CN101786505B - Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof - Google Patents
Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof Download PDFInfo
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- CN101786505B CN101786505B CN2010101148578A CN201010114857A CN101786505B CN 101786505 B CN101786505 B CN 101786505B CN 2010101148578 A CN2010101148578 A CN 2010101148578A CN 201010114857 A CN201010114857 A CN 201010114857A CN 101786505 B CN101786505 B CN 101786505B
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Abstract
The invention provides a low-orbit aircraft based on aerodynamic attitude control and an attitude control method thereof, relating to the low-orbit aircraft and the attitude control method thereof and solving the problems of high fuel consumption of the current low-orbit aircraft and the attitude control method thereof and short on-orbit service life of the aircraft. The low-orbit aircraft comprises an aircraft body, a pair of pitching-direction attitude control aerodynamic auxiliary boards, a pair of yawing-direction attitude control aerodynamic auxiliary boards, a first rotating mechanical arm, a second rotating mechanical arm, a third rotating mechanical arm and a fourth rotating mechanical arm. The attitude control method of the low-orbit aircraft comprises the following steps of: acquiring the current attitude angle and the target attitude angle of the low-orbit aircraft, obtaining a member to be deflexed and an angle through combining with aircraft attitude dynamics model and a kinematics model, rotating the member, then calculating the deviation angle at the moment, and then finishing the control process when the deviation angle is in the allowed range. The invention is suitable for the attitude control field of the low-orbit aircraft in the height of 200-500 km.
Description
Technical field
The present invention relates to a kind of low-orbit aircraft and attitude control method thereof.
Background technology
Along with accidents such as earthquake, fire and terrorism to low-cost, high demand of heavily visiting frequency and high resolution observations, the Low Earth Orbit aircraft receives increasing concern.Low-orbit aircraft mainly receives the influence of aerodynamic force in orbit in the process, mainly shows as the influence to spacecraft orbit and attitude.Existing low-orbit aircraft and attitude control method thereof adopt active mostly; Like jet control, the control of zero momentum wheel, the control of bias momentum wheel, control-moment gyro control etc.; The Fuel Consumption of these control methods is big; Cause aircraft short in the rail life-span thus, the control system in these control methods is comparatively complicated simultaneously.
Summary of the invention
The Fuel Consumption that the objective of the invention is to solve at present existing low-orbit aircraft and attitude control method thereof greatly and the aircraft that causes thus in short problem of rail life-span, a kind of low-orbit aircraft and attitude control method thereof based on the control of aerodynamic force attitude is provided.
Low-orbit aircraft based on the control of aerodynamic force attitude; It comprises aircraft body, a pair of pitching to attitude control aerodynamic force accessory plate, a pair of driftage to attitude control aerodynamic force accessory plate, the first rotary machine arm, the second rotary machine arm, the 3rd rotary machine arm and the 4th rotary machine arm; Wherein, Said pitching is made up of the first aerodynamic force accessory plate and the second aerodynamic force accessory plate to attitude control aerodynamic force accessory plate, and driftage is made up of the 3rd aerodynamic force accessory plate and the 4th aerodynamic force accessory plate to attitude control aerodynamic force accessory plate;
One end of one end of one end of the said first rotary machine arm, the second rotary machine arm, the 3rd rotary machine arm and an end of the 4th rotary machine arm are connected the afterbody of aircraft body respectively; The other end of the other end of the other end of the other end of the first rotary machine arm, the second rotary machine arm, the 3rd rotary machine arm and the 4th rotary machine arm points to the last rear of aircraft body, following rear, left back and right back respectively; And the other end of the first rotary machine arm connects the first aerodynamic force accessory plate; And to make the first aerodynamic force accessory plate can be the rotation after central shaft is driven with the central axis of the first rotary machine arm; The other end of the second rotary machine arm connects the second aerodynamic force accessory plate; And to make the second aerodynamic force accessory plate can be the rotation after central shaft is driven with the central axis of the second rotary machine arm; The other end of the 3rd rotary machine arm connects the 3rd aerodynamic force accessory plate; And to make the 3rd aerodynamic force accessory plate can be the rotation after central shaft is driven with the central axis of the 3rd rotary machine arm; The other end of the 4th rotary machine arm connects the 4th aerodynamic force accessory plate, and to make the 4th aerodynamic force accessory plate can be the rotation after central shaft is driven with the central axis of the 4th rotary machine arm;
Said aircraft body is the rotational symmetry cylinder, and the said first rotary machine arm, the second rotary machine arm, the 3rd rotary machine arm and the 4th rotary machine arm are symmetrical set about the central axis of aircraft body.
