CN107651171A - Aircraft tailspin state auxiliary driving device - Google Patents
Aircraft tailspin state auxiliary driving device Download PDFInfo
- Publication number
- CN107651171A CN107651171A CN201710913348.3A CN201710913348A CN107651171A CN 107651171 A CN107651171 A CN 107651171A CN 201710913348 A CN201710913348 A CN 201710913348A CN 107651171 A CN107651171 A CN 107651171A
- Authority
- CN
- China
- Prior art keywords
- component
- aircraft
- tailspin
- voice message
- yawrate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000008859 change Effects 0.000 claims abstract description 9
- 230000007246 mechanism Effects 0.000 claims abstract description 8
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
- B64D43/02—Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Emergency Alarm Devices (AREA)
Abstract
Aircraft tailspin state auxiliary driving device, airborne mechanism and aircraft control computer including changing tailspin driving for second-mission aircraft, wherein, airborne mechanism includes instruction component, acquisition component, processing component and voice message component, indicate that component is arranged on Flight Instrument plate, acquisition component, processing component, voice message component are arranged in box body, and acquisition component one end is connected with aircraft control computer, the other end is connected with processing component, processing component is connected with instruction component, and voice message component is connected with processing component.The present invention is by increasing instruction component and voice message component, the indication signal being readily appreciated that and voice signal are provided for pilot, pilot can be helped promptly and accurately to judge flight status, and tailspin direction, pilot is contributed to take correct tailspin to change measure in time, aircraft is changed tailspin state, reduce the peril for fatal crass occur.
Description
Technical field
The present invention relates to aircraft handling ancillary technique field, more particularly to a kind of aircraft tailspin state auxiliary driving device.
Background technology
Tailspin is a kind of critical flight states, is after the angle of attack of aircraft exceedes the critical angle of attack, one kind of generation is continuous certainly
Dynamic rotary motion.In tailspin generating process, helical trajectory of the aircraft along a minor radius rotates, while drastically
Decline, and constantly vibrated around rolling, pitching, three axles of driftage simultaneously.Tailspin is most complicated with most dangerous state of flight, aeronautical chart
Visually it is referred to as " death spiral ".And to change tailspin this state of flight, pilot is firstly the need of the direction for judging tailspin, so
After take appropriate measures, primary control surface, aircraft is stopped the rotation, the angle of attack is dropped in the critical angle of attack, and underriding speedup changes.
Modern combat aircraft is in tailspin, and general vibration is very violent, simultaneously because abruptly entering tailspin, pilot psychological is tight
, in turn result in pilot and be not easy to judge aircraft tailspin direction, cause correct tailspin can not be taken to change measure.In addition,
Because pilot psychological is nervous, it is also possible to pilot's reaction occur slowly, fail to take tailspin to change measure in time.These feelings
Condition, it is likely to cause aircraft to change tailspin, the peril of fatal crass occurs.
The content of the invention
Technical problem solved by the invention is to provide a kind of aircraft tailspin state auxiliary driving device, above-mentioned to solve
The shortcomings that in background technology.
Technical problem solved by the invention is realized using following technical scheme：
Aircraft tailspin state auxiliary driving device, including change airborne mechanism and the aircraft control that tailspin drives for second-mission aircraft
Computer, wherein, airborne mechanism includes instruction component, acquisition component, processing component and voice message component, instruction component installation
On Flight Instrument plate, acquisition component, processing component, voice message component are arranged in box body, and acquisition component one end
It is connected with aircraft control computer, the other end is connected with processing component, and processing component is connected with instruction component, voice message component
It is connected with processing component.
In the present invention, processing component is connected by cable with instruction component.
In the present invention, instruction component includes left indicator lamp and right indicating lamp.
In the present invention, sensor is provided with acquisition component, acquisition component is counted from one group of sensor and/or aircraft control
Calculation machine gathers the one group of flight parameter and configuration data for being relevant to aircraft, and this group of flight parameter includes the angle of attack of aircraft, yaw angle
Speed etc., the position configured for example including wing flap or other flight control assemblies of aircraft.
In the present invention, the flight parameter that processing component transmits according to acquisition component determines the stalling angle of aircraft, and will
Aircraft angle of attack is contrasted with stalling angle, if aircraft angle of attack is more than stalling angle, continues to judge the yawrate of aircraft
Whether absolute value is more than 30 degrees seconds；If the absolute value of yawrate is more than 30 degrees seconds, processing component gives voice message group
Part signal, voice message component provide the voice message of " entering tailspin "；By the positive and negative of yawrate, airplane tail is judged
The direction of rotation, if yawrate is more than 0, for right tailspin, right indicating lamp is bright, and voice message component provides the language of " right tailspin "
Sound is prompted；If yawrate is less than 0, for left tailspin, left indicator lamp is bright, and voice message component provides " left tailspin "
Voice message；When the absolute value of yawrate is less than 30 degrees seconds, and aircraft angle of attack is less than stalling angle, voice message stops
Only, indicate that the indicator lamp of component extinguishes.
