CN112429222A - Single-person wing type jet backpack aircraft - Google Patents
Single-person wing type jet backpack aircraft Download PDFInfo
- Publication number
- CN112429222A CN112429222A CN202011404762.XA CN202011404762A CN112429222A CN 112429222 A CN112429222 A CN 112429222A CN 202011404762 A CN202011404762 A CN 202011404762A CN 112429222 A CN112429222 A CN 112429222A
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- China
- Prior art keywords
- aircraft
- jet
- rack
- engine
- outer sleeve
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- 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
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 15
- 238000009434 installation Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
- B64C31/02—Gliders, e.g. sailplanes
- B64C31/024—Gliders, e.g. sailplanes with auxiliary power plant
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- 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
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
- B64D33/06—Silencing exhaust or propulsion jets
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention discloses a single wing type jet backpack aircraft which comprises a rack, wings, jet engines, an oil tank, a parachute and a flight control system, wherein the wings are arranged on two sides of the top of the rack, the jet engines are arranged on two sides of the bottom of the rack, the oil tank is fixed at the tail end of the top of the rack, the parachute is positioned on the back of a pilot and is bound on the body of the pilot, the whole rack is bound on the back of the pilot through a binding band arranged at the bottom of the rack, and the flight control system is fixed on the rack and is used for controlling the starting, the stopping and the flight direction of the aircraft; the jet engine provides power, and the jet engine is provided with the oil tank to provide energy, so that the jet engine has the advantages of high speed and long endurance time; the jet orifice of the jet engine is provided with the outer sleeve type vectoring nozzle, so that the flight direction of the aircraft can be flexibly controlled.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a single-person wing type air injection backpack aircraft.
Background
The single aircraft in the prior art is various, such as a single aircraft SOLOTEK-XFV developed by Michel Moxier in America, the aircraft is driven by a piston engine to generate lift force to drive the aircraft to take off, but the aircraft has no wings, the engine drives the ducted fan to generate lift force to fly in the whole flying process, and the aircraft is slow in speed, short in flight distance and short in endurance time; there are many kinds of aircraft using jet engines as driving sources, but most of the aircraft have fixed jet directions, and the flight direction control of the aircraft is extremely inflexible.
Disclosure of Invention
The invention aims to provide a single wing type jet backpack aircraft, which aims to solve the problems in the prior art, provides energy through a jet engine, is provided with an oil tank to provide power for the jet engine, and has the advantages of high speed and long endurance time; the jet port of the jet engine is provided with a jacket type vector, so that the flexible control of the flight direction of the aircraft can be realized.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a single wing type jet backpack aircraft which comprises a rack, wings, jet engines, an oil tank, parachutes and a flight control system, wherein the wings are arranged on two sides of the top of the rack, the jet engines are arranged on two sides of the bottom of the rack, the oil tank is fixed at the tail end of the top of the rack, the parachutes are positioned on the back of a pilot and are bound on the body of the pilot, the whole rack is bound on the back of the pilot through a binding band arranged at the bottom of the rack, and the flight control system is fixed on the rack and is used for controlling the starting, the stopping and the flight direction of the aircraft;
the jet engine comprises an engine body, an outer sleeve type vectoring nozzle and a servo steering engine, wherein the outer sleeve type vectoring nozzle is sleeved at a nozzle of the engine body and is connected with the engine body in a rotating mode through a rotating shaft, the servo steering engine is arranged at the top end of the engine body and is connected with the top of the outer sleeve type vectoring nozzle in a hinged mode through a pull rod, and the servo steering engine rotates to pull the outer sleeve type vectoring nozzle through the pull rod to enable the outer sleeve type vectoring nozzle to rotate up and down with the rotating shaft as an axis.
Preferably, the rack comprises two longitudinal supports, two transverse beams and a wing fixing transverse beam, the two longitudinal supports are transversely opposite, the oil tank is fixed between the two longitudinal supports, the two transverse beams transversely penetrate through the two longitudinal supports and extend towards two sides of the two longitudinal supports, and the jet engine is fixed on two sides of the bottom of the two transverse beams; and two wing fixing cross beams are arranged on the outer side of each longitudinal support and used for fixing the wings.
Preferably, three binding bands are longitudinally distributed and penetrate through the bottoms of the two longitudinal supports.
