A mars surface take-off deployment device for a quadcopter mars flyer

Abstract

The present application relates to a kind of four-rotor Mars aircraft's Mars surface take-off deployment device, belong to spaceflight Mars rotor aircraft technical field.Solve the problem of aircraft Mars surface take-off deployment, including envelope top plate, side plate locking assembly, envelope side plate, support platform, locking assembly, envelope bottom plate and lander, lander is provided with envelope bottom plate, the middle part of envelope bottom plate is provided with locking assembly and support platform, the edge of envelope bottom plate is connected with envelope side plate by side plate locking assembly, side plate locking assembly is connected with locking assembly, the upper portion of support platform is provided with lander, the upper portion of lander is provided with envelope top plate, envelope side plate and envelope top plate establish cooperation, Mars aircraft is placed on support platform.The present application needs few fixed unlocking points, locking state is stable, structure is simple and does not need to drag cable, and it has important significance to Mars aircraft's Mars surface take-off deployment etc..

Description

TECHNICAL FIELD

[0001] The present application relates to a kind of ground surface take-off deployment device, belong to aerospace Mars rotorcraft technical field. BACKGROUND

[0002] The overall Mars ground is sand dune, and is interspersed with gravel of different sizes, which greatly limits and affects the exploration range and efficiency of the Mars rover. The Mars aircraft can fly in the air and is not limited by the terrain, can cross the canyon, mountain and steep slope on the surface of Mars, and can more widely explore the surface of Mars than the Mars rover, and the exploration efficiency is higher. Today, the feasibility of Mars rotorcraft has been verified, which provides more possibilities for Mars exploration.

[0003] The four-rotor Mars aircraft is simple to operate and stable in structure, but the overall structure is not compact. To meet the launch requirements of the spacecraft, the Mars aircraft needs to be folded and deployed. To improve the reliability and safety of the aircraft take-off deployment, the Mars ground surface take-off deployment is used. However, there is no suitable Mars ground surface take-off deployment device for the existing folding and take-off deployment scheme of the four-rotor Mars aircraft.

[0004] Therefore, it is urgent to provide a Mars ground surface take-off deployment device for a four-rotor Mars aircraft to solve the above technical problems. SUMMARY

[0005] The present application provides a Mars ground surface take-off deployment device for a four-rotor Mars aircraft to solve the above technical problems.

[0006] Technical scheme of the present application:

[0007] A Mars ground surface take-off deployment device for a four-rotor Mars aircraft includes an envelope top plate, a side plate locking assembly, an envelope side plate, a support table, a locking assembly, an envelope bottom plate and a lander. The lander is provided with the envelope bottom plate, the middle part of the envelope bottom plate is provided with the locking assembly and the support table, the edge of the envelope bottom plate is connected with the envelope side plate through the side plate locking assembly, the side plate locking assembly is connected with the locking assembly, the upper part of the support table is provided with the lander, the upper part of the lander is provided with the envelope top plate, the envelope side plate cooperates with the envelope top plate, and the Mars aircraft is placed on the support table.

[0008] Preferably, the side plate locking assembly comprises a rotating assembly, a tension adjusting assembly, a lock piece and a steel rope, the middle part of the steel rope is provided with the tension adjusting assembly, one end of the steel rope is provided with the lock piece, the other end of the steel rope is provided with the locking assembly, and the envelope bottom plate is connected with the envelope side plate through the rotating assembly.

[0009] Preferably, the rotating assembly comprises a first side plate rotating shaft, a first torsional spring, a first lock holder, a pin shaft, a first cylindrical spring, a second lock holder, a steel rubber and a second side plate rotating shaft, the first side plate rotating shaft is connected with the envelope bottom plate, the first side plate rotating shaft is rotationally connected with the lower end of the envelope side plate, the first torsional spring is sleeved on the first side plate rotating shaft, and the two ends of the first torsional spring are tightly pressed against the envelope bottom plate and the envelope side plate respectively.

[0010] The first lock holder is connected with the envelope bottom plate, the steel rubber is arranged on the first lock holder, the first lock holder is connected with the second lock holder through the second side plate rotating shaft, the first lock holder is processed with an inner cavity, the first cylindrical spring is arranged in the inner cavity of the first lock holder, the end of the first cylindrical spring is provided with the pin shaft, and the pin shaft is matched with the positioning hole of the first lock holder.

[0011] Preferably, the tension adjusting assembly comprises a first tension piece, a disc spring, a second tension piece and a third tension piece, the second tension piece is slidably arranged in the inner cavity of the first tension piece, the inner wall of the first tension piece is provided with a thread, the third tension piece is threadedly connected with the first tension piece, the disc spring is arranged between the second tension piece and the third tension piece, one end of the second tension piece extends out through the third tension piece, and the first tension piece, the second tension piece and the steel rope are connected.

