CN109815572A - The re-entry space vehicle design method and re-entry space vehicle of two-graded fusion - Google Patents
The re-entry space vehicle design method and re-entry space vehicle of two-graded fusion Download PDFInfo
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- CN109815572A CN109815572A CN201910039339.5A CN201910039339A CN109815572A CN 109815572 A CN109815572 A CN 109815572A CN 201910039339 A CN201910039339 A CN 201910039339A CN 109815572 A CN109815572 A CN 109815572A
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Abstract
The present invention provides the re-entry space vehicle design methods and re-entry space vehicle of a kind of two-graded fusion.By the way of two sub- grade fusions, the aeroperformance of re-entry space vehicle can be improved to avoid the high heat in two in the prior art sub- grade gaps, reduce launch cost.
Description
Technical field
The present invention relates to field of flight vehicle design, the re-entry space vehicle design method and empty day for being related to a kind of two-graded fusion fly
The re-entry space vehicle design method and re-entry space vehicle of row device more particularly to a kind of two-graded fusion based on Waverider.
Background technique
Currently, the almost all of space loading transmitting in the whole world is responsible for by disposable rocket delivery system, expense is high
It is expensive.Spatial emission cost can be greatly reduced by repeatedly using in reusable re-entry space vehicle.In addition, empty day flight
Device is different from the Vertical Launch of rocket, it can be used as low earth orbit load transportation platform in normal airfield horizontal take-off,
It is alternatively arranged as air and space operation weapon platform.
After studying successfully with U.S. space shuttle, it is more advanced based on air suction type combination that various countries propose technology one after another
The Horizontal Take-off and Landing re-entry space vehicle scheme of power, such as the empty day plan of U.S.'s proposition, " Sang Geer " scheme of Germany's proposition, English
" Huo Tuoer " scheme that state proposes.But since the technical difficulty of Single Stage To Orbit re-entry space vehicle is huge, main cause is will be a large amount of
Architecture quality bring space into, the requirement to structural coefficient is extremely stringent, enters the orbit so research emphasis is transferred to two-stage by the U.S.
Re-entry space vehicle.Two-stage is entered the orbit, and re-entry space vehicle technical difficulty is relatively low, and significantly simpler to implement, a sub- grade is using suction
Gas formula assembly power, two sub- grades will faster form practical ability using rocket-powered two-stage re-entry space vehicle of entering the orbit.
The flight performance requirement for the sub- grade of re-entry space vehicle two of being entered the orbit due to two-stage and the difference of flight environment of vehicle, to aerodynamic configuration
Design also proposed different design objectives.Therefore, two-stage is designed simultaneously there is no a kind of design method at present, Ji Nengman
The respective flight performance requirement of foot, and can guarantee still there is good aeroperformance when fusion.
Waverider aircraft is based on setting up enumeration and being designed, and is deteriorated in off-design point flying quality, is unable to satisfy modern fly
The fast domain of capable width requires, by the way that by the Waverider Combined design of two kinds of different designs points, can solve Waverider cannot achieve wide speed
The shortcomings that domain flight, has further expanded the practicability of Waverider aircraft.
Re-entry space vehicle is one kind using air suction type combined engine as power, can be in dense atmosphere, close to space vehicle
The novel world round transport aircraft.Enter the orbit re-entry space vehicle and Single Stage To Orbit sky day of two-stage can be divided into according to series of entering the orbit to fly
Row device.Single Stage To Orbit can substantially reduce launch cost, but implement more difficulty, and main cause is by a large amount of architecture quality
Bring space into, the requirement to structural coefficient is extremely stringent.And two-stage is entered the orbit, re-entry space vehicle technical difficulty is relatively low, realizes
Next relatively simple, a sub- grade uses rocket-powered two-stage to enter the orbit re-entry space vehicle using air suction type assembly power, two sub- grades will
Faster form practical ability.
