CN209366451U - A kind of rocket unmanned plane integral system - Google Patents

Abstract

The utility model discloses a kind of rocket unmanned plane integral systems, belong to vehicle technology field.It includes rocket ontology, linked ejection device and unmanned plane；The rocket body interior is successively arranged nose cone cabin, loading cabin and enging cabin from top to bottom；The unmanned plane is multi-rotor unmanned aerial vehicle, and the unmanned plane is fixed in loading cabin by linked ejection device；The nose cone cabin can be opened to form ejection channel；The linked ejection device out of loading cabin for launching away unmanned plane.The utility model can break in tradition the rocket only combined thinking with fixed-wing unmanned plane, and in the case where not changing unmanned plane self structure, rocket is eliminated to the adverse effect of unmanned plane static stability, also it eliminates unmanned plane to adversely affect the normal transmission and flight course bring of rocket, so that rocket unmanned plane integral system whole efficiency is higher, more stable；In addition, also having manipulation simple and high reliability.

Description

A kind of rocket unmanned plane integral system

Technical field

The utility model belongs to vehicle technology field, and more particularly, it relate to a kind of nobody machine integrated systems of rocket System.

Background technique

In recent years, with the fast development of field of aerospace technology, model rocket and multi-rotor unmanned aerial vehicle are respective Field is developed quite rapid, and unmanned plane even becomes a part in everybody life gradually.

Currently, the combination of rocket and unmanned plane is mainly warbird boosting fixed-wing unmanned plane, in transmitter section due to adding Booster rocket is entered, unmanned plane is caused to move with booster rocket assembly center of gravity, unmanned plane stress changes, and leads to it Static stability reduces.Meanwhile the acceleration of unmanned plane is larger, velocity variations are violent, and unmanned plane has very strong in emission process It is non-linear, and there may be installation error and disturbing influences, in addition can normal transmission to rocket and flight course bring not Benefit influences, and system model shows a series of problem such as uncertainty.Such as: China Patent No. 201711309677.3, Publication date is the Chinese patent document on 4 years 20 dates in 2018, discloses a kind of unmanned plane two point form rocket assist transmitting dress It sets and its method comprising for installing the thrust frame of booster rocket and the pedestal being installed on body and hook ring；It is described Thrust frame on be fixedly installed two distance rods and one hook；There are two ball-and-sockets and one to hang for setting on the pedestal Hanging point, the hook are mounted on hook ring, the top difference support top of two distance rods in ball-and-socket, hook, distance rod and Body forms A-frame structure, and distance rod transmits rocket assist power to body by two ball-and-sockets；The sling point is used for Connect the hoist cable for determining thrust line；The attachment base for connecting thrust line measurement device is additionally provided on thrust frame.For another example: China Patent No. 201810216067.7, publication date are the Chinese patent document on July 17th, 2018, disclose a kind of small-sized folding Stacked fixed-wing unmanned plane comprising wing-folding device, body, gravity center adjusting mechanism, power section, rocket assist and separation Mechanism can greatly reduce the lateral dimension of fuselage by the radial folding of wing, empennage and vertical fin, so as to be stored in circle In cylindricality launching tube, facilitate storage and transport, takes out assembling without artificial when transmitting, then body is released and sent out by booster rocket point Shooting cylinder.

System of the rocket in conjunction with fixed-wing unmanned plane have the defects that it is above-mentioned, even if by changing itself structure energy It is enough to overcome drawbacks described above to a certain extent, but the aeroperformance of fixed-wing unmanned plane can also be adversely affected, in turn The structural complexity of fixed-wing unmanned plane is increased, and installation accuracy requirement is very high, also increases production installation cost.And it is fiery There is presently no appearance for system of the arrow in conjunction with multi-rotor unmanned aerial vehicle, compared to system of the rocket in conjunction with fixed-wing unmanned plane With many advantages, and multi-rotor unmanned aerial vehicle can complete the task that many fixed-wing unmanned planes cannot be completed, and have The advantages of manipulating simple and high reliablity.