[0012] Preferably, the lock piece comprises a square sliding sleeve, a lock sliding pin, a second cylindrical spring, a round sliding sleeve and a steel rope positioning column, the square sliding sleeve and the round sliding sleeve are sequentially arranged on the upper end of the envelope side plate, the edge of the envelope top plate is provided with a buckle, the upper and lower sides of the lock sliding pin are slidably connected with the square sliding sleeve and the round sliding sleeve respectively, the middle part of the lock sliding pin is matched with the envelope top plate, the lower end of the lock sliding pin is connected with one end of the steel rope, the second cylindrical spring is sleeved on the lower side of the lock sliding pin, and the two ends of the second cylindrical spring tightly press against the middle part of the round sliding sleeve and the lock sliding pin, and the steel rope passes through the steel rope positioning column fixed on the envelope side plate.

[0013] Preferably: the locking assembly comprises an anti-loose cap, a locking nut, a loading nut, a spherical pad, a first heat insulation pad, a breakaway, a breakaway shell, a butt flange, a third cylindrical spring, a spring holder, a fixing frame, a spring pressing piece, a hollow shaft, a fourth cylindrical spring, a dustproof film, a second spring sleeve, a first spring sleeve, a fifth cylindrical spring, a second heat insulation pad and a slotted titanium rod, the breakaway shell is connected with the lander, the upper end of the breakaway shell is connected with the second spring sleeve, the second spring sleeve is located in the through hole of the lander, the first spring sleeve is in sliding connection with the second spring sleeve, the breakaway shell is sequentially provided from top to bottom with the second heat insulation pad, the breakaway, the first heat insulation pad and the spherical pad, the slotted titanium rod sequentially passes through the first spring sleeve, the upper end through hole of the breakaway shell, the second heat insulation pad, the breakaway, the first heat insulation pad and the spherical pad, the lower end of the slotted titanium rod is in threaded connection with the loading nut and the locking nut in sequence, the lower end of the breakaway shell is connected with the anti-loose cap, the loading nut and the locking nut are located inside the anti-loose cap, the first spring sleeve is provided with the fifth cylindrical spring, the fifth cylindrical spring is sleeved on the slotted titanium rod, and the two ends of the fifth cylindrical spring are in abutment with the breakaway shell and the first spring sleeve respectively.

[0014] The fixing frame is connected with the envelope bottom plate, the fixing frame is connected with the spring holder, the spring holder is in sliding connection with the spring pressing piece, and the third cylindrical spring is arranged between the spring holder and the spring pressing piece, the third cylindrical spring is in a compressed state, the spring pressing piece presses the lower part of the spring holder, the spring pressing piece and the spring holder clamp the other end of the steel cable, the lower end of the spring pressing piece passes through the envelope bottom plate and is connected with the butt flange, the butt flange and the envelope bottom plate have a gap, and the dustproof film is connected with the butt flange and the envelope bottom plate.

[0015] The hollow shaft is slidably arranged in the spring pressing piece, the inner wall of the spring pressing piece is processed with a baffle, the lower part of the hollow shaft passes through the baffle and is connected with the upper end of the slotted titanium rod, and the fourth cylindrical spring is arranged between the upper part of the hollow shaft and the baffle, the fourth cylindrical spring is sleeved on the hollow shaft, and the two ends of the fourth cylindrical spring are in abutment with the hollow shaft and the baffle respectively.

[0016] Preferably: the part of the slotted titanium rod arranged in the breakaway is processed with a notch.

[0017] Preferably: the envelope top plate is provided with an outwardly extending conical column, the upper end of the Mars spacecraft is provided with a groove, and the outwardly extending conical column of the envelope top plate is correspondingly arranged with the groove.

[0018] Preferably: the positioning assembly comprises a first ball head, a first ball socket and a guide column, the lower end of the Mars spacecraft is provided with the first ball head, the upper end of the support table is provided with the first ball socket, the first ball head is correspondingly arranged with the first ball socket, the support table is provided with a guide cylinder, and the lower end of the Mars spacecraft is provided with the guide column, the guide column is correspondingly arranged with the guide cylinder.

[0019] Preferably, the positioning assembly comprises a second ball head and a second ball socket, the lower side of the envelope base plate is provided with the second ball head, the upper side of the lander is provided with the second ball socket, and the second ball head is arranged correspondingly with the second ball socket.

[0020] The present application has the following beneficial effects:

[0021] The present application has the following beneficial effects: BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a perspective view of a Mars surface take-off deployment device of a four-rotor Mars aircraft.

[0023] Figure 2 It is a partial perspective view of a Mars surface take-off deployment device of a four-rotor Mars aircraft.

[0024] Figure 3 It is Figure 2 the enlarged view at A in FIG.

[0025] Figure 4 It is Figure 2 the enlarged view at B in FIG.

[0026] Figure 5 It is Figure 2 the structural schematic view at C in FIG.

[0027] Figure 6 It is Figure 1 the enlarged view at G in FIG.

[0028] Figure 7 It is a structural schematic view of the locking assembly.

[0029] Figure 8 It is a structural schematic view of the Mars aircraft.

[0030] Figure 9 It is a front view of a Mars surface take-off deployment device of a four-rotor Mars aircraft.

[0031] Figure 10 It is Figure 9 the enlarged view at D in FIG.

[0032] Figure 11 It is Figure 9 the enlarged view at E in FIG.

[0033] Figure 12 It is Figure 9 the enlarged view at F in FIG.

[0034] Figure 13 It is a deployment process diagram.