Traditional two-stage re-entry space vehicle is all the back that two sub- grades are simply mounted to a sub- grade, deposits between two-stage
In a gap.When flying speed is higher and higher, heat between gap it is difficult to predict and control, the structure of aircraft can be made
At destruction.In addition, the aerodynamic characteristic of this mode can not meet the requirement of high-speed flight well, so that re-entry space vehicle
Aeroperformance has a degree of decline.
Due to the particularity of re-entry space vehicle aerial mission, aircraft is needed to can satisfy the performance in wide fast domain, big airspace
Index, and " lift resistance ratio " barrier can be broken through, but conventional aircraft is unable to reach this demand.
To further decrease space transportation cost and improving transportation, countries in the world are all being given priority to air suction type
Combined engine be power, it is reusable and can the novel world of dense atmosphere, close to space vehicle round transport fly
Row device, i.e. re-entry space vehicle.Enter the orbit two sub- grades of re-entry space vehicle of existing two-stage are usually to separately design, and by two sub- grades
It is fixed on back or the abdomen of a sub- grade.When aircraft is with hypersonic flight, the gap between two-stage can generate uncontrollable
High-temperature area, structure is adversely affected, reusable requirement is unsatisfactory for.And since two sub- grades are individually to set
Meter, so the aerodynamic characteristic after being fixed together is not easy to predict and control.
With the fast development of aeronautical and space technology, aircraft faces higher performance indicator requirement, so that aircraft
It designs and develops to the direction in wide fast domain, big airspace.The aerodynamic arrangement of aircraft is maximum flying speed, the maximum for improving aircraft
One of deciding factors of performances such as flying distance.The aerodynamic configuration of conventional aircraft when flight, is deposited under the conditions of hypersonic
At as caused by shape " lift resistance ratio barrier ".In order to break through this limitation, waverider-derived becomes the research hotspot in the field
One of.But the design of traditional Waverider aircraft is completed under specified single design Mach number, in design Mach number
Under, there is admirably aeroperformance, and in non-design Mach number, aeroperformance is decreased obviously, this makes Waverider aircraft
This advantage of high lift-drag ratio substantially weakens.
Summary of the invention
The present invention provides a kind of re-entry space vehicle design method of two-graded fusion based on Waverider.It can be to avoid existing skill
High temperature high heat in art in two sub- grade gaps improves the aeroperformance of re-entry space vehicle, reduces launch cost.
In order to solve the above technical problems, the technical scheme adopted by the invention is that: include the following steps:
Step 1: designing has compressing surface, freely carrys out stream interface and combines Waverider perpendicular to the rear end face of direction of flow
Parameter:
Step 2: choosing the section (EF) of combination Waverider benchmark cone as plane where the rear end face of combination Waverider, make
Its section (EF) is overlapped with the rear end face for combining Waverider, is combined the length of Waverider benchmark cone according to geometrical relationship and is somebody's turn to do
The radius of shock wave section circle at section；
Step 3: according to the parameter for the combination Waverider that step 1 is arranged, obtain combination Waverider freely carrys out stream interface rear
Line equation obtains the rear line for freely carrying out stream interface of combination Waverider；
Step 4: by combine Waverider freely come stream interface rear line equation carry out it is discrete, obtain combination Waverider point cloud number
According to the free direction of flow that will combine Waverider point cloud data along combination Waverider bores projection to the shock wave for combining Waverider, obtains
Freely carry out stream interface to the costa and combination Waverider for combining Waverider；
Step 5: by the costa of combination Waverider, being solved to obtain the pressure of combination Waverider according to streamlined impeller method
The rear line in contracting face and combination Waverider compressing surface obtains combination Waverider；
Step 6: the design parameter of given Upper Stage Waverider:
Step 7: by the design parameter of the upper surface of the given grade of step 6, acquire Upper Stage Waverider half Angle of Shock Waves, again with
It feeds the upper surface of fixed grade Waverider benchmark and bores semi-cone angle, obtain the benchmark cone length of Upper Stage Waverider；
Step 8: it is assumed that the rear end face of combination Waverider is overlapped with the rear end face of Upper Stage Waverider, combining oneself of Waverider
Origin stream interface rear line equation and Upper Stage Waverider freely come that stream interface rear line equation is identical, obtain Upper Stage Waverider
Freely carry out stream interface rear line；By Upper Stage Waverider freely come stream interface rear line equation carry out it is discrete, obtain Upper Stage rider
Body point cloud data, by Upper Stage Waverider point cloud data along free direction of flow upward grade Waverider shock wave cone project, obtain
Costa and Upper Stage Waverider to Upper Stage Waverider freely carry out stream interface；
Step 9: by the costa of Upper Stage Waverider, the pressure of Upper Stage Waverider is acquired by streamlined impeller principle
The compressing surface rear line in contracting face and Upper Stage Waverider, to obtain Upper Stage Waverider.
