CN109018341A - It is a kind of can launch mission load land and water landing unmanned plane - Google Patents
It is a kind of can launch mission load land and water landing unmanned plane Download PDFInfo
- Publication number
- CN109018341A CN109018341A CN201811157285.4A CN201811157285A CN109018341A CN 109018341 A CN109018341 A CN 109018341A CN 201811157285 A CN201811157285 A CN 201811157285A CN 109018341 A CN109018341 A CN 109018341A
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- CN
- China
- Prior art keywords
- fuselage
- unmanned plane
- wing
- water landing
- hull
- 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
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 20
- 238000009434 installation Methods 0.000 claims abstract description 3
- 230000007613 environmental effect Effects 0.000 claims description 3
- 235000006508 Nelumbo nucifera Nutrition 0.000 claims 1
- 240000002853 Nelumbo nucifera Species 0.000 claims 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 claims 1
- 239000000295 fuel oil Substances 0.000 claims 1
- 230000035899 viability Effects 0.000 abstract description 2
- 108091092878 Microsatellite Proteins 0.000 description 3
- 230000006855 networking Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 206010004224 Belligerence Diseases 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/008—Amphibious sea planes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- 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
- B64D7/00—Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangement of rocket launchers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention belongs to field of flight vehicle design, and in particular to it is a kind of can launch mission load land and water landing unmanned plane.It is mostly fighter plane, transporter and bomber that sky, which penetrates auxiliary space to enter the carrier aircraft platform of system,.Above-mentioned aircraft is continental rise landing, however the facilities such as airport are easy to be destroyed, therefore it executes net mending and the task ability for net mending transmitting satellite of meeting an urgent need will be limited significantly.The present invention can launch mission load land and water landing unmanned plane, including fuselage, wing, empennage and engine, the fuselage is using pair binary configuration of hull formulas, fuselage top half uses airflow design, cross sectional shape is the circle or ellipse of truncation, fuselage lower half portion is the hull of aspect ratio, and cross sectional shape is double chine oblique ascension types, and hull lower disposed has first three point type retractable landing gear；The wing has the tie point of installation mission payload across fuselage and at middle part.With the advantages such as low cost, high efficiency, high motor-driven, high viability, big load, reusable.
Description
Technical field
The invention belongs to field of flight vehicle design, and in particular to it is a kind of can launch mission load land and water landing unmanned plane.
The prior art
With being constantly progressive for science and technology, the information obtaining ability of space-based detection system is significantly enhanced, and new one
For satellite development gradually present miniaturization, constellation networking, height independence trend, gradually realize globalize, real time implementation and
It is practical.For the high-intensitive transmitting trend for adapting to low cost, microsatellite networking, new demand is proposed to lift-off technology.Example
Such as, DAPPA carry out microsatellite customize small lot transmitting application model research when it is proposed that: in terms of economy, general
Moonlet launch cost is reduced to 1,000,000 or lower by 50,000,000 dollars/piece；In terms of emission effciency, it is desirable that transmitting is quasi-
Standby time from some months is reduced to several hours；In terms of emission mode, sky also need to be subdivided into using several satellite in a rocket, On-orbit release
Between station release, mother and sons' star release and it is in-orbit separation etc. multiple means.
Compared with continental rise, sea base radiation pattern, air-launched mode have can increase carrying capacity, improve range, machine
The advantages such as dynamic range is big, survival ability is strong, launching costs are low, task response is rapid.Air-launched mode is equivalent to as rocket province
Fall the first order, greatly reduce rocket cost, is very suitable for for emitting low cost, miniaturization, there is constellation networking and height
The satellite of new generation of capacity of will.
Currently, it is mostly fighter plane, transporter and bomber that sky, which penetrates auxiliary space to enter the carrier aircraft platform of system,.It is above-mentioned to fly
Machine is continental rise landing, however under belligerency, the facilities such as airport are easy to be destroyed, therefore it executes net mending and emergency is mended
The task ability of net transmitting satellite will be limited significantly.At the same time, though the flexible load-carrying of fighter plane launch angle is small, and transporter
Internal load level emission mode is mostly used with bomber, technology is complicated, and rapidity, accuracy and overall efficiency are lower.
Summary of the invention
In order to fill up the ability short slab of the air-launcheds carrier aircraft platform such as fighter plane, transporter and bomber, the present invention is proposed
Not depend on airport, distributed deployment, maneuverability, the land and water landing unmanned plane that mission payload accurate delivery can be implemented.
