CN203551961U

CN203551961U - Avionics hardware-in-the-loop simulation system for unmanned plane

Info

Publication number: CN203551961U
Application number: CN201320591302.1U
Authority: CN
Inventors: 钱毅; 王勇; 胡雄文; 左明; 陈贤相; 赵小川; 徐英新; 刘莹; 周宏志; 张敏; 刘珊; 査长流; 赵欣欣; 崔倩楠; 李陈; 刘新广; 瞿蓉; 施建昌; 田铮; 张月
Original assignee: China North Computer Application Technology Research Institute
Current assignee: China North Computer Application Technology Research Institute
Priority date: 2013-09-24
Filing date: 2013-09-24
Publication date: 2014-04-16
Anticipated expiration: 2023-09-24

Abstract

The utility model discloses an avionics hardware-in-the-loop simulation system for an unmanned plane. The simulation environmental system comprises a flight simulation module, a three-dimensional visual scene module, an interface module and a simulation console. A flight control system comprises a flight control module and a ground control station in communication connection with the simulation console. The control command input port and the flight control state information output port of the flight control module are respectively connected with the control command output port and the flight control state information input port of the ground control station. One branch of the steering engine control signal output port of the flight control module is connected with the signal receiver of the steering engine of an unmanned helicopter, and the other branch of the steering engine control signal output port of the flight control module is connected with the controlled quantity input port of the flight simulation module through the interface module. One branch of the unmanned helicopter state output port of the flight simulation module is connected with the unmanned helicopter state input port of the flight control module through the interface module, and the other branch of the unmanned helicopter state output port of the flight simulation module is connected with the display data input port of the three-dimensional visual scene module. According to the technical scheme of the utility model, due to the adoption of the system, the development efficiency of the flight control system is effectively improved, and the development cost of the flight control system is lowered.

Description

A kind of unmanned plane avionics semi-matter simulating system

Technical field

The utility model relates to a kind of unmanned plane avionics semi-matter simulating system.

Background technology

In the development process of unmanned plane, taking a flight test is a very crucial and high risk link, and is subject to the restriction of place, operator, weather etc., is difficult to carry out at any time.On stream; conventionally use mathematical modeling or System Discrimination to obtain the mathematical model of unmanned plane; but mathematical modeling difficulty is high; and be difficult to the precision that reaches higher; although System Discrimination can access more accurate model; but dependence is very high to taking a flight test, need a large amount of flight tests and the difficulty of taking a flight test high.For some, be for example that multiple no-manned plane is coordinated the research topic of controlling in addition, experimentation cost meeting is very high, is difficult to carry out test of many times, or cannot tests.

Utility model content

The purpose of this utility model is to solve above technical matters, and a kind of unmanned plane avionics semi-matter simulating system that flight control system is carried out to the emulation of hardware in loop is provided, for the test of the flight control system of depopulated helicopter provides a kind of hardware architecture.

The technical solution adopted in the utility model is: a kind of unmanned plane avionics semi-matter simulating system, comprise simulated environment system, flight control system and depopulated helicopter, described simulated environment system comprises flight simulation module, three-dimensional vision module, interface module and simulation console, described flight control system comprises flight control module and ground control station, the steering order input port of described flight control module and the corresponding connection of the steering order output port of ground control station, the corresponding connection of flight state of a control input information port of the flight state of a control information output mouth of described flight control module and ground control station, steering wheel control signal output port one branch road of described flight control module is connected with the signal receiver of the steering wheel of depopulated helicopter, the CAN bus of another branch road by interface module turns serial communication path and is connected with the controlled quentity controlled variable input port of flight simulation module, the serial ports of depopulated helicopter State-output port one branch road of described flight simulation module by interface module turns CAN bus communication path and is connected with the depopulated helicopter state input port of flight control module, and another branch road is connected with the demonstration data-in port of three-dimensional vision module, described simulation console is connected with ground control station wireless telecommunications.

The beneficial effects of the utility model are: unmanned plane avionics semi-matter simulating system of the present utility model can be developed control algolithm, the check flight control hardware of flight control system and carry out system integration and test in simulated environment, it can effectively improve the development efficiency of flight control system, reduces cost of development.

Accompanying drawing explanation

Fig. 1 is according to the frame principle figure of unmanned plane avionics semi-matter simulating system described in the utility model.

Embodiment

As shown in Figure 1, unmanned plane avionics semi-matter simulating system of the present utility model comprises simulated environment system 2, flight control system 3 and depopulated helicopter 1, this simulated environment system 2 comprises for moving the flight simulation module 21 of Flight Control Algorithm, existing three-dimensional vision module 24, interface module 22 and simulation console 23, flight control system 3 comprises flight control module 31 and ground control station 32, the flight steering order input port of control module 3 and the corresponding connection of the steering order output port of ground control station 32, the flight flight state of a control information output mouth of control module 31 and the corresponding connection of flight state of a control input information port of ground control station 32, steering wheel control signal output port one branch road of flight control module 31 is connected with the signal receiver of the steering wheel of depopulated helicopter, the CAN bus of another branch road by interface module 22 turns serial communication path and is connected with the controlled quentity controlled variable input port of flight simulation module 21, the serial ports of depopulated helicopter State-output port one branch road of flight simulation module 21 by interface module 22 turns CAN bus communication path and is connected with the depopulated helicopter state input port of flight control module 31, another branch road is connected with the demonstration data-in port of three-dimensional vision module 24, to show in real time flight attitude by three-dimensional vision module 24, the three-dimensional image information such as flight track, above simulation console 23 is connected with ground control station 32 wireless telecommunications, with by the simulation console situation such as control station 32 Remote create helicopter faults, weather environment variation earthward artificially.Above flight simulation module 21 is after receiving the flight control module 31 steering wheel control signal of sending through steering wheel control signal output port by interface module 22, according to default Flight Control Algorithm, calculate the current flight status parameter of depopulated helicopter and (comprise attitude, speed, angular velocity, highly, longitude and latitude and rotating speed etc.), and this flight status parameter is sent to flight control module and three-dimensional vision module via interface module, and flight control module 31 receives above flight status parameter and from the steering order of ground control station 32, by navigate calculation and control rule of existing algorithm, resolve, and then calculate the signal receiver that steering wheel control signal sends to the steering wheel of flight simulation module 21 and depopulated helicopter 1.

The foregoing is only preferably embodiment of the utility model, be not used for limiting practical range of the present utility model, the equivalence of in every case doing in protection domain of the present utility model changes and modifies, and all should think and fall in protection domain of the present utility model.

Claims

1. a unmanned plane avionics semi-matter simulating system, it is characterized in that: comprise simulated environment system, flight control system and depopulated helicopter, described simulated environment system comprises flight simulation module, three-dimensional vision module, interface module and simulation console, described flight control system comprises flight control module and ground control station, the steering order input port of described flight control module and the corresponding connection of the steering order output port of ground control station, the corresponding connection of flight state of a control input information port of the flight state of a control information output mouth of described flight control module and ground control station, steering wheel control signal output port one branch road of described flight control module is connected with the signal receiver of the steering wheel of depopulated helicopter, the CAN bus of another branch road by interface module turns serial communication path and is connected with the controlled quentity controlled variable input port of flight simulation module, the serial ports of depopulated helicopter State-output port one branch road of described flight simulation module by interface module turns CAN bus communication path and is connected with the depopulated helicopter state input port of flight control module, and another branch road is connected with the demonstration data-in port of three-dimensional vision module, described simulation console is connected with ground control station wireless telecommunications.