[0035] Figure: 1 - Envelope top plate, 2 - Positioning assembly, 3 - Side plate locking assembly, 4 - Envelope side plate, 5 - Support platform, 6 - Locking assembly, 7 - Envelope bottom plate, 8 - Landing pad, 9 - Mars flight vehicle, 2-1 - First ball head, 2-2 - First ball socket, 2-3 - Guide column, 2-4 - Second ball head, 2-5 - Second ball socket, 3-1 - First side plate rotating shaft, 3-2 - First torsional spring, 3-3 - First lock holder, 3-4 - Pin shaft, 3-5 - First cylindrical spring, 3-6 - Second lock holder, 3-7 - Steel rubber, 3-8 - Second side plate rotating shaft, 3-9 - Square sliding sleeve, 3-10 - Lock sliding pin, 3-11 - Second cylindrical spring, 3-12 - Round sliding sleeve, 3-13 - Steel rope, 3-14 - Steel rope positioning column, 3-15 - First tensioning piece, 3-16 - Disc spring, 3-17 - Second tensioning piece, 3-18 - Third tensioning piece, 6-1 - Anti - falling cap, 6-2 - Lock nut, 6-3 - Loading nut, 6-4 - Ball -type pad, 6-5 - First heat insulation pad, 6-6 - Expander, 6-7 - Expander shell, 6-8 - Butt flange, 6-9 - Third cylindrical spring, 6-10 - Spring holder, 6-11 - Fixed frame, 6-12 - Spring pressing piece, 6-13 - Hollow shaft, 6-14 - Fourth cylindrical spring, 6-15 - Dustproof film, 6-16 - Second spring sleeve, 6-17 - First spring sleeve, 6-18 - Fifth cylindrical spring, 6-19 - Second heat insulation pad, 6-20 - Grooved titanium rod. DETAILED DESCRIPTION

[0036] In order to make the objectives, technical solutions and advantages of the present application clearer, the present application will be described below in conjunction with specific embodiments shown in the drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present application. In addition, in the following description, the description of known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present application.

[0037] Specific embodiment one: combination Figures 1-13The present embodiment is a Mars surface take-off deployment device for a four-rotor Mars aircraft, which comprises an envelope top plate 1, a side plate locking assembly 3, an envelope side plate 4, a support table 5, a locking assembly 6, an envelope bottom plate 7, and a lander 8. The lander 8 is provided with the envelope bottom plate 7, the middle part of the envelope bottom plate 7 is provided with the locking assembly 6 and the support table 5, the edge of the envelope bottom plate 7 is connected with the envelope side plate 4 through the side plate locking assembly 3, the side plate locking assembly 3 is connected with the locking assembly 6, the upper part of the support table 5 is provided with the lander 8, the upper part of the lander 8 is provided with the envelope top plate 1, the envelope side plate 4 cooperates with the envelope top plate 1, the Mars aircraft 9 is placed on the support table 5, the Mars aircraft 9 is located inside the envelope, the envelope top plate 1 and the envelope bottom plate 7 are square, four envelope side plates 4 are respectively arranged on the four edges of the envelope bottom plate 7, and the four envelope side plates 4, the envelope top plate 1 arranged at the two ends thereof, and the envelope bottom plate 7 form an envelope.

[0038] Specific implementation method two: in combination Figures 1-13 The present embodiment is a Mars surface take-off deployment device for a four-rotor Mars aircraft, which comprises an envelope top plate 1, a side plate locking assembly 3, an envelope side plate 4, a support table 5, a locking assembly 6, an envelope bottom plate 7, and a lander 8. The lander 8 is provided with the envelope bottom plate 7, the middle part of the envelope bottom plate 7 is provided with the locking assembly 6 and the support table 5, the edge of the envelope bottom plate 7 is connected with the envelope side plate 4 through the side plate locking assembly 3, the side plate locking assembly 3 is connected with the locking assembly 6, the upper part of the support table 5 is provided with the lander 8, the upper part of the lander 8 is provided with the envelope top plate 1, the envelope side plate 4 cooperates with the envelope top plate 1, the Mars aircraft 9 is placed on the support table 5, the Mars aircraft 9 is located inside the envelope, the envelope top plate 1 and the envelope bottom plate 7 are square, four envelope side plates 4 are respectively arranged on the four edges of the envelope bottom plate 7, and the four envelope side plates 4, the envelope top plate 1 arranged at the two ends thereof, and the envelope bottom plate 7 form an envelope.

[0039] Specific implementation method three: in combination Figures 1-13 The present embodiment is a Mars surface take-off deployment device for a four-rotor Mars aircraft, which comprises an envelope top plate 1, a side plate locking assembly 3, an envelope side plate 4, a support table 5, a locking assembly 6, an envelope bottom plate 7, and a lander 8. The lander 8 is provided with the envelope bottom plate 7, the middle part of the envelope bottom plate 7 is provided with the locking assembly 6 and the support table 5, the edge of the envelope bottom plate 7 is connected with the envelope side plate 4 through the side plate locking assembly 3, the side plate locking assembly 3 is connected with the locking assembly 6, the upper part of the support table 5 is provided with the lander 8, the upper part of the lander 8 is provided with the envelope top plate 1, the envelope side plate 4 cooperates with the envelope top plate 1, the Mars aircraft 9 is placed on the support table 5, the Mars aircraft 9 is located inside the envelope, the envelope top plate 1 and the envelope bottom plate 7 are square, four envelope side plates 4 are respectively arranged on the four edges of the envelope bottom plate 7, and the four envelope side plates 4, the envelope top plate 1 arranged at the two ends thereof, and the envelope bottom plate 7 form an envelope.