It is a kind of can launch mission load land and water landing unmanned plane, including fuselage, wing, empennage and engine, the machine
Body is using the binary configuration of double hull formulas, and for fuselage top half using airflow design, cross sectional shape is the round or ellipse of truncation
Round, fuselage lower half portion is the hull of aspect ratio, and cross sectional shape is double chine oblique ascension types, and hull lower disposed has front three-point
Formula retractable landing gear；The wing has the tie point of installation mission payload across fuselage and at middle part.
The mission payload is moonlet carrier rocket, is arranged in above or below wing.
The wing uses super large aspect ratio shoulder-wing configuration, supercritical airfoil, primary control surface thereon include wing flap with
And aileron.
The empennage empennage uses symmetrical airfoil, including vertical tail and tailplane, is laid out using T-shape, horizontal tail
The wing is arranged at the top of vertical fin, and rear portion sets elevator.
Engine selects more fanjets, is arranged in the body upper of binary configuration or hangs layout using tail.
It further include fuel system, hydraulic system, environmental control system, avionics system, steerable system, electrical system.
The utility model has the advantages that landing unmanned plane in land and water of the present invention can not depend on conventional land airport and mating due to having
Facility, landing point be numerous and maneuverability, load and loading space is big, implementable mission payload Mobile launch and transmitting essence
The features such as high is spent, can be cooperateed with land airplanes platforms such as active service fighter plane, transporter, bombers, for executing low cost, more
The tasks such as region, distribution, efficient aerial rapid fire moonlet.Since the design has low cost, high efficiency, high machine
The advantages such as dynamic, high viability, big load, reusable, can in 24 hours in meters altitude batch transmitting moonlet or
The micro- satellite of person, single emission cost are about 5000 dollars every kilogram, thus with good economy and wide military-civil
Application prospect.
Detailed description of the invention
Fig. 1 be the present invention can launch mission load land and water landing unmanned plane composition schematic diagram.
1- fuselage；2- wing；3- primary control surface；4- empennage；5- engine；6- mission payload
Specific embodiment
Land and water landing unmanned plane mainly by fuselage 1, wing 2, primary control surface 3, empennage 4, engine 5, modularization load cabin,
The components such as undercarriage are constituted, as shown in Figure 1.
For fuselage 1 using the binary configuration of double hull formulas, 1 top half of fuselage uses airflow design, the circle of truncation or
Ellipse section, lower half portion be hull of the aspect V-type with faulted-stage, hull lower disposed have first three point type can folding and unfolding rise and fall
Frame.To inhibit splash, hull selects double chine oblique ascension type cross sections.Since spacing is larger between two hulls, can meet the water surface makes
It is required with transverse stability, therefore does not need to arrange floating drum in wing two sides again as single hull formula water surface flying device.In addition, for
Binary configuration can be herein the moonlet carrier rocket being launched in the wing arranged beneath mission payload 6 among two hulls,
On the one hand hatch door (watertightness is difficult to realize herein) can be launched to avoid in hull bottom arrangement load in this way, it on the other hand, will
Mission payload 6 is arranged among two hulls and height is set, and the spray of splash when can maximumlly reduce water surface landing impacts task
The probability of load.
Consider that landing unmanned plane in land and water needs good aeroperformance, while relying on binary configuration fuselage to design, therefore adopt
With the wing 2 of super large aspect ratio, shoulder-wing configuration, the primary control surface 3 of main wing includes wing flap and aileron.Empennage 4 includes hanging down
Straight tail and tailplane, are laid out using T-shape, tailplane rear portion set direction rudder.Tailplane is arranged at the top of vertical fin, after
Portion sets elevator.Main wing selects supercritical airfoil, and empennage uses symmetrical airfoil.
The ability that 0.8 Mach is accelerated to meet aircraft with the short time, other than using supercritical airfoil, engine
5 consider to select more fanjets, are arranged in binary configuration body upper or hang layout using tail.
In addition, being provided with fuel system, hydraulic system, environmental control system, avionics system, steerable system, electrical system etc.
Subsystem.
Claims (6)
1. one kind can launch mission load land and water landing unmanned plane, including fuselage (1), wing (2), empennage (4) and engine
(5), it is characterised in that: the fuselage (1) is set using pair binary configuration of hull formulas, fuselage (1) top half using streamlined
Meter, cross sectional shape are the circle or ellipse of truncation, and fuselage (1) lower half portion is the hull of aspect ratio, and cross sectional shape is double
Chine oblique ascension type, hull lower disposed have first three point type retractable landing gear；The wing (2) is across fuselage (1) and at middle part
Tie point with installation mission payload (6).
