CN107933894A - A kind of devices and methods therefor for improving aircraft flight safety - Google Patents

A kind of devices and methods therefor for improving aircraft flight safety Download PDF

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Publication number
CN107933894A
CN107933894A CN201610893599.5A CN201610893599A CN107933894A CN 107933894 A CN107933894 A CN 107933894A CN 201610893599 A CN201610893599 A CN 201610893599A CN 107933894 A CN107933894 A CN 107933894A
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CN
China
Prior art keywords
flight
aircraft
power
auxiliary power
groups
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CN201610893599.5A
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Chinese (zh)
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赵蓝婷
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赵蓝婷
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Priority to CN201610893599.5A priority Critical patent/CN107933894A/en
Publication of CN107933894A publication Critical patent/CN107933894A/en
Pending legal-status Critical Current

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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C17/00Aircraft stabilisation not otherwise provided for

Abstract

A kind of device and method for improving aircraft flight safety of the present invention, can improve makes flight evade the problem of effect is subject to larger restriction because of the feature of the single dimension linear track of aircraft, ability when can especially improve to needing to evade in face of arising suddenly or being anticipated that obtained flight safety obstacle under the conditions of the higher flying speed of contemporary aircraft, makes the active safety flight performance of aircraft further get a promotion.It is completed by the upper and lower and increased auxiliary power unit of two dimensions in left and right for heading on heading and its relevant operation, forms the multiple means that linear processes fine setting can be carried out in three dimensions.

