CN104539376B

CN104539376B - Portable flight parameter system's test equipment

Info

Publication number: CN104539376B
Application number: CN201510001170.6A
Authority: CN
Inventors: 杨卫平
Original assignee: Beijing Jun Mao Guo Xing Technology Co ltd
Current assignee: Beijing Jun Mao Guo Xing Technology Co ltd
Priority date: 2015-01-04
Filing date: 2015-01-04
Publication date: 2023-07-04
Anticipated expiration: 2035-01-04
Also published as: CN104539376A

Abstract

The invention discloses test equipment of a portable flight system, which comprises an equipment body, wherein the equipment body comprises a cover body and a box body, wherein a display screen is arranged on the cover body. The whole flight parameter system (comprising an airborne radio station, a ground base station and a communication server) can be simulated by one device, various flight parameter data can be tested, the testing efficiency is improved, the storage battery is installed, and the outfield test can be conveniently carried out. The equipment is provided with various heat dissipation devices, so that the heat dissipation effect is good and the service life is long.

Description

Portable flight parameter system's test equipment

Technical Field

The invention relates to a test device for testing wireless communication parameters, in particular to a test device for a portable flight parameter system, which can test and maintain a flight data real-time feedback monitoring system under the condition that an external field does not have test conditions.

Background

The active military aircraft is equipped with various airborne equipment for ensuring the safety of the aircraft, improving the flight training level and enhancing the combat readiness. Because of the testing and maintenance of different airborne equipment, a plurality of fixed testing instruments are needed, and professional technicians are needed, the maintenance capability of the army on the aircraft is reduced; the complex test procedure requires a lot of manpower and material resources.

Currently, a large number of equipment and instruments are required to be used for detection in the aspects of testing and maintenance of a flight parameter system. When testing the airborne equipment, the ground receiving equipment, the test computer and various test instruments are required to be carried; similarly, when testing ground equipment, calibration of on-board equipment, test computers, and test instruments is required. The test procedure is very complex, and a great deal of manpower and material resources are required to be consumed. In addition, most of the test instruments need 220V voltage power supply, high requirements are set up for the test environment, particularly, in the field test, the power supply for the test environment is greatly limited, and sometimes, the normal working voltage cannot be provided on site, so that great difficulty is caused to test and maintenance.

Disclosure of Invention

In order to overcome the limitation and complexity of the prior art on the flight parameter test, the invention provides a new portable flight parameter system test device which can test various parameters and communication states of the flight parameter system.

In order to achieve the above purpose, the technical scheme of the invention is as follows: the utility model provides a test equipment of portable flight system, includes the equipment body, the equipment body is including lid and the box of installing the display screen, its characterized in that, the box is provided with the cavity, the cavity layering sets up, and the function board is installed on the upper strata, and the battery is installed to the lower floor, the function board includes mainboard, switch board and constitutes flight system's power amplifier board, baseband board and interface board, baseband board and mainboard connection, the interface board is connected with the switch board, the mainboard is connected with the switch board, the box both sides are provided with the test end interface.

Further, the cavity is provided with two layers.

Further, a first radiating block and a second radiating block are arranged on the side wall of the cavity, and a mounting block is arranged between the first radiating block and the second radiating block.

Further, the first heat dissipation block and the second heat dissipation block are provided with heat dissipation strips.

Further, the switch contains 4 ethernet interfaces.

Further, the laminate is provided with heat dissipation holes.

Furthermore, the equipment body is made of aviation aluminum material.

Further, the corner of equipment body is provided with abrasionproof and decreases angle bar.

The beneficial effects of the invention are as follows: the method is characterized in that open, easy-to-implement and simple-structure hardware is used as a general platform, as many communication functions as possible are realized by upgradeable and replaceable software, the hardware is connected with a software network through an Ethernet port, and finally, the simulation test of various interfaces of a military aircraft on flight parameters and the generation of various interfaces of flight parameters are realized, and various airborne equipment is detected; the whole flight parameter system (comprising an airborne radio station, a ground base station and a communication server) can be simulated by one device, various flight parameter data can be tested, the testing efficiency is improved, the storage battery is installed, and the outfield test can be conveniently carried out. The equipment is provided with various heat dissipation devices and different heat dissipation structures, so that the heat dissipation effect is good and the service life is long.