[0040] The bottom surface of the first lock frame 3-3 is fixedly connected with the bottom plate 7 of the envelope body, a steel rubber 3-7 is arranged on the vertical surface of the first lock frame 3-3, the first lock frame 3-3 is connected with the second lock frame 3-6 through a second side plate rotating shaft 3-8, an inner cavity is processed on the first lock frame 3-3, a first cylindrical spring 3-5 is arranged in the inner cavity of the first lock frame 3-3, a pin shaft 3-4 is arranged at the end of the first cylindrical spring 3-5, the first cylindrical spring 3-5 is in a compressed state, the second side plate rotating shaft 3-8 is coaxially arranged with the first side plate rotating shaft 3-1, and the pin shaft 3-4 cooperates with a positioning hole processed on the side surface of the first lock frame 3-3; at this time, the first cylindrical spring 3-5 is in a compressed state due to the constraint of the side plate (side surface) of the first lock frame 3-3, when the second lock frame 3-6 rotates 90° with the envelope body side plate 4, the two pin shafts 3-4 cooperate with the positioning hole under the action of the first cylindrical spring 3-5 to complete the locking of the envelope body side plate 4, prevent rebound, and the steel rubber 3-7 is used for buffering when the envelope body side plate 4 is unfolded.

[0041] Specific implementation four: combined Figures 1-13 In this embodiment, the tension adjusting assembly includes a first tensioning member 3-15, a disc spring 3-16, a second tensioning member 3-17 and a third tensioning member 3-18. The inner cavity of the first tensioning member 3-15 is slidably provided with the second tensioning member 3-17. The inner wall of the first tensioning member 3-15 is provided with threads. The third tensioning member 3-18 is threadedly connected with the first tensioning member 3-15. The disc spring 3-16 is arranged between the second tensioning member 3-17 and the third tensioning member 3-18. One end of the second tensioning member 3-17 extends through the third tensioning member 3-18. The first tensioning member 3-15, the second tensioning member 3-17 and the steel rope 3-13 are connected. The steel rope 3-13 includes a first section of steel rope and a second section of steel rope. The first tensioning member 3-15 is connected with the first section of steel rope. The extending end of the second tensioning member 3-17 is connected with the second section of steel rope, so that the first section of steel rope and the second section of steel rope are connected to form the steel rope 3-13. The third tensioning member 3-18 is rotated to change the cooperation length between the first tensioning member 3-15 and the third tensioning member 3-18, so as to change the compression state of the disc spring 3-16, change the stress of the first tensioning member 3-15, and realize the change of the tension of the steel rope 3-13.

[0042] Specific implementation five: combined Figures 1-13The locking piece includes a square sliding sleeve 3-9, a locking sliding pin 3-10, a second cylindrical spring 3-11, a round sliding sleeve 3-12, and a steel rope positioning column 3-14. The upper end of the envelope side plate 4 is sequentially provided with the square sliding sleeve 3-9 and the round sliding sleeve 3-12. The edge of the envelope top plate 1 has a buckle. The upper and lower sides of the locking sliding pin 3-10 are respectively in sliding connection with the square sliding sleeve 3-9 and the round sliding sleeve 3-12. The middle part of the locking sliding pin 3-10 is in cooperation with the envelope top plate 1. The lower end of the locking sliding pin 3-10 is connected with one end of a steel rope 3-13. The second cylindrical spring 3-11 is sleeved on the lower side of the locking sliding pin 3-10. The two ends of the second cylindrical spring 3-11 abut against the middle part of the locking sliding pin 3-10 and the round sliding sleeve 3-12. The middle part of the locking sliding pin 3-10 is a clamping block with an inclined surface. The buckle of the edge of the envelope top plate 1 has an inclined surface matched with the middle part of the locking sliding pin 3-10. The two inclined surfaces are in contact and are pressed tightly. The steel rope 3-13 passes through the steel rope positioning column 3-14 fixed on the envelope side plate 4. Figure 6 The locking sliding pin 3-10 is subjected to the force downwardly applied by the steel rope 3-13, and the buckle shown in FIG. 6 is pressed tightly through the locking sliding pin 3-10, and the second cylindrical spring 3-11 is compressed. The steel rope 3-13 is connected with the envelope side plate 4 through the steel rope positioning column 3-14 and is fixed by the locking assembly 6.

