CN205168890U - Energy -conserving aircraft of VTOL - Google Patents
Energy -conserving aircraft of VTOL Download PDFInfo
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- CN205168890U CN205168890U CN201520715006.7U CN201520715006U CN205168890U CN 205168890 U CN205168890 U CN 205168890U CN 201520715006 U CN201520715006 U CN 201520715006U CN 205168890 U CN205168890 U CN 205168890U
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Abstract
The utility model provides an energy -conserving aircraft of VTOL, the organism is connected in an organic whole with the two wings of aircraft, and the fin is connected in an organic whole with the two wings of aircraft, and the bumper bracket that rises and falls forms an organic whole with the fin, sets up at the fin tail end, forms firm organism part, and many engines distribute on the two wings of aircraft, still are equipped with energy storehouse on the organism for it can the source module to place, the composite control storehouse for installation control system, external equipment warehouse for according to aircraft mission requirements carry equipment, energy storehouse, composite control storehouse, external equipment warehouse pass through power cord and data line connection in an organic whole, and by the unified control of airborne computer in the composite control storehouse. The utility model has the beneficial effect of simple structure reliably, the carry space greatly, carry weight is big, the energy consumption low, and the VTOL performance is steady, takes off and land, hovers peacefully to fly to cruise the conversion simply reliably.
Description
Technical field
The utility model belongs to vehicle technology field, especially relates to the energy-conservation aircraft of a kind of vertical takeoff and landing.
Background technology
Manufactured and the aircraft kind that uses in current international airline field and model a lot, due to its respective application target and environment different, its version and performance characteristics are also different, this wherein, can the kind of fixed wing aircraft of vertical takeoff and landing (VTOL) also little, representing model is the U.S. " osprey ", but this model complex structure, manufacturing cost is high, and fault rate is high, find according to current technology and equipment thereof, vertical take-off and landing aircraft (VTOL aircraft) needs to research and develop further.
Utility model content
The purpose of this utility model is to provide a kind of simple and reliable for structure, and carry space is large, carry weight is large, the energy-conservation aircraft of vertical takeoff and landing.
The technical solution of the utility model is: the energy-conservation aircraft of a kind of vertical takeoff and landing, and the buffer rack that rises and falls is arranged at airplane tail group, consistent with engine thrust direction, and attitude regulation driving engine is distributed on the aircraft wing.Body is also provided with energy storehouse, for placing lithium cell or/and fuel oil; Comprehensive Control storehouse, for installation control system; Equipment compartment, for according to aircraft mission requirements carry equipment; Energy storehouse, Comprehensive Control storehouse, equipment compartment, by connection lead, be connected to one, and control by the airborne computer in Comprehensive Control storehouse is unified.Or/and chaufeur direct control controls in cockpit.
Further, power combination or single-point position aeroplane engine mechanomotive force are arranged to adopt multiple spot to arrange, be connected with multiple thrust output point, the form of multiple output point thrust can be adjusted respectively, by adjusting multiple power takeoff point power, produce different thrust, adjust aspect, realize vertical takeoff and landing, hovering.
Further, pose adjustment driving engine can use single power or multiple power, and the combination of multiple stage driving engine, multi-point is arranged
Further, utilize pose adjustment driving engine, adjustment aspect, realizes vertical takeoff and landing and hovering, and after lift-off, pose adjustment driving engine provides thrust to aircraft, or and lift-off after with double-vane or multiple wing lifting flight, reduce energy consumption.
Further, or/and sustainer, main engine is arranged in airplane tail group, multiple pose adjustment engine position is at aircraft forward, be connected to one by flexible pipe link or link span and airframe, when taking off and hover and land, multiple flexible pipe link or link span driving plurality pose adjustment driving engine stretch out or offset, adjustment aircraft balanced, when aircraft proceeds to high-speed flight, multiple flexible pipe link or link span driving plurality pose adjustment driving engine are regained or skew, reduce aircraft flight resistance.There is provided augmented thrust to aircraft simultaneously.
Further, described single power is; The power that electrical motor, piston engine, rotating combustion engine or aero-engine produce.
The advantage that the utility model has and good effect are:
1, complete machine structure is simple, housing construction is good, reliability is high, and manufacturing process is uncomplicated, low cost of manufacture.
2, the maneuverability that brings of multiple spot power combination, hoverning stability, vertical takeoff and landing stable performance, handling is remarkable.
3, aircraft components is few, lightweight, and dopey can also adopt double-vane or multiple wing design, and airplane ascensional force is large, energy-conservation, and the cruise time of leaving a blank is longer.
