CN110775296A - Design method for pressure center backward movement of reusable aerospace vehicle - Google Patents
Design method for pressure center backward movement of reusable aerospace vehicle Download PDFInfo
- Publication number
- CN110775296A CN110775296A CN201911100957.2A CN201911100957A CN110775296A CN 110775296 A CN110775296 A CN 110775296A CN 201911100957 A CN201911100957 A CN 201911100957A CN 110775296 A CN110775296 A CN 110775296A
- Authority
- CN
- China
- Prior art keywords
- aerospace vehicle
- design method
- pressure center
- reusable
- retropulsion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/14—Space shuttles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a design method for the pressure center backward movement of a reusable aerospace vehicle. By adopting the design method for the pressure center backward movement of the reusable aerospace vehicle, the pressure center of the aerospace vehicle can be backward moved, and the pitching stability of the aerospace vehicle under different flight conditions can be adjusted.
Description
Technical Field
The invention relates to a design method for pressure center backward movement of a reusable aerospace vehicle, in particular to a design method for enhancing the pitching stability margin of the reusable aerospace vehicle based on a pitching stabilizer plate, and belongs to the technical field of aircrafts.
Background
The reusable aerospace vehicle is a novel aircraft with aviation and aerospace functions, and can flexibly maneuver on the atmosphere and a near-earth orbit according to different task requirements. The reusable aerospace vehicle flies higher and faster than a traditional airplane, is more flexible and reusable than a common spacecraft, can meet the fundamental requirement of entering space quickly and cheaply, and can reach the space in real time in the global range. Therefore, the reusable aerospace vehicle has become a strategic high point of competing for the emphatic right and space advantage of the aerospace countries in the world.
In addition to the retired partially reusable space shuttle, the development of the space shuttle in various countries of the world is still in the research and verification stage, and currently, the research projects mainly include space orbit aircraft X-37B in the united states, trial space shuttle XS-1, skis tower Skylon in the united kingdom, reusable vehicle technology verifier RLV-TD in india, and "tengyun" engineering in china. Among them, the X-37B tester, as the latest and most advanced reentry vehicle in the united states air force, mainly serves to provide a low-risk technology for the reusable spacecraft, and to develop some novel experimental methods and unconventional operational concepts, which have been regarded as a key component for maintaining the future space dominance in the united states. From 2011, X-37B performed a total of 5 orbital missions (all completed, last return in 2019 at 10 and 27 days, and on-orbit operation for 780 days), and planned to perform the 6 th orbital mission in 2019 at 11 months.
For the reusable aerospace vehicle, the special requirements of lift-drag matching, stability-operating matching and the like of a wide airspace and a wide speed range provide important challenges for the aerodynamic layout design of the aerospace vehicle. When an aerospace plane represented by American X-37B flies again in the atmosphere, the flight Mach number range is 0.2 to 25, the attack angle variation range is 5 to 40 degrees, and the pressure center position of the aerospace plane is greatly changed due to the wide flight speed and attitude adjustment, so that the aerospace plane is difficult to simultaneously consider the longitudinal stability of hypersonic speed and sub/transonic speed when the aerodynamic layout of the aerospace plane is designed. In order to ensure the aerodynamic performance and the heat protection requirement of a high-Mach number flight state, the aerodynamic configuration of the aerospace plane mainly adopts the typical wing body assembly layout with a low-aspect-ratio sweepback wing and a V-shaped empennage, the wing is positioned in the middle section of the plane body, and the pitching trim control is carried out by using the body flap of the aerospace plane for reference. Relevant researches show that under the conditions of medium and low Mach number and medium angle flight, the static stability margin may be insufficient even if the air-borne spacecraft is fully optimized under the original aerodynamic layout because the pressure center of the air-borne spacecraft is relatively forward.
Disclosure of Invention
The invention aims to: aiming at the existing problems, the invention provides a design method for the pressure center backward movement of the reusable aerospace vehicle.
