CN114162349A - Parallelly connected repeatedly usable's two-stage rail aircraft with pneumatic integrated configuration - Google Patents
Parallelly connected repeatedly usable's two-stage rail aircraft with pneumatic integrated configuration Download PDFInfo
- Publication number
- CN114162349A CN114162349A CN202210131377.5A CN202210131377A CN114162349A CN 114162349 A CN114162349 A CN 114162349A CN 202210131377 A CN202210131377 A CN 202210131377A CN 114162349 A CN114162349 A CN 114162349A
- Authority
- CN
- China
- Prior art keywords
- wing
- stage
- aircraft
- level
- wave
- 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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
Abstract
The invention discloses a parallel reusable two-stage orbit entering aircraft with a pneumatic combination structure, which comprises a boosting stage aircraft and a rail stage aircraft, wherein the upper surface of the boosting stage aircraft is provided with a guide plane for mounting the rail stage aircraft, the guide plane is along the length direction of boosting stage flight, and the guide plane is seamlessly attached to the lower surface of the rail stage aircraft. The invention constructs a boosting level wave-rider matrix and a track level wave-rider in a two-stage in-orbit horizontal separation mode, and adds a deformable wing and the pneumatic layout of a vertical tail wing rudder to the boosting level wave-rider matrix, so that the pneumatic combination structure of the two-stage in-orbit aircraft has good wide-speed-range pneumatic performance and stability, the technical risk of interstage separation is effectively reduced, and the two-stage in-orbit aircraft can be used as a scheme of a transport shuttle aircraft in the field of reusable aerospace.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a two-stage orbit entering aircraft with a pneumatic combined structure, which is connected in parallel and can be repeatedly used.
Background
Since the last 80 s, the united states proposed a permanent space station project, with countries around the world demanding thousands of times to transport personnel, supplies and equipment to the space station every year, with the traditional disposable launch vehicles, state airships or space shuttles costing billions of dollars. Such high space launch costs have led countries around the world to have vigorously developed reusable space-to-ground transport shuttle systems, including Sanger two-stage orbital vehicles in Germany in the 90 s, partially reusable aerospace rail vehicles X-37b in the United states, the Boeing two-stage orbital approach, and TSTO Reference Vehicle by NASA, among others.
The reusable world transportation shuttle system comprises single-stage track entering, two-stage track entering and multi-stage track entering. Generally, the single-stage rail entering can reduce the launching cost to the maximum, but the requirement on a power propulsion system of an engine is very high, the existing propulsion system is difficult to meet the requirement, and the technical risk is very high; the multistage orbit entering aircraft increases the interstage separation times and improves the technical risk; the two-stage orbit-entering aircraft has lower requirements on a propulsion system, good economy, high efficiency and high reliability, can be completely reused, is the most practical reusable world transportation shuttle system at present, and becomes a large engineering project which is researched by the world in advance. For the development of the current propulsion system, the reusable rocket power is in reality, and the wide-speed-range air-breathing engine has made a great breakthrough, so that the horizontal take-off and landing two-stage orbit aircraft composed of the air-breathing combined power boosting stage and the rocket power orbit stage is expected to make a great progress in nearly two-thirty years.
The two-stage orbit entering aircraft needs to fly in a wide speed range from subsonic velocity to hypersonic velocity, so that the boosting stage aircraft needs to have excellent lift-drag ratio pneumatic performance in the wide speed range under the condition of limited thrust-weight ratio, the two-stage orbit entering aircraft can quickly climb and accelerate to an interstage separation point, and the boosting stage needs to have wide speed range assisted stability operation matching. For the orbit stage, after the interstage separation, the rail needs to quickly climb into a target orbit under the power of a rocket, so that the rail needs to have large capacity and carry enough fuel while carrying people and goods. Most importantly, the vertical separation, which is a conventional interstage separation mode, can generate complex aerodynamic interference in the hypersonic interstage separation process, generate high-pressure and high-heat flow areas on two-stage surfaces, and influence the flight stability in the separation process by unsteady aerodynamic loads. In response to these significant technical challenges and problems, the present invention provides a reusable two-stage in-orbit aircraft with a pneumatic combined structure in parallel.
Disclosure of Invention
The invention aims to provide a parallel reusable two-stage orbit entering aircraft with a pneumatic combination structure, which consists of a reusable booster-stage aircraft with a wide-speed-range self-adaptive deformation wing and a triangular sweepback wing aerospace plane orbit stage, and effectively solves the technical problems in the background technology.
In order to solve the technical problems, the invention specifically provides the following technical scheme:
a two-stage in-orbit aircraft with a pneumatic combined structure and capable of being repeatedly used in parallel comprises a boosting stage aircraft and a track stage aircraft, wherein a guide plane for mounting the track stage aircraft is arranged on the upper surface of the boosting stage aircraft, the guide plane is arranged along the length direction of the boosting stage aircraft, and the guide plane is seamlessly attached to the lower surface of the track stage aircraft;
the boost-level aircraft comprises a boost-level wave rider base body and deformable wings arranged on two sides of the boost-level wave rider base body, wherein a boost-level aileron and a boost-level wing flap are arranged on the surfaces of the deformable wings, which are close to the rear end surface of the boost-level wave rider base body, two boost-level vertical tail wings are arranged on the boost-level wave rider base body in a mirror symmetry manner, and a boost-level tail wing rudder is arranged on the boost-level vertical tail wing;
the track-level aircraft comprises a track-level wave-rider and a fairing arranged at the front end of the track-level wave-rider, triangular sweepback wings are arranged on two sides of the track-level wave-rider, the bottom surfaces of the triangular sweepback wings are seamlessly attached to the guide plane, track-level ailerons and track-level flaps are arranged on the surfaces, close to the rear end face of the track-level wave-rider, of the triangular sweepback wings, a track-level vertical tail wing is arranged in the middle of the top of the track-level wave-rider, the track-level vertical tail wing extends along the length direction of the track-level wave-rider, and a track-level tail wing rudder is arranged at the end, close to the rear end face of the track-level wave-rider, of the track-level vertical tail wing.
As a preferable aspect of the present invention, the deformable wing extends from a midpoint of leading edge curves on both sides of the boost-level waverider base body to a rear end surface of the boost-level waverider base body and expands in a width direction of the boost-level waverider base body until an end of the deformable wing is in agreement with the rear end surface of the boost-level waverider base body;
the outer edge of the deformable wing keeps smooth tangency with the leading edge curves of the two sides of the boosting level wave-multiplying matrix.
As a preferable scheme of the invention, the deformable wing comprises a fixed wing section and a deformable wing section connected to the fixed wing section, the side edge of the fixed wing section, which is far away from the deformable wing section, is rotatably connected to the side edge of the boost-level wave-rider base body through a connecting rod, and a second steering engine for driving the fixed wing section to rotate around the connecting rod is arranged in the boost-level wave-rider base body;
the deformation wing section comprises a hollow skin wing body and a wing rib plate group arranged inside the hollow skin wing body, the wing rib plate group comprises a plurality of wing ribs which are distributed at equal intervals along the width direction of the hollow skin wing body, and the lengths of the wing ribs are matched with the length of the hollow skin wing body;
every the wing rib is connected with a telescopic connecting rod at least, just telescopic connecting rod follows the width direction of the cavity covering wing body extends to fixed wing section, be provided with in the fixed wing section and connect telescopic connecting rod's first steering wheel, just first steering wheel control telescopic connecting rod is in the width direction change of cavity covering wing body, and then control adjacent two distance between the wing rib.
