CN203365656U

CN203365656U - Control and protection experiment apparatus for airplane power supply system

Info

Publication number: CN203365656U
Application number: CN 201320406549
Authority: CN
Inventors: 程若发; 江晓舟
Original assignee: Nanchang Hangkong University
Current assignee: Nanchang Hangkong University
Priority date: 2013-07-09
Filing date: 2013-07-09
Publication date: 2013-12-25
Anticipated expiration: 2023-07-09

Abstract

Provided is a control and protection experiment apparatus for an airplane power supply system. The apparatus is characterized by comprising a frequency converter, a motor, an AC synchronous generator, a generator control unit, an AC power distribution center, a simulation airplane-use AC load, rectifiers, a DC power distribution center, a simulation airplane DC load, a central controller and the like. By using the apparatus provided by the utility model, the problems of complicated structure, high price, poor safety and the like of a conventional airplane power supply system experiment platform can be solved, the operation performance of the airplane power supply system under different conditions can be simulated, and dada including voltage, current, frequency, power, power factor and the like can be measured. By restoring the different flying states of the airplane power supply system in real flight and the effects exerted on the operation performance of the airplane power supply system by the load change inside a plane, a basis is provided for the research on the optimization and control, protection, and reliability analysis of the airplane power supply system. The investment of the apparatus is about one tenth of the investment in conventional airplane power supply system experiment teaching equipment to the utmost, the operation cost is low, and the safety and reliability are high.

Description

Aircraft power system control and protection experimental provision

Technical field

The utility model relates to a kind of aircraft power supply experimental apparatus for testing.

Background technology

Aircraft electrical power system is comprised of power-supply system and distribution system, its effect is to provide electric energy to all consumers (control system like flying, avionics system, fire control system etc.) on aircraft, with the safe flight that guarantees aircraft with complete transportation and combat duty.Along with large aircraft to many electricity and complete electric direction develop rapidly, the system architecture of present generation aircraft electric system and control also become increasingly complex, various electronic equipments on aircraft are increasing, power consumption constantly increases, the electricity consumption load characteristic is increasingly complex also, except conventional linear load, also have the nonlinear loads such as a large amount of constant power loads and reproducibility load etc., this stability to the power-supply system of conventional airplane, reliability and the quality of power supply propose urgent demand.Till settled the present; China is for the research of at present Based Intelligent Control, protection and the control performance appraisal procedure of the electric system of how electric aircraft and external larger gap in addition, especially for the aircraft electrical power system of current many power technologies, realizes that the research of optimal control, protection and control performance experimental apparatus for testing seldom reports.For stability, reliability and the security that effectively improves modern large aircraft electric system, require the generator voltage pressure regulator that higher static accuracy is not only arranged, also good dynamic perfromance to be arranged, it is controlled parameter and can automatically adapt to the load variations of aircraft electrical power system and change, be that the intelligent adaptive excitation controls to guarantee the aircraft electrical power system power supply quality, researching and developing high performance optimization of excitation control algolithm needs control algolithm performance test means and corresponding hardware experiments device; In the face of colleges and universities also must consider the Personal Safety of student experimenting and the security of equipment as the teaching and scientific research experimental provision.

The utility model content

The purpose of this utility model is to provide a kind of aircraft power system control and protection experimental provision, overcomes at present the high and poor stability of experiment test device complex structure, price for aircraft power system, can't obtain the shortcoming of extensively promoting in the field research scientific research.

A kind of aircraft power system control and protection experimental provision is characterized in that: comprise frequency converter, motor, synchronous alternating-current generator, generator control unit, AC power distributing center, AC load, rectifier, DC power distributing center, simulated aircraft DC load, central controller, oscillograph and electric energy attribute test instrument for simulated aircraft; Described frequency converter and motor are realized frequency control, the actual speed of engine shaft during the different state of flight of simulated aircraft; Described generator and control module thereof are realized the excitation control of aircraft, and can carry out various excitation intelligent control algorithms by the generator control unit provides the checking means; Described AC power distributing center is realized the correct switching of alternator AC1 and alternator AC2 and tri-redundancy AC power of inverter AC3, normal to guarantee two voltages on ac bus; Described DC power distributing center is realized the handoff-security of a plurality of redundant powers such as two rectification DC power supply DC1, DC2 and standby battery; Described alternating current-direct current load simulation aircraft actual bringing onto load situation under various states, the collecting devices such as the voltage of various character, electric current, frequency directly interconnect with central controller; Oscillograph, electric energy attribute test instrument are used for analysis and the research of electric current, voltage and the quality of power supply.