Preferably, two rotating shafts are symmetrically arranged on two sides of a gas nozzle of the engine body, two opposite sides of the outer sleeve type vectoring nozzle are provided with rotating sleeve holes, and the rotating shafts are inserted into the opposite rotating sleeve holes.
Preferably, the top end of the outer sleeve type vectoring nozzle is provided with a connecting rib, the connecting rib is provided with a hinge hole, one end of the pull rod is hinged to the connecting rib through the hinge hole, and the other end of the pull rod is hinged to a rotating head of the servo steering engine.
Preferably, the bottom that the engine body with servo steering wheel is relative is provided with the installation clamp, the installation clamp be used for with the crossbeam is connected.
Preferably, the flight control system further comprises an operating rod and an accelerator rod, the operating rod and the accelerator rod are respectively arranged on the two longitudinal supports and are opposite to the natural position of a human hand, and the operating rod and the accelerator rod are electrically connected with the flight control system.
Compared with the prior art, the invention has the following beneficial technical effects:
the single-person wing type jet backpack aircraft provided by the invention provides power through the jet engine, is provided with the oil tank to provide power for the jet engine, and has the advantages of high speed and long endurance time; jet engine's jet orifice sets up outer sleeve type vector, and the rotating head of spray tube steering wheel passes through the pull rod to be connected with outer sleeve type vector spray tube, and then drives outer sleeve type vector spray tube luffing motion, can realize the change of engine jet-propelled 13 degrees directions, can realize aircraft flight direction's nimble control, has device simple structure, advantage with low costs.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is an overall perspective assembly view of a human body wearing state of a single-person wing type jet backpack aircraft according to the present invention;
FIG. 2 is a schematic perspective view of the frame of the present invention;
FIG. 3 is a schematic perspective view of a jet engine according to the present invention;
FIG. 4 is a schematic diagram of a forward configuration of a jet engine according to the present invention;
in the figure: the method comprises the following steps of 1-a rack, 11-a longitudinal support, 12-a cross beam, 13-a wing fixed cross beam, 2-a wing, 3-a jet engine, 31-an engine body, 32-an outer sleeve type vector nozzle, 33-a servo steering engine, 34-a pull rod, 35-a rotating shaft, 36-a connecting rib, 37-an installation clamp, 4-an oil tank and 5-a binding band.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a single-person wing type air injection backpack aircraft to solve the problems in the prior art.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
The single wing type jet backpack aircraft in the embodiment is shown in fig. 1-2 and comprises a rack 1, wings 2, jet engines 3, an oil tank 4, parachutes (not shown in the figure) and a flight control system (not shown in the figure), wherein the wings 2 are arranged on two sides of the top of the rack 1, the jet engines 3 are arranged on two sides of the bottom of the rack 1, the oil tank 4 is fixed at the tail end of the top of the rack 1, the parachutes are positioned on the back of a pilot and bound on the body of the pilot, the whole rack 1 is bound on the back of the pilot through a binding band 5 arranged at the bottom of the rack, and the flight control system is fixed on the rack 1 and used for controlling;
in the embodiment, the frame 1 comprises two longitudinal supports 11, two transverse beams 12 and two wing fixing transverse beams 13 which are transversely opposite, the oil tank 4 is fixed between the two longitudinal supports 11, the two transverse beams 12 transversely penetrate through the two longitudinal supports 11 and extend to two sides of the two longitudinal supports 11, and the jet engine 3 is fixed on two sides of the bottom of the two transverse beams 12; two wing fixing cross beams 13 are arranged on the outer side of each longitudinal support 11 and used for fixing the wings 2; three binding bands 5 are longitudinally distributed and penetrate through the bottoms of the two longitudinal supports 11, and are used for wearing the whole aircraft on a human body.
