CN108298110A - A kind of two-stage is entered the orbit re-entry space vehicle ascending path and design method - Google Patents
A kind of two-stage is entered the orbit re-entry space vehicle ascending path and design method Download PDFInfo
- Publication number
- CN108298110A CN108298110A CN201711399526.1A CN201711399526A CN108298110A CN 108298110 A CN108298110 A CN 108298110A CN 201711399526 A CN201711399526 A CN 201711399526A CN 108298110 A CN108298110 A CN 108298110A
- Authority
- CN
- China
- Prior art keywords
- level
- section
- ascending path
- point
- orbit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Traffic Control Systems (AREA)
Abstract
The present invention proposes that a kind of enter the orbit re-entry space vehicle ascending path and design method of two-stage determines ascending path form by being divided to a two level ascent stage, it is first determined breakout locations, then second order trajectory design is carried out, finally carry out level-one Trajectory Design.Inventive algorithm is succinct, it is efficient to solve, and can be widely used for re-entry space vehicle, the design of near space Hypersonic Aircraft ascending path.
Description
Technical field
Enter the orbit re-entry space vehicle ascending path and design method the present invention relates to a kind of two-stage, belongs to re-entry space vehicle and enter
Rail Trajectory Design technical field.
Background technology
Re-entry space vehicle be one kind using air suction type combined engine as power, can be in dense atmosphere, near space, space
The novel world of shuttle flight device is round transported aircraft, and can be divided into two-stage according to series of entering the orbit enters the orbit re-entry space vehicle and single-stage
Enter the orbit re-entry space vehicle, and two-stage re-entry space vehicle technical difficulty of entering the orbit is relatively low, and a sub- grade is dynamic using air suction type combination
Power, two sub- grades will be formed faster using rocket-powered two-stage re-entry space vehicle (referred to as two-stage enter the orbit re-entry space vehicle) of entering the orbit
Practical ability.
Ascent stage includes that vehicle rises and flies to load and enter the orbit whole tracks.Existing carrier rocket uses the side of taking off vertically
Formula, rocket-powered high thrust accelerate, and the track form that gets through the earth's atmosphere quickly is simple, and the ascent stage is flown using fixed mission program
Row is designed by mission program when ascending path designs and is realized.By over half a century experience accumulation carrier rocket flight journey
Sequence has formed fixed form, optimizes the flight journey that can be met the requirements to mission program parameter according to mission requirements
Sequence completes ascending path design.
Different from carrier rocket, two-stage re-entry space vehicle is promoted using horizontal take-off mode, assembly power, ascent stage rail
Mark can be sub-divided into a level segment and two level segments.The sub grade assembly power of one level segment one be operated in dense atmosphere, close to space vehicle with
Position, Velocity Azimuth requirement when obtaining speed increment and a second-order separation.Two level segments, the two sub- rocket-powered work of grade, it is lasting to accelerate
Into target track, this section of track form is no different with carrier rocket.
Due to track form difference, two level carrier rocket ascending path design method is not applied for the flight of two-stage sky day
Device ascending path designs.And two-stage re-entry space vehicle ascending path design method research of entering the orbit at present is concentrated mainly on vertical put down
In face in terms of nominal Optimal design of trajectory method, design objective is mostly that fuel is optimal, the time is most short etc., it is not intended that airport and mesh
Orbit space relative position relation is marked, ascending path design cannot be satisfied space constraint requirement.
Invention content
It is an object of the invention to overcome the shortage of prior art, provides a kind of two-stage of space constraint requirement and enter the orbit empty day
Aircraft ascending path and design method meet airport position (launch point) and target track (injection point) relative position about
Beam.
Technical solution of the invention：A kind of two-stage is entered the orbit re-entry space vehicle ascending path, and two-stage empty day of entering the orbit flies
It is rocket-powered that row device level-one uses air suction type assembly power, two level to use, and two-stage enters the orbit re-entry space vehicle ascending path by one
Grade ascending path and two level ascending path composition, the level-one ascending path are from takeoff point is divided into burble point
Fly section, accelerates I section, course adjustment section, accelerate II section, cruising flight section, penetrate face adjustment section and accelerate III section, in the level-one
It is constraint in the track drift angle initial value of burble point, separation moment and breakout locations that section track, which is risen, by two level ascending path；
The section of taking off, accelerate I section, accelerate II section and accelerate III section without rolling and sideslip, speed, height, inclination angle and
Voyage determines by vertical plane nominal trajectory, and the course adjustment section and directive adjustment section have rolling without sideslip, constant speed, etc. soar
Row, the cruising flight section is without rolling and sideslip, constant speed, constant-level flight.