4, body has larger load space, can carry more equipment, is convenient to aircraft and performs various task.
5, can someone drive also can driverless operation, control system is simple and reliable, and maintenance cost is low, also directly can use the ripe control system of existing aircraft.
6, also can according to aircraft mission requirements, use variety classes driving engine (electrical motor, piston engine, rotating combustion engine, various aeroplane engine or other can produce the driving engine of thrust), combination carries out multi-point power arrangement.
Accompanying drawing explanation
Fig. 1 is the birds-eye view of embodiment 1.
Fig. 2 is the front elevation of embodiment 1.
Fig. 3 is the birds-eye view of embodiment 2.
Fig. 4 is the front elevation of embodiment 2.
Fig. 5 is the birds-eye view of embodiment 3.
Fig. 6 is the front elevation of embodiment 3.
Fig. 7 is the flexible pipe link of embodiment 4 or the structural representation of frame stretching, extension.
Fig. 8 is the flexible pipe link of embodiment 4 or the structural representation of frame withdrawal.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is elaborated.
embodiment 1
As shown in Figure 1-2, the energy-conservation aircraft of a kind of vertical takeoff and landing of the present utility model, body and aircraft double-vane 5, 6 are connected to one, empennage 3-1, 3-2 and aircraft double-vane are connected to one, rise and fall buffer rack 4-1, 4-2, 4-3, 4-4 and empennage form one, at empennage tail end, form firm body part, attitude regulation driving engine 2-1, 2-2, 2-3, 2-4 is distributed on aircraft double-vane, attitude regulation driving engine is provided with screw propeller 1-1, 1-2, 1-3, 1-4, energy storehouse 9 placing battery energy block, various control system (airborne computer is installed in Comprehensive Control storehouse 10, flight control modules, image transmission module, GPS module, obstacle sensing apparatus control etc.), plug-in device storehouse 7, 11, 12 can according to the various equipment of aircraft mission requirements carry.
Energy storehouse 9, Comprehensive Control storehouse 10, plug-in device storehouse 7,11,12, be connected to one by power lead and data line, and control by the airborne computer in Comprehensive Control storehouse 10 is unified.
Aircraft is assigned instruction by remote controller to the airborne computer in Comprehensive Control storehouse 10 by ground handling operator or is performed aerial mission by airborne computer by predetermined program design, or performs aerial mission by chaufeur direct control.
Take off: in Comprehensive Control storehouse 10 computing machine accept or after independently assigning instruction, energy storehouse 9 powers, and is controlled by flying in Comprehensive Control storehouse 10, and energy storehouse 9 powers to motor 2-1,2-2,2-3,2-4, carrying screws 1-1,1-2,1-3,1-4, aircraft vertical steadily takes off.
Cruising flight: after computing machine accepts or independently assigns adjustment flight attitude order in energy storehouse 9, by flying control, control energy storehouse 9 to powering with motor 2-1,2-2,2-3,2-4, diverse location driven by motor screw propeller produces different lift, change aspect, aircraft revert to level flight cruises, aircraft double-vane produces lift, and motor power consumption reduces, and aircraft enters low energy consumption state of flight.
Hovering: after Comprehensive Control storehouse 10 computing machine accepts or independently assigns adjustment flight attitude order, by flying control, control energy storehouse 9 to powering with motor 2-1,2-2,2-3,2-4, diverse location driven by motor screw propeller 1-1,1-2,1-3,1-4 produce different lift, change aspect, the lift that aircraft produces by 4 screw propellers, steadily hovers.
Gesture stability in-flight: after airborne computer accepts or independently assigns adjustment flight attitude order in Comprehensive Control storehouse 10, by flying control, control energy storehouse 9 to providing different supply currents from motor 2-1,2-2,2-3,2-4, diverse location driven by motor screw propeller 1-1,1-2,1-3,1-4 produce different thrust, change the flight attitude of aircraft very flexibly.
Pinpoint landing; After in Comprehensive Control storehouse 10, computing machine accepts or independently assigns adjustment flight attitude order, by flying control, control energy storehouse 9 to providing different supply currents from motor 2-1,2-2,2-3,2-4, diverse location driven by motor screw propeller 1-1,1-2,1-3,1-4 produce different thrust, change aspect, aircraft steadily hovers, and slowly declines, and arrives predetermined level point.
