WO2012119468A1 - 一种用于飞行器的超高压流体喷射动力变轨系统及方法 - Google Patents
一种用于飞行器的超高压流体喷射动力变轨系统及方法 Download PDFInfo
- Publication number
- WO2012119468A1 WO2012119468A1 PCT/CN2011/083309 CN2011083309W WO2012119468A1 WO 2012119468 A1 WO2012119468 A1 WO 2012119468A1 CN 2011083309 W CN2011083309 W CN 2011083309W WO 2012119468 A1 WO2012119468 A1 WO 2012119468A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- aircraft
- nozzle
- combined
- nozzles
- wing
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/14—Attitude, flight direction, or altitude control by jet reaction the jets being other than main propulsion jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/38—Jet flaps
Definitions
- the present invention relates to the field of aerospace vehicles, and more particularly to an ultrahigh pressure fluid jet power rail system and method for an aircraft.
- the aerodynamic shape of an aircraft will determine its aerodynamic characteristics under given gas flow conditions. Now the shape of space shuttles, space planes, and aerospace aircraft have inherent design flaws that cause them to need more auxiliary equipment. The device is equipped with it, so the design becomes more and more complicated, more and more difficult to operate, and more and more heavy, making the aircraft more and more energy-consuming, and there are a series of defects.
- the shape design of the space shuttle is a big astronomical failure. Its shape is basically like a cigar-shaped metal rod. This aerodynamic shape can't help with the lifting force of air in flight. The space shuttle took off, so it can only be lifted off with the help of a large thrust rocket. This is because it requires huge energy to be consumed by it. This method is not enough for the aerospace industry and will be eliminated in the future.
- the sky plane also mimics the shape of the space shuttle.
- the take-off mode is similar to that of the space shuttle. It is only sent to the air by a large aircraft, and then the rocket engine is carried out to fly out of the atmosphere. The ills are also fully reflected in it, and will be eliminated in the future.
- the take-off of the aircraft is mainly achieved by the force generated by the two wings and the air. Since the contact surface of the aircraft wing and the air is very limited, only the method of increasing the engine power can be used to make the aircraft start. The speed is increased to make up for the lack of aircraft lift capacity. This is the inherent deficiency of the aircraft's shape design, and the defects of the shape design, resulting in extra huge energy loss.
- the object of the present invention is to overcome the deficiencies of the prior art and to provide an ultra-throated fluid jet power rail system (hereinafter referred to as an "orbital system”) and method for an aircraft.
- an orbiting system for an aircraft including a gas pipeline, a nozzle, and a central automatic control system, characterized in that the rail changing system further comprises a combined orifice, the combination
- the nozzle hole is composed of a plurality of nozzles arranged in a honeycomb geometry (hereinafter referred to as: combined nozzle hole), and the combined nozzle hole is installed at the leading edge and the trailing edge of the aircraft wing, or is mounted on the tail or pelvic fin or duck of the aircraft.
- the symmetry plane of the wing or the fuselage, the rail changing system further comprises a pneumatic storage device (hereinafter referred to as: a storage device) or several reservoirs, the storage device is supplied by the engine, placed inside the aircraft, and the storage device
- a pneumatic storage device hereinafter referred to as: a storage device
- the combined orifices are connected by a gas pipeline, and a nozzle that is sprayed downward may be provided under the reservoir.
- the invention relates to an orbiting system applied to an aircraft, characterized in that the nozzle of the combined orifice is injecting gas outward, the combined orifice comprises two types of nozzles, and one type is sprayed in a fixed direction.
- a gas nozzle, another type is a nozzle that changes the direction of the injected gas.
- the invention relates to a rail changing system for an aircraft, characterized in that the rail changing system is applied to a military or civilian tailed aircraft, and the front edge of the aircraft wing is symmetrically connected from the top to the bottom.
- the combined orifices constitute a combined orifice arranged by the upper, middle and lower sides, and the rear edge of the wing (at the flap of the original wing, at the aileron, the following is similar) is symmetrical from the top to the bottom.
- the nozzle hole constitutes a combined nozzle hole which is arranged in series by the upper, middle and lower sides.
- the symmetrical side of the tail of the aircraft is provided with a combined nozzle hole, and the rear end of the aircraft is symmetrically arranged with a combined nozzle hole on the upper and lower sides, and the body is symmetric with a central axis.
- the above-described rail changing system for an aircraft characterized in that the rail changing system is applied to a rear-end military aircraft correction page (Article 91)
- the front edge of the military wing is symmetrically provided with a combined spray hole from the top to the bottom, forming a combined spray hole arranged in the upper, middle and lower sides, and the rear edge of the wing is symmetrically connected from the top to the bottom.