The technical scheme adopted by the invention is as follows:
a design method for repeatedly using a pressure center of an aerospace vehicle to move backwards is characterized in that a pair of pitching stabilizing plates are symmetrically arranged on two sides of a tail section of a fuselage of the aerospace vehicle, the pitching stabilizing plates are connected with the fuselage through rudder shafts, and the pitching stabilizing plates can rotate around the rudder shafts, so that the switching of an opening mode and a retracting mode of the pitching stabilizing plates is realized.
In the scheme, the pitching stabilizing plate rotates around the rudder shaft, and when the pitching stabilizing plate is tightly attached to the side edge of the aircraft body, the pitching stabilizing plate is in a retraction mode, so that the basic aerodynamic layout of the aerospace aircraft can be maintained; when the pitching stabilizing plate is turned outwards by 90 degrees around the rudder axis and is unfolded into a movable part similar to a stable airfoil surface, the opening mode is adopted, and because the pitching stabilizing plate is vertical to the incoming flow, the generated resistance can be completely used for forming low head moment so as to move the pressure center position backwards to the maximum extent, thereby improving the pitching static stability margin of the aerospace vehicle.
Preferably, the installation azimuth angle of the rudder shaft is selected according to the flight attack angle of the pitching stabilizing plate in the opening mode.
Preferably, the installation azimuth angle of the rudder shaft is 20-30 degrees.
Preferably, when the aerospace vehicle reenters the flight process, the flight Mach number is 3-5, and the flight attack angle is 20 +/-5 degrees, the pitching stabilizing plate is in an opening mode; and under other flight states, the pitching stabilizing plate is in a retraction mode.
The pitching stabilizing plate is supported by the steering engine arranged in the fuselage and is in an opening mode, and the pitching stabilizing plate is in a retracting mode in other flight states.
Preferably, the pitch stabilising plate is aligned with the aft end of the aerospace vehicle in the stowed mode.
Preferably, the pitch stabilising plate is trapezoidal.
Preferably, the pitch stabilising plate is a right angle pentagon.
Preferably, the basic aerodynamic layout of the aerospace vehicle adopts a method (CST) based on a type function and a shape function for parametric shape generation.
Preferably, the aerospace vehicle comprises a head, a fuselage, wings, flaperons, a speed reduction plate, a tail wing and body flaps; the wings are positioned on two sides of the aircraft body, the flaperons are positioned on the rear edges of the wings, the empennages are positioned at the tail of the aircraft body, the speed reducing plate is positioned between the pair of empennages, and the body flaps are positioned at the rear part of the aerospace aircraft.
Preferably, the head is designed to be a blunt sphere, the fuselage is designed to be a semicircular and inverted square section, the wings are double-triangular wings formed by combining a long and thin strake wing and a short triangular wing, and the flaperon is designed to be a full-span wing.
According to the design method for the pressure center backward movement of the reusable aerospace vehicle, disclosed by the invention, in order to solve the problem of serious pneumatic heating in the high-speed reentry process, the head part adopts a blunt sphere design, and the body adopts a semicircular and inverted square section, so that the volume utilization rate can be fully ensured; the wings on two sides are double delta wings formed by combining a long and thin strake wing and a short delta wing, the double delta wings have better hypersonic lift-drag characteristics, and the trailing edges of the wings are provided with flaperons with full wingspans to implement roll control; the speed reduction plate for tail end energy management and resistance control in an approach landing stage is positioned between a pair of V-shaped empennages, the V-shaped empennages have the functions of a rudder and an elevator, and meanwhile, the back of the aircraft is provided with a body flap, so that pitching trim under a large attack angle flight state is mainly realized.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. in the pitching stable plate opening mode, because the pitching stable plate is perpendicular to the incoming flow when in use, the generated resistance can be used for forming a low head moment to move the pressure center position backwards to the maximum extent, so that the pitching static stability margin of the aerial vehicle is improved.