Preferably, the step 1 are as follows:
Given combination Waverider benchmark cone, the design Mach number and cone angle, combination rider of design combination Waverider benchmark cone
Half exhibition angle of body, finds out the Angle of Shock Waves of combination Waverider.
Preferably, the step 3 are as follows: according to half exhibition angle of combination Waverider, find out the coordinate of point K, it is assumed that combination rider
It is for X=R that body, which freely carrys out stream interface rear line equation form,0+A0·Y2, according to the control parameter R of the coordinate of point K and setting0It can ask
Obtain A0, to show that combination Waverider freely carrys out stream interface rear line equation.
Preferably, the step 6 are as follows: it is assumed that the rear line of Upper Stage Waverider is overlapped with Waverider rear line is combined, lead to
It crosses geometrical relationship and obtains the shock wave cone of Upper Stage Waverider, to obtain the benchmark cone of Upper Stage Waverider.
Preferably, the step 6 further include: it is assumed that half exhibition of Upper Stage Waverider design Mach number, Upper Stage Waverider
Angle, Upper Stage Waverider benchmark bore semi-cone angle.
Preferably, the length of the Upper Stage Waverider is less than the length of combination Waverider.
Preferably, the stream interface that freely comes of the combination Waverider and the Upper Stage Waverider is designed to be parallel to from origin
Flow the form in direction.
The present invention also provides a kind of re-entry space vehicle, the shape of the re-entry space vehicle passes through design method described above
It is made.
The invention has the benefit that
1. the present invention provides a kind of re-entry space vehicle design method of two-graded fusion based on Waverider.It can be to avoid existing
High heat in technology in two sub- grade gaps improves the aeroperformance of re-entry space vehicle, reduces launch cost.
2. waverider configuration can break through " lift resistance ratio " barrier, it is suitble to hypersonic flight.The present invention is set using two-graded fusion
Meter, two sub- grades (Upper Stage and lower stage) meet rider characteristic when being not only fused together, and can still meet respectively after separating
Rider performance.It therefore, not only can be to avoid the high heat between in the prior art one sub- grade and two sub- grades in gap, moreover it is possible to greatly
The aeroperformance of re-entry space vehicle is improved, launch cost is reduced.Further, since the design Mach number of two sub grade Waveriders is different,
And the design Mach number (combining the design Mach number of Waverider) of lower stage is lower than the design Mach number of Upper Stage Waverider,
Also make can only just have the Waverider of high lift-drag ratio characteristic that can fly in broader velocity interval near design point originally.
3. the invention proposes by the Waverider Combined design of two kinds of design points, provided for two-stage re-entry space vehicle of entering the orbit
A kind of new Exterior Surface Design.Making it before separation has rider characteristic, possesses high lift-drag ratio aeroperformance.And it is separating
Afterwards, the second level (Upper Stage Waverider) can still reach fabulous rider performance under higher flying speed.