- the combination is provided with a combined orifice, which also constitutes a combined orifice arranged by the upper, middle and lower sides.
- the original vertical tail or ventral fin of the wing tail is symmetrically arranged above and below with a combined orifice, the belly of the fuselage or under the wing
- the nozzle is symmetrical in the middle axis, and the air pressure reservoir is arranged in the fuselage or the wing.
- the above-described rail changing system for an aircraft is characterized in that the rail changing system is applied to a helicopter, and a quadrilateral or hexagonal or octagonal shape is mounted on the top of the helicopter propeller bearing. Polygonal rotating disk with corners, polygon
- the side of the rotating disc is provided with a combined orifice, and the inner part of the rotating disc and the central part of the bearing have a hollow structure, and the hollow shaft is supported by the combined nozzle hole on the polygonal rotating disc at the top of the bearing.
- the above-described rail changing system for an aircraft is characterized in that the rail changing system is applied to a rocket or a missile, and a combined nozzle hole is provided in a surface layer of the casing of the rocket or the missile.
- the aircraft has a circular dish shape, and the aircraft is divided into upper, middle and lower three-layer structures.
- the central position of the middle layer of the aircraft and the upper part of the lower layer are provided with a reservoir, and the center point of the middle layer of the aircraft is at an angle of 90'C.
- Four exhaust nozzle ports are arranged in four directions, and the upper and lower two nozzles are respectively arranged in the four exhaust nozzle ports, and the nozzle guiding tips are arranged in the middle of the upper and lower nozzles.
- the bottom of the reservoir is provided with a row of circumferential downward spray nozzles, and the upper and lower surface layers of the aircraft are respectively provided with combined spray holes.
- the above-mentioned variable rail system for an aircraft is characterized in that the nozzle and the combined orifice are configured to radiate outward in a center of a circle.
- the above-mentioned rail changing system for an aircraft is characterized in that the upper and lower two nozzles of the middle nozzle wall of the aircraft are provided with a certain angle of inclination at the nozzle valve.
- the method for an orbital system of an aircraft is characterized in that the application method is as follows: (A) Flight: When two nozzles adjacent to the middle of the dish are jetted, the flying saucer makes a horizontal flight forward.
- the flying saucer When closing one nozzle on one side and opening the adjacent nozzle jet on the other side, the flying saucer will make a orbital movement in the 90'C direction.
- the flying saucer When closing the two open nozzles, open the opposite two nozzles.
- the flying saucer When flying, the flying saucer will act as a brake or reverse the horizontal direction of the flight;
- the aircraft will be lifted off: Open the downwardly sprayed nozzle, and when the flying saucer is lifted vertically to a certain height, open the No. 3 No. 4 nozzle, so that the flying saucer is pushed horizontally.
- crawling and lifting close the vertically lifted nozzle and open the combined nozzle of the designated part of the lower controller.
- the horizontal airflow in the lower layer of the flying saucer is injected by the combined nozzle.
- the vertical airflow resistance is blocked, the direction of the airflow movement is changed, and the head of the flying saucer is lifted upward to form an orbital flight in an upward oblique direction;
- (D) Combination nozzle brake When the aircraft is doing any horizontal flight movement, it needs to brake and close the No. 3 and No. 4 nozzles. Due to the inertia, the flying saucer is still doing the forward flight. The combined nozzles of the designated parts of the upper and lower controllers of the flying saucer are simultaneously opened, and the horizontal airflow forms a vertical direction against the jet airflow, hindering the flying saucer from flying forward, and braking action; (E) left-handed orbital change, When the aircraft needs to rotate left-handed in horizontal direction, open the combined nozzle of the 45° angle from the left to the lower part of the upper and lower controllers. Since the horizontal airflow is blocked by the resistance of the jet curtain wall, the flying direction of the flying saucer will be left.
- the angle is deflected, the orbit is formed, and after the requirement of the orbital angle is reached, the combined nozzle is closed, and the flying saucer flies in the direction after the orbital change;
- the right-handed orbital when the aircraft needs to rotate the right-handed orbit in the horizontal direction Open the combined nozzle of the right 45 ⁇ angle of the designated part of the upper and lower controllers. Because the horizontal airflow is blocked by the resistance of the jet curtain wall, the flying saucer It will be deflected to the direction of flight of the right angle, forming orbit, to achieve the required orbit angle, close the combined nozzle holes, flying saucer in the direction of flight of the orbit.
- the invention has the advantages of low equipment cost, simple operation and maintenance, greatly reduced the cost of aerospace and aviation, and does not require a large-scale, complex equipment space launching site or a large airport runway. Only one airport is needed.