The attitude control method of above-mentioned low-orbit aircraft based on aerodynamic force attitude control, its process is:
Step 2, according to the deviation angle of current attitude angle and object attitude angle and utilize attitude of flight vehicle dynamics and the kinematics model that has the aerodynamic force accessory plate; Calculating and obtaining pitching needs the parts of deflection and the angle that said parts need deflection to attitude control aerodynamic force accessory plate and driftage in attitude control aerodynamic force accessory plate, then according to the parts deflection corresponding angle of result of calculation with needs deflection;
Step 3, obtain the current attitude angle of low-orbit aircraft, and calculate the deviation angle of current attitude angle and object attitude angle, judge that this deviation angle is whether in the error range that allows: if then execution in step four; Otherwise, return execution in step two;
Good effect of the present invention: the present invention adopts big aerodynamic force to realize the attitude control of low-orbit aircraft; Utilize low-orbit aircraft of the present invention and attitude control method thereof; Can effectively improve the propellant amount of carrying when reducing low-orbit aircraft and entering the orbit, and under the situation that does not increase propellant expenditure, improve the life-span of low-orbit aircraft in the rail service.
Description of drawings
Fig. 1 is the front view of the low-orbit aircraft of embodiment of the present invention two; Fig. 2 is the side view of the low-orbit aircraft of embodiment of the present invention two; Fig. 3 is the vertical view of the low-orbit aircraft of embodiment of the present invention two; Fig. 4 is the stereographic map of the low-orbit aircraft of embodiment of the present invention two; Fig. 5 is the side view of the low-orbit aircraft of embodiment of the present invention three; Fig. 6 is the vertical view of the low-orbit aircraft of embodiment of the present invention three; Fig. 7 is the process flow diagram of the attitude control method of embodiment of the present invention four.
Embodiment
Embodiment one: the low-orbit aircraft based on the control of aerodynamic force attitude of this embodiment; It comprises aircraft body 1, pitching to attitude control aerodynamic force accessory plate, driftage to attitude control aerodynamic force accessory plate, the first rotary machine arm 5, the second rotary machine arm 6, the 3rd rotary machine arm 7 and the 4th rotary machine arm 8; Wherein, Said pitching is made up of the first aerodynamic force accessory plate 21 and the second aerodynamic force accessory plate 22 to attitude control aerodynamic force accessory plate, and driftage is made up of the 3rd aerodynamic force accessory plate 31 and the 4th aerodynamic force accessory plate 32 to attitude control aerodynamic force accessory plate;
One end of one end of one end of the said first rotary machine arm 5, the second rotary machine arm 6, the 3rd rotary machine arm 7 and an end of the 4th rotary machine arm 8 are connected the afterbody of aircraft body 1 respectively; The other end of the other end of the other end of the other end of the first rotary machine arm 5, the second rotary machine arm 6, the 3rd rotary machine arm 7 and the 4th rotary machine arm 8 points to the last rear of aircraft body 1, following rear, left back and right back respectively; And the other end of the first rotary machine arm 5 connects the first aerodynamic force accessory plate 21; And to make the first aerodynamic force accessory plate 21 can be the rotation after central shaft is driven with the central axis of the first rotary machine arm 5; The other end of the second rotary machine arm 6 connects the second aerodynamic force accessory plate 22; And to make the second aerodynamic force accessory plate 22 can be the rotation after central shaft is driven with the central axis of the second rotary machine arm 6; The other end of the 3rd rotary machine arm 7 connects the 3rd aerodynamic force accessory plate 31; And to make the 3rd aerodynamic force accessory plate 31 can be the rotation after central shaft is driven with the central axis of the 3rd rotary machine arm 7; The other end of the 4th rotary machine arm 8 connects the 4th aerodynamic force accessory plate 32, and to make the 4th aerodynamic force accessory plate 32 can be the rotation after central shaft is driven with the central axis of the 4th rotary machine arm 8;
Said aircraft body 1 is the rotational symmetry cylinder, and the said first rotary machine arm 5, the second rotary machine arm 6, the 3rd rotary machine arm 7 and the 4th rotary machine arm 8 are symmetrical set about the central axis of aircraft body 1.