4. since a sub grade Waverider of the prior art and two sub grade Waveriders are consolidated two sub- grades using individually designed
It is scheduled on back or the abdomen of a sub- grade, so that two sub- grades are combined, since the shock wave of two sub- grades can generate interference,
Aperture temp is with height between leading to two sub- grades.The present invention is using a sub- grade (lower stage) and two sub- grade (Upper Stage) fusions one
Design is played, designs Upper Stage rider by first designing the configuration of a combination Waverider, then on the basis of combining Waverider
The configuration of body.And two sub- grade meet rider characteristic when being not only fused together, can still meet rider performance respectively after separating.
Due to using a sub- grade (lower stage) and two sub- grade (Upper Stage) Combined designs, it not only can be to avoid in the prior art two
High heat between height grade in gap, moreover it is possible to greatly improve the aeroperformance of re-entry space vehicle, reduce launch cost.
Detailed description of the invention
Fig. 1 is a kind of re-entry space vehicle design method schematic illustration of two-graded fusion provided in an embodiment of the present invention；
Fig. 2 is schematic cross-sectional view of the Fig. 1 on the section XEZ；
Fig. 3 is schematic cross-sectional view of the Fig. 1 on the section XEY；
Fig. 4 is cross-sectional view of the Fig. 1 on the section XEZ；
Combination Waverider is three-dimensional in a kind of Fig. 5 re-entry space vehicle design method of two-graded fusion provided in an embodiment of the present invention
Structural schematic diagram；
Fig. 6 is that combination Waverider is another in a kind of re-entry space vehicle design method of two-graded fusion provided in an embodiment of the present invention
A kind of view stereo structural schematic diagram；
Fig. 7 is that Upper Stage Waverider is vertical in a kind of re-entry space vehicle design method for two-graded fusion that inventive embodiments provide
Body structural schematic diagram；(Fig. 7 is the half of Upper Stage Waverider, by the edge Fig. 7)
Fig. 8 is that lower stage Waverider is vertical in a kind of re-entry space vehicle design method for two-graded fusion that inventive embodiments provide
Body structural schematic diagram.
Appended drawing reference:
1: Upper Stage Waverider；2: lower stage Waverider
MBG: Upper Stage Waverider freely carrys out stream interface；AKB: that combines Waverider freely carrys out stream interface；AMGK: lower stage
Waverider freely carrys out stream interface；
ACK: the compressing surface of Waverider is combined；MGH: the compressing surface of Upper Stage Waverider；
BMH: Upper Stage Waverider rear end face: BAC: the rear end face of Waverider is combined；
BHG: the plane of symmetry of Upper Stage Waverider: BCK: the plane of symmetry of Waverider is combined；
KB: combination Waverider freely carrys out the rear line of stream interface；KC: the rear line of combination Waverider compressing surface；MB: Upper Stage
Waverider freely carrys out the rear line of stream interface；MH: the rear line of Upper Stage Waverider compressing surface；
DET: combination Waverider benchmark cone；DEF: combination Waverider shock wave cone；
NES: Upper Stage Waverider shock wave cone: NEP: Upper Stage Waverider benchmark cone；
AK: the costa of Waverider is combined；MG: the costa of Upper Stage Waverider；
ABCK: combination Waverider；BGHM: Upper Stage Waverider；
Specific embodiment
With reference to the accompanying drawings of the specification and embodiment further description of the technical solution of the present invention.
It should be noted that embodiment provided by the invention is part preferred embodiment, the embodiment of the present invention is unlimited
For system to protection scope of the present invention, protection scope of the present invention is subject to claims provided by the invention.
Waverider is made of three faces and three lines, is respectively: compressing surface (upper surface), freely come stream interface (lower surface),
Perpendicular to the rear end face of free direction of flow, costa, compressing surface rear line, freely carry out stream interface rear line.
The embodiment of the present invention is illustrated with the two-graded fusion for leading Waverider based on cone.By the first sub grade Waverider at
For lower stage Waverider, the second sub- grade is known as Upper Stage Waverider, is that shape is known as combining Waverider by two-graded fusion.
