CN116720266B - Dynamics modeling method of recyclable aerospace carrier - Google Patents
Dynamics modeling method of recyclable aerospace carrier Download PDFInfo
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- 238000004364 calculation method Methods 0.000 claims abstract description 17
- 238000004064 recycling Methods 0.000 claims abstract description 13
- 238000005265 energy consumption Methods 0.000 claims abstract description 12
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- 230000005484 gravity Effects 0.000 description 5
- FFBHFFJDDLITSX-UHFFFAOYSA-N benzyl N-[2-hydroxy-4-(3-oxomorpholin-4-yl)phenyl]carbamate Chemical compound OC1=C(NC(=O)OCC2=CC=CC=C2)C=CC(=C1)N1CCOCC1=O FFBHFFJDDLITSX-UHFFFAOYSA-N 0.000 description 4
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- 229920006351 engineering plastic Polymers 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
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- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
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- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses a dynamic modeling method of a recyclable aerospace carrier, which relates to the field of aerospace carriers, and comprises the following steps: determining basic parameters of a launching process and a recycling process of the recyclable aerospace carrier, determining basic parameters of a single flywheel fan engine, respectively calculating effective launching energy provided by the single flywheel fan engine according to a related formula, calculating effective energy demand in the launching process, circularly calculating the actual number of the flywheel fan engines according to judgment conditions, determining a symmetrical array arrangement mode and a rotation direction layout of the flywheel fan engines, calculating energy consumption of a parachute in the landing and recycling process, and optimizing the volume and the mass of the parachute. The invention provides a recoverable aerospace vehicle dynamics modeling method, which is characterized in that a series of dynamics quantitative analysis calculation mathematical models are established, theoretical basis is provided for optimizing multivariable parameters, and the safety and stability of a launching process and a recovery process are ensured.
Description
Technical Field
The invention relates to the technical field of aerospace vehicles, in particular to a dynamic modeling method of a recyclable aerospace vehicle.
Background
The flywheel battery has the advantages of high energy density, high mechanical energy conversion efficiency, long cycle service life and the like, and is widely applied to the fields of energy storage, transportation and aerospace. Along with the development of science and technology, the application of the recyclable aerospace vehicle in the aerospace field has good development prospect, but the problem of the dynamic modeling method of the recyclable aerospace vehicle is to be solved because of the large number of dynamic parameter variables.
Disclosure of Invention
The invention aims to provide a dynamic modeling method of a recyclable aerospace carrier, which quantitatively reveals the law of energy conversion in the launching process and the recycling process of the recyclable aerospace carrier by establishing a series of dynamic quantitative analysis calculation mathematical models, provides theoretical basis for optimizing multivariable parameters, and ensures the safety and stability of the launching process and the recycling process.
In order to achieve the above object, the present invention provides the following solutions:
a method of modeling dynamics of a recyclable aerospace vehicle, wherein the recyclable aerospace vehicle comprises a chassis and two or more even number of flywheel fan engines; the chassis is provided with a control system and a parachute; each flywheel fan engine includes a fan, a flywheel, and a pod, the method comprising:
first, basic parameters of a recoverable aerospace vehicle launching process and a recovery process are determined: emission height H 1 TransmittingFinal rate v 1 Recovery landing Rate v 2 And rocket mass m r ；
Second, determining basic parameters of a single flywheel fan engine: flywheel rotational speed n at the beginning of emission 0 Flywheel speed n at the end of the launch process 1 Flywheel rotational speed n during landing recovery 2 Flywheel fan engine mass m 1 Moment of inertia J of flywheel 0 ；
Third, calculate the effective emission energy E provided by a single flywheel fan engine 1 ；
Fourth, presetting the number N of flywheel fan engines 0 ，N 0 Is an even number greater than or equal to 2, and is N according to the preset number of flywheel fan engines 0 Calculating the total mass m of a recyclable aerospace vehicle a ：
Fifth, calculate the effective energy demand E of the recoverable aerospace vehicle launch process 2 ：
Step six, calculating the number N of required flywheel fan engines:
seventh, judging and calculating the number N of flywheel fan engines and the number N of preset flywheel fan engines 0 Whether or not to equal: n=n 0 ？
If n=n 0 Performing an eleventh step; conversely, N+.N 0 Then, performing an eighth step;
eighth step, judge whether N>N 0 The method comprises the steps of carrying out a first treatment on the surface of the If N>N 0 A ninth step is carried out; conversely, if not N>N 0 A tenth step is carried out;
ninth step, reset N 0 : let N 0 =N 0 Returning to the fourth step after +2;
tenth step, reset N 0 : let N 0 =N 0 -2, returning to the fourth step;
eleventh step, obtaining the actual number N of flywheel fan engines;
twelfth, determining symmetrical array arrangement modes and rotation direction layout of N flywheel fan engines;
thirteenth step, calculate the recoverable typeEnergy consumption E of parachute in aerospace carrier landing recovery process 3 And according to E 3 Is used for optimizing the volume and quality parameters of the parachute.