Summary of the invention

1. to solve the problems, such as

Drone center of unmanned aerial vehicle is caused to move for unmanned plane in the prior art and booster rocket assembly, stress becomes Change, and then leads to the reduction of its static stability；The acceleration of unmanned plane is larger, and velocity variations are violent, and unmanned plane has in emission process Have it is very strong non-linear, in addition existing installation error and disturbing influence, can the normal transmission to rocket brought with flight course Adverse effect, and then whole system is caused to there is a problem of very big uncertainty, the utility model provide a kind of rocket nobody Machine integrated system also eliminates unmanned plane to the normal of model rocket in the case where not changing unmanned plane self structure Transmitting is influenced with flight course bring；In addition, also having manipulation simple and high reliability.

2. technical solution

To solve the above-mentioned problems, technical solution used by the utility model is as follows:

A kind of rocket unmanned plane integral system, including rocket ontology, linked ejection device and unmanned plane；The rocket Body interior is successively arranged nose cone cabin, loading cabin and enging cabin from top to bottom；The unmanned plane is multi-rotor unmanned aerial vehicle, institute The unmanned plane stated is fixed in loading cabin by linked ejection device；The nose cone cabin can be opened to form ejection channel； The linked ejection device out of loading cabin for launching away unmanned plane.

It further, further include steering engine；The rocket ontology includes cylinder and nose cone section；The loading cabin and start Cabin is located in cylinder；The nose cone freight space is in nose cone section；The steering engine is located in nose cone cabin；The nose cone section packet Include left nose cone section and right nose cone section；The left nose cone section and right nose cone Duan Jun pass through the hinge and cylinder that respective bottom is arranged in Hingedly；It is equipped with torque spring in the hinge, at no external force constraint left nose cone section and right nose cone section can automatically open； The steering engine is closed and separates for controlling left nose cone section and right nose cone section；Wherein, steering engine is fixed on left nose cone section or right nose It bores in section.

Further, the linked ejection device includes support base, ejection-spring and retaining mechanism；The support base For circular platform and it is horizontally fixed in loading cabin；The ejection-spring be it is multiple and uniformly distributed on support base, it is described Retaining mechanism be located at the center of support base；The retaining mechanism is for locking unmanned plane；The nose cone cabin, which will be opened, to drive So that retaining mechanism is failed, and then unmanned aerial vehicle ejecting is gone out by ejection-spring.

Further, the bottom centre of the unmanned plane is equipped with locking bracket and is equipped with ejection around locking bracket Bracket；The locking bracket is a column structure, and side is equipped with jack；The retaining mechanism is a circular protrusions, and Inner vertical is equipped with lockhole；In the locking bracket insertion lockhole；The linked ejection device further includes bolt, locking bullet Spring and baffle；The baffle is fixed on support base and is located at position between retaining mechanism and left nose cone section or right nose cone section Place；One end of the bolt passes through in the side wall insertion jack of retaining mechanism, and the other end sequentially passes through locking spring and baffle It is connect afterwards by rope with the bottom that left nose bores section or right nose cone section；Wherein, locking spring drives in bolt insertion jack.

Further, the side of the bolt is equipped with annular protrusion；The locking spring is located at annular protrusion and gear Between plate, the locking spring is in compressive state；The locking spring is given bolt one by annular protrusion and is close to The power of jack.

Further, the linked ejection device further includes pulley；The pulley is fixed on support by pulley base On seat；Wherein, the collinear laying in the center of pulley, baffle and retaining mechanism three；One end of the rope is fixed with bolt, separately One end bypasses the bottom for boring section or right nose cone section with left nose after pulley and connect.

Further, the center of gravity of the rocket ontology, unmanned plane and linked ejection device is respectively positioned on same vertical line On.

Further, the tail portion of the rocket ontology is symmetrically installed with 3~5 empennages.

Further, parachute is installed in the nose cone cabin；The parachute and left nose cone section or right nose cone section Connection.