The two-graded fusion design method is not only applicable to lead the waverider configuration that Waverider design principle obtains using cone, also
Suitable for the configuration obtained based on other Waverider design methods.The present invention does not limit the benchmark cone-shaped for combining Waverider and its
Cross sectional shape as rear end facial plane.
It should be noted that semi-cone angle is the half of cone angle in the present embodiment, half opens up the half that angle is exhibition angle, half shock wave
Angle is the half of Angle of Shock Waves.
In the art, since aircraft is symmetric form.Therefore the design of aircraft, usually only design wherein one
Half, the other half is by symmetrically can be obtained, to obtain complete aircraft.
The embodiment of the present invention provides a kind of re-entry space vehicle design method of two-graded fusion, includes the following steps:
Step 1: designing has compressing surface, freely carrys out stream interface and combines Waverider perpendicular to the rear end face of direction of flow
Parameter: given combination Waverider benchmark bores DET, and the design Mach number and cone angle δ of design combination Waverider benchmark cone can be in the hope of
Obtain Angle of Shock Waves β；
It is assumed that: combine the design Mach number Ma=6 of Waverider, the semi-cone angle δ of combination Waverider benchmark cone DET1=13 °,
It combines Waverider half and opens up angle φ1=60 °, combine Waverider half Angle of Shock Waves β1≈17.146°；
Step 2: as shown in Fig. 2, choosing rear end face institute of the section EF of combination Waverider benchmark cone as combination Waverider
In plane, it is overlapped its section EF with the rear end face for combining Waverider, the length L bored according to geometrical relationship benchmark0=1/
The radius R=L of shock wave section circle at tan (δ) and the section0·tan(β)；
The present embodiment chooses combination Waverider benchmark and bores radius of circle R1Position of the section as cut-off plane EF at=1,
The length L of combination Waverider benchmark cone is obtained by geometrical relationship1=4.3314；Combination Waverider shock wave cone DEF at this time exists
Projection radius of circle on cut-off plane EF is r1.Regulation combination Waverider freely carrys out stream interface rear line midpoint B distance combination rider
The distance R of body benchmark axis of cone line DE0It can determine position of the combination Waverider in taper flow field；
Step 3: according to half exhibition angle φ of combination Waverider1, the coordinate of point K can be found out, the present embodiment acquires the coordinate of K point
For k (0.668,1.1573)；It is assumed that it is for X=R that combination Waverider, which freely carrys out stream interface rear line equation form,0+A0·Y2, according to
The coordinate of point K and the control parameter R of setting0A can be acquired0, to show that combination Waverider freely carrys out stream interface rear line equation；
This embodiment assumes that R0It is 0.5, so as to find out A0≈ 0.126, to obtain the freedom of the present embodiment combination Waverider
Carrying out stream interface rear line equation is X=0.5+0.126Y2, to obtain the rear line KB that combination Waverider freely carrys out stream interface；
The present embodiment combination Waverider freely carrys out stream interface rear line equation and is not limited to quadratic equation, can also be biquadratic equation
Or other forms.The present embodiment does not limit the scope of the invention.