According to a preferable scheme of the invention, the surface of the hollow skin wing body is coated with an aerodynamic force sensing layer, the aerodynamic force sensing layer sequentially comprises a carbon fiber layer and a glass fiber layer from inside to outside, and a pressure sensor network layer is distributed between the carbon fiber layer and the glass fiber layer.
As a preferred scheme of the invention, a deformation wing control module, an aerodynamic force measuring and calculating module, a wing sweep angle control module and a wing dihedral control module are further arranged in the boosting level wave-rider base body;
the aerodynamic force measuring and calculating module is used for acquiring aerodynamic force data received by the deformable wing in the flying process through the pressure sensor network layer;
the deformation wing control module receives aerodynamic force data of the aerodynamic force measuring and calculating module and sends control instructions to the wing sweep angle control module and the wing dihedral angle control module;
the wing dihedral angle control module controls the second steering engine to drive the connecting rod to rotate through a control instruction, and changes the upper dihedral angle and the lower dihedral angle of the boosting-level aircraft;
the wing sweep angle control module controls the first steering engine to drive the length of the telescopic connecting rod to change through a control command, and changes the span width of the deformed wing section;
the wing sweep angle control module is used for sending aerodynamic force measurement and calculation signals to the aerodynamic force measurement and calculation module after the wing dihedral angle control module completes the upper dihedral angle and the lower dihedral angle of the booster-class aircraft, and the wing sweep angle control module changes the span width of the deformed wing section and changes the sweep angle of the booster-class aircraft.
In a preferred embodiment of the present invention, the lower surface of the booster stage waverider base includes a waverider surface obtained by tracing a leading edge curve of the booster stage waverider base by a streamline, and a horizontal cut surface formed by horizontally cutting the head of the booster stage waverider base from a rear end surface of the booster stage waverider base.
As a preferred embodiment of the present invention, the baseline profile of the boost-level waverider base body specifically includes a horizontal line segment and first parabolic line segments smoothly tangent to and connected to both ends of the horizontal line segment, the first parabolic line segments located at both ends of the horizontal line segment are mirror-symmetric, the end portions of the first parabolic line segments far away from the horizontal line segment are smoothly tangent to and connected with second parabolic line segments, and the second parabolic line segments located at both sides of the horizontal line segment are mirror-symmetric;
and the guide plane is formed by a free flow surface generated by the horizontal line segment in the supersonic circular cone reference flow field model.
As a preferable aspect of the present invention, the booster-stage vertical tail is perpendicular to the upper surface of the booster-stage wave-rider base body formed by the first parabolic segment, and the booster-stage vertical tail and the first parabolic segment are in agreement with each other in the projection direction of the supersonic velocity around the conical reference flow field model, and one end of the booster-stage vertical tail is in agreement with the rear end surface of the booster-stage wave-rider base body.
As a preferable mode of the present invention, a horizontal guide rail on which the track-level wave multiplier is mounted is provided in the middle of the guide plane, and the horizontal guide rail positions the center of mass of the boosting-level wave multiplier base body and the center of mass of the track-level wave multiplier in the same normal direction.
As a preferable aspect of the present invention, the fairing includes two half-cone cover bodies connected in a mirror image manner, the two half-cone cover bodies are connected by a first separation explosive bolt, and the two half-cone cover bodies are connected with the head of the track-level wave multiplier by a second separation explosive bolt.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides a two-stage orbit entering aircraft with a pneumatic combined structure, which is connected in parallel and can be repeatedly used; the boosting-level pneumatic layout adopts a wide-speed-range self-adaptive variable wing reusable boosting-level aircraft pneumatic layout, and a variable wing body fusion design is adopted based on a waverider. The parallel reusable two-stage orbit entering aircraft adopting the horizontal interstage separation technology can be completely reused.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
FIG. 1 is a schematic structural view of the aerodynamic layout of a booster stage aircraft of the two-stage on-orbit aircraft of the present invention;
FIG. 2 is a schematic view of the aerodynamic layout and combination structure of the reusable booster-grade aircraft and the rail-grade aircraft with the wide-speed-range adaptive morphing wing of the present invention;
FIG. 3 is a schematic view of the aerodynamic layout of the rail-level vehicle of the present invention;
FIG. 4 is a schematic illustration of the horizontal interstage separation condition of the booster stage vehicle and the rail stage vehicle of the present invention;
FIG. 5 is a schematic diagram of a two-stage on-track mission of the present invention;
FIG. 6 is a schematic top view of a track-level waverider according to the present invention;
FIG. 7 is a schematic structural view of a flight control module of the transformable wing of the present invention;
FIG. 8 is a schematic diagram of the structure of the rear end face of the boosting stage wave-multiplying matrix of the present invention in longitudinal section.
The reference numerals in the drawings denote the following, respectively:
1-boosting level wave-multiplying matrix; 2-a deformable wing; 3-boosting auxiliary wings; 4-booster flap; 5-boosting vertical tail wing; 6-boosting tail wing rudder; 7-orbital level waverider; 8-a fairing; 9-triangular sweepback wings; 10-a guide plane; 11-rail grade ailerons; 12-track level flaps; 13-track level vertical tail; 14-rail level tail rudder; 15-horizontal guide rail; 16-a morphing wing control module; 17-a pneumatic power measuring and calculating module;
201-fixed wing panel; 202-morphing wing panel; 203-connecting rod; 204-a second steering engine; 205-telescopic connecting rod; 206-a first steering engine; 207-carbon fiber layer; 208-a glass fiber layer; 209-pressure sensor network layer;
2021-hollow skin wing body; 2022-rib panel set;
101-horizontal line segment; 102-a first parabolic segment; 103-a second parabolic segment;
801-half cone cover body; 802-first breakaway blast bolt; 803-second separate explosive bolt.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 to 8, the invention provides a parallel reusable two-stage approach vehicle with a pneumatic combination structure, which comprises a booster-stage vehicle and a track-stage vehicle, wherein a guide plane 10 for installing the track-stage vehicle is arranged on the upper surface of the booster-stage vehicle, the guide plane 10 is along the length direction of the booster-stage vehicle, and the guide plane 10 is seamlessly attached to the lower surface of the track-stage vehicle.
The invention relates to a reusable boosting-stage aircraft with wide-speed-range self-adaptive deformation wings and a triangular sweepback wing aerospace plane orbit-stage component.
The specific scheme is as follows:
the booster-level aircraft comprises a booster-level wave rider base body 1 and deformable wings 2 arranged on two sides of the booster-level wave rider base body 1, wherein booster-level ailerons 3 and booster-level flaps 4 are arranged on the surfaces, close to the rear end faces of the booster-level wave rider base body 1, of the deformable wings 2, two booster-level vertical tail wings 5 are symmetrically arranged on the booster-level wave rider base body 1 in a mirror image mode, and booster-level tail wing rudders 6 are arranged on the booster-level vertical tail wings 5.