The vertical plane nominal trajectory is known in the art technology, can tie up the optimization algorithms such as law popularization by Gauss and determine.
The burble point determines that criterion is：Burble point is the mesh in the motor-driven coverage of level-one air suction type assembly power
Mark track substar.
The burble point determines that steps are as follows：
(1) sub-satellite track is formed with target track element in desired emission period；
(2) it is that radius makees maneuvering range circle using field takeoff point as dot, level-one maneuverability, is in level-one maneuvering range
Substar in circle can be used as optional breakout locations；
(3) according to other requirements to aerial mission to burble point, such as level-one flying distance it is minimum, enter the orbit and want constantly
It asks, burble point specific location is determined from step (2).
The two level ascending path be divided into from burble point to injection point a power flight phase, unpowered coasting-flight phase and
Secondary power inflight phase is defeated with the scheduled discrete state initial value of level-one (speed, height and track inclination angle) and breakout locations
Enter to carry out second order trajectory design, be designed specifically to using rocket-powered flight path design known technology.
The scheduled discrete state initial value of level-one is related to level-one air suction type assembly power, is from level-one air suction type assembly power
In attainable discrete state (speed, height and track inclination angle) optionally.
A kind of two-stage is entered the orbit re-entry space vehicle ascending path design method, and two-stage enters the orbit re-entry space vehicle level-one using inhaling
Using rocket-powered, the two-stage enters the orbit re-entry space vehicle ascending path by the level-one ascent stage for gas formula assembly power, two level
Track and two level ascending path composition, specific design are realized by following steps：
The first step determines level-one, the second-order separation point,
The burble point determines that criterion is：Burble point is the mesh in the motor-driven coverage of level-one air suction type assembly power
Mark track substar；
Second step determines that two level ascending path, the two level ascending path are divided into one from burble point to injection point
Secondary power flight phase, unpowered coasting-flight phase and secondary power inflight phase, with predetermined discrete state (speed, height and the rail of level-one
Mark inclination angle), breakout locations and target track parameter be that input carries out second order trajectory design, obtain two level ascending path point
Track drift angle initial value, separation moment from point；
This step is designed specifically to, using rocket-powered flight path design known technology, carry out using Newton iteration method
Optimization design.
Third walks, and trajectory calculation is carried out to the two level ascending path parameter that second step obtains, if entering the orbit in trajectory calculation
Precision meets mission requirements and then carries out the 4th step, and the first step is returned if being unsatisfactory for and is adjusted to burble point, repeat second,
Three steps, until orbit injection accuracy meets mission requirements；
4th step determines that level-one ascending path, the level-one ascending path are to be divided into from takeoff point to burble point
Section of taking off accelerates I section, course adjustment section, accelerates II section, cruising flight section, penetrates III section of face adjustment section and acceleration, and described takes off
Section accelerates I section, accelerates II section and accelerate III section without rolling and sideslip, and the course adjustment section and directive adjustment section have rolling
Without sideslip, constant speed, constant-level flight, the cruising flight section is without rolling and sideslip, constant speed, constant-level flight；
It is as follows：
A4.1, the vertical plane nominal trajectory for designing level-one ascending path；
Vertical plane nominal trajectory is known in the art technology, and specific design refers to Tang Guojin, Luo Yazhong, harmony grace rice writes《Boat
Its device track optimizing theory, method and application》The Beijing [M]：Science Press, 2011.
A4.2, it is designed according to the determining two level ascending path of third step, obtains two level at the beginning of the track drift angle of burble point
Value and separation moment, i.e. level-one obtain in the separated track drift angle of burble point and separation moment according to the determining burble point of third step
To the longitude and latitude of burble point；
A4.3, take off parameter, including takeoff point longitude and latitude and level-one initial track drift angle ψ are determinedf0, level-one initial track is inclined
Angle ψf0For airfield runway azimuth, takeoff point longitude and latitude is airfield runway longitude and latitude, is given value；
A4.4, section of taking off is determined according to the vertical plane nominal trajectory that step A4.1 is obtained, accelerates I section, accelerates II section and adds
Speed, height, inclination angle and the voyage of III section of speed；
This step is known technology, specifically refers to Tang Guojin, Luo Yazhong, harmony grace rice writes《Space trajectory optimum theory, side
Method and application》The Beijing [M]：Science Press, 2011.