Step 4: by combine Waverider freely come stream interface rear line equation carry out it is discrete, obtain combination Waverider point cloud number
According to the present embodiment obtains the coordinate of 101 points by taking 101 points as an example；Waverider point cloud data will be combined along combination Waverider
Free direction of flow to combination Waverider shock wave bore projection, obtain combination Waverider costa AK and combination Waverider from
Origin stream interface AKB；(stream interface that freely comes of combination Waverider is designed to be parallel to the form of free direction of flow)
Step 5: by the costa of combination Waverider, being solved to obtain the pressure of combination Waverider according to streamlined impeller method
Contracting face ACK and combine Waverider compressing surface rear line KC, then with combination Waverider rear end face place plane by figure into
Row closing, so that obtaining half group closes Waverider ABCK.The other half of combination Waverider is symmetrical along the face BCK with ABCK, can be obtained
Complete combination Waverider.The assembly rider body length that the present embodiment obtains is l1=2.71；
Step 6: the design parameter of given Upper Stage Waverider:
It is assumed that the rear line that Upper Stage Waverider freely carrys out stream interface freely carrys out the coincidence of stream interface rear line with Waverider is combined, i.e.,
Upper Stage Waverider freely slips the rear line of plum and the R for combining the free flow rear line of Waverider0It is identical, i.e. Upper Stage rider
Body freely carrys out distance R of the stream interface rear line midpoint apart from the Upper Stage Waverider benchmark axis of cone0With combine Waverider from origin
The distance R of the stream interface rear line midpoint distance combination Waverider benchmark axis of cone0' identical, it is all BE.It is available by geometrical relationship
The shock wave of Upper Stage Waverider bores NES.The benchmark of the available Upper Stage Waverider of NES is bored by the shock wave of Upper Stage Waverider
Bore NEP.
It is assumed that half exhibition angle φ of Upper Stage Waverider design Mach number Ma=15, Upper Stage Waverider2=40 °, Upper Stage
Waverider benchmark bores semi-cone angle δ2=11.13 °, the length of Upper Stage Waverider is less than the length of combination Waverider, the present embodiment
0.3 times of combination rider body length is taken as using Upper Stage rider body length；
Step 7: half Angle of Shock Waves β of Upper Stage Waverider can be acquired by Talor-macoll equation212.777 ° of ≈, this
When can be calculated Upper Stage Waverider benchmark cone length L2=3.018；
Step 8: it is assumed that the rear end face of combination Waverider is overlapped with the rear end face of Upper Stage Waverider, i.e. Upper Stage Waverider
Freely come stream interface rear line equation with combine Waverider freely to carry out stream interface rear line equation identical.Its factorial wave body above is certainly
Origin stream interface rear line equation is X=0.5+0.126Y2.Available Upper Stage Waverider freely carrys out the rear line of stream interface
MB.By Upper Stage Waverider freely come stream interface rear line equation carry out it is discrete, obtain Upper Stage Waverider point cloud data, this reality
Example is applied by taking 101 points as an example, obtains the coordinate of 101 points；Upper Stage Waverider point cloud data is upward along free direction of flow
The shock wave of face grade Waverider bores projection, and the costa MG and Upper Stage Waverider for obtaining Upper Stage Waverider freely carry out stream interface；
(it should be noted that the number of the present embodiment point cloud data can be several, such as 100-200 are ok.) Upper Stage
The stream interface that freely comes of Waverider is designed to be parallel to the form of free direction of flow.
Step 9: by the costa MG of Upper Stage Waverider, Upper Stage Waverider being acquired by streamlined impeller principle
The rear line of compressing surface and Upper Stage Waverider compressing surface, then where the rear end face of Upper Stage Waverider plane by figure into
Row closing, obtains half of Upper Stage Waverider BGHM, and the other half of Upper Stage Waverider is symmetrical along the face BHG with BGHM, can be obtained
Complete Upper Stage Waverider.It is l that the present embodiment, which the upper surface of obtains grade rider body length,2=0.813.
It should be noted that as seen in figs. 5-6, combination stage Waverider includes Upper Stage Waverider 1 and lower stage Waverider
2。
Another embodiment of the present invention provides a kind of re-entry space vehicle, the shape of the aircraft is obtained by above-mentioned design method.