Optionally, the calculation formula of the effective emission energy provided by the single flywheel fan engine is as follows:
；
wherein ,E1 Efficient emission energy provided for a single flywheel fan engine; pi is the circumference ratio; j (J) 0 The flywheel rotational inertia;the effective energy average conversion rate of the flywheel fan engine; n is n 0 The flywheel rotation speed is the rotation speed at the beginning of emission; n is n 1 For flywheel speed at the end of the launch process.
Optionally, the calculation formula of the effective energy demand of the emission process of the recyclable aerospace vehicle is as follows:
；
wherein ,E2 An effective energy demand for a recyclable aerospace vehicle launch process; m is m r Is rocket mass; m is m a Is the total mass of the recyclable aerospace carrier; g is gravity acceleration; h 1 Is the emission height; v 1 A final firing rate for the recyclable aerospace vehicle; c (C) D1 The wind resistance coefficient is the wind resistance coefficient of the recyclable aerospace carrier in the launching stage; a is the windward area of the recyclable aerospace vehicle; t is t 1 Time elapsed from the start of transmission to the end of the transmission process; ρ is the air density; v t Is the velocity of the recyclable aerospace vehicle at the moment of the launch phase t.
Optionally, the calculation formula of the number N of the required flywheel fan engines is as follows:
；
wherein N is the number of flywheel fan engines required; ceil () is an upward integer function; e (E) 1 Efficient emission energy provided for a single flywheel fan engine; e (E) 2 An effective launch energy demand for a recyclable aerospace vehicle launch process.
Optionally, in the twelfth step, the symmetrical array arrangement mode of the N flywheel fan engines is an annular array symmetrical arrangement mode or a rectangular array symmetrical arrangement mode; the rotational layout of the N flywheel fan engines is as follows: wherein half of the flywheel fan engines rotate in a clockwise direction and the other half of the flywheel fan engines rotate in a counter-clockwise direction.
Optionally, the calculation formula of the energy consumption of the parachute in the landing and recycling process of the recyclable aerospace carrier is as follows:
；
wherein ,E3 The energy consumption of the parachute in the landing and recycling process of the recyclable aerospace carrier is realized; m is m a Is the total mass of the recyclable aerospace carrier; g is gravity acceleration; h 1 Is the emission height; v 1 For the end of transmission rate; v 2 To recover landing rate; j (J) 0 The flywheel rotational inertia; pi is the circumference ratio;the effective energy average conversion rate of the flywheel fan engine; n is n 1 Flywheel rotational speed at the end of the launch process; n is n 2 The flywheel rotating speed is recovered when landing; c (C) D2 The wind resistance coefficient is the wind resistance coefficient in the landing recovery process of the recyclable aerospace carrier; a is the windward area of the recyclable aerospace vehicle; [ t ] 10 ，t 2 ]The time interval is the resistance action time generated by opening the parachute, t 10 To the opening time of the parachute in the process of recovering the parachute, t 2 Time elapsed from the start of the launch to the recovery landing; ρ is the air density; v t Is the velocity of the recyclable aerospace vehicle at the moment of the fall recovery phase t.