- the space plane completes a flight, it can take off again after maintenance. People can travel in the same way as a plane. Even if you don't go to space, it is convenient to take it to the other side of the ocean to visit friends. And in military value, it can also be converted into aerospace fighters, air-to-air bombers and air-to-air transport aircraft.
- the space plane's strong penetration is able to easily break through the enemy's defense system and attack the enemy, destroying the enemy's living power.
- FIG. 1 Schematic diagram of the combination of the honeycomb geometry of the present invention mounted on the sides of the aircraft tail or the empennage or ventral fin, for example: each square hole represents a honeycomb nozzle;
- the controller specifies to open the 1-a group or the 1-b group, and the combined orifice forms a geometrical schematic diagram of two different parts:
- the controller specifies to open the 1-a group and the 1-b group at the same time, and the combined orifice forms an integral L shape.
- Schematic diagram of the geometric shape
- Figure 2 Schematic diagram of the combined orifices of the combined orifices of the present invention mounted on the leading or trailing edge (former flap, aileron) or duck wing of the wing, such as: Represents a honeycomb nozzle;
- the controller specifies to open the 2-a group, and the combined orifices form a schematic diagram of the geometry of the single row jet:
- the controller specifies to open the 2-b group, and the combined orifice constitutes a geometrical schematic diagram of the plurality of rows of sprays;
- Figure 3 is a cross-sectional view of the combined orifice of the present invention mounted on the leading and trailing edges of the wing;
- FIG. 4 Schematic diagram of the layout of the military or civilian tail aircraft used in the present invention:
- 4- a is a combination nozzle for the front edge of the aircraft
- 4-d is a combination of spray holes on both sides of the symmetrical side of the aircraft
- 4-e is a combination nozzle on the upper and lower sides of the symmetrical aircraft tail
- the combined nozzle is installed at the front edge of the aircraft, icon 5 - a ;
- the combined nozzle is installed at the rear edge of the aircraft, icon 5 - b;
- the combined nozzle is installed on the left and right sides of the tail of the aircraft and the upper and lower parts, icon 5 - c;
- a combination nozzle for vertical take-off and landing is installed in a symmetrical part of the center of the abdomen of the aircraft.
- Figure 5 - Mountain Figure 6 Schematic diagram of the structure of the upper, middle and lower layers of the present invention applied to the dish;
- the 6-1 icon is a combination nozzle
- the icon is the gas pipe of the combined orifice
- the 6-4 icon is a nozzle for vertical take-off and landing
- 6-6 icon is the valve inside the power nozzle
- Figure 7 Schematic diagram of the layout of the middle nozzle for the invention and the flying direction of the flying saucer when the nozzle is opened;
- (F). is a sectional view of the flying saucer;
- Figure 8 a bottom view of the nozzle opening with 8 downward jets at the bottom of the lower layer of the flying saucer;
- Figure 9 The combined orifice of the present invention is mounted on the upper and lower layers of the flying saucer, Design layout map applied to the orbit;
- Figure 10 The working state diagram when the dish is changed into a track when the controller is applied to the controller to open the part;
- (B) is a working state diagram of the downward flight of the present invention applied to the downward direction of the dish, and when the upper layer of the designated working portion is sprayed upward, the aircraft is flying downward;
- the invention is applied to the braking of the dish-shaped aircraft, and simultaneously opens the upper and lower layers of the designated working portion, and the working state diagram of the upper and lower jets simultaneously
- (E) is a working state diagram when the present invention is applied to a right-handed orbit of a dish, and the designated working portion of the upper and lower layers is opened;
- Figure 11 The invention is applied to a helicopter
- 11-1 is a disk surface view of the rotating disk
- 11-2 is a bearing view of the rotating disc and the chain
- 11--3 is a hollow view of the bearing center
- 11- 4 is a view showing one side of the octagonal rotating disk mounted with the present invention.
- 11-- 5 is applied to the rotating disc on the top of the helicopter propeller bearing, the controller is designated to open the nozzle hole
- FIG. 12-2 is the installation of the combined nozzle hole: Figure 13: (A).
- the icon is applied to the rocket and missile on the invention, and the controller specifies the opening of the nozzle jet.
- Figure 1 is an example: see the 1-a icon combination nozzle opening, the form of a shape of a jet shape is formed; see 1-b icon combination nozzle opening, forming an oblique rectangular shape; When the combined orifices of the 1-a and 1-b icons are simultaneously smashed, an L-shaped jet form is formed.
- FIG. 5 See the 5-a, 5-b icons on the original flap, aileron or duck wing parts of the aircraft wing. Install the combined spray holes from the upper, middle and lower symmetry. See 3-a icon and 3. -b icon; each square hole represents a combined nozzle nozzle see 2-a, 2-b icon, after programming, can form a single row of injection or multiple rows of injection gas;
- the flaps, ailerons, tail fins (the rear wing including the horizontal tail and the vertical tail), the duck wings, the pelvic fins, etc. installed on the existing aircraft are all taking off, landing, balancing, and orbiting the aircraft. Such as the role, or for the fighter to take the role of short takeoff and landing, rollover and so on.
