CN113716036B - Lifting/pushing integrated power system of fixed wing vertical take-off and landing aircraft and control method - Google Patents
Lifting/pushing integrated power system of fixed wing vertical take-off and landing aircraft and control method Download PDFInfo
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- CN113716036B CN113716036B CN202111045270.0A CN202111045270A CN113716036B CN 113716036 B CN113716036 B CN 113716036B CN 202111045270 A CN202111045270 A CN 202111045270A CN 113716036 B CN113716036 B CN 113716036B
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- 238000000034 method Methods 0.000 title claims abstract description 10
- 230000007704 transition Effects 0.000 claims abstract description 7
- 239000007921 spray Substances 0.000 claims description 67
- 230000001133 acceleration Effects 0.000 claims description 3
- 239000002699 waste material Substances 0.000 abstract description 7
- 230000007246 mechanism Effects 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 description 9
- 230000001105 regulatory effect Effects 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 206010017472 Fumbling Diseases 0.000 description 1
- KEUKAQNPUBYCIC-UHFFFAOYSA-N ethaneperoxoic acid;hydrogen peroxide Chemical compound OO.CC(=O)OO KEUKAQNPUBYCIC-UHFFFAOYSA-N 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
- B64C29/0058—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with vertical jet
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
- B64C29/0066—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with horizontal jet and jet deflector
Abstract
The invention relates to a lifting/pushing integrated power system of a fixed wing vertical take-off and landing aircraft and a control method, which can provide lifting force and pushing force simultaneously through simple valve adjustment. Complex mechanisms are avoided, and the transition state from the vertical take-off and landing state to the flat flight state is simple and reliable; the redundancy of the system is avoided, the waste load and waste resistance caused by the lifting system in the flat flight state are reduced, and the space, weight and aerodynamic efficiency of the fixed wing vertical take-off and landing aircraft are greatly improved.
Description
Technical Field
The invention belongs to the field of vertical take-off and landing aircrafts, and particularly relates to a lifting/pushing integrated power system of a fixed wing vertical take-off and landing aircrafts and a control method.
Background
The vertical take-off and landing aircraft has low requirements on take-off and landing sites, is flexible to arrange and convenient to use, and can realize hovering, so that the vertical take-off and landing aircraft has unique performance advantages, is more and more widely applied particularly in the field of small unmanned aircrafts, and has increasingly strong requirements in various application fields.
The power system is a key point for determining success and failure and performance of the vertical take-off and landing aircraft, in the field of the rotor wing vertical take-off and landing aircraft, the technology gradually tends to be mature and perfect, but the rotor wing aircraft is low in flight speed, short in voyage and voyage, poor in stealth performance and the like, and the rotor wing aircraft is a performance short board which cannot be overcome. In the field of fixed wing vertical take-off and landing aircrafts, the power system technology of the fixed wing vertical take-off and landing aircrafts is still in a continuous fumbling and development stage.
The existing fixed wing aircraft vertical take-off and landing technology mainly has two major types, namely a thrust vectoring nozzle, such as a power system of a 'ray' fighter in the United kingdom; and the second is a combined power system of a thrust vectoring nozzle and a lifting fan, such as a power system of an F-35B fighter in the United states. The two types of vertical take-off and landing technologies have the unavoidable defects that the structure of the thrust vectoring nozzle is complex, the control mechanism is more complex, and the matching requirement on an engine and the nozzle is very high; the thrust vectoring nozzle and the lifting fan are combined to reduce the difficulty of matching the engine with the nozzle to a certain extent, but the lifting fan plays a role in taking off and landing and hovering stages, becomes a waste resistance of the aircraft in other flight stages, occupies installation space and increases the structural weight of the aircraft.
Therefore, from the aspect of the existing vertical take-off and landing technology of the fixed wing aircraft, the problems of complex structure and adjusting mechanism, poor reliability and large waste carrying capacity and space are urgently needed to be overcome.
Disclosure of Invention
The invention solves the technical problems that: based on the technical weakness of the existing fixed wing vertical take-off and landing aircraft power system, the invention provides a fixed wing vertical take-off and landing aircraft power system technology capable of integrally realizing lift force and thrust force output, and the technology can realize arbitrary proportion control between lift force and thrust force on the same set of system components through simple valve control, so that the technical defects that the existing power system technology is complex in structure and poor in reliability or lift force and thrust force respectively need different components to provide are overcome.