The xsect of said aircraft body 1 is center symmetry polygon or circle.
Embodiment two: different with embodiment one is; This embodiment also comprises two wedge shape ailerons 4; And the xsect of said wedge shape aileron (4) is a wedge shape; One of them wedge shape aileron 4 is positioned at the left side of aircraft body 1 and is connected with aircraft body 1 left-hand face, and another wedge shape aileron 4 is positioned at the right side of aircraft body 1 and is connected with the right lateral surface of aircraft body 1.
Each wedge shape aileron 4 is the seal of being made up of five blocks of plates; Wherein, Said five blocks of plates comprise rectangular slab and two set squares that three block specifications are identical; Said three rectangular slabs join end to end successively and form the triangle cylinder of a hollow, and said two set squares place the upper bottom surface place and the bottom surface place of this triangle cylinder respectively, and the junction of these five blocks of plates is and is tightly connected.
In this embodiment; Pitching adopts rotatable machine arm with aircraft body 1 to be connected with driftage to attitude control aerodynamic force accessory plate to attitude control aerodynamic force accessory plate; When pitching is controlled the aerodynamic force accessory plate and gone off course after attitude is controlled each aerodynamic force accessory plate biasing special angle in the aerodynamic force accessory plate to attitude; Can make the barycenter of low-orbit aircraft change, and then produce required aerodynamic moment with pressing distance in the heart.
Pitching is responsible for pitching to attitude control aerodynamic force accessory plate and is controlled to attitude; Driftage is responsible for driftage to attitude control aerodynamic force accessory plate and is controlled to attitude; Pitching is controlled the aerodynamic force accessory plate and is gone off course when attitude control aerodynamic force accessory plate is used to attitude; Can realize that lift-over controls to attitude; Promptly rotate pitching to attitude control aerodynamic force accessory plate and driftage each aerodynamic force accessory plate in attitude control aerodynamic force accessory plate; Make the distributional class behind the first aerodynamic force accessory plate 21, the second aerodynamic force accessory plate 22, the 3rd aerodynamic force accessory plate 31 and the 4th aerodynamic force accessory plate 32 each autorotation special angle be similar to the blade on the windmill, two wedge shape ailerons 4 just can make upper and lower surfaces that bigger motor-driven angle is arranged when making wobble shaft rotate smaller angle; When need not attitude control, pitching is forwarded to along airflow direction to attitude control aerodynamic force accessory plate and driftage each aerodynamic force accessory plate in attitude control aerodynamic force accessory plate, disturb with the aerodynamic drag that reduces aircraft.This embodiment can be realized the attitude control of pitching, lift-over and three passages of driftage simultaneously.
Referring to Fig. 4, X is to the heading that is low-orbit aircraft, and the X axle is the wobble shaft of low-orbit aircraft, and the Y axle is the pitch axis of low-orbit aircraft, and the Z axle is the yaw axis of low-orbit aircraft, and wherein X-Y plane is parallel to the ground.The low-orbit aircraft of this embodiment is in the rail flight course, and heading is an optimal cases with minimum front face area.
This embodiment adopts the aerodynamic force accessory plate to add the configuration design of wedge shape aileron, through control accessory plate and wedge shape aileron, can realize the attitude maneuver and stable control of low-orbit aircraft pitching, lift-over and three passages of driftage.The present invention is applicable to the attitude control of 200～500km height low-orbit aircraft; And can adopt the mode of independent aerodynamic force accessory plate according to concrete task choosing; Also can adopt the aerodynamic force accessory plate to add the mode of wedge shape aileron, space tasks is had certain extended capability.