Claims (8)
1. a kind of re-entry space vehicle design method of two-graded fusion, which comprises the steps of:
Step 1: designing has compressing surface, freely carrys out stream interface and the ginseng for combining Waverider of the rear end face perpendicular to direction of flow
Number:
Step 2: choosing the section (EF) of combination Waverider benchmark cone as plane where the rear end face of combination Waverider, make section
(EF) it is overlapped with the rear end face for combining Waverider, is combined at length and section of Waverider benchmark cone according to geometrical relationship
The radius of shock wave section circle；
Step 3: according to the parameter for the combination Waverider that step 1 is arranged, obtain combination Waverider freely comes stream interface rear line side
Journey obtains the rear line for freely carrying out stream interface of combination Waverider；
Step 4: by combine Waverider freely come stream interface rear line carry out it is discrete, obtain combination Waverider freely carry out stream interface rear
The point cloud data of line, the free direction of flow by point cloud data along combination Waverider are bored projection to the shock wave of combination Waverider, are obtained
Freely carry out stream interface to the costa and combination Waverider for combining Waverider；
Step 5: by the costa of combination Waverider, downstream being tracked according to streamlined impeller method, solution obtains a group rideshare
The compressing surface of wave body and the rear line of combination Waverider compressing surface, obtain combination Waverider；
Step 6: the design parameter of given Upper Stage Waverider:
Step 7: by the design parameter of the upper surface of the given grade of step 6, acquiring half Angle of Shock Waves and benchmark cone of Upper Stage Waverider
Semi-cone angle bores length by the benchmark that geometrical relationship acquires Upper Stage Waverider；
Step 8: it is assumed that the rear end face of combination Waverider is overlapped with the rear end face of Upper Stage Waverider, combine Waverider from origin
Stream interface rear line equation and Upper Stage Waverider freely to carry out stream interface rear line equation identical, give Upper Stage Waverider half and open up
Angle, obtain Upper Stage Waverider freely carrys out stream interface rear line；By Upper Stage Waverider freely come stream interface rear line carry out from
It dissipates, obtains Upper Stage Waverider point cloud data, by Upper Stage Waverider point cloud data along free direction of flow upward grade rider
The shock wave of body bores projection, and the costa and Upper Stage Waverider for obtaining Upper Stage Waverider freely carry out stream interface；
Step 9: by the costa of Upper Stage Waverider, the compressing surface of Upper Stage Waverider is acquired by streamlined impeller principle
With the compressing surface rear line of Upper Stage Waverider, to obtain Upper Stage Waverider.
2. design method according to claim 1, which is characterized in that the step 1 are as follows:
Given combination Waverider benchmark cone, the design Mach number and cone angle of design combination Waverider benchmark cone, finds out combination rider
The Angle of Shock Waves of body.
3. design method according to claim 1, which is characterized in that the step 3 are as follows: according to given combination Waverider
Half exhibition angle, find out the coordinate of point K, it is assumed that combination Waverider freely come stream interface rear line equation form be X=R0+A0·Y2, root
The coordinate of strong point K and the control parameter R of setting0A can be acquired0, to show that combination Waverider freely comes stream interface rear line side
Journey.
4. design method according to claim 1, which is characterized in that the step 6 are as follows: it is assumed that after Upper Stage Waverider
Edge line is overlapped with Waverider rear line is combined, and is bored by the shock wave that geometrical relationship obtains Upper Stage Waverider, to obtain above
The benchmark cone of grade Waverider.
5. design method according to claim 4, which is characterized in that the step 6 further include: it is assumed that Upper Stage Waverider
Design Mach number, half exhibition angle of Upper Stage Waverider, Upper Stage Waverider benchmark cone semi-cone angle.
6. design method according to claim 4, which is characterized in that the length of the Upper Stage Waverider is less than group rideshare
The length of wave body.
7. design method according to claim 1, which is characterized in that the combination Waverider and the Upper Stage Waverider
The stream interface that freely comes be designed to be parallel to the form of free direction of flow.
8. a kind of re-entry space vehicle, by claim 1-7, any one design method obtains the shape of the re-entry space vehicle.
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| CN110816871A (en) * | 2019-11-12 | 2020-02-21 | 湖南云顶智能科技有限公司 | Novel two-stage waverider design method based on cone-guided method |
| CN113153529A (en) * | 2021-04-21 | 2021-07-23 | 厦门大学 | Wide-speed-range air inlet channel design method based on double-incidence bending shock wave |
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