The application method of rocket unmanned plane integral system described in more than one, the steps include:

A. under the action of the engine that rocket ontology is arranged inside its enging cabin, flight to predetermined position, unmanned plane Driving motor is unlocked, driving motor is made to be in idling mode；

B. before flying speed is kept to zero, steering engine controls left nose cone section and the separation of right nose cone section, pulls rope, drives slotting Pin leaves jack；

C. left nose cone section or right nose cone section rotate outward angle be 45 °~75 ° when, bolt leaves jack completely, locking Failure mechanisms, ejection-spring go out unmanned aerial vehicle ejecting；

D. parachute is opened, and rocket ontology slowly falls to ground.

3. beneficial effect

Compared with the prior art, the utility model has the following beneficial effects:

(1) a kind of rocket unmanned plane integral system of the utility model utilizes small volume and less weight under the premise of rocket assist Multi-rotor unmanned aerial vehicle substitute fixed-wing unmanned plane, and more rotors are put into the center in rocket body inner horizontal direction, with The prior art is compared, and has broken in tradition the rocket only combined thinking with fixed-wing unmanned plane, and do not changing unmanned plane In the case where self structure, the adverse effect of the right unmanned plane static stability of rocket is eliminated, meanwhile, unmanned plane is eliminated to fire The normal transmission of arrow and flight course bring adversely affect, so that rocket unmanned plane integral system whole efficiency is higher, more For stabilization；In addition, also having manipulation simple and high reliability；

(2) a kind of rocket unmanned plane integral system of the utility model, can be rapidly reached certain altitude in a short time Pop up unmanned plane with after distance, realize scout, exploration, the tasks such as monitoring, greatly shorten from taking off and fly to required position Time quickly arrives at the destination and executes inter-related task；It can also be used for the functions such as the combination performance of model rocket and unmanned plane, Take full advantage of multi-rotor unmanned aerial vehicle small volume and less weight, it is reliable and stable, manipulation is simple, duties are high the advantages that, can greatly reduce Unmanned plane influences rocket normal transmission and flight bring；

(3) a kind of rocket unmanned plane integral system of the utility model, left nose are bored section and are separated with right nose cone section opening, can draw Running rope rope, drives bolt to leave jack, further such that retaining mechanism fails to the limit function of locking bracket, in ejection-spring Under the action of, unmanned aerial vehicle ejecting is gone out, in addition original movement initial velocity, can easily realize the separation of rocket body and unmanned plane, The tasks such as scouting, exploration, monitoring are fast implemented by wireless remotecontrol, that is, controllable unmanned plane again；

(4) a kind of rocket unmanned plane integral system of the utility model, after rocket body is separated with unmanned plane, parachute is by sky The resistance of gas can voluntarily be unfolded so that rocket body slowly falls to ground, and rocket body structure is prevented to be damaged, and is conducive to recycling and goes forward side by side Row is recycled, and is good for the environment, also reduces production cost.

Detailed description of the invention

Fig. 1 is the structural schematic diagram one of rocket unmanned plane integral system of the present invention；

Fig. 2 is the enlarged drawing of A in Fig. 1 of the present invention；

Fig. 3 is the structural schematic diagram two of rocket unmanned plane integral system of the present invention；

Fig. 4 is the internal structure chart of Fig. 2 in the present invention；

Fig. 5 is the enlarged drawing of B in Fig. 4 of the present invention；

Fig. 6 is the structural schematic diagram of linked ejection device in the present invention；

Fig. 7 is the internal structure chart of linked ejection device in the present invention；

Fig. 8 is the structural schematic diagram of unmanned plane in the present invention；

Fig. 9 is the structural assembly diagram of unmanned plane and linked ejection device in the present invention；

Figure 10 is the internal structure chart of unmanned plane and linked ejection device in the present invention.

In figure: 1, rocket ontology；101, cylinder；102, left nose bores section；1021, left lug boss；103, right nose cone section；104, Empennage；105, nose cone cabin；106, loading cabin；107, enging cabin；

2, steering engine；

3, linked ejection device；301, support base；302, ejection-spring；303, retaining mechanism；3031, lockhole；304, it inserts Pin；3041, annular protrusion；305, locking spring；306, baffle；307, rope；308, pulley；

4, parachute；

5, unmanned plane；501, locking bracket；502, shot support.

Specific embodiment

The utility model is further described below combined with specific embodiments below.