Parameter of taking off (takeoff point longitude and latitude and the level-one that A4.5, the parameter obtained according to step A4.4, step A4.3 are determined
Initial track drift angle ψf0), step A4.2 separation parameters (the separation moment, burble point longitude and latitude and level-one burble point separation rail
Mark drift angle) and the constraint of level-one trace end, determine that course adjustment section terminates track drift angle ψ using Newton iteration methodft1, cruise section
Time Δ tsxTerminate track drift angle ψ with directive adjustment sectionft2With departure time tf0,
Level-one trace end constrains：
Wherein tff、ψff、λff、φffSeparation moment, separated track drift angle, burble point longitude and latitude in being calculated for level-one track is practical
Degree, ψffobjIt is level-one in the separated track drift angle of burble point, numerically equal to two level ascending path is inclined in the track of burble point
Angle initial value ψs0, tffobjLevel-one detaches moment t at the separation moment of burble point, numerically equal to two level ascending paths0, λffobj、
φffobjFor the longitude and latitude of burble point；
5th step carries out trajectory calculation, if trajectory calculation knot to the level-one ascending path parameter that the 4th step designs
Separation accuracy meets mission requirements and then terminates to design in fruit, if not satisfied, then returning to the first successive step burble point, is carrying out second
To five steps, until separation accuracy meets mission requirements.
Third walks and the trajectory calculation of the 5th step is known in the art technology, does not just repeat one by one herein.
The advantageous effect of the present invention compared with prior art：
(1) Trajectory Design of the present invention meets airport position and target track relative position constraint；
(2) present invention can effectively solve the problem that in three dimensions that two-stage is entered the orbit re-entry space vehicle ascending path design problem,
It can be widely used for re-entry space vehicle, the design of near space Hypersonic Aircraft ascending path；
(3) present invention with a second-order separation must substantially in target track plane, level-one maneuverability is limited is
Criterion gives burble point choosing method, then is solved by the way that Trajectory Design problem is converted to trajectory parameters, is with terminal condition
The solution of trajectory parameters is completed in constraint using Newton iteration method, and algorithm is succinct, it is efficient to solve.
Description of the drawings
Fig. 1 is form schematic diagram in track of the present invention；
Fig. 2 is design flow diagram of the present invention；
Fig. 3 is that level-one ascending path of the present invention parameterizes schematic diagram.
Specific implementation mode
Below in conjunction with attached drawing and specific example, the present invention will be described in detail.
The present invention provides two-stage as shown in Figure 1 and enters the orbit re-entry space vehicle ascending path, and two-stage is entered the orbit re-entry space vehicle
It is rocket-powered that level-one uses air suction type assembly power, two level to use, and two-stage enters the orbit re-entry space vehicle ascending path by level-one
Section track and two level ascending path composition are risen, the level-one ascending path is to be divided into taking off from takeoff point to burble point
Section accelerates I section, course adjustment section, accelerates II section, cruising flight section, penetrates face adjustment section and accelerate III section, two level ascending path
It is divided into a power flight phase, unpowered coasting-flight phase and secondary power inflight phase from burble point to injection point, it is scheduled with level-one
Discrete state initial value (speed, height and track inclination angle) and breakout locations are that input carries out second order trajectory design.
Level-one ascending path is by two level ascending path in the track drift angle initial value of burble point, separation moment and burble point
Position is constraint；III section of section of taking off, I section of acceleration, II section of acceleration and acceleration are without rolling and sideslip, speed, height, inclination angle and voyage
It is determined by vertical plane nominal trajectory, course adjustment section and directive adjustment section have rolling without sideslip, and constant speed, constant-level flight are cruised and flown
Row section is without rolling and sideslip, constant speed, constant-level flight.
Enter the orbit re-entry space vehicle ascending path design method the present invention also provides two-stage as shown in Figure 2, according to target
Orbit parameter, airport position, level-one maneuverability will determine breakout locations, then with level-one predetermined discrete state (speed, height
And track inclination angle) and breakout locations be that input carries out second order trajectory design, track drift angle in last second order trajectory design result
Initial value, discrete state and breakout locations are that constraint requirements carry out level-one Trajectory Design.
It is as follows：
1, burble point choosing method
Level-one has flexible maneuverability using air suction type assembly power, and different separation is reached by maneuvering flight
Point, since I and II track form determines, disengaged position determines the trend of rising trace, therefore rising trace design first
Step will choose breakout locations.For burble point, first, do not have crossrange maneuvering ability substantially using rocket-powered two level, point
From must be substantially in target track plane, second is that level-one maneuverability is limited, burble point must be motor-driven reachable in level-one
In range, the optional range that can determine burble point based on above 2 points.
Specific method is as follows：Sub-satellite track is formed with target track element in desired emission period, then with airport
It is that radius makees maneuvering range circle for dot, level-one maneuverability, the substar in the motor-driven range circle of level-one can be used as can
The breakout locations of choosing.The specific location of burble point can (such as level-one flying distance be minimum, enter the orbit requires constantly according to specific requirement
Deng) determine.
2, I and II method for planning track
(1) two level is in-flight without rolling and sideslip, and trajectory is substantially coplanar interior, the pass of pitch angle and trajectory tilt angle, the angle of attack
System is：
Two level positive incidence progress serpentine climbs after separation, and angle of attack engine ignition after separation is stablized is increased rapidly to most
Big value, beginning track forces down after climbing to certain altitude, and the angle of attack is gradually decrease to zero.
The angle of attack of I inflight phase of second motive force is designed as：
α in formulasmFor I section of maximum angle of attack of second motive force flight, ts0(two-stage can be approximately considered for second motive force time of ignition
Detach the moment), tslFor track pull-up finish time, ts1fIt flies I section of finish time for second motive force.
Two level is unpowered, and coasting-flight phase pitch angle linear function indicates, second motive force flies II section as constant value pitch angle.To sum up,
The design of two level mission program is as follows
Second motive force flies I section：
Two level is unpowered coasting-flight phase：
Or
In formulaFor a dynamically working end point pitch angle,For unpowered coasting-flight phase Elevation angle changing rate, tssfFor
It is unpowered to slide finish time.
Second motive force flies II section：
In formulaPitch angle at the end of for unpowered slide, ts2fIt works finish time for secondary power.
tslIt can be taken as constant value or a certain value be decreased to by dynamic pressure to determine, ts1fIt can be determined by first time shutdown speed, two level
The design variable of mission program is selected as：αsm、tssf、ts2f, other also two level initial track drift angle ψs0With the separation moment
ts0, flight program angle design variable and ψs0、ts0Second order trajectory design variable is constituted, second order trajectory design is exactly Trajectory Design
Variable Optimization Solution process.
In order to ensure that second order trajectory calculation of design parameters can restrain within effective time, asked using Newton iteration method
Solution, two level ascent stage end conswtraint such as following formula.
A, e, ω, Ω, i, f respectively actually enter orbit parameter a in formulaobj、eobj、ωobj、Ωobj、iobj、fobjRespectively
Target enters orbit parameter.
(2) the two level ascending path obtained to (1) design carries out trajectory calculation, if orbit injection accuracy in trajectory calculation result
Meet mission requirements and then carry out level-one ascending path design, if not satisfied, 1 adjustment burble point is then returned to, from new design two level
Ascending path.
(3) the level-one ascent stage is complex three-dimensional track, and I, II, III section of section of taking off and acceleration are without rolling and sideslip, speed, height
Degree, inclination angle and voyage are determined that vertical plane nominal trajectory can tie up the optimization algorithms such as law popularization by Gauss and determine by vertical plane nominal trajectory；
Course adjustment section has rolling without sideslip, the certain constant speed of turning radius, constant-level flight with directive adjustment section；Cruise section is without rolling and side
It is sliding, constant speed, constant-level flight.
As shown in figure 3, level-one ascending path is by level-one initial track drift angle ψf0, course adjustment terminate track drift angle ψft1、
Cruise section time Δ tsx, directive adjustment section terminate track drift angle ψft2, departure time tf0It determines.Initial track drift angle ψf0For airport
Runway azimuth, therefore the design of level-one rising trace has also been transformed into trajectory parameters ψft1、Δtsx、ψft2、tf0It solves.
Level-one ascending path parameter is also solved using Newton iteration method, and one the second-order separation track of end conswtraint is inclined
Angle, longitude and latitude, end conswtraint are shown below.
ψ in formulaff、λff、φffFor the practical calculating parameter in level-one track, ψffobjIt is equal to ψs0, tffobjIt is equal to ts0,
λffobj、φffobjFor burble point longitude and latitude.
(4) trajectory calculation is carried out to the level-one ascending path that design obtains, if separation accuracy is full in trajectory calculation result
Sufficient mission requirements then terminate to design, if not satisfied, then returning to 1 adjustment burble point, redesign.
Unspecified part of the present invention is known to the skilled person technology.
Claims (7)
- The re-entry space vehicle ascending path 1. a kind of two-stage is entered the orbit, two-stage re-entry space vehicle level-one of entering the orbit are dynamic using air suction type combination Using rocket-powered, two-stage enters the orbit re-entry space vehicle ascending path by level-one ascending path and two level ascent stage for power, two level Track forms, it is characterised in that：The level-one ascending path be divided into from takeoff point to burble point section of taking off, accelerate I section, Course adjustment section accelerates II section, cruising flight section, penetrates III section of face adjustment section and acceleration, and the level-one ascending path is by two Grade ascending path is constraint in the track drift angle initial value of burble point, separation moment and breakout locations；III section of section of taking off, I section of acceleration, II section of acceleration and the acceleration is without rolling and sideslip, speed, height, inclination angle and voyage It being determined by vertical plane nominal trajectory, the course adjustment section and directive adjustment section have rolling without sideslip, constant speed, constant-level flight, The cruising flight section is without rolling and sideslip, constant speed, constant-level flight.
- The re-entry space vehicle ascending path 2. a kind of two-stage according to claim 1 is entered the orbit, it is characterised in that：Point Determine that criterion is from：Burble point is the target track substar in the motor-driven coverage of level-one air suction type assembly power.
- The re-entry space vehicle ascending path 3. a kind of two-stage according to claim 2 is entered the orbit, it is characterised in that：Point Determine that steps are as follows from：(1) sub-satellite track is formed with target track element in desired emission period；(2) it is that radius makees maneuvering range circle using field takeoff point as dot, level-one maneuverability, in the motor-driven range circle of level-one Substar can be used as optional breakout locations；(3) according to other requirements to aerial mission to burble point, burble point specific location is determined from step (2).
- The re-entry space vehicle ascending path 4. a kind of two-stage according to claim 1 is entered the orbit, it is characterised in that：Described two Grade ascending path is divided into a power flight phase, unpowered coasting-flight phase and secondary power inflight phase from burble point to injection point, It is that input carries out second order trajectory design with the scheduled discrete state initial value of level-one and breakout locations.
- The re-entry space vehicle ascending path design method 5. a kind of two-stage is entered the orbit, two-stage enter the orbit re-entry space vehicle level-one using air-breathing Using rocket-powered, the two-stage enters the orbit re-entry space vehicle ascending path by level-one ascent stage rail for formula assembly power, two level Mark and two level ascending path composition, which is characterized in that design is realized by following steps：The first step determines level-one, the second-order separation point,The burble point determines that criterion is：Burble point is the target track in the motor-driven coverage of level-one air suction type assembly power Road substar；Second step determines that two level ascending path, the two level ascending path are divided into primary dynamic from burble point to injection point Power inflight phase, unpowered coasting-flight phase and secondary power inflight phase, with predetermined discrete state, breakout locations and the target track of level-one Road parameter is that input carries out second order trajectory design, obtains two level ascending path in track drift angle initial value, the separation of burble point It carves；Third walks, and trajectory calculation is carried out to the two level ascending path parameter that second step obtains, if orbit injection accuracy in trajectory calculation Meet mission requirements and then carry out the 4th step, the first step is returned if being unsatisfactory for, burble point is adjusted, repeat second and third Step, until orbit injection accuracy meets mission requirements；4th step determines that level-one ascending path, the level-one ascending path are to be divided into taking off from takeoff point to burble point Section, accelerate I section, course adjustment section, accelerate II section, cruising flight section, penetrate face adjustment section and accelerate III section, the section of taking off, Accelerate I section, accelerate II section and accelerate III section without rolling and sideslip, the course adjustment section and directive adjustment section have rolling without side Sliding, constant speed, constant-level flight, the cruising flight section is without rolling and sideslip, constant speed, constant-level flight；5th step carries out trajectory calculation, if in trajectory calculation result to the level-one ascending path parameter that the 4th step designs Separation accuracy, which meets mission requirements, then to be terminated to design, if not satisfied, then returning to the first successive step burble point, is carrying out the second to five Step, until separation accuracy meets mission requirements.
- The re-entry space vehicle ascending path design method 6. a kind of two-stage according to claim 5 is entered the orbit, it is characterised in that： Steps are as follows for 4th step：A4.1, the vertical plane nominal trajectory for designing level-one ascending path；A4.2, determine separation parameter, according to third step, determining two level ascending path designs, obtain two level burble point rail Mark drift angle initial value and separation moment, i.e. level-one are in the separated track drift angle of burble point and detach the moment, determining according to third step Burble point obtains the longitude and latitude of burble point；A4.3, take off parameter, including takeoff point longitude and latitude and level-one initial track drift angle ψ are determinedf0, level-one initial track drift angle ψf0 For airfield runway azimuth, takeoff point longitude and latitude is airfield runway longitude and latitude, is given value；A4.4, section of taking off is determined according to the vertical plane nominal trajectory that step A4.1 is obtained, accelerates I section, accelerate II section and acceleration III Speed, height, inclination angle and the voyage of section；Parameter of taking off, step A4.2 separation parameters and the level-one that A4.5, the parameter obtained according to step A4.4, step A4.3 are determined Trace end constrains, and determines that course adjustment section terminates track drift angle ψ using Newton iteration methodft1, cruise section time Δ tsxAnd directive Adjustment section terminates track drift angle ψft2With departure time tf0,Level-one trace end constrains：Wherein tff、ψff、λff、φffSeparation moment, separated track drift angle, burble point longitude and latitude in being calculated for level-one track is practical, ψffobjIt is level-one in the separated track drift angle of burble point, numerically equal to two level ascending path is at the beginning of the track drift angle of burble point Value ψs0, tffobjLevel-one detaches moment t at the separation moment of burble point, numerically equal to two level ascending paths0, λffobj、 φffobjFor the longitude and latitude of burble point.
- The re-entry space vehicle ascending path design method 7. a kind of two-stage according to claim 5 is entered the orbit, it is characterised in that： Burble point determines that steps are as follows in the first step：(1) sub-satellite track is formed with target track element in desired emission period；(2) it is that radius makees maneuvering range circle using field takeoff point as dot, level-one maneuverability, in the motor-driven range circle of level-one Substar can be used as optional breakout locations；(3) according to other requirements to aerial mission to burble point, burble point specific location is determined from step (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711399526.1A CN108298110A (en) | 2017-12-22 | 2017-12-22 | A kind of two-stage is entered the orbit re-entry space vehicle ascending path and design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711399526.1A CN108298110A (en) | 2017-12-22 | 2017-12-22 | A kind of two-stage is entered the orbit re-entry space vehicle ascending path and design method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108298110A true CN108298110A (en) | 2018-07-20 |
Family
ID=62870897
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711399526.1A Pending CN108298110A (en) | 2017-12-22 | 2017-12-22 | A kind of two-stage is entered the orbit re-entry space vehicle ascending path and design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108298110A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112306075A (en) * | 2020-10-20 | 2021-02-02 | 中国运载火箭技术研究院 | High-precision off-orbit reverse iterative guidance method |
| CN113721646A (en) * | 2021-08-11 | 2021-11-30 | 中山大学 | Combined power aircraft trajectory rapid planning method considering secondary pull-up |
| CN115167126A (en) * | 2022-06-24 | 2022-10-11 | 西北工业大学 | Method for designing and optimizing longitudinal trajectory of ascending section of two-stage orbit-entering hypersonic aircraft |
| CN115421388A (en) * | 2022-09-23 | 2022-12-02 | 南京理工大学 | Convex optimization-based remote missile final-stage multi-attitude constraint online trajectory planning method |
| CN116049998A (en) * | 2023-03-30 | 2023-05-02 | 中国人民解放军96901部队 | Method and device for quickly determining separation point parameters of variable-level combined aircraft |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1237934A (en) * | 1996-09-16 | 1999-12-08 | 太空通道有限公司 | Low earth orbit payload launch system |