- the basic principle of these orbital devices is that when these devices are opened, the horizontal airflow encounters resistance, thereby causing the horizontal airflow to change the direction of motion, resulting in a orbital effect on the aircraft.
- the system of the invention can help the aircraft to remove all complicated orbital auxiliary devices except the fuselage and the wing, greatly simplifying the internal and external structure of the aircraft, removing the quality of these devices, and adding more oil to the aircraft. Or materials, the economic benefits of flight have been greatly improved, and can play a positive role in some aspects of the design of aviation aircraft in the future.
- the nozzles and combined nozzles installed in different parts of the aircraft can open vertical takeoff, vertical landing, hovering, balancing, turning and orbiting for the aircraft by opening different nozzles and combined nozzles during the orbital change. The role of rollover.
- the invention is applied to a dished aircraft comprising the following units:
- Engine According to the different requirements of the aircraft, choose to use different "rocket engines”, “aviation engines”, or other types of engines. You can use one or multiple engines to combine the power of the aircraft. .
- Aircraft Cooling System Avoid excessive temperature build-up of the engine that prevents some parts of the engine or other equipment from functioning properly. Cooling can protect the engine's components and other equipment components from working properly.
- High-temperature resistant, high-pressure energy storage (hereinafter referred to as: storage): Because the energy generated by the work of the engine is very high, the pressure is very high. To store these high-temperature and high-pressure energy, one must have a high resistance.
- the storage of warm and high-pressure gas energy, the energy in the storage one of which: can provide the power source for the aircraft to fly at low speed in the atmosphere, and the second: it is the change of the "ultra-high pressure fluid-injected power rail system" Provide a source of power.
- each storage unit is The gas pressure is relatively stable, and the pressure of the jets of each nozzle is eliminated when the gas is discharged, which has the function of voltage regulation.
- High-temperature resistant, high-pressure gas pipeline It is designed according to the different use requirements of the aircraft.
- the pipeline is laid, and the pressure storage is linked with the nozzle or the combined nozzle.
- the pipeline mainly serves as the nozzle and nozzle. The role of conveying power gas.
- High-temperature resistant, high-pressure variable nozzle It is designed according to the shape of the aircraft. One or more jet nozzles can be set at the required part of the aircraft to make vertical lift, horizontal flight, hover and change for the aircraft. Rails and the like provide energy power.
- High temperature resistant, high pressure variable or fixed nozzle According to the design requirements of the aircraft, the honeycomb geometry nozzles can be arranged into different densities, different orifice sizes, nozzles fixed or rotated, arbitrary geometry.
- the nozzle combination (hereinafter referred to as: combination nozzle) is installed in the surface level required by the aircraft, and is used in conjunction with the nozzle.
- the aircraft performs vertical takeoff and landing, hovering, balancing, braking, and super maneuvering. This system can replace the various "tangible orbital" devices on modern aircraft.
- Central automatic control system It is the central automatic control system of the aircraft. It is connected to all the equipment devices on the aircraft through the cable line. According to the set procedure, all the action instructions on the aircraft are automatically controlled, commanded and released.
- the central control system controls the emissions to enable the aircraft to complete these actions.
- the inventors designed to divide the structure of the aircraft into upper, middle and lower layers, and placed the reservoir at the center of the upper and lower upper portions of the aircraft. (See Figure 6)
- a row of circumferential down-spray nozzles are laid under the air pressure storage.
- the number of nozzles is determined as needed.
- the nozzles mainly serve to provide vertical take-off and landing and suspension for the aircraft. effect. (See Figure 8)
- the combined nozzles are installed in the upper and lower layers of the aircraft.
- the nozzles are instructed by the controller to inject gas outward (see Figure 7-F).
- the direction of the airflow passing through the horizontal direction of the surface of the aircraft forms a vertical direction of motion.
- this jet of squirting gas blocks the passage of horizontal airflow like a wall, it forces the horizontally moving airflow to change its direction of motion. At that time, the force that moves in the other direction is formed.
- the aircraft uses this force to make the maneuvering orbit.
- the control system closes the injection hole and returns the aircraft to the level. Direction of movement.
- the angle at which the fixed nozzle is sprayed can be set as needed, and the variable angle nozzle can change the jet angle of the jet.
