CN114261538B - Parallel double-waverider two-stage in-orbit aircraft horizontal interstage separation design method - Google Patents
Parallel double-waverider two-stage in-orbit aircraft horizontal interstage separation design method Download PDFInfo
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Abstract
The invention discloses a design method for horizontal interstage separation of a parallel double-waverider two-stage orbit entering aircraft, which comprises the steps of constructing a combined structure of an orbit-stage waverider aircraft and a boosting-stage waverider aircraft; when the flight of the combined structure reaches an interstage separation condition, the lift forces borne by the two side wings of the boosting stage wave-rider aircraft are unbalanced, and the combined structure rolls by 90 degrees laterally around the aircraft body; under the condition of keeping the lateral rolling of the combined structure at 90 degrees, the track-level waverider aircraft is horizontally separated along the upper surface of the boosting-level waverider aircraft under the driving of the power of the track-level waverider aircraft; after the orbit-level wave-rider aircraft is separated from the boosting-level wave-rider aircraft, the orbit-level wave-rider aircraft rolls for 90 degrees laterally and climbs to the target orbit, and the boosting-level wave-rider aircraft rolls for 90 degrees reversely to recover the initial flight state, so that the horizontal interstage separation of the orbit-level wave-rider aircraft and the target orbit is realized. The horizontal interstage separation method of the invention avoids the problems of high pressure, high heat flow and stability in the conventional separation process under the hypersonic speed condition.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a design method for horizontal interstage separation of a parallel double-waverider two-stage orbit entering aircraft.
Background
Two-stage orbital vehicles are extensively studied as the next generation of reusable shuttle systems for world transportation at low cost, high efficiency, and high reliability. The horizontal take-off and landing two-stage in-orbit aircraft consists of an air suction type power boosting stage and a reusable rocket power orbit stage. The horizontal take-off and landing two-stage orbit-entering aircraft generally adopts a boosting stage to carry a rail stage to perform gliding take-off in a conventional airport, the aircraft rapidly climbs under the boosting stage air-breathing type power and accelerates to reach the condition of inter-stage separation of the two-stage aircraft, after the inter-stage separation, the boosting stage is mechanically controlled to automatically return to the airport, the rail stage climbs into an orbit under the driving of rocket power, and the rail stage glides and returns to land after the orbit-entering task is completed. Therefore, the two-stage orbit-entering aircraft is used as a large scientific research engineering construction and faces three technical difficulties: the combined power engine comprises a boosting stage air-breathing combined power engine, a two-stage aircraft hypersonic interstage separation, an aircraft thermal protection and the like.
The two-stage orbit entering aircraft interstage separation is generally carried out under the hypersonic speed condition, which can bring complicated pneumatic interference and severe pneumatic heating problems to the two-stage aircraft interstage separation process. In a general two-stage separation concept scheme, an interstage separation mode is adopted, but the vertical separation can generate serious shock wave interference between two stages, so that the brought unsteady pneumatic load and pneumatic heating are not favorable for the operation stability and the thermal protection of a two-stage aircraft, and the two-stage on-orbit task can be directly failed. Horizontal separation can avoid the problem, surface fitting is carried out without clearance separation between two stages, and unsteady aerodynamic load and aerodynamic heat problems caused by shock wave interference reflection are avoided between the two stages. The two-stage orbit aircraft boosting stage generally selects a wing body fusion aircraft or a wave-rider aircraft with high lift-drag ratio, and the orbit stage generally selects a space plane or a wave-rider aircraft. In order to solve the above problems, in the prior art, for example, a layout of a horizontal take-off and landing two-stage approach-track reusable aerospace plane with a publication number of CN201910784771.7 is used to satisfy the TSTO flight principle based on TBCC, so as to achieve design requirements of lift-drag matching, push-drag matching, stability-handling matching, and volume-weight matching in full speed domain and full airspace, and to achieve the closing of the TSTO technical scheme in the concept design stage, but there are some defects, for example, when the track-level aerodynamic layout selects a high lift-drag ratio wave carrier aerodynamic layout, because the lower surface of the wave carrier is generally curved (non-planar), it cannot be completely attached to the upper surface of the boost stage in horizontal separation (shock wave interference can generate high-pressure and high-heat flow regions in separation). In order to solve the problem, the invention provides a 90-degree rolling horizontal interstage separation technology of a parallel double-waverider two-stage orbit entering aircraft by adopting a two-stage pneumatic layout arrangement method that the upper surface of a track-stage waverider is attached to the upper surface of a boosting stage horizontally and freely and the waverider faces upwards from the requirement of a two-stage orbit entering task.