[0043] Specific implementation six: combined with Figures 1-13To illustrate the embodiment, the Mars surface take-off deployment device of the four-rotor Mars flying vehicle in the embodiment comprises a locking assembly 6, which comprises an anti-dropping cap 6-1, a locking nut 6-2, a loading nut 6-3, a spherical pad 6-4, a first heat insulation pad 6-5, a rupturer 6-6, a rupturer shell 6-7, a docking flange 6-8, a third cylindrical spring 6-9, a spring holder 6-10, a fixing holder 6-11, a spring pressing piece 6-12, a hollow shaft 6-13, a fourth cylindrical spring 6-14, a dustproof film 6-15, a second spring sleeve 6-16, a first spring sleeve 6-17, a fifth cylindrical spring 6-18, a second heat insulation pad 6-19, and a slotted titanium rod 6-20. The rupturer shell 6-7 is fixedly connected with a lander 8. The upper end of the rupturer shell 6-7 is fixedly connected with the second spring sleeve 6-16. The second spring sleeve 6-16 is located in a through hole of the lander 8. The first spring sleeve 6-17 is located inside the second spring sleeve 6-16 and is in sliding connection with the second spring sleeve 6-16. The rupturer shell 6-7 sequentially has, from top to bottom, the second heat insulation pad 6-19, the rupturer 6-6, the first heat insulation pad 6-5, and the spherical pad 6-4. The slotted titanium rod 6-20 sequentially passes through the first spring sleeve 6-17, the upper end through hole of the rupturer shell 6-7, the second heat insulation pad 6-19, the rupturer 6-6, the first heat insulation pad 6-5, and the spherical pad 6-4. The lower end of the slotted titanium rod 6-20 is in threaded connection, in sequence, with the loading nut 6-3 and the locking nut 6-2. The loading nut 6-3 and the rupturer shell 6-7 top the components in the rupturer shell 6-7 against the inner wall on the upper side of the rupturer shell 6-7. The lower end of the rupturer shell 6-7 is fixedly connected with the anti-dropping cap 6-1. The loading nut 6-3 and the locking nut 6-2 are located inside the anti-dropping cap 6-1. The first spring sleeve 6-17 is provided with the fifth cylindrical spring 6-18, which is sleeved on the slotted titanium rod 6-20 and tightly presses the upper end face of the rupturer shell 6-7 and the inner wall on the upper side of the first spring sleeve 6-17 at both ends, for providing power for the first spring sleeve 6-17. Since the rupturer 6-6 is sensitive to temperature, the first heat insulation pad 6-5 and the second heat insulation pad 6-19 at both ends of the rupturer 6-6 are used for heat insulation, to reduce the influence of external temperature on the rupturer 6-6. The loading nut 6-3 transmits force to the rupturer 6-6 through the spherical pad 6-4. Changing the position of the loading nut 6-3 changes the pre-tightening force of the slotted titanium rod 6-20, to ensure that the rupturer 6-6 can generate enough force to cut off the titanium rod. The locking nut 6-2 is used to apply force to the loading nut 6-3, in a double-nut manner, for locking.The expansion breaker 6-6 is powered on, heated and expanded to cut off the slotted titanium rod 6-20, the anti-escape cap 6-1 is used to limit the position of the lower end of the slotted titanium rod 6-2 and the internal parts of the expansion breaker shell 6-7, preventing pollution to the environment, the upper end of the slotted titanium rod 6-20 and the hollow shaft 6-13 move upward under the action of the fourth cylindrical spring 6-14 and the fifth cylindrical spring 6-18, completing the separation of the envelope body and the lander 8, the fixing frame 6-11 is used to limit the position of the upper end of the slotted titanium rod 6-20 and the hollow shaft 6-13, preventing pollution to the environment;

[0044] The fixing frame 6-11 is fixedly connected with the envelope body bottom plate 7, the fixing frame 6-11 is fixedly connected with the upper part of the spring frame 6-10 through bolts, the spring frame 6-10 is slidably connected with the spring pressing piece 6-12, and the third cylindrical spring 6-9 is arranged between the spring frame 6-10 and the spring pressing piece 6-12, the third cylindrical spring 6-9 is in a compressed state, the spring pressing piece 6-12 presses the lower part of the spring frame 6-10, the spring pressing piece 6-12 clamps the other end of the steel wire 3-13 with the spring frame 6-10, the lower end of the spring pressing piece 6-12 passes through the envelope body bottom plate 7 and is connected with the butt flange 6-8 through bolts, the butt flange 6-8 and the envelope body bottom plate 7 have a gap, the dustproof film 6-15 is fixedly connected with the butt flange 6-8 and the envelope body bottom plate 7, and is used for plugging the gap to prevent dust from entering the inside of the envelope body; the upper end of the spring pressing piece 6-12 has four guide columns, the fixing frame 6-11 and the spring frame 6-10 corresponding to the guide columns are processed with sliding holes, the third cylindrical spring 6-9 is sleeved on the guide column, the guide column passes through the sliding hole, and the two ends of the third cylindrical spring 6-9 abut against the spring frame 6-10 and the spring pressing piece 6-12 respectively, a hemispherical groove is processed in the middle lower end face of the spring pressing piece 6-12, a hemispherical groove is processed in the upper end face of the lower part of the spring frame 6-10, the two hemispherical grooves are correspondingly arranged, the other end of the steel wire 3-13 has a spherical structure, and the two hemispherical grooves form a spherical cavity for clamping the spherical structure of the steel wire 3-13; after the envelope body and the lander 8 are separated, the mechanical arm 10 moves the envelope body to the Mars surface 11, the butt flange 6-8 is placed on the Mars surface 11, the envelope body bottom plate 7 moves relative to the butt flange 6-8 due to gravity, the lower part of the spring frame 6-10 and the middle part of the spring pressing piece 6-12 are separated, the spherical structure at the end of the steel wire 3-13 is released from the constraint, the lock sliding pin 3-10 moves upward under the action of the second cylindrical spring 3-11, and the release and separation between the envelope body side plate 4 and the envelope body top plate 1 are completed;