Embodiment 1

Shown in as shown in Figure 1, Figure 3 and Figure 4, a kind of rocket unmanned plane integral system, including rocket ontology 1, linked ejection dress 3 and unmanned plane 5 are set, are successively arranged nose cone cabin 105, loading cabin 106 and enging cabin 107, nothing inside rocket ontology 1 from top to bottom Man-machine 5 be multi-rotor unmanned aerial vehicle, and if drag cup passes through machine, unmanned plane 5 is fixed in loading cabin 106 by linked ejection device 3, It is reaching a certain height with after distance, nose cone cabin 105 is opened to form ejection channel, and linked ejection device 3 is used for unmanned plane 5 It is launched away out of loading cabin 106；It is vertical that the center of gravity of rocket ontology 1, unmanned plane 5 and linked ejection device 3 is respectively positioned on same On line.Rocket unmanned plane integral system in the present embodiment, after certain altitude and distance can be rapidly reached in a short time Pop up unmanned plane 5, realize scout, exploration, the tasks such as monitoring, greatly shorten from taking off and fly to the time of required position, i.e., Quickly arrives at the destination and execute inter-related task；It can also be used for the functions such as the combination performance of rocket ontology 1 and unmanned plane 5, sufficiently Be utilized multi-rotor unmanned aerial vehicle small volume and less weight, it is reliable and stable, manipulation is simple, duties are high the advantages that, nobody can be greatly reduced Machine 5 influences 1 normal transmission of rocket ontology and flight bring；Compared with prior art, rocket ontology 1 has been broken in tradition only Rocket ontology is eliminated and in the case where not changing 5 self structure of unmanned plane with the combined thinking of fixed-wing unmanned plane The adverse effect of 1 pair of 5 static stability of unmanned plane, meanwhile, unmanned plane 5 is eliminated to the normal transmission of rocket ontology 1 and is flown Journey bring adverse effect, so that rocket unmanned plane integral system whole efficiency is higher, more stable；In addition, also having behaviour Control simple and high reliability.

Specific above-mentioned structure, rocket ontology 1 include cylinder 101 and nose cone section, loading cabin 106 and enging cabin 107 In in cylinder 101；As shown in Fig. 2, further including steering engine 2, nose cone cabin 105 is located in nose cone section；Steering engine 2 is located in nose cone cabin 105, Nose cone section includes left nose cone section 102 and right nose cone section 103, and left nose bores section 102 and right nose cone section 103 by being arranged at respective bottom The hinge and cylinder 101 in portion are hinged, and torque spring is equipped in hinge, and left nose can be made to bore 102 He of section in no external force constraint Right nose cone section 103 automatically opens, and steering engine 2 is closed and separates for controlling left nose cone section 102 and right nose cone section 103；Wherein, left nose The junction of cone section 102 and right nose cone section 103 is equipped with connecting plate from top to bottom, and connecting plate is mutually adjacent to, and steering engine 2 is fixed on Left nose bores the left side of the bottom on the connecting plate of section 102, and steering engine 2 is equipped with shaft, and one end of shaft is mounted on inside steering engine 2, The other end stretches to the right side of the connecting plate in right nose cone section 103 and by the gag lever post of setting by the connection in right nose cone section 103 Plate is caught on, so that left nose cone section 102 and right nose cone section are mutually adjacent to, certainly, steering engine 2 can also be fixed on right nose cone section 103 The left side of bottom on connecting plate, steering engine 2 are equipped with shaft, and one end of shaft is mounted on inside steering engine 2, and the other end stretches to left nose It bores the right side of the connecting plate in section 102 and left nose is bored the connecting plate in section 102 and caught on by the gag lever post by being arranged, so that left nose Cone section 102 and right nose cone section are mutually adjacent to.Steering engine 2 can drive shaft to rotate, and gag lever post is driven to rotate up to the company of completely disengaging The view field of fishplate bar, left nose bore section 102 and right nose cone section 103 under the action of torque spring, are unfolded into bullet outward Penetrate channel；As long as by control steering engine 2 drive shaft rotation can be realized left nose bore the separation of section 102 and right nose cone section 103 with Closure control；There are many modes of control, can adjust duty ratio by the output of 51 single-chip simulation pwm signals to control Steering engine 2 drives shaft to rotate and then controls the separation and closure of left nose cone section 102 and right nose cone section 103 should be in model when flight Speed opens nose cone cabin 105 before being kept to zero after rocket launching, and the circuit control part of 51 single chip computer devices can be laid in In the bottom in rocket body loading cabin 106.