Further, the specific design steps of the aerodynamic layout of the reusable booster-class aircraft with the wide-speed-range self-adaptive deformable wing are as follows:
step 1: according to the condition Mach 7 of separation between two stages of in-orbit stages as a design point, a boosting stage multiplication matrix is involved. According to the two-stage orbit-entering horizontal separation mode, the boosting stage wave-rider matrix adopts a flat-top design, namely a guide plane 10;
step 2: on the basis of a boosting level wave-multiplying matrix, a deformable wing is added, and comprises a high-strain distributed sensor (a pressure sensor), a local deformation controller and the like.
The deformable wing can change the wing span and the sweepback angle and the upper (lower) dihedral angle thereof at the same time.
The variable span wing expands and deforms from the middle section of the boost stage waverider base body, and the curve of the leading edge of the variable span wing is smoothly tangent to the curve of the leading edge of the boost stage waverider base body.
And step 3: then the distributed pressure sensor is used for measuring the pressure in the boosting-stage wide-speed-range flight process, and primarily estimating the lift force of the boosting-stage wing; the wingspan is adjusted according to the flight state through lift measurement and calculation and a wing deformation control system to reach an expected lift-drag ratio state;
meanwhile, the flight controller system is called to maintain the stability of the booster-stage aircraft in the wing profile changing process. The lift measurement and calculation, the wing deformation control system and the flight controller system form a feedback closed loop, and the optimal self-adaptive intelligent wingspan deformation of the boosting-level wide-speed-range flight is realized.
And 4, step 4: in the wide-speed-range flight process, aiming at the target flight state with excellent aerodynamic performance and flight stability, when the deformation control system of the deformable wing changes the wingspan according to a program, the flight control system can maintain the stability in the deformation process; meanwhile, the flight control system can operate the deformation control system of the deformable wing to serve as an operation mechanism of the boost aircraft, and can assist operation by utilizing a pneumatic effect caused by wingspan deformation of the deformable wing, so that better maneuvering operation and stability control are realized.
And 5: a boosting-level vertical tail wing is mounted on the fuselage, a boosting-level rudder of the vertical tail wing can adjust the lateral attitude, a boosting-level wing flap and a boosting-level aileron are mounted on the deformable wing, the boosting-level wing flap is used for adjusting the pitching motion of the aircraft, and the boosting-level aileron is used for controlling the rolling motion of the aircraft.
Step 6: an air suction type combined power engine, such as a turbine-ram combined power engine, is installed on the bottom section of the boosting stage aircraft to provide power for wide-speed-range flight of the two-stage aircraft.
The configuration method for the boosting level wave-multiplying matrix comprises the following steps:
step 100, determining free incoming flow conditions of a designed boosting stage wave multiplication matrix based on two-stage orbit-entering interstage separation, as well as the length of a reference cone and a shock wave angle, and obtaining an ultrasonic velocity winding cone reference flow field model required by the designed boosting stage wave multiplication matrix;
step 200, determining initial parameters of a half boosting level wave multiplication matrix according to the two-stage on-track interstage separation requirement, and obtaining the whole boosting level wave multiplication matrix through mirror symmetry of the half boosting level wave multiplication matrix;
the initial parameters comprise the length and the width of a half boosting level multiplication base body, a wing deflection angle and a positioning height;
step 300, determining a reference line type of the half boosting stage wave multiplication base body according to the two-stage on-track interstage separation requirement, wherein the reference line type of the half boosting stage wave multiplication base body specifically comprises the following steps: obtaining a base line linear function of the horizontal line segment, the lower opening parabola (first parabola segment) segment and the upper opening parabola (second parabola segment) segment according to initial parameters;
one end of a lower opening parabola (first parabola segment) segment is connected with the end part of a horizontal segment in a smooth tangent mode, the other end of the lower opening parabola (first parabola segment) segment is connected with one end of an upper opening parabola (second parabola segment) in a smooth tangent mode, and the other end of the upper opening parabola (second parabola segment) is horizontal;
step 400, calculating by using a cone guided shock wave theory based on an ultrasonic velocity winding cone reference flow field model required by designing a boost level multiplication matrix according to initial parameters and a reference line linear function to obtain the boost level multiplication matrix;
and 500, constructing variable wingspan wings and a rudder perpendicular to the boosting level wave-rider base body on the boosting level wave-rider base body to obtain the wide-speed-range aircraft based on the boosting level wave-rider base body.
The specific method for calculating and obtaining the boost-stage waverider matrix by using the cone-guided shock wave theory based on the supersonic velocity required by designing the boost-stage waverider matrix around the conical reference flow field model comprises the following steps:
step 401, horizontally projecting a reference line linear function onto a conical shock wave surface of an ultrasonic velocity winding conical reference flow field model to obtain a discrete leading edge curve of a boosting level wave-multiplying matrix, and forming an upper surface of the boosting level wave-multiplying matrix by a free flow surface starting from the discrete leading edge curve;
step 402, obtaining a plurality of flow lines of a plane where the discrete leading edge curve is located from the discrete leading edge curve to a datum line type through a flow line tracing technology, wherein the plurality of flow lines form the lower surface of the boosting level wave-multiplying matrix;
step 403, tracing the reference line type by the plurality of streamline lines to form a plurality of discrete points on the plane, connecting the plurality of off-line points to form a trailing edge curve of the boost-level waverider base body, and connecting the trailing edge curve with the reference line type to form the rear end face of the boost-level waverider base body;
and step 404, importing the rear end face, the upper surface and the lower surface into three-dimensional modeling software to obtain a three-dimensional boosting stage wave multiplication substrate through curved surface lofting, curved surface stretching and curved surface sewing operations.
In step 300, the expressions of the baseline function of the horizontal line segment, the lower opening parabola (first parabola segment) segment and the upper opening parabola (second parabola segment) segment are obtained according to the initial parameters as follows:
wherein d represents the length of half booster stage waverider base body, dhWidth of half horizontal line segment, dcDenotes the sum of the width of half a horizontal line segment and the horizontal length of a lower opening parabola (first parabola segment) segment, k1、k2Denotes the parabolic coefficient, h1Is the positioning height h of the horizontal line section relative to the origin of the supersonic velocity circular cone reference flow field model2Horizontal tangency of upper opening parabola (second parabola segment) segmentAnd the positioning height of the ultrasonic wave around the origin of the conical reference flow field model is relative to the ultrasonic speed, namely the drooping height of two side wings of the boosting stage multiplication wave matrix is finally formed.
In step 300, the thickness of the generated boost-stage waverider base body is controlled by the positioning height of the half boost-stage waverider base body, and the control formula is specifically as follows:
wherein, H represents the thickness of the boosting stage wave-rider matrix, d represents the width of half of the boosting stage wave-rider matrix, and R represents the radius of the conical shock wave quasi-surface.