As shown in fig. 3-4, the jet engine 3 includes an engine body 31, an outer sleeve type vectoring nozzle 32 and a servo steering engine 33, the outer sleeve type vectoring nozzle 32 is sleeved at a nozzle of the engine body 31, the outer sleeve type vectoring nozzle 32 is rotatably connected with the engine body 31 through a rotating shaft 35, the servo steering engine 33 is arranged at the top end of the engine body 31, the servo steering engine 33 is hinged with the top of the outer sleeve type vectoring nozzle 32 through a pull rod 34, and the servo steering engine 33 rotates to pull the outer sleeve type vectoring nozzle 32 through the pull rod 34, so that the outer sleeve type vectoring nozzle 32 rotates up and down with the rotating shaft 35 as an axis; two rotating shafts 35 are arranged, the two rotating shafts 35 are symmetrically arranged on two sides of a gas nozzle of the engine body 31, two opposite sides of the outer sleeve type vectoring nozzle 32 are provided with rotating sleeve holes, and the rotating shafts 35 are inserted into the opposite rotating sleeve holes; a connecting rib 36 is arranged at the top end of the outer sleeve type vectoring nozzle 32, a hinge hole is formed in the connecting rib 36, one end of the pull rod 34 is hinged with the connecting rib 36 through the hinge hole, and the other end of the pull rod 34 is hinged with a rotating head of the servo steering engine 33; the bottom of the engine body 31 opposite to the servo steering engine 33 is provided with a mounting clamp 37, and the mounting clamp 37 is used for being connected with the cross beam 12.
The flight control system further comprises an operating rod and an accelerator rod (not shown in the figure), wherein the operating rod and the accelerator rod are respectively arranged on the two longitudinal supports and are opposite to natural positions of human hands, and the operating rod and the accelerator rod are electrically connected with the flight control system and are connected with each other through cables to transmit control signals.
The principle and the implementation mode of the invention are explained by applying specific examples, and the description of the above examples is only used for helping understanding the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In summary, this summary should not be construed to limit the present invention.
Claims (7)
1. The utility model provides a jet-propelled knapsack aircraft of single wing formula which characterized in that: the aircraft flight control system comprises a rack, wings, jet engines, an oil tank, parachutes and a flight control system, wherein the wings are arranged on two sides of the top of the rack, the jet engines are arranged on two sides of the bottom of the rack, the oil tank is fixed at the tail end of the top of the rack, the parachutes are located on the back of a pilot and are bound on the body of the pilot, the whole rack is bound on the back of the pilot through a binding band arranged at the bottom of the rack, and the flight control system is fixed on the rack and used for controlling the starting, the stopping and the flight direction of an aircraft;
the jet engine comprises an engine body, an outer sleeve type vectoring nozzle and a servo steering engine, wherein the outer sleeve type vectoring nozzle is sleeved at a nozzle of the engine body and is connected with the engine body in a rotating mode through a rotating shaft, the servo steering engine is arranged at the top end of the engine body and is connected with the top of the outer sleeve type vectoring nozzle in a hinged mode through a pull rod, and the servo steering engine rotates to pull the outer sleeve type vectoring nozzle through the pull rod to enable the outer sleeve type vectoring nozzle to rotate up and down with the rotating shaft as an axis.
2. The single wing jet backpack aircraft of claim 1, characterized in that: the frame comprises two longitudinal supports, a cross beam and a wing fixing cross beam, the two longitudinal supports are transversely opposite, the oil tank is fixed between the two longitudinal supports, the two cross beams transversely penetrate through the two longitudinal supports and extend towards two sides of the two longitudinal supports, and the jet engine is fixed on two sides of the bottom of the two cross beams; and two wing fixing cross beams are arranged on the outer side of each longitudinal support and used for fixing the wings.
3. The single wing jet backpack aircraft of claim 2, characterized in that: three binding bands are longitudinally distributed and penetrate through the bottoms of the two longitudinal supports.
4. The single wing jet backpack aircraft of claim 1, characterized in that: the rotating shafts are symmetrically arranged on two sides of a gas jet port of the engine body, rotating sleeve holes are formed in two opposite sides of the outer sleeve type vectoring nozzle, and the rotating shafts are inserted into the opposite rotating sleeve holes.
5. The single wing jet backpack aircraft of claim 1, characterized in that: the top end of the outer sleeve type vectoring nozzle is provided with a connecting rib, a hinge hole is formed in the connecting rib, one end of the pull rod is hinged to the connecting rib through the hinge hole, and the other end of the pull rod is hinged to a rotating head of the servo steering engine.
6. The single wing jet backpack aircraft of claim 2, characterized in that: the bottom of the engine body opposite to the servo steering engine is provided with an installation clamp, and the installation clamp is used for being connected with the cross beam.
