RU2263044C1 - Aircraft with general-purpose equipment control system - Google Patents

Abstract

FIELD: aeronautical engineering; control of training and practicing flights.

SUBSTANCE: proposed aircraft has fuselage, wing, tail unit, landing gear, engines of main power plant and air intakes with passages bounded by wing. Door turnably secured on wing is flush with upper surface. Auxiliary power plant is arranged in tail fuselage across longitudinal axis. Provision is made control system of general-purpose aircraft equipment. Two automatic control loops are provided in main and reserve conversion and calculation units which are connected to actuators through monitoring and control unit. Manual control loop is provided with control panels, enunciator panel and central signal light. Control system is engageable via multiplex channel with onboard digital computer, electronic control systems of port and starboard engines, recording and monitoring system, guidance and landing equipment and complex control system. Performed by code communication lines is tie-in with fuel control and monitoring system, voice message equipment, complex electron display system and auxiliary power plant. Provision is made for control of general-purposed aircraft equipment both in automatic and manual modes.

EFFECT: enhanced mobility of aircraft.

2 cl, 1 dwg

Description

The invention relates to aircraft and is intended for use in the implementation of control of training aircraft.

A well-known training aircraft having a fuselage, wing air intakes bounded by a wing, landing gear, a power plant with engines, horizontal and vertical tail, as well as a set of on-board equipment (RU 2144885 C1, B 64 C 3/14, 01/27/2000).

A disadvantage of the known aircraft is determined by unsatisfactory flight performance due to the lack of structural elements for effective control.

Closest to the proposed one is a multi-purpose aircraft containing a fuselage with a cockpit in the bow, wing air intakes bounded by a wing, landing gear, a main power plant with two turbojet engines located in the middle of the fuselage, horizontal and single-keel vertical plumage, an auxiliary power plant that provides launch engines of the main power plant, power supply of airborne equipment on the ground and in flight, compressed air supply to the aircraft systems in the rear part of the fuselage, the bow of which is made with a removable nose compartment and pivoting flaps fixed to the corresponding parts of the wing, made with the possibility of overlapping the axial inlets of the corresponding air intakes and the corresponding additional inlets in the wing, as well as a complex of on-board equipment (RU 2210522 C1, B 64 From 1/36, 08/20/2003).

However, the specified aircraft does not provide comprehensive control of all-aircraft equipment in all possible modes.

The objective of the invention is the creation of an aircraft with increased mobility and the ability to control general aircraft equipment (CCA) in both automatic and manual mode. The technical result is to increase the efficiency of flights.

The problem is solved in that the aircraft containing the fuselage, wing, empennage, landing gear, the engines of the main power plant, air intakes with channels bounded by the wing, on which the sash is fixed with the possibility of rotation and flush with the upper surface of the wing, the auxiliary power unit, located in the rear of the fuselage across its longitudinal axis, additionally contains an OSO control system, which has two automatic control loops, structurally designed in the main and backup th conversion and calculation units connected to executive devices via a control and monitoring unit, as well as a manual control circuit with control panels, light-signal boards and a central light-signal light, and is connected via a multiplex channel to a complex of on-board digital computers, an electronic left-hand engine control system, an electronic control system of the right engine, registration and control system, guidance and landing equipment, an integrated control system, and whether by code communications - with a fuel management and control system, voice communications equipment, an integrated electronic display system and an auxiliary power unit.

Partial essential features of the invention contribute to the solution of the problem, according to which the controlled CCA includes an air conditioning system, an integrated control system, an inter-cabin light alarm system, an inter-aircraft intercom, a pneumatic hydraulic system, a wheel braking system, a fire protection system, a windshield heating system, an emergency equipment complex leaving, the power plant launch, control and monitoring system, life support system, power supply system a fuel control and monitoring system, a fuel meter system, an auxiliary power unit start-up and control system, an oxygen system, a chassis control system, a radio altimeter, a radio compass, a lamp lock alarm system, an external lighting equipment system, a fuel system, a lamp visor air protection system, a system centralized oil refueling, guidance and landing equipment, range finder, air intake flap control system, avionics complex system equipment, auxiliary power unit.

The drawing shows a structural diagram of a control system for general aircraft equipment (SU CCA).

The following are indicated on the diagram: control panel (NP OCO) 1, light-emitting diode panel with button-lamps type PKN (TS PKN) 2, central light-signal light (ЦСО) 3, multiplex information exchange channel (MKIO) 4, conversion and calculation unit (BPV) 5, control and monitoring unit (BUK) 6, the system of general aircraft equipment 7, the air conditioning system (SCR) 8, the integrated control system (KSU) 9, the in-car alarm system 10, the inter-aircraft intercom (MSPU) 11, the pneumohydrosystem 12, the braking system wheels (STK) 13, si fire protection system (SPZ) 14, windshield heating system (SOLS) 15, emergency exit system (KSAP) 16, power plant start-up, control and monitoring system (SZUK SU) 17, life support system (SZO) 18, power supply system ( SES) 19, fuel management and control system (SUIT) 20, fuel consumption meter (STR) 21, auxiliary power unit start and control system (AFU) 22, oxygen system (KS) 23, chassis control system (SS) 24, radio altimeter 25 , radio compass (ARC) 26, alarm system locks lantern (CVD F) 27, the system of external lighting equipment (ESPO) 28, the fuel system (TS) 29, the control system of the air intake flaps (SVZS) 30, the centralized oil filling system (SPM) 31, the guidance and landing equipment 32, the range finder 33, the control system of the air intake flaps 34, systems of the complex of avionic electronic equipment (avionics) 35, auxiliary power unit (AFU) 36, BTsVM 37.

SU OCO, as already mentioned, has two automatic control loops, structurally designed into the main and backup conversion and computation units 5, connected to executive devices through the control and control unit 6, as well as a manual control loop with control panels 1, light-signal boards 2 and the central light signal 3 and is interfaced via multiplex channel 4 with a complex of on-board digital computers 37, an electronic control system of the left engine, an electronic control system of the right th engine, registration and control systems, guidance and landing equipment 32, an integrated controller 9, and on code communication links system (CLS) - a fuel control and monitoring system 20, voice message equipment, a complex electron display system and auxiliary power unit 36.

SU OSO is designed to perform the tasks:

monitoring systems of the object and issuing information to prepare the display of their status;

issuing alarm messages about the status of systems and their modes of operation;

control of the CCA 7 and its actuators in manual and automatic modes;

collection, transformation and transportation to consumers of information about the parameters of the object and the state of its systems.

SU CCA provides the following functions:

reception of analog and discrete information from interfaced systems of an object;

receiving information on code lines from the conjugated systems of the facility with parameters that meet the requirements of GOST 18977-79 and RTM 1495-75 with amendment 2;

reception of information transmitted through the MKIO 4 information exchange channel (primary and backup) from interfaced systems of an object with parameters meeting the requirements of GOST 26765. 52-87;

logical processing of received information;

formation and issuance of signaling information on the light-signal boards TS 2, the central light-signal light ЦСО 3 and the light-signal fields of button-lamps for emergency information;

formation and issuance of signaling information to the light-signal fields of button lamps, warning and notification information (continuous burning) by the following systems: power unit (SU), auxiliary power unit VSU 36, and KSAP 16 emergency exit system;

Disabling CCO 3;

separate brightness control of ЦСО 3, ТС 2 and signal fields of button-lamps in the first and second cabins are separate;

centralized performance monitoring of the central heating station 3, vehicle 2 and signal fields of button lamps in the first and second cabins are separate;

formation and issuance to the interfaced systems, with their ground monitoring, of serviceability request signals initiating their launch into the advanced monitoring mode;

management of CCA and their actuators in manual and automatic modes;

flight control of the technical condition of general aircraft OSO systems and avionics 35;

organization of ground control of systems and equipment during maintenance and preparation for flight;