Embodiment three:Different with embodiment one is; This embodiment also comprises the first aerodynamic force accessory plate aileron 9, the second aerodynamic force accessory plate aileron 10, the 5th rotary machine arm 11 and the 6th rotary machine arm 12; Wherein an end of the 5th rotary machine arm 11 connects the left side of aircraft body 1; One end of the 6th rotary machine arm 12 connects the right side of aircraft body 1; The other end of the 5th rotary machine arm 11 connects the first aerodynamic force accessory plate aileron 9; And to make the first aerodynamic force accessory plate aileron 9 can be the rotation after central shaft is driven with the central axis of the 5th rotary machine arm 11, and the other end of the 6th rotary machine arm 12 connects the second aerodynamic force accessory plate aileron 10, and to make the second aerodynamic force accessory plate aileron 10 can be the rotation after central shaft is driven with the central axis of the 6th rotary machine arm 12.
Embodiment four:This embodiment is the attitude control method of the described low-orbit aircraft based on the control of aerodynamic force attitude of embodiment one, and its process is following:
Step 2, according to the deviation angle of current attitude angle and object attitude angle and utilize attitude of flight vehicle dynamics and the kinematics model that has the aerodynamic force accessory plate; Calculating and obtaining pitching needs the parts of deflection and the angle that said parts need deflection to attitude control aerodynamic force accessory plate and driftage in attitude control aerodynamic force accessory plate, then according to the parts deflection corresponding angle of result of calculation with needs deflection;
Step 3, obtain the current attitude angle of low-orbit aircraft, and calculate the deviation angle of current attitude angle and object attitude angle, judge that this deviation angle is whether in the error range that allows: if then execution in step four; Otherwise, return execution in step two;
Embodiment five:This embodiment is the further qualification to embodiment four, and said low-orbit aircraft based on the control of aerodynamic force attitude also comprises two wedge shape ailerons 4, and the said process of step 2 is:
Deviation angle according to current attitude angle and object attitude angle is also utilized attitude of flight vehicle dynamics and the kinematics model that has the aerodynamic force accessory plate; Calculating and obtaining pitching needs the parts of deflection and the angle that said parts need deflection to attitude control aerodynamic force accessory plate, driftage in attitude control aerodynamic force accessory plate and wedge shape aileron 4, then according to the parts deflection corresponding angle of result of calculation with needs deflection.
This embodiment adopts aerodynamic force to realize the attitude control of low-orbit aircraft; Can require pitching is carried out the adaptability configuration to attitude control aerodynamic force accessory plate, driftage to attitude control aerodynamic force accessory plate and wedge shape aileron 4 according to specific tasks, make the method that is proposed possess good configurability and extendability.For the low rail of 200～500km, the propellant amount of carrying that the attitude control method of this embodiment can effectively reduce low-orbit aircraft when entering the orbit, and under the situation that does not increase propellant expenditure, improve the life-span of low-orbit aircraft in the rail service.
Embodiment six:This embodiment is the further qualification to embodiment four; Said low-orbit aircraft based on the control of aerodynamic force attitude also comprises the first aerodynamic force accessory plate aileron, the second aerodynamic force accessory plate aileron, the 5th rotary machine arm and the 6th rotary machine arm, and the said process of step 2 is:
Deviation angle according to current attitude angle and object attitude angle is also utilized attitude of flight vehicle dynamics and the kinematics model that has the aerodynamic force accessory plate; Calculating and obtaining pitching needs the parts of deflection and the angle that said parts need deflection to attitude control aerodynamic force accessory plate, driftage in attitude control aerodynamic force accessory plate, the first aerodynamic force accessory plate aileron and the second aerodynamic force accessory plate aileron, then according to the parts deflection corresponding angle of result of calculation with needs deflection.
