CN220251367U - Underwater high-speed separation attitude test system for aircraft - Google Patents
Underwater high-speed separation attitude test system for aircraft Download PDFInfo
- Publication number
- CN220251367U CN220251367U CN202321847331.XU CN202321847331U CN220251367U CN 220251367 U CN220251367 U CN 220251367U CN 202321847331 U CN202321847331 U CN 202321847331U CN 220251367 U CN220251367 U CN 220251367U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- underwater
- separation
- test system
- attitude
- 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.)
- Active
Links
- 238000000926 separation method Methods 0.000 title claims abstract description 59
- 238000012360 testing method Methods 0.000 title claims abstract description 52
- 238000005259 measurement Methods 0.000 claims abstract description 13
- 230000003287 optical effect Effects 0.000 claims abstract description 12
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052744 lithium Inorganic materials 0.000 claims abstract description 5
- 238000012800 visualization Methods 0.000 abstract description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 10
- 238000013461 design Methods 0.000 description 5
- 238000001612 separation test Methods 0.000 description 5
- 238000004364 calculation method Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000011084 recovery Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013500 data storage Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/30—Assessment of water resources
Landscapes
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The utility model discloses an underwater high-speed separation attitude testing system of an aircraft, which comprises the aircraft and an external separation load, wherein the aircraft and the external separation load comprise an underwater attitude tester, a depth sensor, a fluorescent assembly, a battery pack and a connector assembly, the aircraft further comprises an optical assembly, and the optical assembly comprises a high-definition wide-angle camera and an illuminating lamp. The underwater attitude tester comprises a control module, an inertial measurement unit, a memory, an interface module and a shell. The fluorescent component adopts a low-power LED light-emitting device. The battery pack employs a reusable lithium battery pack. The inertial measurement unit adopts a high-precision MEMS inertial measurement component. The interface module comprises an RS422 interface and an RS232 interface. The problem that an existing separation posture testing system cannot realize underwater separation posture data testing and does not have underwater visualization capability is solved.
Description
Technical Field
The utility model relates to the technical field of underwater separation attitude test of aircrafts, in particular to an underwater high-speed separation attitude test system of an aircrafts.
Background
In recent years, the development of underwater vehicles (such as UUV, AUV, manned underwater vehicles and the like) in China is increased year by year, the functions of the underwater vehicles are more and more complex, and the vehicles carry a large amount of separable or detachable task loads. When the vehicle separates the task load or releases the small-sized vehicle or the vehicle itself separates and throws away the negative mass part, the stability, reliability and rapidity of separation have great influence on the product performance, and meanwhile, the separation matrix (the vehicle platform) and the separation body (the separated parts such as the load) are required to be ensured not to collide, so that how to accurately and rapidly test the motion gesture of each separation body of the vehicle is significant to the research of the separation technology of the vehicle. However, because the difficulty of the underwater test is high, the test means are few, the data which can be collected are limited, and particularly, the test cost is high in the offshore or lake test, the current system for the separation test is relatively few, the system mainly focuses on the ground or air separation test, the system for the underwater separation test is less, and the visualization of the underwater separation test is relatively lack. For underwater separation or underwater launching of an aircraft, how to reliably and stably test and record separation tracks, attitude information of a motion process after separation and the like has great significance for the research and design of separation technology of the aircraft. The existing separation attitude test system has the following defects:
1. the system is mainly used for ground static separation test or air separation dynamic test, and lacks an underwater separation attitude data acquisition system of the aircraft.
2. The underwater high-speed dynamic attitude test is relatively insufficient.
3. The data storage capacity is limited.
4. The test system is not highly versatile.
5. And does not have underwater visualization capability.
Disclosure of Invention
The utility model aims to provide an underwater high-speed separation attitude testing system for an aircraft, which aims to solve the problem that the existing separation attitude testing system cannot realize underwater separation attitude data testing and does not have underwater visualization capability.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides an aircraft high-speed separation gesture test system under water, includes aircraft and outer load that leaves, aircraft and outer load that leaves all include under water gesture tester, depth sensor, fluorescence subassembly, group battery and connector assembly, still include optical component in the aircraft.
The depth sensor mainly comprises a water pressure sensor, a data interface and the like, is responsible for measuring underwater depth information of each separated body of the aircraft, acquires the water pressure information in real time, obtains a water depth position through calculation, and adopts a high-precision water pressure sensor.
The fluorescent assembly mainly comprises the led lamp strip and the mounting part, can continuously flash and emit light for a long time, is convenient for recovery personnel and salvagers to find an aircraft or separate load positions in time when the recovery personnel and the salvagers sink unexpectedly, and adopts the low-power-consumption led light-emitting device.
The battery pack is composed of a lithium battery, a cable assembly, an output interface and the like, is responsible for providing various stable electric energy for the test system, is provided with an internal and external electric switching interface, is plug and play, is convenient to debug and flexible to use electricity, and adopts the lithium battery pack capable of being reused.
The optical assembly consists of a high-definition wide-angle camera, an illuminating lamp, a cable and the like, can record underwater separation image information of the aircraft, and can intuitively give underwater separation conditions by adopting the high-definition wide-angle camera. The high-definition wide-angle camera adopts a low-cost high-definition camera with mature technology, acquires the information of the aircraft and the separated load image in real time and sends the information to the underwater attitude tester for storage, and the illuminating lamp provides a light source for the underwater camera, so that the definition and the distance of the underwater acquired video image are improved.
The connector assembly can be reliably connected with the inside and the outside, realizes stable data transmission and collection, has the capability of charging a lithium battery, is connected with the separating body through the falling connector with fixed length, can test the instantaneous separation speed when the separating body is broken, and has the capability of preventing water with large water depth at an external interface.
The underwater attitude tester mainly comprises a control module, an Inertial Measurement Unit (IMU), a memory, an interface module, a shell and the like, wherein in the separation process of the aircraft, the angular velocity and the linear acceleration of the separation body are measured in real time, and information such as the velocity, the position, the heading, the attitude and the like of the separation body is provided through calculation.
The control module is a comprehensive control management and calculation processing component of the test system and mainly comprises a processor chip, a control circuit component, a peripheral component and the like, and is used for completing the control of various data acquisition, calculation, storage, reading and the like;
the memory mainly comprises a memory chip, a memory module circuit assembly, a data interface and the like, adopts a high-capacity high-speed memory, and can record, store and read various collected signal data;
the interface module mainly comprises a plug, a socket, a cable and the like, adopts interfaces such as a main stream RS422, an RS232 and the like, can realize reliable connection and insertion with the inside and the outside, and realizes stable data transmission and acquisition;
the shell adopts a high-strength aluminum alloy material and a sealing buffer structure design, so that strength protection, waterproof protection and the like are provided for the underwater separation posture testing system.
The inertial measurement unit adopts a high-precision MEMS inertial measurement component.
Compared with the prior art, the utility model has the beneficial effects that:
the underwater high-speed separation attitude test system of the aircraft has the capability of dynamically testing the underwater separation body, can solve the problem of attitude measurement of the underwater separation body of the aircraft, and provides test data for separation stability and reliability design. The sensor has the capability of testing the underwater high-speed separation posture by adopting a wide-range high-precision high-response sensor. The high-definition wide-angle camera is adopted, the optical image and the video screen acquisition capability are provided, and the underwater dynamic separation process is recorded in a multi-dimensional manner. And by adopting a modularized design, each acquisition module can be optimally combined, installed and used.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present utility model;
FIG. 2 is a schematic view of the structure of the underwater attitude tester of the present utility model.
Reference numerals: 1. an underwater attitude tester; 10. an interface module; 11. a housing; 12. high definition wide angle camera; 13. a lighting lamp; 2. a depth sensor; 3. a fluorescent assembly; 4. a battery pack; 5. an optical component; 6. a connector assembly; 7. a control module; 8. an inertial measurement unit; 9. a memory.
Detailed Description
The utility model is further described in connection with the following detailed description, in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the utility model easy to understand.
In the description of the present utility model, it should be noted that, directions or positions indicated by terms such as "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end", etc., are based on directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the apparatus or elements to be referred to must have a specific direction, be configured and operated in the specific direction, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present utility model, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "provided," "connected," and the like are to be construed broadly, and may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
As shown in fig. 1, the utility model relates to an underwater high-speed separation attitude test system of an aircraft, which comprises a main test piece underwater attitude tester 1 adopting a high-precision measuring element, a depth sensor 2 for acquiring water pressure information in real time with high precision, a fluorescent component 3 for flashing and lighting for a long time, a battery pack 4 with multi-channel power supply, an optical component 5 adopting a high-definition wide-angle camera 12, a connector component 6 for realizing stable data transmission and preventing large water depth leakage, and the like.
As shown in fig. 2, the underwater posture tester 1 of the core posture testing component comprises a control module 7 adopting a high-performance processor, an inertial measurement unit 8 adopting a high-precision sensitive element, a memory 9 adopting a high-capacity high-speed flash memory chip, an interface module 10 adopting a rich data interface, a shell 11 adopting a high-strength aluminum alloy and the like, wherein the interface module 10 comprises an RS422 interface and an RS232 interface.
When in assembly, the control module 7, the inertial measurement unit 8 and the memory 9 are firstly installed and fixed together, and after the internal and external circuit connection is carried out through the interface module 10, the control module is fixed into the shell 11, and the underwater attitude tester 1 is formed by coating waterproof glue and other sealing. One set of test components, i.e. the underwater pose tester 1, the depth sensor 2, the fluorescent assembly 3, the battery pack 4, the optical assembly 5, the plug-in assembly 6, etc., is adapted to be mounted on the aircraft, and the other set of test components, i.e. the underwater pose tester 1, the depth sensor 2, the fluorescent assembly 3, the battery pack 4, the plug-in assembly 6, etc., is adapted to be mounted on a separate load. After the test system is properly assembled, the circuit is detected and the aircraft is assembled, so that the test system can be used for executing test tasks. The "fitting" refers to the adaptive design of the test aircraft and the separation load structure thereof according to the specific structure and the requirements of the aircraft and the separation load thereof, and is convenient for the test system to be installed on the aircraft and the separation load.