A kind of aircraft power system control and protection experimental provision, it is characterized in that: two synchronous alternating-current generators are realized generating by two Frequency Converter Control respective electrical motivations respectively, the 200V sent, the three-phase alternating current of 400Hz is delivered to AC power distributing center (ACPC), again electric energy safe distributed to two ac bus ACBUS1 and ACBUS2, aircraft obtains electric power with the analog AC load by two ac bus, two rectifiers convert alternating current respectively to direct current supply analog DC load use for aircraft of 28V again, the direct supply DC1 that storage batteries D C3 exports as two rectifiers simultaneously and DC2's is standby, standby power supply by inverter output AC electricity AC3 as two alternator power supply AC1 and AC2.

A kind of aircraft power system control and protection experimental provision; it is characterized in that: frequency converter obtains the speed governing of controlling electric energy motor frequency change from electrical network; the actual speed of simulated aircraft engine shaft when different mission phases; frequency converter timing scope 0-15000rpm wherein; synchronous alternating-current generator generating under the excitation of its control module is controlled, can realize various excitation intelligent control algorithm checkings by generator control unit GCU.

The utility model has solved the difficult problems such as conventional airplane power-supply system experiment porch complex structure, expensive, poor stability, but the runnability of simulated aircraft power-supply system under different condition, but the data such as measuring voltage, electric current, frequency, power, power factor.Change and impact that its runnability is produced by reduction aircraft power system different flight state and machine internal burden in practical flight, thereby provide foundation for aircraft power system optimal control, protection and Reliability Analysis Research.Adopt investment of the present utility model mostly to be 1/10th left and right that conventional airplane power-supply system experimental teaching equipment drops into most, operating cost is low and safe and reliable.By simulate the aeromotor device by inverter control motor, reduced equipment, whole test unit structure is relatively simple, easy to operate, has reduced cost of investment and experimental cost; Adopt two low-voltage alternating-current synchronous generators and control module thereof to form aircraft power supply master Blast Furnace Top Gas Recovery Turbine Unit (TRT), very easily realize that generator intelligence excitation control algolithm realizes and checking, has also improved the security of student and scientific research personnel's test; Adopt AC power distributing center and DC power distributing center to realize aircraft power system failure reconfiguration algorithm and electric network protection Algorithm Analysis research and checking in laboratory.

The accompanying drawing explanation

Fig. 1 is the structural representation of the utility model experimental provision;

Fig. 2 is that the AC power distributing center of the utility model experimental provision is controlled schematic diagram;

Fig. 3 is that the DC power distributing center of the utility model experimental provision is controlled schematic diagram.

Embodiment

Now the invention will be further described in conjunction with the accompanying drawings and embodiments:

As shown in the figure: a kind of aircraft power system control and protection experimental provision is characterized in that: comprise frequency converter, motor, synchronous alternating-current generator, generator control unit, AC power distributing center, AC load, rectifier, DC power distributing center, DC load, central controller, oscillograph and electric energy attribute test instrument for simulated aircraft for simulated aircraft, synchronous alternating-current generator is realized generating by inverter control motor, the 200V sent, the three-phase alternating current of 400Hz is delivered to AC power distributing center (ACPC), again electric energy safe distributed to two ac bus ACBUS1 and ACBUS2, aircraft obtains electric power with analog AC by two ac bus, two rectifiers convert alternating current respectively to the direct current supply aircraft analog DC load use of 28V again, the direct supply DC1 that storage batteries D C3 exports as two rectifiers simultaneously and DC2's is standby, standby battery by inverter output AC electricity AC3 also as the standby power supply of two alternator power supply AC1 and AC2.In experimental provision, frequency converter obtains the speed governing of controlling electric energy motor frequency change from electrical network, the actual speed of simulated aircraft engine shaft when different mission phases, frequency converter timing scope 0-15000rpm wherein, during the utility model experimental provision aircraft generator normal power generation, the speed setting of generator is at 9000-15000rpm.Direct motor drive synchronous alternating-current generator operation in experimental provision is sent stable frequency-changing AC electricity under the excitation of generator control unit is controlled, and various advanced persons' intelligent excitation control algolithm can be studied and verify by generator control unit GCU.