[0045] The hollow shaft 6-13 is slidingly arranged inside the spring pressing sheet 6-12, the inner wall of the spring pressing sheet 6-12 is processed with a baffle, the lower part of the hollow shaft 6-13 is threadedly connected with the upper end of the slotted titanium rod 6-20 through the baffle, and the upper part of the hollow shaft 6-13 is provided with the fourth cylindrical spring 6-14 between the baffle, the fourth cylindrical spring 6-14 is sleeved on the hollow shaft 6-13, and the two ends of the fourth cylindrical spring 6-14 are respectively tightly pressed against the hollow shaft 6-13 and the baffle.

[0046] Specific embodiment seven: in combination Figures 1-13 In this embodiment, the slotted titanium rod 6-20 is arranged in the part of the expander 6-6 and is processed with a notch, the notch on the slotted titanium rod 6-20 is a weak link of the slotted titanium rod 6-20 and is easily cut off under stress, so that the efficiency is high and the energy consumption is reduced.

[0047] Specific embodiment eight: in combination Figures 1-13 In this embodiment, the envelope top plate 1 is provided with an outwardly extending conical column, the upper end of the Mars aircraft 9 is provided with a groove, and the outwardly extending conical column of the envelope top plate 1 is correspondingly arranged with the groove; the Mars aircraft 9 and the envelope top plate 1 are constrained and positioned.

[0048] Specific embodiment nine: in combination Figures 1-13 In this embodiment, the Mars aircraft 9 includes a rotor arm shaft assembly 9-1, a shaft assembly 9-2, a rotor arm assembly 9-3, a landing leg 9-4 and a fuselage 9-5, the rotor arm assembly 9-3 and the landing leg 9-4 of the Mars aircraft 9 are connected with the fuselage 9-5 through the rotor arm shaft assembly 9-1 and the shaft assembly 9-2 respectively, and the rotor arm assembly 9-3 and the landing leg 9-4 are expanded under the action of torsion springs in the rotor arm shaft assembly 9-1 and the landing leg shaft assembly 9-2 during the expansion of the envelope side plate 4; the positioning assembly 2 includes a first ball head 2-1, a first ball socket 2-2 and a guide column 2-3, the lower end of the fuselage 9-5 of the Mars aircraft 9 is provided with the first ball head 2-1, the upper end of the support table 5 is provided with the first ball socket 2-2, the first ball head 2-1 and the first ball socket 2-2 are correspondingly arranged, the support table 5 is provided with a guide cylinder, the lower end of the fuselage 9-5 of the Mars aircraft 9 is provided with the guide column 2-3, and the guide column 2-3 is correspondingly arranged with the guide cylinder; the positioning assembly 2 can be relatively moved and is used for guiding in the initial stage of lifting the aircraft.

[0049] Specific embodiment ten: in combination Figures 1-13In order to illustrate the embodiment, the Mars surface take-off deployment device of the four-rotor Mars aircraft in the embodiment further comprises a positioning assembly 2, the positioning assembly 2 comprises a second ball head 2-4 and a second ball socket 2-5, the lower side of the envelope bottom plate 7 is provided with the second ball head 2-4, the upper side of the lander 8 is provided with the second ball socket 2-5, and the second ball head 2-4 and the second ball socket 2-5 are correspondingly arranged; the structure is stable, and the position can be adjusted and guided, and the structure is convenient to split.

[0050] The deployment process is as follows:

[0051] The expansion cutter 6-6 is powered on, heated and expanded, the slotted titanium rod 6-20 is cut off, the lower end of the slotted titanium rod 6-20 and the internal parts of the expansion cutter shell 6-7 move downward, the upper end of the slotted titanium rod 6-20 and the hollow shaft 6-13 move upward under the action of the fourth cylindrical spring 6-14 and the fifth cylindrical spring 6-18, the anti-escape cap 6-1 and the fixing frame 6-11 limit the positions of the parts respectively, and pollution to the environment is prevented, and thus the separation between the envelope and the lander 8 is completed; the mechanical arm 10 transfers the envelope to the Mars surface 11, the docking flange 6-8 moves upward under the gravity of the envelope and releases the constraint on the terminal spherical fixed end of the steel wire 3-13; the steel wire 3-13 and the lock slide pin 3-10 move upward under the action of the second cylindrical spring 3-11, the lock slide pin 3-10 releases the constraint between the envelope top plate 1 and the envelope side plate 4, the envelope side plate 4 rotates around the first side plate rotating shaft 3-1 under the action of the first torsional spring 3-2, when the envelope side plate 4 rotates by 90°, the first cylindrical spring 3-5 pushes out the two pin shafts 3-4 from the holes respectively, and the first lock frame 3-3 is locked, so that the envelope side plate 4 is prevented from rebounding, in the process of rotation of the envelope side plate 4, the rotor arm assembly 9-3 and the landing leg 9-4 are unfolded under the action of the torsional springs in the rotor arm shaft assembly 9-1 and the landing leg shaft assembly 9-2, the rotor is tested to rotate, and the blades are unfolded; after the test is completed, the mechanical arm 10 removes the envelope top plate 1, the rotor speed increases, and the Mars aircraft 9 starts to lift upward, in the initial stage of upward lifting of the Mars aircraft 9, the guide column 2-3 connected to the bottom end of the fuselage 9-5 moves upward along the through hole at the top end of the support table 5, before being separated, the guide column 2-3 plays a role in guiding the lifting of the Mars aircraft 9, and thus the vertical unfolding and the Mars surface take-off deployment of the Mars aircraft are completed.

[0052] It should be noted that, in the above embodiments, any non-contradictory technical solutions can be arranged and combined, and those skilled in the art can exhaust all possibilities according to the mathematical knowledge of arrangement and combination, so that the technical solutions after arrangement and combination are no longer explained one by one, but it should be understood that the technical solutions after arrangement and combination have been disclosed by the present application.

[0053] The above merely provides the preferred embodiments of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the principles and technical scope of the present application shall fall into the scope of the present application.

Claims

1. A Mars surface take-off deployment apparatus for a quadcopter Mars flyer, characterized by: The envelope top plate (1), the side plate locking assembly (3), the envelope side plate (4), the support table (5), the locking assembly (6), the envelope bottom plate (7) and the lander (8) are arranged on the lander (8), the middle part of the envelope bottom plate (7) is provided with the locking assembly (6) and the support table (5), the edge of the envelope bottom plate (7) is connected with the envelope side plate (4) through the side plate locking assembly (3), the side plate locking assembly (3) is connected with the locking assembly (6), the upper part of the support table (5) is provided with the Mars spacecraft (9), the upper part of the Mars spacecraft (9) is provided with the envelope top plate (1), the envelope side plate (4) cooperates with the envelope top plate (1), and the Mars spacecraft (9) is placed on the support table (5); The locking assembly (6) comprises a anti-drop cap (6-1), a anti-loose nut (6-2), a loading nut (6-3), a ball-shaped pad (6-4), a first heat insulation pad (6-5), a breakaway device (6-6), a breakaway device shell (6-7), a butt flange (6-8), a third cylindrical spring (6-9), a spring frame (6-10), a fixed frame (6-11), a spring pressing piece (6-12), a hollow shaft (6-13), a fourth cylindrical spring (6-14), a dustproof film (6-15), a second spring sleeve (6-16), a first spring sleeve (6-17), a fifth cylindrical spring (6-18), a second heat insulation pad (6-19) and a slotted titanium rod (6-20), the breakaway device shell (6-7) is connected with the lander (8), the upper end of the breakaway device shell (6-7) is connected with the second spring sleeve (6-16), the second spring sleeve (6-16) is located in the through hole of the lander (8), the first spring sleeve (6-17) is slidably connected with the second spring sleeve (6-16), the breakaway device shell (6-7) is sequentially provided, from top to bottom, with the second heat insulation pad (6-19), the breakaway device (6-6), the first heat insulation pad (6-5) and the ball-shaped pad (6-4), the slotted titanium rod (6-20) sequentially passes through the first spring sleeve (6-17), the upper end through hole of the breakaway device shell (6-7), the second heat insulation pad (6-19), the breakaway device (6-6), the first heat insulation pad (6-5) and the ball-shaped pad (6-4), the lower end of the slotted titanium rod (6-20) is sequentially connected with the loading nut (6-3) and the anti-loose nut (6-2) through threads, the lower end of the breakaway device shell (6-7) is connected with the anti-drop cap (6-1), the loading nut (6-3) and the anti-loose nut (6-2) are located in the anti-drop cap (6-1), the first spring sleeve (6-17) is provided with the fifth cylindrical spring (6-18), the fifth cylindrical spring (6-18) is sleeved on the slotted titanium rod (6-20), and the two ends of the fifth cylindrical spring (6-18) are respectively tightly pressed against the breakaway device shell (6-7) and the first spring sleeve (6-17). The fixed frame (6-11) is connected with the envelope bottom plate (7), the fixed frame (6-11) is connected with the spring frame (6-10), the spring frame (6-10) is slidably connected with the spring pressing piece (6-12), and the third cylindrical spring (6-9) is arranged between the spring frame (6-10) and the spring pressing piece (6-12), the third cylindrical spring (6-9) is in a compressed state, the spring pressing piece (6-12) presses the lower part of the spring frame (6-10), the spring pressing piece (6-12) clamps the other end of the steel rope (3-13) with the spring frame (6-10), the lower end of the spring pressing piece (6-12) passes through the envelope bottom plate (7) and is connected with the butt flange (6-8), the butt flange (6-8) and the envelope bottom plate (7) have a gap, and the dustproof film (6-15) is connected with the butt flange (6-8) and the envelope bottom plate (7); The hollow shaft (6-13) is slidably arranged in the spring pressing piece (6-12), the inner wall of the spring pressing piece (6-12) is processed with a baffle, the lower part of the hollow shaft (6-13) passes through the baffle and is connected with the upper end of the slotted groove titanium rod (6-20), and the fourth cylindrical spring (6-14) is arranged between the upper part of the hollow shaft (6-13) and the baffle, the fourth cylindrical spring (6-14) is sleeved on the hollow shaft (6-13), and the two ends of the fourth cylindrical spring (6-14) abut against the hollow shaft (6-13) and the baffle respectively.

2. The apparatus according to claim 1, wherein: The side plate locking assembly (3) comprises a rotating assembly, a tension adjusting assembly, a lock piece and a steel rope (3-13), the middle part of the steel rope (3-13) is provided with the tension adjusting assembly, one end of the steel rope (3-13) is provided with the lock piece, and the other end of the steel rope (3-13) is provided with the locking assembly (6), and the envelope bottom plate (7) is connected with the envelope side plate (4) through the rotating assembly.

3. The apparatus according to claim 2, wherein: The rotating assembly comprises a first side plate rotating shaft (3-1), a first torsional spring (3-2), a first lock frame (3-3), a pin shaft (3-4), a first cylindrical spring (3-5), a second lock frame (3-6), a steel rubber (3-7) and a second side plate rotating shaft (3-8), the first side plate rotating shaft (3-1) is connected with the envelope bottom plate (7), the first side plate rotating shaft (3-1) is rotatably connected with the lower end of the envelope side plate (4), the first torsional spring (3-2) is sleeved on the first side plate rotating shaft (3-1), and the two ends of the first torsional spring (3-2) abut against the envelope bottom plate (7) and the envelope side plate (4) respectively; The first lock frame (3-3) is connected with the envelope bottom plate (7), the steel rubber (3-7) is arranged on the first lock frame (3-3), the first lock frame (3-3) is connected with the second lock frame (3-6) through the second side plate rotating shaft (3-8), the first lock frame (3-3) is processed with an inner cavity, the first cylindrical spring (3-5) is arranged in the inner cavity of the first lock frame (3-3), the end part of the first cylindrical spring (3-5) is provided with the pin shaft (3-4), and the pin shaft (3-4) is matched with the positioning hole processed in the first lock frame (3-3).

4. The apparatus according to claim 3, wherein: The tension adjusting assembly comprises a first tensioning piece (3-15), a disc spring (3-16), a second tensioning piece (3-17) and a third tensioning piece (3-18), the inner cavity of the first tensioning piece (3-15) is slidably provided with the second tensioning piece (3-17), the inner wall of the first tensioning piece (3-15) is provided with threads, the third tensioning piece (3-18) is threadedly connected with the first tensioning piece (3-15), the disc spring (3-16) is arranged between the second tensioning piece (3-17) and the third tensioning piece (3-18), one end of the second tensioning piece (3-17) extends through the third tensioning piece (3-18), and the first tensioning piece (3-15), the second tensioning piece (3-17) and the steel rope (3-13) are connected.

5. The apparatus according to claim 4, wherein: The lock piece comprises a square sliding sleeve (3-9), a lock sliding pin (3-10), a second cylindrical spring (3-11), a round sliding sleeve (3-12) and a steel rope positioning column (3-14), the upper end of the envelope side plate (4) is sequentially provided with the square sliding sleeve (3-9) and the round sliding sleeve (3-12), the edge of the envelope top plate (1) is provided with a buckle, the upper and lower sides of the lock sliding pin (3-10) are slidably connected with the square sliding sleeve (3-9) and the round sliding sleeve (3-12) respectively, the middle part of the lock sliding pin (3-10) is matched with the envelope top plate (1), the lower end of the lock sliding pin (3-10) is connected with one end of the steel rope (3-13), the second cylindrical spring (3-11) is sleeved on the lower side of the lock sliding pin (3-10), and the two ends of the second cylindrical spring (3-11) abut against the middle part of the lock sliding pin (3-10) and the round sliding sleeve (3-12), and the steel rope (3-13) passes through the steel rope positioning column (3-14) fixed on the envelope side plate (4).

6. The apparatus according to claim 1, wherein: The slotted titanium rod (6-20) is arranged in the expander (6-6) and is provided with a notch.

7. The apparatus according to claim 1, wherein: The envelope top plate (1) is provided with an outwardly extending conical column, the upper end of the Mars spacecraft (9) is provided with a groove, and the outwardly extending conical column of the envelope top plate (1) is correspondingly arranged with the groove.

8. The apparatus according to claim 1, wherein: The positioning assembly (2) comprises a first ball head (2-1), a first ball socket (2-2) and a guide column (2-3), the lower end of the Mars spacecraft (9) is provided with the first ball head (2-1), the upper end of the support table (5) is provided with the first ball socket (2-2), the first ball head (2-1) is correspondingly arranged with the first ball socket (2-2), the support table (5) is provided with a guide cylinder, and the lower end of the Mars spacecraft (9) is provided with the guide column (2-3), and the guide column (2-3) is correspondingly arranged with the guide cylinder.

9. The apparatus according to claim 1, wherein: The positioning assembly (2) comprises a second ball head (2-4) and a second ball socket (2-5), the lower side of the envelope bottom plate (7) is provided with the second ball head (2-4), the upper side of the lander (8) is provided with the second ball socket (2-5), and the second ball head (2-4) is correspondingly arranged with the second ball socket (2-5).

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