Description

A kind of devices and methods therefor for improving aircraft flight safety
Technical field
The present invention relates to a kind of devices and methods therefor of aircraft.Device more particularly to aircraft flight safety and its Method.
Background technology
Current aircraft is linear track, and with the raising of flying speed, the linear character of flight path is more bright It is aobvious, can only be by means of traditional auxiliary if to need to evade in face of burst of or being anticipated that obtained flight obstacle Means, for example, the mode such as adjustment aileron, elevator or engine power outbound course, tilts aircraft fuselage and carries out linearly Adjustment, is smooth Linear fine tuning.In view of this single means that Linear fine tuning is only carried out in one dimension of heading, constraint The diversity of aircraft various dimensions adjustment, to cause flight to evade effect and security will be subject to larger restriction.
The content of the invention
A kind of device and method for improving aircraft flight safety of the present invention, can improve because of the single dimension of aircraft The feature of linear track and flight is evaded the problem of effect is subject to larger restriction, it is particularly possible to improve it is higher to contemporary aircraft Ability when needing to evade in face of burst of or being anticipated that obtained flight safety obstacle under the conditions of flying speed, makes flight The active safety flight performance of device further gets a promotion.
It is of the present invention it is a kind of improve aircraft security flight device and method, it be by with heading head on for The upper and lower and increased auxiliary power unit of two dimensions in left and right and its relevant operation complete, form can three dimensions into The multiple means of line and non-linear trimming.
The purpose of the present invention is what is be achieved through the following technical solutions:
1, respectively symmetrically increase one, two or three auxiliary power unit on the flying wing of two groups of the left and right of aircraft, Specifically will be depending on flying wing quantity and its needs, which is installed at the close middle outer end of flying wing, by connector, makes The upper and lower and dimension auxiliary power of left and right two that the device can produce for heading on heading in flight exports;
2, which can be jet pipe spout, pick up from the shunting output of aircraft jet power itself;This is auxiliary Power-assisting device can be the rotor power output that other independent power sources provide;Can also be both combinations.No matter the dress The auxiliary power put is exported by spout output or rotor, and the device and its auxiliary power outbound course can be with flying Line direction head on for upper and lower and left and right 360 degree of two dimensions in rotation (360 degree of meaning is to be met with heading below Upper and lower and two dimensional spaces in left and right for face), any angle of the device in the range of this 360 degree is actively provided The auxiliary power output of safe flight, so as to directly affect aircraft in the flight kept or close under keeping level conditions Highly, flight two-dimensional angle position and heading;
3, by rationally adjusting (including integrated regulation and adjustment respectively), two groups of auxiliary power units can pass through output work The setting of rate size, the adjustment of output power size, the setting of output power angle, the coordination in direction of doing work each other, Ji Huke To complete flight of the aircraft keeping or close to any fixed angle and angle changing of two-dimensional space under holding level conditions Adjustment requirement, makes flight path produce drift angle (the present patent application definition of a small direction or displacement:The drift angle in direction is Refer to the change of heading, the drift angle of displacement refers to that heading does not change, the simply two-dimensional spatial location in 360 degree of change It is mobile), the following two kinds effect can be produced:One, no longer it is smooth Linear fine tuning, but have a small direction deflection angle tune It is whole, just as one seems that the football for flying to goal will deviate target soon, the shoulder of a sportsman, wink are slightly clipped suddenly Between produce a small drift angle and to have injected goal-net suddenly the same, so as to evade to greatest extent it is precipitate before Fang Feihang obstacles;Two, be no longer smooth Linear fine tuning, but have the adjustment of two-dimensional space displacement drift angle, just as with small bird Struggle to flutter wing lifting flying height, helicopter rotating screw lifting flying height is similar, and small bird and helicopter are preceding winged same When, in 360 degree of two-dimensional spaces only have " upper and lower " dimension the displacement of lifting flying height act on, do not have " left and right " this The transverse translation displacement effect of dimension, and the present invention is provided simultaneously with both displacement functions.
4, the setting of output power size:Front and rear each two maximum work outputs in two groups of flight auxiliary powers of the device Rate will be set respectively, to match different weight before and after aircraft, and make aircraft in flight course integrally in place Move drift angle adjustment.
5, the adjustment of output power size:Refer to that the auxiliary power unit provides thrust or the size of pulling force, you can with whole Body adjusts, and can also adjust respectively.Integrated regulation refers to that two groups of auxiliary power units synchronously receive the tune of thrust or pulling force size Whole instruction, for example, two groups of auxiliary power units synchronously receive the adjust instruction of thrust or pulling force size, and aircraft will obtain size The displacement not waited is without the change that heading occurs.Auxiliary power unit each receives to push away before and after adjustment refers to two groups respectively The adjust instruction of power or pulling force size, for example, four auxiliary power units each receive the adjust instruction of thrust or pulling force size, Aircraft can obtain small drift angle and adjust the change so that change of flight direction, cannot but obtain the global displacement of aircraft Effect;
6, the setting of output power angle:Refer to angle initialization of the auxiliary power unit in acting, you can with entirety Adjustment, can also adjust, integrated regulation refers to that two groups of auxiliary power units synchronously receive the tune of two-dimensional space angle initialization respectively Whole instruction, to determine the dynamics of flight displacement drift angle, adjustment respectively refers to that auxiliary power unit receives different tune before and after two groups Whole instruction, to determine the dynamics of heading drift angle;
7, the coordination in direction of doing work each other:Refer to the general effect adjustment of the auxiliary power unit, it will not only combine upper The adjustment effect of output power size and the adjustment effect of output power angle initialization are stated, also to be considered other such as wind-force wind To natural climate situations such as shear wind heavy rain lightnings, evade the instant situations such as precipitate flight safety obstacle, it is total to be subject to Comprehensive coordination.
After devices and methods therefor using raising aircraft flight safety of the present invention, it is possible to which flight is evaded in raising The ability of risk, that there was only preceding the latter dimensional space originally evades flight risk means, and present patent application so far is determined Aircraft (" explanation of nouns in the figure " part seen below) all methods for evading flight risk of justice be built upon it is such before On the basis of the latter dimensional space because aircraft so far only have dimension direction flying power output (even if The tail-rotor of helicopter is also only in that the torsion that symmetric screw propeller itself produces).Now in addition the present invention is due to adding The auxiliary power of two dimensions is exported to evade aircraft exterior flight risk means, is enriched aircraft and is evaded external flight wind Dangerous means selection, so as to improve the ability of propulsion safety.
The present invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 is the floor map of embodiment 1, aircraft and its safety device;
Fig. 2 is the front schematic view of embodiment 1, aircraft and its safety device;
Fig. 3 is the side schematic view of embodiment 1, aircraft and its safety device;
Fig. 4 is embodiment 1, and rotation paddle machine plane signal drawing, picks up from the A in Fig. 1;
Fig. 5 is embodiment 1, rotation paddle pusher side face signal drawing;Pick up from the B in Fig. 3;
Fig. 6 is the floor map of embodiment 2, aircraft and its safety device;
Fig. 7 is the front schematic view of embodiment 2, aircraft and its safety device;
Fig. 8 is the side schematic view of embodiment 2, aircraft and its safety device;
Fig. 9 is embodiment 2, and nozzle assembly plane signal drawing, picks up from the C in Fig. 1;
Figure 10 is embodiment 2, and nozzle assembly side signal drawing, picks up from the D in Fig. 1;
Figure 11 is embodiment 3, aircraft left-hand turn schematic diagram;
Figure 12 is embodiment 4, and aircraft is integrally flown nonstop to plus two-dimentional 45 degree of displacement flight schematic diagrames;
Figure 13 is embodiment 5, and aircraft is integrally flown nonstop to plus lower dimension displacement flight schematic diagram.
Explanation of nouns in figure:
1, aircraft wings, abbreviation flying wing --- the effect of flight lift and balance flight is provided;
2, revolve paddle machine --- it is self-powered and can 360 degree spin devices;
3, connector --- the device for connecting rotation paddle machine with flying wing;
4, revolve paddle --- the propeller in rotation paddle machine, can produce output power;
5, nozzle assembly --- with nozzle can 360 degree spin devices,;
6, nozzle --- jet picks up from aircraft body, can produce thrust output;
7, jet pipe and connector --- the device for connecting nozzle assembly and flying wing;
8, aircraft --- carry the flight instruments that flying wing and rudder and engine can go up to the air.
Carrying out practically is such:
Embodiment 1:Increase an auxiliary power unit, the device respectively on four flying wings of left-right and front-back of aircraft It is made of, is installed on by connector at the close middle outer end of flying wing, using the terminal of connector as the center of circle rotation paddle machine and rotation paddle (longitudinal direction in the center of circle is consistent with the heading of the aircraft) can do 360 degree of rotating power outputs.
Embodiment 2:Increase an auxiliary power unit, the device respectively on four flying wings of left-right and front-back of aircraft By nozzle assembly and sprinkler composition, it is installed on by jet pipe and connector at the close middle outer end of flying wing, with the end of connector 360 degree of rotating power outputs can be done for the center of circle (longitudinal direction in the center of circle is consistent with the heading of the aircraft) by holding.
Embodiment 3:When finding that front is unexpected or is anticipated that the flight obstacle occurred needs to evade, can start The rotation paddle machine [2] or nozzle assembly [5] on the left side on preceding flying wing [1], left direction can be produced by being allowed to rotate and being positioned at Motivation of adjustment, the other three rotation paddle machine [2] or nozzle assembly [5] are allowed to rotate and are positioned at and can produce vertically Motivation of adjustment, with the yaw maneuver of left-handed paddle machine [2] or nozzle assembly [5] before cooperation, balances the horizontality of aircraft.Four The coordination of auxiliary power unit can make aircraft [8] produce the left-hand drift angle of horizontal plane, and not have to as traditional use side Yawed to rudder and achieve the purpose that to turn to flight to tilt aircraft [8].Steering flight reason toward right direction is as the same.Tilt The flight attitude of aircraft [8] always has certain risk, especially in the operation of large-scale airliner.And the dress that the present invention uses Put and its method can not only keep the level flight condition of aircraft [8], but also the purpose for turning to flight can be produced, attempting to advise Security is just improved when keeping away flight obstacle, the travelling experience of the safety and steady of aviation passenger is got a promotion.
Embodiment 4:When finding that front is unexpected or is anticipated that the flight obstacle occurred needs to evade, can start Rotation paddle machine [1] or nozzle assembly [5] on front and rear flying wing are run at the same time, and are allowed to upper and lower and two dimensions 360 in left and right Degree orientation gets into smooth, and the rotation paddle machine [1] or nozzle assembly [5] before and after order on flying wing produce the thrust or pulling force of displacement, make Aircraft overall [8] produces 45 degree of displacement effects.The thrust of rotation paddle machine [1] or nozzle assembly [5] before and after adjusting on flying wing Or the output power of pulling force, and the speed and strength for controlling them to be operated with 45 degree of orientation, can protect aircraft overall [8] Card is horizontal and directly to 45 degree of displacement flight requirements during flight, are reached, and produces non-traditional linear flight path, makes to evade flight obstacle A kind of again more selections of thing, improve flight safety to a certain extent.
Embodiment 5:Generally, as flight travel passengers, both know about aircraft safety coefficient in parallel flight and compare Height, there is certain risk when taking off or landing, wherein it is exactly stall to have one, the flight elevation angle exceedes the critical elevation angle.Use the elevation angle The relevant apparatus such as sensor can no doubt monitor, but aircraft pilot always empirically lifts the flight elevation angle to obtain lift, Since substantially producing for flight effect has a hysteresis effect than with flight operation, give again when monitor and control facility sends alarm Correction, then to rectifying effect is produced, perhaps risk has been produced and acted on, and therefore, most basic solution is, A kind of method for no at all relying on lift required for flight big-elevation can just obtain again is provided.By the present invention in that aircraft is whole The displacement that body [8] produces dimension up and down in flying nonstop to acts on, i.e., rotation paddle machine [1] or nozzle assembly [5] one on front and rear flying wing Cause to produce the thrust shifted up or pulling force, then, aircraft does not have to rely on flight big-elevation, only can just be obtained with the medium and small elevation angle Necessary lift, so as to thoroughly prevent the stall event produced because the flight elevation angle exceedes the critical elevation angle.

Claims (9)

  1. A kind of 1. devices and methods therefor for improving aircraft flight safety, it is characterised in that:It is provided by what is newly increased Lower and left and right (for flight head-on, similarly hereinafter) device of two dimension auxiliary powers is formed, plus original aircraft face The front and rear dimension linearly flown forwards, constitutes the aircraft of a three dimensionality powered, makes aircraft in line forwards Property flight while can carry out two other dimension linearly or nonlinearly auxiliary displacement flight or drift angle flight, so as to improve The diversity of aircraft flight track, opened up 360 degree of displacements flight of aircraft winged domain (aircraft preceding winged while also Can fly in up and down and left and right two dimensions flying area), improve to large extent aircraft evade arise suddenly or It is anticipated that the ability of obtained various flight obstacles, the efficiency of flight safety get a promotion.
  2. A kind of 2. devices and methods therefor of flight safety according to claim 1, it is characterised in that:What is newly increased provides Symmetrically it is made of two groups of left and right flight auxiliary power with the device of the two dimension flight auxiliary powers in left and right, the device up and down, often Group has one, two or three flight auxiliary power, specifically will be depending on flying wing quantity and its needs, wherein every group two are Left and right totally four combination it is the most typical.Two groups of flight auxiliary power units are separately mounted at the close middle outer end of flying wing, Both it can be placed in before flying wing, can also be placed in behind flying wing.By connector, make this two groups of flight auxiliary Power set can produce the upper and lower and two lateral power of dimension in left and right for heading on heading in aircraft flight Output, i.e., must can be done using the terminal of connector as the center of circle (longitudinal direction in the center of circle is consistent with the heading of the aircraft) 360 degree of rotating power outputs, can be any angle and one above and below aircraft is produced in flight and in two dimensions in left and right Fixed displacement demand provides assisting in flying output power adjustment.
  3. A kind of 3. devices and methods therefor of flight safety according to claim 2, it is characterised in that:Two groups of the device fly The output of row auxiliary power can be the shunting for picking up from aircraft jet power itself, provided by spout, can be self-powered source The rotor power output of offer, is provided by the rotation of rotor.Can also be the various power outputs that other independent power sources provide, By the port of adaptation or in a manner of provide.
  4. A kind of 4. devices and methods therefor of flight safety according to claim 3, it is characterised in that:Two groups of the device fly If row auxiliary power is exported using rotor power, in the case where ensureing power output direction unanimous circumstances, the rotor that two group of left and right Direction of rotation must be reverse, and one group counterclockwise, and another group must be clockwise, to balance reaction torque of the rotor to aircraft body.
  5. A kind of 5. devices and methods therefor of flight safety according to claim 2, it is characterised in that:Two groups of the device fly The setting of the peak power output of front and rear each two in row auxiliary power should be suitable or close with front and rear flying wing area ratio, Its role is to can the front and rear equivalent flight auxiliary power unit that adaptedly plays synchronously do 360 degree of global displacements adjustment flights When, still can keep aircraft it is horizontal or it is straight to horizontal flight attitude because front and rear dead weight is not to aircraft in itself With.
  6. A kind of 6. devices and methods therefor of flight safety according to claim 5, it is characterised in that:Before two groups of the device Maximum output effect will can make aircraft keep water flat or straight to (landing during horizontal flight in flight auxiliary power afterwards Except) monolithic stability and obvious displacement effect can be completed, to prove that it is dynamic in high speed flight that the aircraft can have the ability 360 degrees omnidirection adjustment of displacement flight is carried out in state (except landing), it is stablized and obvious displacement effect standard will by design Ask and provide.Current technology means can provide completely flight auxiliary power is enough before and after two groups of the device output power with Reach such design requirement, as long as because aircraft imposes certain two into horizontal flight dynamic in high speed water flat or straight Lateral power is tieed up, remarkable result will be produced.
  7. A kind of 7. devices and methods therefor of flight safety according to claim 6, it is characterised in that:Before two groups of the device The effect main during landing of flight auxiliary power is to provide under aircraft front and rear body non-standard state whole afterwards The auxiliary lifting of body.
  8. A kind of 8. devices and methods therefor of flight safety according to claim 7, it is characterised in that:Before two groups of the device Flight auxiliary power can also be operated independently afterwards, to reach the generation flight side under conditions of aircraft horizontal flight is kept To drift angle adjust, make aircraft occur direction change, so as to evade front flight obstacle.
  9. A kind of 9. devices and methods therefor of flight safety according to claim 8, it is characterised in that:Before two groups of the device Flight auxiliary power will be coordinated mutually afterwards, to ensure that aircraft still horizontal can fly when heading occurs and actively changes OK.When front left flight auxiliary power performs left-hand flight, aircraft produces the flight of left-hand drift angle, and other flight auxiliary powers are done Balance coordination (does work) up or down;For dextrad flight when, front right flight auxiliary power perform dextrad flight, produce aircraft Raw dextrad drift angle flight, other flight auxiliary powers do balance coordination (doing work up or down).
CN201610893599.5A 2016-10-13 2016-10-13 A kind of devices and methods therefor for improving aircraft flight safety Pending CN107933894A (en)

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2830237A1 (en) * 2001-09-28 2003-04-04 Lariviere Jean Soulez Heavier than air aircraft comprises pivoting screw nacelles at ends of arms projecting from fuselage sides
CN101596931A (en) * 2009-06-26 2009-12-09 中国人民解放军国防科学技术大学 A kind of triple helical oar is the method for vector propelling initiatively
US20120091257A1 (en) * 2009-05-27 2012-04-19 Israel Aerospace Industries Ltd. Air vehicle
CN204279944U (en) * 2014-11-22 2015-04-22 吴建伟 A kind of combined type vertically taking off and landing flyer
FR3024431A1 (en) * 2012-12-10 2016-02-05 Gerome Bermond Convertible aircraft comprising two caren rotors at the end of a wing and a horizontal fan in fuselage
CN205034337U (en) * 2015-05-25 2016-02-17 郝思阳 Distributing type vector advancing mechanism
US20160244157A1 (en) * 2015-02-19 2016-08-25 Amazon Technologies, Inc. Vehicle configuration with motors that rotate between a lifting position and a thrusting position

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2830237A1 (en) * 2001-09-28 2003-04-04 Lariviere Jean Soulez Heavier than air aircraft comprises pivoting screw nacelles at ends of arms projecting from fuselage sides
US20120091257A1 (en) * 2009-05-27 2012-04-19 Israel Aerospace Industries Ltd. Air vehicle
CN101596931A (en) * 2009-06-26 2009-12-09 中国人民解放军国防科学技术大学 A kind of triple helical oar is the method for vector propelling initiatively
FR3024431A1 (en) * 2012-12-10 2016-02-05 Gerome Bermond Convertible aircraft comprising two caren rotors at the end of a wing and a horizontal fan in fuselage
CN204279944U (en) * 2014-11-22 2015-04-22 吴建伟 A kind of combined type vertically taking off and landing flyer
US20160244157A1 (en) * 2015-02-19 2016-08-25 Amazon Technologies, Inc. Vehicle configuration with motors that rotate between a lifting position and a thrusting position
CN205034337U (en) * 2015-05-25 2016-02-17 郝思阳 Distributing type vector advancing mechanism

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