Use this embodiment below, provide a specific embodiment:
Described attitude of flight vehicle dynamics and the kinematics model that has the aerodynamic force accessory plate of step 2 is:
In the following formula; It is the angle that the 5th rotary machine arm 11 needs deflection;
is the motor-driven angle that the 6th rotary machine arm 12 needs deflection;
is the angle that the first rotary machine arm 5 needs deflection;
is the angle that the second rotary machine arm 6 needs deflection;
is the angle that the 3rd rotary machine arm 7 needs deflection;
is the angle that the 4th rotary machine arm 8 needs deflection;
is roll angle;
is the angle of pitch;
is crab angle;
is respectively angular velocity in roll, rate of pitch and yaw rate;
is respectively roll angle acceleration, angle of pitch acceleration and crab angle acceleration, and coefficient in the formula
is respectively:
Wherein,
ABe the wobble shaft principal moment of inertia,
BBe the pitch axis principal moment of inertia,
CBe the yaw axis principal moment of inertia,
C 1Be the attitude dynamics coefficient that the first rotary machine arm 5 needs deflection angle,
C 2Be the attitude dynamics coefficient that the second rotary machine arm 6 needs deflection angle,
C 3Being the attitude dynamics coefficient that the 3rd rotary machine arm 7 needs deflection angle, is the attitude dynamics coefficient that the 4th rotary machine arm 8 needs deflection angle,
C 1
Ail Be the attitude dynamics coefficient that the 5th rotary machine arm 11 needs deflection angle,
C 2
Ail Be the attitude dynamics coefficient that the 6th rotary machine arm 12 needs deflection angle,
nBe spacecraft orbit angular velocity,
C ψ For the yaw axis attitude motion is learned coefficient,
C θ For the pitch axis attitude motion is learned coefficient.
Said control algolithm selection percentage-differential control algolithm, represent as follows:
Wherein,
is the wobble shaft control moment;
is the pitch axis control moment;
is the yaw axis control moment;
is respectively the differential coefficient of wobble shaft, pitch axis and yaw axis, and
is respectively the scale-up factor of wobble shaft, pitch axis and yaw axis.
System has adopted inearized model in this example, and optional scope is bigger on controlled variable is selected, and when selecting different parameters within the specific limits, does not influence its final stable its convergence time that just influences.This routine selected controlled variable is:
Calculate and obtain
,
,
,
,
and
; According to the corresponding parts of above deflection as a result; Can realize that the moment of each passage that is the deflection of each passage aerodynamic force accessory plate come the attitude of controlling aircraft, thereby reach the purpose of adjustment attitude.
Calculate the current attitude angle of low-orbit aircraft this moment and the deviation angle of object attitude angle again, deviation angle finishes this control procedure behind all parts that therefore reset in allowed band at this moment.
This embodiment can effectively reduce the complexity of low-orbit aircraft attitude control system, can reduce the Fuel Consumption that attitude control brings, thereby can prolong low-orbit aircraft in the rail life-span.This embodiment utilizes atmospherical drag to carry out attitude control; Aerodynamic drag is converted into active role to the interference effect of low-orbit aircraft, simplifies the low-orbit aircraft attitude control method, improved reliability and reduced cost; Not only can effectively reduce the satellite energy resource consumption; And utilize aerodynamic force control for low-orbit satellite, can access enough attitude stabilizations and trajectory accuracy, for the control of the low-orbit aircraft of low-cost low-power consumption in the future provides a kind of new strategy.
Claims (8)
1. the low-orbit aircraft of controlling based on the aerodynamic force attitude; It is characterized in that it comprise aircraft body (1), pitching to attitude control aerodynamic force accessory plate, driftage to attitude control aerodynamic force accessory plate, the first rotary machine arm (5), the second rotary machine arm (6), the 3rd rotary machine arm (7) and the 4th rotary machine arm (8); Wherein, Said pitching is made up of the first aerodynamic force accessory plate (21) and the second aerodynamic force accessory plate (22) to attitude control aerodynamic force accessory plate, and driftage is made up of the 3rd aerodynamic force accessory plate (31) and the 4th aerodynamic force accessory plate (32) to attitude control aerodynamic force accessory plate;
One end of one end of one end of the said first rotary machine arm (5), the second rotary machine arm (6), the 3rd rotary machine arm (7) and an end of the 4th rotary machine arm (8) are connected the afterbody of aircraft body (1) respectively; The other end of the other end of the other end of the other end of the first rotary machine arm (5), the second rotary machine arm (6), the 3rd rotary machine arm (7) and the 4th rotary machine arm (8) points to the last rear of aircraft body (1), following rear, left back and right back respectively; And the other end of the first rotary machine arm (5) connects the first aerodynamic force accessory plate (21); And to make the first aerodynamic force accessory plate (21) can be the rotation after central shaft is driven with the central axis of the first rotary machine arm (5); The other end of the second rotary machine arm (6) connects the second aerodynamic force accessory plate (22); And to make the second aerodynamic force accessory plate (22) can be the rotation after central shaft is driven with the central axis of the second rotary machine arm (6); The other end of the 3rd rotary machine arm (7) connects the 3rd aerodynamic force accessory plate (31); And to make the 3rd aerodynamic force accessory plate (31) can be the rotation after central shaft is driven with the central axis of the 3rd rotary machine arm (7); The other end of the 4th rotary machine arm (8) connects the 4th aerodynamic force accessory plate (32), and to make the 4th aerodynamic force accessory plate (32) can be the rotation after central shaft is driven with the central axis of the 4th rotary machine arm (8);
Said aircraft body (1) is the rotational symmetry cylinder; The said first rotary machine arm (5) and the second rotary machine arm (6) are symmetrical set about the axis of pitch of aircraft body (1), and the 3rd rotary machine arm (7) and the 4th rotary machine arm (8) are symmetrical set about the vertical axis of aircraft body (1).
2. the low-orbit aircraft based on the control of aerodynamic force attitude according to claim 1, the xsect that it is characterized in that said aircraft body (1) are center symmetry polygon or circle.
3. the low-orbit aircraft based on the control of aerodynamic force attitude according to claim 1 and 2; It is characterized in that it also comprises two wedge shape ailerons (4); And the xsect of said wedge shape aileron (4) is a wedge shape; One of them wedge shape aileron (4) is positioned at the left side of aircraft body (1) and is connected with aircraft body (1) left-hand face, and another wedge shape aileron (4) is positioned at the right side of aircraft body (1) and is connected with the right lateral surface of aircraft body (1).
4. the low-orbit aircraft based on the control of aerodynamic force attitude according to claim 3; It is characterized in that the seal of each wedge shape aileron (4) for forming by five blocks of plates; Wherein, said five blocks of plates comprise rectangular slab and two set squares that three block specifications are identical, and said three rectangular slabs join end to end successively and form the triangle cylinder of a hollow; Said two set squares place the upper bottom surface place and the bottom surface place of this triangle cylinder respectively, and the junction of these five blocks of plates is and is tightly connected.
5. the low-orbit aircraft based on the control of aerodynamic force attitude according to claim 1; It is characterized in that it also comprises the first aerodynamic force accessory plate aileron (9), the second aerodynamic force accessory plate aileron (10), the 5th rotary machine arm (11) and the 6th rotary machine arm (12); Wherein an end of the 5th rotary machine arm (11) connects the left side of aircraft body (1); One end of the 6th rotary machine arm (12) connects the right side of aircraft body (1); The other end of the 5th rotary machine arm (11) connects the first aerodynamic force accessory plate aileron (9); And to make the first aerodynamic force accessory plate aileron (9) can be the rotation after central shaft is driven with the central axis of the 5th rotary machine arm (11); The other end of the 6th rotary machine arm (12) connects the second aerodynamic force accessory plate aileron (10), and to make the second aerodynamic force accessory plate aileron (10) can be the rotation after central shaft is driven with the central axis of the 6th rotary machine arm (12).