- the aircraft Since the aircraft is a circular dish-shaped object, the nozzle and the combined nozzle hole are laid, and the method of laying the core into the circumference is adopted. Therefore, the aircraft has no defined head or tail direction, and the four directions can be called As the head or tail, this direction is the head of the aircraft only when we artificially set a certain part of it as the head. (See Figure 9)
- the aircraft can fly at low speed, it can also fly at super high speed, when the aircraft reaches a certain speed at high speed.
- the above-mentioned left and right orbital method can be used to set the flight mode of the aircraft to a mode in which the center of the aircraft is rotated forward by centripetal force.
- This flight mode can avoid the occurrence of shock phenomena (or sonic explosion). Because the force point of the outer surface of the flying object is solved by the centrifugal force when the object rotates at a high speed, the surface of the aircraft is greatly reduced, and the high temperature generated by the direct force and the friction of the air is on the aircraft. The surface plays a vital role in protection.
- the aircraft can sail on the water:
- variable orbits are all combined with the method of jet-jet change, and because of its disc shape and the outer edge of the arc with a 30-inch angle, the aircraft can be produced very well. Invisible effect. See Figure 7: Design and application of the four-way laying nozzle in the middle of the aircraft
- the function of the nozzle is designed to cross the center of the aircraft. When the two forces intersect at the center point, a forward force is synthesized (see Figure 7-A).
- the advantage of the square nozzle is that When the adjacent No. 3 and No. 4 nozzles are opened, the flight direction of the aircraft is to fly in a horizontal direction (see Figure 7-B); when the adjacent No. 1 and No. 2 nozzles are opened, the aircraft will start To the braking effect, or to fly in a direction opposite to the horizontal direction (see Figure 7-C); when opening No. 2, 3
- the vertical vertical take-off and landing nozzle in the center of the inner ring of the lower part of the aircraft for the aircraft to make a downward jet when it is vertically hoisted and hovered. It can be matched with the combined nozzle and balanced by the jetting force of the combined nozzle.
- the stability of the aircraft can also be selected as the vertical take-off and landing nozzle on the outer ring of the lower part of the aircraft.
- the advantage of the vertical take-off and shoot nozzle of the outer ring is that the aircraft takes off and land.
- the stability is better than in the middle, and the lack of space is large.
- Hovering in the air can open the combined nozzle-based jet hovering mode, because the aircraft does not need to have a large thrust upwards, as long as the aircraft is secured in the air with the gravity and the aircraft The ascending lift balance is sufficient, and of course depends on whether the jet force of the combined orifice can reach the gravity of the supporting aircraft. See Figure 9: Combination of the array of aircraft arrangements:
- the aircraft is a circular object.
- the inventor designed the combined nozzle holes to be arranged in a circumferential shape.
- the number of combined nozzle holes in the upper and lower surface layers is the same, and the mounting portions are symmetrical, so that the same amount of symmetrical arrangement, It is possible to ensure the synchronism of the jet change (see Figure 9).
- the aircraft When opening the combined jet injection of the aircraft in the following form (see Figure 10), the aircraft is required to be lifted at an angle of 30 (see Figure 10-A) or landing. (See Figure 10-B)
- the effect of the application, as well as the effect of the aircraft during in-flight braking see Figure 10-C).
- FIG. 10-A for aircraft to take off: Open the vertical take-off and landing nozzle, and when the aircraft is lifted vertically to a certain degree, open the No. 3 and No. 4 nozzles to make the aircraft advance horizontally. Vertically lift the nozzle and open the lower combined nozzle at the same time. Because the lift of the horizontal airflow of the aircraft is blocked by the vertical airflow resistance of the nozzle, the direction of the airflow changes, and the head of the aircraft will rise upwards to form an upward oblique direction. Orbital flight. See Figure 10-B. Aircraft landing: When the aircraft is flying horizontally in the air and needs to land, close the No. 3 and No. 4 nozzles.
- the aircraft uses the inertial flight of the flight speed to open the upper combined nozzle, due to the horizontal airflow of the upper surface layer of the aircraft. Blocked by the vertical airflow resistance of the nozzle, the direction of the airflow changes, and the head of the aircraft moves in a downward direction to form an orbital flight in a downward oblique direction.
- a part of the vertical lift is provided to the helicopter by means of a nozzle mounted on the bottom of the helicopter.
- a rotating disc with a quadrilateral or hexagonal or octagonal corner is mounted on the top of the helicopter's counterfeit bearing, the side of the polygonal rotating disc
- a combined orifice is provided, and the inner portion of the rotating disc and the central portion of the bearing chain are hollow, and the hollow bearing is used to deliver gas to the combined orifice on the polygonal rotating disc at the top of the bearing.
- the shaft is spinning at an idle speed
- the combined orifice on the side of the top of the rotating disc injects gas outward. This gas is ejected in a shape similar to the shape of the propeller blade. This design will be the original "tangible propeller blade" of the helicopter. "Changed to "invisible propeller blades”.
