CN107972891A - A kind of Spacecraft Attitude Control and realization device using plasma flow control technology - Google Patents
A kind of Spacecraft Attitude Control and realization device using plasma flow control technology Download PDFInfo
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- CN107972891A CN107972891A CN201711210969.1A CN201711210969A CN107972891A CN 107972891 A CN107972891 A CN 107972891A CN 201711210969 A CN201711210969 A CN 201711210969A CN 107972891 A CN107972891 A CN 107972891A
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- control
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- plasma discharge
- discharge apparatus
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- 238000005516 engineering process Methods 0.000 title claims abstract description 16
- 238000005096 rolling process Methods 0.000 claims abstract description 9
- 230000008859 change Effects 0.000 claims description 5
- 230000009467 reduction Effects 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims 2
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 5
- 230000004888 barrier function Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 210000000078 claw Anatomy 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
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- 230000004044 response Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
- B64G1/245—Attitude control algorithms for spacecraft attitude control
Abstract
The invention discloses a kind of Spacecraft Attitude Control and realization device using plasma flow control technology, belong to plasma flow control technical field.The control method, which is included on wing and empennage, arranges plasma discharge apparatus；By controlling plasma discharge apparatus to discharge, pitch control, rolling control and the yaw control of aircraft are realized.The applicable flight range of the present invention is wide, small to aircraft flight state and structural requirement, simple in structure.By reasonably arranging plasma discharge apparatus in the present invention, lift can be increased single aerofoil or reduce resistance, aircraft manufacturing technology is realized by the lift difference between two aerofoils and resistance difference.Meanwhile this plasma control device can realize good control in high-altitude low-density, low dynamic pressure and big angles-of-attack, and meet the needs of stealthy, can control and be used in combination with traditional, pneumatic rudder face, or even substitute pneumatic rudder face control completely.
Description
Technical field
The invention belongs to plasma flow control technical field, and in particular to one kind utilizes plasma flow control skill
The Spacecraft Attitude Control and realization device of art.
Background technology
Aircraft realizes that gesture stability is generally controlled to realize using pneumatic rudder face at present, but the gas under many flying conditions
There are some drawbacks for dynamic rudder face control.Pneumatic rudder face control is by the flight pole such as flight environment of vehicle and flying drilling angle, maximum trim ang1e of attack
Parameter limitation is limited, in high-altitude low-density, low dynamic pressure or big angles-of-attack, rudder face control efficiency reduces even entirely ineffective；Gas
Dynamic rudder face is longer to the control instruction response time (being typically the magnitude of second), easily causes attitude regulation hysteresis, it is impossible to meet quick
Maneuvering flight requirement；In addition, by limitations such as construction weight, pneumatic solar heat protection, stealthy requirements, meeting many general design requirements
Under the premise of, gesture stability is carried out using pneumatic rudder face certain restriction is brought to pneumatic design.
The content of the invention
The present invention proposes that a kind of using plasma flow control technique realizes the scheme of aircraft manufacturing technology, main logical
Lift and resistance that plasma flow control technology changes aerofoil are crossed, is produced using the lift difference or resistance difference of different aerofoils
Operating torque.The generation of plasma of the present invention is produced using dielectric barrier discharge (DBD) device.
A kind of Spacecraft Attitude Control using plasma flow control technology of the present invention, including following step
Suddenly：
Step 1：Plasma discharge apparatus is arranged on wing and empennage.
The plasma discharge apparatus is to increase a bare electrode B on the basis of traditional DBD devices, described
Bare electrode B is arranged in the opposite side of buried electrodes, opposite with original bare electrode, and two bare electrodes are in parallel.
Step 2：Pitch control.For a kind of aircraft of normal arrangement, it is respectively arranged in horizontal tail upper and lower surface trailing edge
Plasma discharge device.Discharged by plasma discharge apparatus, form higher-pressure region on horizontal tail surface, change the lift of horizontal tail,
Aircraft pitch control is realized by the change of lift suffered by horizontal tail.
Step 3：Rolling controls.Surface trailing edge arrangement plasma discharge apparatus under the wings of an airplane, passes through unilateral plasma
Electric discharge device discharges, and higher-pressure region is formed under the wing of side, makes the side airfoil lift increase, realizes that aircraft rolls by lift difference
Turn control.
Step 4：Yaw control.Plasma discharge apparatus is arranged in wing upper and lower surface trailing edge, passes through unilateral plasma
Body electric discharge device discharges, and makes reduction one side wing drag, vehicle yaw control is realized by resistance difference.
The advantage of the invention is that：
(1) it is wide to be applicable in flight range.Plasma flow control Scheme of Attitude Control can make under different flying conditions
With.In each flight environment of vehicle and flying speed, plasma control apparatus effectively can realize attitude of flight vehicle by induced draft
Control.Plasma flow control Scheme of Attitude Control can be used under the different angles of attack.In Low Angle Of Attack, plasma control
Scheme realizes gesture stability using lift difference and resistance difference, and in the big angle of attack, plasma control apparatus can inhibit separation, at this time
Plasma control apparatus remains to realize gesture stability.
