CN112623179B - Recoverable flexible formula transmission nacelle - Google Patents
Recoverable flexible formula transmission nacelle Download PDFInfo
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- CN112623179B CN112623179B CN202011536840.1A CN202011536840A CN112623179B CN 112623179 B CN112623179 B CN 112623179B CN 202011536840 A CN202011536840 A CN 202011536840A CN 112623179 B CN112623179 B CN 112623179B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/22—Arrangement of cabins or gondolas
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
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Abstract
The invention belongs to the technical field of pod equipment, and provides a recoverable deformable launch pod based on the defects of the existing aerostat pod. The nacelle can realize the integration of functions such as floating flight suspension, near-air launching and launching, safe buffer landing, stealth shielding, repeatable repeated recovery and launching and the like by utilizing the deformation of the nacelle. And simultaneously, a plurality of buffers can realize synchronous buffering.
Description
Technical Field
The invention belongs to the technical field of pod equipment, and particularly relates to a recyclable deformable launch pod.
Background
A pod is a streamlined, short-cabin segment that is equipped with some onboard equipment or weapons and is suspended from the fuselage or wings. With the development of aviation technology, the technology of airborne pod has also been greatly improved. Generally speaking, airborne pods can be divided into: weapons pods (including aircraft gun pods, aircraft rocket pods), reconnaissance pods, fire control pods, logistics aids pods (fueling pods).
At present, the research on aerostat launching pods is few on the global scale, and particularly, the aerostat launching pods with deformable bodies are not precedent.
The existing few aerostat launching pods can only realize the aircraft launching function, and can not realize the integration of functions such as floating flight suspension, near-air launching and launching, safe buffer landing, stealth shielding, repeatable repeated recovery and launching and the like through whole-body deformation.
Meanwhile, the buffer damping devices of various landers are difficult to realize synchronous buffering.
Disclosure of Invention
Based on the defects of the existing aerostat nacelle, the invention provides the recoverable and deformable launch nacelle which can realize functional integration of floating flight suspension, near-air launch launching, safe buffer landing, stealth shielding, repeatable repeated recovery launching and the like by using deformation of a machine body. And simultaneously, a plurality of buffers can realize synchronous buffering.
The technical scheme adopted by the invention is as follows:
the utility model provides a recoverable flexible formula transmission nacelle, includes that electric load cabin, nacelle warp the frame, along with shape fixed frame, underframe, synchronous bumper shock absorber, hangs aircraft and rope actuating system, hang the aircraft and hang on the lifting hook in electric load cabin, along with the bottom that shape fixed frame is fixed in electric load cabin through a central mount, limit mount an and limit mount b, hang the aircraft and set up in the along with shape supported hole along with shape fixed frame, synchronous bumper shock absorber installs in the bottom relevant position in electric load cabin, rope actuating system installs in electric load cabin, four wire rope of rope actuating system pass through the leading-in synchronous bumper shock absorber of multiunit fixed pulley in to be fixed in the relevant position of underframe, receive and release through four wire rope.
Furthermore, the electric load cabin comprises an electric load cabin frame, the electric load cabin frame is of a multi-pipe welded frame structure, a rope driving system, a power supply system and a control system are installed in the electric load cabin frame, an upper cover plate, a lower cover plate, a front side plate, a rear side plate, a left side plate, a right side plate and an inclined side plate are sequentially arranged outside the electric load cabin frame in a covering mode, and the electric load cabin frame is fixed at the corresponding position of the bottom of the electric load cabin through a hinged support lug c.
Further, the pod deformation frame is arranged into an upper deformation frame and a lower deformation frame, wherein the upper deformation frame comprises a left upper deformation frame, a right upper deformation frame, a front upper deformation frame, a rear upper deformation frame and an inclined upper deformation frame; the lower deformation frame comprises a left lower deformation frame, a right lower deformation frame, a front lower deformation frame, a rear lower deformation frame and an inclined lower deformation frame; the upper deformation frame is hinged on the electric load cabin, and the lower deformation frame is hinged on the upper deformation frame; the bottom frame is hinged to the lower deformation frame, a deformation system of the pod is formed jointly, and deformation of the launch pod and switching of a hanging posture, a launching posture and a recovery posture are achieved.