6. the attitude control method of the described low-orbit aircraft based on aerodynamic force attitude control of claim 1 is characterized in that its process is following:
Step 1, measure sensor with attitude of flight vehicle and obtain the current attitude angle of said low-orbit aircraft and confirm the object attitude angle of low-orbit aircraft, calculate and obtain the deviation angle of current attitude angle and object attitude angle according to mission planning;
Step 2, according to the deviation angle of current attitude angle and object attitude angle and utilize attitude of flight vehicle dynamics and the kinematics model that has the aerodynamic force accessory plate; Calculating and obtaining pitching needs the parts of deflection and the angle that said parts need deflection to attitude control aerodynamic force accessory plate and driftage in attitude control aerodynamic force accessory plate, then according to the parts deflection corresponding angle of result of calculation with needs deflection;
Step 3, obtain the current attitude angle of low-orbit aircraft, and calculate the deviation angle of current attitude angle and object attitude angle, judge that this deviation angle is whether in the error range that allows: if then execution in step four; Otherwise, return execution in step two;
Step 4, make the parts that are rotated in the step 2 reply original state, finishing control process.
7. the attitude control method of low-orbit aircraft according to claim 6 is characterized in that said low-orbit aircraft based on the control of aerodynamic force attitude also comprises two wedge shape ailerons (4), and the said process of step 2 is:
Deviation angle according to current attitude angle and object attitude angle is also utilized attitude of flight vehicle dynamics and the kinematics model that has the aerodynamic force accessory plate; Calculating and obtaining pitching needs the parts of deflection and the angle that said parts need deflection to attitude control aerodynamic force accessory plate, driftage in attitude control aerodynamic force accessory plate and wedge shape aileron (4), then according to the parts deflection corresponding angle of result of calculation with needs deflection.
8. the attitude control method of low-orbit aircraft according to claim 6; It is characterized in that said low-orbit aircraft based on the control of aerodynamic force attitude also comprises the first aerodynamic force accessory plate aileron (9), the second aerodynamic force accessory plate aileron (10), the 5th rotary machine arm (11) and the 6th rotary machine arm (12), the said process of step 2 is:
Deviation angle according to current attitude angle and object attitude angle is also utilized attitude of flight vehicle dynamics and the kinematics model that has the aerodynamic force accessory plate; Calculating and obtaining pitching needs the parts of deflection and the angle that said parts need deflection to attitude control aerodynamic force accessory plate, driftage in attitude control aerodynamic force accessory plate, the first aerodynamic force accessory plate aileron (9) and the second aerodynamic force accessory plate aileron (10), then according to the parts deflection corresponding angle of result of calculation with needs deflection.
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| CN103466102B (en) * | 2013-09-24 | 2015-09-23 | 北京航天自动控制研究所 | Flying vehicles control effect redistribution method in cross configuration actuator failure situation |
| CN104977936A (en) * | 2014-04-09 | 2015-10-14 | 上海九鹰电子科技有限公司 | Remote signal sending/receiving method and device, remote controller and remote control model |
| FR3022530B1 (en) * | 2014-06-19 | 2018-03-02 | Airbus Defence And Space Sas | METHOD FOR CONTROLLING THE ORBIT OF A SATELLITE IN TERRESTRIAL ORBIT, SATELLITE AND SYSTEM FOR CONTROLLING THE ORBIT OF SUCH A SATELLITE |
| CN104743100B (en) * | 2015-03-03 | 2017-01-25 | 北京航天自动控制研究所 | Redistribution method of control action for aircraft under fault condition of executing mechanisms for X-type configuration |
| CN105836161B (en) * | 2016-04-29 | 2017-12-26 | 北京零壹空间科技有限公司 | Staged aircraft control system and method, staged aircraft and guided missile and rocket |
| CN106005482B (en) * | 2016-05-23 | 2018-05-01 | 北京空间飞行器总体设计部 | A kind of zero bias continuous days for being suitable for navigation inclined plane satellite determine method |
| CN107585328A (en) * | 2017-08-22 | 2018-01-16 | 北京空间技术研制试验中心 | The multi-functional manned spacecraft that can be flown for a long time |
| CN113602533B (en) * | 2021-08-26 | 2023-04-07 | 北京航空航天大学 | Ultra-low orbit satellite orbit control method based on aerodynamic assistance |
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