(2) it is small to aircraft flight state and structural requirement.Plasma control apparatus will not notable shadow when being not turned on
Aircraft performance is rung, the problems such as Stealth performance will not be destroyed after unlatching, extra Aerodynamic Heating will not be produced.Deng from
Daughter control device is not required to extra source of the gas or load mechanism, low to aircraft structural requirement itself.
(3) it is simple in structure.Plasma control apparatus no-movable part, weight and volume all very littles, will not change of flight
Think highly of the heart, manufacture cost is low.
(4) by reasonably arranging plasma discharge apparatus in the present invention, lift or reduction can be increased to single aerofoil
Resistance, aircraft manufacturing technology is realized by the lift difference between two aerofoils and resistance difference.Meanwhile this plasma control dress
Good control can be realized in high-altitude low-density, low dynamic pressure and big angles-of-attack by putting, and meet the needs of stealthy, can be with tradition
Pneumatic rudder face control is used in combination, or even substitutes pneumatic rudder face control completely.
Brief description of the drawings
Fig. 1 is plasma discharge apparatus structure diagram provided by the invention；
Fig. 2 is the position schematic diagram of plasma discharge device of the present invention；
Fig. 3 is that aircraft wing lower surface trailing edge arranges DBD schematic devices in embodiment 1.
Embodiment
The present invention is described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of method that aircraft manufacturing technology is carried out using plasma flow control technology, for normal
Advise layout aircraft, by arranging plasma discharge apparatus in wing and horizontal tail, using electric discharge device to aircraft lift and
The influence of resistance, realizes aircraft manufacturing technology.
Present invention employs the method for plasma flow flow control technique control attitude of flight vehicle, pass through reasonable Arrangement
Plasma discharge apparatus, electric discharge device meet to form penetrating along aerofoil normal direction along aerofoil induced jet, two strands along aerofoil jet stream
Stream, this jet stream retardance incoming, makes wing lower surface specific position form higher-pressure region and low-pressure area, make aircraft produce lift difference and
Resistance difference, realizes the control to attitude of flight vehicle under various flight conditions.
Spacecraft Attitude Control provided by the invention using plasma flow control technology, implements step
It is as follows：
Step 1：Plasma of the present invention is produced using dielectric barrier discharge (DBD) device.DBD devices in the present invention
Add a bare electrode B4 on traditional DBD devices to improve, as shown in Figure 1, traditional DBD devices are to be situated between
The both sides of matter layer 1 are respectively arranged buried electrodes 2 and bare electrode A3, and invention increases a bare electrode B4, described is naked
Dew electrode B 4 is arranged in the opposite side of buried electrodes 2, and opposite with original bare electrode A3, two bare electrode A3, B4 are in parallel.This
DBD devices substantially can be understood as two DBD devices are oppositely positioned together, make grade between two bare electrodes from
The air-flow counter current flow of daughter induction moves, and produces normal direction jet stream.On this basis, by reasonable Arrangement plasma discharge apparatus,
As shown in Fig. 2, electric discharge device is arranged in aerofoil, along aerofoil induced jet, two strands are met to be formed along aerofoil normal direction along aerofoil jet stream
Jet stream, this jet stream retardance incoming, makes aerofoil surface specific position form higher-pressure region and low-pressure area, aircraft is produced lift poor
And resistance difference, realize the control to attitude of flight vehicle under various flight conditions.
Step 2：Pitch control.For a kind of aircraft of normal arrangement, in both sides, horizontal tail upper and lower surface trailing edge distinguishes cloth
Put plasma discharge apparatus.Higher-pressure region is formed on horizontal tail surface by plasma discharge apparatus, changes the lift of horizontal tail, leads to
Aircraft pitch control is realized in the change for crossing lift suffered by horizontal tail.
Step 3：Rolling controls.Arrange plasma discharge apparatus in wing upper and lower surface trailing edge, by unilateral grade from
Daughter electric discharge device discharges, and higher-pressure region is formed under the wing of side, makes the side airfoil lift increase, passes through the lift of both sides wing
Difference realizes that aircraft rolling controls.
Step 4：Yaw control.Plasma discharge apparatus is arranged in wing upper and lower surface trailing edge, passes through unilateral wing
Plasma discharge apparatus discharges, and makes reduction one side wing drag, vehicle yaw control is realized by the resistance difference of two wings
System.
Embodiment 1：Rolling control is realized using Spacecraft Attitude Control provided by the invention, and carrier aircraft uses X-UAV
Claws of a hawk aircraft.Aeroplane span 1718mm, fuselage length 1100mm, wing area 54.5dm2, for the V tail carrier aircrafts of normal arrangement, use
80A electricity is adjusted, 3720-KV1200 motors, and 5200ma/h 4S1P batteries, flying weight 3KG, cruising speed is in 12m/s or so.Such as
Shown in Fig. 3, trailing edge arrangement in surface can use 3.6KV along the plasma discharge apparatus of wing normal direction air blowing under the wings of an airplane respectively
High-frequency ac power drives, and unilateral output power is in 120W or so.In-flight by it is differential startup both sides DBD devices, it can be achieved that
The rolling control of aircraft.In flight test, after aircraft enters experiment segment and leveling, DBD devices are separately turned on, aircraft can
Realization roll left turn or right rolling.The present invention can be well control aircraft roll attitude.