Furthermore, the left upper deformation frame and the right upper deformation frame comprise a left upper deformation frame, a right upper deformation frame, a hinge lug plate c, a hinge lug a and a stealth cover plate, wherein the hinge lug plate c is fixed at the top of the left upper deformation frame and the right upper deformation frame, the hinge lug a is fixed at the bottom of the left upper deformation frame and the right upper deformation frame, the stealth cover plate is fixed at the outer side of the left upper deformation frame and the right upper deformation frame, the left upper deformation frame and the right upper deformation frame are of a multi-square-tube welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is set to be 85 degrees, and one oblique beam is welded inside the trapezoid;
the front upper deformation frame and the rear upper deformation frame comprise front upper deformation frames and rear upper deformation frames, hinge lug plates c, hinge lugs a and stealth covering plates, wherein the hinge lug plates c are fixed at the tops of the front upper deformation frames and the rear upper deformation frames, the hinge lugs a are fixed at the bottoms of the front upper deformation frames and the rear upper deformation frames, the stealth covering plates are fixed at the outer sides of the front upper deformation frames and the rear upper deformation frames, the front upper deformation frames and the rear upper deformation frames are in a multi-side pipe welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is set to be 85 degrees, and two oblique beams are welded in the trapezoid to form a cross posture;
go up to one side and warp the frame including going up to one side and warp frame, articulated otic placode c, articulated journal stirrup a, stealth overlay, wherein articulated otic placode c is fixed in and warp the frame top to one side, and articulated journal stirrup a is fixed in and warp the frame bottom to one side, and stealth overlay is fixed in and warp the outside of frame to one side, goes up to one side and warp the frame and set up to many square tube welding isosceles trapezoid structure, and isosceles trapezoid structure angle sets up to 85 degrees, and trapezoidal internal weld has one sloping.
Furthermore, the left lower deformation frame and the right lower deformation frame comprise a left lower deformation frame, a right lower deformation frame, a hinge lug plate a, a hinge lug b and a stealth cover plate, wherein the hinge lug b is fixed at the top of the left lower deformation frame and the right lower deformation frame, the hinge lug b is fixed at the bottom of the left lower deformation frame and the right lower deformation frame, the stealth cover plate is fixed at the outer side of the left lower deformation frame and the right lower deformation frame, the left lower deformation frame and the right lower deformation frame are of a multi-square-tube welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is set to be 85 degrees, and one oblique beam is welded inside the trapezoid;
the front lower deformation frame and the rear lower deformation frame comprise a front lower deformation frame and a rear lower deformation frame, hinge lug plates a, hinge lugs b and stealth covering plates, wherein the hinge lugs b are fixed at the tops of the front lower deformation frame and the rear lower deformation frame, the hinge lugs b are fixed at the bottoms of the front lower deformation frame and the rear lower deformation frame, the stealth covering plates are fixed at the outer sides of the front lower deformation frame and the rear lower deformation frame, the front lower deformation frame and the rear lower deformation frame are of a multi-square-tube welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is set to be 85 degrees, and two oblique beams are welded in the trapezoid to form a cross posture;
the frame warp under to one side includes warp frame, articulated otic placode a, articulated journal stirrup b, stealthy overlay under to one side, and wherein articulated journal stirrup b is fixed in warp the frame top under to one side, and articulated journal stirrup b is fixed in warp the frame bottom under to one side, and stealthy overlay is fixed in the outside of warping the frame under to one side, and the frame that warp sets up to many square tube welding isosceles trapezoid structure under to one side, and isosceles trapezoid structure angle sets up to 85 degrees, and trapezoidal internal weld has one sloping.
Further, the underframe includes underframe frame, foamed aluminum shock attenuation frame, articulated otic placode b, on foamed aluminum shock attenuation frame was fixed in the underframe frame, articulated otic placode b was fixed in underframe frame relevant position, formed the underframe, and the underframe sets up to the octagon hollow out frame who contains foamed aluminum buffer material.
Furthermore, the pod is in a hanging posture, the angle between the upper deformation frame and the lower deformation frame in the hanging posture is set to be 155 degrees, the limit position of the pod is a lower limit position of the posture, the limit position of the pod is a flexible contact limit between the stealth covering plates, the rigid limit of the hinge support lug c and the hinge lug plate c, the rigid limit of the hinge support lug a and the hinge lug plate a and the rigid limit of the hinge support lug b and the hinge lug plate b are adopted, and the suspension state of the pod can not be generated.
Furthermore, the pod is in a launching attitude, the angle between the upper deformation frame and the lower deformation frame in the attitude is set to be about 30 degrees, the reference position is the mutual contact position of the synchronous damper and the bottom frame, the synchronous damper and the bottom frame are in mutual contact, the steel wire rope is prevented from being exposed in the pod during launching, and launching safety is guaranteed.