2. Compared with conventional pitching stability enhancement schemes such as body flap growth, body flap widening and horizontal stabilizing wing adding, the pitching stabilizing plate can be retracted when not in use, no additional aerodynamic force is generated at the moment, the aerodynamic characteristics and the aerodynamic data use of the original scheme are not influenced, and the pitching stabilizing plate is particularly suitable for improving the aerodynamic performance of the aircraft at a specific flight stage; under the condition of achieving the same pitch stability enhancing effect, the design scale of the scheme is relatively small.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a mechanism for the aerospace vehicle based on the rearward displacement of a pressure core of a pitch stabilizing plate;
FIG. 2 is a schematic view of a pitch stabilizer blade opening pattern;
FIG. 3 is a schematic view of a pitch stabilizer stow mode;
FIG. 4 is a schematic view of a pitch stabilizer plate configuration;
FIG. 5 is another schematic view of the pitch stabilizer plate configuration;
fig. 6 is a three-view illustration of an aerospace vehicle with pitch stabilizer.
The labels in the figure are: the rudder shaft is connected with the edges of the 1-head part, the 2-fuselage part, the 3-wing part, the 4-flaperon part, the 5-speed reducing plate, the 6-empennage part, the 7-body flap part, the 8-pitching stable plate and the 9-pitching stable plate.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
Example 1
The basic aerodynamic layout of the aerospace vehicle in the embodiment adopts a method (CST) based on a type function and a shape function to carry out parametric shape generation, and the number of design parameters is more than 50. Wherein, the basic parameters are selected as follows: the total length of the fuselage is 8.9 meters, the total width of the fuselage is 4.3 meters, the total height of the fuselage is 2.9 meters, and the radius of the head is 0.3 meter; the wing root of the wing is 3.5 meters long and 1.5 meters wide; the total length of the V-shaped empennage is 1.6 meters, and the width of the V-shaped empennage is 0.8 meter; the length of the body flap is 0.8 meter, the width is 1.3 meters, and the thickness is 0.2 meter.
A pair of trapezoidal pitching stabilizing plates are symmetrically arranged on two sides of the tail section of the aircraft body of the aerospace vehicle, the pitching stabilizing plates are connected with the aircraft body through rudder shafts, the connecting edges of the pitching stabilizing plates and the rudder shafts are trapezoidal waists, and the pitching stabilizing plates are aligned with the tail end of the aerospace vehicle in a retraction mode. The basic parameters of the trapezoidal pitching stabilizer plate are as follows: lower bottom edge L
01.5 m, upper bottom edge L
1The height H is 1.0 meter, the installation azimuth angle theta of the rudder shaft is 30 degrees, and the effective infiltration area is 1.8 square meters.
According to the design method for the reusable aerospace vehicle pressure center backward shift, under the conditions that the flight Mach number is 4 and the flight attack angle is 25 degrees, when the machine side pitching stabilizing plate is changed from the retraction mode to the opening mode, the pressure center of the aerospace vehicle can be shifted backward by 1% of the total length of the aircraft body.
Example 2
The basic aerodynamic layout of the aerospace vehicle in the embodiment adopts a method (CST) based on a type function and a shape function to carry out parametric shape generation, and the number of design parameters is more than 50. Wherein, the basic parameters are selected as follows: the total length of the fuselage is 8.9 meters, the total width of the fuselage is 4.3 meters, the total height of the fuselage is 2.9 meters, and the radius of the head is 0.3 meter; the wing root of the wing is 3.5 meters long and 1.5 meters wide; the total length of the V-shaped empennage is 1.6 meters, and the width of the V-shaped empennage is 0.8 meter; the length of the body flap is 0.8 meter, the width is 1.3 meters, and the thickness is 0.2 meter.