In step 300, the specific method for obtaining the baseline linear function includes:
301, appointing the estimated size of the wing deflection angle according to the designer
Width d of half booster-level waverider base and length of horizontal straight-line segment of reference line
Boosting step-by-step substrate length
Height of positioning
The conical shock wave radius R establishes a system of equations:
solving the shock angle of conical shock wave by solving the established equation set
The projection radius R of the conical shock wave on the rear end surface;
step 302, establishing a geometric equation set of the intersection point of the datum line and the conical surface:
solving sag amplitude of two side wings of boost stage waverider base body
；
Step 303, establishing an equation according to the continuous relationship between the first derivative and the second derivative of the smooth tangent position of the upper opening parabola (second parabola segment) segment and the lower opening parabola (first parabola segment) segment of the reference line type:
obtained by solving and calculating
And
and further completing the construction of the baseline linear function.
In step 500, a deformable wing is constructed on the obtained booster stage wave-rider base body, and the method specifically comprises the following steps:
extending from the middle point of the leading edge curves at two sides of the boosting level wave-multiplying base body to the rear end surface of the boosting level wave-multiplying base body and expanding along the width direction of the boosting level wave-multiplying base body until the end part of the deformable wing is consistent with the rear end surface of the boosting level wave-multiplying base body;
the outer edge of the deformable wing keeps smooth tangency with the leading edge curves on the two sides of the boosting level wave-multiplying matrix.
In step 500, a vertical rudder is constructed for the obtained boosted wave-multiplying matrix, and the specific method comprises the following steps:
setting the height of a vertical rudder, enabling the vertical rudder to be perpendicular to the smooth tangent position of the upper opening parabola (second parabola segment) section and the lower opening parabola (first parabola segment) section, and enabling the vertical rudder to face the projection direction of the datum line type at the supersonic speed around the conical reference flow field model;
the reference line type of the boost-level waverider base body 1 specifically comprises a horizontal line segment 101 and first parabolic segments 102 which are smoothly tangent to each other and connected to two ends of the horizontal line segment 101, the first parabolic segments 102 located at two ends of the horizontal line segment 101 are mirror-symmetrical, the end portions of the horizontal line segments 101, far away from the first parabolic segments 102, are smoothly tangent to each other and connected with second parabolic segments 103, and the second parabolic segments 103 located at two sides of the horizontal line segment 101 are mirror-symmetrical.
Wherein, the guide plane 10 is formed by a free flow surface generated by a horizontal line segment 101 in the supersonic circular cone reference flow field model.
Step 404 further includes performing a cutting operation on the lower surface of the boost-stage waverider substrate, specifically including:
the front edge curve is cut horizontally from the bottom of the rear end surface of the boost-level waverider base body along the bottom surface of the boost-level waverider base body, so that the lower surface of the boost-level waverider base body is composed of a part of the original waverider surface and a cut plane.
The specific calculation method for cutting the lower surface of the boost-stage waverider base body comprises the following steps:
set the cutting thickness to
The cutting length is
:
Then contract
，
Length of cut
Comprises the following steps:
wherein the content of the first and second substances,
in order to boost the thickness of the wave-multiplying matrix,
the length of the lower surface of the boosting level wave-multiplying matrix.
The track-level aircraft provided by the invention comprises a track-level wave-rider body 7 and a fairing 8 arranged at the front end of the track-level wave-rider body 7, triangular sweepback wings 9 are arranged on two sides of the track-level wave-rider body 7, the bottom surfaces of the triangular sweepback wings 9 are in seamless fit with a guide plane 10, track-level ailerons 11 and track-level flaps 12 are arranged on the surfaces of the triangular sweepback wings 9 close to the rear end face of the track-level wave-rider body 7, a track-level vertical tail wing 13 is arranged in the middle of the top of the track-level wave-rider body 7, the track-level vertical tail wing 13 extends along the length direction of the track-level wave-rider body 7, and a track-level tail wing rudder 14 is arranged at the end part of the track-level vertical tail wing 13 close to the rear end face of the track-level wave-rider body 7.
Specifically, the aerodynamic layout design steps of the rail-level aircraft comprise:
step 1: because the orbit-level aircraft needs to climb under the action of rocket thrust to enter a target orbit after two-stage separation, enough fuel must be carried to climb into the orbit, and in addition, people and objects need to be carried, so that a large enough volume ratio is needed, and therefore, the body of the boosting-level aircraft adopts a semi-elliptical and inverted-rectangular cross-section shape, so that the orbit-level aircraft has a large volume ratio;
step 2: in the two-stage track entering process, the two-stage aircraft needs to quickly climb to an interstage separation point, so in order to effectively reduce the drag of the two-stage combination body, a fairing is installed at the head of the track-stage aircraft.
In addition, the head of the rail-grade aircraft adopts a blunt ball head design because the rail-grade aircraft needs to face a severe thermal environment in the process of flying again;
and step 3: in order to reduce the shock wave resistance in the climbing and accelerating processes of the two-stage aircraft, the rail stage adopts the wing body fusion design of the large triangular sweepback wing, and the small-aspect-ratio triangular sweepback wing can effectively reduce the shock wave resistance in supersonic flight, increase lift and reduce drag and can prevent heat.
The other purpose of adopting the triangular sweepback wing 9 as the wing of the orbit-level aircraft is to ensure that the orbit level can be attached to the back of the boosting level to be beneficial to horizontal separation;
and 4, step 4: in the process of climbing into a rail and then entering into the atmosphere for gliding and landing, in order to adjust the attitude and control the flight, a rail-level vertical tail wing is arranged on the body of the rail-level aircraft, a rail-level rudder on the rail-level vertical tail wing can adjust the lateral attitude, and a rail-level flap arranged on a triangular sweepback wing 9 can adjust the pitching attitude and adjust the attack angle to decelerate; the rail-level ailerons can be used for adjusting the rolling attitude of the rail-level aircraft.
The two-stage orbit entering aircraft adopts a horizontal separation mode, when the two-stage aircraft reaches a target interstage separation condition, the two stages receive a separation instruction, a rocket engine of the orbit stage aircraft is ignited, and the orbit stage aircraft performs horizontal interstage separation motion along a guide plane of the boosting stage aircraft under the action of rocket thrust.
In the horizontal separation interstage process, the surfaces of the booster stage aircraft and the rail stage aircraft are attached, normal motion does not exist between the two stages, and no gap exists, so that the problems of flight stability and control and the like caused by high pressure on the surfaces of the two stages of aircraft, high heat flow load and abruptly changed pneumatic load due to complicated and serious shock wave interference in the hypersonic velocity interstage separation process can be solved, the technical risk of the two-stage orbit-entering interstage separation is greatly reduced, and the safety and reliability of the two-stage orbit-entering are improved.
In the aspect of structural materials, the deformable wing of the booster-grade aircraft adopts an anisotropic variable-rigidity deformable skin structure, so that the shape change and small area increase of the deformable wing can be realized, the rigidity can be actively controlled, and the flexibility in the wingspan direction and the customized driving force of a distributed driver are ensured.
For larger wing variations, deployable morphing skin structures may be employed. The two-stage fuselage is made of high-strength composite materials, and the head and the leading edge of the wing are made of carbon-carbon composite materials or high-temperature-resistant ceramic matrix composite materials.