Furthermore, the pod is in a recovery posture, the upper deformation frame and the lower deformation frame are arranged at about 30 degrees in the recovery posture, the reference position is the mutual contact position of the synchronous damper and the bottom frame, the synchronous damper and the bottom frame are in mutual contact, the steel wire rope cannot be exposed in the pod during recovery control, and the recovery safety is guaranteed; secondly, when the nacelle is in contact with the ground, the angle of the upper and lower deformation frames of the nacelle is changed between 30 degrees through compression of the synchronous shock absorber, and the angle range depends on the elastic forming range of the synchronous shock absorber.
The invention has the beneficial effects that:
1. the nacelle deformation system comprises 16 deformation frames, an electrical load cabin, a bottom frame and a rope driving system, each deformation frame comprises an upper titanium alloy hinged support lug and a lower titanium alloy hinged support lug, 16 titanium alloy hinged support lugs are fixed on the electrical load cabin of the nacelle, 16 titanium alloy hinged support lugs are fixed on the bottom frame of the nacelle, the 16 deformation frames, the hinged support lugs of the electrical load cabin and the bottom frame are hinged with each other through a pin shaft and a graphite lubrication bearing to form a deformation frame structure, a limit structure is arranged between the support lugs to ensure that the deformation of the nacelle does not exceed an effective range, and the deformation system can realize the switching of three postures of stealth hanging of the nacelle, aircraft launching and buffer landing of the nacelle under the driving of the rope driving system, so that the repeatability of the functions of floating flight hanging of the nacelle, near-air launching, safe buffer landing, stealth shielding, multiple recovery and launching and the like can be realized.
2. When the nacelle is in a hanging posture, the cabin body is deformed into a closed state, the whole nacelle is closed into one cabin body, the aircraft is suspended in the cabin body through the lifting ropes and the hot knife and is fixed in the cabin body through the aircraft conformal fixing frame, the aircraft is guaranteed not to shake relative to the nacelle, the stealth material is fixed on the outer layer of the nacelle frame, a multi-pyramid stealth structure is formed, the aircraft is shielded, and the nacelle is stealthed.
3. When the pod is in a launching attitude, the cabin body deforms to be in a launching state, the whole pod is unfolded, the front part and the middle part of the aircraft are exposed out of the pod body, the rear part of the aircraft is fixed in a shape-following fixing frame and is suspended in the pod body through a lifting rope and a hot knife, the attitude can ensure that the aircraft has a large launching window, the shape-following fixing frame ensures that the aircraft is launched along the pod deformation direction, when the pod has a certain inclination angle relative to a ground vertical line, the aircraft can still be launched along the pod deformation direction, other parts of the pod body cannot be touched, launching safety is ensured, when the hot knife cuts off the aircraft suspension rope, the aircraft is launched along the pod deformation direction, and after several seconds, the aircraft is ignited, and the suspension type launching of the aircraft is completed. Meanwhile, the flexible steel cable in the hanging cabin is also limited in the synchronous shock absorber, so that the launching cannot be influenced by the vibration of the steel cable, and the launching safety is ensured.
4. When the aircraft is launched, the pod is in a cabin body buffering landing posture, the pod suspension parachute is separated from the floating air ball at the moment, the pod slowly descends under the deceleration of the parachute, and when the bottom frame of the pod is in contact with the ground, the bottom frame is made of foamed aluminum damping materials, the synchronous damper, the flexible conformal fixing frame, the flexible engine body frame, the electric cabin foam board and other damping systems have comprehensive effects, so that safe landing and repeatable recycling of the pod are realized. It is worth mentioning that the main shock absorbers are four synchronous shock absorbers, due to the special nacelle deformation frame structure, the deformation and the shock absorption force of the four synchronous shock absorbers are changed synchronously, when the nacelle obliquely lands, the shock absorbers can simultaneously and synchronously provide shock absorption at each moment, the landing buffering performance of the nacelle is greatly improved, meanwhile, the center of the nacelle descends under the attitude, the landing area is increased, and the anti-overturning performance of the nacelle during landing is improved.