Set up a pair of right angle pentagon every single move stabilising plate in aerospace vehicle fuselage tail section bilateral symmetry, every single move stabilising plate passes through the rudder axle and is connected with the fuselage, and every single move stabilising plate is the hypotenuse of right angle pentagon with the connection limit of rudder axle, and every single move stabilising plate aligns with aerospace vehicle's tail end under the mode of packing up. The basic parameters of the right-angle pentagonal pitch stabilizing plate are as follows: bottom edge L
01.5 m, the height H of the rudder shaft from the bottom edge
1The height H is 0.5 m, the total height H is 1.3 m, the installation azimuth angle theta of the rudder shaft is 30 degrees, and the effective infiltration area is 3.0 square meters.
According to the design method for the reusable aerospace vehicle pressure center backward movement, under the conditions that the flight Mach number is 4 and the flight attack angle is 25 degrees, when the machine side pitching stabilizing plate is changed from the retraction mode to the opening mode, the pressure center of the aerospace vehicle can move backward by about 2% of the total length of the aircraft body.
In conclusion, by adopting the design method for the pressure center backward movement of the reusable aerospace vehicle, the pressure center of the aerospace vehicle can be backward moved, and the pitching stability of the aerospace vehicle under different flight conditions can be adjusted.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (10)
1. A design method for the pressure center backward movement of a reusable aerospace vehicle is characterized by comprising the following steps: a pair of pitching stabilizing plates are symmetrically arranged on two sides of the tail section of the aircraft body of the aerospace vehicle, the pitching stabilizing plates are connected with the aircraft body through rudder shafts, and the pitching stabilizing plates can rotate around the rudder shafts, so that the switching between the opening mode and the retracting mode of the pitching stabilizing plates is realized.
2. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: and the installation azimuth angle of the rudder shaft is selected according to the flight attack angle of the pitching stabilizing plate in the starting mode.
3. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the installation azimuth angle of the rudder shaft is 20-30 degrees.
4. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: and in the process of reentry flight of the aerospace vehicle, the flight Mach number is 3-5, and when the flight attack angle is 20 +/-5 degrees, the pitching stabilizing plate is in an opening mode.
5. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the pitch stabilizer plate is aligned with the aft end of the aerospace vehicle in the stowed mode.
6. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the pitching stabilizing plate is trapezoidal.
7. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the pitching stabilizing plate is a right-angle pentagon.
8. The design method for the pressure center retropulsion of the reusable aerospace vehicle as claimed in claim 1, wherein: the basic aerodynamic layout of the aerospace vehicle adopts a method (CST) based on a type function and a shape function to carry out parametric shape generation.
9. The design method for the pressure center retropulsion of the reusable aerospace vehicle of claim 8, wherein: the aerospace craft comprises a head, a fuselage, wings, flaperons, a speed-reducing plate, a tail wing and a body flap; the wings are positioned on two sides of the aircraft body, the flaperons are positioned on the rear edges of the wings, the empennages are positioned at the tail of the aircraft body, the speed reducing plate is positioned between the pair of empennages, and the body flaps are positioned at the rear part of the aerospace aircraft.
