provides whether
Touch the mark, whether track is smooth etc. needs specific detection means detection, to find potential faults that launcher is present, it is ensured that
Unmanned plane safe take-off.
Article《Ivory tower guide precision detection method based on laser tracker》In propose one kind and use laser
The method that tracker detects launcher track precision.This method is on the basis of the measuring principle of analysis laser tracker, using sharp
Optical tracker system realizes the detection to ivory tower guide rail, gives detailed detecting step, finally measures uncertainty
Evaluation, demonstrate the validity and feasibility of this method.In above-mentioned document, realized based on laser tracker to Vertical Launch
Frame guide precision is detected that the precision of detection is high, but the laser tracker that this method is used is expensive, is suitable for transmitting
Product quality before frame dispatches from the factory is detected, is not suitable for the detection each time before transmitting.In actual unmanned plane application, unmanned plane hair
Frame is penetrated after multiple carrying, use, the performance of launcher may change, and the method for document one is not suitable for this detection.
In addition, document one is only single detection trajectory accuracy, it is impossible to detect the other specification of launcher.
Patent (CN201220346709) discloses a kind of digital device for measuring force of rocket bomb transmitting frame releasing force, and it is by sending out
Penetrate frame, imitating shell, digital force-measuring instrument, pull bar, the even composition such as section, loading frame, nut, screw rod, rocking handle, blocking wedge living.Lay
Imitating shell on launcher is set by live shell, and motor powered of the releasing force loading in loading frame is carried out, and field condition is such as
Unregulated power, can manually be carried out with rocking handle, and releasing force is, by the support A on imitating shell, constantly to increase to the blocking wedge on launcher
Plus thrust, until unblock, the size of releasing force is shown by digital force-measuring instrument, it has the functions such as holding and peak holding, can be with calculating
Machine is connected, and carries out data processing and result printing, and it detects that performance is stable, and detection efficiency is high.But the content of its detection is only
Releasing force.
The content of the invention
To solve the above problems, the invention provides a kind of unmanned plane launcher detection method and device.The price of the present invention
It is cheap, easy to carry, it can be detected before unmanned aerial vehicle ejecting each time, the detection of static, dynamic multiple parameters, dynamic can be carried out
Detection process is consistent with unmanned aerial vehicle ejecting take-off process, and the validity of detection is strong.
To reach above-mentioned technique effect, the technical scheme is that：
A kind of unmanned plane launcher detection method, comprises the following steps：
Step one) Static Detection unmanned plane launcher：Place after unmanned aerial vehicle ejecting frame, detection means is arranged on nobody
On machine launcher, position, height and the orientation information of unmanned aerial vehicle ejecting frame are detected, if attitude angle data is abnormal, passes through alarm
Indicator provides prompting, terminates process；Unmanned aerial vehicle ejecting frame is readjusted, is detected again, until attitude angle data is normal；
Step 2) dynamic detection unmanned plane launcher：Ejection imitating shell is installed on unmanned plane launcher, unmanned plane is detected
The height above sea level of launcher position；Acceleration, angular speed and the three axle magnetic force of imitating shell, are then calculated during detection ejection
The Eulerian angles of launcher installation and then the flip angle for detecting launcher, detect the speed of ejection process；If data exception,
Prompting is provided by warning indicator, terminates process；Then unmanned aerial vehicle ejecting frame is readjusted, is detected again, until data are just
Often；
Step 3) formal ejection：According to step 2) the middle data transmitting unmanned plane set, then terminates test.
It is further to improve, position, height and the orientation information of unmanned aerial vehicle ejecting frame, unmanned plane launcher position
Height above sea level, the acceleration of imitating shell, angular speed, the data message of three axle magnetic force and speed are adopted in real time by central processing unit
Collect and calculate.
It is further to improve, position, height and the orientation information of unmanned aerial vehicle ejecting frame, unmanned plane launcher position
Height above sea level, the acceleration of imitating shell, angular speed, the data message of three axle magnetic force and speed are recorded in real time on memory or logical
Cross wireless communication system and be sent to host computer.