| CN106021628A (en) * | 2015-07-03 | 2016-10-12 | 中国运载火箭技术研究院 | Vertical returning trajectory design method for carrier rocket |
| CN107235159A (en) * | 2017-04-26 | 2017-10-10 | 西北工业大学 | A kind of three-level is entered the orbit space launch vehicle |
-
2017
- 2017-12-22 CN CN201711399526.1A patent/CN108298110A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1237934A (en) * | 1996-09-16 | 1999-12-08 | 太空通道有限公司 | Low earth orbit payload launch system |
| CN106021628A (en) * | 2015-07-03 | 2016-10-12 | 中国运载火箭技术研究院 | Vertical returning trajectory design method for carrier rocket |
| CN107235159A (en) * | 2017-04-26 | 2017-10-10 | 西北工业大学 | A kind of three-level is entered the orbit space launch vehicle |
Non-Patent Citations (1)
| Title |
|---|
| 王永圣等: "两级入轨火箭动力二级上升轨迹设计方法", 《战术导弹技术》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112306075A (en) * | 2020-10-20 | 2021-02-02 | 中国运载火箭技术研究院 | High-precision off-orbit reverse iterative guidance method |
| CN112306075B (en) * | 2020-10-20 | 2023-08-29 | 中国运载火箭技术研究院 | High-precision off-track reverse iteration guidance method |
| CN113721646A (en) * | 2021-08-11 | 2021-11-30 | 中山大学 | Combined power aircraft trajectory rapid planning method considering secondary pull-up |
| CN115167126A (en) * | 2022-06-24 | 2022-10-11 | 西北工业大学 | Method for designing and optimizing longitudinal trajectory of ascending section of two-stage orbit-entering hypersonic aircraft |
| CN115167126B (en) * | 2022-06-24 | 2024-04-30 | 西北工业大学 | Method for designing and optimizing longitudinal track of ascending section of two-stage orbital hypersonic aircraft |
| CN115421388A (en) * | 2022-09-23 | 2022-12-02 | 南京理工大学 | Convex optimization-based remote missile final-stage multi-attitude constraint online trajectory planning method |
| CN116049998A (en) * | 2023-03-30 | 2023-05-02 | 中国人民解放军96901部队 | Method and device for quickly determining separation point parameters of variable-level combined aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108298110A (en) | A kind of two-stage is entered the orbit re-entry space vehicle ascending path and design method | |
| CN106021628B (en) | A kind of carrier rocket vertically returns to ballistic design method | |
| CN110908396B (en) | Full-stage reentry return guidance method for reusable vehicle | |
| Langener et al. | Trajectory simulation and optimization of the LAPCAT MR2 hypersonic cruiser concept | |
| US8489258B2 (en) | Propulsive guidance for atmospheric skip entry trajectories | |
| CN110160407A (en) | A kind of carrier rocket grade is settled in an area scope control system | |
| CN107992074A (en) | A kind of reentry trajectory design method based on flight path angle planning | |
| CN106371312B (en) | Lift formula based on fuzzy controller reenters prediction-correction method of guidance | |
| JP5822676B2 (en) | Multistage rocket guidance device, multistage rocket guidance program, multistage rocket guidance method, and multistage rocket guidance system | |
| CN109080854B (en) | Orbit-changing planning method for large elliptical orbit of spacecraft returning to preset drop point | |
| CN110733670B (en) | Short-range low-overload reentry track design method | |
| Sippel et al. | System investigations of the SpaceLiner concept in fast20xx | |
| Wolf et al. | Toward improved landing precision on Mars | |
| CN113742840A (en) | Rapid ballistic iteration calculation method for test prototype of vertical take-off and landing reusable carrier | |
| Andersson et al. | Cooperating uavs using thermal lift to extend endurance | |
| Tsuchiya et al. | Optimal design of two-stage-to-orbit space planes with airbreathing engines | |
| Han et al. | Optimal ballistic coefficient control for Mars aerocapture | |
| Wolf et al. | Improving the landing precision of an MSL-class vehicle | |
| CN113176787B (en) | Power descent trajectory planning online triggering method based on drop point prediction | |
| Peng et al. | A novel emergency flight path planning strategy for civil airplanes in total loss of thrust | |
| Sostaric et al. | Trajectory guidance for Mars robotic precursors: aerocapture, entry, descent, and landing | |
| Nebylov et al. | Improving the safety of the spacecraft landing capsule by optimizing its search | |
| Baek et al. | Trajectory optimization and the control of a re-entry vehicle in TAEM phase | |
| Foust et al. | Dragonfly First Flight–Preliminary Flight Dynamics Analysis | |
| CN113486524B (en) | Separation window design method based on condition of meeting load release point multiple constraints |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180720 |