In conclusion, the parallel reusable two-stage orbit entering aircraft aerodynamic layout adopting the horizontal interstage separation technology is composed of an auxiliary-stage wave-rider matrix with excellent aerodynamic performance and operation stability in wide-speed-range flight and an aerodynamic layout between triangular wing aerospace plane orbit-stage wave-rider matrixes with large volume ratios.
When the two-stage in-orbit aircraft is launched, the boosting stage aircraft which can be repeatedly used by the wide-speed-range self-adaptive deformation wing carries the rail stage to perform sliding takeoff at a conventional airport, the boosting stage aircraft quickly climbs to an interstage separation point by virtue of the excellent pneumatic performance of the deformable wide-speed-range self-adaptive deformation wing, namely the interstage separation Mach number is 7, the separation height is 40km, and the two-stage aircraft can perform interstage separation by adopting a vertical separation mode and a horizontal separation mode; after interstage separation is completed, the boosting stage automatically returns to the conventional airport and lands back, the orbit-level aircraft is accelerated to climb to the target orbit under the driving of rocket power, and after the orbit-entering task is completed, the orbit-level aircraft returns from the target orbit and then enters the atmosphere to glide and land back to the conventional airport, so that two stages of the orbit-level aircraft can be completely reused.
The two-stage orbit-entering aircraft can carry people and goods, can send two tons of effective loads into the space, and can be applied to intercontinental travel, space launching, hypersonic aerial platforms and the like in the future.
The two-stage orbit entering aircraft has excellent pneumatic performance, can greatly reduce fuel use and increase effective load quality, can be completely reused, has good economy, safety and reliability, and is expected to become a next generation transportation scheme of a world transportation shuttle system.
Further, the deformable wing 2 extends from the midpoint of the leading edge curves at two sides of the boost level wave-multiplying matrix 1 to the rear end face of the boost level wave-multiplying matrix 1 and expands along the width direction of the boost level wave-multiplying matrix 1 until the end part of the deformable wing 2 is consistent with the rear end face of the boost level wave-multiplying matrix 1;
the outer edge of the deformable wing 2 keeps a smooth tangent with the leading edge curves of the two sides of the boosting level wave-multiplying matrix 1.
The deformable wing 2 comprises a fixed wing section 201 and a deformable wing section 202 connected to the fixed wing section 201, the side edge of the fixed wing section 201 far away from the deformable wing section 202 is rotatably connected to the side edge of the boost-level waverider base body 1 through a connecting rod 203, and a second steering engine 204 for driving the fixed wing section 201 to rotate around the connecting rod 203 is arranged in the boost-level waverider base body 1;
morphing wing section 202 includes hollow skin wing body 2021 and wing rib group 2022 installed inside hollow skin wing body 2021, and wing rib group 2022 includes a plurality of ribs distributed at equal intervals along the width direction of hollow skin wing body 2021, and the length of the plurality of ribs matches the length of hollow skin wing body 2021;
each wing rib is at least connected with one telescopic connecting rod 205, the telescopic connecting rods 205 extend to the fixed wing sections 201 along the width direction of the hollow skin wing bodies 2021, first steering gears 206 connected with the telescopic connecting rods 205 are arranged in the fixed wing sections 201, and the first steering gears 206 control the telescopic connecting rods 205 to change in the width direction of the hollow skin wing bodies 2021, so that the distance between every two adjacent wing ribs is controlled.
The surface of the hollow skin wing body 2021 is coated with an aerodynamic force sensing layer, the aerodynamic force sensing layer sequentially comprises a carbon fiber layer 207 and a glass fiber layer 208 from inside to outside, and a pressure sensor network layer 209 is distributed between the carbon fiber layer 207 and the glass fiber layer 208.
The deformation control process of the deformable wing is as follows, for example, when the boost-level aircraft flies from low speed to high supersonic speed, the wingspan of the deformable wing needs to be reduced, and the sweep angle is increased.
In the process, the first steering engine 206 is required to control the telescopic connecting rod 205, and the telescopic connecting rod 205 is sequentially controlled from back to front from the rear edge of the deformable wing section 202, so that each section of the telescopic connecting rod 205 connected with the wing rib sequentially shrinks from the hollow skin wing body 2021 to the tail end, and simultaneously, each wing rib fixedly connected with the telescopic connecting rod 205 sequentially moves from the wing tip to the wing root of the deformable wing, and the purpose of changing the wing span (simultaneously increasing the sweepback angle) of the wing is achieved.
For the first steering engine 206 the length of the telescopic connecting rod 205 needs to be changed:
assuming that the position of each telescopic link 205 arranged from the leading edge curve to the trailing edge curve of the hollow skin airfoil body 2021 is denoted by length x1, x2, x3... xn, the initial wing span length of the hollow skin airfoil body 2021 is d1, and the sweep angle is
After deformation, the wing span length is d2, and the sweep angle is
The length of each telescopic connecting rod 205 required to be extended from back to front is
。
For measuring and calculating aerodynamic force, pressure data measured by the pressure sensor network layer is transmitted to the aerodynamic force measuring and calculating module, and the measurement result is obtained through an integral formula:
the aerodynamic force of the deformable wing can be rapidly calculated, wherein N is the normal force borne by the boosting-stage aircraft, A is the axial force borne by the boosting-stage aircraft, L is the lift force, D is the resistance force,
is the angle of attack of the incoming flow.
And then, aerodynamic force data obtained by a real-time meter is transmitted to a deformation control system, and then a flight control system sends an instruction to a telescopic rod control steering engine to change the sweepback angle and the wingspan of the wing, so that a negative feedback loop is formed.
For a mechanism system for controlling the size of the up-down dihedral angle of the wing, the specific deformation control process is as follows:
the whole wing is divided into a deformable wing section and a fixed wing section, the deformable wing section can be used for controlling the span length of the wing and changing the sweep angle, the deformable wing section is connected with the fixed wing section through the tail section of a deformable telescopic rod, and the fixed wing section is connected with the fuselage through a movable rod piece. The connection part of the movable rod piece and the machine body keeps the rotational freedom degree of the rod piece.
When the up-down dihedral angle of the wing does not need to be adjusted, the rotational freedom degree is blocked. The wing dihedral angle control steering engine (second steering engine) changes the magnitude instruction of the wing dihedral angle value to be adjusted according to the requirement sent by the wing dihedral angle control module, transmits torque to the movable rod piece connected with the fixed wing section and the fuselage through the connecting rod, and the connecting rod can control the rotation angle of the movable rod piece through gear box transmission or pull rod transmission, so as to drive the integral upper and lower dihedral angle of the fixed wing section and the deformable wing section.
After the dihedral angle of the wing is adjusted, the aerodynamic characteristics and the dynamic stability characteristics are measured and calculated through the aerodynamic measuring and calculating module, the data are transmitted to the control system, and then the flight control system sends an instruction to the wing dihedral angle control module to change the up-down dihedral angle of the wing, so that a negative feedback loop is formed.