Claims (3)
- A kind of 1. Spacecraft Attitude Control using plasma flow control technology, it is characterised in that：Step 1：Plasma discharge apparatus is arranged on wing and empennage；Step 2：Pitch control：Plasma discharge apparatus is respectively arranged in horizontal tail upper and lower surface trailing edge, is put by plasma Electric installation discharges, and forms higher-pressure region on horizontal tail surface, changes the lift of horizontal tail, and flight is realized by the change of lift suffered by horizontal tail Device pitch control；Step 3：Rolling controls：Surface trailing edge arrangement plasma discharge apparatus under the wings of an airplane, passes through unilateral plasma discharge Device discharges, and higher-pressure region is formed under the wing of side, makes the side airfoil lift increase, aircraft rolling control is realized by lift difference System；Step 4：Yaw control：Plasma discharge apparatus is arranged in wing upper and lower surface trailing edge, is put by unilateral plasma Electric installation discharges, and makes reduction one side wing drag, vehicle yaw control is realized by resistance difference.
- 2. a kind of Spacecraft Attitude Control using plasma flow control technology according to claim 1, its It is characterized in that：The plasma discharge apparatus is to increase a bare electrode B on the basis of traditional DBD devices, described Bare electrode B be arranged in the opposite sides of buried electrodes, opposite with original bare electrode, two bare electrodes are in parallel.
- A kind of 3. Spacecraft Attitude Control realization device using plasma flow control technology, it is characterised in that：Institute Stating device includes being arranged in the plasma discharge apparatus of wing upper and lower surface trailing edge and horizontal tail upper and lower surface trailing edge, described etc. The both sides that plasma discharge device is included in dielectric layer are respectively arranged buried electrodes and bare electrode A, and bare electrode B, institute The bare electrode B stated is arranged in the opposite side of buried electrodes, opposite with bare electrode A, and two bare electrode A, B are in parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711210969.1A CN107972891A (en) | 2017-11-28 | 2017-11-28 | A kind of Spacecraft Attitude Control and realization device using plasma flow control technology |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711210969.1A CN107972891A (en) | 2017-11-28 | 2017-11-28 | A kind of Spacecraft Attitude Control and realization device using plasma flow control technology |
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| CN107972891A true CN107972891A (en) | 2018-05-01 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111511089A (en) * | 2020-06-17 | 2020-08-07 | 沈阳航空航天大学 | Method for realizing equipment stealth by using plasma jet |
| CN111683447A (en) * | 2020-06-17 | 2020-09-18 | 沈阳航空航天大学 | Electrode arrangement structure for realizing uniform distribution of surface plasmas of equipment |
| WO2021135067A1 (en) * | 2019-12-31 | 2021-07-08 | 浙江大学 | Electrohydrodynamic-based environmentally-adaptable bladeless aircraft and control method therefor |
| CN114291252A (en) * | 2022-01-27 | 2022-04-08 | 北京航空航天大学 | Aircraft three-axis attitude control system and method |
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| CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
| US8016247B2 (en) * | 2007-05-25 | 2011-09-13 | The Boeing Company | Plasma flow control actuator system and method |
| CN102602541A (en) * | 2012-03-20 | 2012-07-25 | 南京航空航天大学 | Method for using plasma exciters to control aircraft attitude |
-
2017
- 2017-11-28 CN CN201711210969.1A patent/CN107972891A/en not_active Withdrawn
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8016247B2 (en) * | 2007-05-25 | 2011-09-13 | The Boeing Company | Plasma flow control actuator system and method |
| CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
| CN102602541A (en) * | 2012-03-20 | 2012-07-25 | 南京航空航天大学 | Method for using plasma exciters to control aircraft attitude |
Non-Patent Citations (1)
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| 杜海: "等离子体流动控制技术及其在飞行器上的应用研究", 《中国优秀硕士学位论文全文数据库工程科技II辑》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021135067A1 (en) * | 2019-12-31 | 2021-07-08 | 浙江大学 | Electrohydrodynamic-based environmentally-adaptable bladeless aircraft and control method therefor |
| CN111511089A (en) * | 2020-06-17 | 2020-08-07 | 沈阳航空航天大学 | Method for realizing equipment stealth by using plasma jet |
| CN111683447A (en) * | 2020-06-17 | 2020-09-18 | 沈阳航空航天大学 | Electrode arrangement structure for realizing uniform distribution of surface plasmas of equipment |
| CN114291252A (en) * | 2022-01-27 | 2022-04-08 | 北京航空航天大学 | Aircraft three-axis attitude control system and method |
| CN114291252B (en) * | 2022-01-27 | 2024-02-27 | 北京航空航天大学 | Three-axis attitude control system and method for aircraft |
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Application publication date: 20180501 |
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