Disclosure of Invention
The invention aims to provide a design method for horizontal interstage separation of a parallel double-waverider two-stage orbit entering aircraft, so as to solve the technical problem of horizontal separation of the parallel double-waverider aircraft in the prior art.
In order to solve the technical problems, the invention specifically provides the following technical scheme:
a design method for horizontal interstage separation of a parallel double-waverider two-stage orbit entering aircraft comprises the following specific steps:
step 100, constructing a combined structure of the orbit-level wave-rider aircraft and the boost-level wave-rider aircraft under the determined interstage separation condition, so that the orbit-level wave-rider aircraft and the boost-level wave-rider aircraft are restrained by opposite normal forces in the flight process;
200, when the flight of the combined structure reaches an interstage separation condition, enabling the lift forces borne by the two side wings of the boosting stage wave-rider aircraft to be unbalanced, and further enabling the combined structure to roll for 90 degrees along the lateral direction of the aircraft body;
300, under the condition of keeping the lateral rolling angle posture of the combination structure, which rolls for 90 degrees, the track-level wave-rider aircraft is driven by the power of the track-level wave-rider aircraft to horizontally separate along the upper surface of the boosting-level wave-rider aircraft;
after the track-level waverider aircraft is separated from the boosting-level waverider aircraft, the track-level waverider aircraft adjusts the unbalanced lift force borne by the two side wings, further continues to roll for 90 degrees laterally under the rolling angle posture of rolling for 90 degrees laterally, and climbs to a target track;
and step 400, reversely rolling the boosting level wave-rider aircraft by 90 degrees under the rolling angle posture of rolling by 90 degrees in the lateral direction by enabling the lifting forces generated by the two side wings of the boosting level wave-rider aircraft to be unbalanced and changed again, and recovering the initial flight state to realize the horizontal interstage separation of the boosting level wave-rider aircraft and the track level wave-rider aircraft.
As a preferred scheme of the present invention, in step 200 and step 300, the specific method for controlling the lift imbalance suffered by the two wings of the track-level wave-rider aircraft and the boost-level wave-rider aircraft comprises:
arranging morphing wings and ailerons on two sides of the track-level waverider aircraft and the boosting-level waverider aircraft;
when the combined structure reaches an interstage separation condition, the boosting stage wave-rider aircraft generates initial rolling under the control of an instantaneous rolling excitation signal generated by the flight control system, and the flight control system controls the aileron action or controls the deformation of the deformed wing to enable the lifting forces borne by the two side wings of the boosting stage wave-rider aircraft to be unbalanced, so that the combined structure generates rolling torque and initial rolling acceleration.
As a preferred scheme of the invention, when the magnitude of the roll damping torque generated by the combined body structure in the rolling process is equal to the magnitude of the roll torque and reaches balance, the combined body structure performs steady rolling;
after the combined structure is in the roll angle posture of rolling 90 degrees in the lateral direction, adjusting the wingspan of the deformed wing of the boosting level wave-rider aircraft to enable the roll torque and the roll damping torque to be balanced, and maintaining the roll angle of the combined structure to be 90 degrees;
after the rolling moment acting on the combination of the orbit-level wave-rider aircraft and the boosting-level wave-rider aircraft is cancelled, the rolling damping moment borne by the combination enables the combination to start decelerating from a steady rolling motion state and stop.
As a preferred aspect of the present invention, in step 100, a specific method for constructing a combined structure of an orbital wave-rider spacecraft and a booster wave-rider spacecraft under a determined interstage separation condition includes:
step 101, determining reference line types of a track-level wave-rider aircraft and a boosting-level wave-rider aircraft according to an existing two-level orbit aerospace craft interstage separation mode;
the datum line type of the boosting level wave-rider aircraft comprises a horizontal line segment, first curve segments connected to two ends of the horizontal line segment, and second curve segments which are located at two ends of the horizontal line segment and are in mirror symmetry and smoothly tangent with the first curve segments;
the datum line type of the track-level waverider aircraft is a horizontal line segment, and the length of the datum line type of the track-level waverider aircraft is equal to the length of the horizontal line segment of the datum line type of the boosting-level waverider aircraft;
generating wave multiplying matrix structures of an orbit-level wave multiplying body aircraft and a boosting-level wave multiplying body aircraft respectively according to a cone-guided wave multiplying body generation theory;
102, arranging a track-level vertical tail rudder on the windward side of a wave-rider base body of a track-level wave-rider aircraft;
the method comprises the following steps that (1) deformable wings are arranged on two sides of a wave-riding base body of a boosting level wave-riding aircraft, and a pair of symmetrical boosting level vertical tail wing rudders are arranged on the windward side of the wave-riding base body of the boosting level wave-riding aircraft;
and 103, attaching and connecting the surface of the wave-multiplying base body of the orbit-level wave-multiplying body aircraft formed by the horizontal line segment with the surface of the wave-multiplying base body of the boosting-level wave-multiplying body aircraft formed by the horizontal line segment to construct an assembly structure of the orbit-level wave-multiplying body aircraft and the boosting-level wave-multiplying body aircraft.
As a preferred scheme of the present invention, in step 101, a specific method for constructing a boost level wave-rider aircraft is as follows:
step 1011, obtaining a leading edge curve of the boosting level waverider aircraft by the horizontal projection of the datum line type of the boosting level waverider aircraft on the conical shock wave surface;
step 1012, tracking the leading edge curve through a streamline to obtain the lower surface and the trailing edge curve of the boosting level wave-rider aircraft;
the upper surface of the boosting level wave-rider aircraft is formed by a self-flowing surface formed by the front edge curve;
and 1013, forming the rear end face of the boosting level waverider aircraft by the datum line type and the trailing edge curve together to complete the construction of the waverider base body of the boosting level waverider aircraft.
As a preferable mode of the present invention, the morphing wing extends from a midpoint of positions on both sides of a leading edge curve of a waverider base body of the boost level waverider aircraft to a rear end face of the waverider base body, and extends in a width direction of the waverider base body of the boost level waverider aircraft until an end of the morphing wing is in agreement with the rear end face of the waverider base body;
and the leading edge curves of the morphing wings and the waverider base body are kept smooth and tangent.
In a preferred embodiment of the present invention, the vertical tail rudder is perpendicular to the upper surface of the wave-rider base body formed by the first curved section, and the vertical tail rudder and the first curved section are aligned in the projection direction of the conical shock surface.
As a preferred aspect of the present invention, in the case where the flight control system controls the deformation of the morphing wing to realize the lift imbalance suffered by the two wings of the booster-class waverider aircraft, the specifically changed state of the morphing wing includes: wing span, sweep angle, and dihedral angle.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides a 90-degree rolling horizontal interstage separation technology of a parallel double-waverider two-stage in-orbit aircraft;
when the interstage separation mode of the two-stage orbit entering aircraft adopts horizontal separation, the problem of complex and serious shock wave interference in the common vertical interstage separation process can be avoided, so that unsteady pneumatic load borne by the two stages in the interstage separation process is avoided, and the flight stability control in the separation process is facilitated; meanwhile, high-pressure and high-heat flow areas are prevented from being generated on the two-stage surface, and the safety and the reliability in the two-stage in-orbit interstage separation process are improved;
the invention provides a parallel double waverider aircraft which adopts a back-to-back combined layout, applies the appearance of the conventional waverider aircraft to a two-stage orbit-entering horizontal interstage separation scheme, adopts the rolling horizontal separation technology, can easily and quickly enable the two-stage waverider aircraft to return to a designed flight state, and avoids collision after two-stage separation.
When the two-stage combined aircraft performs 90-degree rolling maneuver, the two-stage combined aircraft can realize rolling through aileron control, and can also perform rolling control by changing the spreading lengths of the left wing and the right wing through boosting stage, so that the parallel double-waverider aircraft 90-degree rolling horizontal separation technology has flexibility.
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 diagram of a parallel double-waverider two-stage track-in assembly according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a separation process of a horizontal interstage separation method for two-stage orbital flight with parallel double waverider according to an embodiment of the present invention;
fig. 3 is a schematic diagram of a horizontal interstage separation tail view separation process of the parallel double waverider in fig. 2 according to an embodiment of the present invention.
The reference numerals in the drawings denote the following, respectively:
1-an orbital wave-rider aircraft; 2-boosting level wave-rider aircraft; 3-morphing the wing.
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, the invention specifically designs an aircraft structure with two-stage orbit-entering parallel waverider in the horizontal interstage separation process of a two-stage orbit-entering aircraft, and the parallel double waverider aircraft is a boosting stage waverider aircraft 2 and an orbit stage waverider aircraft 1 aiming at a horizontal take-off and landing two-stage orbit-entering flight task.
The parallel double-waverider aircraft is used as a boosting stage and a track stage of two-stage orbit entering, the boosting stage is a variable span width speed range aircraft with waverider characteristics, the track stage is a waverider, and the designed Mach number of the two-stage waverider is the interstage separation Mach number Ma = 7.
The specific method for constructing the combined structure of the orbital wave-rider aircraft 1 and the boosting wave-rider aircraft 2 under the determined interstage separation condition comprises the following steps:
101, determining reference line types of a track-level wave-rider aircraft 1 and a boosting-level wave-rider aircraft 2 according to an existing two-level orbit-entering aerospace vehicle interstage separation mode;
the datum line type of the boosting level wave-rider aircraft 2 comprises a horizontal line segment, first curve segments connected to two ends of the horizontal line segment, and second curve segments which are located at two ends of the horizontal line segment and are in mirror symmetry and smoothly tangent with the first curve segments;
the datum line type of the track-level waverider aircraft 1 is a horizontal line segment, and the length of the datum line type of the track-level waverider aircraft is equal to that of the horizontal line segment of the datum line type of the boosting-level waverider aircraft 2;
generating wave-multiplying matrix structures of an orbit-level wave-multiplying body aircraft 1 and a boosting-level wave-multiplying body aircraft 2 respectively according to a cone-guided wave-multiplying body generation theory;
102, arranging a track-level vertical tail rudder on the windward side of a wave-rider base body of the track-level wave-rider aircraft 1;
the two sides of the wave-riding base body of the boosting-level wave-riding aircraft 2 are provided with morphing wings 3, and the windward side of the wave-riding base body of the boosting-level wave-riding aircraft 2 is provided with a pair of symmetrical boosting-level vertical tail wing rudders;
and 103, attaching and connecting the surfaces of the waverider matrixes of the track-level waverider aircraft 1 and the boosting-level waverider aircraft 2, which are formed by horizontal line segments, so as to construct a combined structure of the track-level waverider aircraft 1 and the boosting-level waverider aircraft 2.
The middle horizontal plane of the upper surface of the boosting level wave-rider aircraft 2 is attached to the horizontal free flow surface of the track level wave-rider aircraft 1, and no gap exists between the two levels. When the two-stage aircrafts reach the interstage separation condition, the orbit-stage waverider aircraft 1 is horizontally separated forwards along the upper surface of the boosting-stage waverider aircraft 2 under the driving of rocket power, the horizontal separation mode can avoid serious shock wave interference and aerodynamic heat between two stages in the interstage separation process, avoid severe aerodynamic sharp change, and is beneficial to the flight stability and safety of the two stages in the separation process.
In step 101, the specific method for constructing the boost level waverider aircraft 2 is as follows:
step 1011, obtaining a leading edge curve of the boosting level waverider aircraft 2 by the horizontal projection of the datum line type of the boosting level waverider aircraft 2 on the conical shock wave surface;
step 1012, tracking the leading edge curve through a streamline to obtain a lower surface and a trailing edge curve of the boosting level wave-multiplying body aircraft 2;
the self-flow surface formed by the front edge curve forms the upper surface of the boosting level wave-rider aircraft 2;
and 1013, forming the rear end face of the boosting level wave-rider aircraft 2 by the datum line type and the trailing edge curve, and completing the construction of the wave-rider base body of the boosting level wave-rider aircraft 2.
The morphing wing 3 extends from the middle point of the two sides of the leading edge curve of the wave-rider base body of the boosting level wave-rider aircraft 2 to the rear end surface of the wave-rider base body, and expands along the width direction of the wave-rider base body of the boosting level wave-rider aircraft 2 until the end part of the morphing wing 3 is consistent with the rear end surface of the wave-rider base body;
and the morphing wing 3 keeps smooth tangency with the leading edge curve of the waverider base body.
The vertical tail rudder is perpendicular to the upper surface of the wave-rider base body formed by the first curved section, and the projection directions of the vertical tail rudder and the first curved section on the conical shock wave surface are kept consistent.
In the flight control system controlling the deformation of the morphing wing 3 to realize the imbalance of the lift force borne by the two side wings of the boost-level wave-rider aircraft 2, the specifically changed state of the morphing wing 3 comprises the following steps: wing span, sweep angle, and dihedral angle.
After the two-stage parallel waverider forms the combination layout, the parallel double waveriders are restrained by opposite normal forces due to the waverider characteristics of the boosting stage waverider aircraft 2, so that the two-stage combination is connected more tightly before separation.
Due to the normal force constraint, in the two-stage horizontal separation process, the orbit-level wave-rider aircraft 1 can be tightly attached to the surface of the boosting-level wave-rider aircraft 2 and moves forwards horizontally under the power of the rocket.
The horizontal separation mode can not generate a gap between two stages, so that the problem of serious shock wave interference between two stages in the separation process under the hypersonic speed condition is solved:
firstly, a high-pressure and high-heat flow area cannot be generated on the two-stage surface;
and secondly, the unsteady aerodynamic load which changes sharply for two stages in the two-stage separation process is not generated, and the stable operation of the two-stage aircraft in the separation process is facilitated.
After the track-level waverider aircraft 1 is separated from the upper surface of the boosting-level waverider aircraft 2 under the power of the rocket, if the high-lift-ratio waverider aerodynamic characteristics in the design state need to be restored, the track-level waverider needs to roll by 180 degrees.
Under the condition of hypersonic two-stage separation, the track-level waverider rolls 180 degrees and is difficult to operate and high in risk, and the track-level waverider is very easy to collide with a boosting stage, so that a two-stage track entering task fails. In order to solve the problem and apply the wave-rider configuration aircraft to two-stage in-orbit horizontal separation, a parallel double-wave-rider 90-degree rolling horizontal separation technology is proposed:
as shown in fig. 2 and fig. 3, for this purpose, the present invention provides a design method for horizontal interstage separation of a parallel double waverider two-stage orbit aircraft, which includes the following specific steps:
step 100, constructing a combined structure of the orbit-level wave-rider aircraft 1 and the boosting-level wave-rider aircraft 2 under the determined interstage separation condition, so that the orbit-level wave-rider aircraft 1 and the boosting-level wave-rider aircraft 2 are restrained by opposite normal forces in the flight process;
step 200, when the flight of the combined structure reaches an interstage separation condition, the lift forces borne by the two side wings of the boosting stage wave-rider aircraft 2 are unbalanced, and then the combined structure rolls for 90 degrees laterally around the aircraft body;
300, under the condition of keeping the lateral rolling angle posture of the combined body structure rolling for 90 degrees, the track-level waverider aircraft 1 is driven by the power of the track-level waverider aircraft 1 to horizontally separate along the upper surface of the boosting-level waverider aircraft;
after the track-level waverider aircraft 1 is separated from the boosting-level waverider aircraft 2, the track-level waverider aircraft 1 adjusts the imbalance of the lifting forces borne by the two side wings, further continues to roll for 90 degrees laterally under the rolling angle posture of rolling for 90 degrees laterally, and climbs to a target track;
and step 400, enabling the boosting level wave-rider aircraft 2 to reversely roll for 90 degrees under the rolling angle posture of the lateral rolling for 90 degrees to recover the initial flight state through the unbalanced change of the secondary lift force of the two side wings, and realizing the horizontal interstage separation of the boosting level wave-rider aircraft 2 and the track level wave-rider aircraft 1.
In step 200 and step 300, the specific method for controlling the lift imbalance borne by the two side wings of the track-level wave-rider aircraft 1 and the boosting-level wave-rider aircraft 2 comprises the following steps:
both sides of the track-level wave-rider aircraft 1 and the boosting-level wave-rider aircraft 2 are provided with morphing wings 3 and ailerons;
when the combined body structure reaches the interstage separation condition, the boosting stage wave-multiplying body aircraft 2 generates initial rolling under the control of the instantaneous rolling excitation signal generated by the flight control system, and the flight control system controls the deformation of the ailerons and/or the deformation wings 3 to enable the lifting forces borne by the two side wings of the boosting stage wave-multiplying body aircraft 2 to be unbalanced, so that the combined body structure generates rolling torque and initial rolling acceleration.
The combined body rolling excitation and ailerons, deformable wing 3 manipulation and rolling moment cancellation of the orbit-level waverider aircraft 1 and the boosting-level waverider aircraft 2 are uniformly controlled by an aircraft control system.
When the roll damping torque generated by the combined body structure in the roll process is equal to the roll torque in size and reaches balance, the combined body structure rolls regularly.
After the combined body structure is in the roll angle posture of rolling at 90 degrees in the lateral direction, the wingspan of the deformed wing 3 of the boosting step wave-rider aircraft 2 is adjusted to enable the roll torque and the roll damping torque to be balanced, and the roll angle of the combined body structure is maintained to be 90 degrees.
After the rolling moment acting on the combination of the orbit-level wave-rider aircraft and the boosting-level wave-rider aircraft is cancelled, the rolling damping moment borne by the combination enables the combination to start decelerating from a steady rolling motion state and stop.
According to the invention, aiming at the horizontal interstage separation mode of the two-stage orbit entering aircraft, the appearance aircraft combination layout mode of the double waverider (the orbit-level waverider aircraft 1 and the orbit-level waverider aircraft 1) is applied to the two-stage orbit entering task, and the combination of the parallel double waveriders is successfully separated by adopting a 90-degree rolling horizontal separation mode.
When the parallel double-waverider two-stage orbit entering aircraft reaches the interstage separation condition, the wing span of the two-stage combination body is changed by the auxiliary wings of the boosting stage waverider or the left and right deformable wings of the boosting stage waverider flying, so that the left and right wings are unbalanced in lift force, the two-stage combination body rolls around the fuselage in the lateral direction by 90 degrees, and the schematic diagram of the parallel double-waverider two-stage orbit entering aircraft combination body in the lateral direction by 90 degrees is shown in fig. 2.
FIG. 3 is a schematic diagram of the rolling horizontal separation process of the parallel double-waverider two-stage orbital flight vehicle assembly according to the present invention.
The invention provides a 90-degree rolling horizontal interstage separation technology for a parallel double-waverider two-stage orbit entering aircraft, the parallel double-waverider aircraft is taken as the two-stage orbit entering aircraft in a back-to-back combination mode (the boosting stage waverider aircraft 2 and the track stage waverider aircraft 1 are kept to face upwards in an integral waverider mode), the two-stage waveriders are successfully separated through the 90-degree rolling horizontal separation technology, the technical risk is low, safety and reliability are realized, the problems of high pressure, high heat flow and stability in the conventional separation process under the hypersonic speed condition are solved, and the two-stage configuration of the parallel double-waverider is successfully applied.
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 (8)
1. A design method for horizontal interstage separation of a parallel double-waverider two-stage orbit entering aircraft is characterized by comprising the following specific steps:
step 100, constructing a combined structure of the track-level wave-multiplying body aircraft and the boosting-level wave-multiplying body aircraft under the determined interstage separation condition, so that the track-level wave-multiplying body aircraft and the boosting-level wave-multiplying body aircraft are restrained by opposite normal forces in the flight process;
200, when the flight of the combined structure reaches an interstage separation condition, enabling the lift forces borne by the two side wings of the boosting stage wave-rider aircraft to be unbalanced, and further enabling the combined structure to roll for 90 degrees along the lateral direction of the aircraft body;
300, under the condition of keeping the lateral rolling angle posture of the combined body structure rolling for 90 degrees, the track-level waverider aircraft is driven by the power of the track-level waverider aircraft to horizontally separate along the upper surface of the boosting-level waverider aircraft;
after the track-level waverider aircraft is separated from the boosting-level waverider aircraft, the track-level waverider aircraft adjusts the unbalanced lift force borne by the two side wings, further continues to roll for 90 degrees laterally under the rolling angle posture of rolling for 90 degrees laterally, and climbs to a target track;
and step 400, reversely rolling the boosting level wave-rider aircraft by 90 degrees under the rolling angle posture of rolling by 90 degrees in the lateral direction by enabling the lifting forces generated by the two side wings of the boosting level wave-rider aircraft to be unbalanced and changed again, and recovering the initial flight state to realize the horizontal interstage separation of the boosting level wave-rider aircraft and the track level wave-rider aircraft.
2. The design method for horizontal interstage separation of the parallel double-waverider two-stage orbit-entering aircraft according to claim 1, wherein in the steps 200 and 300, the specific method for controlling the imbalance of the lift force borne by the two side wings of the track-stage waverider aircraft and the boost-stage waverider aircraft comprises the following steps:
arranging morphing wings and ailerons on two sides of the track-level waverider aircraft and the boosting-level waverider aircraft;
when the combined structure reaches an interstage separation condition, the boosting stage wave-rider aircraft generates initial rolling under the control of an instantaneous rolling excitation signal generated by the flight control system, and the flight control system controls the aileron action or controls the deformation of the deformed wing to enable the lifting forces borne by the two side wings of the boosting stage wave-rider aircraft to be unbalanced, so that the combined structure generates rolling torque and initial rolling acceleration.
3. The design method for horizontal interstage separation of a parallel double waverider two-stage orbit entering aircraft according to claim 2, wherein when the magnitude of the roll damping torque generated by the combined structure in the process of rolling is equal to the magnitude of the roll torque and reaches a balance, the combined structure rolls regularly;
after the combined structure is in the roll angle posture of rolling 90 degrees in the lateral direction, adjusting the wingspan of the deformed wing of the boosting level wave-rider aircraft to enable the roll torque and the roll damping torque to be balanced, and maintaining the roll angle of the combined structure to be 90 degrees;
after the rolling moment acting on the combination of the orbit-level wave-rider aircraft and the boosting-level wave-rider aircraft is cancelled, the rolling damping moment borne by the combination enables the combination to start decelerating from a steady rolling motion state and stop.
4. The design method of horizontal interstage separation of a parallel double-waverider two-stage orbit entering flight vehicle according to claim 3, wherein in step 100, the specific method for constructing the combined structure of the orbit-grade waverider flight vehicle and the booster-grade waverider flight vehicle under the determined interstage separation condition comprises the following steps:
step 101, determining reference line types of a track-level wave-rider aircraft and a boosting-level wave-rider aircraft according to an existing two-level orbit aerospace craft interstage separation mode;
the datum line type of the boosting level wave-rider aircraft comprises a horizontal line segment, first curve segments connected to two ends of the horizontal line segment, and second curve segments which are located at two ends of the horizontal line segment and are in mirror symmetry and smoothly tangent with the first curve segments;
the datum line type of the track-level waverider aircraft is a horizontal line segment, and the length of the datum line type of the track-level waverider aircraft is equal to the length of the horizontal line segment of the datum line type of the boosting-level waverider aircraft;
generating wave multiplying matrix structures of an orbit-level wave multiplying body aircraft and a boosting-level wave multiplying body aircraft respectively according to a cone-guided wave multiplying body generation theory;
102, arranging a track-level vertical tail wing rudder on the windward side of a wave-rider base body of a track-level wave-rider aircraft;
the method comprises the following steps that (1) deformable wings are arranged on two sides of a wave-riding base body of a boosting level wave-riding aircraft, and a pair of symmetrical boosting level vertical tail wing rudders are arranged on the windward side of the wave-riding base body of the boosting level wave-riding aircraft;
and 103, attaching and connecting the surface of the wave-multiplying base body of the orbit-level wave-multiplying body aircraft formed by the horizontal line segment with the surface of the wave-multiplying base body of the boosting-level wave-multiplying body aircraft formed by the horizontal line segment to construct an assembly structure of the orbit-level wave-multiplying body aircraft and the boosting-level wave-multiplying body aircraft.
5. The design method for horizontal interstage separation of the parallel double-waverider two-stage orbit entering aircraft according to claim 4, wherein in step 101, the specific method for constructing the boost-level waverider aircraft is as follows:
step 1011, obtaining a leading edge curve of the boosting level waverider aircraft by the horizontal projection of the datum line type of the boosting level waverider aircraft on the conical shock wave surface;
step 1012, tracking the front edge curve through a streamline to obtain a lower surface and a rear edge curve of the boosting level wave-multiplying body aircraft;
the upper surface of the boosting level wave-rider aircraft is formed by a self-flow surface formed by the front edge curve;
and 1013, forming the rear end face of the boosting level wave-rider aircraft by the datum line type and the trailing edge curve, and finishing the construction of the wave-rider base body of the boosting level wave-rider aircraft.
6. The design method for horizontal interstage separation of a parallel double-waverider aircraft according to claim 5, wherein the morphing wing extends from the midpoint of the two sides of the leading edge curve of the waverider base of the boost-grade waverider aircraft to the rear end face of the waverider base and extends along the width direction of the waverider base of the boost-grade waverider aircraft until the end of the morphing wing is consistent with the rear end face of the waverider base;
and the leading edge curves of the morphing wings and the waverider base body are kept smooth and tangent.
7. The design method of horizontal interstage separation of a parallel double-waverider two-stage approach-track aircraft according to claim 6, wherein the vertical tail rudder is perpendicular to the upper surface of the waverider base body formed by the first curved section, and the projection directions of the vertical tail rudder and the first curved section on the conical shock surface are consistent.
8. The design method for horizontal interstage separation of the parallel double-waverider two-stage in-orbit aircraft according to claim 6, wherein in the case that the flight control system controls the deformation of the morphing wing to realize the lift imbalance suffered by the two side wings of the booster-stage waverider aircraft, the specifically changed state of the morphing wing comprises the following steps: wing span, sweep angle, and dihedral angle.
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