Anti-icing and deicing device and method for wings and emages of turbo-prop aircraft

A turboprop and anti-icing technology, applied in de-icing devices, aircraft parts, transportation and packaging, etc., can solve the problems of increasing aircraft accidents, prolonging the time of de-icing, and consuming large amounts of heat, so as to improve system reliability and improve Deicing efficiency and the effect of extending the use time

What is AI technical title?
AI technical title is built by PatSnap AI team. It summarizes the technical point description of the patent document.
A turboprop and anti-icing technology, applied in de-icing devices, aircraft parts, transportation and packaging, etc., can solve the problems of increasing aircraft accidents, prolonging the time of de-icing, and consuming large amounts of heat, so as to improve system reliability and improve Deicing efficiency and the effect of extending the use time

CN109878740APending Publication Date: 2019-06-14SHANGHAI UNIV OF ENG SCI

10 Cites 10 Cited by

Image

Smart Image Click on the blue labels to locate them in the text.

Viewing Examples

Smart Image

Examples

Experimental program

Comparison scheme

Effect test

Embodiment

[0072] The installation positions of the main components of this embodiment on the aircraft are as follows: figure 1 Shown.

[0073] Aiming at the shortcomings of single-engine turboprop aircraft anti-icing and deicing technology and the shortcomings of loop heat pipes and TKS used in aircraft anti-icing and deicing, a circuit using engine waste heat is proposed based on the improvement of loop heat pipes. The heat pipe assists the efficient, economical and reliable anti-icing and deicing device and method of the TKS system. It mainly performs anti-icing and deicing on the wings and tail of single-engine turboprop aircraft.

[0074] An anti-icing and deicing device for the wing and tail of a turboprop aircraft, comprising:

[0075] System closed loop: including heat transfer evaporator 1 and No. 1 valve 14 that are connected end to end along the flow direction of the working fluid;

[0076] TKS liquid storage tank heating circuit: including heat transfer evaporator 1, steam line, TKS...

Embodiment approach

[0112] Rely on the sensor signal to control the opening and closing of the valve.

[0113] The atmospheric temperature sensor 7 detects the atmospheric temperature and controls the first valve 14 and the second valve 15. The TKS liquid storage tank temperature sensor 9 detects the temperature of the TKS liquid and controls the third valve 16. The icing detector 8 detects whether it is icing, and controls the fourth valve 17, the fifth valve 18 and the pressure pump 5.

[0114] The flow of anti-icing and deicing methods is as follows Figure 8 Shown:

[0115] Step 1: At the beginning, the aircraft starts, and the No. 1 valve 14, the No. 2 valve 15, the No. 3 valve 16, the No. 4 valve 17, and the No. 5 valve 18 are closed.

[0116] Step 2: The atmospheric temperature sensor 7 detects whether the atmospheric temperature is higher than 5°C.

[0117] If it is higher than 5°C, the No. 1 valve 14 is opened and the No. 2 valve 15 is closed, and the aircraft is in the closed state of the anti-...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine

Login to View More

PUM

Login to View More

Abstract

The invention relates to an anti-icing and deicing device and method for wings and emages of a turbo-prop aircraft, the device comprises a system close loop, a TKS fluid reservoir heating loop, an anti-icing and deicing heat transfer loop heat pipe, a distributed loop heat pipe and a TKS deicing mechanism, wherein the system close loop, the TKS fluid reservoir heating loop and a heat transfer loopshare a set of heat transfer evaporator (1), in an anti-icing state, the TKS fluid reservoir heating loop, the anti-icing and deicing heat transfer loop heat pipe and the distributed loop heat pipe work; in a deicing state, the TKS deicing mechanism works. Compared with the prior art, the TKS system deicing efficiency is improved greatly, the icing phenomena of the wings and the emages are reduced, the flight stability of the aircraft is ensured, and the system safety is reliable; waste heat of an exhaust pipe is taken as a heat source, and the energy comprehensive utilization ratio of a single turbo-prop aircraft is improved.

Description

Technical field [0001] The invention relates to an aircraft anti-icing and deicing technology, in particular to an anti-icing and deicing device and method for the wing and tail of a turboprop aircraft. Background technique [0002] With the continuous advancement of propeller technology, the propulsion efficiency of turboprop aircraft has been greatly improved, the noise level has been greatly reduced, and the ride comfort has been comparable to that of turbofan aircraft. At the same time, the turboprop aircraft has good runway adaptability and can take off and land on runways such as sand, gravel, grass, etc. The slipstream of the propeller can greatly improve the aircraft’s take-off / landing performance, allowing a shorter take-off / landing distance Therefore, turboprop aircraft has always been a common type of military aircraft. In addition, turboprop aircraft are also commonly used models for elementary and intermediate trainers and reconnaissance / attack drones due to their g...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine

Login to View More

Application Information

Patent Timeline

14 Jun 2019

Publication

CN109878740A

IPC: B64D15/06; B64D15/20; B64D15/22

Inventors: 徐梦瑶; 赵鸣