To airborne computer programming, aircraft independently can complete aerial mission according to fixed route and position, and flight also can adjust aerial mission in way at any time, again flight directive data is sent to airborne computer.
embodiment 2
As shown in Figure 3-4, the energy-conservation aircraft of a kind of vertical takeoff and landing of the present utility model, body and aircraft double-vane 5, 6 are connected to one, empennage 3-1, 3-2 and aircraft double-vane 5, 6 are connected to one, rise and fall buffer rack 4-1, 4-2, 4-3, 4-4 and empennage 3-1, 3-2 forms one, be arranged on empennage tail end, form firm body part, fuel engines is established in power bin 11, main screw 8 is driven to be arranged on head, control motor 2-1, 1-2, 2-3, 2-4 is distributed on aircraft double-vane, on 1-1 is installed, 1-2, 1-3, 1-4 gesture stability screw propeller, Oil Fuel Tank 13 places aircraft fuel oil, the battery compartment 12 placing battery energy, various control system (airborne computer is placed in Comprehensive Control storehouse 10, fly to control module, figure transmission module, GPS module etc.), plug-in device storehouse 7, 9 can according to the various equipment of aircraft mission requirements carry, aircraft double-vane 5, also store mounting point can be increased according to demand on 6.
Comprehensive Control storehouse 10, power bin 11, battery compartment 12, Oil Fuel Tank 13, plug-in device storehouse 7,9, by power lead, data line and fuel feed pipe, be connected to one by demand respectively, and control by airborne computer in Comprehensive Control storehouse 10 is unified.
Aircraft is assigned instruction by remote controller to airborne computer in Comprehensive Control storehouse 10 by ground handling operator or is performed aerial mission by airborne computer by predetermined program design.
Take off: in Comprehensive Control storehouse 10 computing machine accept or after independently assigning instruction, by flying control, control battery compartment 12 to power to motor 2-1,1-2,2-3,2-4, carrying screws 1-1,1-2,1-3,1-4, produce lift control aspect, in power bin 11, fuel engines starts simultaneously, drives main screw 8, and controlling power bin 11 Power output by Comprehensive Control storehouse 10 internal controller, aircraft vertical steadily takes off.
Cruising flight, after Comprehensive Control storehouse 10 computing machine accepts or independently assigns the order of adjustment flight attitude, by flying control, control battery compartment 12 and supply motor 2-1, 1-2, 2-3, the different supply current of 2-4, diverse location driven by motor screw propeller 1-1, 1-2, 1-3, 1-4 produces different lift, change aspect, aircraft is adjusted to put down and is flown state, aircraft double-vane 5, 6 start to produce lift, motor power consumption reduces, fuel engines reduces fuel oil consumption, aircraft enters low energy consumption state of flight, Comprehensive Control storehouse 10 internal controller assigns charging instruction, electrical motor changes electrical generator into battery compartment 12 batteries charging.
Hovering; After in the computing machine of Comprehensive Control storehouse 10, computing machine accepts or independently assigns adjustment flight attitude order, by flying control, control battery compartment 12 and supply the different supply current of motor 2-1,1-2,2-3,2-4, diverse location driven by motor screw propeller 1-1,1-2,1-3,1-4 produce different lift, change aspect, aircraft controls attitude by 4 gesture stability screw propellers, and the main lift driving main screw 8 to produce by fuel engines in power bin 11, steadily hovers.
Gesture stability in-flight: after computing machine accepts or independently assigns adjustment flight attitude order in Comprehensive Control storehouse 10, by flying control, control battery compartment 12 to supply current different from motor 2-1,1-2,2-3,2-4, diverse location driven by motor gesture stability screw propeller 1-1,1-2,1-3,1-4 produce different lift, change aspect, aircraft controls attitude by 4 gesture stability screw propellers, coordinate the active force controlling fuel engines in power bin 11 and drive main screw 8 to produce, change the flight attitude of aircraft very flexibly.
Pinpoint landing; After in Comprehensive Control storehouse 10, computing machine accepts or independently assigns adjustment flight attitude order, by flying control, control battery compartment 12 and supply the different supply current of motor 2-1,1-2,2-3,2-4, diverse location driven by motor gesture stability screw propeller 1-1,1-2,1-3,1-4 produce different lift, change aspect, aircraft controls attitude by 4 gesture stability screw propellers, the main lift driving main screw 8 to produce by fuel engines in power bin 11, steady hovering also progressively declines, and arrives predetermined level point.
embodiment 3
As seen in figs. 5-6, embodiment 3 is consistent with the aircraft steer mode of embodiment 2, and difference is, by rearmounted for power bin 11, to be used for installing miscellaneous equipment by Handpiece Location.
embodiment 4
As Figure 7-8, the technical solution of the utility model also can use on high-speed aircraft.