- the lift capacity may not reach the load capacity of the "tangible blade” bearing weight, so we can increase its lift capacity by increasing the engine power, increasing the air pressure and adding more invisible blades.
- the actual situation of this idea is to be determined by experimentation.
- Helicopter rotation effects and orbital problems can be solved by installing a "tracking system" at a suitable location on the fuselage. Since the propeller blade has a "tangible” shape and becomes an “invisible” object, the safety factor is greatly improved.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/004,166 US20140001275A1 (en) | 2011-03-10 | 2011-12-01 | Ultra-High-Pressure Fluid Injection Dynamic Orbit-Transfer System and Method Used in Aircraft |
US15/201,319 US20170088254A1 (en) | 2011-03-10 | 2016-07-01 | Ultra-High-Pressure Fluid Injection Dynamic Orbit-Transfer System and Method |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201110057190.7 | 2011-03-10 | ||
CN2011100571907A CN102167162A (zh) | 2011-03-10 | 2011-03-10 | 一种用于飞行器的超高压流体喷射动力变轨系统及方法 |
Related Child Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/004,166 A-371-Of-International US20140001275A1 (en) | 2011-03-10 | 2011-12-01 | Ultra-High-Pressure Fluid Injection Dynamic Orbit-Transfer System and Method Used in Aircraft |
US15/201,319 Continuation-In-Part US20170088254A1 (en) | 2011-03-10 | 2016-07-01 | Ultra-High-Pressure Fluid Injection Dynamic Orbit-Transfer System and Method |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012119468A1 true WO2012119468A1 (zh) | 2012-09-13 |
Family
ID=44488530
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CN2011/083309 WO2012119468A1 (zh) | 2011-03-10 | 2011-12-01 | 一种用于飞行器的超高压流体喷射动力变轨系统及方法 |
Country Status (3)
Country | Link |
---|---|
US (1) | US20140001275A1 (zh) |
CN (1) | CN102167162A (zh) |
WO (1) | WO2012119468A1 (zh) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102167162A (zh) * | 2011-03-10 | 2011-08-31 | 洪瑞庆 | 一种用于飞行器的超高压流体喷射动力变轨系统及方法 |
CN103204238B (zh) * | 2013-04-18 | 2015-06-24 | 包绍宸 | 喷流舵面控制系统、使用此系统的飞行器及控制方法 |
CN103253369A (zh) * | 2013-05-14 | 2013-08-21 | 张红艳 | 一种便于转向的碟状飞行器 |
US9741049B2 (en) * | 2013-09-18 | 2017-08-22 | Honeywell International Inc. | Generation of cost-per-braking event values |
CN105730682A (zh) * | 2016-02-02 | 2016-07-06 | 毕国伟 | 多点矢量推力分布的主动式气动布局的飞机 |
CN107416187A (zh) * | 2016-07-01 | 2017-12-01 | 洪瑞庆 | 一种采用超高压流体喷射动力学轨道转移的飞行物 |
CN106828885A (zh) * | 2016-12-30 | 2017-06-13 | 上海牧羽航空科技有限公司 | 一种采用喷气形式控制偏航和俯仰的倾转旋翼机 |
CN107176297A (zh) * | 2017-06-20 | 2017-09-19 | 北京迪鸥航空科技有限公司 | 一种飞行器 |
CN109502037B (zh) * | 2018-11-14 | 2021-11-09 | 三亚哈尔滨工程大学南海创新发展基地 | 一种反向喷气通气空泡航空飞行器水面迫降机构 |
CN109677608A (zh) * | 2018-11-27 | 2019-04-26 | 西华大学 | 无尾飞翼耦合动力飞行器 |
CN109579637B (zh) * | 2018-12-07 | 2023-04-18 | 中国人民解放军国防科技大学 | 一种无舵面导弹姿态控制机构 |
CN110155371B (zh) * | 2019-06-03 | 2021-06-01 | 北京航空航天大学 | 一种充气喷射起飞滑翔回收的火星飞行器及其使用方法 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN2440751Y (zh) * | 2000-08-04 | 2001-08-01 | 于树林 | 飞机空中防碰撞灵活急转弯装置 |
CN2584512Y (zh) * | 2002-11-11 | 2003-11-05 | 金洪奎 | 飞行器的外形结构 |
CN1498821A (zh) * | 2002-11-11 | 2004-05-26 | 陶杰杰 | 飞盘飞行器 |
US7104499B1 (en) * | 2002-09-25 | 2006-09-12 | Northrop Grumman Corporation | Rechargeable compressed air system and method for supplemental aircraft thrust |
CN102167162A (zh) * | 2011-03-10 | 2011-08-31 | 洪瑞庆 | 一种用于飞行器的超高压流体喷射动力变轨系统及方法 |
Family Cites Families (35)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2885162A (en) * | 1956-02-08 | 1959-05-05 | Elizabeth M Griswold | Integrated jet-wing |