The technical scheme of the invention is as follows: a lifting/pushing integrated power system of a fixed wing vertical take-off and landing aircraft comprises an impeller, an annular volute air collection chamber, a plurality of lift spray pipes, lift spray pipe control valves, thrust spray pipes and thrust spray pipe control valves;
the annular volute gas collection chamber is in a shape of b, and a cavity is formed in the annular volute gas collection chamber; the impeller is positioned in the central area; the thrust jet pipe is positioned at the b-shaped port, a thrust jet pipe control valve is arranged at the port, and the direction of the nozzle of the thrust jet pipe is parallel to the rotation plane of the impeller; a plurality of lift force spray pipes are uniformly distributed on one side of the annular surface of the annular volute gas collection chamber, a lift force spray pipe control valve is arranged at the lift force spray pipe control valve, and the direction of the spray holes of the lift force spray pipes is perpendicular to the rotation plane of the impeller; the high-energy gas generated by the rotation of the impeller firstly enters the annular volute gas collection chamber and then respectively enters the lift spray pipe and the thrust spray pipe; the lift force spray pipe control valve and the thrust spray pipe control valve respectively control the area of the outlet of the lift force spray pipe and the area of the outlet of the thrust spray pipe, and control the flow rate of the spray flow, so that the lift force and the thrust force are respectively controlled.
The invention further adopts the technical scheme that: the opening and closing degree of the lift force spray pipe control valve and the thrust spray pipe control valve are controlled to respectively control the lift force and the thrust.
The invention further adopts the technical scheme that: the impeller is centrifugal or diagonal flow.
The invention further adopts the technical scheme that: a control method based on a lifting/pushing integrated power system of a fixed-wing vertical take-off and landing aircraft comprises the following steps of controlling the fixed-wing vertical take-off and landing aircraft from a vertical take-off stage to a horizontal flight stage, hovering or vertical landing stage:
when the vertical fly reaches the flat fly stage, the control process comprises the following steps:
step 1: the impeller is started, the impeller works in a high rotating speed state, the thrust spray pipe control valve is completely closed, the lift spray pipe control valve is completely opened, the forward thrust is zero, and the lift reaches the maximum value; the aircraft vertically takes off;
step 2: when the aircraft reaches the required height, the aircraft enters a transition state from vertical flying to horizontal flying, at the moment, the rotating speed of the impeller is gradually increased to the maximum rotating speed, meanwhile, the thrust jet pipe control valve is gradually opened, the thrust jet pipe generates forward thrust, the aircraft is gradually accelerated, and aerodynamic lift force is gradually generated on the wing; the lift force of the lift force spray pipe is reduced by gradually closing the lift force spray pipe control valve, the lift force spray pipe control valve is completely closed until the aerodynamic lift force on the wing is equal to the weight of the aircraft, at the moment, the lift force spray pipe does not provide lift force any more, the aircraft completes the flying in a transition state, and the aircraft enters a flat flying state; the speed and the acceleration of the aircraft during the flat flight are controlled by adjusting the rotation speed of the impeller and the opening of the thrust jet pipe control valve;
in the hovering phase, comprising the steps of:
step 1: gradually closing the thrust jet control valve and gradually opening the lift jet control valve;
step 2: when the flying speed is reduced to zero, the thrust jet control valve is in a completely closed state, and the opening and closing degree of the lift jet control valve is matched with the rotating speed of the impeller, so that the lift jet provides lift required for keeping the aircraft hovering;
in the vertical drop phase, comprising the steps of:
step 1: controlling an aircraft to hover in the sky above the area to be lowered;
step 2: the rotating speed of the impeller and the opening and closing degree of the lift spray pipe control valve are matched and adjusted, so that the lift provided by the lift spray pipe is smaller than the weight of the aircraft, and the aircraft is ensured to descend according to the designated descent rate and land at a certain landing speed.
Effects of the invention
The invention has the technical effects that: in the above analysis, it is mentioned that the vertical take-off and landing technology of the existing fixed wing aircraft relies on a vector thrust nozzle and a lift fan, which have the problems of high complexity of an insurmountable structure and an adjusting mechanism, poor reliability and large waste carrying capacity and space. According to the invention, the nozzle body parts of the thrust nozzle 3 and the lift nozzle 5 do not need to be regulated and have no regulating mechanism, and only a simple thrust nozzle control valve 4 and a simple lift nozzle control valve 6 are respectively arranged in the thrust nozzle 3 and the lift nozzle 5, so that the conversion between lift and thrust can be realized by matching and regulating the opening and closing degree of the thrust nozzle control valve 4 and the lift nozzle control valve 6 and the rotating speed of the impeller 1. Complex mechanisms are avoided, and simple and reliable conversion among vertical take-off and landing, hovering and flat flying states is realized. The reliability and convenience between flight state transitions can be greatly improved, and the waste load and waste resistance caused by redundant components of the lifting system in a flat flight state are reduced, so that the space arrangement, weight and pneumatic efficiency of the fixed wing vertical take-off and landing aircraft are improved, and the reliability of the whole aircraft is also improved.