Airframe 1 and tail undercarriage 6 are connected to one, and pose adjustment driving engine 2-1,3-1 are arranged in aircraft forward and are connected to one by flexible pipe link or frame 5 with body 1, and sustainer, main engine 4 is arranged in airplane tail group.
When taking off and hover and land, sustainer, main engine 4 provides main thrust, flexible pipe link or frame 5 stretch out or offset, and pose adjustment driving engine 2-1,3-1 provide augmented thrust, and by the different engine power of adjustment, adjustment aspect keeps aircraft balanced, complete and take off and hover and landing task, when aircraft proceeds to high-speed flight, flexible pipe link or frame 5 are regained or are offset, pose adjustment driving engine 2-2,3-2 near aircraft, reduction aircraft flight resistance, and provide augmented thrust to aircraft.
Above an embodiment of the present utility model has been described in detail, but described content being only preferred embodiment of the present utility model, can not being considered to for limiting practical range of the present utility model.All equalizations done according to the utility model application range change and improve, and all should still belong within patent covering scope of the present utility model.
Claims (5)
1. the energy-conservation aircraft of vertical takeoff and landing, it is characterized in that: the buffer rack that rises and falls is arranged at airplane tail group, consistent with engine thrust direction, multiple stage attitude regulation driving engine is distributed on the aircraft wing or body, body is also provided with energy storehouse, for placing lithium cell or/and fuel oil; Comprehensive Control storehouse, for installation control system; Equipment compartment, for according to aircraft mission requirements loading facilities; Energy storehouse, Comprehensive Control storehouse, equipment compartment, by connection lead, be connected to one, and control by the airborne computer in Comprehensive Control storehouse is unified, or/and chaufeur direct control controls in cockpit.
2. the energy-conservation aircraft of a kind of vertical takeoff and landing according to claim 1, it is characterized in that: adopt multiple spot to arrange power combination, or single-point position power is arranged, is connected with multiple thrust output point, the form of multiple output point thrust can be adjusted respectively, by adjusting multiple power takeoff point power, produce different thrust, adjust aspect, realize vertical takeoff and landing, hovering.
3. the energy-conservation aircraft of a kind of vertical takeoff and landing according to claim 1, is characterized in that: driving engine can use single power or the combination of multiple different dynamic, and the combination of multiple stage driving engine is arranged.
4. the energy-conservation aircraft of a kind of vertical takeoff and landing according to claim 1, it is characterized in that: utilize adjustment multiple stage engine output power, adjustment aspect, realizes vertical takeoff and landing and hovering, or and lift-off after with double-vane or multiple wing lifting flight, reduce energy consumption.
5. the energy-conservation aircraft of a kind of vertical takeoff and landing according to claim 1, it is characterized in that: or and sustainer, main engine be arranged in airplane tail group, multiple stage pose adjustment engine position is at aircraft forward, one is connected to by flexible pipe link or link span and airframe, take off, when landing and hovering, multiple flexible pipe link or link span driving plurality pose adjustment driving engine stretch out or offset, adjustment aircraft balanced, complete landing and hovering task, when aircraft proceeds to high-speed flight, multiple flexible pipe link or link span driving plurality pose adjustment driving engine are regained or skew, reduce aircraft flight resistance, there is provided augmented thrust to aircraft simultaneously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520715006.7U CN205168890U (en) | 2015-09-14 | 2015-09-14 | Energy -conserving aircraft of VTOL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520715006.7U CN205168890U (en) | 2015-09-14 | 2015-09-14 | Energy -conserving aircraft of VTOL |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205168890U true CN205168890U (en) | 2016-04-20 |
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ID=55732907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520715006.7U Expired - Fee Related CN205168890U (en) | 2015-09-14 | 2015-09-14 | Energy -conserving aircraft of VTOL |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205168890U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112693607A (en) * | 2021-01-14 | 2021-04-23 | 湖南翰坤实业有限公司 | Posture adjusting device and air-sea amphibious unmanned combat equipment |
| US11618565B2 (en) | 2017-12-20 | 2023-04-04 | Wing Aviation Llc | Methods and systems for self-deployment of operational infrastructure by an unmanned aerial vehicle (UAV) |
-
2015
- 2015-09-14 CN CN201520715006.7U patent/CN205168890U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11618565B2 (en) | 2017-12-20 | 2023-04-04 | Wing Aviation Llc | Methods and systems for self-deployment of operational infrastructure by an unmanned aerial vehicle (UAV) |
| CN112693607A (en) * | 2021-01-14 | 2021-04-23 | 湖南翰坤实业有限公司 | Posture adjusting device and air-sea amphibious unmanned combat equipment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160420 Termination date: 20160914 |