Optionally, the total mass m of the recyclable aerospace vehicle a The calculation formula of (2) is as follows:
；
wherein ,ma Is the total mass of the recyclable aerospace carrier; n (N) 0 The number of flywheel fan engines is preset; m is m 1 Mass for a single flywheel fan engine; m is m 2 Is the total mass of the chassis.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects: the invention provides a dynamic modeling method of a recyclable aerospace carrier, which comprises the following steps: determining basic parameters of a launching process and a recycling process of the recyclable aerospace carrier, determining basic parameters of a single flywheel fan engine, respectively calculating effective launching energy provided by the single flywheel fan engine according to a related formula, calculating effective energy demand in the launching process, circularly calculating the actual number of the flywheel fan engines according to judgment conditions, determining a symmetrical array arrangement mode and a rotation direction layout of the flywheel fan engines, calculating energy consumption of a parachute in the landing recycling process, optimizing the volume and the mass of the parachute and the like. The invention provides a recoverable aerospace carrier dynamics modeling method, and establishes a series of dynamics quantitative analysis calculation mathematical models, so that theoretical basis is provided for optimization of multivariable parameters, and safety and stability of a launching process and a recovery process are ensured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow diagram of a method for modeling dynamics of a recyclable aerospace vehicle provided by an embodiment of the present invention;
FIG. 2 is a top plan view of a structural layout of a recyclable aerospace vehicle provided in an embodiment of the present invention;
FIG. 3 is a cross-sectional view of a recyclable aerospace vehicle provided in an embodiment of the present invention, taken along the A-A direction of FIG. 2;
fig. 4 is a timing chart of the emission process and the recovery landing process and a variation curve of the relevant parameters according to the embodiment of the present invention.
Symbol description:
1-a flywheel fan engine; 2-chassis; 3-a control system; 4-rocket; 5-a transmitting station; 6-a fan; 7-flywheel; 8, a diversion cover; 9-vectoring nozzle; 10-load bracket; 11-parachute chambers; 12-parachute; 13-a gas generator; 14-a control unit; 15-a flywheel rotation speed sensor; 16-a speed sensor; 17-a horizontal attitude sensor; 18-rocket electromagnetic gripper; 19-an igniter; 20-vector nozzle actuator; 21-a storage battery; 22-an electric motor; 23-a speed increasing box; 24-the carrier emits an electromagnetic gripper.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a dynamic modeling method of a recyclable aerospace vehicle.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
As shown in fig. 1, the invention provides a method for modeling dynamics of a recyclable aerospace vehicle, wherein the recyclable aerospace vehicle implementing the method comprises a chassis 2 and two or more even number of flywheel fan engines 1; the chassis is provided with a control system 3 and two parachutes 12; each flywheel fan engine 1 comprises a fan 6, a flywheel 7 and a nacelle 8; the method comprises the following steps:
s1: determining basic parameters of a recoverable aerospace vehicle launching process and a recovery process: emission height H 1 End of transmission rate v 1 Recovery landing Rate v 2 Rocket mass m r 。
S2: determining basic parameters of a single flywheel fan engine: flywheel rotational speed n at the beginning of emission 0 Flywheel speed n at the end of the launch process 1 Flywheel rotational speed n during landing recovery 2 Flywheel fan engine mass m 1 Moment of inertia J of flywheel 0 。
S3: calculating the effective emission energy E provided by a single flywheel fan engine 1 。
S4: presetting the number N of flywheel fan engines 0 ，N 0 Is an even number greater than or equal to 2, and is N according to the preset number of flywheel fan engines 0 Calculating the total mass m of a recyclable aerospace vehicle a 。
S5: calculating an effective energy demand E for a recoverable aerospace vehicle launch process 2 。
S6: and calculating the number N of required flywheel fan engines.