Low power consumption, high reliability, short development period, strong anti-interference capability of spread spectrum communication, low interception probability and easy networking. The installation and the use of the lithium battery with large volume and high capacity are adopted, and reliable guarantee is provided for the power-off test of the external field.

The portable solar energy collector is small in size and light in weight, and can adapt to severe natural environment conditions by adopting the fully-closed cavity, and is good in flexibility and strong in portability.

Drawings

FIG. 1 is a schematic diagram of the overall structure of a test device of a portable flight system;

FIG. 2 is a schematic structural view of a cavity of a test device of the portable flight parameter system;

FIG. 3 is a schematic view of the upper layer of the cavity of the test equipment of the portable flight system;

fig. 4 is a schematic structural view of a lower layer of a cavity of a test device of the portable flight parameter system.

Wherein: 1. the anti-abrasion LED lamp comprises a cover body, 2, a box body, 3, a cavity, 4, anti-abrasion angle iron, 11, a display screen, 31, a laminate, 32, a first radiating block, 33, a second radiating block, 34, a mounting block, 35, radiating holes, 311, a main board, 312, an interface board, 313 baseband boards, 314, a power amplifier board, 315 and a storage battery.

Detailed Description

The objects, technical solutions and advantages of the present invention will become more apparent by the following detailed description of the present invention with reference to the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.

The main board 311 and the flight parameter system are designed and installed in the cavity 3 in a centralized way, and various test software required by the design and installation is designed and installed on the main board 311, so that the device can simulate the airborne device and the ground device of the flight parameter system and test various flight parameter data by utilizing various software.

1-4, the equipment body comprises a cover body 1 provided with a display screen 11 and a box body 2, wherein a cavity 3 of the box body 2 adopts a double-layer design, and a main board 311, a switchboard board, a power amplification board 314, a baseband board 313 and an interface board 312 which form a flight parameter system are arranged on the upper layer; the storage battery 315 with high energy storage is arranged at the lower layer of the cavity, and can provide working voltage for the receiving channels of the main board 311, the switch board, the baseband board 313, the interface board 312 and the power amplifier board 314 under the condition that power supply is not allowed in the outfield test, so that the equipment can continuously work for more than 5 hours, and the test work can be smoothly carried out.

The device adopts aviation aluminum material and a totally-enclosed cavity 3, and the heat dissipation function mainly depends on the shell of the box body. Meanwhile, in order to further increase the heat dissipation effect, the side wall of the cavity 3 is provided with a first heat dissipation block 32 and a second heat dissipation block 33, a mounting block 34 is arranged between the first heat dissipation block 32 and the second heat dissipation block 33, the first heat dissipation block 32 and the second heat dissipation block 33 are provided with heat dissipation strips, and the laminate 31 is provided with heat dissipation holes 35.

In order to prevent corner wear, wear-resistant angle irons 4 are arranged at the corners.

The power amplifier board, the baseband board and the interface board jointly form the existing flight parameter system, the wiring mode refers to the wiring of the flight parameter system, and the data receiving and transmitting port and the testing port are connected to the reserved position of the case through the cable plug for realizing the testing function of equipment; the Ethernet receiving and transmitting port on the baseband board is connected to the network port of the main board through a network cable, the Ethernet receiving and transmitting port on the interface board is connected to the network port of the switch board through a network cable, and the Ethernet receiving and transmitting port of the main board is connected to the network port of the switch board through a network cable, so that the computer server is connected with the test system, and the combination of the test system and the server is realized.