Beneficial effect：The present invention provides what is be readily appreciated that by increasing instruction component and voice message component for pilot
Indication signal and voice signal, pilot can be helped promptly and accurately to judge flight status, and tailspin direction, help to fly
Office staff takes correct tailspin to change measure in time, aircraft is changed tailspin state, reduces the peril for fatal crass occur.
Brief description of the drawings
Fig. 1 is the structural representation of presently preferred embodiments of the present invention.
Embodiment
In order that the technical means, the inventive features, the objects and the advantages of the present invention are easy to understand, tie below
Conjunction is specifically illustrating, and the present invention is expanded on further.
Referring to Fig. 1 aircraft tailspin state auxiliary driving device, including airborne mechanism 1, instruction component 2, left indicator lamp 3,
Right indicating lamp 4, aircraft control computer 5, acquisition component 6, processing component 7, voice message component 8, cable 9 and box body 10, its
In, the airborne mechanism 1 of tailspin driving is changed for second-mission aircraft includes instruction component 2, acquisition component 6, processing component 7 and voice
Component 8 is prompted, instruction component 2 is arranged on Flight Instrument plate, and acquisition component 6, processing component 7, voice message component 8 are pacified
In box body, and the one end of acquisition component 6 is connected with aircraft control computer 5, and the other end is connected with processing component 7, treatment group
Part 7 is connected by cable 9 with instruction component 2, and voice message component 8 is connected with processing component 7, and instruction component 2 includes left instruction
Lamp 3 and right indicating lamp 4；
In the present embodiment, acquisition component 6 is relevant to the one of aircraft from one group of sensor and/or the collection of aircraft control computer 5
Group flight parameter and configuration data, this group of flight parameter include the angle of attack of aircraft, yawrate etc., and the configuration of aircraft is for example wrapped
Include wing flap or the position of other flight control assemblies.
Processing component 7 is transmitted come the position of flight parameter such as wing flap or other flight control assemblies according to acquisition component 6,
Determine the stalling angle of aircraft（The stalling angle of corresponding configuration is determined in early stage correlation test, and is stored in processing
In component 7）, aircraft angle of attack and stalling angle are contrasted；If aircraft angle of attack is more than stalling angle, continue to judge the inclined of aircraft
Whether the absolute value of boat angular speed is more than 30 degrees seconds；If the absolute value of yawrate is more than 30 degrees seconds, processing component 7 is given
The signal of voice message component 8, voice message component 8 provide the voice message of " entering tailspin "；By yawrate just
It is negative, judge the direction of aircraft tailspin, if yawrate is more than 0, for right tailspin, right indicating lamp 4 is bright, voice message component 8
Provide the voice message of " right tailspin "；If yawrate is less than 0, for left tailspin, left indicator lamp 3 is bright, and voice message
Component 8 provides the voice message of " left tailspin "；When the absolute value of yawrate is less than 30 degrees seconds, and aircraft angle of attack is less than and lost
During the fast angle of attack, voice message stops, and the indicator lamp of instruction component 2 extinguishes.
The general principle and principal character and advantages of the present invention of the present invention has been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and the simply explanation described in above-described embodiment and specification is originally
The principle of invention, without departing from the spirit and scope of the present invention, various changes and modifications of the present invention are possible, these changes
Change and improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention by appended claims and its
Equivalent thereof.
Claims (5)
1. aircraft tailspin state auxiliary driving device, including change airborne mechanism and the aircraft control that tailspin drives for second-mission aircraft
Computer processed, it is characterised in that airborne mechanism includes instruction component, acquisition component, processing component and voice message component, instruction
Component is arranged on Flight Instrument plate, and acquisition component, processing component, voice message component are arranged in box body, and are gathered
Component one end is connected with aircraft control computer, and the other end is connected with processing component, and processing component is connected with instruction component, voice
Prompting component is connected with processing component.
2. aircraft tailspin state auxiliary driving device according to claim 1, it is characterised in that processing component passes through cable
It is connected with instruction component.
3. aircraft tailspin state auxiliary driving device according to claim 1, it is characterised in that instruction component includes a left side
Indicator lamp and right indicating lamp.
4. aircraft tailspin state auxiliary driving device according to claim 1, it is characterised in that be provided with acquisition component
Sensor.