2. it is according to claim 1 can launch mission load land and water landing unmanned plane, it is characterised in that: the task carries
Lotus (6) is moonlet carrier rocket (6), is arranged in above or below wing (2).
3. it is according to claim 2 can launch mission load land and water landing unmanned plane, it is characterised in that: the wing
(2) super large aspect ratio shoulder-wing configuration is used, supercritical airfoil, primary control surface (3) thereon includes wing flap and aileron.
4. it is according to claim 3 can launch mission load land and water landing unmanned plane, it is characterised in that: the empennage
(4) empennage uses symmetrical airfoil, including vertical tail and tailplane, is laid out using T-shape, tailplane is arranged in vertical fin top
Portion, rear portion set elevator.
5. it is according to claim 4 can launch mission load land and water landing unmanned plane, it is characterised in that: engine (5)
More fanjets are selected, be arranged in above the fuselage (1) of binary configuration or layout is hung using tail.
6. it is according to claim 4 can launch mission load land and water landing unmanned plane, it is characterised in that: further include fuel oil
System, hydraulic system, environmental control system, avionics system, steerable system, electrical system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811157285.4A CN109018341A (en) | 2018-09-30 | 2018-09-30 | It is a kind of can launch mission load land and water landing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811157285.4A CN109018341A (en) | 2018-09-30 | 2018-09-30 | It is a kind of can launch mission load land and water landing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109018341A true CN109018341A (en) | 2018-12-18 |
Family
ID=64615830
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811157285.4A Pending CN109018341A (en) | 2018-09-30 | 2018-09-30 | It is a kind of can launch mission load land and water landing unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109018341A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920883A (en) * | 2019-12-05 | 2020-03-27 | 中国特种飞行器研究所 | Three-stage speed-reducing water-landing seaplane |
| CN113665306A (en) * | 2021-10-25 | 2021-11-19 | 中国空气动力研究与发展中心空天技术研究所 | Cross-medium aircraft water-air dual-purpose empennage |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2120991A (en) * | 1982-05-28 | 1983-12-14 | Kjoelseth Paul | Tail structure for ground effect vehicle |
| CN2555229Y (en) * | 2002-04-30 | 2003-06-11 | 广州天象地效飞行器股份有限公司 | Ground effect aircraft having specific water dynamic distribution |
| US7874514B2 (en) * | 2006-06-05 | 2011-01-25 | Lockheed Martin Corporation | Amphibious aircraft |
| CN204473142U (en) * | 2015-01-12 | 2015-07-15 | 章伟义 | Coastal waters Three-wing-surface category-B ground effect ship |
| CN205819572U (en) * | 2016-06-14 | 2016-12-21 | 李鹏 | Unrestricted and without supporting leg the reusable sky of length penetrates carrier rocket |
| CN107972869A (en) * | 2017-11-29 | 2018-05-01 | 北京航空航天大学 | A kind of across water sky medium unmanned vehicle of variable configuration binary |
| CN108501636A (en) * | 2018-05-30 | 2018-09-07 | 佛山市神风航空科技有限公司 | A kind of amphibious aircraft |
-
2018
- 2018-09-30 CN CN201811157285.4A patent/CN109018341A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2120991A (en) * | 1982-05-28 | 1983-12-14 | Kjoelseth Paul | Tail structure for ground effect vehicle |
| CN2555229Y (en) * | 2002-04-30 | 2003-06-11 | 广州天象地效飞行器股份有限公司 | Ground effect aircraft having specific water dynamic distribution |
| US7874514B2 (en) * | 2006-06-05 | 2011-01-25 | Lockheed Martin Corporation | Amphibious aircraft |
| CN204473142U (en) * | 2015-01-12 | 2015-07-15 | 章伟义 | Coastal waters Three-wing-surface category-B ground effect ship |
| CN205819572U (en) * | 2016-06-14 | 2016-12-21 | 李鹏 | Unrestricted and without supporting leg the reusable sky of length penetrates carrier rocket |
| CN107972869A (en) * | 2017-11-29 | 2018-05-01 | 北京航空航天大学 | A kind of across water sky medium unmanned vehicle of variable configuration binary |
| CN108501636A (en) * | 2018-05-30 | 2018-09-07 | 佛山市神风航空科技有限公司 | A kind of amphibious aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920883A (en) * | 2019-12-05 | 2020-03-27 | 中国特种飞行器研究所 | Three-stage speed-reducing water-landing seaplane |
| CN113665306A (en) * | 2021-10-25 | 2021-11-19 | 中国空气动力研究与发展中心空天技术研究所 | Cross-medium aircraft water-air dual-purpose empennage |
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| 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: 20181218 |