Drawings
FIG. 1 is a front view of a lift/push integrated power system for a fixed wing vertical takeoff and landing aircraft
Fig. 2 is a bottom view of a lift/push integrated power system for a fixed wing vertical take-off and landing aircraft
FIG. 3 is a schematic illustration of a fixed wing vertical takeoff and landing aircraft with an integrated lift/thrust power system installed
Reference numerals illustrate: 1-an impeller; 2-an annular volute plenum; 3-thrust nozzle; 4-thrust jet control valve; 5-lifting force spray pipe; 6-lift nozzle control valve.
Detailed Description
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Referring to fig. 1-3, a fixed wing vertical take-off and landing aircraft lift/thrust integrated power system includes: centrifugal or diagonal flow impellers are used for acting on the airflow, so that the mechanical energy of the airflow is improved; the annular volute gas collection chamber is used for enabling high-energy airflow flowing out of the impeller to enter the volute gas collection chamber; the lift force spray pipes are arranged at equal intervals along the circumferential direction of the volute gas collection chamber, and when high-energy airflow is sprayed out of the lift force spray pipes, vertical upward lift force is generated; the lift spray pipe control valve controls the size of the outlet area of the lift spray pipe so as to control the airflow flow of the lift spray pipe, thereby controlling the size of lift; the thrust jet pipe is a radial or tangential outlet of air flow from the annular volute gas collection chamber, and when high-energy gas is ejected from the thrust jet pipe, forward thrust is generated; the thrust jet pipe control valve controls the outlet area of the thrust jet pipe so as to control the airflow flow of the thrust jet pipe and further control the thrust.
Further, the centrifugal or diagonal flow impeller does work on the airflow, improves the flow speed or total pressure of the airflow, and provides energy for generating jet flow lifting force and jet flow thrust.
Further, the annular volute plenum surrounds the impeller, and the high energy airflow exiting the impeller first enters the annular volute plenum.
Further, the lift force spray pipe is circumferentially arranged on one side of the annular volute air collection chamber, the nozzle direction is perpendicular to the rotation plane of the impeller, and when the lift force spray pipe control valve is opened, air flow is sprayed out of the lift force spray pipe, upward lift force is generated.
Further, the thrust jet nozzles jet the air flow rearward, producing forward thrust.
Further, the opening and closing degrees of the lift force spray pipe control valve and the thrust spray pipe control valve are controlled to control the lift force and the thrust respectively.
The invention provides a lifting/pushing integrated power system of a fixed wing vertical take-off and landing aircraft, which is shown in figures 1 and 2 and comprises the following components: centrifugal or diagonal flow impeller 1, annular volute plenum 2, thrust nozzle 3 and thrust nozzle control valve 4, lift nozzle 5 and lift nozzle control valve 6.
Figure 3 provides an exemplary fixed wing vertical takeoff and landing aircraft incorporating the power system of the present invention. The invention fully utilizes the advantages of strong single-stage pressurizing capacity, wide flow and pressure ratio regulating range, wide efficient working range, stable and reliable performance and the like of the centrifugal or diagonal flow impeller 1, and is used as a working component for air flow to improve the flow speed or total pressure of the air flow, the high-energy air flow passing through the impeller 1 is converged into the annular volute air collection chamber 2, and then is sprayed outwards through the lift spray pipe 5 or the thrust spray pipe 3 to generate lift or thrust. The flow of the lift spray pipe 5 and the thrust spray pipe 3 are respectively controlled through the lift spray pipe control valve 6 and the thrust spray pipe control valve 4, so that the control of the lift and the thrust is realized.