5. the aircraft tailspin state auxiliary driving device according to any one of Claims 1 to 4, it is characterised in that treatment group
The flight parameter that part transmits according to acquisition component determines the stalling angle of aircraft, and aircraft angle of attack and stalling angle are carried out pair
Than if aircraft angle of attack is more than stalling angle, continuing to judge whether the absolute value of the yawrate of aircraft is more than 30 degrees seconds；If
The absolute value of yawrate is more than 30 degrees seconds, and processing component gives voice message component signals, and voice message component provides
The voice message of " entering tailspin "；By the positive and negative of yawrate, the direction of aircraft tailspin is being judged, if yawrate is big
Then it is right tailspin, right indicating lamp is bright, and voice message component provides the voice message of " right tailspin " in 0；If yawrate is less than
0, then it is left tailspin, left indicator lamp is bright, and voice message component provides the voice message of " left tailspin "；When yawrate
Absolute value is less than 30 degrees seconds, and when aircraft angle of attack is less than stalling angle, voice message stops, and indicates that the indicator lamp of component extinguishes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710913348.3A CN107651171A (en) | 2017-09-30 | 2017-09-30 | Aircraft tailspin state auxiliary driving device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710913348.3A CN107651171A (en) | 2017-09-30 | 2017-09-30 | Aircraft tailspin state auxiliary driving device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107651171A true CN107651171A (en) | 2018-02-02 |
Family
ID=61116212
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710913348.3A Pending CN107651171A (en) | 2017-09-30 | 2017-09-30 | Aircraft tailspin state auxiliary driving device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107651171A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5595357A (en) * | 1994-07-05 | 1997-01-21 | The B. F. Goodrich Company | Aircraft stall warning system |
| CN103514360A (en) * | 2012-06-18 | 2014-01-15 | 波音公司 | Stall management system |
| CN103847971A (en) * | 2012-11-30 | 2014-06-11 | 空中客车股份有限公司 | Assistance with piloting of aircraft in stall |
| CN104670666A (en) * | 2015-02-27 | 2015-06-03 | 中国民航大学 | Aircraft landing attitude alarming system and alarming control method |
| US9580186B1 (en) * | 2015-08-28 | 2017-02-28 | Safe Flight Instrument Corporation | Helicopter tactile stall warning |
-
2017
- 2017-09-30 CN CN201710913348.3A patent/CN107651171A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5595357A (en) * | 1994-07-05 | 1997-01-21 | The B. F. Goodrich Company | Aircraft stall warning system |
| CN103514360A (en) * | 2012-06-18 | 2014-01-15 | 波音公司 | Stall management system |
| CN103847971A (en) * | 2012-11-30 | 2014-06-11 | 空中客车股份有限公司 | Assistance with piloting of aircraft in stall |
| CN104670666A (en) * | 2015-02-27 | 2015-06-03 | 中国民航大学 | Aircraft landing attitude alarming system and alarming control method |
| US9580186B1 (en) * | 2015-08-28 | 2017-02-28 | Safe Flight Instrument Corporation | Helicopter tactile stall warning |
Non-Patent Citations (1)
| Title |
|---|
| 李季陆等: "尾旋自动防止***非线性解耦控制律综合方法", 《航空学报》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9789952B2 (en) | Methods and apparatus of notification of a flight asymmetry influencing an aircraft | |
| CN204989831U (en) | Self -driving car control system | |
| US9193473B2 (en) | Angle of attack display | |
| ES2632175T3 (en) | Calculation and display of the warning speed for control with thrust asymmetry | |
| US8887570B2 (en) | Contact detection | |
| CN106525388B (en) | A kind of rotor class aircraft ditching model test method | |
| EP2676883B1 (en) | Stall management system | |
| CN102763049A (en) | Stall prevention/recovery system and method | |
| US20170243505A1 (en) | Adaptive assistance for flight simulation | |
| CN107406240B (en) | Revolving gear | |
| WO2011017601A1 (en) | Upset recovery training using a sustained-g multi-axis platform or a centrifuge | |
| CN107651171A (en) | Aircraft tailspin state auxiliary driving device | |
| CN108202852A (en) | The method of fluctuation pressure is reduced by real-time vibration information and the rotation angle of adjusting propeller in twinscrewvessel | |
| CN107792404A (en) | The safety belt that section is drawn close in a kind of spacecrafts rendezvous translation determines method | |
| Grafton et al. | Wind-tunnel free-flight investigation of a model of a spin-resistant fighter configuration | |
| EP3627272B1 (en) | Aircraft anti-spin systems | |
| CN104764464B (en) | A method of carrying out aircraft redundant diagnostic using full dose information | |
| KR101055662B1 (en) | Flight control system and method for general bomb flight aids | |
| CN105424267A (en) | Probe used for total pressure measurement of rotorcraft | |
| Metzler | G-LOC due to the push-pull effect in a fatal F-16 mishap | |
| EP2687440A1 (en) | Apparatus and method for reducing, avoiding or eliminating lateral vibrations of a helicopter | |
| CN203291517U (en) | Model airplane | |
| US20200124442A1 (en) | Aeronautical display system and method | |
| CN103121504A (en) | Coordination control device and coordination control method for accelerating turning of four-paddle drive boat | |
| Xing et al. | Design and implementation of UAV flight simulation based on Matlab/Simulink |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180202 |