The boosting-stage vertical tail wing 5 is perpendicular to the upper surface of the boosting-stage wave rider base body 1 formed by the first parabolic segment 102, the projection directions of the boosting-stage vertical tail wing 5 and the first parabolic segment 102 around the conical reference flow field model at the supersonic speed are kept consistent, and one end of the boosting-stage vertical tail wing 5 is kept consistent with the rear end face of the boosting-stage wave rider base body 1.
The middle of the guide plane 10 is provided with a horizontal guide rail 15 for installing the track-level wave-multiplying body 7, and the horizontal guide rail 15 enables the mass centers of the boosting-level wave-multiplying base body 1 and the track-level wave-multiplying body 7 to be positioned in the same normal direction.
Further, the fairing 8 in the invention comprises two half-cone cover bodies 801 connected in a mirror image mode, wherein the two half-cone cover bodies 801 are connected through a first separation explosive bolt 802, and the two half-cone cover bodies 801 are connected with the head of the track-level wave multiplier 7 through a second separation explosive bolt 803.
Due to the fact that the size of the head of the rail-grade wave carrier is small, the first separation explosion bolt 802 and the second separation explosion bolt 803 are specifically point type connection unlocking devices, and separation of a fairing at the head of the rail-grade wave carrier adopts a separation spring as a separation energy source.
After the separation of the orbit-level aircraft and the booster-level aircraft is completed, the separation of the two half cone cover bodies 801 of the fairing of the orbit-level wave carrier adopts flat throw type separation, so that in order to avoid the interference of the longitudinal connecting surface on the transverse separation, the first separation explosion bolt 801 is detonated firstly to complete the unlocking of the longitudinal separation surface formed between the two half cone cover bodies 801, then the second separation explosion bolt 803 is detonated to complete the unlocking of the transverse separation surface formed between the two half cone cover bodies 801 and the orbit-level wave carrier 7.
The parallel reusable two-stage orbit entering aircraft aerodynamic layout adopting the horizontal interstage separation technology comprises a wave-rider-based wide-speed-domain self-adaptive deformation wing reusable boosting stage aircraft, has good wide-speed-domain lift-drag ratio aerodynamic performance and flight stability, and adopts a flat-top design for placing the rail stages and performing interstage horizontal separation.
In the technical scheme provided by the invention, the design point of the boost-stage wave multiplying matrix of the reusable boost-stage aircraft with the wide-speed-range adaptive deformation wing is the interstage separation Mach number 7, so that the boost-stage wave multiplying matrix has certain wave multiplying properties, and the boost-stage wave multiplying matrix has certain longitudinal static stability by cutting the bottom of the boost-stage wave multiplying matrix.
The reusable booster-level aircraft with the wide-speed-range self-adaptive deformable wings adopts a wing body fusion design, the deformable wings on the left side and the right side of the booster-level wave-multiplying matrix are fused with the booster-level wave-multiplying matrix, and the wingspans of the left and the right deformable wings can gradually change from the maximum wingspan to the minimum adaptable flight condition in the wide-speed range from low Mach number to high Mach number so as to achieve excellent lift-drag ratio characteristics and simultaneously change a sweep angle and upper and lower dihedral angles to realize the stability control of the aircraft. On the other hand, aerodynamic effects caused by the deformable wing can be used as an auxiliary steering mechanism.
In the technical scheme, the reusable booster-level aircraft with the wide-speed-range self-adaptive deformable wing further comprises a flight control system, and the flight control system comprises a deformable wing control module, an aerodynamic force measuring and calculating module, a wing sweep angle control module and a wing dihedral angle control module which are arranged in the booster-level wave rider base body 1 aiming at the intelligent control of the deformable wing.
The aerodynamic force measuring and calculating module is used for acquiring aerodynamic force data received by the deformable wing 2 in the flying process through the network layer of the pressure sensor;
the deformable wing control module receives aerodynamic force data of the aerodynamic force measuring and calculating module and sends control instructions to the wing sweep angle control module and the wing dihedral control module;
the wing dihedral angle control module controls a second steering engine to drive the connecting rod to rotate through a control instruction, and changes the upper dihedral angle and the lower dihedral angle of the boosting-level aircraft;
the wing sweep angle control module controls the first steering engine to drive the length change of the telescopic connecting rod 205 through a control command, and changes the span width of the deformed wing section 202;
the wing sweep angle control module is used for sending aerodynamic force measurement and calculation signals to the aerodynamic force measurement and calculation module after the wing dihedral angle control module completes the upper dihedral angle and the lower dihedral angle of the boosting-level aircraft, the wing sweep angle control module changes the span width of the deformed wing section 202 and changes the sweep angle of the boosting-level aircraft, the optimal self-adaptive intelligent span deformation of the two-stage orbit entering aircraft in wide-speed-range flight is achieved, and the stability of the boosting-level aircraft is maintained by the aid of the control system in the deformation process.
In the technical scheme, the wide-speed-range self-adaptive deformable wing can be used for repeatedly using the booster aircraft, and the air-breathing combined power engine is arranged in the lower space of the aircraft body.
In the technical scheme, the boosting-stage and track-stage two-stage aircrafts are in a pneumatic layout of a two-stage orbit aircraft combination body formed by adopting normal centroid superposition arrangement (the boosting-stage wave-multiplying base body and the track-stage wave-multiplying body are connected through the arranged horizontal guide rail), so that unstable flight caused by instantaneous change of the centroid in the interstage separation process of the two-stage aircrafts is avoided.
The parallel reusable two-stage orbit entering aircraft adopting the horizontal interstage separation technology can be completely reused, and has the advantages of good economy, high reliability and flexible and wide application.
The above embodiments are only exemplary embodiments of the present application, and are not intended to limit the present application, and the protection scope of the present application is defined by the claims. Various modifications and equivalents may be made by those skilled in the art within the spirit and scope of the present application and such modifications and equivalents should also be considered to be within the scope of the present application.
Claims (10)
1. The parallel reusable two-stage orbit entering aircraft with a pneumatic combined structure is characterized by comprising a boosting stage aircraft and a track stage aircraft, wherein a guide plane (10) for mounting the track stage aircraft is arranged on the upper surface of the boosting stage aircraft, the guide plane (10) is arranged along the length direction of the boosting stage aircraft, and the guide plane (10) is in seamless fit with the lower surface of the track stage aircraft;
the boost-level aircraft comprises a boost-level wave-rider base body (1) and deformable wings (2) arranged on two sides of the boost-level wave-rider base body (1), wherein a boost-level aileron (3) and a boost-level wing flap (4) are arranged on the surface, close to the rear end face of the boost-level wave-rider base body (1), of the deformable wings (2), two boost-level vertical tail wings (5) are symmetrically arranged on the boost-level wave-rider base body (1) in a mirror image mode, and a boost-level tail wing rudder (6) is arranged on each boost-level vertical tail wing (5);
the rail-level aircraft comprises a rail-level wave-rider (7) and a fairing (8) arranged at the front end of the rail-level wave-rider (7), triangular sweepback wings (9) are arranged on two sides of the track-level waverider (7), the bottom surfaces of the triangular sweepback wings (9) are in seamless fit with the guide plane (10), the surface of the triangular sweepback wing (9) close to the rear end surface of the track-level wave rider (7) is provided with a track-level aileron (11) and a track-level flap (12), a track-level vertical tail (13) is arranged in the middle of the top of the track-level wave-rider (7), the track-level vertical tail (13) extends along the length direction of the track-level wave rider (7), and a track-level empennage rudder (14) is arranged at the end part of the track-level vertical empennage (13) close to the rear end surface of the track-level waverider (7).