In the vertical take-off stage, the impeller 1 works in a high rotating speed state, the thrust jet pipe control valve 4 is completely closed, the lift force jet pipe control valve 6 is completely opened, the forward thrust is zero, and the lift force reaches the maximum value. When the aircraft reaches a certain height, the aircraft starts to enter a transition state from vertical flying to flat flying, at the moment, the rotating speed of the impeller 1 is gradually increased to the maximum, meanwhile, the thrust jet pipe control valve 4 is gradually opened, the thrust jet pipe 3 generates forward thrust, the aircraft is gradually accelerated, aerodynamic lift is gradually generated on the wing, at the moment, according to the principle that the total lift is balanced with the total weight of the aircraft, the lift force of the lift force jet pipe 5 is reduced by gradually closing the lift force jet pipe control valve 6 until the aerodynamic lift force on the wing is equal to the weight of the aircraft, the lift force jet pipe control valve 6 is completely closed, at the moment, the lift force jet pipe 5 does not provide lift force any more, the aircraft completes the transition state flying, and the aircraft enters the flat flying state. The speed and the acceleration of the aircraft during the flat flight are controlled by adjusting the rotating speed of the impeller 1 and the opening degree of the thrust jet pipe control valve 4.
When the aircraft hovers in the air, the thrust jet control valve 4 is gradually closed, the lift jet control valve 6 is gradually opened, in the process, the flying speed is gradually reduced, and the resistance and aerodynamic lift of the aircraft body are also gradually reduced, so that the opening and closing degree of the thrust jet control valve 4 and the lift jet control valve 6 and the rotating speed of the impeller 1 are matched and adjusted according to the flying resistance and the lift requirement. When the flying speed is reduced to zero, the thrust jet control valve 4 is in a completely closed state, and the opening and closing degree of the lift jet control valve 6 is matched with the rotating speed of the impeller 1, so that the lift jet 5 provides lift required for keeping the aircraft hovering.
When the aircraft is to realize vertical landing, firstly controlling the aircraft to realize hovering above a region to be lowered; and then the rotating speed of the impeller 1 and the opening and closing degree of the lift nozzle control valve 6 are matched and regulated simultaneously, so that the lift force provided by the lift nozzle 5 is smaller than the weight of the aircraft, and the aircraft is ensured to descend according to the designated descent rate and land at a certain landing speed.
Claims (4)
1. The lifting/pushing integrated power system of the fixed wing vertical take-off and landing aircraft is characterized by comprising an impeller (1), an annular volute gas collection chamber (2), a plurality of lift spray pipes (5), a lift spray pipe control valve (6), a thrust spray pipe (3) and a thrust spray pipe control valve (4);
the annular volute gas collection chamber (2) is in a shape of b, and a cavity is formed in the annular volute gas collection chamber; the impeller (1) is positioned in the central area; the thrust jet pipe (3) is positioned at the b-shaped port, a thrust jet pipe control valve (4) is arranged at the port, and the direction of the nozzle of the thrust jet pipe (3) is parallel to the rotating plane of the impeller (1); a plurality of lift spray pipes (5) are uniformly distributed on one side of the annular surface of the annular volute gas collection chamber (2), a lift spray pipe control valve (6) is arranged at the lift spray pipe control valve, and the direction of a spray opening of the lift spray pipe (5) is perpendicular to the rotating plane of the impeller (1); the high-energy gas generated by the rotation of the impeller (1) firstly enters the annular volute gas collection chamber (2) and then respectively enters the lift spray pipe (5) and the thrust spray pipe (3); the lift force spray pipe control valve and the thrust spray pipe control valve respectively control the area of the outlet of the lift force spray pipe and the area of the outlet of the thrust spray pipe, and control the flow rate of the spray flow, so that the lift force and the thrust force are respectively controlled.
2. The lift/thrust integrated power system of the fixed wing vertical take-off and landing aircraft according to claim 1, wherein the magnitude of lift and thrust are controlled respectively by controlling the opening and closing degree of a lift nozzle control valve and a thrust nozzle control valve.
3. A fixed wing vertical take-off and landing aircraft lift/thrust integrated power system as claimed in claim 1, characterized in that said impeller (1) is centrifugal or diagonal.