S7: judging, calculating and obtaining the number N of flywheel fan engines and the number N of preset flywheel fan engines 0 Whether or not to equal: n=n 0 ？
If n=n 0 S11, performing a step; conversely, N+.N 0 S8 is performed.
S8: judging whether N is>N 0 ? If N>N 0 S9, performing; conversely, if not N>N 0 I.e. N < N 0 S10 is performed.
S9: reset N 0 : let N 0 =N 0 After +2, return to S4.
S10: reset N 0 : let N 0 =N 0 After-2, return to S4.
S11: and obtaining the actual number N of flywheel fan engines.
S12: and determining the symmetrical array arrangement mode and the rotation direction layout of the N flywheel fan engines.
S13: calculating energy consumption E of parachute in landing recovery process of recoverable aerospace carrier 3 And according to E 3 Is optimized for the volume and mass of the parachute.
Calculating the effective emitted energy provided by a single flywheel fan engine according to the formula:
。
wherein ,E1 Efficient emission energy provided for a single flywheel fan engine; pi is the circumference ratio; j (J) 0 The flywheel rotational inertia;the effective energy average conversion rate of the flywheel fan engine; n is n 0 The flywheel rotation speed is the rotation speed at the beginning of emission; n is n 1 For flywheel speed at the end of the launch process.
The number N of flywheel fan engines is preset before calculating the effective energy demand for the launch process of the recyclable aerospace vehicle 0 ，N 0 Is an even number greater than or equal to 2. The total mass of the recyclable aerospace vehicle is then calculated. Recoverable aerospace vehicle total mass m a The calculation formula of (2) is as follows:
。
wherein ,ma Is the total mass of the recyclable aerospace carrier; n (N) 0 The number of flywheel fan engines is preset; m is m 1 Mass for a single flywheel fan engine; m is m 2 Is the total mass of the chassis.
After calculating the total mass of the recyclable aerospace vehicle, in S5, the effective energy demand of the recyclable aerospace vehicle in the launching process is calculated as follows:
。
wherein ,E2 An effective energy demand for a recyclable aerospace vehicle launch process; m is m r Is rocket mass; m is m a Is the total mass of the recyclable aerospace carrier; g is gravity acceleration; h 1 Is the emission height; v 1 A final firing rate for the recyclable aerospace vehicle; c (C) D1 The wind resistance coefficient is the wind resistance coefficient of the recyclable aerospace carrier in the launching stage; a is the windward area of the recyclable aerospace vehicle; t is t 1 Time elapsed from the start of transmission to the end of the transmission process; ρ is the air density; v t Is the velocity of the recyclable aerospace vehicle at the moment of the launch phase t.
In this embodiment, the calculation formula of the number N of flywheel fan engines required in S6 is as follows:
。
where ceil () is an upward integer function.
After the actual number N of the flywheel fan engines is obtained in S11, the symmetrical array arrangement and the rotation direction layout of the flywheel fan engines need to be further determined. In S12, the symmetrical array arrangement of the N flywheel fan engines may be a circular array symmetrical arrangement or a rectangular array symmetrical arrangement. The spin-direction layout is as follows: half of the flywheel fan motors rotate in a clockwise direction and the other half of the flywheel fan motors rotate in a counter-clockwise direction as shown in fig. 2.
In S13, calculating the energy consumption E of the parachute in the landing and recycling process of the recyclable aerospace carrier 3 The calculation formula of (1) is as followsThe following steps:
。
wherein ,E3 The energy consumption of the parachute in the landing and recycling process of the recyclable aerospace carrier is realized; m is m a Is the total mass of the recyclable aerospace carrier; g is gravity acceleration; h 1 Is the emission height; v 1 For the end of transmission rate; v 2 To recover landing rate; j (J) 0 The flywheel rotational inertia; pi is the circumference ratio;the effective energy average conversion rate of the flywheel fan engine; n is n 1 Flywheel rotational speed at the end of the launch process; n is n 2 The flywheel rotating speed is recovered when landing; c (C) D2 The wind resistance coefficient is the wind resistance coefficient in the landing recovery process of the recyclable aerospace carrier; a is the windward area of the recyclable aerospace vehicle; [ t ] 10 ，t 2 ]The time interval is the resistance action time generated by opening the parachute, t 10 To the opening time of the parachute in the process of recovering the parachute, t 2 Time elapsed from the start of the launch to the recovery landing; ρ is the air density; v t Is the velocity of the recyclable aerospace vehicle at the moment of the fall recovery phase t.
As shown in fig. 2 and 3, a recyclable aerospace vehicle embodying the present invention includes a chassis 2 and two or more even number of flywheel fan engines 1. Each flywheel fan engine 1 comprises a fan 6 and a flywheel 7 and a nacelle 8. In this embodiment, the actual number N of flywheel fan engines is eight obtained by the above method.
The eight flywheel fan engines 1 are symmetrically arranged in a rectangular array at the center of the horizontal plane of the chassis 2; the four flywheel fan engines 1 rotate clockwise, and the other four flywheel fan engines 1 rotate anticlockwise, so that the torque generated by the eight flywheel fan engines 1 in the working process is mutually offset, and the stability of the running posture of the eight flywheel fan engines is ensured.
The flywheel 7 of each flywheel fan engine 1 drives the fan 6 to rotate at a high speed, the generated high-speed airflow is downwards ejected through the air guide sleeve 8 and the vector jet pipe 9, and the generated reaction thrust is used as acceleration thrust in the launching process and deceleration resistance in the landing and recovery process of the recyclable aerospace carrier. The center of the chassis 2 is also provided with a load bracket 10, the periphery of the load bracket 10 is provided with two parachute chambers 11, and a parachute 12 is preset in each parachute chamber 11; a gas generator 13 is arranged below each parachute 12.
In order to meet the operation control requirement, a control system 3 is further arranged on the chassis 2, and the control system 3 comprises a control unit 14, a flywheel rotation speed sensor 15, a speed sensor 16, a horizontal posture sensor 17, a rocket electromagnetic clamp 18, an igniter 19, a vector nozzle actuator 20 and a storage battery 21. The storage battery 21 is a power supply of the control system 3, each flywheel rotation speed sensor 15 inputs a flywheel 7 detection signal of each flywheel fan engine 1 to the electronic control unit 14, and the speed sensor 16 and the horizontal posture sensor 17 respectively input detection signals to the electronic control unit 14; the electronic control unit 14 outputs control execution instructions to the rocket electromagnetic clamp 18, the two igniters 19 and each vector nozzle actuator 20 according to the control of the memory program.
The working process of the recyclable aerospace vehicle is further described below by taking the application situation of the first-stage carrier for rocket launching in the embodiment as an example, and the working process of the recyclable aerospace vehicle is divided into a launching preparation stage, a launching stage and a landing recovery stage.
First stage of preparation for emission
Before launching a carrier rocket of the recyclable aerospace carrier, hoisting the recyclable aerospace carrier onto a launching platform 5, enabling an energy input shaft at the lower end of a flywheel 7 of each flywheel fan engine 1 to be in butt joint with an output shaft of a speed increasing box 23, and electrifying and locking a carrier launching electromagnetic clamp 24; then hoisting the rocket 4 to the load support 10, and electrifying and locking the rocket electromagnetic clamp 18; the motor 22 is electrified to accelerate and rotate, the motor 22 drives the flywheel 7 of the flywheel fan engine 1 to rotate at a high speed through the speed increasing box 23 to obtain energy, the flywheel rotation speed sensor 15 detects the rotation speed of the flywheel 7, and each flywheel 7 is ready to be drivenReaching the same predetermined value n 0 The effective emission energy E provided by the single flywheel fan engine can be obtained 1 The transmit preparation phase ends.
According to E 1 The calculation formula can be given by: e (E) 1 Average conversion rate of effective energy with flywheel fan engineIn proportion to the flywheel speed n at the beginning of the emission 0 Flywheel speed n at the end of the launch process 1 The square of the difference between the two is proportional. Thus, the effective emitted energy E provided by a single flywheel fan engine can be increased by the following optimization approach 1 ：
a. Optimizing the structure of the fan 6 and the air guide sleeve 8 to improve the effective energy average conversion rate of the flywheel fan engine。
b. The flywheel 7 is supported by a magnetic bearing, and a vacuum state is kept between the flywheel 7 and a shell thereof so as to improve the effective energy average conversion rate of the flywheel fan engine。
c. Increasing flywheel speed n at start of launch 0 In this embodiment, the flywheel speed n at the start of the emission 0 =15000 to 50000rpm. On the one hand, the effective energy E provided by a single flywheel fan engine can be effectively improved 1 On the other hand, the flywheel rotation speed n at the start of emission is prevented by the restriction of the strength of the manufacturing material 0 Too high brings about a significant increase in manufacturing costs.
And (II) a transmitting stage:
after receiving the launching instruction, the electromagnetic gripper 24 for launching the carrier is powered off and released, and under the combined pushing of the reaction force generated by the high-speed high-pressure air flow ejected from the vector jet pipe 9 by the eight flywheel fan engines 1, the recyclable aerospace carrier and the rocket leave the launching platform 5 to accelerate and take off, and the acceleration a at the beginning of the launching stage 0 For acceleration a t Maximum value of (1)The level sensor 16 detects the rate and acceleration values of the ascent process when the emission height H is reached 1 End of transmission rate v 1 After the target value is set, the rocket electromagnetic clamp 18 is powered off and released, the rocket 4 is ignited, the recyclable aerospace carrier is separated from the rocket 4, and the launching stage is completed.
In the launch phase, the control unit 14 receives the detection signal of the horizontal attitude sensor 17, so as to control the actuation of the vectoring nozzle actuator 20 and adjust the angle of the vectoring nozzle 9, so that the recyclable aerospace vehicle maintains the required flight attitude.
According to E 2 The effective energy demand of the emission process can be reduced by the following optimization approach:
a. preferably, engineering plastics, aluminum alloy, carbon fiber and other materials are used as main structural component materials to reduce the mass m of the flywheel fan engine 1 1 And by optimizing the structure of the flywheel 7 to reduce the total mass m of the recyclable aerospace vehicle a 。
b. Reducing the windage coefficient C of a recoverable aerospace vehicle launch process by optimizing the structure D1 。
c. The windward area A of the recyclable aerospace vehicle is reduced.
(III) drop recovery stage
After the rocket 4 is ignited and separated, the recyclable aerospace carrier keeps inertial rising, and begins to descend after the inertial rising reaches the maximum height, [ t ] 1 ，t 10 ]The time interval is the time window for the parachute to be opened, at t 10 At the moment, the control unit 14 controls the two igniters 19 to simultaneously ignite, so that the solid fuel in the gas generator 13 generates a large amount of N under high temperature and high pressure 2 Ejecting two parachutes 12 from the parachute chambers 11, and opening the two parachutes 12; under the combined action of the two parachutes 12 and the high-speed air flow resistance sprayed from the vectoring nozzle 9 of the eight flywheel fan engines 1, the gravity is overcome, so that the recyclable aerospace carrier slowly descends until the low-speed landing and the landing recovery stage is finished.
In the landing recovery phase, the control unit 14 receives the detection signal of the horizontal attitude sensor 17, so as to control the actuation of the vectoring nozzle actuator 20 and adjust the angle of the vectoring nozzle 9, so that the recoverable aerospace vehicle maintains the required flight attitude.
According to E 3 The energy consumption of the parachute during the recovery of the parachute can be reduced by the following optimized route to reduce the volume and weight of the parachute 12:
a. to maintain sufficient drop resistance of the flywheel fan engine 1, the flywheel speed value n is at the end of the firing process 1 Is not too low, so that the flywheel speed n at the end of the emission in this embodiment 1 =5000 to 8000rpm, flywheel rotation speed n during recovery landing 2 =1000~2000rpm。
b. Optimizing the ignition time t of the igniter 19 10 The time interval t for which the parachute 12 is opened to generate a resistance effect can be optimized 10 ，t 2 ]。
c. Increasing the windage coefficient C of the recoverable aerospace vehicle during the fall recovery process D2 Which is advantageous in reducing the landing rate.
A timing diagram of the recoverable aerospace vehicle launch process and recovery landing process and a plot of the change in the relevant parameters is shown in figure 4.
In addition, the operation of the recyclable aerospace vehicle as an aerospace vehicle is similar to that described above, except that the load is changed from rocket 4 to an aerospace load, and the detailed operation thereof is not described herein.
According to the invention, by establishing the effective emission energy model required by the emission stage and the energy consumption model of the parachute in the landing recovery stage, the emission process and the energy conversion rule of the recovery process of the recoverable aerospace carrier can be quantitatively revealed, so that theoretical basis is provided for further optimizing various variable parameters (dynamic parameters and geometric structure parameters), the power performance of the recoverable aerospace carrier can be improved, and the stability of the emission process and the recovery process of the recoverable aerospace carrier can be ensured.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (3)
1. A method of modeling dynamics of a recyclable aerospace vehicle, wherein the recyclable aerospace vehicle comprises a chassis and two or more even number of flywheel fan engines; the chassis is provided with a control system and a parachute; each of the flywheel fan engines comprises a fan, a flywheel and a pod, wherein the method comprises:
first, determining basic parameters of the launching process and the recovery process of the recyclable aerospace vehicle: height of emissionH 1 Rate of end of transmissionv 1 Recovery landing ratev 2 And rocket massm r ；
Second, determining basic parameters of a single flywheel fan engine: flywheel rotational speed at start of launchn 0 Flywheel rotational speed at end of launchn 1 Flywheel rotational speed during landing recoveryn 2 Flywheel fan engine massm 1 Moment of inertia of flywheelJ 0 ；
Third, calculating the effective emission energy provided by a single flywheel fan engineE 1 The method comprises the steps of carrying out a first treatment on the surface of the The calculation formula of the effective emission energy provided by the single flywheel fan engine is as follows:
；
wherein ,E 1 efficient emission energy provided for a single flywheel fan engine; pi is the circumference ratio;J 0 the flywheel rotational inertia;the effective energy average conversion rate of the flywheel fan engine;n 0 the flywheel rotation speed is the rotation speed at the beginning of emission;n 1 flywheel rotational speed at the end of the launch process;
fourth, presetting the number of flywheel fan enginesN 0 ，N 0 Is an even number greater than or equal to 2, and according to the preset number of flywheel fan enginesN 0 Calculating the total mass of the recyclable aerospace vehiclem a ：
Fifth, calculate the effective energy demand of the recyclable aerospace vehicle launch processE 2 : the calculation formula of the effective energy demand of the emission process of the recyclable aerospace vehicle is as follows:
；
wherein ,E 2 an effective energy demand for a recyclable aerospace vehicle launch process;m r is rocket mass;m a is the total mass of the recyclable aerospace carrier;ggravitational acceleration;H 1 is the emission height;v 1 a final firing rate for the recyclable aerospace vehicle;C D1 the wind resistance coefficient is the wind resistance coefficient of the recyclable aerospace carrier in the launching stage;Ais the windward area of the recyclable aerospace carrier;t 1 time elapsed from the start of transmission to the end of the transmission process;ρis air density;v t in launch phase for a recyclable aerospace vehicletThe rate of time of day;