The AC power control center of experimental provision realizes the correct switching of alternator AC1 and alternator AC2 and tri-redundancy AC power of inverter AC3.When two generator AC1 and AC2 are normal, their respectively do for oneself ACBUS1 and ACBUS2 power supply, now inverter is idle; During a still fault in AC1 and AC2, so normal that generator is given ACBUS1 and ACBUS2 power supply simultaneously; When AC1 and AC2 simultaneous faults, inverter startup is simultaneously to two ac bus power supplies.By central controller, power control center is controlled and can be realized aircraft power supply fault network restructing algorithm experimental study.

The DC power control center of experimental provision completes the correct switching of rectifier DC1 and rectifier DC2 and tri-redundancy direct supplys of standby battery DC3.When two rectifier DC1 and rectifier DC2 are normal, their respectively do for oneself DCBUS1 and DCBUS2 power supply, now accumulator is in charged state; During a still fault in DC1 and DC2, so normal that rectifier is given DCBUS1 and DCBUS2 power supply simultaneously; When DC1 and DC2 simultaneous faults, standby battery is simultaneously DC bus powered to two.By simulating the failure condition of different direct supplys, realized the correct switching of aircraft DC power supply by central controller, and then realize aircraft DC electric power network failure reconfiguration proof of algorithm and assessment.

Experimental provision is analyzed and is studied the quality of power supply of aircraft power system by oscillograph and electric energy attribute test data that instrument obtains; Experimental provision analyzes by regulating simulated aircraft the impact in the different loads situation, aircraft electrical network actual motion brought by the size of alternating current-direct current load, thereby protect proof of algorithm for the optimal control of aircraft power system, provide foundation; Experimental provision is realized collection, processing, warning, storage, inquiry and the demonstration to system data by central controller, and realizes optimal control and protection to working state of system.

Above content is in conjunction with concrete preferred implementation further detailed description of the utility model, can not assert that concrete enforcement of the present utility model is confined to these explanations.For the utility model person of an ordinary skill in the technical field; make without departing from the concept of the premise utility some alternative or obvious modification that are equal to; and performance or purposes identical, should be considered as belonging to the definite protection domain of claims that the utility model is submitted to.For the utility model, so long as the rail clip of design in pull bar block simultaneously the flange of rail and the web of the rail with guarantee Rail apart from and prevent the steel rail web deformation failure all within the utility model scope of patent protection.

Claims

1. an aircraft power system control and protection experimental provision, is characterized in that: comprise frequency converter, motor, synchronous alternating-current generator, the generator control unit, the AC power distributing center, the simulated aircraft AC load, rectifier, the DC power distributing center, the simulated aircraft DC load, central controller, oscillograph and electric energy attribute test instrument, two synchronous alternating-current generators are realized generating, the 200V sent by two Frequency Converter Control respective electrical motivations respectively, the three-phase alternating current of 400Hz is delivered to AC power distributing center (ACPC), again electric energy safe distributed to two ac bus ACBUS1 and ACBUS2, aircraft obtains electric power with the analog AC load by two ac bus, two rectifiers convert alternating current respectively to direct current supply analog DC load use for aircraft of 28V again, the direct supply DC1 that storage batteries D C3 exports as two rectifiers simultaneously and DC2's is standby, the standby power supply by inverter output AC electricity AC3 as two alternator power supply AC1 and AC2.

2. aircraft power system control and protection experimental provision according to claim 1; it is characterized in that: frequency converter obtains the speed governing of controlling electric energy motor frequency change from electrical network; the actual speed of simulated aircraft engine shaft when different mission phases; frequency converter timing scope 0-15000rpm wherein; synchronous alternating-current generator generating under the excitation of its control module is controlled, can realize various excitation intelligent control algorithm checkings by generator control unit GCU.