Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function

A technology for unmanned helicopters and power supply systems, applied in electrical components, circuit devices, emergency power supply arrangements, etc., can solve the problems of flight control system failure, loss of pressure on airborne equipment, and large voltage drop of on-board power grids, so as to overcome voltage fluctuations. Excessive, the effect of increasing the capacity

Inactive Publication Date: 2010-05-19
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Once the helicopter engine stops in the air, it needs to be restarted; when starting, the current increases instantaneously, with an increase of about 70A (depending on the helicopter), resulting in an excessive voltage drop of the on-board power grid, and a momentary loss of voltage on the on-board equipment. The flight control system of the manned helicopter failed, resulting in a major accident
The current unmanned helicopter power supply system design avoids the above situation by using super capacitor auxiliary power supply method, which can partially improve the voltage drop when starting, but there is still serious interference with the power grid voltage of the entire airborne equipment

Method used

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  • Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function
  • Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function
  • Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function

Examples

Experimental program
Comparison scheme
Effect test

Embodiment approach 1

[0024] figure 1 The power supply system of a light unmanned helicopter is shown. In this example, the starter and the generator are two independent devices.

[0025] The engine 101 is connected with the starter 103 through the gear 106 and drives the generator 102 through the belt 105 . The generator 102 is controlled on and off by the main control box 109 . The generator control box 104 keeps the output voltage value of the generator 102 within a required voltage range by controlling the field current of the generator 102 . The generator 102 converts the generated alternating current into direct current through its internal diode. The diodes also prevent the equipment battery 108 and starter battery 110 from discharging through the generator 102 when the generator 102 voltage is too low.

[0026] The starting battery 110 and the socket 111 are connected to the power distribution bus 206 through the power distribution line 210 and the normally closed relay 114 . Here 114 s...

Embodiment approach 2

[0037] figure 2 The power supply system of a heavy-duty unmanned helicopter is shown. In this example, the starter and the generator are the same equipment.

[0038] Engine 101 is connected to starter / generator 120 through gear 106 . When the engine 101 is started, the starter / generator 120 runs electrically and drives the engine 101 to accelerate to idle speed. After the engine 101 is ignited, the engine 101 drives the starter / generator 120 to make it run in the state of power generation, and to supply power to the distribution network. Provide electrical energy. The starter generator control box 122 collects the current position and rotational speed of the rotor through the signal line 220 , detects the current current through the signal line 221 , and controls the power converter 121 through the control line 304 . The power converter 121 ensures the input and output of electric energy. The power converter is to ensure the normal operation of the forward and reverse dire...

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Abstract

The invention relates to an unmanned helicopter continuous voltage-stabilizing power supply system with an engine air restarting function, which comprises at least one generator, at least one generator control box, a distribution network, at least one equipment battery, at least one starting battery, a second electromagnetic relay, a third electromagnetic relay and a main control box, wherein the generator is driven by an unmanned helicopter engine to supply voltage; the generator control box is connected with the generator; the distribution network is connected to the generator through a transmission line to receive the voltage generated by the generator; the equipment battery is connected to the distribution network through the transmission line; the starting battery is connected to the distribution network through a first electromagnetic relay; the second electromagnetic relay is used for switching on or switching off the connection of the generator control box and the distribution network; the third electromagnetic relay is used for switching on or switching off a starter; and the main control box is connected with the first electromagnetic relay, the second electromagnetic relay and the third electromagnetic relay, receives the instruction of an airborne management computer connected with the main control box, and amplifies the current to drive each electromagnetic relay.

Description

technical field [0001] The invention relates to the power supply of unmanned aerial vehicles, in particular to a low-voltage DC power supply system for unmanned helicopters. In particular, it refers to the unmanned helicopter continuous stable voltage power supply system with the function of restarting the engine in the air. Background technique [0002] The power supply system of the unmanned helicopter needs to ensure stable and continuous power supply throughout the flight, and excessive fluctuations in the grid voltage on the aircraft are not allowed at any time. Once the helicopter engine stops in the air, it needs to be restarted; when starting, the current increases instantaneously, with an increase of about 70A (depending on the helicopter), resulting in an excessive voltage drop of the on-board power grid, and a momentary loss of voltage on the on-board equipment. The flight control system of the manned helicopter failed, resulting in a major accident. The current...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02J9/06H02J3/01
CPCY02E40/40
Inventor 周尧明章磊祝明武哲
Owner BEIHANG UNIV
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