4. The control method of the lifting/pushing integrated power system of the fixed-wing vertical take-off and landing aircraft based on the claim 1 is characterized by comprising the control process of three stages of vertical take-off and landing of the fixed-wing vertical take-off and landing aircraft from a vertical take-off stage to a horizontal fly stage, hovering or vertical landing:
when the vertical fly reaches the flat fly stage, the control process comprises the following steps:
step 1: the impeller (1) is started to work in a high rotating speed state, the thrust spray pipe control valve (4) is completely closed, the lift spray pipe control valve (6) is completely opened, the forward thrust is zero, and the lift reaches the maximum value; the aircraft vertically takes off;
step 2: when the aircraft reaches the required height, the aircraft enters a transition state from vertical flying to horizontal flying, at the moment, the rotating speed of the impeller (1) is gradually increased to the maximum rotating speed, meanwhile, the thrust jet pipe control valve (4) is gradually opened, the thrust jet pipe (3) generates forward thrust, the aircraft is gradually accelerated, and aerodynamic lift force is gradually generated on the wing; the lift force of the lift force spray pipe (5) is reduced by gradually closing the lift force spray pipe control valve (6), the lift force spray pipe control valve (6) is completely closed until the aerodynamic lift force on the wing is equal to the weight of the aircraft, at the moment, the lift force spray pipe (5) does not provide lift force any more, the aircraft completes the flying in a transitional state, and the aircraft enters a flat flying state; the speed and the acceleration of the aircraft during the flat flight are controlled by adjusting the rotating speed of the impeller (1) and the opening of the thrust jet pipe control valve (4);
in the hovering phase, comprising the steps of:
step 1: gradually closing the thrust jet control valve (4) and simultaneously gradually opening the lift jet control valve (6);
step 2: when the flying speed is reduced to zero, the thrust jet control valve (4) is in a completely closed state, and the opening and closing degree of the lift jet control valve (6) is matched with the rotating speed of the impeller (1), so that the lift jet (5) provides lift required for keeping the flying of the aircraft;
in the vertical drop phase, comprising the steps of:
step 1: controlling an aircraft to hover in the sky above the area to be lowered;
step 2: the rotating speed of the impeller (1) and the opening and closing degree of the lift spray pipe control valve (6) are matched and adjusted, so that the lift provided by the lift spray pipe (5) is smaller than the weight of the aircraft, and the aircraft is ensured to descend according to the designated descent rate and land at a certain landing speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111045270.0A CN113716036B (en) | 2021-09-07 | 2021-09-07 | Lifting/pushing integrated power system of fixed wing vertical take-off and landing aircraft and control method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111045270.0A CN113716036B (en) | 2021-09-07 | 2021-09-07 | Lifting/pushing integrated power system of fixed wing vertical take-off and landing aircraft and control method |
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| Publication Number | Publication Date |
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| CN113716036A CN113716036A (en) | 2021-11-30 |
| CN113716036B true CN113716036B (en) | 2023-11-14 |
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| DE1287366B (en) * | 1963-07-15 | 1969-01-16 | Rolls Royce | Bypass gas turbine jet engine |
| CN2827873Y (en) * | 2005-07-06 | 2006-10-18 | 雷良榆 | Helicopter with airfoil fluidic fixing wing |
| CN106143900A (en) * | 2016-06-21 | 2016-11-23 | 王启振 | The aircraft of VTOL |
| CN110985238A (en) * | 2019-12-31 | 2020-04-10 | 西北工业大学 | Variable working condition rocket engine capable of realizing height compensation |
| CN111336012A (en) * | 2019-11-06 | 2020-06-26 | 西北工业大学 | Centrifugal compressor and turbine blade integrated micro engine impeller disc |
| CN112829925A (en) * | 2021-03-22 | 2021-05-25 | 禹班工程科技(上海)有限公司 | Lift device for vertical take-off and landing of aircraft, aircraft and fixed-wing aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150336665A1 (en) * | 2014-05-22 | 2015-11-26 | Chen Li Jing | VTOL aircraft with a thrust-to-weight ratio smaller than 0.08 |
-
2021
- 2021-09-07 CN CN202111045270.0A patent/CN113716036B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1287366B (en) * | 1963-07-15 | 1969-01-16 | Rolls Royce | Bypass gas turbine jet engine |
| CN2827873Y (en) * | 2005-07-06 | 2006-10-18 | 雷良榆 | Helicopter with airfoil fluidic fixing wing |
| CN106143900A (en) * | 2016-06-21 | 2016-11-23 | 王启振 | The aircraft of VTOL |
| CN111336012A (en) * | 2019-11-06 | 2020-06-26 | 西北工业大学 | Centrifugal compressor and turbine blade integrated micro engine impeller disc |
| CN110985238A (en) * | 2019-12-31 | 2020-04-10 | 西北工业大学 | Variable working condition rocket engine capable of realizing height compensation |
| CN112829925A (en) * | 2021-03-22 | 2021-05-25 | 禹班工程科技(上海)有限公司 | Lift device for vertical take-off and landing of aircraft, aircraft and fixed-wing aircraft |
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| CN113716036A (en) | 2021-11-30 |
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