The tail portion of rocket ontology 1 is symmetrically installed with 3~5 empennages 104, the stabilization during adjustable rocket flight Property.Parachute 4 is installed in nose cone cabin 105, is separated by partition with 105 lower section space of nose cone cabin, parachute 4 may be mounted at Left nose is bored in section 102 or right nose cone section 103.In the present embodiment, the quantity of empennage 104 is 4, and left nose bores section 102 and right nose cone After 103 separation of section is opened to centainly, parachute 4 can be voluntarily unfolded by the resistance of air, be also beneficial to carry out rocket body ontology 1 Recycling.

Embodiment 2

With embodiment 1, except that: as shown in Figure 6 and Figure 7, linked ejection device 3 includes support base 301, ejection bullet Spring 302 and retaining mechanism 303, support base 301 are circular platform and are horizontally fixed in loading cabin 106 that ejection-spring 302 is more A and uniformly distributed on support base 301, retaining mechanism 303 is located at the center of support base 301, and retaining mechanism 303 is for locking Unmanned plane 5, nose cone cabin 105, which is opened, will drive retaining mechanism 303 to fail, and then be ejected unmanned plane 5 by ejection-spring 302 It goes.

Specific above-mentioned structure, as shown in figure 8, unmanned plane 5 by rack, driving motor, propeller, image delivering system with Power supply composition, the bottom of the frame center of unmanned plane 5 are equipped with locking bracket 501 and are equipped with ejection branch around locking bracket 501 Frame 502, the quantity and ejection-spring 302 of shot support 502 correspond, and locking bracket 501 is a column structure, and side is set There is jack, as shown in Fig. 5, Fig. 9 and Figure 10, retaining mechanism 303 is a circular protrusions, and inner vertical is equipped with lockhole 3031, lock Locking bracket 501 is inserted into lockhole 3031, and linked ejection device 3 further includes bolt 304, locking spring 305 and baffle 306, baffle 306 are fixed on support base 301 and are located between retaining mechanism 303 and left nose cone section 102 or right nose cone section 103 at position, insert One end of pin 304 passes through in the side wall insertion jack of retaining mechanism 303, and the other end sequentially passes through locking spring 305 and baffle 306 It is connect afterwards by rope 307 with the bottom that left nose bores section 102 or right nose cone section 103；Wherein, locking spring 305 drives bolt 304 It is inserted into jack.In the present embodiment, shot support 502 compress ejection-spring 302 make its to after energy storage state by pin 304 by nothing Man-machine 5 lock, and when rocket unmanned plane integral system reaches predetermined altitude and position, speed is kept to zero before for nose cone cabin 105 open, and left nose cone section 102 and right nose cone section 103 opening separates, and pulling rope 307 drives bolt 304 to leave jack, into making It obtains retaining mechanism 303 to fail to the limit function of locking bracket 501, under the action of ejection-spring 302, unmanned plane 5 is launched It goes out, in addition original movement initial velocity, can easily realize the separation of rocket body Yu unmanned plane 5, then pass through wireless remotecontrol Manipulation unmanned plane 5 fast implements the tasks such as scouting, exploration, monitoring.

The laying mode that locking spring 305 drives bolt 304 to be inserted into jack can be various ways, as: bolt 304 Side is equipped with annular protrusion 3041, and between annular protrusion 3041 and baffle 306, locking spring 305 is in locking spring 305 Compressive state, locking spring 305 give bolt 304 1 power for being close to jack by annular protrusion 3041.

