CN113734473B - Pneumatic layout of high-speed-reduction extraterrestrial celestial body entering device with rear body resistance and stability increasing function - Google Patents
Pneumatic layout of high-speed-reduction extraterrestrial celestial body entering device with rear body resistance and stability increasing function Download PDFInfo
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- CN113734473B CN113734473B CN202111014969.0A CN202111014969A CN113734473B CN 113734473 B CN113734473 B CN 113734473B CN 202111014969 A CN202111014969 A CN 202111014969A CN 113734473 B CN113734473 B CN 113734473B
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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
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
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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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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Abstract
The aerodynamic configuration of the high-speed-reduction extraterrestrial celestial body entering device with the rear body resistance and stability increasing function is an axisymmetric revolving body structure and comprises a windward front body, a leeward rear body and an adjusting wing plate; the windward forebody comprises a ball head and a windward frustum, the ball head is arranged at the small end of the windward frustum, and the ball head and the windward frustum are in smooth transition; the leeward afterbody comprises an afterbody frustum and an afterbody ball table, and the large end of the afterbody ball table and the small end of the afterbody frustum are in smooth transition; the adjusting wing plate is embedded on the side wall of the rear body frustum; the windward frustum and the rear body frustum adopt peripheral arc transition to form a transition shoulder. The invention is applicable to all types of ballistic or semi-ballistic access missions.
Description
Technical Field
The invention belongs to the field of pneumatic design of deep-space extraterrestrial celestial body entry, and relates to an extraterrestrial celestial body entry device.
Technical Field
For the high-speed reentry task of the celestial body outside the atmospheric ground, how to utilize the shape of the entrant to carry out high-efficiency pneumatic deceleration and ensure that the entrant has good flight stability and reasonable surface thermal environment distribution is a key element for realizing safe entrance deceleration landing of the entrant. For the condition that the atmosphere of the celestial body is thin or the entering speed is extremely high, the aerodynamic shape is required to have high deceleration performance, namely large resistance characteristic, so that the speed of an entering cabin entering at a high speed can be reduced to a lower level before reaching the parachute opening height, and safe parachute opening is realized; secondly, the aerodynamic shape is required to have better static and dynamic stability in most sections of entering flight so as to ensure that the attitude of entering the cabin can be kept near a balance attack angle, and large-angle drift or overturning can not occur, so that the thermal protection system is damaged or the large-attack angle parachute opening fails; third, it is desirable that the aerodynamic profile have a reasonable heat flow density distribution, that local heat flow spikes do not occur, and that the surface high heat flow area be as small as possible to avoid local failure or increased weight consumption of the thermal protection system.
The existing foreign celestial body entering device in foreign countries has the appearance of a ball head, a frustum windward front body and an inverted cone rear body, can provide efficient aerodynamic resistance according to the requirement of entering a task and meet the reasonable surface thermal environment distribution of the design requirement of a heat-proof structure, but has the defects of weak high-altitude static stability and weak ultrasonic-crossing quick-action stability, and is not beneficial to the entering of the entering device for safely entering the speed-reducing landing. Before the invention, a related knowledge system of the appearance design of the extraterrestrial celestial body entrance device is not formed in China, and the appearance characteristics of the conventional reentry satellite, the Shenzhou airship reentry capsule and the lunar exploration three-phase returning device have large difference with the requirement of high deceleration of the extraterrestrial celestial body, so that the extraterrestrial celestial body entrance device cannot be adopted.
Disclosure of Invention
The invention aims to provide a pneumatic layout of a high-deceleration extraterrestrial celestial body entrance device with increased resistance and stability of a rear body, aiming at the defects in the appearance design of the existing extraterrestrial celestial body entrance device at home and abroad, and the pneumatic layout is suitable for various ballistic or semi-ballistic entrance tasks. Wherein, the expansion of the adjusting wing plate can realize the increase or decrease of the flying attack angle, and can improve the resistance and the static/dynamic stability of the small attack angle.
In order to achieve the purpose, the invention provides a pneumatic layout of a high-speed-reduction extraterrestrial celestial body entering device for increasing resistance and stability of a rear body, wherein the pneumatic appearance of the entering device is an axisymmetric revolving body structure and comprises a windward front body, a leeward rear body and an adjusting wing plate;
the windward forebody comprises a ball head and a windward frustum, the ball head is arranged at the small end of the windward frustum, the ball head and the windward frustum are in smooth transition, the radius of the ball head and the half cone angle of the windward frustum are adjusted according to the lift-drag performance requirement, the radius of the ball head is not more than 40% of the maximum windward section diameter of the feeder, and the half cone angle of the windward frustum is not more than 75 degrees;
the leeward afterbody comprises an afterbody frustum and an afterbody ball table, and the large end of the afterbody ball table and the small end of the afterbody frustum are in smooth transition; the frustum half cone angle of the rear body frustum and the radius and height of the rear body ball table are adjusted according to stability augmentation design requirements; the frustum half cone angle of the rear body frustum is not less than 22 degrees, and the radius of the rear body ball table is not less than 70 percent of the maximum windward section diameter of the inlet device;
the adjusting wing plate is embedded on the side wall of the rear body frustum, when the adjusting wing plate is unfolded, the resistance coefficient and the lift coefficient of the inlet device in a full attack angle range can be increased, the pitching moment coefficient of the inlet device in an attack angle range of +/-60 degrees is increased, the static and stable moment derivative of the inlet device in a range of +/-30 degrees is reduced, and the small attack angle dynamic derivative of the inlet device is changed towards a direction smaller than 0, so that the effects of increasing resistance and enhancing stability can be realized while the trim attack angle of the inlet device is changed.
The windward frustum and the rear body frustum adopt peripheral arc transition to form a transition shoulder, and the radius of the arc is not less than 5% of that of the ball head.
The adjusting wing plate is a flat plate or an arc panel with the same radian as the conical surface of the rear body frustum; after the adjusting wing plate is folded, the outer surface of the adjusting wing plate is superposed with the outer peripheral conical surface of the rear body frustum or slightly lower than the outer peripheral conical surface of the rear body frustum.
The small end of the rear ball table is a circular plane.
The transverse mass center of the feeder is offset or not offset from the rotating shaft: when the transverse direction is not offset, the inlet device obtains a trim attack angle by opening the adjusting wing plate; when the transverse center of mass is offset, the entrance device can realize the attack angle recovery by opening the adjusting wing plate.
Compared with the prior art, the invention has the beneficial effects that:
(1) The pneumatic appearance of the extraterrestrial celestial body feeder can improve the stability of ultrasonic quick motion under the condition of basically not reducing the resistance of the feeder and the lift-drag ratio performance through the matching design of the leeward rear body sphere-cone combination appearance parameters, thereby reducing the attitude oscillation of the feeder before opening the umbrella and improving the safety of opening the umbrella;
(2) The pneumatic appearance of the extraterrestrial celestial body feeder adopts the layout of the expandable adjusting wing plates arranged on the conical surface of the rear body, and the resistance performance and stability are improved by opening the wing plates at high altitude and a main deceleration section, or the stability is improved and the attack angle is recovered by opening the wing plates before opening the parachute. Thereby improving the safety of the entering device entering into deceleration landing.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Figure 1 is a schematic diagram of the pneumatic profile of a spark injector according to one embodiment of the present invention.
Figure 2 is a diagram of the relationship of the size parameters of the aerodynamic body of the spark injector according to one embodiment of the present invention.
Figure 3 is a schematic view of the pneumatic profile of the spark injector in an open state of the adjustment flap, according to one embodiment of the present invention.
Fig. 4 is a schematic diagram of the pitch aerodynamic forces and moments experienced by the aerodynamic profile of a mars injector in the oncoming wind according to an embodiment of the present invention.
FIG. 5 is a schematic representation of the aerodynamic profile of a Mars injector for a three cone aft body similar to the US MSL lander.
FIG. 6 shows the centroid pitching moment coefficient C at Ma =1.5 and the coefficients of the transverse and longitudinal centroids (0.27D, -0.009D) for a Mars injector aerodynamic profile according to an embodiment of the invention and a Mars injector aerodynamic profile for a tricone back body as a comparative example Mzg The change curves along the attack angle are compared with each other.
Fig. 7 is a comparison graph of the entrance drag coefficient versus angle of attack for a mars entrance aerodynamic profile with adjustment flaps open before and after Ma =5 in accordance with an embodiment of the present invention.
FIG. 8 is a diagram of a Mars inlet aerodynamic profile with center of mass pitching moment coefficient C at Ma =1.5 and transverse and longitudinal center of mass coefficients (0.27D, -0.009D), according to an embodiment of the present invention Mzg The change curves along the attack angle are compared with each other.
Detailed Description
The present invention is described in further detail below with reference to the attached drawings and examples.
A mars entry figure comprising: the device comprises a ball head 1, a windward frustum 2, a transition shoulder 3, a rear body frustum 4, a rear body ball table 5, a rear body small end 6 and an adjusting wing plate 7, which are shown in the figures 1, 2 and 3.
The pneumatic appearance of the inlet is an axisymmetric revolution body structure and comprises a windward front body, a leeward rear body and an adjusting wing plate 7;
the windward forebody comprises a ball head 1 and a windward frustum 2, wherein the ball head 1 is arranged at the small end of the windward frustum 2, the ball head 1 and the windward frustum 2 are in smooth transition, the radius of the ball head 1 and the frustum half-cone angle of the windward frustum 2 are adjusted according to the lift-drag performance requirement, the radius of the ball head 1 is not more than 40% of the maximum windward section diameter of the air inlet device, and the half-cone angle of the windward frustum 2 is not more than 75 degrees;
the leeward afterbody comprises an afterbody frustum 4 and an afterbody ball table 5, and the large end of the afterbody ball table 5 is in smooth transition with the small end of the afterbody frustum 4; the frustum half cone angle of the rear body frustum 4 and the radius and height of the rear body ball table 5 are adjusted according to stability augmentation design requirements; the frustum half cone angle of the rear body frustum 4 is not less than 22 degrees, and the radius of the rear body ball table 5 is not less than 70 percent of the maximum windward section diameter of the inlet device;
the adjusting wing plate 7 is embedded on the side wall of the rear body frustum 4, when the adjusting wing plate 7 is unfolded, the resistance coefficient and the lift coefficient of the inlet device in the full attack angle range can be increased, the pitching moment coefficient of the inlet device in the attack angle range of +/-60 degrees is increased, the static stability moment derivative of the inlet device in the range of +/-30 degrees is reduced, and the small attack angle dynamic derivative of the inlet device is changed towards the direction smaller than 0, so that the effects of increasing resistance and enhancing stability can be realized while the trim attack angle of the inlet device is changed.
The large end of the windward frustum 2 is in butt joint with the large end of the rear body frustum 4, the large end of the windward frustum 2 and the large end of the rear body frustum 4 are in peripheral arc transition to form a transition shoulder 3, and the radius of the arc is not less than 5% of that of the ball head 1.
The adjusting wing plate 7 is a flat plate or an arc panel with the same radian as the conical surface of the rear body frustum 4; after the adjusting wing plate 7 is folded, the outer surface of the adjusting wing plate is superposed with the outer peripheral conical surface of the back body frustum 4 or is slightly lower than the outer peripheral conical surface of the back body frustum 4.
The small end of the rear ball table 5 is a circular plane.
The transverse mass center of the feeder is offset or not offset from the rotating shaft: when not laterally offset, the entry device obtains a trim angle of attack by opening the adjustment wing plate 7; when the transverse centroid is offset, the entrance device achieves angle of attack restoration by opening the adjustment flap 7.
The air flow flies towards the air flow at a certain attack angle when entering the device, the air flow generates corresponding axial force CA and normal force CN on the device respectively, the pneumatic force is decomposed under the wind shaft system of the device, the pneumatic force is decomposed into resistance CD along the air flow direction and lift CL vertical to the air flow direction, the device receives the resultant moment C of the air flow at the center of mass in the pitching direction of the device mz g The trim angle of attack and static stability of the feeder are characterized, see FIG. 4. When a certain angle of attack is C mz g At 0, the angle of attack is the entry trim angle of attack. When C is present mz g When the slope of the curve increases with angle of attack, or when C is not required mz g C with curve zero crossing far away from design requirement mz g At zero crossing (design trim angle of attack), the characterization enters the static stability enhancement of the device.
For the pneumatic shape of the Mars injector of the embodiment, the non-requirement C is before the supersonic parachute opening mz g The distance between the second zero-crossing point of the curve and the design leveling point is farther than the shape (see fig. 5) of the MSL tricone rear body inlet (see fig. 6), thereby proving that the shapes of the rear body frustum 4 and the rear body ball table 5 corresponding to the invention improve the static flying stability of the inlet at supersonic speed.
For the aerodynamic shape of the Mars feeder of the embodiment, the pitching derivative Cmq is lower than the three-cone afterbody shape near the trim attack angle before the supersonic parachute opening, that is, the supersonic velocity dynamic stability of the Mars feeder of the embodiment is improved compared with the three-cone afterbody feeder.
Table 1 shows the comparison of the profile of the present embodiment with the supersonic pitch derivative of the profile of the rear body of the tricone
For the pneumatic shape of the Mars injector of the embodiment, when the adjusting wing plates 7 arranged on the rear body cone platform 4 are opened, the resistance performance near the hypersonic trim attack angle is improved by about 9 percent compared with the folded state of the wing plates (see figure 7), the pitching moment of the mass center and the slope (namely static stability margin) of the mass center in the vicinity of the hypersonic trim attack angle are increased compared with the folded state of the wing plates 7 (see figure 8), and therefore the corresponding layout design of the rear body extensible adjusting wing plates has the effects of increasing the resistance and the static and dynamic stability near the trim attack angle for the injector, and has the return effect on the trim attack angle of the injector under the bias of the transverse mass center.
For the aerodynamic shape of the Mars advancer of the embodiment, when the initial transverse centroid of the advancer deviates from the rotating shaft, i.e. the advancer has a trim attack angle in the main deceleration section, the deployed adjusting wing plate state of the supersonic advancer is lower than the pitching derivative Cmq near the trim attack angle of the folded adjusting wing plate, i.e. the deployed adjusting wing plate in the aerodynamic shape of the Mars advancer of the embodiment has enhanced supersonic dynamic stability.
Table 2 shows the comparison of the front and rear supersonic pitching derivatives of the profile adjusting wing plate of this embodiment
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
The present invention has not been described in detail, partly as is known to the person skilled in the art.
Claims (5)
1. The aerodynamic layout of the high-deceleration extraterrestrial celestial body entering device for increasing the resistance and stability of the afterbody is characterized in that the aerodynamic appearance of the entering device is an axisymmetric revolving body structure and comprises a windward forebody, a leeward afterbody and an adjusting wing plate (7);
the windward forebody comprises a ball head (1) and a windward frustum (2), the ball head (1) is arranged at the small end of the windward frustum (2), and the ball head (1) and the windward frustum (2) are in smooth transition;
the leeward afterbody comprises an afterbody frustum (4) and an afterbody ball table (5), and the large end of the afterbody ball table (5) is in smooth transition with the small end of the afterbody frustum (4);
the adjusting wing plate (7) is installed on the side wall of the rear body frustum (4) in an embedded mode;
the large end of the windward frustum (2) and the large end of the rear body frustum (4) are in peripheral arc transition to form a transition shoulder (3);
when the adjusting wing plate (7) is unfolded, the resistance coefficient and the lift coefficient of the entering device in a full attack angle range can be increased, the pitching moment coefficient of the entering device in an attack angle range of +/-60 degrees is increased, the static and stable moment derivative of the entering device in a range of +/-30 degrees is reduced, and the small attack angle dynamic derivative of the entering device is changed towards a direction smaller than 0;
the transverse mass center of the feeder is offset or not offset from the rotating shaft: when the transverse direction is not biased, the inlet device obtains a trim attack angle by opening the adjusting wing plate (7); when the transverse center of mass is offset, the entrance device realizes attack angle recovery by opening the adjusting wing plate (7);
the radius of the ball head (1) is not more than 40% of the diameter of the largest windward section of the entering device, and the half cone angle of the windward frustum (2) is not more than 75 degrees;
the frustum half cone angle of the rear body frustum (4) is not less than 22 degrees, and the radius of the rear body ball platform (5) is not less than 70 percent of the diameter of the maximum windward section of the air inlet device;
the radius of the arc of the transition shoulder (3) is not less than 5% of the radius of the ball head (1).
2. The aerodynamic layout of the high-deceleration extraterrestrial celestial body entering device with the rear body resistance-increasing and stability-increasing functions as claimed in claim 1, wherein the radius of the ball head (1) and the frustum half-cone angle of the windward frustum (2) are adjusted according to the resistance-increasing performance requirement.
3. The aerodynamic layout of the high-deceleration extraterrestrial celestial body entering device with the rear body resistance-increasing and stability-increasing functions as claimed in claim 2, wherein the frustum half-cone angle of the rear body frustum (4) and the radius and height of the rear body spherical platform (5) are adjusted according to stability-increasing design requirements.
4. The aerodynamic layout of the high-deceleration extraterrestrial celestial body entering device with the rear body resistance-increasing and stability-increasing functions as claimed in claim 3, wherein the adjusting wing plates (7) are flat plates or cambered plates with the same radian as the conical surface of the rear body frustum (4); after the adjusting wing plate (7) is folded, the outer surface of the adjusting wing plate is superposed with the outer peripheral conical surface of the rear body frustum (4) or is lower than the outer peripheral conical surface of the rear body frustum (4).
5. The pneumatic layout of the high-deceleration extraterrestrial celestial body entering device with the resistance and stability increasing function of the afterbody according to claim 4, wherein the small end of the afterbody ball table (5) is a circular plane.
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| CN202111014969.0A CN113734473B (en) | 2021-08-31 | 2021-08-31 | Pneumatic layout of high-speed-reduction extraterrestrial celestial body entering device with rear body resistance and stability increasing function |
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| CN202111014969.0A CN113734473B (en) | 2021-08-31 | 2021-08-31 | Pneumatic layout of high-speed-reduction extraterrestrial celestial body entering device with rear body resistance and stability increasing function |
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| CN113734473B true CN113734473B (en) | 2022-10-14 |
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| US7431242B1 (en) * | 2005-11-01 | 2008-10-07 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration (Nasa) | Re-entry vehicle shape for enhanced performance |
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| CN112249365A (en) * | 2020-10-29 | 2021-01-22 | 北京空间飞行器总体设计部 | Reusable spacecraft |
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| US11565833B2 (en) * | 2019-09-10 | 2023-01-31 | Planetary Systems Corporation | Recovery of a final stage of a spacecraft launch vehicle |
| CN112693628B (en) * | 2020-12-28 | 2022-04-12 | 中国航天空气动力技术研究院 | Pneumatic layout structure of mars landing inspection tour ware |
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- 2021-08-31 CN CN202111014969.0A patent/CN113734473B/en active Active
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|---|---|---|---|---|
| US4817895A (en) * | 1985-06-18 | 1989-04-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Aerobraking orbital transfer vehicle |
| US7431242B1 (en) * | 2005-11-01 | 2008-10-07 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration (Nasa) | Re-entry vehicle shape for enhanced performance |
| CN102941927A (en) * | 2012-11-30 | 2013-02-27 | 中国航天空气动力技术研究院 | Axial-symmetry blunt body returner |
| CN112249365A (en) * | 2020-10-29 | 2021-01-22 | 北京空间飞行器总体设计部 | Reusable spacecraft |
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| Title |
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