7. The single wing jet backpack aircraft of claim 1, characterized in that: the flight control system is characterized by further comprising an operating lever and a throttle lever, wherein the operating lever and the throttle lever are respectively arranged on the two longitudinal supports and are opposite to the natural position of a human hand, and the operating lever and the throttle lever are electrically connected with the flight control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011404762.XA CN112429222A (en) | 2020-12-03 | 2020-12-03 | Single-person wing type jet backpack aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011404762.XA CN112429222A (en) | 2020-12-03 | 2020-12-03 | Single-person wing type jet backpack aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112429222A true CN112429222A (en) | 2021-03-02 |
Family
ID=74692482
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011404762.XA Pending CN112429222A (en) | 2020-12-03 | 2020-12-03 | Single-person wing type jet backpack aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112429222A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112527004A (en) * | 2020-10-22 | 2021-03-19 | 泰州镭昇光电科技有限公司 | Speed and direction integrated regulation and control system |
| CN113060274A (en) * | 2021-04-30 | 2021-07-02 | 深圳市清华动力信息技术有限公司 | Control method and system for miniature jet power aircraft |
| CN113548180A (en) * | 2021-08-04 | 2021-10-26 | 郑桂良 | Novel single aircraft |
| CN114228995A (en) * | 2022-01-06 | 2022-03-25 | 宁波大学 | Jet-propelled combined power single aircraft |
| CN114455059A (en) * | 2021-12-27 | 2022-05-10 | 浙江云途飞行器技术有限公司 | Individual soldier aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2667568A1 (en) * | 1990-10-09 | 1992-04-10 | Vintila Eugen | Individual powered flight apparatus |
| CN1203167A (en) * | 1997-06-24 | 1998-12-30 | 宫晓明 | Manned aerobat capable of landing or taking-off vertically |
| CN102991673A (en) * | 2012-12-17 | 2013-03-27 | 刘斌 | New type one-man flight vehicle capable of vertically taking off and landing and with fixed wings |
| CN104276281A (en) * | 2013-07-10 | 2015-01-14 | 赵辉 | One-man flight vehicle |
| CN206278270U (en) * | 2016-12-09 | 2017-06-27 | 河北工业大学 | A kind of VUAV vector puller system |
| CN206704545U (en) * | 2017-04-29 | 2017-12-05 | 徐曙辉 | Portable pressure spraying machine |
| CN110017219A (en) * | 2019-05-21 | 2019-07-16 | 东莞市飞翼电子科技有限公司 | A kind of ball-type vector spray |
-
2020
- 2020-12-03 CN CN202011404762.XA patent/CN112429222A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2667568A1 (en) * | 1990-10-09 | 1992-04-10 | Vintila Eugen | Individual powered flight apparatus |
| CN1203167A (en) * | 1997-06-24 | 1998-12-30 | 宫晓明 | Manned aerobat capable of landing or taking-off vertically |
| CN102991673A (en) * | 2012-12-17 | 2013-03-27 | 刘斌 | New type one-man flight vehicle capable of vertically taking off and landing and with fixed wings |
| CN104276281A (en) * | 2013-07-10 | 2015-01-14 | 赵辉 | One-man flight vehicle |
| CN206278270U (en) * | 2016-12-09 | 2017-06-27 | 河北工业大学 | A kind of VUAV vector puller system |
| CN206704545U (en) * | 2017-04-29 | 2017-12-05 | 徐曙辉 | Portable pressure spraying machine |
| CN110017219A (en) * | 2019-05-21 | 2019-07-16 | 东莞市飞翼电子科技有限公司 | A kind of ball-type vector spray |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112527004A (en) * | 2020-10-22 | 2021-03-19 | 泰州镭昇光电科技有限公司 | Speed and direction integrated regulation and control system |
| CN113060274A (en) * | 2021-04-30 | 2021-07-02 | 深圳市清华动力信息技术有限公司 | Control method and system for miniature jet power aircraft |
| CN113548180A (en) * | 2021-08-04 | 2021-10-26 | 郑桂良 | Novel single aircraft |
| CN114455059A (en) * | 2021-12-27 | 2022-05-10 | 浙江云途飞行器技术有限公司 | Individual soldier aircraft |
| CN114228995A (en) * | 2022-01-06 | 2022-03-25 | 宁波大学 | Jet-propelled combined power single aircraft |
| CN114228995B (en) * | 2022-01-06 | 2024-05-31 | 宁波大学 | Jet-type combined power single-person aircraft |
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| 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: 20210302 |