10. The design method for the pressure center retropulsion of the reusable aerospace vehicle of claim 9, wherein: the head is designed to be a blunt sphere, the fuselage is designed to be a semicircular and inverted square section, the wings are double triangular wings formed by combining a long and thin edge wing and a short triangular wing, and the flaperon is designed to be a full span.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911100957.2A CN110775296A (en) | 2019-11-12 | 2019-11-12 | Design method for pressure center backward movement of reusable aerospace vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911100957.2A CN110775296A (en) | 2019-11-12 | 2019-11-12 | Design method for pressure center backward movement of reusable aerospace vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110775296A true CN110775296A (en) | 2020-02-11 |
Family
ID=69390478
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911100957.2A Pending CN110775296A (en) | 2019-11-12 | 2019-11-12 | Design method for pressure center backward movement of reusable aerospace vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110775296A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112678206A (en) * | 2020-12-29 | 2021-04-20 | 中国航天空气动力技术研究院 | Pneumatic layout structure and design method of reusable carrier |
| CN112829907A (en) * | 2020-12-16 | 2021-05-25 | 江苏华阳重工股份有限公司 | Steering device of submarine |
| CN115231005A (en) * | 2022-09-24 | 2022-10-25 | 北京星途探索科技有限公司 | Locking and releasing device for wave-rider aircraft with vortex effect |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1332026A (en) * | 1971-08-07 | 1973-10-03 | British Aircraft Corp Ltd | Aircraft |
| GB1416342A (en) * | 1972-02-04 | 1975-12-03 | Senhenn L A | Fixed-wing dual-purpose aeroplanes |
| US4440362A (en) * | 1980-07-16 | 1984-04-03 | Walker Robert A | Two-axis rudder trim for aircraft |
| US5813628A (en) * | 1996-05-13 | 1998-09-29 | Redwood Aircraft Corporation | Lifting-fuselage/wing aircraft having low induced drag |
| US6732974B1 (en) * | 1997-11-19 | 2004-05-11 | Accurate Automation Corporation | Tiperon |
| WO2005044661A2 (en) * | 2003-08-29 | 2005-05-19 | Supersonic Aerospace International, Inc. | Supersonic aircraft with aerodynamic control |
| RU2005140386A (en) * | 2005-12-26 | 2007-07-10 | Открытое акционерное общество "Ракетно-космическа корпораци "Энерги " имени С.П. Королева" (RU) | SPACE VEHICLE FOR DOWNLOAD FROM THE ORBIT OF THE ARTIFICIAL SATELLITE OF THE EARTH AND THE METHOD OF ITS DEPARTURE FROM THE ORBIT OF THE ARTIFICIAL SATELLITE OF THE EARTH |
| US8434712B1 (en) * | 2011-01-12 | 2013-05-07 | Lockheed Martin Corporation | Methods and apparatus for driving rotational elements of a vehicle |
| CN105659735B (en) * | 2009-07-15 | 2013-08-14 | 北京航空航天大学 | A kind of reuse aircraft across atmosphere aerodynamic arrangement |
| CN203512023U (en) * | 2013-10-27 | 2014-04-02 | 中国航空工业集团公司哈尔滨空气动力研究所 | Pitching control rudder surface on tail of airframe of airplane |
| CN105667764A (en) * | 2016-03-07 | 2016-06-15 | 邓冠柔 | Rotating-tail type morphing aircraft |
| CN108100212A (en) * | 2018-01-29 | 2018-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of adaptive response body Flying-wing fighter plane of low aspect ratio |
| CN109747860A (en) * | 2019-03-08 | 2019-05-14 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of grid rudder wing suitable for canister launch mixes aerodynamic arrangement and design method |
-
2019
- 2019-11-12 CN CN201911100957.2A patent/CN110775296A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1332026A (en) * | 1971-08-07 | 1973-10-03 | British Aircraft Corp Ltd | Aircraft |
| GB1416342A (en) * | 1972-02-04 | 1975-12-03 | Senhenn L A | Fixed-wing dual-purpose aeroplanes |
| US4440362A (en) * | 1980-07-16 | 1984-04-03 | Walker Robert A | Two-axis rudder trim for aircraft |
| US5813628A (en) * | 1996-05-13 | 1998-09-29 | Redwood Aircraft Corporation | Lifting-fuselage/wing aircraft having low induced drag |
| US6732974B1 (en) * | 1997-11-19 | 2004-05-11 | Accurate Automation Corporation | Tiperon |
| WO2005044661A2 (en) * | 2003-08-29 | 2005-05-19 | Supersonic Aerospace International, Inc. | Supersonic aircraft with aerodynamic control |