2. The aircraft of claim 1, wherein the deformable wing (2) extends from the midpoint of the leading edge curves at two sides of the boosting stage wave-multiplying matrix (1) to the rear end surface of the boosting stage wave-multiplying matrix (1) and expands along the width direction of the boosting stage wave-multiplying matrix (1) until the end of the deformable wing (2) is consistent with the rear end surface of the boosting stage wave-multiplying matrix (1);
the outer edge of the deformable wing (2) keeps smooth tangency with the leading edge curves of the two sides of the boosting grade wave-multiplying matrix (1).
3. The parallel reusable two-stage orbit entering aircraft with the pneumatic combination structure according to claim 2, wherein the deformable wing (2) comprises a fixed wing section (201) and a deformable wing section (202) connected to the fixed wing section (201), the side of the fixed wing section (201) far away from the deformable wing section (202) is rotatably connected to the side of the boosting stage wave-rider base body (1) through a connecting rod (203), and a second steering engine (204) for driving the fixed wing section (201) to rotate around the connecting rod (203) is arranged in the boosting stage wave-rider base body (1);
the morphing wing panel (202) comprises a hollow skin wing body (2021) and a wing rib group (2022) installed inside the hollow skin wing body (2021), wherein the wing rib group (2022) comprises a plurality of ribs distributed at equal intervals along the width direction of the hollow skin wing body (2021), and the length of the plurality of ribs is matched with that of the hollow skin wing body (2021);
each wing rib is at least connected with one telescopic connecting rod (205), the telescopic connecting rods (205) extend to the fixed wing sections (201) along the width direction of the hollow skin wing bodies (2021), first steering engines (206) connected with the telescopic connecting rods (205) are arranged in the fixed wing sections (201), the telescopic connecting rods (205) are controlled by the first steering engines (206) to change in the width direction of the hollow skin wing bodies (2021), and then the distance between every two adjacent wing ribs is controlled.
4. The parallel reusable two-stage in-orbit aircraft with an aerodynamic composite structure according to claim 3, characterized in that the surface of the hollow skin wing body (2021) is coated with an aerodynamic force sensing layer, the aerodynamic force sensing layer comprises a carbon fiber layer (207) and a glass fiber layer (208) in sequence from inside to outside, and a pressure sensor network layer (209) is distributed between the carbon fiber layer (207) and the glass fiber layer (208).
5. The parallel reusable two-stage approach vehicle with the aerodynamic combined structure is characterized in that a deformation wing control module, an aerodynamic force measuring and calculating module, a wing sweep angle control module and a wing dihedral angle control module are further installed in the boosting stage ride matrix (1);
the aerodynamic force measuring and calculating module is used for acquiring aerodynamic force data received by the deformable wing (2) in the flying process through the pressure sensor network layer;
the deformation wing control module receives aerodynamic force data of the aerodynamic force measuring and calculating module and sends control instructions to the wing sweep angle control module and the wing dihedral angle control module;
the wing dihedral angle control module controls the second steering engine to drive the connecting rod to rotate through a control instruction, and changes the upper dihedral angle and the lower dihedral angle of the boosting-level aircraft;
the wing sweep angle control module controls the first steering engine to drive the length change of the telescopic connecting rod (205) through a control command, and changes the span width of the deformed wing section (202);
the wing sweep angle control module is used for sending aerodynamic force measurement and calculation signals to the aerodynamic force measurement and calculation module after the wing dihedral angle control module completes the upper dihedral angle and the lower dihedral angle of the booster-class aircraft, and the wing sweep angle control module changes the span width of the deformed wing section (202) and changes the sweep angle of the booster-class aircraft.
6. The parallel reusable two-stage approach vehicle with aerodynamic composite structure according to claim 5, characterized in that the lower surface of the boosting stage ride matrix (1) is composed of a ride surface traced by the leading edge curve of the boosting stage ride matrix (1) through streamline and a horizontal cutting surface formed by horizontally cutting from the rear end surface of the boosting stage ride matrix (1) to the head of the boosting stage ride matrix (1).
7. The parallel reusable two-stage orbit entering aircraft with the aerodynamic combined structure according to claim 4, wherein the datum line of the boosting stage wave-rider base body (1) specifically comprises a horizontal line segment (101) and first parabolic segments (102) which are connected to two ends of the horizontal line segment (101) in a smooth and tangent mode, the first parabolic segments (102) located at two ends of the horizontal line segment (101) are in mirror symmetry, the ends, far away from the horizontal line segment (101), of the first parabolic segments (102) are connected with second parabolic segments (103) in a smooth and tangent mode, and the second parabolic segments (103) located at two sides of the horizontal line segment (101) are in mirror symmetry;
wherein the guide plane (10) is formed by a free flow surface generated by the horizontal line segment (101) in a supersonic circular cone reference flow field model.
8. The aircraft of claim 2, wherein the booster stage vertical tail (5) is perpendicular to the upper surface of the booster stage ride matrix (1) formed by the first parabolic segment (102), the booster stage vertical tail (5) and the first parabolic segment (102) are consistent in projection direction around a conical reference flow field model at supersonic speed, and one end of the booster stage vertical tail (5) and the rear end surface of the booster stage ride matrix (1) are consistent.
9. The aircraft with the aerodynamic combination structure and the two-stage approach track reusable parallel connection according to claim 8 is characterized in that a horizontal guide rail (15) for installing the track-level wave rider (7) is arranged in the middle of the guide plane (10), and the horizontal guide rail (15) enables the mass centers of the boosting-level wave rider base body (1) and the track-level wave rider (7) to be located in the same normal direction.