The method comprises the following steps of designing an idea, a main technology, main characteristics and an equipment body, wherein the idea adopts a network and software radio design scheme, the basic idea is that open, easy-to-implement and simple-structure hardware is used as a general platform, as many communication functions as possible are realized by using upgradeable and replaceable software, the hardware is connected with a software network through an Ethernet port, and finally, various interfaces of a military aircraft are subjected to flight parameter simulation test, various interfaces of the military aircraft are generated, and various airborne equipment is detected; the main technology utilizes the characteristics of low power consumption, high reliability, short development period, strong anti-interference capability of spread spectrum communication, low interception probability, easiness in networking and the like of the FPGA, and the FPGA is used for realizing software wireless test equipment, so that the equipment volume is reduced, and the flexibility and the controllability are higher; the main characteristics are that

Broadband data transmission: the working frequency of 200 MHz-2.4 GHz (the departure can be customized according to the frequency band required by customers), the transmission of flight parameter data can be realized under the environment condition of multiple frequencies, and reliable guarantee is provided for the complex radio environment;

a variety of data interfaces: the system has a plurality of interfaces (other interfaces can be customized) such as RS232, RS422, RS485, 1553B, ethernet, optical ports and 429, and the like, so that the requirements of the plurality of interfaces of different airplanes are met;

powerful cruising ability: the use of the large-volume and high-capacity lithium battery can provide powerful maintenance guarantee for the outfield test;

perfect software support: the software system for testing and maintaining various airborne equipment is developed by adopting the world leading global satellite positioning technology, the data transmission frequency hopping radio communication technology, the GIS geographic information processing technology and the computer network communication and FPGA data processing technology. By utilizing the system, all high-speed moving targets such as aircrafts and the like in the radio communication coverage range can be remotely and wirelessly monitored. And the positioning information acquired by the airborne equipment and the flight parameter information acquired by the flight parameter equipment are transmitted to the comprehensive inspection instrument by utilizing the wireless air relay communication network, and the visual information such as the position, the moving speed, the flight parameter, the simulation cabin and the like of the moving target can be obtained after software interpretation.

The main functions of the device include:

1: SSC-39 station check function (wireless, wired).

2: SSC-51 station check function (wireless, wired).

3: the flight reference RS422 interface is used for outputting an analog digital source.

4: and F, flight parameter NET information source analog output.

5: on-board 1553B source analog output.

6: cooperating with SSC-39 station temporary base station server function.

7: cooperating with SSC-51 station temporary base station server function.

8: the interface self-defines the output function of the output format analog information source.

9: the interface data receives display data functions (special display needs programming).

9: the SSC-39 station set-up function (wireless, wired).

10: the SSC-51 station set-up function (wireless, wired).

11: wireless spectrum scanning function.

12: radio frequency detection function.

The device adopts a network and software radio design scheme, and the basic idea is to use open, easy-to-implement and simple-structure hardware as a general platform, realize as many communication functions as possible by using upgradeable and replaceable software, and connect the hardware with a software network through an Ethernet port. Finally, the simulation test of various interfaces of the military aircraft and the generation of various interface flight parameter sources are realized, and various airborne equipment is detected.

The method can be suitable for testing and simulating the generation of various flight parameters on various types of fighters, such as primary teaching-6, fighter 7, fighter 8, K-8, fighter 9, fighter 10, transportation 8, bombing 6 and the like, strong, bombing, transportation, helicopters, unmanned aerial vehicles and other various types of aircrafts.

It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explanation of the principles of the present invention and are in no way limiting of the invention. Accordingly, any modification, equivalent replacement, improvement, etc. made without departing from the spirit and scope of the present invention should be included in the scope of the present invention. Furthermore, the appended claims are intended to cover all such changes and modifications that fall within the scope and boundary of the appended claims, or equivalents of such scope and boundary.

Claims

1. The utility model provides a test equipment of portable flight system, includes the equipment body, the equipment body is including lid and the box of installing the display screen, its characterized in that, the box is provided with the cavity, the cavity layering sets up, and the upper strata is installed the function board, and the lower floor installs the battery, the function board includes mainboard, switch board and constitutes flight system's power amplifier board, baseband board and interface board, baseband board is connected with the mainboard, the interface board is connected with the switch board, the mainboard is connected with the switch board, the box both sides are provided with the test terminal interface;

the cavity is provided with two layers;

the side wall of the cavity is provided with a first radiating block and a second radiating block, and a mounting block is arranged between the first radiating block and the second radiating block;

the first radiating block and the second radiating block are provided with radiating strips;

the switch comprises 4 Ethernet interfaces;

the laminate is provided with heat dissipation holes;

the equipment body is made of aviation aluminum material;

the corner of equipment body is provided with abrasionproof and decreases angle bar.