Advantages of the present invention：
1st, detection means price is low, easy to carry, can be detected before unmanned aerial vehicle ejecting each time.
2nd, the parameter of detection is more, the three-dimensional Eulerian angles containing launching cradle, ejection force, ejection acceleration, speed, slide rail flatness
Etc. multiple indexs.
3rd, detection means contains Static Detection and dynamic detection, and dynamic detection process is consistent with unmanned aerial vehicle ejecting take-off process,
The validity of detection is strong.
Brief description of the drawings
Fig. 1 is the structural representation of the detection means of embodiment 2；
Fig. 2 is the detecting step schematic diagram of embodiment 1；
Fig. 3 is that unmanned plane launcher puts schematic diagram；
Fig. 4 is the schematic diagram that unmanned plane launcher is fixed after unmanned plane.
Embodiment
Embodiment 1
A kind of unmanned plane launcher detection method as in Figure 2-4, comprises the following steps：
Step one) Static Detection unmanned plane launcher：Place after unmanned aerial vehicle ejecting frame, detection means is arranged on nobody
On machine launcher, position, height and the orientation information of unmanned aerial vehicle ejecting frame are detected, if attitude angle data is abnormal, passes through alarm
Indicator provides prompting, terminates process；Unmanned aerial vehicle ejecting frame is readjusted, is detected again, until attitude angle data is normal；
Step 2) dynamic detection unmanned plane launcher：Ejection imitating shell is installed on unmanned plane launcher, unmanned plane is detected
The height above sea level of launcher position；Acceleration, angular speed and the three axle magnetic force of imitating shell, are then calculated during detection ejection
The Eulerian angles of launcher installation and then the flip angle for detecting launcher, detect the speed of ejection process；If data exception,
Prompting is provided by warning indicator, terminates process；Then unmanned aerial vehicle ejecting frame is readjusted, is detected again, until data are just
Often；
Step 3) formal ejection：According to step 2) the middle data transmitting unmanned plane set, then terminates test.
The position of unmanned aerial vehicle ejecting frame, height and orientation information in embodiment 1, the height above sea level of unmanned plane launcher position
Highly, the data message of the acceleration of imitating shell, angular speed, three axle magnetic force and speed is gathered simultaneously in real time by central processing unit
Calculate..
The position of unmanned aerial vehicle ejecting frame, height and orientation information in embodiment 1, the height above sea level of unmanned plane launcher position
Highly, the data message of the acceleration of imitating shell, angular speed, three axle magnetic force and speed is recorded in real time on memory or by nothing
Line communication system is sent to host computer.
Embodiment 2
A kind of unmanned plane launcher detection means as shown in Figure 1, including central processing unit 1,1 point of the central processing unit
Be not connected with measurement height above sea level pneumatics sensor 2, obtain air speed data airspeed sensor 3, obtain launcher position,
The GPS 4 of height, the accelerometer 5 of measurement ejection brief acceleration, the turn meter 6 of angular speed, measurement during measurement ejection
The magnetometer 7 of launcher direction, records the memory 8 of gathered data and the warning indicator 9 of prompting abnormal information.The center
Processor 1 is connected with the data radio station 11 that measurement data is delivered to host computer 10 by RTTY.
The present apparatus can detect a variety of abnormalities of launcher, including the three-dimensional Euler attitude angle that launcher is installed, and be used for
Static state judges whether the launcher installed meets launch angle requirement；The ejection force of launching cradle is also can detect that by analog transmissions
Size, speed, the acceleration change of ejection travel, obtainable initial velocity, acceleration at the end of ejection, for judging launcher
Dynamic property.
Whether the present apparatus can abnormal according to the status data real-time judgment launcher of detection, if existing abnormal by referring to extremely
Show that module is alarmed.
The status data of detection can be shown in host computer in real time by data radio station, data can also be stored in into memory
For later data analysis.
The present apparatus can be used for unmanned aerial vehicle ejecting take off before detection each time, detection content includes the three dimensions of launcher
Flip angle, launch whole process track flatness, launch whole process speed, acceleration value.Detection content
It is various, easy to use.
The description of the above examples is only intended to facilitate the understand of the core idea of the present invention；Simultaneously for the general of this area
Technical staff, according to the thought of the present invention, will change in specific embodiments and applications, in summary,
This specification content should not be construed as limiting the invention.
Claims (3)
1. a kind of unmanned plane launcher detection method, it is characterised in that comprise the following steps：
Step one) Static Detection unmanned plane launcher：Place after unmanned aerial vehicle ejecting frame, detection means is sent out installed in unmanned plane
Penetrate on frame, detect position, height and the orientation information of unmanned aerial vehicle ejecting frame, if attitude angle data is abnormal, pass through police instruction
Device provides prompting, terminates process；Unmanned aerial vehicle ejecting frame is readjusted, is detected again, until attitude angle data is normal；
Step 2) dynamic detection unmanned plane launcher：Ejection imitating shell, detection unmanned plane transmitting are installed on unmanned plane launcher
The height above sea level of frame position；Acceleration, angular speed and the three axle magnetic force of imitating shell, then calculate transmitting during detection ejection
The Eulerian angles of frame installation and then the flip angle for detecting launcher, detect the speed of ejection process；If data exception, pass through
Warning indicator provides prompting, terminates process；Then unmanned aerial vehicle ejecting frame is readjusted, is detected again, until data are normal；
Step 3) formal ejection：According to step 2) the middle data transmitting unmanned plane set, then terminates test.
2. unmanned plane launcher detection method as claimed in claim 1, it is characterised in that the position of unmanned aerial vehicle ejecting frame, height
Degree and orientation information, the height above sea level of unmanned plane launcher position, the acceleration of imitating shell, angular speed, three axle magnetic force and
The data message of speed is gathered and calculated in real time by central processing unit.
3. unmanned plane launcher detection method as claimed in claim 1, it is characterised in that the position of unmanned aerial vehicle ejecting frame, height
Degree and orientation information, the height above sea level of unmanned plane launcher position, the acceleration of imitating shell, angular speed, three axle magnetic force and
The data message of speed is recorded in real time on memory or is sent to host computer by wireless communication system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510352830.5A CN105043759B (en) | 2015-06-24 | 2015-06-24 | A kind of unmanned plane launcher detection method and device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510352830.5A CN105043759B (en) | 2015-06-24 | 2015-06-24 | A kind of unmanned plane launcher detection method and device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105043759A CN105043759A (en) | 2015-11-11 |
| CN105043759B true CN105043759B (en) | 2017-09-29 |
Family
ID=54450477
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510352830.5A Expired - Fee Related CN105043759B (en) | 2015-06-24 | 2015-06-24 | A kind of unmanned plane launcher detection method and device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105043759B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005466B (en) * | 2016-07-12 | 2018-03-30 | 福建工程学院 | A kind of reassembling type SUAV launching cradle |
| CN106885916A (en) * | 2017-03-08 | 2017-06-23 | 西北工业大学 | SUAV launching cradle speed measuring device |
| CN107643105B (en) * | 2017-10-30 | 2024-04-02 | 程鹏 | Weather modification rocket launcher detector |
| CN111776247A (en) * | 2020-06-04 | 2020-10-16 | 核工业北京地质研究院 | System and method for measuring thrust of launching system of gliding unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202693178U (en) * | 2012-07-13 | 2013-01-23 | 吉林市江机民科实业有限公司 | Releasing force digital detecting device for rocket projectile launching rack |
| CN203630152U (en) * | 2013-12-20 | 2014-06-04 | 海鹰航空通用装备有限责任公司 | Launching cradle speed measuring device of unmanned aerial vehicle |
| CN204197307U (en) * | 2014-10-16 | 2015-03-11 | 天津米岚泽科技发展有限公司 | A kind of novel unmanned aerial vehicle ejecting frame |
| CN104477400A (en) * | 2014-11-28 | 2015-04-01 | 四川航空工业川西机器有限责任公司 | Unmanned aerial vehicle hydraulic catapult launching system |
| CN104590577A (en) * | 2014-12-25 | 2015-05-06 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle launch booster mounting base adjusting and installing platform and usage method thereof |
| CN204758292U (en) * | 2015-06-24 | 2015-11-11 | 福建工程学院 | Unmanned aerial vehicle launcher detection device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20120115464A (en) * | 2011-04-10 | 2012-10-18 | 박재형 | Suav(small unmanned aerial vehicle) launcher using hand motion recognizing controller |
-
2015
- 2015-06-24 CN CN201510352830.5A patent/CN105043759B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202693178U (en) * | 2012-07-13 | 2013-01-23 | 吉林市江机民科实业有限公司 | Releasing force digital detecting device for rocket projectile launching rack |
| CN203630152U (en) * | 2013-12-20 | 2014-06-04 | 海鹰航空通用装备有限责任公司 | Launching cradle speed measuring device of unmanned aerial vehicle |
| CN204197307U (en) * | 2014-10-16 | 2015-03-11 | 天津米岚泽科技发展有限公司 | A kind of novel unmanned aerial vehicle ejecting frame |
| CN104477400A (en) * | 2014-11-28 | 2015-04-01 | 四川航空工业川西机器有限责任公司 | Unmanned aerial vehicle hydraulic catapult launching system |
| CN104590577A (en) * | 2014-12-25 | 2015-05-06 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle launch booster mounting base adjusting and installing platform and usage method thereof |
| CN204758292U (en) * | 2015-06-24 | 2015-11-11 | 福建工程学院 | Unmanned aerial vehicle launcher detection device |
Non-Patent Citations (1)
| Title |
|---|
| 弹射式导弹发射时载机动力学响应研究;杜泉峰 等;《飞行力学》;20100430;第28卷(第2期);51-54 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105043759A (en) | 2015-11-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102419381B (en) | For the airspeed sensing system of aircraft | |
| CN105043759B (en) | A kind of unmanned plane launcher detection method and device | |
| CN103257348B (en) | Measurement system of relative altitude and relative attitude of air vehicle and measurement method thereof | |
| US8774989B1 (en) | Aircraft energy state display | |
| CN102680201B (en) | Buffeting wind tunnel testing method based on video measurement | |
| US20110257818A1 (en) | Dynamically Monitoring Airborne Turbulence | |
| CN108132134A (en) | Aerodynamic derivative discrimination method and system based on wind tunnel free flight test | |
| CN103282798B (en) | Gasoloid detects | |
| US11840349B2 (en) | Aerial vehicle powering off method and device, and aerial vehicle | |
| CN105807779A (en) | Flight control system and method for unmanned aerial vehicle | |
| CN207067409U (en) | A kind of unmanned plane remains searching device | |
| FR2883983B1 (en) | METHOD AND DEVICE FOR MEASURING AIR TURBULENCE IN THE ENVIRONMENT OF AN AIRCRAFT | |
| CN105807087A (en) | Method and device for determining the wind speed to be taken into account in order to optimize the takeoff weight of an aircraft | |
| CN204758292U (en) | Unmanned aerial vehicle launcher detection device | |
| CN205469873U (en) | A device for testing small -size unmanned vehicles take -off speed | |
| RU155825U1 (en) | ON-BOARD SYSTEM FOR MEASURING THE PARAMETERS OF THE WIND SPEED VECTOR AT THE PARKING, STARTING AND TAKEOFF AND LANDING MODES | |
| CN203630152U (en) | Launching cradle speed measuring device of unmanned aerial vehicle | |
| CN102853961A (en) | Airplane external aerostatic pressure measuring device adopting trailing cone as carrier | |
| CN204642165U (en) | Miniature self-service mechanomotive force size digital test compound table | |
| CN206557611U (en) | Unmanned plane | |
| CN203981407U (en) | The portable brake performance tester of embedded electronic gyroscope | |
| CN102541065A (en) | High-accuracy low-height control method and system for aircraft | |
| RU2587389C1 (en) | Onboard system of measuring parameters of wind velocity vector at station, takeoff and landing helicopter | |
| CN108490218A (en) | Anemoclinograph field calibration system and method based on unmanned air vehicle technique | |
| CN111222082B (en) | Method for identifying position and speed of ascending airflow suitable for unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| 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: 20170929 Termination date: 20200624 |