10. The parallel reusable two-stage inbound track vehicle with aerodynamic profile as claimed in claim 1, characterized in that said fairing (8) comprises two half cone shells (801) connected in mirror image, two of said half cone shells (801) being connected by a first separation explosive bolt (802), two of said half cone shells (801) being connected by a second separation explosive bolt (803) to the head of the orbital ride (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210131377.5A CN114162349A (en) | 2022-02-14 | 2022-02-14 | Parallelly connected repeatedly usable's two-stage rail aircraft with pneumatic integrated configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210131377.5A CN114162349A (en) | 2022-02-14 | 2022-02-14 | Parallelly connected repeatedly usable's two-stage rail aircraft with pneumatic integrated configuration |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114162349A true CN114162349A (en) | 2022-03-11 |
Family
ID=80489935
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210131377.5A Pending CN114162349A (en) | 2022-02-14 | 2022-02-14 | Parallelly connected repeatedly usable's two-stage rail aircraft with pneumatic integrated configuration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114162349A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115292818A (en) * | 2022-08-15 | 2022-11-04 | 北京航空航天大学 | Three-section wing tail edge side edge noise reduction scheme design with special-configuration baffle |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4802639A (en) * | 1984-09-28 | 1989-02-07 | The Boeing Company | Horizontal-takeoff transatmospheric launch system |
| DE3740645A1 (en) * | 1987-12-01 | 1989-06-15 | Dornier Gmbh | Multistage space transportation system |
| CN1337912A (en) * | 1998-12-31 | 2002-02-27 | 太空通道有限公司 | Payload carry and Launch system |
| US6612522B1 (en) * | 1998-03-17 | 2003-09-02 | Starcraft Boosters, Inc. | Flyback booster with removable rocket propulsion module |
| US20060118675A1 (en) * | 2004-12-07 | 2006-06-08 | Tidwell John Z | Transformable fluid foil with pivoting spars and ribs |
| 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 |
| CN107985551A (en) * | 2017-12-09 | 2018-05-04 | 佛山市神风航空科技有限公司 | A kind of wing that can be folded |
| CN108928490A (en) * | 2018-07-13 | 2018-12-04 | 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 Horizontal Take-off and Landing two-stage enters the aerodynamic arrangement of orbit aerocraft |
| CN110510149A (en) * | 2019-08-23 | 2019-11-29 | 中国航天空气动力技术研究院 | A kind of Horizontal Take-off and Landing two-stage, which is entered the orbit, reuses sky and space plane layout |
| CN112141364A (en) * | 2020-09-25 | 2020-12-29 | 中国科学院空间应用工程与技术中心 | Reusable earth-moon transportation system and method |
| CN113415114A (en) * | 2021-07-27 | 2021-09-21 | 北京理工大学 | Cross-medium aircraft based on bionic morphing wing |
-
2022
- 2022-02-14 CN CN202210131377.5A patent/CN114162349A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4802639A (en) * | 1984-09-28 | 1989-02-07 | The Boeing Company | Horizontal-takeoff transatmospheric launch system |
| DE3740645A1 (en) * | 1987-12-01 | 1989-06-15 | Dornier Gmbh | Multistage space transportation system |
| US6612522B1 (en) * | 1998-03-17 | 2003-09-02 | Starcraft Boosters, Inc. | Flyback booster with removable rocket propulsion module |
| CN1337912A (en) * | 1998-12-31 | 2002-02-27 | 太空通道有限公司 | Payload carry and Launch system |
| US20060118675A1 (en) * | 2004-12-07 | 2006-06-08 | Tidwell John Z | Transformable fluid foil with pivoting spars and ribs |
| 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 |
| CN107985551A (en) * | 2017-12-09 | 2018-05-04 | 佛山市神风航空科技有限公司 | A kind of wing that can be folded |
| CN108928490A (en) * | 2018-07-13 | 2018-12-04 | 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 Horizontal Take-off and Landing two-stage enters the aerodynamic arrangement of orbit aerocraft |
| CN110510149A (en) * | 2019-08-23 | 2019-11-29 | 中国航天空气动力技术研究院 | A kind of Horizontal Take-off and Landing two-stage, which is entered the orbit, reuses sky and space plane layout |
| CN112141364A (en) * | 2020-09-25 | 2020-12-29 | 中国科学院空间应用工程与技术中心 | Reusable earth-moon transportation system and method |
| CN113415114A (en) * | 2021-07-27 | 2021-09-21 | 北京理工大学 | Cross-medium aircraft based on bionic morphing wing |
Non-Patent Citations (4)
| Title |
|---|
| FENG DING,JUN LIU,CHIBING SHEN,WEI HUANG: "Novel inlet–airframe integration methodology for hypersonic waverider vehicles", 《ACTA ASTRONAUTICA》 * |
| 张国成，姚彦龙，王慧: "美国两级入轨水平起降可重复使用", 《飞机设计》 * |
| 王粤，汪运鹏，薛晓鹏， 姜宗林: "TSTO马赫7安全级间分离问题的数值研究", 《力学学报》 * |
| 韩天依星，罗磊，许晨豪，蒋崇文: "嵌入式乘波设计的两级入轨飞行器概念研究", 《航空科学技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115292818A (en) * | 2022-08-15 | 2022-11-04 | 北京航空航天大学 | Three-section wing tail edge side edge noise reduction scheme design with special-configuration baffle |
| CN115292818B (en) * | 2022-08-15 | 2024-01-23 | 北京航空航天大学 | Method for reducing noise of side edge of three-section trailing edge of flap with baffle for passive flow control |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Jha et al. | Morphing aircraft concepts, classifications, and challenges | |
| WO2022068022A1 (en) | Tailsitter-type vertical take-off and landing unmanned aerial vehicle and control method therefor | |
| Samuel et al. | Design and testing of a pneumatic telescopic wing for unmanned aerial vehicles | |
| US20140145027A1 (en) | Aircraft with an integral aerodynamic configuration | |
| CN111315655B (en) | Assembly of three composite wings for an air, water, land or space vehicle | |
| CN107310714B (en) | Flight control system of stealth unmanned aerial vehicle with flying wing layout and control method thereof | |
| CN108928490A (en) | A kind of Horizontal Take-off and Landing two-stage enters the aerodynamic arrangement of orbit aerocraft | |
| CN114313253B (en) | Aerodynamic layout and design method of high-lift-drag-ratio air-breathing hypersonic aircraft | |
| US20220097849A1 (en) | Tailstock type vertical take-off and landing unmanned aerial vehicle and control method thereof | |
| Frediani et al. | Design of a prototype of light amphibious PrandtlPlane | |
| CN114261538B (en) | Parallel double-waverider two-stage in-orbit aircraft horizontal interstage separation design method | |
| CN114148549B (en) | Aircraft with two-stage in-orbit horizontal interstage separation and shock wave impact preventing method thereof | |
| Bowlus et al. | Challenges and opportunities in tailless aircraft stability and control | |
| Wang et al. | Modeling and simulation of mass-actuated flexible aircraft for roll control | |
| CN114162349A (en) | Parallelly connected repeatedly usable's two-stage rail aircraft with pneumatic integrated configuration | |
| CN110844071A (en) | Unmanned aerial vehicle capable of long-endurance wide-speed-range high-mobility cruise flight | |
| CN110116802A (en) | A kind of big loading small-sized unmanned aircraft of high universalizable | |
| CN114180100B (en) | Wave-rider base body construction method, booster-stage aircraft and wing control system | |
| CN110920881A (en) | Vertical take-off and landing unmanned conveyor and control method thereof | |
| CN111422348A (en) | Vertical take-off and landing unmanned aerial vehicle and control method thereof | |
| CN114115323B (en) | Modeling and control method of three-steering engine driven bird-like ornithopter | |
| CN211253019U (en) | Vertical take-off and landing unmanned conveyor | |
| Çoban et al. | Innovative morphing UAV design and manufacture | |
| US20220315250A1 (en) | Space aircraft with optimised design and architecture | |
| CN212423467U (en) | Unmanned aerial vehicle capable of long-endurance wide-speed-range high-mobility cruise flight |
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 |