Drawings
FIG. 1 is a three-dimensional view of the pod-hanging attitude of the present invention;
FIG. 2 is a bottom view of the nacelle suspension attitude of the present invention;
FIG. 3 is a side view of the launch attitude of the pod of the present invention;
FIG. 4 is a three-dimensional view of the launch attitude of the pod of the present invention;
FIG. 5 is a three-dimensional view of the landing retrieval attitude of the pod of the present invention;
FIG. 6 is a bottom view of the landing retrieval attitude of the pod of the present invention;
FIG. 7 is a three-dimensional view of the pod launch attitude frame of the present invention;
FIG. 8 is a three-dimensional view of the nacelle-hanging attitude frame of the present invention;
FIG. 9 is an oblique top view of the nacelle-hanging attitude frame of the present invention;
FIG. 10 is a schematic view of the hinge connection of the electrical load compartment and the upper deformed frame according to the present invention;
FIG. 11 is a schematic view of the hinge connection between the upper and lower deformable frames of the present invention;
FIG. 12 is a schematic view of the hinge connection between the lower deformable frame and the bottom frame of the present invention;
wherein, 1, an electric load cabin; 2. an upper deformation frame; 3. a shape-following fixing frame; 4. a bottom frame; 5. a lower deformation frame; 6. a synchronous damper; 7. hanging the aircraft; 8. left and right upper deformation frames; 9. obliquely lifting the deformation frame; 10. front and back upper deformation frames; 11. an inclined side plate; 12. a left and a right side plate; 13. an upper cover plate; 14. front and rear side plates; 15. a central fixing frame; 16. left and right upper deformable frames; 17. left and right lower deformable frames; 18. a diagonally lower deformed frame; 19. obliquely upward deforming the frame; 20. a front-back lower deformed frame; 21. a front and rear upper deformable frame; 22. a wire rope; 23. a foamed aluminum shock absorbing frame; 24. a side fixing frame a; 25. a control system; 26. a power supply system; 27. a side fixing frame b; 28. a rope drive system; 29. a hinge lug c; 30. a hinged ear plate c; 31. a hinge lug a; 32. a hinged ear plate a; 33. a fixing plate; 34. a hinged lug b; 35. hinging the ear plate b; 36. a hook; 37. a pin shaft and a sliding bearing; 38. a lower cover plate; 39. an electrical load compartment frame; 40. left and right lower deformation frames; 41. obliquely downward deforming frames; 42. and a front and back lower deformation frame.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
Example 1
The embodiment of the invention relates to a recoverable deformable launch pod, which is shown in figures 1, 2, 3, 8 and 9 and comprises eight parts, namely an electric load cabin 1, an upper deformation frame 2, a shape-following fixed frame 3, a bottom frame 4, a lower deformation frame 5, a synchronous shock absorber 6, a hanging aircraft 7 and a rope driving system 28. 16 hinge lugs c29 are installed on the electric load compartment 1, 16 hinge lug plates c30 of 8 upper deformation frames 2 are hinged and installed on the 16 hinge lugs c29 on the electric load compartment 1 through pin shafts and sliding bearings 37, 16 hinge lug plates a32 of 8 lower deformation frames 5 are hinged and installed on 16 hinge lugs a31 of 8 upper deformation frames 2 through pin shafts and sliding bearings 37, and the hinge lug plates a32 and the hinge lugs a31 are connected through fixing plates 33; 16 hinged ear plates b35 of the bottom frame 4 are hinged and installed on 16 hinged support ears b34 of 8 lower deformation frames 5 through a pin shaft and a sliding bearing 37, a hanging aircraft 7 is hung on a lifting hook 36 of the electric load cabin 1, a conformal fixing frame 3 is fixed at the bottom of the electric load cabin 1 through a central fixing frame 15, a side fixing frame a24 and a side fixing frame b27, the hanging aircraft 7 is located in a conformal supporting hole of the conformal fixing frame 3 so as to ensure that the hanging state of the aircraft cannot shake or collide, the launching state can be emitted linearly along the deformation direction of the nacelle, 4 synchronous dampers 6 are installed at corresponding positions at the bottom of the electric load cabin 1 to play a landing buffering role, a rope driving system 28 is installed in the electric load cabin, four steel wire ropes 22 of the rope driving system 28 are guided into the synchronous dampers 6 through a plurality of fixed pulleys and are fixed at corresponding positions of the bottom frame 4, the four steel wire ropes 22 are retracted, the switching of nacelle deformation, the nacelle launching, the nacelle deformation, the hanging attitude, the launching attitude and the recovery attitude of the 4 synchronous dampers is realized, the bottom frame is synchronously deformed, the same damping effect is constantly kept, and the same damping effect is ensured when the nacelle is landed.
In another embodiment of the present invention, as shown in fig. 5, 6, 7, and 9, the electrical load compartment 1 is composed of an electrical load compartment frame 39, a hinged lug c29, an upper cover plate 13, a lower cover plate 38, a front and rear side plate 1, a left and right side plate 12, an inclined side plate 11, a rope driving system 28, a power supply system 26, a control system 25, and the like, wherein the electrical load compartment frame 39 is a multi-tube welded frame structure, and 1 rope driving system 28, 1 power supply system 26, 1 control system 25, and the like are installed inside the electrical load compartment frame, and 1 upper cover plate 13, 1 lower cover plate 38, 2 front and rear side plates 14, 2 left and right side plates 12, 4 inclined side plates 11, and 16 hinged lugs c29 are covered outside the electrical load compartment frame and fixed at corresponding positions at the bottom of the electrical load compartment 1. The installation of the rope drive system 28, the power supply system 26, the control system 25, and the towing of the towed aircraft 7, as well as the flexible frame articulated towing, is accomplished by the electrical load compartment 1.
In still another embodiment of the present invention, as shown in fig. 4, 5, 7, 10, 11 and 12, the nacelle transformation frame is composed of an upper transformation frame 2 and a lower transformation frame 5, wherein the upper transformation frame 2 is composed of 2 left and right upper transformation frames 8, 2 front and rear upper transformation frames 10 and 4 inclined upper transformation frames 9, and the lower transformation frame 5 is composed of 2 left and right lower transformation frames 40, 2 front and rear lower transformation frames 42 and 4 inclined lower transformation frames 41. 16 hinged lug plates c30 of the upper deformation frame 2 are hinged on 16 hinged lugs c29 on the electric load cabin 1 through a pin shaft and a sliding bearing 37, 16 hinged lug plates a32 of the lower deformation frame 5 are hinged on 16 hinged lugs a31 of the upper deformation frame 2 through a pin shaft and a sliding bearing 37, the hinged lug plates a32 and the hinged lugs a31 are connected through a fixing plate 33, 16 hinged lug plates b35 of the bottom frame 4 are hinged on 16 hinged lugs b34 of the lower deformation frame 5 through a pin shaft and a sliding bearing 37, a deformation system of the pod is formed together, and the transformation of the pod is achieved, and the switching of the pod launching posture, the pod hanging posture, the pod launching posture and the pod recovering posture is achieved. The left upper deformation frame 8 and the right upper deformation frame 8 are composed of 1 left upper deformation frame 16, a right upper deformation frame 16, 2 hinge lug plates c30, 2 hinge lugs a31 and 1 hiding cover plate, wherein the 2 hinge lug plates c30 are fixed at the top of the left upper deformation frame 16 and the right upper deformation frame 16, the 2 hinge lugs a31 are fixed at the bottom of the left upper deformation frame 16 and the right upper deformation frame 16, the hiding cover plate is fixed at the outer sides of the left upper deformation frame 16 and the right upper deformation frame 16, the left upper deformation frame 16 and the right upper deformation frame 16 are of a multi-square pipe welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and one inclined beam is welded inside the trapezoid; the front and rear upper deformation frames 10 are composed of 1 front and rear upper deformation frame 21, 2 hinged ear plates c30, 2 hinged lugs a31 and 1 hiding cover plate, wherein the 2 hinged ear plates c30 are fixed at the top of the front and rear upper deformation frame 21, the 2 hinged lugs a31 are fixed at the bottom of the front and rear upper deformation frame 21, the hiding cover plate is fixed at the outer side of the front and rear upper deformation frame 21, the front and rear upper deformation frame 21 is of a multi-side pipe welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and two oblique beams are welded inside the trapezoid to form a cross posture; the inclined upper deformation frame 9 consists of 1 inclined upper deformation frame 19, 2 hinge lug plates c30, 2 hinge lugs a31 and 1 hiding cover plate, wherein the 2 hinge lug plates c30 are fixed at the top of the inclined upper deformation frame 19, the 2 hinge lugs a31 are fixed at the bottom of the inclined upper deformation frame 19, the hiding cover plate is fixed at the outer side of the inclined upper deformation frame 19, the inclined upper deformation frame 19 is of a multi-square-tube welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and one inclined beam is welded inside the trapezoid; the left and right lower deformation frames 40 are composed of 1 left and right lower deformation frame 17, 2 hinged lug plates a32, 2 hinged lugs b34 and 1 stealth cover plate, wherein the 2 hinged lugs b34 are fixed at the top of the left and right lower deformation frame 17, the 2 hinged lugs b34 are fixed at the bottom of the left and right lower deformation frame 17, the stealth cover plate is fixed at the outer side of the left and right lower deformation frame 17, the left and right lower deformation frame 17 is of a multi-side pipe welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and one oblique beam is welded inside the trapezoid; the front and rear lower deformation frame 42 is composed of 1 front and rear lower deformation frame 20, 2 hinge lug plates a32, 2 hinge lugs b34 and 1 stealth cover plate, wherein the 2 hinge lugs b34 are fixed at the top of the front and rear lower deformation frame 20, the 2 hinge lugs b34 are fixed at the bottom of the front and rear lower deformation frame 20, the stealth cover plate is fixed at the outer side of the front and rear lower deformation frame 20, the front and rear lower deformation frame 20 is of a multi-square-tube welded isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and two inclined beams are welded inside the trapezoid and are in a cross posture; the inclined lower deformation frame 41 is composed of 1 inclined lower deformation frame 18, 2 hinged lug plates a32, 2 hinged lugs b34 and 1 invisible covering plate, wherein the 2 hinged lugs b34 are fixed at the top of the inclined lower deformation frame 18, the 2 hinged lugs b34 are fixed at the bottom of the inclined lower deformation frame 18, the invisible covering plate is fixed at the outer side of the inclined lower deformation frame 18, the inclined lower deformation frame 18 is of a multi-square-tube welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and one inclined beam is welded inside the trapezoid. The 16 deformation frames are respectively hinged to corresponding hinged points of the electric load cabin 1 and the bottom frame 4 and are mutually hinged to form a lantern-like deformation cabin body structure, so that the deformation of the machine body is realized, the deformation guarantee is provided for the switching of the hanging posture, the launching posture and the recovery posture, and the integration of functions of floating flight hanging, near-air launching and launching, safe buffer landing, stealth shielding, repeated repeatability and repeated recovery and launching and the like is realized.
In another embodiment of the present invention, as shown in fig. 2, 8 and 12, the bottom frame 4 is composed of a bottom frame 43, a foamed aluminum shock absorbing frame 23 and hinge ear plates b35, wherein the foamed aluminum shock absorbing frame 23 is fixed on the bottom frame 43, 16 hinge ear plates b35 are fixed at corresponding positions of the bottom frame 43 to form the bottom frame 4, and the bottom frame 4 is an octagonal hollow frame containing foamed aluminum buffer material. The bottom frame 4 provides lower support for pod body deformation and provides ground impact supporting force for pod buffering landing, and the foamed aluminum shock absorption frame 23 has buffering and shock absorption performance.
In another embodiment of the present invention, as shown in fig. 1, 10, 11 and 12, the pod is in a hanging posture, the angle of the upper and lower deformation frames in the hanging posture is 155 degrees, the limit position of the lower limit position of the hanging posture is a flexible contact limit between the stealth covering plates, the rigid limit of the hinge lug c29 and the hinge lug c30, the rigid limit of the hinge lug a31 and the hinge lug a32, and the rigid limit of the hinge lug b34 and the hinge lug b35 ensure that the frame does not drop down in the hanging posture of the pod.
In another embodiment of the present invention, as shown in fig. 3, 4, 5, 6 and 7, the pod is in a launching attitude, in which the angle of the upper and lower deformation frames is about 30 degrees, the reference position is the mutual contact position of the synchronous damper 6 and the bottom frame 4, and the attitude position is not mandatory, and the synchronous damper 6 and the bottom frame 4 need to be in mutual contact, so as to ensure that the steel wire rope 22 does not expose inside the pod during launching, and ensure the launching safety.
According to another embodiment of the invention, as shown in fig. 3, 4, 5, 6 and 7, the nacelle is in a recovery attitude, the angle of the upper and lower deformation frames in the recovery attitude is about 30 degrees, the reference position is the mutual contact position of the synchronous damper 6 and the bottom frame 4, the attitude position has no mandatory requirement, the synchronous damper 6 and the bottom frame 4 are required to be in mutual contact, so as to ensure that the steel wire rope 22 is not exposed in the nacelle during recovery, and the recovery safety is ensured; secondly, when the nacelle is in contact with the ground, the angle of the upper and lower deformation frames of the nacelle varies between 15 degrees and 30 degrees due to the compression of the synchronous damper 6, and the angle range depends on the elastic forming range of the synchronous damper 6. The 4 synchronous dampers 6 synchronously deform to keep the same damping effect all the time, so that the landing damping effect of the nacelle during landing is ensured, meanwhile, the deformation of the nacelle greatly reduces the gravity center of the whole machine, improves the grounding area of the whole machine, and improves the landing safety and the overturning resistance.
The significance of pod deformation is:
1. the integration of functions such as pod floating flight hanging, near-air launching, safe buffer landing, stealth shielding, repeatable repeated recovery and launching and the like is realized.
2. Under the hanging posture of the aircraft, the aircraft is hung in a multi-diamond cabin body, foam is arranged along with a shape fixing frame to limit the swing of the aircraft, stealth materials are arranged outside the cabin body to realize the whole-body shielding of the aircraft, the stealth shielding of a nacelle is realized, and the safe hanging and swing inhibition of the aircraft in the hanging process are realized;
3. under the launching posture of the aircraft, the front middle part of the aircraft is exposed out of the nacelle, the rear part of the aircraft is limited in the foam conformal fixing frame, after the hanging rope is cut by the hot knife, the aircraft can be launched linearly along the deformation direction of the nacelle and cannot collide with the nacelle for launching, and meanwhile, the flexible steel cable in the nacelle is also limited in the synchronous shock absorber, so that launching cannot be influenced by vibration of the steel cable, and launching safety is ensured;
4. under the recovery state of the aircraft, the comprehensive action of the shock absorption systems such as foamed aluminum shock absorption materials of a pod bottom frame, synchronous shock absorbers, flexible conformal fixing frames, flexible machine body frames and electric cabin foam boards is realized, the safe landing and the repeatability recycling of the pod are realized, it is worth mentioning that the four synchronous shock absorbers are adopted as main shock absorbers, due to the special pod deformation frame structure, the deformation and the shock absorption force are synchronously changed, when the pod obliquely lands, the shock absorbers can simultaneously and synchronously provide shock absorption at each moment, the landing buffering performance of the pod is greatly improved, meanwhile, the center of the pod descends under the attitude, the landing area is increased, and the anti-overturning performance of the pod during landing is improved.
The above description is not meant to be limiting, it being noted that: it will be apparent to those skilled in the art that various changes, modifications, additions and substitutions can be made without departing from the true scope of the invention, and these improvements and modifications should also be construed as within the scope of the invention.
Claims (6)
1. The recoverable deformable launch pod is characterized by comprising an electric load cabin (1), a pod deformation frame, a conformal fixed frame (3), a bottom frame (4), a synchronous shock absorber (6), a hanging aircraft (7) and a rope driving system (28), wherein the hanging aircraft (7) is hung on a lifting hook (36) of the electric load cabin (1), the conformal fixed frame (3) is fixed at the bottom of the electric load cabin (1) through a central fixed frame (15), a side fixed frame a (24) and a side fixed frame b (27), the hanging aircraft (7) is arranged in conformal supporting holes of the conformal fixed frame (3), the synchronous shock absorber (6) is arranged at the corresponding position of the bottom of the electric load cabin (1), the rope driving system (28) is arranged in the electric load cabin (1), four steel wire ropes (22) of the rope driving system (28) are guided into the synchronous shock absorber (6) through a plurality of fixed pulleys and are fixed at the corresponding positions of the bottom frame (4), and the bottom frame (4) is stored and released through the steel wire ropes (22);
the nacelle deformation frame is composed of an upper deformation frame (2) and a lower deformation frame (5), the upper deformation frame (2) is hinged on the electric load cabin (1), and the lower deformation frame (5) is hinged on the upper deformation frame (2);
the pod is in a hanging posture, the angle between an upper deformation frame (2) and a lower deformation frame (5) in the hanging posture is set to be 155 degrees, the limit position is the limit position under the posture, the limit position is limited by flexible contact between the stealth covering plates, a hinge lug c (29) and a hinge lug plate c (30) are limited rigidly, a hinge lug a (31) and a hinge lug plate a (32) are limited rigidly, and a hinge lug b (34) and a hinge lug plate b (35) are limited rigidly in a mixed limit mode, and the frame falling state can not occur under the hanging posture of the pod;
the pod is in a launching attitude, the angle of an upper deformation frame (2) and a lower deformation frame (5) in the attitude is set to be about 30 degrees, the reference position of the pod is the mutual contact position of a synchronous damper (6) and a bottom frame (4), the synchronous damper (6) and the bottom frame (4) are mutually contacted, and a steel wire rope (22) is not exposed in the pod during launching;
the nacelle is in a recovery posture, the upper deformation frame (2) and the lower deformation frame (5) are arranged at about 30 degrees in the recovery posture, the reference position of the nacelle is the mutual contact position of the synchronous damper (6) and the bottom frame (4), the synchronous damper (6) and the bottom frame (4) are in mutual contact, and the steel wire rope cannot be exposed in the nacelle during recovery control; secondly, when the nacelle is in contact with the ground, the angle of the vertical deformation frame of the nacelle is set to be changed between 15 degrees and 30 degrees through compression of the synchronous shock absorber (6), and the angle range of the vertical deformation frame depends on the elastic forming range of the synchronous shock absorber (6).
2. The recoverable and deformable pod for launching as claimed in claim 1, wherein the electrical load compartment (1) comprises an electrical load compartment frame (39), the electrical load compartment frame (39) is configured as a multi-tube welded frame structure, a rope driving system (28), a power supply system (26) and a control system (25) are mounted in the electrical load compartment frame, an upper cover plate (13), a lower cover plate (38), a front side plate (14), a rear side plate (14), a left side plate (12), a right side plate (12) and a slanting side plate (11) are sequentially covered and arranged outside the electrical load compartment frame, and the electrical load compartment frame (39) is fixed at a corresponding position at the bottom of the electrical load compartment (1) through a hinge lug c (29).
3. The recoverable and deformable style pod of claim 1, wherein the upper deformation frame (2) comprises left and right upper deformation frames (8), front and rear upper deformation frames (10), and a slanted upper deformation frame (9); the lower deformation frame (5) comprises a left lower deformation frame (40), a right lower deformation frame (40), a front lower deformation frame (42), a rear lower deformation frame (42) and an inclined lower deformation frame (41); the bottom frame (4) is hinged to the lower deformation frame (5), a deformation system of the pod is formed together, and the transformation of the launch pod and the switching of the hanging posture, the launching posture and the recovery posture are achieved.
4. A recyclable deformable pod according to claim 3, characterized in that the left and right upper deformable frames (8) comprise left and right upper deformable frames (16), the left and right upper deformable frames (16) are arranged in a multi-square pipe welded isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and one oblique beam is welded inside the trapezoid;
the front upper deformation frame and the rear upper deformation frame (10) comprise front upper deformation frames and rear upper deformation frames (21), the front upper deformation frames and the rear upper deformation frames (21) are arranged into a multi-square-tube welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is set to be 85 degrees, and two oblique beams are welded inside the trapezoid and are in a cross posture;
go up to one side and warp frame (9) including going up to one side and warp frame (19), go up to one side and warp frame (19) and set up to many square tube welding isosceles trapezoid structure, isosceles trapezoid structure angle sets up to 85 degrees, and trapezoidal internal weld has an oblique beam.
5. The recyclable deformable pod as claimed in claim 3, wherein the left and right lower deformable frames (40) comprise left and right lower deformable frames (17), the left and right lower deformable frames (17) are arranged in a multi-square pipe welded isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and one oblique beam is welded inside the trapezoid;
the front and rear lower deformation frames (42) comprise front and rear lower deformation frames (20), the front and rear lower deformation frames (20) are arranged into a multi-square pipe welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is set to be 85 degrees, and two oblique beams are welded in the trapezoid and are in a cross posture;
the inclined lower deformation frame (41) comprises an inclined lower deformation frame (18), the inclined lower deformation frame (18) is of a multi-square pipe welding isosceles trapezoid structure, the angle of the isosceles trapezoid structure is 85 degrees, and an inclined beam is welded inside the trapezoid.
6. A recoverable and deformable pod according to claim 1, wherein the base frame (4) comprises a base frame (43), a foamed aluminium shock absorbing frame (23), and a hinged ear plate b (35), wherein the foamed aluminium shock absorbing frame (23) is fixed on the base frame (43), the hinged ear plate b (35) is fixed at a corresponding position on the base frame (43) to form the base frame (4), and the base frame (4) is an octagonal hollow frame containing foamed aluminium buffer material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202011536840.1A CN112623179B (en) | 2020-12-23 | 2020-12-23 | Recoverable flexible formula transmission nacelle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011536840.1A CN112623179B (en) | 2020-12-23 | 2020-12-23 | Recoverable flexible formula transmission nacelle |
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| CN112623179A CN112623179A (en) | 2021-04-09 |
| CN112623179B true CN112623179B (en) | 2022-11-22 |
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| CN113264187B (en) * | 2021-06-11 | 2022-08-09 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Design method and device of buffer driving device for air-drop soft landing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR3037316A1 (en) * | 2015-06-12 | 2016-12-16 | Airborne Concept | FLYING DEVICE WITHOUT AERO-LARGABLE PILOT |
| CN104960657B (en) * | 2015-07-23 | 2017-03-08 | 北京天航华创科技股份有限公司 | A kind of combination separate type stratosphere flight device system |
| CN105416557B (en) * | 2015-11-13 | 2017-10-27 | 中国人民解放军国防科学技术大学 | A kind of high altitude balloon carrying and the system and method for letting Helios fly away |
| CN105439021B (en) * | 2015-12-08 | 2017-08-15 | 浙江理工大学 | Many suspension centre winding of single layer hoist engines with angle pulley |
| CN106516168B (en) * | 2016-09-23 | 2019-01-29 | 北京空间技术研制试验中心 | A kind of full protection flexibility expansion re-entry deceleration device |
| CN109502002B (en) * | 2018-11-13 | 2023-09-08 | 中国科学院光电研究院 | Carbon fiber composite heavy-load nacelle frame and connecting method |
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