US3055614A (en) * | 1960-05-12 | 1962-09-25 | Wendell J Thompson | Air-ejector aircraft |
US3465988A (en) * | 1966-08-02 | 1969-09-09 | Anthony Hugh Orr | Aerodynamic lift producing devices |
DE3612175C1 (de) * | 1986-04-11 | 1987-10-08 | Messerschmitt Boelkow Blohm | Schnellfliegender Flugkoerper |
US5156353A (en) * | 1987-04-13 | 1992-10-20 | General Electric Company | Aircraft pylon |
US5050819A (en) * | 1990-08-10 | 1991-09-24 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Rotatable non-circular forebody flow controller |
US5366177A (en) * | 1992-10-05 | 1994-11-22 | Rockwell International Corporation | Laminar flow control apparatus for aerodynamic surfaces |
US5590854A (en) * | 1994-11-02 | 1997-01-07 | Shatz; Solomon | Movable sheet for laminar flow and deicing |
US6142425A (en) * | 1995-08-22 | 2000-11-07 | Georgia Institute Of Technology | Apparatus and method for aerodynamic blowing control using smart materials |
US5794887A (en) * | 1995-11-17 | 1998-08-18 | Komerath; Narayanan M. | Stagnation point vortex controller |
US5779196A (en) * | 1995-12-08 | 1998-07-14 | The Boeing Company | Ram air drive laminar flow control system |
US5853143A (en) * | 1996-12-23 | 1998-12-29 | Boeing North American, Inc. | Airbreathing propulsion assisted flight vehicle |
DE19820097C2 (de) * | 1998-05-06 | 2003-02-13 | Airbus Gmbh | Anordnung zur Grenzschichtabsaugung und Stoßgrenzschichtkontrolle für ein Flugzeug |
US6622963B1 (en) * | 2002-04-16 | 2003-09-23 | Honeywell International Inc. | System and method for controlling the movement of an aircraft engine cowl door |
AU2003230975A1 (en) * | 2002-04-18 | 2003-11-03 | Airbus Deutschland Gmbh | Perforated skin structure for laminar-flow systems |
US6907724B2 (en) * | 2002-09-13 | 2005-06-21 | The Boeing Company | Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance |
CN1405063A (zh) * | 2002-11-11 | 2003-03-26 | 金洪奎 | 飞行器的控制其飞行姿态的结构 |
US7661629B2 (en) * | 2004-02-20 | 2010-02-16 | The Boeing Company | Systems and methods for destabilizing an airfoil vortex |
DE602005002144D1 (de) * | 2004-05-13 | 2007-10-04 | Airbus Gmbh | Flugzeugbauteil, insbesondere flügel |
US7213788B1 (en) * | 2004-06-01 | 2007-05-08 | Florida State University Research Foundation | Microjet-based control system for cavity flows |
US7150432B2 (en) * | 2004-06-18 | 2006-12-19 | The Boeing Company | Horizontal augmented thrust system and method for creating augmented thrust |
US20060202082A1 (en) * | 2005-01-21 | 2006-09-14 | Alvi Farrukh S | Microjet actuators for the control of flow separation and distortion |
US20090261206A1 (en) * | 2005-01-21 | 2009-10-22 | Alvi Farrukh S | Method of using microjet actuators for the control of flow separation and distortion |
DE102005039043A1 (de) * | 2005-08-18 | 2007-03-15 | Affeldt, Ralf, Dipl.-Ing. | Antriebssystem bestehend aus einer Anordnung von Luftleitkanälen und Luftschrauben zur Erzeugung eines richtungsgesteuerten Schubs |
US7874525B2 (en) * | 2006-05-04 | 2011-01-25 | Lockheed Martin Corporation | Method and system for fully fixed vehicle control surfaces |
US7966826B2 (en) * | 2007-02-14 | 2011-06-28 | The Boeing Company | Systems and methods for reducing noise from jet engine exhaust |
US8794567B2 (en) * | 2007-05-08 | 2014-08-05 | Yigal Adir | Control and safety system for an airplane |
US7866609B2 (en) * | 2007-06-15 | 2011-01-11 | The Boeing Company | Passive removal of suction air for laminar flow control, and associated systems and methods |
US8359825B2 (en) * | 2008-05-21 | 2013-01-29 | Florida State University Research Foundation | Microjet creation and control of shock waves |