| RU2005140386A (en) * | 2005-12-26 | 2007-07-10 | Открытое акционерное общество "Ракетно-космическа корпораци "Энерги " имени С.П. Королева" (RU) | SPACE VEHICLE FOR DOWNLOAD FROM THE ORBIT OF THE ARTIFICIAL SATELLITE OF THE EARTH AND THE METHOD OF ITS DEPARTURE FROM THE ORBIT OF THE ARTIFICIAL SATELLITE OF THE EARTH |
| CN105659735B (en) * | 2009-07-15 | 2013-08-14 | 北京航空航天大学 | A kind of reuse aircraft across atmosphere aerodynamic arrangement |
| US8434712B1 (en) * | 2011-01-12 | 2013-05-07 | Lockheed Martin Corporation | Methods and apparatus for driving rotational elements of a vehicle |
| CN203512023U (en) * | 2013-10-27 | 2014-04-02 | 中国航空工业集团公司哈尔滨空气动力研究所 | Pitching control rudder surface on tail of airframe of airplane |
| CN105667764A (en) * | 2016-03-07 | 2016-06-15 | 邓冠柔 | Rotating-tail type morphing aircraft |
| CN108100212A (en) * | 2018-01-29 | 2018-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of adaptive response body Flying-wing fighter plane of low aspect ratio |
| CN109747860A (en) * | 2019-03-08 | 2019-05-14 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of grid rudder wing suitable for canister launch mixes aerodynamic arrangement and design method |
Non-Patent Citations (2)
| Title |
|---|
| 唐伟，曾磊，冯毅，肖光明，桂业伟: "升力体机动飞行器气动布局概念设计", 《空气动力学学报》 * |
| 彭悟宇，杨涛，涂建秋，丰志伟，张斌: "高超声速变形飞行器翼面变形模式分析", 《国防科技大学学报》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112829907A (en) * | 2020-12-16 | 2021-05-25 | 江苏华阳重工股份有限公司 | Steering device of submarine |
| CN112678206A (en) * | 2020-12-29 | 2021-04-20 | 中国航天空气动力技术研究院 | Pneumatic layout structure and design method of reusable carrier |
| CN115231005A (en) * | 2022-09-24 | 2022-10-25 | 北京星途探索科技有限公司 | Locking and releasing device for wave-rider aircraft with vortex effect |
| CN115231005B (en) * | 2022-09-24 | 2022-12-20 | 北京星途探索科技有限公司 | Locking and releasing device for wave-rider aircraft with vortex wave effect |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7854409B2 (en) | Canarded deltoid main wing aircraft | |
| US9440740B2 (en) | Oblique blended wing body aircraft | |
| CN202279235U (en) | Variant canard tailless aerodynamic configuration | |
| CN105775117B (en) | A kind of helicopter of VTOL horizontal flight and its application | |
| CN102336267B (en) | Rotor blade airplane with variable flight mode | |
| CN103963972B (en) | What a kind of wing tip docked can oblique wing all-wing aircraft Unmanned Aircraft Systems (UAS) in parallel | |
| US9561844B2 (en) | System and method for an air vehicle | |
| CN110775296A (en) | Design method for pressure center backward movement of reusable aerospace vehicle | |
| WO2012026846A1 (en) | Aircraft with an integral aerodynamic configuration | |
| US20160009391A1 (en) | Stable Low Aspect Ratio Flying Wing | |
| CN105366049A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN108045575A (en) | A kind of short takeoff vertical landing aircraft | |
| CN105882961A (en) | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft | |
| CN103171766A (en) | Short distance rising and landing unmanned all-wing aircraft | |
| CN110104160B (en) | Middle-distance coupling folding double-wing aircraft | |
| US20070278354A1 (en) | Slotted high lift aerofoils | |
| CN108082471A (en) | A kind of variant supersonic plane | |
| CN106828918A (en) | A kind of Three-wing-surface vertically taking off and landing flyer | |
| US8262017B2 (en) | Aircraft with forward lifting elevator and rudder, with the main lifting surface aft, containing ailerons and flaps, and airbrake | |
| Polhamus | Applying slender wing benefits to military aircraft | |
| CN103754360A (en) | Similar flying saucer type rotaplane | |
| CN103523223A (en) | Transverse course control system and transverse course control method for flying wing configuration | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN116186904B (en) | Mechanical overall aerodynamic layout method with lifting surface moving in fluid | |
| CN207089635U (en) | The flight control system of the stealthy unmanned plane of Flying-wing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |