CN103010454A - Wave rider aircraft with redundant pneumatic distribution and control method thereof - Google Patents
Wave rider aircraft with redundant pneumatic distribution and control method thereof Download PDFInfo
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- CN103010454A CN103010454A CN201210490611XA CN201210490611A CN103010454A CN 103010454 A CN103010454 A CN 103010454A CN 201210490611X A CN201210490611X A CN 201210490611XA CN 201210490611 A CN201210490611 A CN 201210490611A CN 103010454 A CN103010454 A CN 103010454A
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Abstract
The invention discloses a wave rider aircraft with redundant pneumatic distribution. The wave rider aircraft adopts an ideal wave riding configuration as a precursor, two sides of the tail of the wave rider aircraft are provided with rotatable full moving control rudders, the upper and lower surfaces of the tail of the wave rider aircraft are provided with rotatable embedded type control surfaces, and two sides of the bottom surface of the wave rider aircraft are respectively provided with two groups of beveled spray pipes. The wave rider aircraft with the redundant pneumatic distribution, provided by the invention, has the advantages of excellent aerodynamic force property, good controllability, high robustness, and the damping adjustment is realized.
Description
Technical field
The invention belongs to the general structure design technical field of rider aircraft, relate in particular to a kind of rider aircraft and control method thereof with redundant aerodynamic arrangement.
Background technology
Aerodynamic arrangement's design is the basis of gliding type Flight Vehicle Design.Under hypersonic condition, Waverider has preferably aerodynamic performance, becomes a kind of effective trial that breaks through " 1ift-drag ratio barrier " that the conventional aircraft hypersonic flight faces.Yet desirable Waverider, need to carry out correction of the flank shape to desirable Waverider and process in gliding type aerodynamic configuration of aircraft design process without any the steering unit of attitude regulation.
Analysis through us finds, only on the basis of desirable Waverider, edge has carried out suitable passivation correction of the flank shape in the aerodynamic arrangement of existing rider aircraft, and cooperates little jet pipe with base plane to carry out attitude to control.Such topological design, although so that the rider aircraft to depart from desirable Waverider at overall configuration less, have preferably aerodynamic performance, face larger challenge in the Thermal Protection System design.Meanwhile, the means of carrying out attitude control owing to existing rider aircraft are very limited, and there is defective in the poor robustness of its control system in the ability of controlling.In addition, because the damping in pitch of existing rider aircraft is little, its pitch channel is easy to unstability.
Summary of the invention
The technical problem to be solved in the present invention is to overcome the deficiencies in the prior art, provide a kind of simple in structure, aerodynamic performance is excellent, handling good, strong robustness, can realize the rider aircraft with redundant aerodynamic arrangement that damping is regulated, and a kind of control method of simple this rider aircraft also is provided.
For solving the problems of the technologies described above, the technical scheme that the present invention proposes is a kind of rider aircraft with redundant aerodynamic arrangement, this rider aircraft is as precursor take desirable Waverider, the two sides of tail of described rider aircraft is provided with rotating all-movable control, the upper and lower surface of the afterbody of described rider aircraft all offers rotating embedded Control face, and the both sides, bottom surface of described rider aircraft offer respectively two groups of oblique cut nozzle, nozzle with scarfed exit planes.
The technical scheme of the invention described above by the various control parts being applied in the aerodynamic arrangement based on the Waverider design, makes up between the different function uniies mutually, can form the various control means; According to the demand of this layout triple channel (containing pitching, driftage, lift-over) in different mission phases (comprising the differences such as flying height, flying speed) attitude control system, can adopt that different combination control devices is the most effective to the rider attitude of flight vehicle to realize, the control of optimization ground.
In the above-mentioned rider aircraft with redundant aerodynamic arrangement, preferred, described all-movable control comprises left all movable rudder and right all movable rudder, and described left all movable rudder and right all movable rudder are arranged symmetrically along the midplane of described rider aircraft; The both sides of described rider aircraft afterbody are provided with two mounting planes substantially parallel with midplane (this mounting plane is to obtain after two class triangular cones by the outermost both sides, desirable Waverider rear portion of pruning), and the installation rotating shaft of described all-movable control is installed perpendicular to mounting plane.Described left all movable rudder and right all movable rudder can rotate around installation rotating shaft separately.When left all movable rudder and right all movable rudder carry out in the same way deflection (being that left all movable rudder and right all movable rudder carry out cw or conter clockwise deflection simultaneously around installation rotating shaft separately) equal angular, can realize the control to the pitch channel of rider aircraft; When carrying out differential deflection (be left all movable rudder and right all movable rudder around separately simultaneously in the opposite direction deflection of installation rotating shaft) equal angular, left all movable rudder and right all movable rudder can realize the control of rider aircraft roll channel; When deflection angle not simultaneously because stressed asymmetric, all can be influential to pitching, driftage and roll channel, can realize rolling and driftage control to the rider aircraft.Size, shape and the installation site of the control rudder face of described all-movable control is general relevant with selected Waverider concrete shape parameter and needed design performance, and those skilled in the art can carry out calculative determination by Pneumatic design method.
As to further improvement in the technical proposal, the postmedian of described rider aircraft upper surface offers the upper groove of two class triangular tapers (by carrying out correction of the flank shape at desirable Waverider upper surface near the position in trailing edge and the outside, be whittled into two symmetrical expression platforms), the postmedian of described rider aircraft lower surface offers the low groove of two class triangular tapers (by carrying out correction of the flank shape at desirable Waverider lower surface near the position in trailing edge and the outside, be whittled into two symmetrical expression platforms), the afterbody of described upper groove and low groove is equipped with the embedded Control face, described upper groove, low groove and embedded Control face all are arranged symmetrically along the midplane of described rider aircraft.Preferred, described embedded Control face is positioned on the rotating tri-prismoid, and the S. A. of described tri-prismoid is installed in described upper groove and the low groove along the direction perpendicular to described midplane.The bottom surface preferred parallel of described tri-prismoid is in described midplane, and described S. A. is adjacent and parallel with an incline of tri-prismoid.
In above-mentioned preferred technical scheme, the anglec of rotation of described embedded Control face is come the restrictions on the parameters such as stream mode and symmetrical expression platform angle.In the upper groove in symmetrically arranged two embedded Control faces or the low groove symmetrically arranged two embedded Control faces when equidirectional deflection equal angular, can realize the control of rider aircraft pitch channel; And during differential deflection, then can realize the control to the pitching of rider aircraft, driftage and roll channel; The facing up deflection of embedded Control in upper groove, and the embedded Control in the low groove is when facing down deflection, the damping that then can increase the rider aerodynamic configuration of aircraft improves the little defective of desirable Waverider damping; When deflection angle not simultaneously because stressed asymmetric, all can be influential to pitching, driftage and roll channel.
As to further improvement in the technical proposal, in the described rider aircraft, every group of described oblique cut nozzle, nozzle with scarfed exit plane is comprised of upper oblique cut nozzle, nozzle with scarfed exit plane unit, middle oblique cut nozzle, nozzle with scarfed exit plane unit and lower oblique cut nozzle, nozzle with scarfed exit plane unit, and described two groups of oblique cut nozzle, nozzle with scarfed exit planes are arranged symmetrically along the midplane of described rider aircraft.Preferred, described upper and lower oblique cut nozzle, nozzle with scarfed exit plane unit is positioned at same perpendicular, and compares the more close described midplane in middle oblique cut nozzle, nozzle with scarfed exit plane unit; The injection direction of described upper oblique cut nozzle, nozzle with scarfed exit plane unit up, the injection direction of described lower oblique cut nozzle, nozzle with scarfed exit plane unit down, the injection direction of described middle oblique cut nozzle, nozzle with scarfed exit plane unit is outwardly.By our repeatedly experiment measuring and calculating, the axis of described upper oblique cut nozzle, nozzle with scarfed exit plane unit and horizontal surface preferably are 30 °～60 ° elevations angle, the axis of described lower oblique cut nozzle, nozzle with scarfed exit plane unit preferably is 30 °～60 ° angles of depression (particularly preferably the elevation angle angle with upper oblique cut nozzle, nozzle with scarfed exit plane unit is identical) with horizontal surface, and the axis of described middle oblique cut nozzle, nozzle with scarfed exit plane unit and midplane preferably are 30 °～60 ° angles.Two groups of oblique cut nozzle, nozzle with scarfed exit planes mainly used when the initial stage, atmosphere was thinner reentering: work simultaneously or two lower oblique cut nozzle, nozzle with scarfed exit plane unit when working simultaneously when two upper oblique cut nozzle, nozzle with scarfed exit plane unit, can realize the control of rider aircraft pitch channel; And the control of rider vehicle yaw passage then can be realized when working independently in the middle oblique cut nozzle, nozzle with scarfed exit plane unit on left side or right side; When working simultaneously in the upper oblique cut nozzle, nozzle with scarfed exit plane unit in left side and the lower oblique cut nozzle, nozzle with scarfed exit plane unit on right side, perhaps when work simultaneously in the upper oblique cut nozzle, nozzle with scarfed exit plane unit on the lower oblique cut nozzle, nozzle with scarfed exit plane unit in left side and right side, then can realize the control of rider aircraft roll channel.
As a total technical conceive, the present invention also provides a kind of control method of above-mentioned rider aircraft, and the size of incoming flow dynamic pressure is carried out compound type to the rider aircraft and controlled during by the rider aircraft flight, specifically comprises following operation:
When incoming flow dynamic pressure during less than a certain value (preferably as 100 handkerchiefs) (corresponding rider aircraft reenters the starting stage of glide process), the flying height of rider aircraft is higher at this moment, atmosphere is thin, dynamic pressure is lower, the actuating force of each air operated control face (comprising all-movable control and embedded Control face) is less, enough Torque Control rider attitude of flight vehicle can not be provided, almost do not have the effect of attitude control, at this moment, the control of oblique cut nozzle, nozzle with scarfed exit plane plays a leading role, and can utilize described two groups of oblique cut nozzle, nozzle with scarfed exit planes realization to effective control of rider attitude of flight vehicle;
Because the work efficiency of oblique cut nozzle, nozzle with scarfed exit plane and pneumatic control surface all is closely related with the incoming flow dynamic pressure in the rider aircraft of the present invention, therefore, when the incoming flow dynamic pressure increased, the work efficiency of oblique cut nozzle, nozzle with scarfed exit plane descended, and the work efficiency of air operated control face then rises; When incoming flow dynamic pressure during greater than a certain value (preferably as 460 handkerchiefs) (when correspondence reenters the main phase of glide process), then can utilize described all-movable control and embedded Control face to carry out combined operation, realize the effective control to the rider attitude of flight vehicle;
When (for example between 100 handkerchiefs～460 handkerchiefs), carry out common combination by described two groups of oblique cut nozzle, nozzle with scarfed exit planes, all-movable control and embedded Control face and handle between two cut off value when the incoming flow dynamic pressure, realize the effective control to the rider attitude of flight vehicle.
Because the above-mentioned redundant aerodynamic arrangement that the present invention proposes does not comprise vertical tail, so the Lateral static stability of rider aircraft then mainly relies on the upper anti-design of described all-movable control to realize.When the rider aircraft produced sideslip, difference appearred in lift and distribution thereof that upper anti-all-movable control will cause the rider aircraft left and right sides to be subject to, thereby produced the lift-over countermoment.
The above-mentioned redundant aerodynamic arrangement that the present invention proposes can also produce yawing moment with the drag rudder work pattern by described embedded Control face.But, in actual design process, very responsive to yaw angle as power, the hot feature of the hypersonic gliding type rider aircraft of basic layout for adopting Waverider, the motor-driven main control roll channel attitude of passing through in its horizontal course changes, and realizes to roll the turning mode.
Compared with prior art, the invention has the advantages that: it is little that the redundant aerodynamic arrangement of the present invention departs from desirable Waverider, thereby still possess its aerodynamic performance more excellent under hypersonic condition; Meanwhile, the present invention by introducing the compound type mode of all-movable control, embedded Control face and oblique cut nozzle, nozzle with scarfed exit plane, has not only avoided the severe Aerodynamic Heating problem that conventional in layout faces under hypersonic condition on the Waverider basis.And the embedded Control face also can be used as the artificial damping device and uses, and improves the little defective of desirable Waverider damping.Because the control of the attitude of rider aircraft of the present invention can realize by the multiple combination mode of six air operated control faces and two groups of oblique cut nozzle, nozzle with scarfed exit planes, therefore its Control System Design exists redundant, the strong robustness of control system, significant to effective control of hypersonic gliding type rider attitude of flight vehicle.
Description of drawings
Fig. 1 is the structural representation (block diagram) that has the rider aircraft of redundant aerodynamic arrangement in the embodiment of the invention, and shade namely represents the position (lower same) at embedded Control face place among the figure.
Fig. 2 is the birds-eye view that has the rider aircraft of redundant aerodynamic arrangement in the embodiment of the invention.
Fig. 3 is the schematic diagram of all-movable control when deflection in the same way of rider aircraft in the embodiment of the invention.
Fig. 4 is the schematic diagram of all-movable control when differential deflection of rider aircraft in the embodiment of the invention.
Fig. 5 is the front view that has the rider aircraft of redundant aerodynamic arrangement in the embodiment of the invention.
Fig. 6 is the partial enlarged drawing of rider aircraft postmedian among Fig. 5.
Fig. 7 is the schematic diagram of embedded Control face when deflection in the same way of rider aircraft upper groove in the embodiment of the invention.
Fig. 8 is the schematic diagram of embedded Control face when differential deflection of rider aircraft upper groove in the embodiment of the invention.
Fig. 9 is the left view that has the rider aircraft of redundant aerodynamic arrangement in the embodiment of the invention.
Figure 10 is the scheme of installation (volume rendering behind local the amplification) of the right oblique cut nozzle, nozzle with scarfed exit plane group of rider aircraft in the embodiment of the invention.
Figure 11 is the flight path schematic diagram of rider aircraft in the embodiment of the invention.
Figure 12 is the variation diagram of rider aircraft starting stage oblique cut nozzle, nozzle with scarfed exit plane control torque in the embodiment of the invention.
Figure 13 is the variation diagram of a rider aircraft starting stage angle of rudder reflection in the embodiment of the invention.
Marginal data:
1, left all movable rudder; 2, upper left embedded Control face; 3, upper right embedded Control face; 4, right all movable rudder; 5, bottom right embedded Control face; 6, lower-left embedded Control face; 7, left oblique cut nozzle, nozzle with scarfed exit plane group; 8, right oblique cut nozzle, nozzle with scarfed exit plane group; 81, upper right oblique cut nozzle, nozzle with scarfed exit plane unit; 82, right oblique cut nozzle, nozzle with scarfed exit plane unit; 83, bottom right oblique cut nozzle, nozzle with scarfed exit plane unit; 9, tri-prismoid; 10, rotating shaft is installed; 11, mounting plane; 12, S. A..
The specific embodiment
The invention will be further described with concrete preferred embodiment below in conjunction with Figure of description, but protection domain not thereby limiting the invention.
Embodiment:
A kind of rider aircraft that has redundant aerodynamic arrangement such as Fig. 1～Figure 10, this rider aircraft is as precursor take desirable Waverider, the two sides of tail of this rider aircraft is provided with rotating all-movable control, the upper and lower surface of the afterbody of this rider aircraft all offers rotating embedded Control face, and the both sides, bottom surface of this rider aircraft offer respectively two groups of oblique cut nozzle, nozzle with scarfed exit planes.
Such as Fig. 1～shown in Figure 4, in the above-mentioned rider aircraft with redundant aerodynamic arrangement, all-movable control comprises left all movable rudder 1 and right all movable rudder 4, and left all movable rudder 1 and right all movable rudder 4 are arranged symmetrically along the midplane of rider aircraft; It is to obtain after two class triangular cones by the outermost both sides, desirable Waverider rear portion of pruning that the both sides of rider aircraft afterbody are provided with two these mounting planes 11 of the mounting plane 11(substantially parallel with midplane), the installation rotating shaft 10 of all-movable control is perpendicular to mounting plane 11 installings.Left all movable rudder 1 and right all movable rudder 4 can rotate around installation rotating shaft 10 separately.
As shown in Figure 7 and Figure 8, the postmedian of the present embodiment rider aircraft upper surface offers the upper groove of two class triangular tapers (by carrying out correction of the flank shape at desirable Waverider upper surface near the position in trailing edge and the outside, be whittled into two symmetrical expression platforms), the postmedian of rider aircraft lower surface offers the low groove (by carrying out correction of the flank shape at desirable Waverider lower surface near the position in trailing edge and the outside, being whittled into two symmetrical expression platforms) of two class triangular tapers.The afterbody of upper groove and low groove is equipped with the embedded Control face, and upper groove, low groove and embedded Control face all are arranged symmetrically along the midplane M of rider aircraft.Embedded Control face in the present embodiment is provided with four altogether, comprises respectively the upper left embedded Control face 2 and the upper right embedded Control face 3 that are arranged in upper groove, is arranged in bottom right embedded Control face 5 and the lower-left embedded Control face 6 of low groove; Each embedded Control face all is positioned on the rotating tri-prismoid 9, and the S. A. 12 of each tri-prismoid 9 is installed in upper groove and the low groove along the direction perpendicular to midplane M.The bottom surface of tri-prismoid 9 is parallel to midplane M, and S. A. 12 is adjacent and parallel with an incline (referring to Fig. 7 and Fig. 8) of tri-prismoid 9.
As shown in Figure 9 and Figure 10, two groups of oblique cut nozzle, nozzle with scarfed exit planes in the rider aircraft of the present embodiment refer to respectively left oblique cut nozzle, nozzle with scarfed exit plane group 7 and right oblique cut nozzle, nozzle with scarfed exit plane group 8, every group of oblique cut nozzle, nozzle with scarfed exit plane forms by upper oblique cut nozzle, nozzle with scarfed exit plane unit, middle oblique cut nozzle, nozzle with scarfed exit plane unit and lower oblique cut nozzle, nozzle with scarfed exit plane unit, as shown in figure 10, right oblique cut nozzle, nozzle with scarfed exit plane group 8 namely includes upper right oblique cut nozzle, nozzle with scarfed exit plane unit 81,83, the two groups of oblique cut nozzle, nozzle with scarfed exit planes in right oblique cut nozzle, nozzle with scarfed exit plane unit 82 and oblique cut nozzle, nozzle with scarfed exit plane unit, bottom right are arranged symmetrically along the midplane of rider aircraft.As shown in figure 10, upper right oblique cut nozzle, nozzle with scarfed exit plane unit 81 and oblique cut nozzle, nozzle with scarfed exit plane unit, bottom right 83 are positioned at same perpendicular Y, and compare right oblique cut nozzle, nozzle with scarfed exit plane unit 82 more close midplane M; The injection direction of upper right oblique cut nozzle, nozzle with scarfed exit plane unit 81 up, the injection direction of oblique cut nozzle, nozzle with scarfed exit plane unit, bottom right 83 down, the injection direction of right oblique cut nozzle, nozzle with scarfed exit plane unit 82 is outwardly.By our repeatedly experiment measuring and calculating, the axis of upper right oblique cut nozzle, nozzle with scarfed exit plane unit 81 is horizontal by 60 ° of angle of elevation alpha in the present embodiment, the axis of oblique cut nozzle, nozzle with scarfed exit plane unit, bottom right 83 is horizontal by 60 ° of angle of depression β, and the axis of right oblique cut nozzle, nozzle with scarfed exit plane unit 82 and midplane M(are perpendicular Y) be 60 ° of angle γ.
The control method of the above-mentioned rider aircraft of the present embodiment, the size of incoming flow dynamic pressure is carried out compound type to the rider aircraft and is controlled during by the rider aircraft flight, in the present embodiment with 96 handkerchiefs and the 479 handkerchiefs train spacing point as the incoming flow dynamic pressure, be the transformation point that attitude control mode changes, specifically comprise following operation:
When incoming flow dynamic pressure during less than 96 handkerchief (corresponding rider aircraft reenters the starting stage of glide process), the flying height of rider aircraft is higher at this moment, atmosphere is thin, dynamic pressure is lower, the actuating force of each air operated control face (comprising all-movable control and embedded Control face) is less, enough Torque Control rider attitude of flight vehicle can not be provided, almost do not have the effect of attitude control, at this moment, the control of oblique cut nozzle, nozzle with scarfed exit plane plays a leading role, and can utilize two groups of oblique cut nozzle, nozzle with scarfed exit planes realizations to effective control of rider attitude of flight vehicle;
Because the work efficiency of oblique cut nozzle, nozzle with scarfed exit plane and pneumatic control surface all is closely related with the incoming flow dynamic pressure in the rider aircraft of the present invention, therefore, when the incoming flow dynamic pressure increased, the work efficiency of oblique cut nozzle, nozzle with scarfed exit plane descended, and the work efficiency of air operated control face then rises; When incoming flow dynamic pressure during greater than 479 handkerchief (when correspondence reenters the main phase of glide process), then can utilize all-movable control and embedded Control face to carry out combined operation, realize the effective control to the rider attitude of flight vehicle;
When the incoming flow dynamic pressure is between 96 handkerchiefs～479 handkerchiefs, carry out common combination by two groups of oblique cut nozzle, nozzle with scarfed exit planes, all-movable control and embedded Control face and handle, realize the effective control to the rider attitude of flight vehicle.
It is as shown in table 1 below that the control mechanism of the present embodiment is controlled array mode:
Table 1: the aircraft control mechanism is chosen judgement
| Incoming flow dynamic pressure (Pa) | Jet pipe | All movable rudder | Upper embedded Control face | Lower embedded |
| 0～96 | Be | - | - | - |
| 96～479 | Be | Be | Be | Be |
| 479～ | - | Be | Be | Be |
If the incoming flow dynamic pressure is
Required control torque is M
Instruction, then specifically be allocated as follows:
M
Jet pipe=kM
Instruction
M
Pneumatic=(1-k) M
Instruction
When adopting oblique cut nozzle, nozzle with scarfed exit plane to realize attitude control, always have 6 oblique cut nozzle, nozzle with scarfed exit plane unit for the aerodynamic arrangement of the present embodiment design and realize control to 3 passages, in theory control torque be assigned countless versions, thereby realize Redundant Control.
When adopting six air operated control faces (comprising all-movable control and embedded Control face) to realize the attitude control of rider aircraft, utilize six control surface realizations to the control of three passages, can realize Redundant Control, its control allocative decision has countless versions in theory, can adopt the methods such as direct distribution method to carry out the distribution of control torque, the method of the total angle of rudder reflection minimum of recommend adoption is distributed, namely the angle of inclination sum of six air operated control faces is minimum, can take full advantage of like this control ability of each control surface.
Be controlled to be example with the flight of the present embodiment rider aircraft under concrete flying condition, its design flight path as shown in figure 11, it flies the starting stage (in front 300 seconds), because highly higher, air is thinner, the incoming flow dynamic pressure is less, this moment, attitude control was finished jointly by two groups of oblique cut nozzle, nozzle with scarfed exit planes and pneumatic control surface, three direction control torques and dynamic pressure that Figure 12 has provided that the starting stage needs that oblique cut nozzle, nozzle with scarfed exit plane provides are schemed over time, Figure 13 then is the variation diagram of the angle of inclination of one of them air operated control face, can find out, when incoming flow dynamic pressure during less than 96 handkerchief, control torque is provided by oblique cut nozzle, nozzle with scarfed exit plane, along with the reduction of flying height, the incoming flow dynamic pressure increases gradually, and control torque is born jointly by oblique cut nozzle, nozzle with scarfed exit plane and pneumatic control surface, when incoming flow dynamic pressure during greater than 476 handkerchief, attitude control is mainly realized by each air operated control face.
Because the surperficial Aerodynamic Heating situation of hypersonic gliding type rider aircraft is very severe, usually do not allow it to have angle of side slip or only allow it to have less angle of side slip, its horizontal course is motor-driven will realize in canting turning mode, namely realize by the attitude control to roll channel.
In the above-mentioned control method, the concrete operation method of all-movable control is: when left all movable rudder 1 and right all movable rudder 4 carry out in the same way deflection equal angular, can realize the control to the pitch channel of rider aircraft; When carrying out differential deflection equal angular, left all movable rudder 1 and right all movable rudder 4 can realize the control of rider aircraft roll channel; When deflection angle not simultaneously because stressed asymmetric, all can be influential to pitching, driftage and roll channel, can realize rolling and driftage control to the rider aircraft.
In the above-mentioned control method, the anglec of rotation of embedded Control face is come the restrictions on the parameters such as stream mode and symmetrical expression platform angle.Symmetrically arranged bottom right embedded Control face 5 and lower-left embedded Control face 6 in symmetrically arranged upper left embedded Control face 2 and upper right embedded Control face 3(or the low groove in the upper groove) when equidirectional deflection equal angular, can realize the control of rider aircraft pitch channel; And during differential deflection, then can realize the control to the pitching of rider aircraft, driftage and roll channel; Upper left embedded Control face 2 and upper right embedded Control face 3 in upper groove upward deflect, and the bottom right embedded Control face 5 in the low groove and lower-left embedded Control face 6 are when deflecting down, then can increase the damping of rider aerodynamic configuration of aircraft, improve the little defective of desirable Waverider damping; When deflection angle not simultaneously because stressed asymmetric, all can be influential to pitching, driftage and roll channel.
In the above-mentioned control method, two groups of oblique cut nozzle, nozzle with scarfed exit planes mainly use at the initial stage that reentering: work simultaneously or two lower oblique cut nozzle, nozzle with scarfed exit plane unit when working simultaneously when two upper oblique cut nozzle, nozzle with scarfed exit plane unit, can realize the control of rider aircraft pitch channel; And the control of rider vehicle yaw passage then can be realized when working independently in the middle oblique cut nozzle, nozzle with scarfed exit plane unit on left side or right side; When working simultaneously in the upper oblique cut nozzle, nozzle with scarfed exit plane unit in left side and the lower oblique cut nozzle, nozzle with scarfed exit plane unit on right side, perhaps when work simultaneously in the upper oblique cut nozzle, nozzle with scarfed exit plane unit on the lower oblique cut nozzle, nozzle with scarfed exit plane unit in left side and right side, then can realize the control of rider aircraft roll channel.
Claims (10)
1. rider aircraft with redundant aerodynamic arrangement, this rider aircraft is as precursor take desirable Waverider, it is characterized in that: the two sides of tail of described rider aircraft is provided with rotating all-movable control, the upper and lower surface of the afterbody of described rider aircraft all offers rotating embedded Control face, and the both sides, bottom surface of described rider aircraft offer respectively two groups of oblique cut nozzle, nozzle with scarfed exit planes.
2. the rider aircraft with redundant aerodynamic arrangement according to claim 1, it is characterized in that: described all-movable control comprises left all movable rudder and right all movable rudder, described left all movable rudder and right all movable rudder are arranged symmetrically along the midplane of described rider aircraft; The both sides of described rider aircraft afterbody are provided with two mounting planes substantially parallel with midplane, and the installation rotating shaft of described all-movable control is installed perpendicular to mounting plane.
3. the rider aircraft with redundant aerodynamic arrangement according to claim 1 and 2, it is characterized in that: the postmedian of the upper surface of described rider aircraft offers the upper groove of two class triangular tapers, the postmedian of the lower surface of described rider aircraft offers the low groove of two class triangular tapers, the afterbody of described upper groove and low groove is equipped with the embedded Control face, and described upper groove, low groove and embedded Control face all are arranged symmetrically along the midplane of described rider aircraft.
4. the rider aircraft with redundant aerodynamic arrangement according to claim 3, it is characterized in that: described embedded Control face is positioned on the rotating tri-prismoid, and the S. A. of described tri-prismoid is installed in described upper groove and the low groove along the direction perpendicular to described midplane.
5. the rider aircraft with redundant aerodynamic arrangement according to claim 4, it is characterized in that: the bottom surface of described tri-prismoid is parallel to described midplane, and described S. A. is adjacent and parallel with an incline of tri-prismoid.
6. the rider aircraft with redundant aerodynamic arrangement according to claim 1 and 2, it is characterized in that: every group of described oblique cut nozzle, nozzle with scarfed exit plane is comprised of upper oblique cut nozzle, nozzle with scarfed exit plane unit, middle oblique cut nozzle, nozzle with scarfed exit plane unit and lower oblique cut nozzle, nozzle with scarfed exit plane unit, and described two groups of oblique cut nozzle, nozzle with scarfed exit planes are arranged symmetrically along the midplane of described rider aircraft.
7. the rider aircraft with redundant aerodynamic arrangement according to claim 6, it is characterized in that: described upper and lower oblique cut nozzle, nozzle with scarfed exit plane unit is positioned at same perpendicular, and compares the more close described midplane in middle oblique cut nozzle, nozzle with scarfed exit plane unit; The injection direction of described upper oblique cut nozzle, nozzle with scarfed exit plane unit up, the injection direction of described lower oblique cut nozzle, nozzle with scarfed exit plane unit down, the injection direction of described middle oblique cut nozzle, nozzle with scarfed exit plane unit is outwardly.
8. the rider aircraft with redundant aerodynamic arrangement according to claim 7, it is characterized in that: the axis of described upper oblique cut nozzle, nozzle with scarfed exit plane unit is horizontal by 30 °～60 ° elevations angle, the axis of described lower oblique cut nozzle, nozzle with scarfed exit plane unit is horizontal by 30 °～60 ° angles of depression, and the axis of described middle oblique cut nozzle, nozzle with scarfed exit plane unit and midplane are 30 °～60 ° angles.
9. the control method of each described rider aircraft in the claim 1～8 is characterized in that, the size of incoming flow dynamic pressure is carried out compound type to the rider aircraft and controlled during by the rider aircraft flight, specifically comprises following operation:
When incoming flow dynamic pressure during less than 100 handkerchief, utilize described two groups of oblique cut nozzle, nozzle with scarfed exit planes to realize effective control to the rider attitude of flight vehicle;
When incoming flow dynamic pressure during greater than 460 handkerchief, utilize described all-movable control and embedded Control face to carry out combined operation, realize the effective control to the rider attitude of flight vehicle;
When the incoming flow dynamic pressure is between 100 handkerchiefs～460 handkerchiefs, carry out common combination by described two groups of oblique cut nozzle, nozzle with scarfed exit planes, all-movable control and embedded Control face and handle, realize the effective control to the rider attitude of flight vehicle.
10. the control method of rider aircraft according to claim 9 is characterized in that:
The control method of described all-movable control is specially: carry out in the same way deflection equal angular by making all-movable control, realize the control to the pitch channel of rider aircraft; By making all-movable control carry out differential deflection equal angular, realize the control of rider aircraft roll channel; By making all-movable control deflection different angles, realize rolling and driftage control to the rider aircraft;
The control method of described embedded Control face is specially: by making the embedded Control face offered on the described rider aircraft upper surface in equidirectional deflection equal angular or making embedded Control face that its lower surface offers in equidirectional deflection equal angular, realize the control to rider aircraft pitch channel; By making the differential deflection of embedded Control face of offering on the described rider aircraft upper surface or making the differential deflection of embedded Control face of offering on its lower surface, realize the control to the pitching of rider aircraft, driftage and roll channel; By making the facing up deflection of embedded Control of offering on the described rider aircraft upper surface, make simultaneously the embedded Control of offering on the lower surface deflection that faces down, to increase the damping of rider aerodynamic configuration of aircraft;
The control method of described two groups of oblique cut nozzle, nozzle with scarfed exit planes is specially: by making two groups of oblique cut nozzle, nozzle with scarfed exit planes obliquely upward or tiltedly the below is jet, realize the control to rider aircraft pitch channel; By making one group of oblique cut nozzle, nozzle with scarfed exit plane in two groups of oblique cut nozzle, nozzle with scarfed exit planes outwards jet, realize the control of rider vehicle yaw passage; Another group oblique cut nozzle, nozzle with scarfed exit plane is jet downwards by making one group of oblique cut nozzle, nozzle with scarfed exit plane make progress jet, realizes the control of rider aircraft roll channel.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210490611XA CN103010454A (en) | 2012-11-27 | 2012-11-27 | Wave rider aircraft with redundant pneumatic distribution and control method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210490611XA CN103010454A (en) | 2012-11-27 | 2012-11-27 | Wave rider aircraft with redundant pneumatic distribution and control method thereof |
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| CN103010454A true CN103010454A (en) | 2013-04-03 |
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| CN (1) | CN103010454A (en) |
Cited By (6)
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| CN103662087A (en) * | 2013-12-11 | 2014-03-26 | 厦门大学 | Hypersonic aerocraft and air inlet internal and external waverider integrated design method |
| CN104477376A (en) * | 2014-12-23 | 2015-04-01 | 北京航空航天大学 | Combined pneumatic control method for aerodynamic rudder/reaction control system of hypersonic flight vehicle |
| CN104724281A (en) * | 2015-02-13 | 2015-06-24 | 中国科学院力学研究所 | Combined front-edge wave rider design method and combined front-edge wave rider |
| CN109969374A (en) * | 2019-04-09 | 2019-07-05 | 中国空气动力研究与发展中心计算空气动力研究所 | Biao Mo aerodynamic arrangement and design method for hypersonic boundary layer transition research |
| CN110525679A (en) * | 2019-08-28 | 2019-12-03 | 北京航空航天大学 | Hypersonic embedded Waverider design method |
| CN111003160A (en) * | 2019-11-28 | 2020-04-14 | 中国运载火箭技术研究院 | Self-adaptive high-speed aircraft layout based on wing tip deformation |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662087A (en) * | 2013-12-11 | 2014-03-26 | 厦门大学 | Hypersonic aerocraft and air inlet internal and external waverider integrated design method |
| CN103662087B (en) * | 2013-12-11 | 2015-07-15 | 厦门大学 | Hypersonic aerocraft and air inlet internal and external waverider integrated design method |
| CN104477376A (en) * | 2014-12-23 | 2015-04-01 | 北京航空航天大学 | Combined pneumatic control method for aerodynamic rudder/reaction control system of hypersonic flight vehicle |
| CN104724281A (en) * | 2015-02-13 | 2015-06-24 | 中国科学院力学研究所 | Combined front-edge wave rider design method and combined front-edge wave rider |
| CN109969374A (en) * | 2019-04-09 | 2019-07-05 | 中国空气动力研究与发展中心计算空气动力研究所 | Biao Mo aerodynamic arrangement and design method for hypersonic boundary layer transition research |
| CN110525679A (en) * | 2019-08-28 | 2019-12-03 | 北京航空航天大学 | Hypersonic embedded Waverider design method |
| CN111003160A (en) * | 2019-11-28 | 2020-04-14 | 中国运载火箭技术研究院 | Self-adaptive high-speed aircraft layout based on wing tip deformation |
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