CN205971845U - Backpack fixed wing aircraft vertical take -off auxiliary system - Google Patents
Backpack fixed wing aircraft vertical take -off auxiliary system Download PDFInfo
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- CN205971845U CN205971845U CN201620774884.0U CN201620774884U CN205971845U CN 205971845 U CN205971845 U CN 205971845U CN 201620774884 U CN201620774884 U CN 201620774884U CN 205971845 U CN205971845 U CN 205971845U
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- wing airvehicle
- rotor craft
- locking device
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Abstract
The utility model provides a backpack fixed wing aircraft vertical take -off auxiliary system, including multiaxis rotor craft and fixed wing aircraft, the fuselage top of multiaxis rotor craft has a transmission platform, is equipped with a plurality of slides of undercarriage pulley assorted with fixed wing aircraft on the transmission platform, be equipped with at least one portable locking device on the slide, this portable locking device fixes fixed wing aircraft on the transmission platform through locking undercarriage pulley, fixed wing aircraft flight to predetermined speed and/or high back are born to the multiaxis rotor craft, and portable locking device relieves the locking to the undercarriage pulley, make fixed wing aircraft break away from the multiaxis rotor craft along the slide and fly alone. In this way, the utility model discloses can be under the condition that does not need the current fixed wing aircraft of more change, realization fixed wing aircraft's vertical take -off.
Description
Technical field
This utility model is related to unmanned air vehicle technique field, and more particularly to a kind of backpack Fixed Wing AirVehicle takes off vertically
Aid system.
Background technology
When Fixed Wing AirVehicle is using its rapid flight, the pressure differential that wing upper and lower surface produces obtaining lift, gram
Take gravity and take off, must reach takeoff speed when therefore it takes off could go up to the air.Fixed Wing AirVehicle voyage is remote, speed fast,
Oil consumption is low, once the also certain chance that runs out of steam reduces decrease speed by gliding and reduces air crash loss.But, fixed-wing flies
Device has the drawback that：Need the runway grown just can take off very.
Then, people begin one's study the takeoff auxiliary device of Fixed Wing AirVehicle.For example, can gently turn double side by side using left and right
The V-22 tiltrotor of rotor technology, slightly installs two rotors turning 90 degrees that can incline by the wing in main wing and provides and take off
When lift and control moment, in flat flying, gradually oar disk upward is tilted forward, produces pulling force forward so that aircraft
Accelerate, after reaching certain speed, main wing can produce enough lift, this be lift oar disk forward, traction is provided
Power, promotes aircraft to advance, empennage provides control moment, keeps aircraft balanced and manipulation.The shortcoming of this mode：1) take off vertically
When, wing remains in that level, and some area of oar disk is overlapping with wing so that oar disk lift is cancelled a part, reduces
The efficiency of oar, increases power consumption；2) electromotor and dynamical system are arranged on the wing wing slightly, define a taper load and weight
Measure very big cantilever beam structure so that structure is very easy to shake, vibrations to be reduced, it is necessary for enhancing structure, thus
Construction weight can be greatly increased, limit the aspect ratio of main wing simultaneously；3) main wing pneumatic efficiency, that is, lift-drag ratio is relatively low.Due to
The restriction of layout type, the main wing aspect ratio of this scheme is all smaller, and it is less also to allow for whole machine lift-drag ratio, so can increase
Oil consumption, reduces voyage, although so this kind of flight is bigger than helicopter, but fly much smaller than the normal arrangement of same level
Machine；4) this kind of aircraft using slide take off mode when, because blade is oversize, propeller cannot be fully seated to horizontal level, this
Sample can limit the maximum take-off weight under its sliding race mode；5) this aircraft is when using short distance rolling start, if takeoff speed is too
Low, enough steerages may cannot be provided cannot to take off because of empennage, so constrain it and adopt the minimum under short takeoff pattern
Distance of taking off and flying speed.
Utility model content
This utility model auxiliary mainly solving the technical problems that a kind of backpack Fixed Wing AirVehicle of offer takes off vertically
System, can realize taking off vertically of Fixed Wing AirVehicle in the case of not needing the existing Fixed Wing AirVehicle of more change.
For solving above-mentioned technical problem, the technical scheme that this utility model adopts is：A kind of backpack is provided to fix
Rotor aircraft takes off vertically aid system, including multiaxis rotor craft and Fixed Wing AirVehicle；
The fuselage roof of described multiaxis rotor craft has a flat pad, and described flat pad is provided with solid with described
If the dry slide that the undercarriage pulley determining rotor aircraft matches；
Described slideway is provided with least one removable locking device, and described removable locking device passes through to lock undercarriage
Described Fixed Wing AirVehicle is fixed on flat pad pulley；
Described multiaxis rotor craft bear described Fixed Wing AirVehicle fly to default speed and/or highly after, institute
State the locking to undercarriage pulley for the removable locking device releasing, make Fixed Wing AirVehicle depart from multiaxis rotor craft along slideway
Fly alone.
Wherein, described Fixed Wing AirVehicle is the Fixed Wing AirVehicle with tricycle landing gear；Set on described slideway
There are two removable locking devices, be respectively used to lock the pulley of Fixed Wing AirVehicle two undercarriages rearward.
Preferably, it is provided with a right angle divider in forward with the Fixed Wing AirVehicle corresponding slideway of undercarriage pulley, described
Right angle divider includes the first right angle side guard and the second right angle side guard, and described first right angle side guard is horizontally placed at described slideway
In；Described first right angle side guard is connected with the front end of described flat pad by a stretchable elastomeric element, fixed-wing simultaneously
The forward undercarriage pulley of aircraft is located in right angle divider so that described stretchable elastomeric element is in extended state；Described
When Fixed Wing AirVehicle departs from described multiaxis rotor craft, described stretchable elastomeric element passes through right angle gear described in brought forward
Frame provides motive force forward for described Fixed Wing AirVehicle.
Wherein, described stretchable elastomeric element includes extension spring and elastic drag rope.
Wherein, the propeller of multiaxis rotor craft when bearing and the wing of Fixed Wing AirVehicle and fuselage are not all handed over
Folded, and the propeller of multiaxis rotor craft is less than the horizontal level of the wing of Fixed Wing AirVehicle.
Wherein, described multiaxis rotor craft includes three axle rotor crafts, four axle rotor crafts, six axle rotor flyings
Device and eight axle rotor crafts.
Preferably, the front of described removable locking device has opening breach forward, described removable locking dress
Put including steering wheel and latch, the output shaft of described steering wheel is hinged with one end of described latch by a connecting piece, described latch
The other end passes through described breach, and described undercarriage pulley is located in the space that described breach is surrounded with described latch.
Preferably, described slideway is provided with some screws, and described removable locking device passes through nut, bolt and slideway
On screw be connected with described flat pad.
It is different from the situation of prior art, the beneficial effects of the utility model are：
1) Fixed Wing AirVehicle can take off vertically；
2) undercarriage that the undercarriage on fixed wing airplane can be more traditional is simplified, and is primarily only to complete flexible and slide
Function；
3) taken off using aerial input pattern, be launched the power required for aircraft and need only to meet cruising flight and be
Can improve when aircraft voyage, boat and efficiency so that its power demand reduces, thus reducing system weight；
4) high-altitude throw in take off, there is larger potential energy, can improve further aircraft voyage boat when；
5) maximum take-off weight of Fixed Wing AirVehicle can be improved.
Brief description
Fig. 1 is that a kind of this utility model embodiment backpack Fixed Wing AirVehicle takes off vertically the schematic diagram of aid system；
Fig. 2 is the schematic diagram of the right angle divider of this utility model embodiment；
Fig. 3 is the schematic diagram of the slideway of this utility model embodiment；
Fig. 4 is the schematic diagram of the removable locking device of this utility model embodiment.
Specific embodiment
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely description is it is clear that described embodiment is only a part of embodiment of the present utility model rather than whole
Embodiment.Based on the embodiment in this utility model, those of ordinary skill in the art are not under the premise of making creative work
The every other embodiment being obtained, broadly falls into the scope of this utility model protection.
With reference to Fig. 1, a kind of backpack Fixed Wing AirVehicle takes off vertically aid system, including machine tool multiaxis rotor craft
1 and handset Fixed Wing AirVehicle 2；The fuselage roof of multiaxis rotor craft has a flat pad 10, and flat pad 10 sets
If there being the dry slide 11 that the undercarriage pulley 20 with Fixed Wing AirVehicle 2 matches；Slideway 11 is provided with least one and may move
Locking device (not shown), removable locking device passes through locking undercarriage pulley 20, and described Fixed Wing AirVehicle 2 is fixing
On flat pad 10；Multiaxis rotor craft 1 bear Fixed Wing AirVehicle 2 fly to default speed and/or highly after, on
State the locking to undercarriage pulley 20 for the removable locking device releasing, make Fixed Wing AirVehicle 2 depart from multiaxis rotor along slideway 11
Aircraft 1 flies alone.
Further, above-mentioned Fixed Wing AirVehicle 2 is the Fixed Wing AirVehicle with tricycle landing gear, with front three-point
It is respectively equipped with removable locking device on the corresponding slideway of two undercarriage pulleys after in formula undercarriage, solid for locking
Determine the pulley of rotor aircraft undercarriage rearward.
Further, as shown in Fig. 2 the undercarriage pulley corresponding slideway forward with the position in tricycle landing gear
In be provided with a right angle divider 4, right angle divider 4 includes the first right angle side guard 40 and the second right angle side guard 41, the first right-angle side
Baffle plate 40 is horizontally placed in the forward slideway residing for undercarriage pulley in above-mentioned position；First right angle side guard 40 can draw by one
The front end stretching elastomeric element 5 with flat pad 10 is connected, and the forward undercarriage pulley of Fixed Wing AirVehicle is located at right angle and keeps off simultaneously
So that stretchable elastomeric element 5 is in extended state in frame 4；When Fixed Wing AirVehicle 2 departs from multiaxis rotor craft 1, can
Elongated elastomeric member 5 is provided forward for Fixed Wing AirVehicle 2 by brought forward right angle divider 4 during recovering deformation
Motive force.
Specifically, stretchable elastomeric element 5 can be extension spring, or elastic drag rope such as rubber band bar.
Preferably, as shown in figure 4, above-mentioned removable locking device has opening breach 30 forward, may move locking
Device also includes steering wheel 31 and latch 34, and the output shaft 32 of steering wheel is hinged with one end of latch by a connecting piece 33, latch
The other end passes through opening breach forward, and undercarriage pulley is located in the space that breach is surrounded with latch.When handset born by machine tool
Fly to enough height and/or speed, by the motion of servos control latch, make breach and space that latch is surrounded from
The side of latch is opened, and the undercarriage pulley of handset skids off forward from the breach opened, thus handset can skid off slideway and take off
Fly alone from machine tool.
Preferably, slideway 11 is respectively provided on two sides with strip through hole, as shown in Figure 3；Can open on removable locking device
If 2～4 screws, removable locking device is made to be connected with slideway 11 by nut, bolt, screw and strip through hole.Tool
Body, can be according to the size of machine tool multiaxis rotor craft and handset Fixed Wing AirVehicle and species, will be removable along slideway
Dynamic locking device movement, to suitable position, then makes removable locking by nut, bolt, screw and strip through hole again
Device is connected with slideway.
Wherein, the propeller of multiaxis rotor craft 1 when bearing and the wing of Fixed Wing AirVehicle 2 and fuselage are not all handed over
Folded, and the propeller of multiaxis rotor craft 1 is less than the level height of the wing of Fixed Wing AirVehicle 2.
Specifically, multiaxis rotor craft 1 includes three axle rotor crafts, four axle rotor crafts, six axle rotor flyings
Device and eight axle rotor crafts, Fig. 1 show based on embodiment during four axle rotor crafts.
By the way, the backpack Fixed Wing AirVehicle of this utility model embodiment aid system that takes off vertically makes
Fixed wing airplane can be realized taking off vertically, and can simplify the undercarriage of fixed-wing so that main screw lift reduces；In addition,
After such as 50～3000 meters aerial inputs of certain height, aircraft need not expend the energy of take-off climb.Therefore, this utility model
The construction weight that fuel oil can effectively reduce fixed wing airplane simultaneously being saved, reducing power demand, thus effectively improving it
When voyage and boat.
The foregoing is only embodiment of the present utility model, not thereby limit the scope of the claims of the present utility model, every
The equivalent structure made using this utility model description and accompanying drawing content or equivalent flow conversion, or be directly or indirectly used in
Other related technical fields, are all included in the same manner in scope of patent protection of the present utility model.
Claims (8)
1. a kind of backpack Fixed Wing AirVehicle take off vertically aid system it is characterised in that include multiaxis rotor craft and
Fixed Wing AirVehicle；
The fuselage roof of described multiaxis rotor craft has a flat pad, and described flat pad is provided with and described fixed-wing
If the dry slide that the undercarriage pulley of aircraft matches；
Described slideway is provided with least one removable locking device, and described removable locking device passes through to lock undercarriage pulley
Described Fixed Wing AirVehicle is fixed on flat pad；
Described multiaxis rotor craft bear described Fixed Wing AirVehicle fly to default speed and/or highly after, described can
Moving locking device releases the locking to undercarriage pulley, makes Fixed Wing AirVehicle depart from multiaxis rotor craft alone along slideway
Flight.
2. backpack Fixed Wing AirVehicle according to claim 1 takes off vertically aid system it is characterised in that described solid
Determining rotor aircraft is the Fixed Wing AirVehicle with tricycle landing gear；Described slideway is provided with two removable locking dresses
Put, be respectively used to lock the pulley of Fixed Wing AirVehicle two undercarriages rearward.
3. backpack Fixed Wing AirVehicle according to claim 2 take off vertically aid system it is characterised in that with fixation
It is provided with a right angle divider, described right angle divider includes the first right-angle side in the forward corresponding slideway of undercarriage pulley of rotor aircraft
Baffle plate and the second right angle side guard, described first right angle side guard is horizontally placed in described slideway；
Described first right angle side guard is connected with the front end of described flat pad by a stretchable elastomeric element, fixed-wing simultaneously
The forward undercarriage pulley of aircraft is located in right angle divider so that described stretchable elastomeric element is in extended state；
When described Fixed Wing AirVehicle departs from described multiaxis rotor craft, described stretchable elastomeric element passes through brought forward institute
State right angle divider motive force for the offer of described Fixed Wing AirVehicle forward.
4. taken off vertically aid system according to the arbitrary described backpack Fixed Wing AirVehicle of claims 1 to 3, its feature exists
In the propeller of multiaxis rotor craft when bearing and the wing of Fixed Wing AirVehicle and fuselage all do not overlap, and multiaxis
The propeller of rotor craft is less than the horizontal level of the wing of Fixed Wing AirVehicle.
5. aid system is taken off vertically it is characterised in that described according to the arbitrary described Fixed Wing AirVehicle of claims 1 to 3
Multiaxis rotor craft includes three axle rotor crafts, four axle rotor crafts, six axle rotor crafts and eight axle rotors and flies
Row device.
6. backpack Fixed Wing AirVehicle according to claim 3 takes off vertically aid system it is characterised in that described can
Elongated elastomeric member includes extension spring and elastic drag rope.
7. taken off vertically aid system according to the arbitrary described backpack Fixed Wing AirVehicle of claims 1 to 3, its feature exists
In described removable locking device has opening breach forward, and described removable locking device includes steering wheel and latch, institute
The output shaft stating steering wheel is hinged with one end of described latch by a connecting piece, and the other end of described latch passes through described breach,
Described undercarriage pulley is located in the space that described breach is surrounded with described latch.
8. backpack Fixed Wing AirVehicle according to claim 7 takes off vertically aid system it is characterised in that described
The slideway penetrating platform is provided with some screws, described removable locking device pass through nut, the screw on bolt and slideway with
Described flat pad connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620774884.0U CN205971845U (en) | 2016-07-22 | 2016-07-22 | Backpack fixed wing aircraft vertical take -off auxiliary system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620774884.0U CN205971845U (en) | 2016-07-22 | 2016-07-22 | Backpack fixed wing aircraft vertical take -off auxiliary system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205971845U true CN205971845U (en) | 2017-02-22 |
Family
ID=58026162
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620774884.0U Active CN205971845U (en) | 2016-07-22 | 2016-07-22 | Backpack fixed wing aircraft vertical take -off auxiliary system |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043689A (en) * | 2016-07-22 | 2016-10-26 | 绵阳空天科技有限公司 | Vertical take-off auxiliary system for top-mounted fixed-wing aircraft |
| CN106882386A (en) * | 2017-03-10 | 2017-06-23 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
| CN106892118A (en) * | 2017-03-10 | 2017-06-27 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
| CN106904281A (en) * | 2017-03-10 | 2017-06-30 | 佛山市神风航空科技有限公司 | One kind combination aircraft and its landing mode |
| CN106915445A (en) * | 2017-03-10 | 2017-07-04 | 佛山市神风航空科技有限公司 | One kind combination aircraft and its mode of taking off |
| CN107291094A (en) * | 2017-05-08 | 2017-10-24 | 大陆智源科技（北京）有限公司 | Unmanned plane robot cooperating system |
| CN110182008A (en) * | 2019-05-31 | 2019-08-30 | 北京无线电测量研究所 | A kind of variable unmanned motor platform of appearance of two-stage type |
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2016
- 2016-07-22 CN CN201620774884.0U patent/CN205971845U/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043689A (en) * | 2016-07-22 | 2016-10-26 | 绵阳空天科技有限公司 | Vertical take-off auxiliary system for top-mounted fixed-wing aircraft |
| CN106043689B (en) * | 2016-07-22 | 2019-08-27 | 绵阳空天科技有限公司 | Backpack Fixed Wing AirVehicle takes off vertically auxiliary system |
| CN106882386A (en) * | 2017-03-10 | 2017-06-23 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
| CN106892118A (en) * | 2017-03-10 | 2017-06-27 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
| CN106904281A (en) * | 2017-03-10 | 2017-06-30 | 佛山市神风航空科技有限公司 | One kind combination aircraft and its landing mode |
| CN106915445A (en) * | 2017-03-10 | 2017-07-04 | 佛山市神风航空科技有限公司 | One kind combination aircraft and its mode of taking off |
| CN106904281B (en) * | 2017-03-10 | 2019-06-21 | 新疆博新智航航空科技有限责任公司 | A kind of combination aircraft and its landing mode |
| CN106882386B (en) * | 2017-03-10 | 2019-09-27 | 江苏天一机场专用设备股份有限公司 | A kind of the landing mode and its device of aircraft |
| CN107291094A (en) * | 2017-05-08 | 2017-10-24 | 大陆智源科技（北京）有限公司 | Unmanned plane robot cooperating system |
| CN107390710A (en) * | 2017-05-08 | 2017-11-24 | 大陆智源科技（北京）有限公司 | Unmanned plane recovery system |
| CN110182008A (en) * | 2019-05-31 | 2019-08-30 | 北京无线电测量研究所 | A kind of variable unmanned motor platform of appearance of two-stage type |
| CN110182008B (en) * | 2019-05-31 | 2020-12-22 | 北京无线电测量研究所 | Two-stage type posture-variable unmanned mobile platform |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190110 Address after: 710000 8-storey G-room of Weiye Metropolitan Prospect in the East Section of South Second Ring Road, Yanta District, Xi'an City, Shaanxi Province Patentee after: Xi'an Yifei Mingda Aviation Technology Co., Ltd. Address before: 621050 Room 324, Center Incubator D, Kechuang District, Mianyang City, Sichuan Province Patentee before: MIANYANG KONGTIAN TECHNOLOGY CO., LTD. |