step six, calculating the number of required flywheel fan enginesN: the number of the required flywheel fan enginesNThe calculation formula of (2) is as follows:
；
wherein ,Nthe number of the fan engines is the number of flywheel fans required; ceil () is an upward integer function;E 1 efficient emission energy provided for a single flywheel fan engine;E 2 an effective launch energy demand for a recyclable aerospace vehicle launch process;
seventh step, judging and calculating the number of flywheel fan enginesNAnd presetting the number of flywheel fan enginesN 0 Whether or not to equal:if it isN=N 0 Performing an eleventh step; on the contrary, i.eN≠N 0 Then, performing an eighth step;
eighth step, judge whether or notN>N 0 The method comprises the steps of carrying out a first treatment on the surface of the If it isN>N 0 A ninth step is carried out; on the contrary, if notN>N 0 A tenth step is carried out;
ninth step, resetN 0 : order theN 0 =N 0 Returning to the fourth step after +2;
tenth step, resetN 0 : order theN 0 =N 0 -2, returning to the fourth step;
eleventh step, obtaining the actual number of flywheel fan enginesN；
Twelfth step, confirmNSymmetrical array arrangement and rotation direction layout of the flywheel fan engines;
thirteenth step, calculating the energy consumption of the parachute in the landing and recycling process of the recyclable aerospace carrierE 3 And according toE 3 The volume and quality parameters of the parachute are optimized according to the numerical value of (1);
the calculation formula of the energy consumption of the parachute in the landing and recycling process of the recyclable aerospace carrier is as follows:
；
wherein ,E 3 the energy consumption of the parachute in the landing and recycling process of the recyclable aerospace carrier is realized;m a is the total mass of the recyclable aerospace carrier;ggravitational acceleration;H 1 is the emission height;v 1 for the end of transmission rate;v 2 to recover landing rate;J 0 the flywheel rotational inertia; pi is the circumference ratio;the effective energy average conversion rate of the flywheel fan engine;n 1 flywheel rotational speed at the end of the launch process;n 2 the flywheel rotating speed is recovered when landing;C D2 the wind resistance coefficient is the wind resistance coefficient in the landing recovery process of the recyclable aerospace carrier;Ais the windward area of the recyclable aerospace carrier; [t 10 ，t 2 ]The time interval is the resistance action time generated by opening the parachute,t 10 in order to open the parachute in the process of recovering the parachute,t 2 time elapsed from the start of the launch to the recovery landing;ρis air density;v t in the landing recovery phase for a recoverable aerospace vehicletThe rate of time of day.
2. The method of modeling dynamics of a recyclable aerospace vehicle according to claim 1, characterized in that in the twelfth step, theNThe symmetrical array arrangement mode of the flywheel fan engines is an annular array symmetrical arrangement mode or a rectangular array symmetrical arrangement mode; the saidNThe rotational layout of the flywheel fan engines is as follows: wherein half of the flywheel fan engines rotate in a clockwise direction and the other half of the flywheel fan engines rotate in a counter-clockwise direction.
3. The method of modeling dynamics of a recyclable aerospace vehicle of claim 1, wherein the recyclable aerospace vehicleTotal mass of carrierm a The calculation formula of (2) is as follows:
；
wherein ,m a is the total mass of the recyclable aerospace carrier;N 0 the number of flywheel fan engines is preset;m 1 mass for a single flywheel fan engine;m 2 is the total mass of the chassis.
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| EP2879954A2 (en) * | 2012-08-01 | 2015-06-10 | Bye UAS Inc. | Unmanned aerial systems |
| CN110589033A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Deformable recovery aircraft and recovery method |
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| US20130327014A1 (en) * | 2012-06-12 | 2013-12-12 | Djamal Moulebhar | Devices and Methods to Optimize Aircraft Power Plant and Aircraft Operations |
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| CN110589033A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Deformable recovery aircraft and recovery method |
| CN112213087A (en) * | 2020-09-07 | 2021-01-12 | 蓝箭航天空间科技股份有限公司 | Method for testing falling of spacecraft connector |
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