The test working process of the utility model is as follows: when the aircraft fitted with the test system carries out a separation load test, the test system receives a command signal, the battery pack 4 supplies power, each sensor starts working and feeds back state information to the aircraft control system, after the aircraft receives 'normal state' information, a task load separation command is given, task loads are separated, the underwater attitude tester 1, the depth sensor 2 and the optical component 5 respectively acquire information such as separation attitude, depth, separation optical image and the like in real time, and the acquired information is stored and calculated by the underwater attitude tester 1. After the aircraft is separated from the separation load by a certain distance, the falling connector for connecting the aircraft and the separation load is separated under the action of the breaking force, and then the instantaneous separation speed is calculated. After the separation task is completed, the recovery system recovers the aircraft and the separation load, and the fluorescent assembly 3 starts to flash and emit light, so that recovery personnel can conveniently position and recover for salvage. After the test system is recovered, the test data is read through the plug-in component interface 6, and the separation motion attitude information, the images thereof and other information are obtained, so that test data support is provided for the research of the underwater separation technology of the aircraft.
The foregoing is merely exemplary embodiments of the present utility model, and specific structures and features that are well known in the art are not described in detail herein. It will be evident to those skilled in the art that the utility model is not limited to the details of the foregoing illustrative embodiments, and that the present utility model may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the utility model being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (6)
1. An underwater high-speed separation attitude test system of an aircraft is characterized in that: including the aircraft with outer load that leaves, the aircraft with outer load that leaves all includes underwater attitude tester (1), depth sensor (2), fluorescence subassembly (3), group battery (4) and connector assembly (6), still include optical subassembly (5) in the aircraft, optical subassembly (5) include high definition wide angle camera (12), light (13).
2. The vehicle underwater high-speed separation attitude test system of claim 1, wherein: the underwater attitude tester (1) comprises a control module (7), an inertial measurement unit (8), a memory (9), an interface module (10) and a shell (11).
3. The vehicle underwater high-speed separation attitude test system of claim 1, wherein: the fluorescent component (3) adopts a low-power LED light-emitting device.
4. The underwater high-speed separation attitude test system for an aircraft of claim 2, wherein: the battery pack (4) is a reusable lithium battery pack.
5. The underwater high-speed separation attitude test system for an aircraft of claim 2, wherein: the inertial measurement unit (8) adopts a high-precision MEMS inertial measurement component.
6. The underwater high-speed separation attitude test system for an aircraft of claim 2, wherein: the interface module (10) comprises an RS422 interface and an RS232 interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321847331.XU CN220251367U (en) | 2023-07-14 | 2023-07-14 | Underwater high-speed separation attitude test system for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321847331.XU CN220251367U (en) | 2023-07-14 | 2023-07-14 | Underwater high-speed separation attitude test system for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220251367U true CN220251367U (en) | 2023-12-26 |
Family
ID=89270974
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321847331.XU Active CN220251367U (en) | 2023-07-14 | 2023-07-14 | Underwater high-speed separation attitude test system for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220251367U (en) |
-
2023
- 2023-07-14 CN CN202321847331.XU patent/CN220251367U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201555036U (en) | Digital camera flashlight | |
| CN104539905A (en) | Visible light accurate detection system for electric unmanned helicopter | |
| CN220251367U (en) | Underwater high-speed separation attitude test system for aircraft | |
| CN113184148A (en) | Light operation modularization of snake eel shape is from independently fortune dimension robot under water | |
| CN201202976Y (en) | Underground pipeline rapid picture recording detection device | |
| CN116973148A (en) | System and method for testing underwater high-speed separation attitude of aircraft | |
| CN204291244U (en) | Electric power depopulated helicopter visible ray accurate detection system | |
| CN207623749U (en) | A kind of inside transformer detection robot control system | |
| CN206147296U (en) | Embedded MCU data acquisition module | |
| CN205718958U (en) | Camera inertia measurement monitor in high precision | |
| CN210235283U (en) | Marine communication positioning navigation gripper device | |
| CN208075873U (en) | A kind of vehicle attitude and environmental monitor | |
| CN217384268U (en) | Aircraft attitude measuring device based on inertia measuring unit | |
| CN205724666U (en) | Power circuit polling system | |
| CN102915577A (en) | Portable inspection unit | |
| CN202904686U (en) | Portable polling equipment | |
| CN215043757U (en) | Airtight space inspection unmanned aerial vehicle | |
| CN108769341A (en) | A kind of communication equipment and communication system | |
| CN109443313A (en) | A kind of portable inclination measuring device | |
| CN214057847U (en) | Surface of water environmental monitoring unmanned aerial vehicle that cruises | |
| CN114397007A (en) | Underwater multi-channel distortion-free data acquisition and storage system under high sampling rate | |
| CN114745486A (en) | Visual reading device of electrified equipment with adjustable front and back positions | |
| CN202406211U (en) | GPS route recorder | |
| CN113433963A (en) | Unmanned aerial vehicle multi-platform system and method for magnetic suspension track inspection | |
| CN201434911Y (en) | Living life detector used for aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |