CN202765287U - Unmanned aerial vehicle onboard flight control system - Google Patents
Unmanned aerial vehicle onboard flight control system Download PDFInfo
- Publication number
- CN202765287U CN202765287U CN 201220386120 CN201220386120U CN202765287U CN 202765287 U CN202765287 U CN 202765287U CN 201220386120 CN201220386120 CN 201220386120 CN 201220386120 U CN201220386120 U CN 201220386120U CN 202765287 U CN202765287 U CN 202765287U
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- signal distributor
- steering wheel
- control
- aerial vehicle
- control system
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Abstract
The utility model relates to an unmanned aerial vehicle onboard flight control system which comprises an autopilot. The autopilot used for navigation and attitude control of an aerial vehicle shares a bidirectional information exchange passage with a signal distributor, the signal distributor realizes transfer and redistribution of control signals of the autopilot and is supplied with power by an throttle servo and a rudder servo, the throttle servo controls rotational speed of an engine by controlling oil intake of the engine, and the rudder servo controls attitude of the aerial vehicle. Besides, a data transfer radio is connected with the signal distributor through a RS 232 interface and used for receiving and transmitting data, a power module supplies power for the flight control system, and a capacity diode discharge ignition unit controls start and flame-out of the engine. The unmanned aerial vehicle onboard flight control system is simple in structure and reasonable in design. Owing to the modular design, the unmanned aerial vehicle is small in size and high in reliability, manufacturing difficulty and cost are both lowered, and later updating and upgrading of the system are guaranteed.
Description
Technical field
The utility model relates to the unmanned vehicle control field, particularly relates to the airborne flight control system of a kind of unmanned vehicle.
Background technology
At present, unmanned vehicle flight has in harsh environment and security implementation maneuvering flight on the narrow and complicated landform, hover in the original place and the advantage such as extreme low-altitude nap of the earth flight, also relatively difficult but unmanned vehicle is controlled flexibly.The control system of unmanned vehicle is many at present configures separately control system according to different aircraft series or model, lack interchangeability and commonality, be unfavorable for giving full play to the application potential of unmanned vehicle, especially airborne flight control system circuit is complicated, the circuit card volume is large, debugging work load is large and reliability is low.
Summary of the invention
The purpose of this utility model is to overcome the weak point that exists in the above-mentioned technology, provides a kind of simple in structure, reasonable in design, the airborne flight control system of examination work capacity unmanned vehicle little and that reliability is high.
In order to achieve the above object, the technical solution adopted in the utility model is: comprise the self-driving instrument, described self-driving instrument and signal distributor have the bi-directional exchanges of information passage, be used for navigation and the attitude control of aircraft, signal distributor is realized transfer and the reallocation of self-driving instrument control signal, and provide power supply for throttle steering wheel and rudder face steering wheel, described throttle steering wheel obtains the control signal of receiver by signal distributor, and be installed on the engine oil path, by the control of control engine oil inlet quantity realization to engine speed, described rudder face steering wheel obtains the control signal of receiver by signal distributor, the attitude of control aircraft, data radio station is connected with signal distributor by the RS232 interface, be used for receiving and sending data, power module is given respectively the self-driving instrument, data radio station, signal distributor, receiver, the rudder face steering wheel, the throttle steering wheel, the power supply of di-cap discharge igniting unit, described di-cap discharge igniting unit are passed through the starting of two groups of high tension cord control engines with flame-out.
The utility model has the advantages that:
1, simple in structure, reasonable in design, adopt modular design, reduce manufacture difficulty, have very high interchangeability and commonality, also guaranteed simultaneously system's upgrading from now on;
2, volume is little, can freely arrange, saves aircraft space, does not affect the mounting arrangements of other equipment;
3, cost is low, and debugging work load is little, and reliability is high.
Description of drawings
Fig. 1 is the utility model principle of work block diagram;
Fig. 2 is signal distributor control circuit schematic diagram of the present utility model;
Fig. 3 is the schematic circuit diagram that data radio station of the present utility model is connected with signal distributor;
Fig. 4 is engine start/stop control circuit schematic diagram of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing embodiment of the present utility model is described in further detail.
By Fig. 1-Fig. 4 as can be known, the utility model comprises self-driving instrument 2, described self-driving instrument 2 has the bi-directional exchanges of information passage with signal distributor 4, be used for navigation and the attitude control of aircraft, signal distributor 4 is realized transfer and the reallocation of self-driving instrument 2 control signals, and provide power supply for throttle steering wheel 5 and rudder face steering wheel 3, described throttle steering wheel 5 obtains the control signal of receiver 12 by signal distributor 4, and be installed on driving engine 6 oil circuits, by the control of control engine 6 oil inlet quantities realization to driving engine 6 rotating speeds, described rudder face steering wheel 3 obtains the control signal of receiver 12 by signal distributor 4, the attitude of control aircraft, data radio station 1 is connected with signal distributor 4 by the RS232 interface, be used for receiving and sending data, power module 11 is given respectively self-driving instrument 2, data radio station 1, signal distributor 4, receiver 12, rudder face steering wheel 3, throttle steering wheel 5,7 power supplies of di-cap discharge igniting unit, described di-cap discharge igniting unit 7 are passed through the starting of two groups of high tension cord control engines 6 with flame-out.
Described power module 11 comprises 11.1V lithium cell group 10, a 6V Ni-MH battery group 9, No. two 6V Ni-MH battery groups 8,11.1V lithium cell group 10 is given data radio station 1 and signal distributor 4 power supplies, No. one 6V Ni-MH battery group 9 gives receiver 12 power supplies, and give rudder face steering wheel 3 and 5 power supplies of throttle steering wheel by signal distributor 4 simultaneously, No. two 6V Ni-MH battery group 8 gives di-cap discharge igniting unit 7 power supplies.
The utility model di-cap discharge igniting has improved the reliability of ignition operation.Fig. 2 is the control circuit schematic diagram of signal distributor 4, signal distributor 4 connects receiver 12 by input pin 1-pin 6, receive five road control signals that remote controller sends, control respectively a throttle steering wheel 5 and 4 rudder face steering wheels 3 by output pin 1-pin 6, connect by TxRx pin data radio station 1.Signal distributor 4 TxRx pin data radio station 1 connection mode by signal distributor 4 as shown in Figure 3.Fig. 4 is engine start/stop control circuit schematic diagram, and wherein J1, J3, J6, J8 are plug, and J2, J4, J5, J7 are socket, and S1 is twist switch, and S2 is micro-switch.
The airborne flight control system of unmanned vehicle of the present utility model is take self-driving instrument 2 as control center, set in advance its flight, navigation parameter, and be transferred to self-driving instrument 2 with data radio station 1 by signal distributor 4, when starting, each device is communicated with power supply, self-driving instrument 2 imports into writes the control program of finishing, and by di-cap discharge igniting start the engine 6.The other receiver 12 by being provided with receives five road control signals that remote controller sends, and the rotational angle of what and rudder face steering wheel 3 of control engine 6 oil inlet quantities is controlled the flying height of aircraft and flight attitude, direction.
The utility model adopts modular design, and volume is little, and reliability is high, has reduced simultaneously manufacture difficulty and cost, has guaranteed system's upgrading from now on.
Claims (2)
1. airborne flight control system of unmanned vehicle, comprise self-driving instrument (2), it is characterized in that: described self-driving instrument (2) has the bi-directional exchanges of information passage with signal distributor (4), be used for navigation and the attitude control of aircraft, signal distributor (4) is realized transfer and the reallocation of self-driving instrument (2) control signal, and provide power supply for throttle steering wheel (5) and rudder face steering wheel (3), described throttle steering wheel (5) obtains the control signal of receiver (12) by signal distributor (4), and be installed on driving engine (6) oil circuit, by the control of control engine (6) oil inlet quantity realization to driving engine (6) rotating speed, described rudder face steering wheel (3) obtains the control signal of receiver (12) by signal distributor (4), the attitude of control aircraft, data radio station (1) is connected with signal distributor (4) by the RS232 interface, be used for receiving and sending data, power module (11) is given respectively self-driving instrument (2), data radio station (1), signal distributor (4), receiver (12), rudder face steering wheel (3), throttle steering wheel (5), di-cap discharge igniting unit (7) power supply, described di-cap discharge igniting unit (7) are passed through the starting of two groups of high tension cord control engines (6) with flame-out.
2. the airborne flight control system of unmanned vehicle according to claim 1, it is characterized in that: described power module (11) comprises 11.1V lithium cell group (10), a 6V Ni-MH battery group (9), No. two 6V Ni-MH battery groups (8), 11.1V lithium cell group (10) is given data radio station (1) and signal distributor (4) power supply, a 6V Ni-MH battery group (9) is given receiver (12) power supply, and give rudder face steering wheel (3) and throttle steering wheel (5) power supply by signal distributor (4) simultaneously, No. two 6V Ni-MH battery groups (8) are given di-cap discharge igniting unit (7) power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220386120 CN202765287U (en) | 2012-08-06 | 2012-08-06 | Unmanned aerial vehicle onboard flight control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220386120 CN202765287U (en) | 2012-08-06 | 2012-08-06 | Unmanned aerial vehicle onboard flight control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202765287U true CN202765287U (en) | 2013-03-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220386120 Expired - Lifetime CN202765287U (en) | 2012-08-06 | 2012-08-06 | Unmanned aerial vehicle onboard flight control system |
Country Status (1)
| Country | Link |
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| CN (1) | CN202765287U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104407607A (en) * | 2014-10-15 | 2015-03-11 | 天津全华时代航天科技发展有限公司 | Unmanned aerial vehicle first-person perspective control system |
| CN105242682A (en) * | 2015-11-04 | 2016-01-13 | 北京航天科颐技术有限公司 | Target characteristic measurement system for drone aircraft |
| CN105818971A (en) * | 2016-03-30 | 2016-08-03 | 河南三和航空工业有限公司 | Unmanned gyroplane |
| CN111075628A (en) * | 2019-12-31 | 2020-04-28 | 航天时代飞鸿技术有限公司 | Automatic control system of piston engine |
-
2012
- 2012-08-06 CN CN 201220386120 patent/CN202765287U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104407607A (en) * | 2014-10-15 | 2015-03-11 | 天津全华时代航天科技发展有限公司 | Unmanned aerial vehicle first-person perspective control system |
| CN105242682A (en) * | 2015-11-04 | 2016-01-13 | 北京航天科颐技术有限公司 | Target characteristic measurement system for drone aircraft |
| CN105242682B (en) * | 2015-11-04 | 2018-06-19 | 北京航天科颐技术有限公司 | Target drone target signature measurement system |
| CN105818971A (en) * | 2016-03-30 | 2016-08-03 | 河南三和航空工业有限公司 | Unmanned gyroplane |
| CN111075628A (en) * | 2019-12-31 | 2020-04-28 | 航天时代飞鸿技术有限公司 | Automatic control system of piston engine |
| CN111075628B (en) * | 2019-12-31 | 2022-03-18 | 航天时代飞鸿技术有限公司 | Automatic control system of piston engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130306 |
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| CX01 | Expiry of patent term |