Linked ejection device 3 further includes pulley 308, and pulley 308 is fixed on support base 301 by pulley base；Wherein, sliding The collinear laying in center of wheel 308,303 three of baffle 306 and retaining mechanism, one end of rope 307 and bolt 304 are fixed, another End is around after pulley 308 and in the left lug boss 1021 of bottom inside setting of left nose cone section 102 or the bottom of right nose cone section 103 The right lug boss connection of side setting, left nose cone section 102 and the separation of right nose cone section 103 are used to form ejection channel, and left nose bores section 102 It is bigger with right nose cone section 103 separation angle, pull the shift length of rope 307 long-range, the traversing amount that bolt 304 occurs is more； And when in use, left nose cone section 102 and right nose cone section 103 separation angle needs reache a certain level and ejection channel are expired Foot uses, and the ejection process to unmanned plane 5 is avoided to have an adverse effect, and the separation angle of the two can not be excessive certainly, because Parachute 4 can be voluntarily unfolded by the resistance of air, and parachute 4 makes the bullet of unmanned plane 5 once ejection channel can be locked by opening Penetrating work can not be successfully progress, and discovery is largely tested by inventor, if by left nose bore section 102 and right nose cone section 103 to When outside rotates angle control between 45 °~75 °, starts the ejection work of unmanned plane 5, that is, can avoid above-mentioned two situations Occur, in the present embodiment, it is 60 ° that left nose cone section 102 and right nose cone section 103 rotates angle control outward, left nose cone 102 He of section Right nose cone section 103 rotates angle outward can detect that the setting of pulley 308 being capable of tricing line by the way that angular transducer is arranged What left nose cone section 102 and right nose cone section 103 when the position of rope 307 is conducive to adjust in turn the ejection of unmanned plane 5 rotated outward Angle, furthermore, it is also possible to which the left nose adjusted when unmanned plane 5 launches by the height of projection of left lug boss 1021 and right lug boss is bored The angle that section 102 and right nose cone section 103 rotate outward.

Embodiment 3

A kind of application method of rocket unmanned plane integral system, using the rocket unmanned plane one in embodiment 2 Body system, here are that it is specifically described.

A kind of application method of rocket unmanned plane integral system, the steps include:

A. rocket ontology 1 blasts off, and under the action of the engine being arranged inside enging cabin 107, flight is to predetermined Position adjusts the flight attitude of rocket ontology 1, so that the direction of flight is straight up；

B. unmanned plane 5 unlocks driving motor, and driving motor is made to be in idling mode；

C. before flying speed is kept to zero, steering engine 2 controls left nose cone section 102 and the separation of right nose cone section 103, pulls rope 307, drive bolt 304 to leave jack；

D. left nose cone section 102 or right nose cone section 103 rotate outward angle be 45 °~75 ° when, bolt 304 leaves completely Jack, retaining mechanism 303 fail, and ejection-spring 302 launches away unmanned plane 5；

E. unmanned plane 5 starts offline mode, manipulates unmanned plane 5 by wireless remotecontrol, fast implements scouting, exploration, prison The tasks such as survey；

F. parachute 4 is opened, and rocket ontology 1 slowly falls to ground.

It can be seen that the application method of the rocket unmanned plane integral system, it is only and solid rocket ontology 1 in tradition has been broken Determine the combined thinking of wing unmanned plane, and in the case where not changing 5 self structure of unmanned plane, it is right to eliminate rocket ontology 1 The adverse effect of 5 static stability of unmanned plane, meanwhile, unmanned plane 5 is eliminated to the normal transmission and flight course band of rocket ontology 1 The adverse effect come, so that rocket unmanned plane integral system whole efficiency is higher, more stable；In addition, also having manipulation letter List and high reliability.

Example described in the utility model is only that preferred embodiments of the present invention are described, not to this reality It is defined with novel conception and scope, under the premise of not departing from the design concept of the utility model, this field engineering technology people The various changes and improvements that member makes the technical solution of the utility model, should all fall into the protection scope of the utility model.

Claims (10)

1. a kind of rocket unmanned plane integral system, including rocket ontology (1)；The rocket ontology (1) is internal from top to bottom It is successively arranged nose cone cabin (105), loading cabin (106) and enging cabin (107)；It is characterized by also including linked ejection devices (3) and unmanned plane (5), the center of gravity of the rocket ontology (1), unmanned plane (5) and linked ejection device (3) are respectively positioned on same On vertical line；The unmanned plane (5) is multi-rotor unmanned aerial vehicle, and the unmanned plane (5) is fixed by linked ejection device (3) In loading cabin (106)；The nose cone cabin (105) can be opened to form ejection channel；The linked ejection device (3) For unmanned plane (5) to be launched away out of loading cabin (106)；Parachute (4) are installed in the nose cone cabin (105).