US9239039B2 (en) * | 2008-10-27 | 2016-01-19 | General Electric Company | Active circulation control of aerodynamic structures |
GB0904875D0 (en) * | 2009-03-20 | 2009-05-06 | Geola Technologies Ltd | Electric vtol aircraft |
DE102009026457A1 (de) * | 2009-05-25 | 2010-12-09 | Eads Deutschland Gmbh | Aerodynamisches Bauteil mit verformbarer Außenhaut |
CN101602404B (zh) * | 2009-07-03 | 2013-12-25 | 朱晓义 | 一种新型结构的飞行器 |
US8303024B2 (en) * | 2010-02-22 | 2012-11-06 | Florida State University Research Foundation | Microjet control for flow and noise reduction in automotive applications |
CN101857085B (zh) * | 2010-06-03 | 2013-06-12 | 刘春� | 一种飞行器 |
-
2011
- 2011-03-10 CN CN2011100571907A patent/CN102167162A/zh active Pending
- 2011-12-01 US US14/004,166 patent/US20140001275A1/en not_active Abandoned
- 2011-12-01 WO PCT/CN2011/083309 patent/WO2012119468A1/zh active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN2440751Y (zh) * | 2000-08-04 | 2001-08-01 | 于树林 | 飞机空中防碰撞灵活急转弯装置 |
US7104499B1 (en) * | 2002-09-25 | 2006-09-12 | Northrop Grumman Corporation | Rechargeable compressed air system and method for supplemental aircraft thrust |
CN2584512Y (zh) * | 2002-11-11 | 2003-11-05 | 金洪奎 | 飞行器的外形结构 |
CN1498821A (zh) * | 2002-11-11 | 2004-05-26 | 陶杰杰 | 飞盘飞行器 |
CN102167162A (zh) * | 2011-03-10 | 2011-08-31 | 洪瑞庆 | 一种用于飞行器的超高压流体喷射动力变轨系统及方法 |
Also Published As
Publication number | Publication date |
---|---|
CN102167162A (zh) | 2011-08-31 |
US20140001275A1 (en) | 2014-01-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2012119468A1 (zh) | 一种用于飞行器的超高压流体喷射动力变轨系统及方法 | |
US20220048620A1 (en) | Universal vehicle with improved stability for safe operation in air, water and terrain environments | |
EP2991897B1 (en) | Vertical takeoff and landing (vtol) air vehicle | |
CN101857085B (zh) | 一种飞行器 | |
US6918244B2 (en) | Vertical takeoff and landing aircraft propulsion systems | |
WO2022068022A1 (zh) | 一种尾座式垂直起降无人机及其控制方法 | |
CN105882959A (zh) | 能够垂直起降的飞行设备 | |
HRP20230986T1 (hr) | Zrakoplov s okomitim uzlijetanjem i slijetanjem i postupak upravljanja istim | |
WO2018163156A1 (en) | A free wing multirotor with vertical and horizontal rotors | |
US20070018034A1 (en) | Thrust vectoring | |
CN108698690A (zh) | 具有提供有效的竖直起飞和着陆能力的翼板组件的uav | |
CN106585948A (zh) | 一种水空两栖无人飞行器 | |
CN106184741B (zh) | 一种飞翼式涵道风扇垂直起降无人机 | |
KR101828924B1 (ko) | 내연 엔진과 전기 모터를 구비한 항공기 | |
WO2018059244A1 (zh) | 飞行器 | |
CN103921931A (zh) | 涵道机翼系统以及运用该系统的飞行器 | |
CN102826227A (zh) | 无人空天战机 | |
CN105383681A (zh) | Zql型喷气式超短距垂直起降固定翼飞机 | |
CN106956555A (zh) | 基于共形半环翼的水空两用变体跨越航行器 | |
RU2442727C1 (ru) | Многоразовый ракетно-авиационный модуль и способ его возвращения на космодром | |
CN102730179A (zh) | 复合升力变形飞艇 | |
CN106005371B (zh) | 差分直驱全动三舵面无人机 | |
RU2317220C1 (ru) | Способ создания системы сил летательного аппарата и летательный аппарат - наземно-воздушная амфибия для его осуществления | |
JP3231509U (ja) | 空飛ぶ円盤型航空機 | |
RU2321526C1 (ru) | Многоразовый ускоритель ракеты-носителя |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 11860135 Country of ref document: EP Kind code of ref document: A1 |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 14004166 Country of ref document: US |
|
32PN | Ep: public notification in the ep bulletin as address of the adressee cannot be established |
Free format text: NOTING OF LOSS OF RIGHTS PURSUANT TO RULE 112(1) EPC (EPO FORM 1205A DATED 15/01/2014) |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 11860135 Country of ref document: EP Kind code of ref document: A1 |