reception of the results of control of interfaced systems in the form of discrete signals and their transportation to the BCVM 37 via the MKIO 4 information exchange channel (primary and backup) with parameters meeting the requirements of GOST 26765. 52-87;

collecting, converting and transporting information on the object’s parameters and the state of its systems through the information and communication channel MKIO 4 (primary and backup) to the BCMC 37 with parameters meeting the requirements of GOST 26765. 52-87;

formation and issuance of voice message codes for voice messages on the code line with parameters that meet the requirements of GOST 18977-79 and RTM 1495-75 with amendment 2;

formation and delivery of information to the registration and control system about object failures and operation modes (objective control system) via the MKIO 4 information exchange channel (primary and backup) with parameters meeting the requirements of GOST 26765. 52-87;

management of the operating modes of the registration and control system (objective control system) through the MKIO 4 information exchange channel (primary and backup) with parameters that meet the requirements of GOST 26765. 52-87.

The system provides the following functions on the CCA 7 control channels:

formation and issuance of control signals in CCA 7;

ensuring the issuance of control signals from control panels 1;

maintaining the state (configuration) of the control system, actuators during power outages of one of the sides;

termination of the launch procedures or their return to their original state and the issuance of information to the pilot.

The system provides the execution of CCA 7 control functions in the CCA manual control mode and in the CCA automatic control mode (if this is provided for by the controls and elements of each system separately).

The system in automatic mode ensures the execution of the sequence of inclusion (start) of individual devices (elements) of the object systems.

The system enters the manual control mode of the CCA system for which the manual controls "MANUAL / AUT" are provided, which are located on one of the control panels of the CCO 1 CCA in the first or second cabins.

In the process of information interaction, the system provides reception of one-time teams of three types from the interfaced equipment:

a) type I:

the presence of a signal is a DC voltage with a nominal value of + 27 V, with the quality of electricity according to GOST 19705-89, with Appendix 5 for normal, abnormal and emergency operation of the power supply system;

no signal - a short to the housing (input voltage no more than 3 V) or open circuit (leakage current no more than 0.1 mA);

b) type II:

the presence of a signal - short circuit to the housing (input voltage no more than 3 V); no signal - open circuit (leakage current not more than 0.2 mA);

c) Type III only for the SUIT 20 system:

the presence of a signal - a logical unit - voltage (3.7 ± 1.3) V;

no signal - logical zero - voltage (from 0 to 0.44) V.

The system provides reception and digitalization of up to 50 analog signals from interfaced systems of CCA sensors.

The system provides reception and processing of information transmitted from interfaced systems via code lines of communication, with parameters that meet the requirements of GOST 18977-79 and RTM 1495-75 with amendment 2, information transfer rate of 50 kbit / s + 1%.

The system provides reception and processing of information from interfaced equipment via the ICIE information exchange channel (primary and backup) in accordance with the requirements of GOST 26765. 52-87.

During the logical processing of signals in the advanced control mode, the OSO-130 control system carries out self-control of its units and sends the control results through the MKIO 4 channel to the BTsVM 37 and the registration and control system (objective control system).

In the monitoring mode of CCA 7 and avionics BREO 35, the control system of the CCA, using the "request" commands, initiates the launch of the built-in self-monitoring of systems and complexes of the avionics 35, receives information about the results of the monitoring and transmits it to the digital computer.

The system provides the issuance of 4 values of current parameters, event codes and codes of failed systems blocks identified at all stages of the facility operation to the registration and control system (objective control system) through the ICIE information exchange channel.

The system provides two-channel (two-block) information processing.

With the logical formation of the displayed information, the system provides the formation and delivery to the light-signal boards 2 and display devices of emergency, warning and notification information in the form of one-time commands about the operating modes of the object, including:

light-signaling board with a button (TSC);

on a board light-signaling TS 2;

on the light signal fields of button lamps (type PKN).

The number of brightness control circuits TSK, TS 2 and PKN - two.

The system ensures the issuance of a “health request” signal to each of the interconnected systems of the object. Signal Parameters:

the presence of a signal - voltage from 16.5 to 33 V (load current - not more than 40 mA);

no signal - open circuit (leakage current not more than 0.2 mA).

The system provides the issuance of signals in the ARC on the code line.

The system provides the issuance of 80 control commands (KU) with voltage from 16.5 to 33 V, with a load current from 0.1 to 3.5 A coming to actuators, starters and commutations.

The system provides the issuance of ten one-time commands to the SUIT 20 fuel management and control system in the form of:

the presence of a signal - a logical unit - voltage (3.7 ± 1.3) V;

lack of signal - logical zero - voltage (0 to 0.44) V.

Each channel of the system provides the issuance of information on five lines of the CLS in accordance with the requirements of GOST 18977-81 and RTM 1495-75 rev. 2. Information transfer rate of 50 kBit / s ± 1%.

In case of logical information exchange in accordance with MKIO 4, the system exchanges data via the multiplexed information transmission line (MLPI) in accordance with the requirements of GOST 26765. 52-87 and the communication protocols of the CCS OS with the BCVM 37 complex and with the associated equipment.

Each channel of the system provides work on MKIO 4 with the main and backup communication lines.

The system provides work in the following formats:

“Controller - terminal device”;

"Terminal device - controller";

"Terminal device - terminal device."

The system in case of a failure of the BCVM 37 provides operation according to MKIO 4 as a controller, and in case of failure of the MKIO 4, the control system of the OSO is connected to the multifunctional color indicator MFTS and remote control radial links.

The power supply of the system is carried out from the power supply system SES 19, consisting of two secondary channels (boards) of direct current with a nominal voltage of 27 V.

The quality of electricity complies with GOST 19705-89 for systems with rectifier devices.

In both sides (channels) of the direct current in the parking lot when starting the APU 36, a simultaneous voltage drop is possible (Clause 2.2. 11. GOST 19705-89).

Transformation and calculation units 5 are connected to two channels of SES 19 and operate normally with power quality parameters for one channel for normal and emergency modes (in steady and transient modes), while the second power channel can be powered with electricity with quality parameters for abnormal mode.

With a simultaneous interruption in the power supply or a simultaneous voltage drop in accordance with clause 2.2. 11. GOST 19705-89 through two channels in the parking system does not fail and does not give false signals and commands (except for their removal), when restoring the quality of electricity in at least one power supply channel of SES 19 to a normal or emergency value of the parameters, the system should work fully recover without crew intervention (automatically) in no more than 1 s.

Claims (2)

1. Aircraft containing the fuselage, wing, empennage, landing gear, the engines of the main power plant, air intakes with channels bounded by the wing, on which the sash is fixed with the possibility of rotation and flush with the upper surface of the wing, the auxiliary power plant located across the rear of the fuselage its longitudinal axis, characterized in that it further comprises a control system for general aircraft equipment, which has two automatic control loops, structurally designed in the main the explicit and backup conversion and computation units connected to the executive devices via the control and monitoring unit, as well as the manual control circuit with control panels, light-signal boards and central light-signal fire, and is connected via a multiplex channel to a complex of on-board digital computers, an electronic left-hand engine control system , an electronic control system of the right engine, a registration and control system, guidance and landing equipment, an integrated control system, and through coding communication lines - with a fuel control and monitoring system, voice messaging equipment, an integrated electronic indication system and an auxiliary power unit. 2. The aircraft according to claim 1, characterized in that the controlled aircraft equipment includes an air conditioning system, an integrated control system, an intra-cabin light alarm system, an inter-aircraft intercom, a pneumatic hydraulic system, a wheel braking system, a fire protection system, a windshield heating system, a complex emergency escape facilities, power plant launch, control and monitoring system, life support system, power supply system, fuel management and control system a, fuel flow meter system, start-up and control system for auxiliary power unit, oxygen system, chassis control system, radio altimeter, radio compass, alarm system for lamp locks, external lighting equipment system, fuel system, air lamp visor protection system, centralized oil filling system, guidance equipment and landing, range finder, control system for the shutters of air intakes, the system of the complex of avionics, auxiliary power Settings.