2. a kind of rocket unmanned plane integral system according to claim 1, it is characterised in that: further include steering engine (2)；Institute The rocket ontology (1) stated includes cylinder (101) and nose cone section；The loading cabin (106) and enging cabin (107) is located at cylinder (101) in；The nose cone cabin (105) is located in nose cone section；The steering engine (2) is located in nose cone cabin (105)；The nose Cone section includes left nose cone section (102) and right nose cone section (103)；Left nose cone section (102) and right nose cone section (103) pass through Hinge and cylinder (101) that respective bottom is arranged in are hinged；Torque spring is equipped in the hinge, in no external force constraint Left nose cone section (102) and right nose cone section (103) can be made to automatically open；The steering engine (2) is fixed on left nose cone section (102) or right In nose cone section (103), steering engine (2) is closed and separates for controlling left nose cone section (102) and right nose cone section (103).

3. a kind of rocket unmanned plane integral system according to claim 2, it is characterised in that: the linked ejection dress Setting (3) includes support base (301), ejection-spring (302) and retaining mechanism (303)；The support base (301) is circular platform And it is horizontally fixed in loading cabin (106)；The ejection-spring (302) be it is multiple and uniformly distributed on support base (301), The retaining mechanism (303) is located at the center of support base (301)；The retaining mechanism (303) is for locking unmanned plane (5)；The nose cone cabin (105), which is opened, will drive retaining mechanism (303) to fail, so by ejection-spring (302) by nobody Machine (5) launches away.

4. a kind of rocket unmanned plane integral system according to claim 3, it is characterised in that: the unmanned plane (5) Bottom centre be equipped with locking bracket (501) and be equipped with shot support (502) around locking bracket (501)；The lock Locking bracket (501) is a column structure, and side is equipped with jack；The retaining mechanism (303) is a circular protrusions, and internal It is equipped with lockhole (3031) vertically；In locking bracket (501) insertion lockhole (3031)；The linked ejection device (3) It further include bolt (304), locking spring (305) and baffle (306)；The baffle (306) be fixed on support base (301) and Between retaining mechanism (303) and left nose cone section (102) or right nose cone section (103) at position；The one of the bolt (304) It holds in the side wall insertion jack of retaining mechanism (303), after the other end sequentially passes through locking spring (305) and baffle (306) It is connect by rope (307) with the bottom of left nose cone section (102) or right nose cone section (103)；Wherein, locking spring (305) drives Bolt (304) is inserted into jack.

5. a kind of rocket unmanned plane integral system according to claim 4, it is characterised in that: the bolt (304) Side be equipped with annular protrusion (3041)；The locking spring (305) be located at annular protrusion (3041) and baffle (306) it Between, the locking spring (305) is in compressive state；The locking spring (305) is given by annular protrusion (3041) Bolt (304) one are close to the power of jack.

6. a kind of rocket unmanned plane integral system according to claim 5, it is characterised in that: the linked ejection dress Setting (3) further includes pulley (308)；The pulley (308) is fixed on support base (301) by pulley base；The rope (307) one end and bolt (304) is fixed, and the other end bores section (102) or right nose cone section with left nose afterwards around pulley (308) (103) bottom connection.

7. a kind of rocket unmanned plane integral system according to claim 6, it is characterised in that: pulley (308), baffle (306) and the collinear laying in center of retaining mechanism (303) three.

8. a kind of rocket unmanned plane integral system described according to claim 1~any one of 6, it is characterised in that: institute The tail portion for the rocket ontology (1) stated is symmetrically installed with 3~5 empennages (104).

9. a kind of rocket unmanned plane integral system according to claim 8, it is characterised in that: the empennage (104) Quantity be 4.

10. a kind of rocket unmanned plane integral system described according to claim 1~any one of 6, it is characterised in that: institute The parachute (4) stated is connect with left nose cone section (102) or right nose cone section (103).